diff --git a/GameData/RealismOverhaul/Engine_Configs/RL10_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RL10_Config.cfg index 06b6d80ac9..2ebb4f4912 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RL10_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RL10_Config.cfg @@ -112,7 +112,7 @@ // RL10A-4 // Centaur D2A // -// Dry Mass: 143 Kg (guess, nozzle extension weighs ~25 kg) +// Dry Mass: 149 kg (guess, A-4-2 nozzle extension weighs ~19 kg [16]) // Thrust (SL): ??? kN // Thrust (Vac): 91.2 kN // ISP: 243 SL / 446.4 Vac SL calculated with RPA @@ -142,7 +142,7 @@ // RL10A-4-1 and RL10A-4-2 (represented as RL10A-4-1-2) // Centaur D2A1/D3B-SEC // -// Dry Mass: 142 Kg (guess, nozzle extension weighs ~25 kg) +// Dry Mass: 149 kg [16] A-4-2N w/o nozzle extension // Thrust (SL): ??? kN // Thrust (Vac): 97.9 kN // ISP: 249 SL / 446.4 Vac SL calculated with RPA @@ -172,14 +172,14 @@ // RL10A-4-2N // Centaur D5/III // -// Dry Mass: 168 Kg +// Dry Mass: 168 kg [16] // Thrust (SL): ??? kN -// Thrust (Vac): 99.2 kN -// ISP: 217 SL / 451.0 Vac SL calculated with RPA +// Thrust (Vac): 99.2 kN [16] +// ISP: 217 SL / 451.0 Vac [16], SL calculated with RPA // Burn Time: 894 -// Chamber Pressure: 4.20 MPa +// Chamber Pressure: 4.20 MPa [16] // Propellant: LOX / LH2 -// Prop Ratio: 5.5 +// Prop Ratio: 5.5 [16] // Throttle: N/A // Nozzle Ratio: 84 // Ignitions: 20 @@ -200,16 +200,16 @@ // Ignitions: 20 // ================================================================================= // RL10B-2 -// DCSS +// DCUS/DCSS // -// Dry Mass: 277 Kg +// Dry Mass: 302 kg [16] // Thrust (SL): ??? kN -// Thrust (Vac): 110.1 kN -// ISP: 1 @0.915 atm / 465.5 Vac SL calculated with RPA +// Thrust (Vac): 110.1 kN [16] +// ISP: 1 @0.915 atm / 465.5 Vac [16], SL calculated with RPA // Burn Time: 1130 -// Chamber Pressure: 4.44 MPa +// Chamber Pressure: 4.36 MPa [16] // Propellant: LOX / LH2 -// Prop Ratio: 5.88 +// Prop Ratio: 5.88 [16] // Throttle: N/A // Nozzle Ratio: 290 // Ignitions: 15 @@ -217,44 +217,74 @@ // RL10C-1 // Centaur D5/III // -// Dry Mass: 191 Kg +// Dry Mass: 186 kg [16] // Thrust (SL): ??? kN -// Thrust (Vac): 101.85 kN -// ISP: 154 SL / 449.7 Vac SL calculated with RPA +// Thrust (Vac): 101.85 kN [16] +// ISP: 148 SL / 449.7 Vac [16], SL calculated with RPA // Burn Time: 1130 -// Chamber Pressure: 4.36 MPa +// Chamber Pressure: 4.23 MPa [16] // Propellant: LOX / LH2 -// Prop Ratio: 5.5 +// Prop Ratio: 5.5 [16] // Throttle: N/A // Nozzle Ratio: 130 // Ignitions: 20 // ================================================================================= -// RL10C-1-1 -// Centaur V +// RL10C-1A +// Centaur D5/III (2018? first appearance I can find of an apparently smooth NEX 33" instead of NEX with B-2 mounting lugs) // -// Dry Mass: 188 Kg +// Dry Mass: 192 kg [16] // Thrust (SL): ??? kN -// Thrust (Vac): 105.9 kN -// ISP: 123 SL / 453.8 Vac SL calculated with RPA -// Burn Time: 1200 -// Chamber Pressure: 4.36 MPa +// Thrust (Vac): 102.78 kN [16] +// ISP: 116 SL / 453.8 Vac [16], SL calculated with RPA +// Burn Time: 1130 +// Chamber Pressure: 4.23 MPa [16] // Propellant: LOX / LH2 -// Prop Ratio: 5.5 +// Prop Ratio: 5.5 [16] // Throttle: N/A -// Nozzle Ratio: 155 +// Nozzle Ratio: 155? // Ignitions: 20 // ================================================================================= +// RL10C-1-1 +// Centaur III/V (C-1-1A used on Centaur V but it's identical?) +// +// Dry Mass: 188 kg [16] +// Thrust (SL): ??? kN +// Thrust (Vac): 106.0 kN [16] +// ISP: 122 SL / 453.8 Vac [16], SL calculated with RPA +// Burn Time: 1200 Set to allow full burning of 54 T of propellant (Centaur V full load) with 2x engines +// Chamber Pressure: 4.34 MPa [16] +// Propellant: LOX / LH2 +// Prop Ratio: 5.5 [16] +// Throttle: N/A +// Nozzle Ratio: 155? +// Ignitions: 20? +// ================================================================================= +// RL10C-2 +// ICPS +// +// Dry Mass: 305 kg [16] +// Thrust (SL): ??? kN +// Thrust (Vac): 110.1 kN [16] +// ISP: 1 @0.915 atm / 465.6 Vac calculated with RPA +// Burn Time: 1175? set to allow full burning of 28.6 T of propellant (ICPS full fuel load) +// Chamber Pressure: 4.34 MPa [16] +// Propellant: LOX / LH2 +// Prop Ratio: 5.7 [16] +// Throttle: N/A +// Nozzle Ratio: 285? +// Ignitions: 15? +// ================================================================================= // RL10C-2-1 // DCSS // -// Dry Mass: 277 Kg +// Dry Mass: 300 kg [16] // Thrust (SL): ??? kN -// Thrust (Vac): 111.2 kN -// ISP: 1 @0.915 atm / 465.5 Vac SL calculated with RPA +// Thrust (Vac): 110.1 kN [16] +// ISP: 1 @0.915 atm / 465.5 Vac [16], SL calculated with RPA // Burn Time: 1130 -// Chamber Pressure: 4.44 MPa +// Chamber Pressure: 4.36 MPa [16] // Propellant: LOX / LH2 -// Prop Ratio: 5.88 +// Prop Ratio: 5.88 [16] // Throttle: N/A // Nozzle Ratio: 285 // Ignitions: 15 @@ -262,32 +292,47 @@ // RL10C-3 // EUS // -// Dry Mass: 230 Kg +// Dry Mass: 219 kg [16] // Thrust (SL): ??? kN -// Thrust (Vac): 108.5 kN -// ISP: 52 SL / 460.1 Vac -// Burn Time: 1350 -// Chamber Pressure: 4.44 MPa +// Thrust (Vac): 108.3 kN [16] +// ISP: 45 SL / 460.1 Vac [16], SL calculated with RPA +// Burn Time: 1275? +// Chamber Pressure: 4.34 MPa [16] // Propellant: LOX / LH2 -// Prop Ratio: 5.70 +// Prop Ratio: 5.70 [16] // Throttle: N/A // Nozzle Ratio: 215 // Ignitions: 15 // ================================================================================= -// RL10C-X +// RL10E-1 (RL10C-X) // Centaur V // -// Dry Mass: 231.3 Kg +// Dry Mass: 227 kg [16] // Thrust (SL): ??? kN -// Thrust (Vac): 107.2911 kN -// ISP: 52 SL / 460.9 Vac +// Thrust (Vac): 107.3 kN [16] +// ISP: 24 SL / 460.9 Vac [16] // Burn Time: 1350 -// Chamber Pressure: 4.44 MPa +// Chamber Pressure: 4.34 MPa [16] // Propellant: LOX / LH2 -// Prop Ratio: 5.5 +// Prop Ratio: 5.5 [16] // Throttle: N/A -// Nozzle Ratio: 215 -// Ignitions: 15 +// Nozzle Ratio: 230? +// Ignitions: 25 [16] +// ================================================================================= +// RL10E-3EL (RL10CX-3EL) +// Commercial Passenger Transport +// +// Dry Mass: 272 kg [16] +// Thrust (SL): ??? kN +// Thrust (Vac): 108.1 kN [16] +// ISP: 24 SL / 470.5 Vac [16] +// Burn Time: 1350, 180,000 seconds rated life +// Chamber Pressure: 4.34 MPa [16] +// Propellant: LOX / LH2 +// Prop Ratio: 4.7 [16] +// Throttle: N/A +// Nozzle Ratio: 285 [16] +// Ignitions: 260 // ================================================================================= // CECE-Base // Technology demonstrator (RL10A-4-2 based?) @@ -312,7 +357,7 @@ // Thrust (Vac): 110 kN // ISP: 1 @0.915 atm SL / 