diff --git a/GameData/RealismOverhaul/Engine_Configs/18KS7800_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/18KS7800_Config.cfg index 0a57c41d32..838973515b 100644 --- a/GameData/RealismOverhaul/Engine_Configs/18KS7800_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/18KS7800_Config.cfg @@ -10,7 +10,7 @@ // Dry Mass: 27.21 Kg // Thrust (SL): ??? kN // Thrust (Vac): 34.09 kN -// ISP: ??? SL / 238.8 Vac +// ISP: 200? SL / 238.8 Vac // Burn Time: 1.8 // Chamber Pressure: 6.89 MPa // Propellant: NGNC diff --git a/GameData/RealismOverhaul/Engine_Configs/25KS18000_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/25KS18000_Config.cfg index 5e0f22b954..9f206f1c77 100644 --- a/GameData/RealismOverhaul/Engine_Configs/25KS18000_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/25KS18000_Config.cfg @@ -10,7 +10,7 @@ // Dry Mass: 117.9 Kg // Thrust (SL): 82.7 kN // Thrust (Vac): ??? kN -// ISP: 178 SL / ??? Vac +// ISP: 178 SL / 198.8? Vac // Burn Time: 2.5 // Chamber Pressure: 9.24 MPa // Propellant: NGNC diff --git a/GameData/RealismOverhaul/Engine_Configs/A-4_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/A-4_Config.cfg index 7eba013db8..649ed6ad24 100644 --- a/GameData/RealismOverhaul/Engine_Configs/A-4_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/A-4_Config.cfg @@ -27,7 +27,7 @@ // Thrust (Vac): 288.68 kN // ISP: 220 SL / 255 Vac // Burn Time: 115 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 1.7? MPa estimated with RPA // Propellant: LOX / Hydyne // Prop Ratio: 1.3253, same as A-6H? // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/AJ10_Early_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/AJ10_Early_Config.cfg index 7540184854..42158bdc3f 100644 --- a/GameData/RealismOverhaul/Engine_Configs/AJ10_Early_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/AJ10_Early_Config.cfg @@ -9,7 +9,7 @@ // // Dry Mass: 84 Kg // Thrust (SL): ??? kN -// Thrust (Vac): 35.585 kN +// Thrust (Vac): 33.8 kN // ISP: 122 SL / 271 Vac SL calculated with RPA // Burn Time: 115 // Chamber Pressure: 1.4 MPa diff --git a/GameData/RealismOverhaul/Engine_Configs/AJ260FL_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/AJ260FL_Config.cfg index 25fc4760de..1fe5da3e12 100644 --- a/GameData/RealismOverhaul/Engine_Configs/AJ260FL_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/AJ260FL_Config.cfg @@ -1,29 +1,41 @@ +// ================================================== // AJ-260 FL -// Bluedog_DB // // Manufacturer: Aerojet +// // ================================================================================= // AJ-260 FL -// 30.48 x 6.63448 m + // Dry Mass: 156,126 kg -// Thrust: 35,391 kN Vac +// Thrust (SL): ??? kN +// Thrust (Vac): 35,391 kN // ISP: 238 SL / 263 Vac // Web Burn Time: 114 s // Total Burn Time: 130 s +// Chamber Pressure: 4.15 MPa // Propellant: PBAN -// Propellant Weight: 1,492,229 kg -// Nozzle Diameter: 181 in -// Nozzle Expansion Ratio: 3.8:1 -// Nozzle Exit Area: +// Throttle: N/A +// Nozzle Ratio: 3.8:1 +// Ignitions: 1 // ================================================================================= -// SOURCES +// Sources: + // #1: NASA CR-72127 - 260-in. Diameter Motor Deasibility Demonstration Program: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19670005578.pdf // #2: NASA TM X-1906 - Thrust Vector Control Requirements for Launch Vehicles using a 260-inch Solid Rocket First Stage (1969): https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19700003019.pdf // #3: Test of 260-Inch Diameter Motor SL-3: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19680025253.pdf -// -// ================================================================================= +// Used by: + +// * BDB +// * ROEngines + +// Notes: + +// 30.48 x 6.63448 m +// Propellant Weight: 1,492,229 kg +// Nozzle Diameter: 181 in +// ================================================== @PART[*]:HAS[#engineType[AJ260FL]]:FOR[RealismOverhaulEngines] { %title = #roAJ260FLTitle //AJ-260 FL diff --git a/GameData/RealismOverhaul/Engine_Configs/AJ260SL_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/AJ260SL_Config.cfg index ee6b06ec56..6c58c457c1 100644 --- a/GameData/RealismOverhaul/Engine_Configs/AJ260SL_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/AJ260SL_Config.cfg @@ -1,38 +1,57 @@ +// ================================================== // AJ-260 SL -// Bluedog_DB // // Manufacturer: Aerojet +// // ================================================================================= // AJ-260 SL-1/2 (Short Length) -// 80 ft, 9 in x 261.2 in = 21.6126 x 6.63448 m + // Dry Mass: 181,935 lb = 82,524.26 kg // Liquid Injection Thrust Vector = 6650 kg added // Total Dry Mass: 89,174.26 kg -// Thrust: 3,567,000 lbf = 15,866.8 kN -// Total Impulse: 371,900,000 lb s +// Thrust (SL): 3,567,000 lbf = 15,866.8 kN +// Thrust (Vac): ??? kN // Web Burn Time: 114 s // Total Burn Time: 130 s -// Chamber Pressure: 602 psia (max) +// Chamber Pressure: 4.15 MPa (max) // Propellant: PBAN -// Propellant Weight: 1,676,366 lb = 760,386 kg -// Nozzle Diameter: 181 in +// Throttle: N/A // Nozzle Expansion Ratio: 3.8:1 -// Nozzle Exit Area: +// Ignitions: 1 // ================================================================================= // AJ-260 SL-3 -// Thrust: 5,370,000 lbf = 23,886.941 kN + +// Dry Mass: 181,935 lb = 82,524.26 kg +// Liquid Injection Thrust Vector = 6650 kg added +// Total Dry Mass: 89,174.26 kg +// Thrust (SL): 5,370,000 lbf = 23,886.941 kN +// Thrust (Vac): ??? kN // Web Burn Time: 75.2 s -// Total Burn Time: +// Total Burn Time: ??? +// Chamber Pressure: 4.14 MPa (max) +// Propellant: PBAN +// Throttle: N/A // Nozzle Area Ratio: 3.78 +// Ignitions: 1 // ================================================================================= -// -// SOURCES + +// Sources: + // #1: NASA CR-72127 - 260-in. Diameter Motor Deasibility Demonstration Program: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19670005578.pdf // #2: NASA TM X-1906 - Thrust Vector Control Requirements for Launch Vehicles using a 260-inch Solid Rocket First Stage (1969): https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19700003019.pdf // #3: Test of 260-Inch Diameter Motor SL-3: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19680025253.pdf -// -// ================================================================================= +// Used by: + +// * BDB +// * ROEngines + +// Notes: + +// 80 ft, 9 in x 261.2 in = 21.6126 x 6.63448 m +// Propellant Weight: 1,676,366 lb = 760,386 kg +// Nozzle Diameter: 181 in +// ================================================== @PART[*]:HAS[#engineType[AJ260SL]]:FOR[RealismOverhaulEngines] { %title = #roAJ260SLTitle //AJ-260 SL diff --git a/GameData/RealismOverhaul/Engine_Configs/AR1_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/AR1_Config.cfg index ef5f14cc81..66c00dd6b0 100644 --- a/GameData/RealismOverhaul/Engine_Configs/AR1_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/AR1_Config.cfg @@ -12,13 +12,11 @@ // Thrust (Vac): 2487 kN // ISP: 305 SL / 337 Vac // Burn Time: 450 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 26.66 MPa same as RD-180??? // Propellant: LOX / RP-1 -// Prop Ratio: 2.72 from the RD-180??? -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? +// Prop Ratio: 2.72 same as RD-180??? // Throttle: 100% to 50% -// Nozzle Ratio: ??? +// Nozzle Ratio: 36.87 same as RD-180??? // Ignitions: 1 // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/Aestus_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Aestus_Config.cfg index 76c9a9157d..e455ef18e2 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Aestus_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Aestus_Config.cfg @@ -12,7 +12,7 @@ // Thrust (Vac): 27.8 kN // ISP: 113 SL / 306 Vac // Burn Time: 1110 -// Chamber Pressure: 1.1 +// Chamber Pressure: 1.1 MPa // Propellant: MON3 / MMH designed in the 90s, probably MON3 // Prop Ratio: 1.9 // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/Agena_XLR81_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Agena_XLR81_Config.cfg index 59c8e8c2cf..ae510e5f69 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Agena_XLR81_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Agena_XLR81_Config.cfg @@ -7,7 +7,7 @@ // Model 117 // B-58 Hustler rocket pod // -// Dry Mass: 127 Kg +// Dry Mass: 114.3 Kg a little lighter, because no Gimbal // Thrust (SL): ??? kN // Thrust (Vac): 67 kN // ISP: 207 SL / 265.5 Vac SL calculated with RPA @@ -247,6 +247,7 @@ minThrust = 67 heatProduction = 100 gimbalRange = 0 + massMult = 0.9 PROPELLANT { name = Kerosene diff --git a/GameData/RealismOverhaul/Engine_Configs/Algol_III_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Algol_III_Config.cfg index d6090b5078..6e95e3e497 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Algol_III_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Algol_III_Config.cfg @@ -4,7 +4,7 @@ // Manufacturer: Aerojet // // ================================================================================= -// Algol III +// Algol IIIA // Scout // // Dry Mass: 1391.121 kg @@ -12,7 +12,7 @@ // Thrust (Vac): 530.25896 kN // ISP: 238 SL / 260.289 Vac // Burn Time: 70 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 6.69 MPa // Propellant: PBAN // Prop Ratio: N/A // Throttle: N/A @@ -23,6 +23,7 @@ // Sources: // NASA CR-165950 Scout Launch Vehicle Final Report.PDF +// https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19770010201.pdf // Used by: diff --git a/GameData/RealismOverhaul/Engine_Configs/AltairIII_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/AltairIII_Config.cfg index 1533696810..2d3cda8d92 100644 --- a/GameData/RealismOverhaul/Engine_Configs/AltairIII_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/AltairIII_Config.cfg @@ -1,25 +1,39 @@ -// =============================================================== -// -// Altair III (FW4S) SRM -// Squad, Bluedog_DB +// ================================================== +// Altair III (FW4S) // // Manufacturer: United Aircraft -// Dimensions: 1.484122 x 0.508 m -// First Launch: 1965 -// -// Dry Mass: 23.16585 kg -// Average Thrust: 25.227 kN -// ISP: 284.5 s -// Burn Time: 31.5 s -// Propellant Mass: 274.4232 kg // +// ================================================================================= +// Altair III +// FW-4S +// +// Dry Mass: 23.16585 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 25.227 kN +// ISP: ??? SL / 284.5 Vac +// Burn Time: 31.5 +// Chamber Pressure: 5.92 MPa +// Propellant: CTPB +// Prop Ratio: N/A +// Throttle: N/A +// Nozzle Ratio: ??? +// Ignitions: 1 +// ================================================================================= + +// Sources: + // Source: NASA CR-145136 Scout Nozzle Data Book: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19770010201.pdf // Source 1: NASA CR-165950 Scout Launch Vehicle Final Report.PDF) // Source 2: Performance of a UTC FW-4S Solid-Propellant Rocket Motor // https://apps.dtic.mil/dtic/tr/fulltext/u2/a002149.pdf -// -// =============================================================== +// Used by: + +// Notes: + +// Dimensions: 1.484122 x 0.508 m +// Propellant Mass: 274.4232 kg +// =============================================================== @PART[*]:HAS[#engineType[Altair-III]]:FOR[RealismOverhaulEngines] { @title = #roAltair-IIITitle //Altair III FW-4S diff --git a/GameData/RealismOverhaul/Engine_Configs/Altair_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Altair_Config.cfg index 3cc0135daf..d989148011 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Altair_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Altair_Config.cfg @@ -1,6 +1,34 @@ -//Altair (X-248) -//Squad +// ================================================== +// Altair I // +// Manufacturer: Allegany Ballistics Laboratory +// +// ================================================================================= +// Altair I +// X-248 +// +// Dry Mass: 76.74777 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 16.35 kN +// ISP: ??? SL / 255.04 Vac +// Burn Time: 38.1 +// Chamber Pressure: 1.49 MPa +// Propellant: PBAA +// Prop Ratio: N/A +// Throttle: N/A +// Nozzle Ratio: 25.8 +// Ignitions: 1 +// ================================================================================= + +// Sources: + +// NASA CR-165950 Scout Launch Vehicle Final Report.PDF +// The Vanguard Satellite Launching Vehicle: An Engineering Summary.PDF (1960) +// https://i0.wp.com/www.drewexmachina.com/wp-content/uploads/2017/12/ABL_3rd_stage_motor.jpg?ssl=1 + +// Used by: + +// Notes: // // 1974072500-The-Vanguard-Satellite-Launching-Vehicle-an-Engineering-Summary.pdf // dimensions p.63 & p.65 @@ -15,27 +43,8 @@ // 50 + 420 lb -- 23 + 190 kg 109.1 l // 42 + 463 lb -- 19 + 210 kg 120.65 l // -// =============================================================== -// -// Altair (X-248) SRM -// Squad, Bluedog_DB -// -// Manufacturer: Allegany Ballistics Laboratory -// Dimensions: 1.47828 x 0.4572 m -// First Launch: Vanguard TV-4BU (1959) -// -// Dry Mass: 22.49816 kg -// Average Thrust: 13.34466 kN -// ISP: 255.04 s -// Burn Time: 39 s // Propellant Mass: 206.2029 kg -// -// Source 1: The Vanguard Satellite Launching Vehicle: An Engineering Summary.PDF (1960) -// Source 2: https://i0.wp.com/www.drewexmachina.com/wp-content/uploads/2017/12/ABL_3rd_stage_motor.jpg?ssl=1 -// // =============================================================== - - @PART[*]:HAS[#engineType[Altair]]:FOR[RealismOverhaulEngines] { %title = #roAltairTitle //Altair X-248 diff --git a/GameData/RealismOverhaul/Engine_Configs/Antares_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Antares_Config.cfg index 361e395968..42665c1035 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Antares_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Antares_Config.cfg @@ -12,11 +12,11 @@ // Thrust (Vac): 62.27508 kN // ISP: ??? SL / 256 Vac // Burn Time: 38.1 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 2.03 MPa // Propellant: PBAA // Prop Ratio: N/A // Throttle: N/A -// Nozzle Ratio: 27 +// Nozzle Ratio: 25.15 // Ignitions: 1 // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/Antares_II_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Antares_II_Config.cfg index 897aa5a70e..b1acd25a08 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Antares_II_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Antares_II_Config.cfg @@ -12,13 +12,28 @@ // Thrust (Vac): 93.074555 kN // ISP: ??? SL / 281.15 Vac // Burn Time: 33.7 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 2.87 MPa // Propellant: PBAA // Prop Ratio: N/A // Throttle: N/A // Nozzle Ratio: 17.5 // Ignitions: 1 // ================================================================================= +// Antares IIB +// X-259 +// +// Dry Mass: 99? kg +// Thrust (SL): ??? kN +// Thrust (Vac): 126.8 kN +// ISP: ??? SL / 284.95 Vac +// Burn Time: 28.9 +// Chamber Pressure: 4.76 MPa +// Propellant: PBAA +// Prop Ratio: N/A +// Throttle: N/A +// Nozzle Ratio: ??? +// Ignitions: 1 +// ================================================================================= // Sources: diff --git a/GameData/RealismOverhaul/Engine_Configs/BE-3_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/BE-3_Config.cfg index 1eed43597d..5f06a75409 100644 --- a/GameData/RealismOverhaul/Engine_Configs/BE-3_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/BE-3_Config.cfg @@ -9,14 +9,14 @@ // // Dry Mass: 480 Kg // Thrust (SL): 490 kN -// Thrust (Vac): ??? kN -// ISP: 310 SL / 360 Vac +// Thrust (Vac): 511.3? kN +// ISP: 345 SL / 360 Vac estimated with RPA // Burn Time: 660 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 8.0? MPa guess // Propellant: LOX / LH2 // Prop Ratio: 6.0? // Throttle: 490 kN to 89 kN -// Nozzle Ratio: ??? +// Nozzle Ratio: 5? guess // Ignitions: 5 // ================================================================================= @@ -64,7 +64,7 @@ { name = BE3 specLevel = operational - maxThrust = 569 //490 kN SL + maxThrust = 511.3 //490 kN SL minThrust = 89 PROPELLANT { @@ -80,7 +80,7 @@ atmosphereCurve { key = 0 360 - key = 1 310 //approx + key = 1 345 //approx } ullage = True ignitions = 5 diff --git a/GameData/RealismOverhaul/Engine_Configs/Castor_1_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Castor_1_Config.cfg index a60a151bb6..3a8df6a395 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Castor_1_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Castor_1_Config.cfg @@ -15,6 +15,7 @@ // Dry Mass: 669.9554 kg // Propellant Mass: 3311.222 kg // Nozzle Exit Area: 0.819912 m^2 +// Chamber pressure: 398.7 psi // ISP: 220.137 // // VACUUM VARIANT @@ -26,6 +27,7 @@ // Propellant Mass: 3323.015 // ISP: 273.21 vac // Total Impulse: 2,000,097 lb +// Chamber pressure: 398.7 psi // Nozzle Expansion Ratio: 15.61 // Nozzle Exit Area: 2.4637 m^2 // diff --git a/GameData/RealismOverhaul/Engine_Configs/Castor_2_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Castor_2_Config.cfg index 0310a6fe1f..6546d6efbf 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Castor_2_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Castor_2_Config.cfg @@ -1,20 +1,42 @@ -// =============================================================== -// Castor 2 Solid Rocket Motor -// Bluedog_DB, Ven Stock Revamp +// ================================================== +// Castor II // -// Manufacturer: Thiokol -// Diameter: 0.79 m -// Dry Mass: 677.2129 kg +// Manufacturer: Thiokol // -// Thrust: 270.29164 vac (that is the average, 318.1 is the maxThrust with the thrustCurve) -// ISP: 282.2 vac -// Burn Time: ~39.1 s -// Propellant Mass: 3723.99 kg -// -// Nozzle Expansion Ratio: 21.2 -// Nozzle Exit Area: 2.471928 m^2 +// ================================================================================= +// Castor II SL +// Thor/Delta // -// Sources: +// Dry Mass: 677 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 369.23 kN +// ISP: 235 SL / 260.7 Vac +// Burn Time: 39.1 +// Chamber Pressure: ??? MPa +// Propellant: CTPB +// Prop Ratio: N/A +// Throttle: N/A +// Nozzle Ratio: ??? +// Ignitions: 1 +// ================================================================================= +// Castor II Vac +// Scout +// +// Dry Mass: 677 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 318.1 kN +// ISP: 220? SL / 282.2 Vac +// Burn Time: 39.1 +// Chamber Pressure: 5.51 MPa +// Propellant: CTPB +// Prop Ratio: N/A +// Throttle: N/A +// Nozzle Ratio: 21.2 +// Ignitions: 1 +// ================================================================================= + +// Sources: + // NASA CR-165950 Scout Launch Vehicle Final Report.PDF // NASA CR-145136 Scout Nozzle Data Book (1976): https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19770010201.pdf // Thrust Misalignments of Fixed Solid Rocket Motors: http://rsandt.com/media/Thrust%20Misalignments%20of%20Fixed-Nozzle%20Solid%20Rocket%20Motors.pdf @@ -22,9 +44,13 @@ // NASA CR-146805 Post flight analyses for Delta mission 113: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19760014174.pdf // NASA CR-66259 Desitgn and development of the Castor IIA rocket motor: https://www.ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19670004241.pdf // The Development of Propulsion Technology for U.S. Space-Launch Vehicles (SL Isp of the SL version) -// -// =============================================================== +// Used by: + +// Notes: + +// Propellant Mass: 3723.99 kg +// =============================================================== @PART[*]:HAS[#engineType[Castor-2]]:FOR[RealismOverhaulEngines] { %category = Engine diff --git a/GameData/RealismOverhaul/Engine_Configs/Dropt_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Dropt_Config.cfg index 4e428220ac..56b5f78aab 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Dropt_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Dropt_Config.cfg @@ -1,21 +1,36 @@ -// P 0.68 Dropt SRM (Diamant B/BP4) -// BDB +// ================================================== +// P 0.68 Dropt SRM // // Manufacturer: Aerospatiale -// =============================================================== // -// Dimensions: 1.6 x 1.1 m -// Mass: 67 kg -// Propellant Mass: 685 kg -// Thrust: 50 kN -// ISP: 275s -// Burn Time: 45s -// Propellant: Isolane +// ================================================================================= +// P 0.68 Dropt SRM +// Diamant B/BP4 // +// Dry Mass: 67 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 50 kN +// ISP: ??? SL / 275 Vac +// Burn Time: 45 +// Chamber Pressure: 5.8 MPa +// Propellant: PBAN +// Prop Ratio: N/A +// Throttle: N/A +// Nozzle Ratio: ??? +// Ignitions: 1 +// ================================================================================= + +// Sources: + // Source 1: AIAA-98-3980 Large Space Solid Rocket Motors in Europe - Uhrig & Boury (1998) -// http://majdalani.eng.auburn.edu/courses/09_propulsion_1/Papers/AIAA983980_Uhrig.pdf -// =============================================================== +// http://majdalani.eng.auburn.edu/courses/09_propulsion_1/Papers/AIAA983980_Uhrig.pdf + +// Used by: + +// Notes: +// 685 kg propellant +// ================================================== @PART[*]:HAS[#engineType[Dropt]]:FOR[RealismOverhaulEngines] { %title = #roDroptTitle //P 0.68 Dropt diff --git a/GameData/RealismOverhaul/Engine_Configs/E1_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/E1_Config.cfg index 7a3615bca7..6c50306e09 100644 --- a/GameData/RealismOverhaul/Engine_Configs/E1_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/E1_Config.cfg @@ -4,41 +4,117 @@ // Manufacturer: Rocketdyne // // ================================================================================= -// E-1 -// +// E-1 (-380klbf) +// MA-4, 1963? // -// Dry Mass: ??? Kg -// Thrust (SL): 1690 kN -// Thrust (Vac): 1884 kN (Sutton claims 400klbf, but period documents say only 380klbf was tested). -// ISP: 260 SL / 290 Vac -// Burn Time: 165 -// Chamber Pressure: ??? MPa +// Dry Mass: 1800? kg Assuming a similar TWR to the H-1-188k +// Thrust (SL): 1690.32 kN (Sutton claims 400klbf, but period documents say only 380klbf was tested). +// Thrust (Vac): 1947.53 kN +// ISP: 251.7 SL / 290 Vac estimated with RPA +// Burn Time: 165? +// Chamber Pressure: 5.0 MPa a little more than H-1? // Propellant: LOX / RP-1 -// Prop Ratio: 2.15 +// Prop Ratio: 2.15? // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 12? // Ignitions: 1 // ================================================================================= -// E-1 Dynasoar -// +// E-1 Upgrade +// Deprecated // -// Dry Mass: ??? Kg -// Thrust (SL): 2081 kN -// Thrust (Vac): 2335 kN -// ISP: 256 SL / 290 Vac +// Dry Mass: 1814.4 Kg +// Thrust (SL): 2081.7 kN +// Thrust (Vac): 2366.3 kN +// ISP: 256 SL / 291 Vac // Burn Time: 210 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 5.45 MPa // Propellant: LOX / RP-1 // Prop Ratio: 2.25 // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 12 +// Ignitions: 1 +// ================================================================================= +// E-1 Upgrade2 +// Deprecated +// +// Dry Mass: 1814.4? Kg +// Thrust (SL): ??? kN //525klbf sea level +// Thrust (Vac): 2662.6 kN +// ISP: 264 SL / 301 Vac +// Burn Time: 210? +// Chamber Pressure: 5.45? MPa +// Propellant: LOX / RP-1 +// Prop Ratio: 2.25? +// Throttle: N/A +// Nozzle Ratio: 12? +// Ignitions: 1 +// ================================================================================= +// E-1-468k +// Dynasoar RBS version, 1966? +// +// Dry Mass: 1814.4 Kg +// Thrust (SL): 2081.77 kN 468klbf sl +// Thrust (Vac): 2366.39 kN +// ISP: 256 SL / 291 Vac +// Burn Time: 210 +// Chamber Pressure: 5.45 MPa +// Propellant: LOX / RP-1 +// Prop Ratio: 2.25 +// Throttle: N/A +// Nozzle Ratio: 12 +// Ignitions: 1 +// ================================================================================= +// E-1-500k +// Original target thrust? 1969? +// +// Dry Mass: 1814.4 Kg +// Thrust (SL): 2224.11 kN 500klbf sl +// Thrust (Vac): 2505.97 kN +// ISP: 258.27 SL / 291 Vac +// Burn Time: 210 +// Chamber Pressure: 5.77? MPa +// Propellant: LOX / RP-1 +// Prop Ratio: 2.25? +// Throttle: N/A +// Nozzle Ratio: 12? +// Ignitions: 1 +// ================================================================================= +// E-1-575k +// Speculative. Same thrust increase from standard E-1 as H-1-165k to H-1-250k, 1976? +// +// Dry Mass: 1814.4? Kg +// Thrust (SL): 2557.73 kN //575klbf sea level +// Thrust (Vac): 2828.57 kN +// ISP: 264.04 SL / 292 Vac +// Burn Time: 210? +// Chamber Pressure: 6.45? MPa +// Propellant: LOX / RP-1 +// Prop Ratio: 2.35? assuming slightly leaner to help increase thrust, like late H-1 +// Throttle: N/A +// Nozzle Ratio: 12? +// Ignitions: 1 +// ================================================================================= +// E-1A_KS +// From Kolyma's Shadow +// +// Dry Mass: 1835? Kg a little heavier for nozzle extension? +// Thrust (SL): ??? kN +// Thrust (Vac): 2250 kN +// ISP: 369 SL / 310 Vac +// Burn Time: 240? +// Chamber Pressure: 6.0? MPa estimated with RPA +// Propellant: LOX / RP-1 +// Prop Ratio: 2.35? +// Throttle: N/A +// Nozzle Ratio: 15? estimated with RPA // Ignitions: 1 // ================================================================================= // Sources: -// Operation Dyna Soar Recoverable Booster Study: Selected Booster.PDF: http://www.alternatewars.com/BBOW/Space_Engines/Rocketdyne_Engines.htm -// alternatewars - Rocketdyne engines: http://www.alternatewars.com/BBOW/Space_Engines/Rocketdyne_Engines.htm +// [1]Operation Dyna Soar Recoverable Booster Study: Selected Booster.PDF: http://www.alternatewars.com/BBOW/Space_Engines/Rocketdyne_Engines.htm +// [2]alternatewars - Rocketdyne engines: http://www.alternatewars.com/BBOW/Space_Engines/Rocketdyne_Engines.htm +// [3]https://www.drewexmachina.com/download-pdf/SV_1998_09.pdf // [A] History of Liquid Propellant Rocket Engines, George P. Sutton, Page 430 // Used by: @@ -79,14 +155,14 @@ name = ModuleEngineConfigs type = ModuleEngines configuration = E-1 - origMass = 1.264 // Assuming a similar TWR to the H-1 + origMass = 1.800 CONFIG { name = E-1 specLevel = prototype - minThrust = 1884.59 // 380klbf sea level - maxThrust = 1884.59 + minThrust = 1947.53 + maxThrust = 1947.53 heatProduction = 100 massMult = 1.0 @@ -122,20 +198,199 @@ atmosphereCurve { key = 0 290 - key = 1 260 + key = 1 251.7 } //Never flown, all configs speculative // Copied from H-1, slightly decreased TESTFLIGHT:NEEDS[TestLite|TestFlight] { - testedBurnTime = 900 //Assume halfway between F-1 and H-1 (15 minutes) + testedBurnTime = 775 //Same as H-1-188k ratedBurnTime = 165 safeOverburn = true ignitionReliabilityStart = 0.95 ignitionReliabilityEnd = 0.995 cycleReliabilityStart = 0.96 cycleReliabilityEnd = 0.993 + techTransfer = S-3D,S-3:25 + } + } + + CONFIG + { + name = E-1-468k + description = Uprated E-1 intended for use with the Dyna Soar project. This version is without boostback hardware. + specLevel = concept + minThrust = 2366.3 + maxThrust = 2366.3 + heatProduction = 100 + massMult = 1.008 + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + IGNITOR_RESOURCE + { + name = TEATEB + amount = 1 + } + + PROPELLANT + { + name = RP-1 + ratio = 0.3859 + DrawGauge = True + } + + PROPELLANT + { + name = LqdOxygen + ratio = 0.6141 + } + + atmosphereCurve + { + key = 0 291 + key = 1 256 + } + + //Never flown, all configs speculative + // Copied from H-1-188k + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 2025 //same as H-1 + ratedBurnTime = 165 + safeOverburn = true + ignitionReliabilityStart = 0.980612 + ignitionReliabilityEnd = 0.996939 + cycleReliabilityStart = 0.980612 + cycleReliabilityEnd = 0.996939 + techTransfer = S-3D,S-3:25&E-1:50 + } + } + CONFIG + { + name = E-1-500k + description = Speculative E-1 upgrade, uprated to target thrust level of original E-1 study. + specLevel = speculative + minThrust = 2505.97 + maxThrust = 2505.97 + heatProduction = 100 + massMult = 1.008 + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + IGNITOR_RESOURCE + { + name = TEATEB + amount = 1 + } + + PROPELLANT + { + name = RP-1 + ratio = 0.3859 + DrawGauge = True + } + + PROPELLANT + { + name = LqdOxygen + ratio = 0.6141 + } + + atmosphereCurve + { + key = 0 291 + key = 1 258.27 + } + + //Never flown, all configs speculative + // Copied from H-1-200k + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 2025 //same as H-1 + ratedBurnTime = 165 + safeOverburn = true + ignitionReliabilityStart = 0.976829 + ignitionReliabilityEnd = 0.996341 + cycleReliabilityStart = 0.976829 + cycleReliabilityEnd = 0.996341 + techTransfer = S-3D,S-3:25&E-1-468k,E-1:50 + } + } + CONFIG + { + name = E-1-575k + description = Speculative E-1 upgrade, uprated to maximum possible thrust. + specLevel = speculative + minThrust = 2828.57 + maxThrust = 2828.57 + heatProduction = 100 + massMult = 1.008 + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + IGNITOR_RESOURCE + { + name = TEATEB + amount = 1 + } + + PROPELLANT + { + name = RP-1 + ratio = 0.3756 + DrawGauge = True + } + + PROPELLANT + { + name = LqdOxygen + ratio = 0.6244 + } + + atmosphereCurve + { + key = 0 292 + key = 1 264.04 + } + + //Never flown, all configs speculative + // Copied from H-1-200k + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 2025 //same as H-1 + ratedBurnTime = 165 + safeOverburn = true + ignitionReliabilityStart = 0.976829 + ignitionReliabilityEnd = 0.996341 + cycleReliabilityStart = 0.976829 + cycleReliabilityEnd = 0.996341 + techTransfer = S-3D,S-3:25&E-1-500k,E-1-468k,E-1:50 } } @@ -144,10 +399,11 @@ name = E-1-Upgrade description = Speculative upgrade configuration for the E-1 intended for use with the Dyna Soar project. This version is without boostback hardware. specLevel = speculative + RODeprecated = true minThrust = 2358.25 // 468klbf sea level maxThrust = 2358.25 heatProduction = 100 - massMult = 1.04 // 1.435 = 4000lb for boostback booster + massMult = 1.0 ullage = True pressureFed = False @@ -203,10 +459,11 @@ name = E-1-Upgrade2 description = Speculative upgrade configuration using late 1960s technology. specLevel = speculative + RODeprecated = true minThrust = 2662.6 //525klbf sea level maxThrust = 2662.6 heatProduction = 100 - massMult = 1.2 + massMult = 1.0 ullage = True pressureFed = False @@ -265,7 +522,7 @@ minThrust = 2250 maxThrust = 2250 heatProduction = 100 - massMult = 1.0 + massMult = 1.0194 ullage = True pressureFed = False @@ -286,14 +543,14 @@ PROPELLANT { name = RP-1 - ratio = 0.3859 + ratio = 0.3756 DrawGauge = True } PROPELLANT { name = LqdOxygen - ratio = 0.6141 + ratio = 0.6244 } atmosphereCurve @@ -302,17 +559,17 @@ key = 1 269 } - // RS-27 / F-1A level + // RS-27A / F-1A level TESTFLIGHT:NEEDS[TestLite|TestFlight] { - testedBurnTime = 900 + testedBurnTime = 2025 //same as H-1 ratedBurnTime = 240 safeOverburn = true - ignitionReliabilityStart = 0.99 - ignitionReliabilityEnd = 0.998 - cycleReliabilityStart = 0.99 - cycleReliabilityEnd = 0.998 - techTransfer = E-1-Upgrade2,E-1-Upgrade,E-1:50 + ignitionReliabilityStart = 0.993310 + ignitionReliabilityEnd = 0.998944 + cycleReliabilityStart = 0.993310 + cycleReliabilityEnd = 0.998944 + techTransfer = S-3D,S-3:25&E-1-500k,E-1-468k,E-1:50 } } } diff --git a/GameData/RealismOverhaul/Engine_Configs/F-1A_ETS_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/F-1A_ETS_Config.cfg index 35982efd65..2b976a71ac 100644 --- a/GameData/RealismOverhaul/Engine_Configs/F-1A_ETS_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/F-1A_ETS_Config.cfg @@ -1,14 +1,26 @@ +// ================================================== // Throttlable F-1A series engine as found in 'Eyes Turned Skyward' +// +// Manufacturer: Rocketdyne +// +// ================================================================================= +// F-1A-ETS // // -// ================================================== -// Rocketdyne F-1A engine. +// Dry Mass: 8390 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 9189.6 kN +// ISP: 268.8 SL / 306.2 Vac +// Burn Time: 315 +// Chamber Pressure: 8.0 MPa +// Propellant: LOX / RP1 +// Prop Ratio: 2.27 +// Throttle: 60% - 100% +// Nozzle Ratio: 16 +// Ignitions: 1 +// ================================================================================= -// Dimensions: 3.8 m x 5.7 m -// Gross Mass: 8390 Kg -// Throttle Range: 60% - 100% // Estimation, if this value is canon please correct. -// Burn Time: 150 s -// O/F Ratio: 2.27 +// Sources: // Source 1: http://history.nasa.gov/ap12fj/pdf/a12_sa507-flightmanual.pdf // Source 2: http://history.msfc.nasa.gov/saturn_apollo/documents/F-1_Engine.pdf @@ -72,8 +84,8 @@ } atmosphereCurve { - key = 0 310 - key = 1 270 + key = 0 306.2 + key = 1 268.8 } ullage = True @@ -109,7 +121,7 @@ ignitionReliabilityEnd = 0.998 cycleReliabilityStart = 0.985 cycleReliabilityEnd = 0.998 - techTransfer = F-1-1.5M, F-1-1.52M:50 + techTransfer = F-1-1.5M,F-1-1.52M:50 } } } diff --git a/GameData/RealismOverhaul/Engine_Configs/H1_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/H1_Config.cfg index f7053974f6..493acad2cc 100644 --- a/GameData/RealismOverhaul/Engine_Configs/H1_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/H1_Config.cfg @@ -5,16 +5,16 @@ // // ================================================================================= // H-1 165K -// 1961, SA-1 through SA-4 +// 1961, SA-1 through SA-4. Actually downrated H-1-188k. // -// Dry Mass: 911 Kg -// Thrust (SL): 733.9563 kN -// Thrust (Vac): 823.25 kN -// ISP: 258 SL / 295 Vac SL calculated with RPA +// Dry Mass: 911? Kg +// Thrust (SL): 733.9563 kN [3/10] 165klbf sl +// Thrust (Vac): 846.76 kN +// ISP: 255.7 SL / 295? Vac SL calculated with RPA // Burn Time: 155 -// Chamber Pressure: 4.05 MPa +// Chamber Pressure: 4.05? MPa // Propellant: LOX / RP1 -// Prop Ratio: 2.23 +// Prop Ratio: 2.23? // Throttle: N/A // Nozzle Ratio: 8 // Ignitions: 1 @@ -23,14 +23,14 @@ // H-1 188K // 1964, SA-5 through SA-10 // -// Dry Mass: 911 Kg -// Thrust (SL): 836.26536 kN -// Thrust (Vac): 939.02 kN -// ISP: 263 SL / 295 Vac +// Dry Mass: 911? Kg +// Thrust (SL): 836.26536 kN [3/10] 188klbf sl +// Thrust (Vac): 950.19 kN +// ISP: 259.63 SL / 295 Vac SL calculated with RPA // Burn Time: 155 -// Chamber Pressure: 4.52 MPa +// Chamber Pressure: 4.52 MPa [8] // Propellant: LOX / RP1 -// Prop Ratio: 2.23 +// Prop Ratio: 2.23 [8] // Throttle: N/A // Nozzle Ratio: 8 // Ignitions: 1 @@ -40,13 +40,13 @@ // 1966, SA-201 through SA-205 // // Dry Mass: 911 Kg -// Thrust (SL): 889.644 kN -// Thrust (Vac): 997.889 kN -// ISP: 261 SL / 295 Vac SL calculated with RPA +// Thrust (SL): 886.530 kN [9] 199,300 klbf sl +// Thrust (Vac): 997.93 kN +// ISP: 262.07 SL / 295 Vac SL calculated with RPA // Burn Time: 155 -// Chamber Pressure: 4.36 MPa +// Chamber Pressure: 4.75 MPa [9] // Propellant: LOX / RP1 -// Prop Ratio: 2.23 +// Prop Ratio: 2.338 [9] // Throttle: N/A // Nozzle Ratio: 8 // Ignitions: 1 @@ -56,29 +56,29 @@ // 1973, SA-206 through SA-210 // // Dry Mass: 911 Kg -// Thrust (SL): 911.8851 kN -// Thrust (Vac): 1054.22 kN -// ISP: 263 SL / 295 Vac +// Thrust (SL): 908.771 kN [9] 204,300 klbf sl +// Thrust (Vac): 1021.01 kN +// ISP: 262.57 SL / 295 Vac [1] // Burn Time: 155 -// Chamber Pressure: 4.82 MPa +// Chamber Pressure: 4.82 MPa [9] // Propellant: LOX / RP1 -// Prop Ratio: 2.23 +// Prop Ratio: 2.341 [1/9] // Throttle: N/A // Nozzle Ratio: 8 // Ignitions: 1 // Gimbal: 10.5 // ================================================================================= // H-1 250K -// 1975? Uprated S-IB concept +// 1976? Uprated S-IB concept // // Dry Mass: 911 Kg -// Thrust (SL): 1112.1 kN -// Thrust (Vac): 1247.4 kN -// ISP: 267 SL / 295 Vac SL calculated with RPA +// Thrust (SL): 1112.1 kN 250,000 klbf sl +// Thrust (Vac): 1224.46 kN +// ISP: 267.93 SL / 295 Vac SL calculated with RPA // Burn Time: 155 -// Chamber Pressure: 5.45? MPa +// Chamber Pressure: 5.78? MPa // Propellant: LOX / RP1 -// Prop Ratio: 2.23 +// Prop Ratio: 2.34? // Throttle: N/A // Nozzle Ratio: 8 // Ignitions: 1 @@ -94,7 +94,7 @@ // Burn Time: 240 // Chamber Pressure: 4.85 MPa // Propellant: LOX / RP1 -// Prop Ratio: 2.23 +// Prop Ratio: 2.245 [3/6] // Throttle: N/A // Nozzle Ratio: 8 // Ignitions: 1 @@ -105,29 +105,32 @@ // // Dry Mass: 1147 Kg // Thrust (SL): 890.1 kN -// Thrust (Vac): 1054 kN -// ISP: 255 SL / 302 Vac +// Thrust (Vac): 1054.23 kN +// ISP: 255 SL / 302 Vac [2] // Burn Time: 265 // [A] Nominal Flight Duration: 265s -// Chamber Pressure: 4.85 MPa +// Chamber Pressure: 4.82 MPa [2] // Propellant: LOX / RP1 -// Prop Ratio: 2.24 +// Prop Ratio: 2.245 [3] // Throttle: N/A -// Nozzle Ratio: 12 +// Nozzle Ratio: 12 [2] // Ignitions: 1 // Gimbal: 8.5 // ================================================================================= // Sources: -// #1: MSFC-MAN-206 Skylab Saturn IB Flight Manual (1972): https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19740021163.pdf - -// http://www.rocket.com/rs-27a-engine -// http://www.alternatewars.com/BBOW/Space_Engines/Rocketdyne_Engines.htm -// http://www.apollosaturn.com/sibnews/sec4.htm -// https://web.archive.org/web/20041022144943/http://history.nasa.gov/SP-4206/ch4.htm -// http://www.astronautix.com/engines/rs27a.htm -// RS-27: https://www.history.nasa.gov/SP-4012/vol3/table1.31.htm -// http://www.b14643.de/Spacerockets/Specials/U.S._Rocket_engines/engines.htm +// [1] MSFC-MAN-206 Skylab Saturn IB Flight Manual (1972): https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19740021163.pdf + +// [2] https://web.archive.org/web/20190307173028/https://www.rocket.com/rs-27a-engine +// [3] https://web.archive.org/web/20211229003426/http://www.alternatewars.com/BBOW/Space_Engines/Rocketdyne_Engines.htm +// [4] https://web.archive.org/web/20160520063133/http://www.apollosaturn.com/sibnews/sec4.htm +// [5] https://web.archive.org/web/20041022144943/http://history.nasa.gov/SP-4206/ch4.htm +// [6] http://www.astronautix.com/engines/rs27a.htm +// [7] https://web.archive.org/web/20190714132700/https://www.history.nasa.gov/SP-4012/vol3/table1.31.htm +// [8] http://www.b14643.de/Spacerockets/Specials/U.S._Rocket_engines/engines.htm +// [9] https://web.archive.org/web/20211229003426/http://www.alternatewars.com/BBOW/Space_Engines/H-1C-D_Manual.pdf +// [10] https://web.archive.org/web/20220531043804/https://www.alternatewars.com/BBOW/Space_Engines/Saturn_H-1_Design_Features.pdf +// [11] https://web.archive.org/web/20211229003426/http://www.alternatewars.com/BBOW/Space_Engines/Launch_Vehicles_Engines_PDP_1-JAN-1967.pdf // [A] History of Liquid Propellant Rocket Engines, George P. Sutton, Page 409 Table 7.8-1 // [A] History of Liquid Propelland Rocket Engines, George P. Sutton, Page 424 @@ -175,8 +178,8 @@ name = H-1-165K description = Earliest prototype version of the H-1 Engine that flew on the Saturn I, Block I. It is rated at 165k lbf sea level thrust. specLevel = operational - minThrust = 823.25 - maxThrust = 823.25 + minThrust = 846.76 + maxThrust = 846.76 heatProduction = 100 massMult = 1.0 @@ -213,7 +216,7 @@ atmosphereCurve { key = 0 295 - key = 1 258 + key = 1 255.7 } //Saturn 1 Block I: 4 flights, 0 failures @@ -236,8 +239,8 @@ name = H-1-188K description = Improved version of the H-1 Engine for the Saturn I, Block II. It is rated at 188k lbf sea level thrust. specLevel = operational - minThrust = 938.02 - maxThrust = 938.02 + minThrust = 950.19 + maxThrust = 950.19 heatProduction = 100 massMult = 1.0 @@ -274,14 +277,14 @@ atmosphereCurve { key = 0 295 - key = 1 263 + key = 1 259.63 } //Saturn 1 Block II: 6 flights, 0 failures //48 engines, 0 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] { - testedBurnTime = 775 //Engine pulled from stage and tested in 1971 for Skylab missions. Subjected to 3 full burns and passed with no degradation. 775 seconds (1x acceptance burn, 3x shakedown burn, 1x flight burn) + testedBurnTime = 775 ratedBurnTime = 155 safeOverburn = true ignitionReliabilityStart = 0.980612 @@ -297,8 +300,8 @@ name = H-1-200K description = H-1 Engine that flew on the first 5 Saturn IB launches. It is rated at 200k lbf sea level thrust. specLevel = operational - minThrust = 997.889 - maxThrust = 997.889 + minThrust = 997.93 + maxThrust = 997.93 heatProduction = 100 massMult = 1.0 @@ -335,14 +338,14 @@ atmosphereCurve { key = 0 295 - key = 1 261 + key = 1 262.07 } //Saturn 1B: 5 flights, 0 failures //40 engines, 0 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] { - testedBurnTime = 775 //Engine pulled from stage and tested in 1971 for Skylab missions. Subjected to 3 full burns and passed with no degradation. 775 seconds (1x acceptance burn, 3x shakedown burn, 1x flight burn) + testedBurnTime = 2025 //[11] target lifetime 2025 seconds ratedBurnTime = 155 safeOverburn = true ignitionReliabilityStart = 0.976829 @@ -358,8 +361,8 @@ name = H-1-205K description = Final version of the H-1 Engine for the Saturn IB that flew on the 4 flights of Skylab and ASTP. It is rated at 205k lbf sea level thrust. specLevel = operational - minThrust = 1054.22 - maxThrust = 1054.22 + minThrust = 1021.01 + maxThrust = 1021.01 heatProduction = 100 massMult = 1.0 @@ -396,14 +399,14 @@ atmosphereCurve { key = 0 295 - key = 1 263 + key = 1 262.57 } //Saturn 1B (Skylab): 4 flights, 0 failures //32 engines, 0 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] { - testedBurnTime = 775 //Engine pulled from stage and tested in 1971 for Skylab missions. Subjected to 3 full burns and passed with no degradation. 775 seconds (1x acceptance burn, 3x shakedown burn, 1x flight burn) + testedBurnTime = 2025 //[11] target lifetime 2025 seconds ratedBurnTime = 155 safeOverburn = true ignitionReliabilityStart = 0.976829 @@ -419,8 +422,8 @@ name = H-1-250K description = Maximum possible thrust for H-1 design, proposed for a post-Apollo uprated Saturn IB. Although engines were tested at increased thrust levels, the end of Apollo and selection of Titan III over Saturn IB meant this was never developed further. specLevel = concept - minThrust = 1247.4 - maxThrust = 1247.4 + minThrust = 1224.46 + maxThrust = 1224.46 heatProduction = 100 massMult = 1.0 @@ -457,13 +460,13 @@ atmosphereCurve { key = 0 295 - key = 1 267 + key = 1 267.93 } //No data, same as 205K TESTFLIGHT:NEEDS[TestLite|TestFlight] { - testedBurnTime = 775 //Engine pulled from stage and tested in 1971 for Skylab missions. Subjected to 3 full burns and passed with no degradation. 775 seconds (1x acceptance burn, 3x shakedown burn, 1x flight burn) + testedBurnTime = 2025 //[11] target lifetime 2025 seconds ratedBurnTime = 155 safeOverburn = true ignitionReliabilityStart = 0.976829 @@ -539,7 +542,7 @@ //100 engines, 1 failure TESTFLIGHT:NEEDS[TestLite|TestFlight] { - testedBurnTime = 1200 //Assume also good for 5x burn time, mildly upgraded over H-1 + testedBurnTime = 2025 //[11] target lifetime 2025 seconds ratedBurnTime = 240 safeOverburn = true ignitionReliabilityStart = 0.978053 @@ -555,8 +558,8 @@ name = RS-27A description = RS-27 with a higher expansion nozzle for Delta II specLevel = operational - maxThrust = 1054 - minThrust = 1054 + maxThrust = 1054.23 + minThrust = 1054.23 heatProduction = 100 massMult = 1.10425 @@ -610,7 +613,7 @@ //141 engines, 0 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] { - testedBurnTime = 1200 //Assume also good for 5x burn time, mildly upgraded over H-1 + testedBurnTime = 2025 //[11] target lifetime 2025 seconds ratedBurnTime = 265 safeOverburn = true ignitionReliabilityStart = 0.993310 diff --git a/GameData/RealismOverhaul/Engine_Configs/HG-3_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/HG-3_Config.cfg index e2ea64ffcf..a61d19e733 100644 --- a/GameData/RealismOverhaul/Engine_Configs/HG-3_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/HG-3_Config.cfg @@ -1,19 +1,144 @@ -// HG-3 series engine -// SXT, SHIP // ================================================== -// Rocketdyne HG-3 engine. +// HG-3 +// +// Manufacturer: Rocketdyne +// +// ================================================================================= +// HG-3 +// +// +// Dry Mass: 1780? kg +// Thrust (SL): ??? kN +// Thrust (Vac): 1400.70 kN +// ISP: 270 SL / 451 Vac estimated with RPA +// Burn Time: 500 +// Chamber Pressure: 11.50? MPa +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Throttle: 100% to 67% +// Nozzle Ratio: 75? +// Ignitions: 2 +// ================================================================================= +// HG-3-SL +// +// +// Dry Mass: 1733? kg +// Thrust (SL): ??? kN +// Thrust (Vac): 1382.07 kN +// ISP: 340 SL / 445 Vac estimated with RPA +// Burn Time: 500 +// Chamber Pressure: 11.50? MPa +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Throttle: 100% to 67% +// Nozzle Ratio: 50? +// Ignitions: 1 +// ================================================================================= +// HG-3A +// +// +// Dry Mass: 1780? kg +// Thrust (SL): ??? kN +// Thrust (Vac): 1400.70 kN +// ISP: 270 SL / 451 Vac estimated with RPA +// Burn Time: 500 +// Chamber Pressure: 11.50? MPa +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Throttle: 100% to 67% +// Nozzle Ratio: 75? +// Ignitions: 5 +// ================================================================================= +// HG-3A-SL +// +// +// Dry Mass: 1733? kg +// Thrust (SL): ??? kN +// Thrust (Vac): 1382.07 kN +// ISP: 340 SL / 445 Vac estimated with RPA +// Burn Time: 500 +// Chamber Pressure: 11.50? MPa +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Throttle: 100% to 67% +// Nozzle Ratio: 50? +// Ignitions: 2 +// ================================================================================= +// HG-3B +// +// +// Dry Mass: 1780? kg +// Thrust (SL): ??? kN +// Thrust (Vac): 1400.70 kN +// ISP: 340 SL / 458 Vac estimated with RPA +// Burn Time: 500 +// Chamber Pressure: 16.00? MPa +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Throttle: 100% to 67% +// Nozzle Ratio: 100? +// Ignitions: 5 +// ================================================================================= +// HG-3B-SL +// +// +// Dry Mass: 1733? kg +// Thrust (SL): ??? kN +// Thrust (Vac): 1382.07 kN +// ISP: 352 SL / 452 Vac estimated with RPA +// Burn Time: 500 +// Chamber Pressure: 16.00? MPa +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Throttle: 100% to 67% +// Nozzle Ratio: 67? +// Ignitions: 2 +// ================================================================================= +// HG-3B-2 +// +// +// Dry Mass: 1780? kg +// Thrust (SL): ??? kN +// Thrust (Vac): 1422.44 kN +// ISP: 340 SL / 458 Vac estimated with RPA +// Burn Time: 500 +// Chamber Pressure: 16.00? MPa +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Throttle: 100% to 67% +// Nozzle Ratio: 100? +// Ignitions: 5 +// ================================================================================= +// HG-3B-SL-2 +// +// +// Dry Mass: 1733? kg +// Thrust (SL): ??? kN +// Thrust (Vac): 1403.81 kN +// ISP: 352 SL / 452 Vac estimated with RPA +// Burn Time: 500 +// Chamber Pressure: 16.00? MPa +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Throttle: 100% to 67% +// Nozzle Ratio: 67? +// Ignitions: 2 +// ================================================================================= -// Dimensions: 2.1 m x 3.5 m -// Gross Mass: ?? (Assumed 1780 kg as rough estimate) -// Throttle Range: ?? (67% to 100% as rough estimation and to serve as stepping stone to RS-25) -// Burn Time: 600 s -// O/F Ratio: ?? (Assumed 5.5 ala J-2) - -// Upgrades (HG-3A, etc.) are purely speculative. +// Sources: // Source 1: http://www.astronautix.com/h/hg-3.html // Source 2: http://www.astronautix.com/h/hg-3-sl.html // Source 3: https://history.msfc.nasa.gov/saturn_apollo/propulsion_center.html + +// Used by: + +// SXT +// ROEngines + +// Notes: + +// Upgrades (HG-3A, etc.) are purely speculative. // ================================================== @PART[*]:HAS[#engineType[HG3]]:FOR[RealismOverhaulEngines] { @@ -64,7 +189,7 @@ atmosphereCurve { key = 0 451 - key = 1 280 + key = 1 270 } %ullage = True @@ -172,7 +297,7 @@ atmosphereCurve { key = 0 451 - key = 1 280 + key = 1 270 } %ullage = True @@ -283,7 +408,7 @@ atmosphereCurve { key = 0 458 - key = 1 285 + key = 1 340 } %ullage = True diff --git a/GameData/RealismOverhaul/Engine_Configs/LR105_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/LR105_Config.cfg index 76001a9fb4..c46cf15fe5 100644 --- a/GameData/RealismOverhaul/Engine_Configs/LR105_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/LR105_Config.cfg @@ -12,7 +12,7 @@ // Thrust (Vac): 240.2 kN // ISP: 210 SL / 301 Vac // Burn Time: 330 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.52 MPa estimated with RPA // Propellant: LOX / RP-1 // Prop Ratio: 2.25 // Throttle: N/A @@ -57,7 +57,7 @@ // Thrust (Vac): 373.2 kN // ISP: 217 SL / 313 vac // Burn Time: 350 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.71 MPa // Propellant: LOX / RP1 // Prop Ratio: 2.25 // Throttle: N/A @@ -72,7 +72,7 @@ // Thrust (Vac): 385.2 kN // ISP: 220 SL / 316 vac // Burn Time: 350 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.80 MPa // Propellant: LOX / RP1 // Prop Ratio: 2.25 // Throttle: N/A @@ -87,7 +87,7 @@ // Thrust (Vac): 386.4 kN // ISP: 220 SL / 316 vac // Burn Time: 350 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.80 MPa // Propellant: LOX / RP1 // Prop Ratio: 2.25 // Throttle: N/A @@ -102,7 +102,7 @@ // Thrust (Vac): 386.4 kN // ISP: 220.4 SL / 316 vac // Burn Time: 350 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 5.07 MPa // Propellant: LOX / RP1 // Prop Ratio: 2.25 // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/LR129_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/LR129_Config.cfg index 0bf1d2d95b..cef30bbb00 100644 --- a/GameData/RealismOverhaul/Engine_Configs/LR129_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/LR129_Config.cfg @@ -16,8 +16,6 @@ // Chamber Pressure: 18.89 MPa // Propellant: LOX / LH2 // Prop Ratio: 6.0 -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? // Throttle: 100% to 20% // Nozzle Ratio: 35:1/75:1 // Ignitions: 1 @@ -34,8 +32,6 @@ // Chamber Pressure: 20.68 MPa // Propellant: LOX / LH2 // Prop Ratio: 6.0 -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? // Throttle: 100% to 20% // Nozzle Ratio: 35:1/75:1 // Ignitions: 1 @@ -52,8 +48,22 @@ // Chamber Pressure: 22.75 MPa // Propellant: LOX / LH2 // Prop Ratio: 6.0 -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? +// Throttle: 100% to 50% +// Nozzle Ratio: 35:1/75:1 +// Ignitions: 1 +// ================================================================================= +// LR129-P-3 +// Speculative Space Shuttle main engine Block II +// +// Dry Mass: 1632.9 kg //~3600 lbs + 200 lbs gimbal hardware estimated mass for 350klbf engine +// Thrust (SL): ??? kN +// Thrust (Vac): 1619.2 kN +// ISP: 393 SL / 440 Vac (retracted) SL calculated with RPA +// ISP: 374 SL / 463 Vac (extended) SL calculated with RPA +// Burn Time: 500 +// Chamber Pressure: 22.75 MPa +// Propellant: LOX / LH2 +// Prop Ratio: 6.0 // Throttle: 100% to 50% // Nozzle Ratio: 35:1/75:1 // Ignitions: 1 diff --git a/GameData/RealismOverhaul/Engine_Configs/LR79_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/LR79_Config.cfg index da7e496ebb..1919d73542 100644 --- a/GameData/RealismOverhaul/Engine_Configs/LR79_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/LR79_Config.cfg @@ -13,14 +13,14 @@ // Thrust (vac): Calculated by (766.34 S-3D value * 90%) = 696.6 kN // ISP: 247.62 SL (all sources) / 288 vac // Burn Time: 182 (burn time for Jupiter) -// Chamber Pressure: ??? MPa +// Chamber Pressure: 3.61? MPa // Propellant: LOX / RP1 // Prop Ratio: 2.4 // Throttle: N/A // Nozzle Ratio: 8 // Ignitions: 1 // ================================================================================= -// S-3D +// S-3D (LR79-NA-1?) // // Dry Mass: 945.3 kg (Source #4) // Thrust (SL): 150,000 lbf (all sources) = 667.233 kN @@ -39,7 +39,7 @@ // Thor MB-3 Block I // Data from Source #5 // -// Dry Mass: ??? +// Dry Mass: 933.66? kg interpolated between S-3D and LR79-NA-13 // Thrust (SL): 150,000 lbf = 667.233 kN // Thrust (Vac): 176,000 lbf = 782.886 kN // ISP: 245 SL / 284 vac @@ -57,7 +57,7 @@ // Thor MB-3 Block II // Data from Source #5 // -// Dry Mass: ??? +// Dry Mass: 923.56? kg interpolated between S-3D and LR79-NA-13 // Thrust (SL): 165,453 lbf = 735.9713437 kN // Thrust (Vac): 190,998 lbf = 849.6011236 kN // ISP: 248.3 SL / 286.2 vac @@ -78,7 +78,7 @@ // Lower performance than orignal Hydrazine proposal, but much easier to build due to the properties of // UDMH being much closer to Kerosene. // -// Dry Mass: ??? +// Dry Mass: 923.56? kg same as LR79-NA-11 // Thrust (SL): 165,453 lbf = 735.9713437 kN // Thrust (Vac): 190,998 lbf = 849.6011236 kN // ISP: 266.1 SL / 305.5 vac Calculated with RPA, using estimate with straight hydrazine as correction factor diff --git a/GameData/RealismOverhaul/Engine_Configs/LR83_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/LR83_Config.cfg index 4f984c9cf9..df63a92392 100644 --- a/GameData/RealismOverhaul/Engine_Configs/LR83_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/LR83_Config.cfg @@ -7,16 +7,16 @@ // XLR83 // Navaho G-38 // -// Dry Mass: 90 Kg +// Dry Mass: 1670 kg TWR 110, roughly match LR43-NA-3 // Thrust (SL): 1801.5 kN // Thrust (Vac): ??? kN -// ISP: 245 SL / ??? Vac +// ISP: 245 SL / 282 Vac // Burn Time: 100 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 3.92? MPa same as LR43-NA-3? // Propellant: LOX / RP-1 -// Prop Ratio: 2.25 //assumed to be the same as LR43 +// Prop Ratio: 2.25? same as LR43-NA-3? // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 8? same as LR43-NA-3? // Ignitions: 1 // ================================================================================= @@ -64,7 +64,7 @@ type = ModuleEngines modded = false configuration = XLR83-NA-1 - origMass = 0.415 + origMass = 1.670 CONFIG { name = XLR83-NA-1 diff --git a/GameData/RealismOverhaul/Engine_Configs/LR87LH2_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/LR87LH2_Config.cfg index 95a1a604ca..01a8ce5ff4 100644 --- a/GameData/RealismOverhaul/Engine_Configs/LR87LH2_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/LR87LH2_Config.cfg @@ -1,12 +1,82 @@ -//References +// ================================================== +// LR-87 LH2 +// +// Manufacturer: Aerojet +// +// ================================================================================= +// LR87-LH2-TitanC +// Titan C +// +// Dry Mass: 839? kg same mass as a normal AJ-3 I guess +// Thrust (SL): ??? Kn +// Thrust (Vac): 667 kN +// ISP: 350 SL / 403 Vac sl calculated with RPA +// Burn Time: 300? +// Chamber Pressure: 5.0 MPa A little higher to get advertised sl performance +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Nozzle Ratio: 12? +// Ignitions: 1 +// ================================================================================= +// LR87-LH2-Vacuum +// Upgrade with nozzle extension and uprated for Saturn +// +// Dry Mass: 1050? kg vac nozzle, restart equipment, and general uprating should add mass. Slightly lower TWR than TitanC +// Thrust (SL): ??? Kn +// Thrust (Vac): 778 kN +// ISP: 315 SL / 421 Vac calculated with RPA +// Burn Time: 500? +// Chamber Pressure: 5.48 MPa same as AJ-5 +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Nozzle Ratio: 24? +// Ignitions: 2? +// ================================================================================= +// LR87-LH2-SustainerUpgrade +// Speculative upgrade with sl nozzle +// +// Dry Mass: 939? kg keep TWR below 90 +// Thrust (SL): ??? Kn +// Thrust (Vac): 801 kN +// ISP: 358 SL / 409 Vac calculated with RPA +// Burn Time: 500? +// Chamber Pressure: 5.67 MPa same as AJ-9 +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Nozzle Ratio: 24? +// Ignitions: 2? +// ================================================================================= +// LR87-LH2-VacuumUpgrade +// Speculative upgrade for use on later Saturn V missions +// +// Dry Mass: 1050? kg same as vacuum +// Thrust (SL): ??? Kn +// Thrust (Vac): 889 kN +// ISP: 289 SL / 434 Vac calculated with RPA +// Burn Time: 500? +// Chamber Pressure: 5.67 MPa same as AJ-9 +// Propellant: LOX / LH2 +// Prop Ratio: 5.5? +// Nozzle Ratio: 34? +// Ignitions: 3? +// ================================================================================= + +// Sources: + // http://www.astronautix.com/t/titanc.html -// Note: TitanC config is as of published numbers on engine performance -// for the Titan C application (simmed at 780psi, 12Ae/At). Speculative -// alternates and upgrades simmed by doubling area ratio and (for the upgrades) -// increasing efficiency and chamber pressure to later LR87 levels (5.7MPa). -// The VacuumUpgrade config uses the LR91 nozzle AR (49.2) -// Large increase in weight is from reignition equipment. +// Used by: + +// Notes: +// TitanC config is as of published numbers on engine performance +// for the Titan C application (simmed at 5 MPa, 12Ae/At). Astronautix +// mass figures are obviously wrong (suggesting 90+ TWR) so AJ-3 mass is +// used instead. +// Speculative alternates and upgrades simmed by increasing area ratio and +// increasing chamber pressure to match the most similar standard LR87 +// version. + +// ================================================== @PART[*]:HAS[#engineType[LR87LH2]]:FOR[RealismOverhaulEngines] { %title = #roLR87LH2Title //LR87-LH2 @@ -38,7 +108,7 @@ type = ModuleEngines configuration = LR87-LH2-TitanC modded = false - origMass = 0.74 + origMass = 0.839 CONFIG { name = LR87-LH2-TitanC @@ -51,13 +121,13 @@ PROPELLANT { name = LqdHydrogen - ratio = 0.745 + ratio = 0.7454 DrawGauge = True } PROPELLANT { name = LqdOxygen - ratio = 0.255 + ratio = 0.2546 } atmosphereCurve { @@ -87,22 +157,22 @@ maxThrust = 778.0 heatProduction = 175 ignitions = 2 - massMult = 1.14865 + massMult = 1.25149 PROPELLANT { name = LqdHydrogen - ratio = 0.745 + ratio = 0.7454 DrawGauge = True } PROPELLANT { name = LqdOxygen - ratio = 0.255 + ratio = 0.2546 } atmosphereCurve { - key = 0 419 - key = 1 312 + key = 0 421 + key = 1 315 } TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -126,18 +196,18 @@ minThrust = 801 // 180 klbf maxThrust = 801 heatProduction = 175 - massMult = 1.08109 + massMult = 1.11919 ignitions = 2 PROPELLANT { name = LqdHydrogen - ratio = 0.745 + ratio = 0.7454 DrawGauge = True } PROPELLANT { name = LqdOxygen - ratio = 0.255 + ratio = 0.2546 } atmosphereCurve { @@ -165,23 +235,23 @@ minThrust = 889.0 maxThrust = 889.0 heatProduction = 175 - massMult = 1.18 + massMult = 1.25149 ignitions = 3 PROPELLANT { name = LqdHydrogen - ratio = 0.745 + ratio = 0.7454 DrawGauge = True } PROPELLANT { name = LqdOxygen - ratio = 0.255 + ratio = 0.2546 } atmosphereCurve { key = 0 434 - key = 1 233 + key = 1 289 } TESTFLIGHT:NEEDS[TestLite|TestFlight] diff --git a/GameData/RealismOverhaul/Engine_Configs/LR87_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/LR87_Config.cfg index 7fe7c60424..c610d69fbf 100644 --- a/GameData/RealismOverhaul/Engine_Configs/LR87_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/LR87_Config.cfg @@ -25,7 +25,7 @@ // // Dry Mass: 739 kg // Thrust (SL): 215 klbf -// Thrust (Vac): 236.9 klbf +// Thrust (Vac): 236.9 klbf = 1053.8 kN // ISP: 258.8 SL / 285.2 Vac // Burn Time: 149.26 // Chamber Pressure: 5.48 MPa @@ -54,7 +54,7 @@ // LR87-AJ-9 // Titan III // -// Dry Mass: ??? Kg +// Dry Mass: 713 Kg // Thrust (SL): 1023.1 kN // Thrust (Vac): 1172.1 kN // ISP: 258 SL / 296 Vac diff --git a/GameData/RealismOverhaul/Engine_Configs/LR89_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/LR89_Config.cfg index 5a40b2b119..3e4afc4311 100644 --- a/GameData/RealismOverhaul/Engine_Configs/LR89_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/LR89_Config.cfg @@ -12,11 +12,11 @@ // Thrust (Vac): 617.4 kN // ISP: 230 SL / 265 Vac // Burn Time: 65 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 3.61 MPa estimated with RPA // Propellant: LOX / Ethanol90 // Prop Ratio: 1.375 // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 8? // Ignitions: 1 // ================================================================================= // LR43-NA-3 @@ -27,7 +27,7 @@ // Thrust (Vac): 756.8 kN // ISP: 245 SL / 278 Vac // Burn Time: ??? -// Chamber Pressure: ??? MPa +// Chamber Pressure: 3.92? MPa // Propellant: LOX / RP-1 // Prop Ratio: 2.25 // Throttle: N/A @@ -37,7 +37,7 @@ // LR89-NA-3 // MA-1 // -// Dry Mass: ??? Kg +// Dry Mass: 640.8 Kg // Thrust (SL): 658.8 kN // Thrust (Vac): 758.7 kN // ISP: 248 SL / 282 Vac @@ -52,7 +52,7 @@ // LR89-NA-5 // MA-2 // -// Dry Mass: ??? Kg +// Dry Mass: 828 Kg // Thrust (SL): 710.9 kN // Thrust (Vac): 831.4 kN // ISP: 251 SL / 290 Vac @@ -67,7 +67,7 @@ // LR89-NA-6 // MA-3 Upgrade // -// Dry Mass: ??? Kg +// Dry Mass: 883 Kg // Thrust (SL): 747.3 kN // Thrust (Vac): 846.6 kN // ISP: 256 SL / 290 Vac @@ -82,7 +82,7 @@ // LR89-NA-7.1 // MA-5.1 Atlas-Agena // -// Dry Mass: ??? Kg +// Dry Mass: 1018 Kg // Thrust (SL): 822.7 kN // Thrust (Vac): 931.7 kN // ISP: 258 SL / 292.2 Vac @@ -97,7 +97,7 @@ // LR89-NA-7.2 // MA-5.2 Atlas-Centaur // -// Dry Mass: ??? Kg +// Dry Mass: 1018 Kg // Thrust (SL): 839.6 kN // Thrust (Vac): 950.8 kN // ISP: 259.1 SL / 293.4 Vac diff --git a/GameData/RealismOverhaul/Engine_Configs/LR91_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/LR91_Config.cfg index c8b5b75661..7b88616a6a 100644 --- a/GameData/RealismOverhaul/Engine_Configs/LR91_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/LR91_Config.cfg @@ -6,7 +6,7 @@ // LR91-AJ-3 // Titan A / Titan I // -// Dry Mass: ??? +// Dry Mass: 590 kg // Thrust (SL): ??? // Thrust (vac): 80,603 + 975 (turbine) lbf = 362.88 - Verniers = 360.5 kN // ISP: ??? SL / 310 Vac @@ -21,7 +21,7 @@ // LR91-AJ-5 // Titan B / Titan II // -// Dry Mass: ??? +// Dry Mass: 500 kg // Thrust (SL): ??? // Thrust (vac): 100,000 + 865 (turbine) lbf = 448.67 - Verniers = 446.3 kN // ISP: ??? SL / 315 Vac @@ -36,7 +36,7 @@ // LR91-AJ-7 // Titan II GLV // -// Dry Mass: ??? +// Dry Mass: 565 kg // Thrust (SL): ??? // Thrust (vac): 100,000 + 865 (turbine) lbf = 448.67 - Verniers = 446.3 kN // ISP: ??? SL / 315 Vac @@ -51,7 +51,7 @@ // LR91-AJ-9 // Titan 3A/B/C // -// Dry Mass: ??? +// Dry Mass: 590 kg // Thrust (SL): ??? // Thrust (vac): 456.1 // ISP: ??? SL / 316 Vac @@ -66,7 +66,7 @@ // LR91-AJ-11 // Titan 3D/E // -// Dry Mass: ??? +// Dry Mass: 589 kg // Thrust (SL): ??? // Thrust (vac): 456.1 // ISP: ??? SL / 318 Vac @@ -81,7 +81,7 @@ // LR91-AJ-11A // Titan IV // -// Dry Mass: ??? +// Dry Mass: 589 kg // Thrust (SL): ??? // Thrust (vac): 474.6 // ISP: ??? SL / 325.5 Vac diff --git a/GameData/RealismOverhaul/Engine_Configs/LRBE_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/LRBE_Config.cfg index bb4a9fe983..5b9065e91f 100644 --- a/GameData/RealismOverhaul/Engine_Configs/LRBE_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/LRBE_Config.cfg @@ -27,7 +27,7 @@ // Thrust (Vac): 2473.5 kN // ISP: 327.7 SL / 352.7 Vac // Burn Time: 500 -// Chamber Pressure: ??? MPa (@ 111% throttle) +// Chamber Pressure: 21.02? MPa (@ 111% throttle) // Propellant: LOX / CH4 // Prop Ratio: 3.5 // Throttle: 100% to 67% diff --git a/GameData/RealismOverhaul/Engine_Configs/MR-80B_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/MR-80B_Config.cfg index e6e7021eea..3c23acdc61 100644 --- a/GameData/RealismOverhaul/Engine_Configs/MR-80B_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/MR-80B_Config.cfg @@ -10,13 +10,13 @@ // Dry Mass: 8.5 Kg // Thrust (SL): ??? kN // Thrust (Vac): 3.603 kN -// ISP: 204 SL / 223 Vac +// ISP: 79 SL / 223 Vac 204 is in Mars atmo, sl calculated with RPA // Burn Time: 350 // Chamber Pressure: 2.4 MPa // Propellant: Hydrazine // Prop Ratio: N/A // Throttle: 100% to ~8% -// Nozzle Ratio: 16.7 +// Nozzle Ratio: 27.2 // Ignitions: Infinite // ================================================================================= @@ -24,6 +24,7 @@ // http://matthewwturner.com/uah/IPT2008_summer/baselines/LOW%20Files/Payload/Downloads/AIAA-2007-5481-979.pdf // https://www.rocket.com/sites/default/files/documents/Capabilities/PDFs/Monopropellant%20Data%20Sheets.pdf +// https://www.rocket.com/sites/default/files/documents/In-Space%20Data%20Sheets%204.8.20.pdf // Used by: @@ -82,7 +83,7 @@ atmosphereCurve { key = 0 223 - key = 1 204 + key = 1 79 } ullage = False pressureFed = True @@ -99,6 +100,14 @@ //Extremely simple and reliable monopropellant engines ratedBurnTime = 1000 //tested over 800 seconds, round up to 1000 ratedContinuousBurnTime = 215 //longest single burn + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + ignitionReliabilityStart = 0.99 ignitionReliabilityEnd = 0.999 cycleReliabilityStart = 0.99 diff --git a/GameData/RealismOverhaul/Engine_Configs/Merlin1_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Merlin1_Config.cfg index 7a94d4a6de..f42da90b2f 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Merlin1_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Merlin1_Config.cfg @@ -37,7 +37,7 @@ // Merlin 1BVac // // -// Dry Mass: ??? Kg +// Dry Mass: 912? Kg // Thrust (SL): ??? kN // Thrust (Vac): 421.6 kN // ISP: 161 SL / 332.1 Vac SL calculated with RPA diff --git a/GameData/RealismOverhaul/Engine_Configs/NAA75_110_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/NAA75_110_Config.cfg index 32f68a1c17..270ff38f55 100644 --- a/GameData/RealismOverhaul/Engine_Configs/NAA75_110_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/NAA75_110_Config.cfg @@ -16,7 +16,7 @@ // Propellant: LOX / Ethanol75 // Prop Ratio: 1.354 // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 3.61? // Ignitions: 1 // ================================================================================= // A-6 @@ -34,20 +34,19 @@ // Nozzle Ratio: 3.61 // Ignitions: 1 // ================================================================================= -// A-7 -// Redstone, Mercury-Redstone -// -// Dry Mass: 740 Kg -// Thrust (SL): 346.6 kN (78klbf) -// Thrust (Vac): 395.5 kN -// ISP: 218 SL / 249 Vac -// Burn Time: 143 for MRLV -// Chamber Pressure: 2.19 MPa -// Propellant: LOX / Ethanol75 -// Prop Ratio: 1.354 -// Nozzle Ratio: 3.61 -// Ignitions: 1 -// +// A-7 +// Redstone, Mercury-Redstone +// +// Dry Mass: 740 Kg +// Thrust (SL): 346.6 kN (78klbf) +// Thrust (Vac): 395.5 kN +// ISP: 218 SL / 249 Vac +// Burn Time: 143 for MRLV +// Chamber Pressure: 2.19 MPa +// Propellant: LOX / Ethanol75 +// Prop Ratio: 1.354 +// Nozzle Ratio: 3.61 +// Ignitions: 1 // ================================================================================= // A-6H // Jupiter-C / Juno I diff --git a/GameData/RealismOverhaul/Engine_Configs/NK33_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/NK33_Config.cfg index b0e32a7fdc..36584936ad 100644 --- a/GameData/RealismOverhaul/Engine_Configs/NK33_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/NK33_Config.cfg @@ -4,50 +4,80 @@ // Manufacturer: SNTK Kuznetsov // // ================================================================================= -// NK-15 +// NK-15 (11D51) // N-1 // -// Dry Mass: 1247 Kg +// Dry Mass: 1247 Kg [11] // Thrust (SL): ??? kN -// Thrust (Vac): 1681 kN -// ISP: 284 SL / 318 Vac -// Burn Time: 180 -// Chamber Pressure: ??? MPa +// Thrust (Vac): 1543.6 kN [3/11] +// ISP: 284 SL / 318 Vac [3/4] +// Burn Time: 180? +// Chamber Pressure: 14.5 MPa [11] // Propellant: CooledLOX / CooledRG-1 -// Prop Ratio: 2.5 -// Throttle: 100% to 50% -// Nozzle Ratio: ??? +// Prop Ratio: 2.5 [3/4] +// Throttle: 100% to 50%? +// Nozzle Ratio: 27.7 [3/8/10] // Ignitions: 1 // ================================================================================= -// NK-33 +// NK-33 (11D111) // N-1F, Soyuz 2.1v // -// Dry Mass: 1222 Kg +// Dry Mass: 1240 Kg [6] // Thrust (SL): ??? kN -// Thrust (Vac): 1766 kN -// ISP: 297 SL / 331 Vac -// Burn Time: 240 -// Chamber Pressure: ??? MPa +// Thrust (Vac): 1765.7 kN [6] (1681.6 kN @100%) +// ISP: 297.23 SL / 331 Vac [6/11] +// Burn Time: 365 [6] +// Chamber Pressure: 14.83 MPa [6/11] (14.54 MPa @100% [5/8/10]) // Propellant: CooledLOX / CooledRG-1 -// Prop Ratio: 2.6 -// Throttle: 105% to 50% -// Nozzle Ratio: ??? -// Ignitions: 2 +// Prop Ratio: 2.62 [6] 2.59 +// Throttle: 105% to 50% [6] +// Nozzle Ratio: 27.7 [3/8/10] +// Ignitions: 1 +// ================================================================================= +// AJ26-58 +// Kistler K-1 +// +// Dry Mass: 1407.9 Kg [10] +// Thrust (SL): ??? kN +// Thrust (Vac): 1753.3 kN [6] (1685.9 kN @100%) +// ISP: 297.23 SL / 331 Vac [6/11] +// Burn Time: 365 [6] +// Chamber Pressure: 14.83 MPa [6/11] (14.54 MPa @100% [5/8/10]) +// Propellant: CooledLOX / CooledRG-1 +// Prop Ratio: 2.59 [8] +// Throttle: 104% to 55% [5] +// Nozzle Ratio: 27.7 [3/8/10] +// Ignitions: 1 [10] +// ================================================================================= +// AJ26-59 +// Kistler K-1, restartable +// +// Dry Mass: 1458.8 Kg [10] +// Thrust (SL): ??? kN +// Thrust (Vac): 1753.3 kN [6] (1685.9 kN @100%) +// ISP: 297.23 SL / 331 Vac [6/11] +// Burn Time: 365 [6] +// Chamber Pressure: 14.83 MPa [6/11] (14.54 MPa @100% [5/8/10]) +// Propellant: CooledLOX / CooledRP-1 +// Prop Ratio: 2.59 [8] +// Throttle: 104% to 55% [5] +// Nozzle Ratio: 27.7 [3/8/10] +// Ignitions: 2 [10] // ================================================================================= // AJ26-62 // Antares // -// Dry Mass: 1459 Kg +// Dry Mass: 1459? kg // Thrust (SL): ??? kN // Thrust (Vac): 1815 kN -// ISP: 301.6 SL / 331.9 Vac +// ISP: 301.6 SL / 331.9 Vac [9] // Burn Time: 240 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 16.42 MPa [9] // Propellant: CooledLOX / CooledRP-1 -// Prop Ratio: 2.7 -// Throttle: 100% to 50% -// Nozzle Ratio: ??? -// Ignitions: 2 +// Prop Ratio: 2.7 [9] +// Throttle: 108% to 58% [9] +// Nozzle Ratio: 27.7? +// Ignitions: 1 // ================================================================================= // Sources: @@ -55,13 +85,16 @@ // [1] http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20000088626.pdf // [2] http://www.scribd.com/doc/46957813/Aviadvigatel // [3] http://www.b14643.de/Spacerockets_1/East_Europe_2/N-1/NK/index.htm - dubious -// [4] https://web.archive.org/web/20130703154050/http://www.spaceandtech.com/spacedata/engines/nk33_specs.shtml -// [5] http://www.lpre.de/sntk/NK-33/index.htm -// [6] http://history.nasa.gov/SP-4408pt1.pdf -// [7] http://lpre.de/resources/articles/AIAA-1998-3361.pdf - good on data -// [8] https://web.archive.org/web/20140115161002/http://www.orbital.com/NewsInfo/Publications/Antares%20UG.pdf -// [9] http://sites.nationalacademies.org/cs/groups/depssite/documents/webpage/deps_068011.pdf - AJ26-62 reliability -// [10] Anisimov: "EVOLUTION OF THE NK-33 AND NK-43 REUSABLE LOX/KEROSENE ENGINES" +// [4] http://www.b14643.de/Spacerockets/Specials/Russian_Rocket_engines/engines.htm +// [5] https://web.archive.org/web/20130703154050/http://www.spaceandtech.com/spacedata/engines/nk33_specs.shtml +// [6] http://www.lpre.de/sntk/NK-33/index.htm +// [7] http://history.nasa.gov/SP-4408pt1.pdf +// [8] http://lpre.de/resources/articles/AIAA-1998-3361.pdf - good on data +// [9] https://web.archive.org/web/20140115161002/http://www.orbital.com/NewsInfo/Publications/Antares%20UG.pdf +// [10] http://sites.nationalacademies.org/cs/groups/depssite/documents/webpage/deps_068011.pdf - AJ26-62 reliability +// [11] http://www.lpre.de/sntk/index.htm +// [12] Anisimov: "EVOLUTION OF THE NK-33 AND NK-43 REUSABLE LOX/KEROSENE ENGINES" +// [13] http://lpre.de/resources/articles/LPRE%20DESIGNED%20BY%20KUZNETSOV%20COMPANY.pdf // Used by: @@ -72,9 +105,9 @@ { %title = #roNK33Title //NK-15/33 %manufacturer = #roMfrNPOKuznetstov - %description = #roNK33Desc //The NK-15 and NK-33 were originally built in the 1960s/early 1970s for the Soviet N1 and then N1F rocket, respectively. Though the N1F was scrapped, the engines survived. Aerojet acquired several NK-33 engines in the 1990s and refurbished them as AJ26-62 engines for Orbital Science's Antares launch vehicle. Modifications made by Aerojet included increasing rated thrust and equipping the engines to support gimballing. + %description = #roNK33Desc - @tags ^= :$: USSR okb-276 kuznetsov aerojet nk-15 nk-33 aj26-62 liquid pump booster kerosene lqdoxygen + @tags ^= :$: USSR okb-276 kuznetsov aerojet nk-15 nk-33 aj26-58 aj26-59 aj26-62 liquid pump booster kerosene lqdoxygen %specLevel = operational @@ -99,16 +132,18 @@ name = ModuleEngineConfigs configuration = NK-15 modded = false - origMass = 1.222 + origMass = 1.240 CONFIG { name = NK-15 description = Developed as the first stage engine of the N-1 moon rocket. Gimbal, differential throttle. specLevel = operational - maxThrust = 1681 // 378,000 Ibf - minThrust = 841 + maxThrust = 1543.6 + minThrust = 771.8 heatProduction = 100 - massMult = 1.21812 // 1.020458 (NK-15, no gimbal) * 1.1937 (increase % for gimbal) + massMult = 1.1418 // 1.0056 (NK-15, no gimbal) * 1.1354 (increase % for gimbal) + ullage = True + ignitions = 1 gimbalRange = 6 // 2.5 O/F mass ratio (b14643.de) PROPELLANT @@ -124,12 +159,10 @@ } atmosphereCurve { - key = 0 331 - key = 1 297 + key = 0 318 + key = 1 284 } - ullage = True - ignitions = 1 IGNITOR_RESOURCE { name = ElectricCharge @@ -175,10 +208,12 @@ name = NK-15-Original-NoGimbal description = Developed as the first stage engine of the N-1 moon rocket. No gimbal, differential throttle. specLevel = operational - maxThrust = 1681 - minThrust = 841 + maxThrust = 1543.6 + minThrust = 771.8 heatProduction = 100 - massMult = 1.020458 + massMult = 1.0056 + ullage = True + ignitions = 1 gimbalRange = 0 // 2.5 O/F mass ratio (b14643.de) PROPELLANT @@ -194,12 +229,10 @@ } atmosphereCurve { - key = 0 331 - key = 1 297 + key = 0 318 + key = 1 284 } - ullage = True - ignitions = 1 IGNITOR_RESOURCE { name = ElectricCharge @@ -237,31 +270,31 @@ name = NK-33 description = Developed as an upgrade to the NK-15, and then abandoned with the cancellation of the N-1. Revived following the fall of the USSR, now used on Soyuz 2.1v. Gimbal, differential throttle. specLevel = operational - maxThrust = 1766 //105% rated thrust - minThrust = 841 + maxThrust = 1765.7 + minThrust = 840.8 heatProduction = 100 - massMult = 1.1937 // 1.459t, mass value from AJ26-59 + massMult = 1.1354 //(increase % for gimbal) + ullage = True + ignitions = 1 gimbalRange = 6 - // 2.6 O/F mass ratio (b14643.de) + // 2.62 O/F mass ratio PROPELLANT { name = CooledRG-1 - ratio = 0.3576 + ratio = 0.3558 DrawGauge = true } PROPELLANT { name = CooledLqdOxygen - ratio = 0.6424 + ratio = 0.6442 } atmosphereCurve { key = 0 331 - key = 1 297 - } + key = 1 297.23 + } - ullage = True - ignitions = 2 IGNITOR_RESOURCE { name = ElectricCharge @@ -270,7 +303,7 @@ IGNITOR_RESOURCE { name = TEATEB - amount = 1 + amount = 2 } //due to limited data, data from both the NK-33 and AJ26-62 is used @@ -282,7 +315,7 @@ TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 450 //Tested to 450 seconds - ratedBurnTime = 240 //based on Antares and Soyuz 2-1v burn times. + ratedBurnTime = 365 safeOverburn = true // assume roughly exponential relationship between chamber pressure and lifespan @@ -304,31 +337,31 @@ name = NK-33-Original-NoGimbal description = Developed as an upgrade to the NK-15, and then abandoned with the cancellation of the N-1. Revived following the fall of the USSR, now used on Soyuz 2.1v. No gimbal, differential throttle. specLevel = operational - maxThrust = 1766 - minThrust = 841 + maxThrust = 1765.7 + minThrust = 840.8 heatProduction = 100 - massMult = 1 + massMult = 1.0000 + ullage = True + ignitions = 1 gimbalRange = 0 - // 2.6 O/F mass ratio (b14643.de) + // 2.62 O/F mass ratio PROPELLANT { name = CooledRG-1 - ratio = 0.3576 + ratio = 0.3558 DrawGauge = true } PROPELLANT { name = CooledLqdOxygen - ratio = 0.6424 + ratio = 0.6442 } atmosphereCurve { key = 0 331 - key = 1 297 + key = 1 297.23 } - ullage = True - ignitions = 2 IGNITOR_RESOURCE { name = ElectricCharge @@ -337,13 +370,13 @@ IGNITOR_RESOURCE { name = TEATEB - amount = 1 + amount = 2 } TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 450 //Tested to 450 seconds - ratedBurnTime = 240 + ratedBurnTime = 365 safeOverburn = true // assume roughly exponential relationship between chamber pressure and lifespan @@ -361,15 +394,139 @@ } } CONFIG + { + name = AJ26-58 + description = The NK-33 design was sold to Aerojet in the mid 1990s. Aerojet modified it to create the AJ26. This is a single start reusable version, intended for the K-1 first stage. + specLevel = prototype + maxThrust = 1753.3 + minThrust = 927.2 + heatProduction = 100 + massMult = 1.1354 + ignitions = 1 + ullage = True + gimbalRange = 6 + PROPELLANT + { + name = CooledRP-1 + ratio = 0.3659 + DrawGauge = true + } + PROPELLANT + { + name = CooledLqdOxygen + ratio = 0.6341 + } + atmosphereCurve + { + key = 0 331 + key = 1 297.23 + } + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + IGNITOR_RESOURCE + { + name = TEATEB + amount = 2 + } + + //0.997 target reliability + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 5870 //5870 seconds between overhauls + ratedBurnTime = 365 + safeOverburn = true + overburnPenalty = 1.5 //rated for reuse, but wasn't terribly reliable + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + ignitionReliabilityStart = 0.95 + ignitionReliabilityEnd = 0.997 + cycleReliabilityStart = 0.95 + cycleReliabilityEnd = 0.997 + techTransfer = AJ26-59,NK-33,NK-33-Original-NoGimbal,NK-15,NK-15-Original-NoGimbal:50 + } + } + CONFIG + { + name = AJ26-59 + description = The NK-33 design was sold to Aerojet in the mid 1990s. Aerojet modified it to create the AJ26. This is a two start reusable version, intended for the K-1 first stage. + specLevel = prototype + maxThrust = 1753.3 + minThrust = 927.2 + heatProduction = 100 + massMult = 1.1765 + ignitions = 2 + ullage = True + gimbalRange = 6 + PROPELLANT + { + name = CooledRP-1 + ratio = 0.3659 + DrawGauge = true + } + PROPELLANT + { + name = CooledLqdOxygen + ratio = 0.6341 + } + atmosphereCurve + { + key = 0 331 + key = 1 297.23 + } + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + IGNITOR_RESOURCE + { + name = TEATEB + amount = 1 + } + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 5870 //5870 seconds between overhauls + ratedBurnTime = 365 + safeOverburn = true + overburnPenalty = 1.5 //rated for reuse, but wasn't terribly reliable + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + ignitionReliabilityStart = 0.95 + ignitionReliabilityEnd = 0.997 + cycleReliabilityStart = 0.95 + cycleReliabilityEnd = 0.997 + techTransfer = AJ26-58,NK-33,NK-33-Original-NoGimbal,NK-15,NK-15-Original-NoGimbal:50 + } + } + CONFIG { name = AJ26-62 - description = The NK-33 design was sold to Aerojet in the mid 1990s. Aerojet modified it to create the AJ26. Formerly used for the Antares-100 series + description = The NK-33 design was sold to Aerojet in the mid 1990s. Aerojet modified it to create the AJ26. Non-reusable version for Antares. specLevel = operational maxThrust = 1815 - minThrust = 941.92 + minThrust = 977.82 heatProduction = 100 - massMult = 1.1937 - ignitions = 2 + massMult = 1.1766 + ignitions = 1 + ullage = True gimbalRange = 6 // 2.7 O/F mass ratio (Antares UG) PROPELLANT @@ -389,8 +546,6 @@ key = 1 301.6 // Antares UG } - ullage = True - ignitions = 2 IGNITOR_RESOURCE { name = ElectricCharge @@ -399,12 +554,14 @@ IGNITOR_RESOURCE { name = TEATEB - amount = 1 + amount = 2 } + //0.988 target reliability + //pretty close to actual reliability TESTFLIGHT:NEEDS[TestLite|TestFlight] { - testedBurnTime = 2400 //Tested to 450 seconds. Upgraded for reuse in K-1, with many modifications to increase reliability. Rate for 10 flights? + testedBurnTime = 450 ratedBurnTime = 240 safeOverburn = true overburnPenalty = 1.5 //rated for reuse, but wasn't terribly reliable @@ -420,7 +577,7 @@ ignitionReliabilityEnd = 0.980556 cycleReliabilityStart = 0.876852 cycleReliabilityEnd = 0.980556 - techTransfer = NK-15,NK-15-Original-NoGimbal,NK-33,NK-33-Original-NoGimbal:50 + techTransfer = AJ26-59,AJ26-58,NK-33,NK-33-Original-NoGimbal,NK-15,NK-15-Original-NoGimbal:50 } } } diff --git a/GameData/RealismOverhaul/Engine_Configs/NK43_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/NK43_Config.cfg index f8ff2fb09d..809a38a856 100644 --- a/GameData/RealismOverhaul/Engine_Configs/NK43_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/NK43_Config.cfg @@ -4,44 +4,67 @@ // Manufacturer: SNTK Kuznetsov // // ================================================================================= -// NK-15V +// NK-15V (11D52) // N-1 // -// Dry Mass: 1345 Kg +// Dry Mass: 1396 Kg [11] // Thrust (SL): ??? kN -// Thrust (Vac): 1755 kN -// ISP: 255 SL / 346 Vac SL calculated with RPA +// Thrust (Vac): 1647.5 kN [3/4] +// ISP: 259 SL / 325 Vac [3/4] SL calculated with RPA // Burn Time: 240 -// Chamber Pressure: 14.57? MPa +// Chamber Pressure: 14.5 MPa [11] // Propellant: CooledLOX / CooledRG-1 -// Prop Ratio: 2.5 -// Throttle: 100% to 50% -// Nozzle Ratio: 80? +// Prop Ratio: 2.5 [3/4] +// Throttle: 100% to 50%? +// Nozzle Ratio: 51? NK-15V was smaller and had worse ISP. Assume lower area ratio based on diameter ratio (2/2.5 m) // Ignitions: 1 // ================================================================================= -// NK-43 +// NK-43 (11D112) // N-1 // -// Dry Mass: 1396 Kg +// Dry Mass: 1396 Kg [11/13] // Thrust (SL): ??? kN -// Thrust (Vac): 1755 kN -// ISP: 254 SL / 346 Vac SL calculated with RPA -// Burn Time: 360 -// Chamber Pressure: 14.57 MPa +// Thrust (Vac): 1757.4 kN [3/4/6/11] +// ISP: 251 SL / 346 Vac SL calculated with RPA +// Burn Time: 346 +// Chamber Pressure: 14.57 MPa [3/4/6/11] // Propellant: CooledLOX / CooledRG-1 -// Prop Ratio: 2.8 -// Throttle: 100% to 50% -// Nozzle Ratio: 80? -// Ignitions: 3 +// Prop Ratio: 2.8 [3/4/6] +// Throttle: 100% to 50%? +// Nozzle Ratio: 79.7 [10] +// Ignitions: 3??? +// ================================================================================= +// AJ26-60 +// Kistler K-1 +// +// Dry Mass: 1473 Kg [5] +// Thrust (SL): ??? kN +// Thrust (Vac): 1823.9 kN [5] (1753.8 kN @100%?) +// ISP: 251 SL / 346 Vac SL calculated with RPA +// Burn Time: 346 +// Chamber Pressure: 14.54 MPa [5] +// Propellant: CooledLOX / CooledRP-1 +// Prop Ratio: 2.8 [3/4] +// Throttle: 104% to 55%? [5] +// Nozzle Ratio: 79.7 [10] +// Ignitions: 1 [5] // ================================================================================= // Sources: -// FIXME: NK15 stats from http://www.b14643.de/Spacerockets_1/East_Europe_2/N-1/Propulsion/engines.htm, may be unreliable -// http://www.b14643.de/Spacerockets_1/East_Europe_2/N-1/NK/index.htm (more reliable) -// https://web.archive.org/web/20130703154050/http://www.spaceandtech.com/spacedata/engines/nk33_specs.shtml -// http://www.lpre.de/sntk/NK-33/index.htm -// Assume NK-15V has same performance stats as NK-43(as stated in multiple sources) when no other references are found. +// [1] http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20000088626.pdf +// [2] http://www.scribd.com/doc/46957813/Aviadvigatel +// [3] http://www.b14643.de/Spacerockets_1/East_Europe_2/N-1/NK/index.htm - dubious +// [4] http://www.b14643.de/Spacerockets/Specials/Russian_Rocket_engines/engines.htm +// [5] https://web.archive.org/web/20130703154050/http://www.spaceandtech.com/spacedata/engines/nk33_specs.shtml +// [6] http://www.lpre.de/sntk/NK-33/index.htm +// [7] http://history.nasa.gov/SP-4408pt1.pdf +// [8] http://lpre.de/resources/articles/AIAA-1998-3361.pdf - good on data +// [9] https://web.archive.org/web/20140115161002/http://www.orbital.com/NewsInfo/Publications/Antares%20UG.pdf +// [10] http://sites.nationalacademies.org/cs/groups/depssite/documents/webpage/deps_068011.pdf - AJ26-62 reliability +// [11] http://www.lpre.de/sntk/index.htm +// [12] Anisimov: "EVOLUTION OF THE NK-33 AND NK-43 REUSABLE LOX/KEROSENE ENGINES" +// [13] http://lpre.de/resources/articles/LPRE%20DESIGNED%20BY%20KUZNETSOV%20COMPANY.pdf // Used by: @@ -52,7 +75,7 @@ { %title = #roNK43Title //NK-15V/43 %manufacturer = #roMfrNPOKuznetstov - %description = #roNK43Desc //Originally designed and built for the N1F, the NK-43 is a derivative of the NK-33 with longer bell and restart capability for upper stages. + %description = #roNK43Desc @tags ^= :$: USSR okb-276 kuznetsov nk-15v nk-43 liquid pump upper kerosene lqdoxygen @@ -85,10 +108,12 @@ name = NK-15V description = Developed as the second stage engine of the N-1 moon rocket. Gimbal, differential throttle. specLevel = operational - maxThrust = 1755 - minThrust = 877.5 + maxThrust = 1647.5 + minThrust = 823.75 heatProduction = 100 - massMult = 1.15009 // 0.963467 (NK-15V, no gimbal) * 1.1937 (increase % for gimbal) + massMult = 1.0552 //1.0552 (increase % for gimbal) + ullage = True + ignitions = 1 gimbalRange = 6 // 2.5 O/F mass ratio (b14643.de) PROPELLANT @@ -104,12 +129,10 @@ } atmosphereCurve { - key = 0 346 - key = 1 255 + key = 0 325 + key = 1 259 } - ullage = True - ignitions = 1 IGNITOR_RESOURCE { name = ElectricCharge @@ -148,10 +171,12 @@ name = NK-15V-Original-NoGimbal description = Developed as the second stage engine of the N-1 moon rocket. No gimbal, differential throttle. specLevel = operational - maxThrust = 1755 - minThrust = 877.5 + maxThrust = 1647.5 + minThrust = 823.75 heatProduction = 100 - massMult = 0.963467 + massMult = 1.00 + ullage = True + ignitions = 1 gimbalRange = 0 // 2.5 O/F mass ratio (b14643.de) PROPELLANT @@ -167,12 +192,10 @@ } atmosphereCurve { - key = 0 346 - key = 1 255 + key = 0 325 + key = 1 259 } - ullage = True - ignitions = 1 IGNITOR_RESOURCE { name = ElectricCharge @@ -211,10 +234,12 @@ name = NK-43 description = Developed as an upgrade to the NK-15V, and then abandoned with the cancellation of the N-1. Gimbal, differential throttle. specLevel = prototype - minThrust = 877.5 - maxThrust = 1755 + minThrust = 878.7 + maxThrust = 1757.4 heatProduction = 100 - massMult = 1.1937 // 1 (NK-43, no gimbal) * 1.1937 (increase % for gimbal) + massMult = 1.0552 //1.0552 (increase % for gimbal) + ullage = True + ignitions = 3 gimbalRange = 6 // 2.8 O/F mass ratio (b14643.de) PROPELLANT @@ -231,11 +256,9 @@ atmosphereCurve { key = 0 346 - key = 1 254 + key = 1 251 } - ullage = True - ignitions = 3 IGNITOR_RESOURCE { name = ElectricCharge @@ -250,7 +273,7 @@ TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 450 //Tested to 450 seconds, same as NK-33 - ratedBurnTime = 360 + ratedBurnTime = 346 safeOverburn = true // assume roughly exponential relationship between chamber pressure and lifespan @@ -272,10 +295,12 @@ name = NK-43-Original-NoGimbal description = Developed as an upgrade to the NK-15, and then abandoned with the cancellation of the N-1. No gimbal, differential throttle. specLevel = prototype - maxThrust = 1755 - minThrust = 877.5 + minThrust = 878.7 + maxThrust = 1757.4 heatProduction = 100 massMult = 1 + ullage = True + ignitions = 3 gimbalRange = 0 // 2.8 O/F mass ratio (b14643.de) PROPELLANT @@ -292,11 +317,9 @@ atmosphereCurve { key = 0 346 - key = 1 254 + key = 1 251 } - ullage = True - ignitions = 3 IGNITOR_RESOURCE { name = ElectricCharge @@ -311,7 +334,7 @@ TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 450 //Tested to 450 seconds, same as NK-33 - ratedBurnTime = 360 + ratedBurnTime = 346 safeOverburn = true // assume roughly exponential relationship between chamber pressure and lifespan @@ -328,6 +351,67 @@ techTransfer = NK-43,NK-33,NK-33-Original-NoGimbal:100&NK-15V,NK-15V-Original-NoGimbal:50 } } + CONFIG + { + name = AJ26-60 + description = The NK-33 design was sold to Aerojet in the mid 1990s. Aerojet modified it to create the AJ26. This is a single start reusable version, intended for the K-1 second stage. + specLevel = prototype + minThrust = 964.59 + maxThrust = 1823.9 + heatProduction = 100 + massMult = 1.0552 //1.0552 (increase % for gimbal) + ullage = True + ignitions = 1 + gimbalRange = 6 + // 2.8 O/F mass ratio (b14643.de) + PROPELLANT + { + name = CooledRG-1 + ratio = 0.3408 + DrawGauge = true + } + PROPELLANT + { + name = CooledLqdOxygen + ratio = 0.6592 + } + atmosphereCurve + { + key = 0 346 + key = 1 251 + } + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + IGNITOR_RESOURCE + { + name = TEATEB + amount = 3 + } + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 5870 //5870 seconds between overhauls + ratedBurnTime = 346 + safeOverburn = true + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + ignitionReliabilityStart = 0.95 + ignitionReliabilityEnd = 0.997 + cycleReliabilityStart = 0.95 + cycleReliabilityEnd = 0.997 + techTransfer = NK-43,NK-43-Original-NoGimbal,NK-33,NK-33-Original-NoGimbal:100&NK-15V,NK-15V-Original-NoGimbal:50 + } + } } RESOURCE diff --git a/GameData/RealismOverhaul/Engine_Configs/NK9V_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/NK9V_Config.cfg index 4f37372077..fe5f55791f 100644 --- a/GameData/RealismOverhaul/Engine_Configs/NK9V_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/NK9V_Config.cfg @@ -4,89 +4,97 @@ // Manufacturer: SNTK Kuznetsov // // ================================================================================= -// NK-9V -// +// NK-9V (8D517V?) +// GR-1, N1 // -// Dry Mass: 640 Kg +// Dry Mass: 640? Kg // Thrust (SL): ??? kN -// Thrust (Vac): 451.1 kN -// ISP: 219 SL / 345 Vac SL calculated with RPA +// Thrust (Vac): 451.1 kN [3/4/11] +// ISP: 237 SL / 345 Vac [3/4/11], SL calculated with RPA // Burn Time: 240 -// Chamber Pressure: 7.85 MPa +// Chamber Pressure: 10.34 MPa [3/13] // Propellant: LOX / RG-1 -// Prop Ratio: 2.5 +// Prop Ratio: 2.5 [3/4] // Throttle: N/A -// Nozzle Ratio: 80? +// Nozzle Ratio: 79.7? // Ignitions: 1 // ================================================================================= -// NK-21 +// NK-21 (11D59) // N1 // -// Dry Mass: ??? Kg +// Dry Mass: 584? Kg // Thrust (SL): ??? kN -// Thrust (Vac): 400 kN -// ISP: ??? SL / 340 Vac -// Burn Time: 240 -// Chamber Pressure: ??? MPa +// Thrust (Vac): 402.1 kN [3/4] +// ISP: 225 SL / 340 Vac [3/4], SL calculated with RPA +// Burn Time: 450? +// Chamber Pressure: 9.20 MPa [4] // Propellant: CooledLOX / CooledRG-1 -// Prop Ratio: 2.5 -// Throttle: 100% to 60% -// Nozzle Ratio: ??? +// Prop Ratio: 2.5 [3/4] +// Throttle: 100% to 60%? +// Nozzle Ratio: 79.7? // Ignitions: 1 // ================================================================================= -// NK-19 +// NK-19 (11D53) // N1 // -// Dry Mass: ??? Kg +// Dry Mass: 721.6? Kg // Thrust (SL): ??? kN -// Thrust (Vac): 400 kN -// ISP: ??? SL / 353 Vac -// Burn Time: 240 -// Chamber Pressure: ??? MPa +// Thrust (Vac): 451.1 kN [3/4/11] +// ISP: 230 SL / 345 Vac [3/4], SL calculated with RPA +// Burn Time: 450? +// Chamber Pressure: 9.20 MPa [4] // Propellant: CooledLOX / CooledRG-1 // Prop Ratio: 2.5 -// Throttle: 100% to 60% -// Nozzle Ratio: ??? +// Throttle: 100% to 60%? +// Nozzle Ratio: 79.7? // Ignitions: 1 // ================================================================================= -// NK-39 +// NK-39 (11D113) // N1F // -// Dry Mass: 700 Kg +// Dry Mass: 584 Kg [11] // Thrust (SL): ??? kN -// Thrust (Vac): 400 kN -// ISP: 235 SL / 352 Vac SL calculated with RPA -// Burn Time: 240 -// Chamber Pressure: 9.20 MPa +// Thrust (Vac): 407 kN [3/4/11] +// ISP: 213 SL / 352 Vac [3/4/11] SL calculated with RPA +// Burn Time: 600? +// Chamber Pressure: 9.20 MPa [3/4/13] // Propellant: CooledLOX / CooledRG-1 -// Prop Ratio: 2.6 +// Prop Ratio: 2.62 same as NK-33? // Throttle: 100% to 60% -// Nozzle Ratio: 80? +// Nozzle Ratio: 114 [10] // Ignitions: 1 // ================================================================================= -// NK-31 +// NK-31 (11D114) // N1F // -// Dry Mass: 722 Kg +// Dry Mass: 721.6 Kg [13] // Thrust (SL): ??? kN -// Thrust (Vac): 402 kN -// ISP: 236 SL / 353 Vac SL calculated with RPA -// Burn Time: 240 -// Chamber Pressure: 9.20 MPa +// Thrust (Vac): 402.1 kN [3/4/13] +// ISP: 214 SL / 353 Vac [3/4/11/13] SL calculated with RPA +// Burn Time: 600? +// Chamber Pressure: 9.20 MPa [3/4/13] // Propellant: CooledLOX / CooledRG-1 -// Prop Ratio: 2.6 +// Prop Ratio: 2.62 same as NK-33? // Throttle: 100% to 60% -// Nozzle Ratio: 80? -// Ignitions: 2 +// Nozzle Ratio: 114 [10] +// Ignitions: 2? // ================================================================================= // Sources: - -// http://www.scribd.com/doc/7362263/Russian-Liquid-Propellant-Engines#scribd -// http://www.b14643.de/Spacerockets_1/East_Europe_2/N-1/NK/index.htm -// http://www.k204.ru/books/Aviadvigatel2.pdf -// http://www.lpre.de/sntk/ +// [1] http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20000088626.pdf +// [2] http://www.scribd.com/doc/46957813/Aviadvigatel +// [3] http://www.b14643.de/Spacerockets_1/East_Europe_2/N-1/NK/index.htm - dubious +// [4] http://www.b14643.de/Spacerockets/Specials/Russian_Rocket_engines/engines.htm +// [5] https://web.archive.org/web/20130703154050/http://www.spaceandtech.com/spacedata/engines/nk33_specs.shtml +// [6] http://www.lpre.de/sntk/NK-33/index.htm +// [7] http://history.nasa.gov/SP-4408pt1.pdf +// [8] http://lpre.de/resources/articles/AIAA-1998-3361.pdf - good on data +// [9] https://web.archive.org/web/20140115161002/http://www.orbital.com/NewsInfo/Publications/Antares%20UG.pdf +// [10] http://sites.nationalacademies.org/cs/groups/depssite/documents/webpage/deps_068011.pdf - AJ26-62 reliability +// [11] http://www.lpre.de/sntk/index.htm +// [12] Anisimov: "EVOLUTION OF THE NK-33 AND NK-43 REUSABLE LOX/KEROSENE ENGINES" +// [13] http://lpre.de/resources/articles/LPRE%20DESIGNED%20BY%20KUZNETSOV%20COMPANY.pdf // Used by: // Bobcat @@ -131,11 +139,12 @@ name = NK-9V description = Original vacuum version of NK-9 for the GR-1 rocket. specLevel = prototype - maxThrust = 451.1 // b14643 + maxThrust = 451.1 minThrust = 451.1 heatProduction = 205 - massMult = 1 - // 2.5 O/F mass ratio (b14643.de) + massMult = 1.0 + ullage = True + ignitions = 1 PROPELLANT { name = RG-1 @@ -150,11 +159,9 @@ atmosphereCurve { key = 0 345 - key = 1 219 + key = 1 237 } - ullage = True - ignitions = 1 IGNITOR_RESOURCE { name = ElectricCharge @@ -186,9 +193,12 @@ name = NK-21 description = NK-9V rerated for N1 Block V use. No gimbal, differential throttle. specLevel = operational - maxThrust = 400 // b14643 - minThrust = 240 // assume 60% throttle. + maxThrust = 402.1 + minThrust = 241 // assume 60% throttle. heatProduction = 205 + massMult = 0.9125 + ullage = True + ignitions = 1 // 2.5 O/F mass ratio (b14643.de) PROPELLANT { @@ -203,13 +213,10 @@ } atmosphereCurve { - key = 0 340 // b14643.de - key = 1 219 // guess + key = 0 340 + key = 1 225 } - massMult = 0.9 // I...guess? - ullage = True - ignitions = 1 IGNITOR_RESOURCE { name = ElectricCharge @@ -249,11 +256,12 @@ name = NK-19 description = NK-9V rerated for N1 Block G use. Gimbal, throttle. specLevel = operational - maxThrust = 400 - minThrust = 240 + maxThrust = 451.1 + minThrust = 270.7 heatProduction = 205 - massMult = 1 // I...guess? - // 2.5 O/F mass ratio (b14643.de) + massMult = 1.1275 + ullage = True + ignitions = 1 PROPELLANT { name = CooledRG-1 @@ -267,12 +275,10 @@ } atmosphereCurve { - key = 0 353 //assuming same as NK-31 - key = 1 219 // guess + key = 0 345 + key = 1 230 } - - ullage = True - ignitions = 1 + IGNITOR_RESOURCE { name = ElectricCharge @@ -312,30 +318,29 @@ name = NK-39 description = Improved for N1F Block V. No gimbal, differential throttle. specLevel = prototype - maxThrust = 400 - minThrust = 240 //FIXME guessing 60% min throttle + maxThrust = 407 + minThrust = 244.2 //FIXME guessing 60% min throttle heatProduction = 205 - massMult = 1.09375 // 700kg http://www.scribd.com/doc/7362263/Russian-Liquid-Propellant-Engines#scribd - // 2.6 O/F mass ratio (b14643.de) + massMult = 0.9125 + ullage = True + ignitions = 1 PROPELLANT { name = CooledRG-1 - ratio = 0.3576 + ratio = 0.3558 DrawGauge = true } PROPELLANT { name = CooledLqdOxygen - ratio = 0.6424 + ratio = 0.6442 } atmosphereCurve { key = 0 352 - key = 1 235 + key = 1 213 } - ullage = True - ignitions = 1 IGNITOR_RESOURCE { name = ElectricCharge @@ -373,26 +378,25 @@ name = NK-31 description = Improved for N1F Block G. Relightable. Gimbal, throttle. specLevel = prototype - maxThrust = 402 // b14643 - minThrust = 240 // assume some level of throttle, engine design was capable, and LH2 replacement engine for this stage had throttle. + maxThrust = 402.1 + minThrust = 241.3 // assume some level of throttle, engine design was capable, and LH2 replacement engine for this stage had throttle. heatProduction = 205 - massMult = 1.128125 // 722kg http://www.scribd.com/doc/7362263/Russian-Liquid-Propellant-Engines#scribd - // 2.6 O/F mass ratio (b14643.de) + massMult = 1.1275 PROPELLANT { name = CooledRG-1 - ratio = 0.3576 + ratio = 0.3558 DrawGauge = true } PROPELLANT { name = CooledLqdOxygen - ratio = 0.6424 + ratio = 0.6442 } atmosphereCurve { key = 0 353 - key = 1 236 + key = 1 214 } ullage = True diff --git a/GameData/RealismOverhaul/Engine_Configs/NK9_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/NK9_Config.cfg index 512388c0ce..1f48aaa666 100644 --- a/GameData/RealismOverhaul/Engine_Configs/NK9_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/NK9_Config.cfg @@ -4,27 +4,83 @@ // Manufacturer: SNTK Kuznetsov // // ================================================================================= -// NK-9 -// R-9 +// NK-9 (8D517) +// R-9/GR-1 // -// Dry Mass: ??? Kg +// Dry Mass: 491.55 Kg [13] // Thrust (SL): ??? kN -// Thrust (Vac): 421 kN -// ISP: 286.5 SL / 328 Vac -// Burn Time: 300 -// Chamber Pressure: 7.85 MPa +// Thrust (Vac): 426.6 kN [3/4/13] +// ISP: 286.5 SL / 328 Vac [3/4/11/13] +// Burn Time: 150 [14] +// Chamber Pressure: 10.34 MPa [3/13] // Propellant: LOX / RG-1 +// Prop Ratio: 2.5 [3/4] +// Throttle: N/A +// Nozzle Ratio: 25? estimated with RPA +// Ignitions: 1 +// ================================================================================= +// NK-9-1969 +// speculative upgrade with NK-15 tech +// +// Dry Mass: 491.55 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 482 kN TWR 100? +// ISP: 283.5 SL / 330 Vac +// Burn Time: 190? +// Chamber Pressure: 10.34 MPa +// Propellant: CooledLOX / CooledRG-1 // Prop Ratio: 2.5 // Throttle: N/A -// Nozzle Ratio: 40 +// Nozzle Ratio: 27.7 +// Ignitions: 1 +// ================================================================================= +// NK-9-1972 +// speculative upgrade with NK-33 tech +// +// Dry Mass: 491.55 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 555 kN TWR 115? +// ISP: 286 SL / 331 Vac +// Burn Time: 240? +// Chamber Pressure: 10.58 MPa +// Propellant: CooledLOX / CooledRG-1 +// Prop Ratio: 2.62 +// Throttle: N/A +// Nozzle Ratio: 27.7 +// Ignitions: 1 +// ================================================================================= +// NK-9-2009 +// speculative upgrade with NK-33 tech +// +// Dry Mass: 491.55 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 603 kN TWR 125? +// ISP: 291.3 SL / 331.6 Vac +// Burn Time: 240? +// Chamber Pressure: 11.71 MPa +// Propellant: CooledLOX / CooledRP-1 +// Prop Ratio: 2.7 +// Throttle: N/A +// Nozzle Ratio: 27.7 // Ignitions: 1 // ================================================================================= // Sources: -// http://www.astronautix.com/engines/nk9.htm -// http://www.b14643.de/Spacerockets_1/East_Europe_2/N-1/NK/index.htm -// http://lpre.de/resources/articles/LPRE%20DESIGNED%20BY%20KUZNETSOV%20COMPANY.pdf +// [1] http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20000088626.pdf +// [2] http://www.scribd.com/doc/46957813/Aviadvigatel +// [3] http://www.b14643.de/Spacerockets_1/East_Europe_2/N-1/NK/index.htm - dubious +// [4] http://www.b14643.de/Spacerockets/Specials/Russian_Rocket_engines/engines.htm +// [5] https://web.archive.org/web/20130703154050/http://www.spaceandtech.com/spacedata/engines/nk33_specs.shtml +// [6] http://www.lpre.de/sntk/NK-33/index.htm +// [7] http://history.nasa.gov/SP-4408pt1.pdf +// [8] http://lpre.de/resources/articles/AIAA-1998-3361.pdf - good on data +// [9] https://web.archive.org/web/20140115161002/http://www.orbital.com/NewsInfo/Publications/Antares%20UG.pdf +// [10] http://sites.nationalacademies.org/cs/groups/depssite/documents/webpage/deps_068011.pdf - AJ26-62 reliability +// [11] http://www.lpre.de/sntk/index.htm +// [12] Anisimov: "EVOLUTION OF THE NK-33 AND NK-43 REUSABLE LOX/KEROSENE ENGINES" +// [13] http://lpre.de/resources/articles/LPRE%20DESIGNED%20BY%20KUZNETSOV%20COMPANY.pdf +// [14] https://rocketengines.ru/historical-digest/events/february-21-29-2.html // Used by: // Bobcat @@ -62,7 +118,7 @@ { name = ModuleEngineConfigs type = ModuleEngines - origMass = 0.36 // Guess a TWR of 120 + origMass = 0.49155 engineType = L configuration = NK-9 modded = false @@ -71,9 +127,12 @@ name = NK-9 description = Developed for R-9 ICBM, and later used as the first stage engine for GR-1, the N-1 predecessor. specLevel = prototype - maxThrust = 421 // sources differ. Nautix says 441kN for the engine, but 421kN for the GR-1's stage. lpre.de also says 421 kn, so go with this - minThrust = 421 + maxThrust = 426.6 + minThrust = 426.6 heatProduction = 205 + massMult = 1.0 + ullage = True + ignitions = 1 PROPELLANT { name = RG-1 @@ -88,12 +147,9 @@ atmosphereCurve { key = 0 328 - key = 1 286.5 //calculated from sl and vac thrust + key = 1 286.5 } - massMult = 1.0 - ullage = True - ignitions = 1 IGNITOR_RESOURCE { name = ElectricCharge @@ -125,9 +181,12 @@ name = NK-9-1969 description = Speculative upgrade, assuming technologies from the NK-15 were integrated back into the NK-9 specLevel = speculative - maxThrust = 421 - minThrust = 421 + maxThrust = 482 + minThrust = 482 heatProduction = 205 + massMult = 1.0 + ullage = True + ignitions = 1 PROPELLANT { name = CooledRG-1 @@ -141,13 +200,10 @@ } atmosphereCurve { - key = 0 331 - key = 1 297 + key = 0 330 + key = 1 283.5 } - massMult = 1.0 - ullage = True - ignitions = 1 IGNITOR_RESOURCE { name = ElectricCharge @@ -160,15 +216,16 @@ } //no data, never flown + //same as NK-15 TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 450 //Assume same as NK-33 ratedBurnTime = 190 safeOverburn = true - ignitionReliabilityStart = 0.925824 - ignitionReliabilityEnd = 0.985165 - cycleReliabilityStart = 0.925824 - cycleReliabilityEnd = 0.985165 + ignitionReliabilityStart = 0.876852 + ignitionReliabilityEnd = 0.980556 + cycleReliabilityStart = 0.876852 + cycleReliabilityEnd = 0.980556 techTransfer = NK-9,NK-9V:50 } } @@ -177,29 +234,29 @@ name = NK-9-1972 description = Speculative upgrade, assuming technologies from the NK-33 were integrated back into the NK-9 specLevel = speculative - maxThrust = 436 // (for same TWR as NK-33 - (1766 / 1459) * 360) - minThrust = 436 + maxThrust = 555 + minThrust = 555 heatProduction = 205 + massMult = 1.0 + ullage = True + ignitions = 1 PROPELLANT { name = CooledRG-1 - ratio = 0.3667 + ratio = 0.3558 DrawGauge = true } PROPELLANT { name = CooledLqdOxygen - ratio = 0.6333 + ratio = 0.6442 } atmosphereCurve { key = 0 331 - key = 1 297 + key = 1 286 } - massMult = 1.0 - ullage = True - ignitions = 1 IGNITOR_RESOURCE { name = ElectricCharge @@ -212,15 +269,16 @@ } //no data, never flown + //same as NK-33 TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 450 //Assume same as NK-33 ratedBurnTime = 240 safeOverburn = true - ignitionReliabilityStart = 0.93 - ignitionReliabilityEnd = 0.996 - cycleReliabilityStart = 0.92 - cycleReliabilityEnd = 0.996 + ignitionReliabilityStart = 0.876852 + ignitionReliabilityEnd = 0.980556 + cycleReliabilityStart = 0.876852 + cycleReliabilityEnd = 0.980556 techTransfer = NK-9-1969,NK-9,NK-9V:50 } } @@ -229,10 +287,12 @@ name = NK-9-2009 description = Speculative upgrade, assuming Aerojet purchased and upgraded NK-9s for their own use. specLevel = speculative - maxThrust = 448 // (for same TWR as AJ26-62 - (1815 / (1222 * 1.1937)) * 360) - minThrust = 448 + maxThrust = 603 + minThrust = 603 heatProduction = 205 - // 2.7 O/F mass ratio (Antares UG) + massMult = 1.0 + ullage = True + ignitions = 1 PROPELLANT { name = CooledRP-1 @@ -246,13 +306,10 @@ } atmosphereCurve { - key = 0 331.9 // Antares UG - key = 1 301.6 // Antares UG + key = 0 331.6 + key = 1 291.3 } - massMult = 1.0 - ullage = True - ignitions = 1 IGNITOR_RESOURCE { name = ElectricCharge @@ -265,15 +322,17 @@ } //no data, never flown + //NK-33 really did not enjoy 108+% throttle, poor reliability TESTFLIGHT:NEEDS[TestLite|TestFlight] { - testedBurnTime = 450 //Assume same as NK-33 + testedBurnTime = 450 ratedBurnTime = 240 safeOverburn = true - ignitionReliabilityStart = 0.95 - ignitionReliabilityEnd = 0.996 - cycleReliabilityStart = 0.96 - cycleReliabilityEnd = 0.996 + + ignitionReliabilityStart = 0.876852 + ignitionReliabilityEnd = 0.980556 + cycleReliabilityStart = 0.876852 + cycleReliabilityEnd = 0.980556 techTransfer = NK-9-1972,NK-9-1969,NK-9,NK-9V:50 } } diff --git a/GameData/RealismOverhaul/Engine_Configs/ORM65_config.cfg b/GameData/RealismOverhaul/Engine_Configs/ORM65_config.cfg index 532ee9fcc3..81e4aeea87 100644 --- a/GameData/RealismOverhaul/Engine_Configs/ORM65_config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/ORM65_config.cfg @@ -9,7 +9,7 @@ // // Dry Mass: 90 Kg // Thrust (SL): 1.750 kN -// Thrust (Vac): ??? kN +// Thrust (Vac): 1.785 kN // ISP: 210 SL / 215 Vac // Burn Time: 80 // Chamber Pressure: 2.53 MPa @@ -24,7 +24,22 @@ // // Dry Mass: 90 Kg // Thrust (SL): 1.431 kN -// Thrust (Vac): ??? kN +// Thrust (Vac): 1.460 kN +// ISP: 210 SL / 215 Vac +// Burn Time: 200 +// Chamber Pressure: 2.53 MPa +// Propellant: AK20 / Kerosene +// Prop Ratio: 4.0 +// Throttle: 100% to 34% +// Nozzle Ratio: ??? +// Ignitions: 2 +// ================================================================================= +// RDA-1-150 +// planned upgrade for RP-318 rocket plane +// +// Dry Mass: 90 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 2.942 kN // ISP: 210 SL / 215 Vac // Burn Time: 200 // Chamber Pressure: 2.53 MPa diff --git a/GameData/RealismOverhaul/Engine_Configs/RD0110R_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD0110R_Config.cfg index 6dfa59b177..9965cbb29b 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD0110R_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD0110R_Config.cfg @@ -12,7 +12,7 @@ // Thrust (Vac): 68.3 kN // ISP: 259 SL / 298 Vac // Burn Time: 250 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 15.53 MPa // Propellant: LOX / RG-1 // Prop Ratio: 2.22 // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/RD0164_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD0164_Config.cfg index 1e664075af..74194ed6b0 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD0164_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD0164_Config.cfg @@ -12,11 +12,11 @@ // Thrust (Vac): 3831 kN // ISP: 311.5 SL / 358 Vac // Burn Time: 360 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 16.6? MPa // Propellant: LOX / CH4 -// Prop Ratio: ??? +// Prop Ratio: 3.5? // Throttle: 100% to 45% -// Nozzle Ratio: ??? +// Nozzle Ratio: 40? // Ignitions: 4 // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/RD0169_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD0169_Config.cfg index fbc7646f5a..2440cb1e42 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD0169_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD0169_Config.cfg @@ -12,11 +12,11 @@ // Thrust (Vac): 716 kN // ISP: ??? SL / 372 Vac // Burn Time: 720 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 16.6? MPa // Propellant: LOX / CH4 -// Prop Ratio: ??? +// Prop Ratio: 3.5? // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 90? // Ignitions: 8 // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/RD0214_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD0214_Config.cfg index 55d922e038..b0faf5c586 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD0214_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD0214_Config.cfg @@ -10,13 +10,13 @@ // Dry Mass: 90 Kg // Thrust (SL): ??? kN // Thrust (Vac): 30.98 kN -// ISP: ??? SL / 297 Vac +// ISP: 152 SL / 297 Vac sl calculated with RPA // Burn Time: 150 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 5.3 MPa // Propellant: NTO / UDMH // Prop Ratio: 1.8? // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 43.3 // Ignitions: 1 // ================================================================================= // RD-0214 @@ -25,13 +25,13 @@ // Dry Mass: 90 Kg // Thrust (SL): ??? kN // Thrust (Vac): 30.98 kN -// ISP: ??? SL / 293 Vac +// ISP: 189 SL / 293 Vac // Burn Time: 300 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 5.3? MPa // Propellant: NTO / UDMH -// Prop Ratio: ??? +// Prop Ratio: 1.8? // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 31? estimated with RPA // Ignitions: 1 // ================================================================================= @@ -96,7 +96,7 @@ atmosphereCurve { key = 0 297 - key = 1 215 + key = 1 152 } //UR-200 (8K81) (R&D): 7 flights, 0 failures @@ -144,7 +144,7 @@ atmosphereCurve { key = 0 293 - key = 1 215 + key = 1 189 } //Proton-K (8K82K): 27 flights, 0 failures diff --git a/GameData/RealismOverhaul/Engine_Configs/RD0228_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD0228_Config.cfg index 47cde4aa4b..c7cea604ae 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD0228_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD0228_Config.cfg @@ -8,7 +8,7 @@ // RD-0228 // R-36M, R-36MU // -// Dry Mass: ??? kg +// Dry Mass: 770? kg // Thrust (SL): ??? kN // Thrust (Vac): 760 kN (1)main + verniers total? // ISP: 234 SL / 340 Vac (1)main + verniers total? SL calculated with RPA diff --git a/GameData/RealismOverhaul/Engine_Configs/RD0229_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD0229_Config.cfg index 070562b76d..c33ff4fb6c 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD0229_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD0229_Config.cfg @@ -12,7 +12,7 @@ // Thrust (Vac): 729.02 kN Guess // ISP: 235 SL / 341.4 Vac Guess // Burn Time: 153 (5) -// Chamber Pressure: ??? MPa +// Chamber Pressure: 16.32? MPa // Propellant: NTO / UDMH // Prop Ratio: 2.60 Guess // Throttle: N/A @@ -22,7 +22,7 @@ // RD-0256 // R-36M2, Dnepr // -// Dry Mass: ??? Kg +// Dry Mass: 680? Kg // Thrust (SL): ??? kN // Thrust (Vac): 805.52 kN Guess // ISP: 235 SL / 341.3 Vac Guess diff --git a/GameData/RealismOverhaul/Engine_Configs/RD0230_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD0230_Config.cfg index 7e1c57f4d5..46ec4bb15a 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD0230_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD0230_Config.cfg @@ -12,7 +12,7 @@ // Thrust (Vac): 30.98 kN Guess // ISP: ??? SL / 307 Vac Guess // Burn Time: 175 (5) -// Chamber Pressure: ??? MPa +// Chamber Pressure: 5.3? MPa same as RD-0214 // Propellant: NTO / UDMH // Prop Ratio: 2.6 (Guess) // Throttle: N/A @@ -22,12 +22,12 @@ // RD-0257 // R-36M2, Dnepr // -// Dry Mass: ??? Kg +// Dry Mass: 90? Kg // Thrust (SL): ??? kN // Thrust (Vac): 30.98 kN Guess // ISP: ??? SL / 307 Vac Guess // Burn Time: 190 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 5.3? MPa same as RD-0214 // Propellant: NTO / UDMH // Prop Ratio: 2.6 (Guess) // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/RD0236_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD0236_Config.cfg index 9c18bb7f09..dc7ac4f8ed 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD0236_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD0236_Config.cfg @@ -4,10 +4,10 @@ // Manufacturer: KB Khimavtomatika // // ================================================================================= -// RD-0230 +// RD-0236 // UR-100N, UR-100NUTTKh, Strela, Rokot // -// Dry Mass: ??? Kg +// Dry Mass: 60? Kg // Thrust (SL): ??? kN // Thrust (Vac): 15.76 kN (1) // ISP: 232 SL / 293 Vac (1) SL calculated with RPA @@ -50,7 +50,7 @@ type = ModuleEngines configuration = RD-0236 modded = false - origMass = 0.090 + origMass = 0.060 CONFIG { diff --git a/GameData/RealismOverhaul/Engine_Configs/RD0242M2_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD0242M2_Config.cfg index b3cd36687b..e3c1961d89 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD0242M2_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD0242M2_Config.cfg @@ -12,7 +12,7 @@ // Thrust (Vac): 50.0 kN // ISP: ??? SL / 280 Vac // Burn Time: 380 s -// Chamber Pressure: ??? MPa +// Chamber Pressure: 15.3 MPa // Propellant: NTO / MMH // Prop Ratio: 1.65 // Throttle: 60% to 100% diff --git a/GameData/RealismOverhaul/Engine_Configs/RD100_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD100_Config.cfg index 3a686f5da6..c45996ecbc 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD100_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD100_Config.cfg @@ -42,7 +42,7 @@ // Thrust (Vac): 428 kN // ISP: 214 SL / 235 Vac // Burn Time: 83 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 2.28? MPa halfway between 101 and 103? // Propellant: LOX / Ethanol90 // Prop Ratio: ??? // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/RD107_RD117_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD107_RD117_Config.cfg index f348da6fad..a3622589b4 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD107_RD117_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD107_RD117_Config.cfg @@ -135,7 +135,7 @@ // Thrust (Vac): 1033.3 kN // ISP: 261 SL / 317.6 Vac // Burn Time: 130 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 5.86? MPa // Propellant: Cooled LOX / Cooled Syntin // Prop Ratio: ??? // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/RD108_RD118_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD108_RD118_Config.cfg index 28034ca3b4..a576e7a472 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD108_RD118_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD108_RD118_Config.cfg @@ -133,7 +133,7 @@ // Thrust (Vac): 1011 kN // ISP: 257 SL / 319 Vac // Burn Time: 310 core ~108 tons wet? -// Chamber Pressure: ??? MPa +// Chamber Pressure: 5.86? MPa // Propellant: Cooled LOX / Cooled Syntin // Prop Ratio: ??? // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/RD120_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD120_Config.cfg index 1bb1d1111f..da6c899ab7 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD120_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD120_Config.cfg @@ -37,7 +37,7 @@ // RD-120K // // -// Dry Mass: ??? Kg +// Dry Mass: 1080? Kg // Thrust (SL): ??? kN // Thrust (Vac): 853.18 kN // ISP: 304.4 SL / 330 Vac diff --git a/GameData/RealismOverhaul/Engine_Configs/RD1_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD1_Config.cfg index 8201418d59..5b494d54db 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD1_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD1_Config.cfg @@ -12,7 +12,7 @@ // Thrust (Vac): ??? kN // ISP: 200 SL / ??? Vac // Burn Time: 300 //guess, based on planned 10 minute flight times, assumed half under power, and half gliding -// Chamber Pressure: ??? MPa +// Chamber Pressure: 2.0 MPa // Propellant: AK20 / Kerosene // Prop Ratio: 4.05 // ??? Copy from S2.253 // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/RD253_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD253_Config.cfg index c0d7f64f7c..de370998c1 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD253_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD253_Config.cfg @@ -72,7 +72,7 @@ // Thrust (Vac): 1698 kN // ISP: 285 SL / 316 Vac // Burn Time: 148 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 14.71? MPa // Propellant: NTO / UDMH // Prop Ratio: 2.69 // Throttle: N/A @@ -87,7 +87,7 @@ // Thrust (Vac): 1748 kN // ISP: 285 SL / 316 Vac // Burn Time: 148 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 14.71? MPa // Propellant: NTO / UDMH // Prop Ratio: 2.69 // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/RD254_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD254_Config.cfg index 77f321bb9d..67b9c775b5 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD254_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD254_Config.cfg @@ -72,7 +72,7 @@ // Thrust (Vac): 1782 kN // ISP: 240 SL / 327.8 Vac SL calculated with RPA // Burn Time: 225 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 14.71? MPa // Propellant: NTO / UDMH // Prop Ratio: 2.69 // Throttle: N/A @@ -87,7 +87,7 @@ // Thrust (Vac): 1834 kN // ISP: 240 SL / 327.8 Vac SL calculated with RPA // Burn Time: 225 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 14.71? MPa // Propellant: NTO / UDMH // Prop Ratio: 2.69 // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/RD57_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD57_Config.cfg index defa073da0..df241fa2ba 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD57_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD57_Config.cfg @@ -42,7 +42,7 @@ // Thrust (Vac): 395.0 kN // ISP: 292 SL / 460 Vac SL calculated with RPA // Burn Time: ??? -// Chamber Pressure: ??? MPa +// Chamber Pressure: 11.5? MPa // Propellant: LOX / LH2 // Prop Ratio: 5.80 // Throttle: 303 kN minimum? diff --git a/GameData/RealismOverhaul/Engine_Configs/RL10_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RL10_Config.cfg index fef25acabd..b863ce3af0 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RL10_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RL10_Config.cfg @@ -275,48 +275,48 @@ // Ignitions: 15 // ================================================================================= // CECE-Base -// Technology demonstrator +// Technology demonstrator (RL10A-4-2 based?) // // Dry Mass: 210 Kg // Thrust (SL): ??? kN // Thrust (Vac): 67 kN -// ISP: ??? SL / 460 Vac +// ISP: 249 SL / 460 Vac // Burn Time: 10000 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.20 MPa // Propellant: LOX / LH2 // Prop Ratio: 5.80 // Throttle: 100% to 6.66% -// Nozzle Ratio: ??? +// Nozzle Ratio: 61? no nozzle extension? // Ignitions: 50 // ================================================================================= // CECE-High -// Technology demonstrator +// Technology demonstrator (RL10B-2 based?) // // Dry Mass: 256 Kg // Thrust (SL): ??? kN // Thrust (Vac): 110 kN -// ISP: ??? SL / 465 Vac +// ISP: 1 @0.915 atm SL / 465 Vac // Burn Time: 10000 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.44 MPa // Propellant: LOX / LH2 // Prop Ratio: 5.88 // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 285? probably used B-2 nozzle // Ignitions: 50 // ================================================================================= // CECE-Methane -// Technology demonstrator +// Technology demonstrator (RL10A-4-2 based?) // // Dry Mass: 210 Kg // Thrust (SL): ??? kN // Thrust (Vac): 67 kN -// ISP: ??? SL / 360 Vac +// ISP: 88 SL / 360 Vac // Burn Time: 10000 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.20 MPa // Propellant: LOX / CH4 // Prop Ratio: 3.6 // Throttle: 100% to 25% -// Nozzle Ratio: ??? +// Nozzle Ratio: 61? no nozzle extension? // Ignitions: 50 // ================================================================================= @@ -1366,7 +1366,7 @@ atmosphereCurve { key = 0 460 //target was >445 s - key = 1 100 + key = 1 249 } massMult = 1.257 @@ -1421,7 +1421,7 @@ atmosphereCurve { key = 0 465 - key = 1 100 + key = 0.915 1 } massMult = 1.533 @@ -1469,7 +1469,7 @@ atmosphereCurve { key = 0 360 //target >350 s - key = 1 100 + key = 1 88 } massMult = 1.257 diff --git a/GameData/RealismOverhaul/Engine_Configs/RS2100_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RS2100_Config.cfg index 11f35bb149..21662baafc 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RS2100_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RS2100_Config.cfg @@ -7,14 +7,14 @@ // RS-2100 // // -// Dry Mass: ??? Kg +// Dry Mass: 2948 Kg Target TWR 83 // Thrust (SL): ??? kN // Thrust (Vac): 2399.5 kN // ISP: 384 SL / 450 Vac // Burn Time: ??? -// Chamber Pressure: ??? MPa -// Propellant: LOX / LH2 -// Prop Ratio: ??? +// Chamber Pressure: 22.4 MPa +// Propellant: Subcooled LOX / Subcooled LH2 +// Prop Ratio: 6.0? // Throttle: 100% to 55% // Nozzle Ratio: ??? // Ignitions: 4 @@ -62,7 +62,7 @@ { name = ModuleEngineConfigs type = ModuleEngines - origMass = 2.950 // originally was 6.8 tons but config said it should be this... no idea + origMass = 2.948 configuration = RS-2100 CONFIG @@ -85,14 +85,14 @@ PROPELLANT { name = LqdHydrogen - ratio = 0.72 + ratio = 0.7441 DrawGauge = True } PROPELLANT { - name = LqdOxygen - ratio = 0.28 + name = CooledLqdOxygen + ratio = 0.2559 DrawGauge = False } diff --git a/GameData/RealismOverhaul/Engine_Configs/RS68_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RS68_Config.cfg index d56f9427c4..f7c79aa877 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RS68_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RS68_Config.cfg @@ -40,7 +40,7 @@ // Dry Mass: 6665 Kg 150 lbs heavier // Thrust (SL): ??? kN // Thrust (Vac): 3570 kN same as RS-68A? -// ISP: 362 SL / 412 Vac same as RS-68A? +// ISP: 364 SL / 414.2 Vac [4] sl estimated with RPA // Burn Time: 330 // Chamber Pressure: 9.90 MPa // Propellant: LOX / LH2 @@ -72,21 +72,22 @@ // Thrust (Vac): 4110 kN // ISP: 364 SL / 435 Vac // Burn Time: 450 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 13? MPa // Propellant: LOX / LH2 // Prop Ratio: 6.0 // Throttle: 55% to 102% -// Nozzle Ratio: ??? +// Nozzle Ratio: 40? // Ignitions: 1 // ================================================================================= // Sources: -// ULA - Delta IV launch vehicle summary: http://www.ulalaunch.com/products_deltaiv.aspx -// ULA - Delta IV launch services user's guide: http://www.ulalaunch.com/uploads/docs/Launch_Vehicles/Delta_IV_Users_Guide_June_2013.pdf -// Norbert Brügge - Delta IV propulsion: http://www.b14643.de/Spacerockets_2/United_States_5/Delta_IV/Propulsion/engines.htm -// NTRS - Ares V and RS-68B: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20090014109.pdf +// [1]ULA - Delta IV launch vehicle summary: http://www.ulalaunch.com/products_deltaiv.aspx +// [2]ULA - Delta IV launch services user's guide: http://www.ulalaunch.com/uploads/docs/Launch_Vehicles/Delta_IV_Users_Guide_June_2013.pdf +// [3]Norbert Brügge - Delta IV propulsion: http://www.b14643.de/Spacerockets_2/United_States_5/Delta_IV/Propulsion/engines.htm +// [4]NTRS - Ares V and RS-68B: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20090014109.pdf +// [5]https://forum.nasaspaceflight.com/index.php?topic=56171.0 // History of Liquid Propellant Rocket Engines, George P. Sutton // Used by: @@ -292,8 +293,8 @@ atmosphereCurve { - key = 0 412 - key = 1 362 + key = 0 414.2 + key = 1 364 } //Man-rated, fudge to late-model SSME levels diff --git a/GameData/RealismOverhaul/Engine_Configs/RS76_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RS76_Config.cfg index dd34a0af8e..c5d66a0526 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RS76_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RS76_Config.cfg @@ -19,6 +19,21 @@ // Nozzle Ratio: ??? // Ignitions: 3 //Intended for flyback boosters // ================================================================================= +// RS-76A +// Speculative upgrade with RD-180 parts +// +// Dry Mass: 6732 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 4621.29 kN +// ISP: 308 SL / 337 Vac +// Burn Time: 480 +// Chamber Pressure: 19.31 MPa +// Propellant: LOX / RP1 +// Prop Ratio: 2.7 +// Throttle: 100% to 65% +// Nozzle Ratio: ??? +// Ignitions: 3 //Intended for flyback boosters +// ================================================================================= // Sources: diff --git a/GameData/RealismOverhaul/Engine_Configs/RS88_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RS88_Config.cfg index 66a0177fa0..ed0cf14fb5 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RS88_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RS88_Config.cfg @@ -8,37 +8,40 @@ // prototype // // Dry Mass: 250 Kg -// Thrust (SL): ??? kN -// Thrust (Vac): 220 kN -// ISP: 273 SL / 324 Vac +// Thrust (SL): 230.86 kN +// Thrust (Vac): 255.77 kN [4] +// ISP: 222 SL / 244 Vac [4] // Burn Time: ??? -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.45 MPa [4] // Propellant: LOX / Ethanol75 -// Prop Ratio: 1.29 +// Prop Ratio: 1.49 [4] // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 7.04 [4] // Ignitions: 1 // ================================================================================= // LAE // CST-100 // // Dry Mass: 250 Kg -// Thrust (SL): ??? kN -// Thrust (Vac): 258 kN -// ISP: 220 SL / 290 Vac +// Thrust (SL): 176.6 kN [5],[6] assuming SL +// Thrust (Vac): 193.49 kN +// ISP: 230 SL / 252 Vac estimated with RPA // Burn Time: ??? -// Chamber Pressure: ??? MPa -// Propellant: NTO / MMH -// Prop Ratio: 1.65 -// Throttle: N/A -// Nozzle Ratio: ??? +// Chamber Pressure: 4.45? MPa same as RS-88? +// Propellant: MON3 / MMH +// Prop Ratio: 1.65? +// Throttle: 100-75%? "precise throttle control" +// Nozzle Ratio: 7.04? it looks the same as RS-88? // Ignitions: 1 // ================================================================================= // Sources: -// NTRS - RS-88 Pad Abort Demonstrator Thrust Chamber Assembly: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20050237017.pdf -// Encyclopedia Astronautica - RS-88 engine: http://astronautix.com/r/rs-88.html -// Boeing - Design Considerations for a Commercial Crew Transportation System: http://www.boeing.com/assets/pdf/defense-space/space/ccts/docs/Space_2011_Boeing.pdf +// [1]NTRS - RS-88 Pad Abort Demonstrator Thrust Chamber Assembly: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20050237017.pdf +// [2]Encyclopedia Astronautica - RS-88 engine: http://astronautix.com/r/rs-88.html +// [3]Boeing - Design Considerations for a Commercial Crew Transportation System: http://www.boeing.com/assets/pdf/defense-space/space/ccts/docs/Space_2011_Boeing.pdf +// [4]https://arc.aiaa.org/doi/epdf/10.2514/6.2005-4422 +// [5]https://www.spaceflightinsider.com/organizations/boeing/launch-abort-engines-boeing-cst-100-starliner-undergo-testing/ +// [6]https://www.americaspace.com/2014/08/08/aerojet-rocketdyne-completes-ccicap-work-with-boeings-cst-100-spacecraft/ // Used by: // CST-100 pack @@ -82,8 +85,8 @@ { name = RS-88 specLevel = operational - maxThrust = 220 - minThrust = 220 + maxThrust = 255.77 + minThrust = 191.83 ullage = True pressureFed = True ignitions = 1 @@ -97,21 +100,21 @@ PROPELLANT { name = Ethanol75 - ratio = 0.5285 + ratio = 0.5236 DrawGauge = True } PROPELLANT { name = LqdOxygen - ratio = 0.4715 + ratio = 0.4764 DrawGauge = False } atmosphereCurve { - key = 0 324 - key = 1 273 + key = 0 244 + key = 1 222 } } @@ -119,8 +122,8 @@ { name = LAE specLevel = operational - minThrust = 258 - maxThrust = 258 + minThrust = 145.12 + maxThrust = 193.49 heatProduction = 0.88 //0.220 ullage = True pressureFed = True @@ -149,8 +152,8 @@ atmosphereCurve { - key = 0 290 - key = 1 220 + key = 0 252 + key = 1 230 } } } diff --git a/GameData/RealismOverhaul/Engine_Configs/RSRMV_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RSRMV_Config.cfg index 3c7f3ce6ec..69eb58d131 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RSRMV_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RSRMV_Config.cfg @@ -12,11 +12,11 @@ // Thrust (Vac): 15800 kN // ISP: 242 SL / 266 Vac // Burn Time: 126 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 6.24? MPa // Propellant: PBAN // Prop Ratio: N/A // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 7.2 // Ignitions: 1 // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/RSRM_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RSRM_Config.cfg index 16c3933fe5..1b755f3bb2 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RSRM_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RSRM_Config.cfg @@ -13,11 +13,11 @@ // Thrust (Vac): 14819 kN // ISP: 243 SL / 268 Vac // Burn Time: 123 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 6.24 MPa // Propellant: PBAN // Prop Ratio: N/A // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 7.72 // Ignitions: 1 // ================================================================================= // FWC-SRM @@ -27,11 +27,11 @@ // Thrust (Vac): 14819 kN // ISP: 243 SL / 268 Vac // Burn Time: 123 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 6.24 MPa // Propellant: PBAN // Prop Ratio: N/A // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 7.72 // Ignitions: 1 // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/RZ.20_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RZ.20_Config.cfg index 045166d252..3d619525e2 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RZ.20_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RZ.20_Config.cfg @@ -7,7 +7,7 @@ // RZ.20-Mk1 // Rolls-Royce prototype // -// Dry Mass: ??? Kg +// Dry Mass: 131? Kg same as RL10? // Thrust (SL): ??? kN // Thrust (Vac): 70 kN // ISP: 171 SL / 410 Vac SL calculated with RPA @@ -22,16 +22,16 @@ // RZ.20-Mk2 // Increased expansion ratio proposal // -// Dry Mass: ??? Kg +// Dry Mass: 131? Kg // Thrust (SL): ??? kN // Thrust (Vac): ??? kN // ISP: 185 SL / 425? Vac SL calculated with RPA // Burn Time: ??? -// Chamber Pressure: 2.07 MPa +// Chamber Pressure: 2.72 MPa // Propellant: LOX / LH2 // Prop Ratio: 5.0 // Throttle: N/A -// Nozzle Ratio: 40? same as RL10 +// Nozzle Ratio: 61? same as RL10 // Ignitions: ??? //Used electric ignitor system // ================================================================================= @@ -79,7 +79,7 @@ { name = ModuleEngineConfigs type = ModuleEngines - origMass = 0.167 //Assumed same as RL10 + origMass = 0.131 modded = false configuration = RZ20-Mk1 @@ -107,7 +107,7 @@ key = 0 410 key = 1 171 } - massMult = 0.87 + massMult = 1.0 %ullage = True %ignitions = 10 //assumed same as RL10, used similar spark ignitor system %IGNITOR_RESOURCE @@ -154,7 +154,7 @@ key = 0 425 key = 1 185 } - massMult = 0.95 + massMult = 1.0 %ullage = True %ignitions = 10 //assumed same as RL10, used similar spark ignitor system %IGNITOR_RESOURCE diff --git a/GameData/RealismOverhaul/Engine_Configs/RZ_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RZ_Config.cfg index efb9c697b1..f1ba4bff95 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RZ_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RZ_Config.cfg @@ -13,7 +13,7 @@ // Thrust (Vac): 696.6 kN // ISP: 247.62 SL / 288 Vac // Burn Time: 182 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 3.61 MPa // Propellant: LOX / RP1 // Prop Ratio: 2.4 // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/RangerRetro_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RangerRetro_Config.cfg index 494cad1cd8..01a63737f7 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RangerRetro_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RangerRetro_Config.cfg @@ -7,7 +7,7 @@ // MC-4-610 // Ranger/Mariner Propulsion System // -// Dry Mass: 16.8 Kg //Including tankage and fuel +// Dry Mass: 9.8? kg 16.8 kg Including tankage and fuel // Thrust (SL): ??? kN // Thrust (Vac): 225 N //50 lbf // ISP: 49 SL / 234.97 Vac diff --git a/GameData/RealismOverhaul/Engine_Configs/Rita_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Rita_Config.cfg index d02463b206..03bacc44dd 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Rita_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Rita_Config.cfg @@ -12,7 +12,7 @@ // Thrust (Vac): 180 kN // ISP: ??? SL / 274 Vac // Burn Time: 62 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 5.0 MPa // Propellant: PBAN // Prop Ratio: N/A // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/Rubis_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Rubis_Config.cfg index 85d2cd95f4..eac15e3015 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Rubis_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Rubis_Config.cfg @@ -12,7 +12,7 @@ // Thrust (Vac): 53 kN // ISP: ??? SL / 274 Vac // Burn Time: 45 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.1 MPa // Propellant: PUPE // Prop Ratio: N/A // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/Rutherford_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Rutherford_Config.cfg index 59ab3b3e00..a0494008a8 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Rutherford_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Rutherford_Config.cfg @@ -12,11 +12,11 @@ // Thrust (Vac): 26.19 kN // ISP: 311 SL / 317 Vac // Burn Time: 150 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 12? MPa // Propellant: LOX / RP-1 // Prop Ratio: 2.5 // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 10.5? // Ignitions: 5 // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/Rutherford_Vac_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Rutherford_Vac_Config.cfg index 474ebe86ab..f37a10d979 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Rutherford_Vac_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Rutherford_Vac_Config.cfg @@ -12,11 +12,11 @@ // Thrust (Vac): 25.79 kN // ISP: ??? SL / 343 Vac // Burn Time: 288 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 12? MPa // Propellant: LOX / RP-1 // Prop Ratio: 2.5 // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 35? // Ignitions: 5 // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/S155_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/S155_Config.cfg index 84610933b7..032af3be3c 100644 --- a/GameData/RealismOverhaul/Engine_Configs/S155_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/S155_Config.cfg @@ -12,11 +12,11 @@ // Thrust (Vac): 19.5 kN // ISP: 248.5 SL / 255 Vac // Burn Time: 1200 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 6.5? MPa // Propellant: AK20 / Tonka-250 // Prop Ratio: 3.6 (copied from S5.3M) // Throttle: 100% to 50% -// Nozzle Ratio: ??? +// Nozzle Ratio: 5.6? // Ignitions: ??? // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/S2_253_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/S2_253_Config.cfg index 892ab27492..09d35af7b1 100644 --- a/GameData/RealismOverhaul/Engine_Configs/S2_253_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/S2_253_Config.cfg @@ -26,10 +26,10 @@ // Thrust (Vac): 127.5 kN [1] // ISP: 233 SL / 258 Vac assuming same as S5.2 // Burn Time: 65 [1] -// Chamber Pressure: ??? MPa +// Chamber Pressure: 6.8 MPa assuming same as S5.2 // Propellant: AK27 / TM-185 // Prop Ratio: 3.43 assuming same as S5.2 -// Nozzle Ratio: ??? +// Nozzle Ratio: 10.4 assuming same as S5.2 // Ignitions: 1 // ================================================================================= // S5.2 (9D21) @@ -54,7 +54,7 @@ // Thrust (Vac): 165.5 kN [1] // ISP: 240 SL / 265 Vac [1] // Burn Time: 90 [1] -// Chamber Pressure: ??? MPa +// Chamber Pressure: 6.8? MPa // Propellant: AK27 / UDMH [1] // Prop Ratio: 2.32 [1] 8.5 m2 UDMH, 10.46 m2 AK27, 1.23 volume // Nozzle Ratio: 10.4? diff --git a/GameData/RealismOverhaul/Engine_Configs/S5_92_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/S5_92_Config.cfg index f9639535fc..6f2979be75 100644 --- a/GameData/RealismOverhaul/Engine_Configs/S5_92_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/S5_92_Config.cfg @@ -22,7 +22,7 @@ // S5.92-l.n. // Fregat-M // -// Dry Mass: 75 Kg +// Dry Mass: 80 Kg 5 kg for nozzle extension? // Thrust (SL): ??? kN // Thrust (Vac): 20.01 kN // ISP: 170 SL / 333.4 Vac SL calculated with RPA @@ -171,7 +171,7 @@ minThrust = 13.96 maxThrust = 20.01 gimbalRange = 5.0 - massMult = 1.0 + massMult = 1.0667 ullage = True pressureFed = False ignitions = 50 diff --git a/GameData/RealismOverhaul/Engine_Configs/S5_98M_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/S5_98M_Config.cfg index a98ad7889f..ed5c74b04f 100644 --- a/GameData/RealismOverhaul/Engine_Configs/S5_98M_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/S5_98M_Config.cfg @@ -12,7 +12,7 @@ // Thrust (Vac): 19.61 kN // ISP: 216 SL / 328 Vac SL calculated with RPA // Burn Time: 3200 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 9.8 MPa // Propellant: NTO / UDMH // Prop Ratio: 2.0 // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/SRMU_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/SRMU_Config.cfg index 5c4ee83602..d61363c931 100644 --- a/GameData/RealismOverhaul/Engine_Configs/SRMU_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/SRMU_Config.cfg @@ -12,11 +12,11 @@ // Thrust (Vac): 8233.777 kN // ISP: 251 SL / 281 Vac // Burn Time: 145 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 5.93 MPa // Propellant: HTPB // Prop Ratio: N/A // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 15.7 // Ignitions: 1 // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/SSBE_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/SSBE_Config.cfg index f2839cea4f..25aed96b4c 100644 --- a/GameData/RealismOverhaul/Engine_Configs/SSBE_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/SSBE_Config.cfg @@ -27,7 +27,7 @@ // Thrust (Vac): 2306 kN // ISP: 333.8 SL / 358.7 Vac // Burn Time: 500 -// Chamber Pressure: ??? MPa (@ 111% throttle) +// Chamber Pressure: 21.04? MPa (@ 111% throttle) // Propellant: LOX / RP-1 / LH2 // Prop Ratio: 2.8 // Throttle: 111% to 67% diff --git a/GameData/RealismOverhaul/Engine_Configs/SSME50X_config.cfg b/GameData/RealismOverhaul/Engine_Configs/SSME50X_config.cfg index fd430aa1f8..8532595e14 100644 --- a/GameData/RealismOverhaul/Engine_Configs/SSME50X_config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/SSME50X_config.cfg @@ -29,7 +29,7 @@ // ISP: 394.3 SL / 447.1 Vac (retracted) // ISP: 345 SL / 461 Vac (extended) // Burn Time: 500 -// Chamber Pressure: ??? MPa (@ 111% throttle) +// Chamber Pressure: 21.02? MPa (@ 111% throttle) // Propellant: LOX / LH2 // Prop Ratio: 6.0 // Throttle: 111% to 67% diff --git a/GameData/RealismOverhaul/Engine_Configs/SSME650_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/SSME650_Config.cfg index 6af2dd8a8f..f60389a012 100644 --- a/GameData/RealismOverhaul/Engine_Configs/SSME650_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/SSME650_Config.cfg @@ -12,7 +12,7 @@ // Thrust (Vac): 2093 kN // ISP: 190 SL / 478 Vac SL calculated with RPA // Burn Time: 500 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 21.04 MPa // Propellant: LOX / LH2 // Prop Ratio: 6.0 // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/SSME_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/SSME_Config.cfg index 0648693306..cc1113c4e5 100644 --- a/GameData/RealismOverhaul/Engine_Configs/SSME_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/SSME_Config.cfg @@ -57,7 +57,7 @@ // Thrust (Vac): 2319.9 kN (2268.1 35, 2293.2 50, 2364.5 150) // ISP: 366.3 SL / 452.3 Vac (409.5/442.2 35, 394.3/447.1 50, 345?/461 150) // Burn Time: 500 -// Chamber Pressure: ??? MPa (@ 111% throttle) +// Chamber Pressure: 21.02? MPa (@ 111% throttle) // Propellant: LOX / LH2 // Prop Ratio: 6.0 // Throttle: 111% to 67% diff --git a/GameData/RealismOverhaul/Engine_Configs/Stentor_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Stentor_Config.cfg index 03b4d9ff92..d92c766e80 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Stentor_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Stentor_Config.cfg @@ -10,13 +10,13 @@ // Dry Mass: 339 Kg // Thrust (SL): 110 kN // Thrust (Vac): ??? kN -// ISP: ??? SL / 220 Vac -// Burn Time: ??? -// Chamber Pressure: ??? MPa +// ISP: 200 SL / 220 Vac sl estimated with RPA +// Burn Time: 29 s +// Chamber Pressure: 3.28? MPa same as early gamma? // Propellant: HTP / RP-1 // Prop Ratio: 8.2 // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 5? estimated with RPA // Ignitions: 1 // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/TDE_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/TDE_Config.cfg index ca0746842f..5c71556e31 100644 --- a/GameData/RealismOverhaul/Engine_Configs/TDE_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/TDE_Config.cfg @@ -10,9 +10,9 @@ // Dry Mass: 8.9 Kg // Thrust (SL): ??? kN // Thrust (Vac): 2.811 kN -// ISP: 179 SL / 210 Vac +// ISP: 122 SL / 210 Vac 179 is in Mars atmo?, sl calculated with RPA // Burn Time: ??? -// Chamber Pressure: ??? MPa +// Chamber Pressure: 2.4 MPa // Propellant: Hydrazine // Prop Ratio: N/A // Throttle: 100% to 9% @@ -21,6 +21,7 @@ // ================================================================================= // Sources: +// http://matthewwturner.com/uah/IPT2008_summer/baselines/LOW%20Files/Payload/Downloads/AIAA-2007-5481-979.pdf // Used by: @@ -85,7 +86,7 @@ atmosphereCurve { key = 0 210 - key = 1 179 + key = 1 122 } ullage = False pressureFed = True diff --git a/GameData/RealismOverhaul/Engine_Configs/Topaze_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Topaze_Config.cfg index 9f93133add..5939b16ba8 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Topaze_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Topaze_Config.cfg @@ -5,14 +5,14 @@ // // ================================================================================= // P2.2 Topaze -// Ablestar +// Diamant A and B // // Dry Mass: 456 Kg // Thrust (SL): ??? kN // Thrust (Vac): 156 kN // ISP: ??? SL / 259 Vac // Burn Time: 44 -// Chamber Pressure: 0.7 MPa +// Chamber Pressure: 3.5 MPa // Propellant: PBAN // Prop Ratio: N/A // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/X405_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/X405_Config.cfg index dc12863cf6..c22967286b 100644 --- a/GameData/RealismOverhaul/Engine_Configs/X405_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/X405_Config.cfg @@ -42,7 +42,7 @@ // Thrust (Vac): 156.3 kN // ISP: ??? SL / 311.9 Vac // Burn Time: 245 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.2? MPa // Propellant: LOX / RP-1 // Prop Ratio: 2.40 // Throttle: N/A diff --git a/GameData/RealismOverhaul/Engine_Configs/XLR10_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/XLR10_Config.cfg index b67fc01b41..bab0114aed 100644 --- a/GameData/RealismOverhaul/Engine_Configs/XLR10_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/XLR10_Config.cfg @@ -4,7 +4,7 @@ // Manufacturer: RMI // // ================================================================================= -// XLR-10-RM-2 +// XLR10-RM-2 // Viking // // Dry Mass: 192 Kg //same as X-405? @@ -12,11 +12,11 @@ // Thrust (Vac): 110.5 kN // 24,800 lbf // ISP: 179.6 SL / 214.5 Vac // Burn Time: 103 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 1.5? MPa // Propellant: LOX / 95% Ethanol // Prop Ratio: 1.127 //based on Viking propellant load // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 3.5? estimated with RPA // Ignitions: 1 // ================================================================================= diff --git a/GameData/RealismOverhaul/Engine_Configs/XLR11_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/XLR11_Config.cfg index fa3570edc1..9b10ba7170 100644 --- a/GameData/RealismOverhaul/Engine_Configs/XLR11_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/XLR11_Config.cfg @@ -10,30 +10,30 @@ // Dry Mass: 150 Kg // Thrust (SL): 24.6 kN // Thrust (Vac): 26.68 kN -// ISP: 207 SL / 226.6 Vac (Sutton says 209s SL, but scaling based off 228 on -5) +// ISP: 207 SL / 226.6 Vac (Sutton says 209s SL, but scaling based off 228 on -5)(RPA agrees with 192s SL) // Burn Time: 360 // Reverting from [A] change to allow for low-throttle cruise, as was origina; -// Chamber Pressure: ??? MPa +// Chamber Pressure: 1.52? MPa // Propellant: LOX / Ethanol75 // Prop Ratio: 1.439 (calculated based on X-1 fuel load of 311 Gal LOX 293 Gal Ethanol) // Throttle: 100% to 25%, in 25% increments -// Nozzle Ratio: ??? +// Nozzle Ratio: 3.3? // Ignitions: 4 // ================================================================================= -// XLR35-RM-1 // [A] [B] MX-774 proposed rocket engine. Project cancelled, only 3 test flights - Large amount of data is appropriated from other XLR11 variants, data in [B] missing. -// RTV-A-2 Hiroc Long-Range Ballistic Missile +// XLR35-RM-1 // [A] [B] MX-774 proposed rocket engine. Project cancelled, only 3 test flights - Large amount of data is appropriated from other XLR11 variants, data in [B] missing. +// RTV-A-2 Hiroc Long-Range Ballistic Missile // -// Dry Mass: 185 kg // Guessed based off the removal of separate ignition capabilities and addition of gimbaL -// Thrust (SL): 33.8 kN // 7.6 klbf -// Thrust (VAC): 37.56 kN // 8.4 klbf -// ISP: 211 SL / 234.4 VAC -// Burn Time: ??? -// Chamber Pressure: 2.86 MPa -// Propellant: LOX / Ethanol75 -// Prop Ratio: 1.2 -// Throttle: 100% to 25% -// Nozzle Ratio: ??? -// Ignitions: 1 -// Gimbal: 5 Degrees // Guessed +// Dry Mass: 185 kg // Guessed based off the removal of separate ignition capabilities and addition of gimbaL +// Thrust (SL): 33.8 kN // 7.6 klbf +// Thrust (VAC): 37.56 kN // 8.4 klbf +// ISP: 211 SL / 234.4 VAC +// Burn Time: ??? +// Chamber Pressure: 2.86 MPa +// Propellant: LOX / Ethanol75 +// Prop Ratio: 1.2 +// Throttle: 100% to 25% +// Nozzle Ratio: ??? +// Ignitions: 1 +// Gimbal: 5 Degrees // Guessed // ================================================================================= // XLR11-RM-5 // X-1 @@ -176,7 +176,7 @@ PROPELLANT { name = Nitrogen - ratio = 11.25 + ratio = 11.25 //FIXME: too low, also should probably be Helium ignoreForIsp = True } diff --git a/GameData/RealismOverhaul/Engine_Configs/XLR25_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/XLR25_Config.cfg index 34e6e6a5cc..e2752c666f 100644 --- a/GameData/RealismOverhaul/Engine_Configs/XLR25_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/XLR25_Config.cfg @@ -9,15 +9,15 @@ // // Dry Mass: 157 Kg // Thrust (SL): 66.72 kN -// Thrust (Vac): ??? kN -// ISP: ??? SL / ??? Vac +// Thrust (Vac): 73.75 kN +// ISP: 208 SL / 230 Vac estimated with RPA // Burn Time: 650 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 1.52 MPa same as pumpfed XLR11? // Propellant: LOX / Ethanol75 // Prop Ratio: 1.6 -// Throttle: 66.72 kN to 11.12 kN -// Nozzle Ratio: ??? -// Ignitions: 6 //electrical ignitors and compressed nitrogen was used to start the engine. Going with the same 6 ignitions as XLR99 due to lack of data +// Throttle: 66.72 kN to 11.12 kN (sl) +// Nozzle Ratio: 2.5? estimated with RPA +// Ignitions: 6 electrical ignitors and compressed nitrogen was used to start the engine. Going with the same 6 ignitions as XLR99 due to lack of data // ================================================================================= // Sources: @@ -63,8 +63,8 @@ { name = XLR25-CW-1 specLevel = operational - minThrust = 12.02 - maxThrust = 72.17 + minThrust = 12.29 + maxThrust = 73.75 massMult = 1.0 %ullage = False @@ -91,7 +91,7 @@ } atmosphereCurve { - key = 0 225 + key = 0 230 key = 1 208 } diff --git a/GameData/RealismOverhaul/Engine_Configs/XLR41_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/XLR41_Config.cfg index 31ec5d8af0..d312219cd7 100644 --- a/GameData/RealismOverhaul/Engine_Configs/XLR41_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/XLR41_Config.cfg @@ -12,11 +12,11 @@ // Thrust (Vac): 333 kN // ISP: 203 SL / 239 Vac // Burn Time: 70 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 1.5 MPa same as A-4? // Propellant: LOX / Ethanol75 // Prop Ratio: 1.24 // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 3.4 same as A-4? // Ignitions: 1 // =================================================================================