465 Vac // Burn Time: 10000 -// Chamber Pressure: 4.44 MPa +// Chamber Pressure: 4.36 MPa // Propellant: LOX / LH2 // Prop Ratio: 5.88 // Throttle: N/A @@ -337,21 +382,22 @@ // Sources: -// http://www.alternatewars.com/BBOW/Space_Engines/RL10B-2.pdf -// http://www.alternatewars.com/BBOW/Space_Engines/1966_RL10_Handbook.pdf -// http://www.alternatewars.com/BBOW/Space_Engines/RL10A-4.pdf -// http://www.alternatewars.com/BBOW/Space_Engines/1984_Martin_Marietta_OTV_Excerpt.pdf -// http://www.sei.aero/eng/papers/uploads/archive/AIAA-2013-5479_Paper.pdf - Lunar Lander Designs for Crewed Surface Sortie Missions in a Cost-Constrained Environment -// http://www.islandone.org/SpaceAccessUpdates/930614-DCXN.html -// http://www.rocket.com/common-extensible-cryogenic-engine -// https://web.archive.org/web/20080921093712/http://www.spaceandtech.com/spacedata/engines/rl10_specs.shtml has gimbal ranges! -// http://www.alternatewars.com/BBOW/Space_Engines/RL60.pdf has RL10B-2 ignition count -// http://www.rocket.com/rl10-engine - RL10 Engine, Aerojet Rocketdyne -// https://www.spacelaunchreport.com/vulcan.html - Vulcan Data Sheet -// https://www.b14643.de/Spacerockets/Specials/P&W_RL10_engine/index.htm -// https://www.asme.org/wwwasmeorg/media/resourcefiles/aboutasme/who%20we%20are/engineering%20history/landmarks/36-rl-10-rocket-engine.pdf -// https://ntrs.nasa.gov/citations/19910004173 -// https://ntrs.nasa.gov/citations/19710025908 +// [1] http://www.alternatewars.com/BBOW/Space_Engines/RL10B-2.pdf +// [2] http://www.alternatewars.com/BBOW/Space_Engines/1966_RL10_Handbook.pdf +// [3] http://www.alternatewars.com/BBOW/Space_Engines/RL10A-4.pdf +// [4] http://www.alternatewars.com/BBOW/Space_Engines/1984_Martin_Marietta_OTV_Excerpt.pdf +// [5] http://www.sei.aero/eng/papers/uploads/archive/AIAA-2013-5479_Paper.pdf - Lunar Lander Designs for Crewed Surface Sortie Missions in a Cost-Constrained Environment +// [6] http://www.islandone.org/SpaceAccessUpdates/930614-DCXN.html +// [7] http://www.rocket.com/common-extensible-cryogenic-engine +// [8] https://web.archive.org/web/20080921093712/http://www.spaceandtech.com/spacedata/engines/rl10_specs.shtml has gimbal ranges! +// [9] http://www.alternatewars.com/BBOW/Space_Engines/RL60.pdf has RL10B-2 ignition count +// [10] http://www.rocket.com/rl10-engine - RL10 Engine, Aerojet Rocketdyne +// [11] https://www.spacelaunchreport.com/vulcan.html - Vulcan Data Sheet +// [12] https://www.b14643.de/Spacerockets/Specials/P&W_RL10_engine/index.htm +// [13] https://www.asme.org/wwwasmeorg/media/resourcefiles/aboutasme/who%20we%20are/engineering%20history/landmarks/36-rl-10-rocket-engine.pdf +// [14] https://ntrs.nasa.gov/citations/19910004173 +// [15] https://ntrs.nasa.gov/citations/19710025908 +// [16] https://doi.org/10.2514/6.2022-4270 // History of Liquid Propellant Rocket Engines, George P. Sutton // Used by: @@ -797,11 +843,11 @@ key = 0 446.4 key = 1 243 } - massMult = 0.86 + massMult = 0.8922 - %ullage = True - %ignitions = 20 - %IGNITOR_RESOURCE + ullage = True + ignitions = 20 + IGNITOR_RESOURCE { %name = ElectricCharge %amount = 0.5 @@ -898,11 +944,11 @@ key = 0 446.4 key = 1 249 } - massMult = 0.85 + massMult = 0.8922 - %ullage = True - %ignitions = 20 - %IGNITOR_RESOURCE + ullage = True + ignitions = 20 + IGNITOR_RESOURCE { %name = ElectricCharge %amount = 0.5 @@ -1009,14 +1055,14 @@ key = 0 451.0 key = 1 217 } - massMult = 1.02 + massMult = 1.0060 - %ullage = True - %ignitions = 20 - %IGNITOR_RESOURCE + ullage = True + ignitions = 20 + IGNITOR_RESOURCE { - %name = ElectricCharge - %amount = 0.5 + name = ElectricCharge + amount = 0.5 } TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -1115,14 +1161,14 @@ key = 0 465.5 key = 0.915 1 } - massMult = 1.659 + massMult = 1.8084 - %ullage = True - %ignitions = 15 - %IGNITOR_RESOURCE + ullage = True + ignitions = 15 + IGNITOR_RESOURCE { - %name = ElectricCharge - %amount = 0.5 + name = ElectricCharge + amount = 0.5 } //Delta III: 2 flights, 1 failure. (1 restart) @@ -1134,20 +1180,20 @@ //Delta-4M+(5,4): 4 flights, 0 failures //Delta-4M+(5,4) (upg.): 4 flights, 0 failures //Delta-4H: 7 flights, 0 failures - //Delta-4H (upg.): 6 flights, 0 failures - //44 ignitions, 0 failures - //44 cycles, 0 failures + //Delta-4H (upg.): 9 flights, 0 failures + //47 ignitions, 0 failures + //47 cycles, 0 failures //Assuming 2 ignitions per flight average - //44 restarts, 1 failures + //47 restarts, 1 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 3500 //According to Program Status of RL60 Engine ratedBurnTime = 1130 safeOverburn = true - ignitionReliabilityStart = 0.975094 - ignitionReliabilityEnd = 0.996067 - cycleReliabilityStart = 0.978889 - cycleReliabilityEnd = 0.996667 + ignitionReliabilityStart = 0.976667 + ignitionReliabilityEnd = 0.996316 + cycleReliabilityStart = 0.980208 + cycleReliabilityEnd = 0.996875 ignitionDynPresFailMultiplier = 0.05 techTransfer = RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 } @@ -1159,7 +1205,7 @@ minThrust = 101.85 maxThrust = 101.85 heatProduction = 100 - description = Cost reduced model with modern production techniques, used in single or double engine configurations on Atlas V. + description = Cost-reduced model with modern production techniques, used in single or double engine configurations on Atlas V. PROPELLANT { name = LqdHydrogen @@ -1174,52 +1220,105 @@ atmosphereCurve { key = 0 449.7 - key = 1 154 + key = 1 148 } - massMult = 1.1437 + massMult = 1.1138 - %ullage = True - %ignitions = 20 - %IGNITOR_RESOURCE + ullage = True + ignitions = 20 + IGNITOR_RESOURCE { - %name = ElectricCharge - %amount = 0.5 + name = ElectricCharge + amount = 0.5 } - //Atlas-5(401): 21 flights, 0 failures - //Atlas-5(411): 3 flights, 0 failures - //Atlas-5(421): 5 flights, 0 failures - //Atlas-5(422): 1 flights, 0 failures - //Atlas-5(431): 1 flights, 0 failures - //Atlas-5(501): 2 flights, 0 failures - //Atlas-5(531): 1 flights, 0 failures - //Atlas-5(541): 6 flights, 0 failures - //Atlas-5(551): 7 flights, 0 failures - //48 ignitions, 0 failures - //48 cycles, 0 failures + //Counting all C-1, C-1A, and (for now) C-1-1 variants together until VC can fly more + //Atlas-5(401): 41 flights, 0 failures + //Atlas-5(411): 6 flights, 0 failures + //Atlas-5(421): 9 flights, 0 failures + //Atlas-5(431): 3 flights, 0 failures + //Atlas-5(501): 8 flights, 0 failures + //Atlas-5(511): 1 flights, 0 failures + //Atlas-5(521): 2 flights, 0 failures + //Atlas-5(531): 5 flights, 0 failures + //Atlas-5(541): 9 flights, 0 failures + //Atlas-5(551): 14 flights, 0 failures + //Atlas-5(N22): 3 flights, 0 failures + //17 launches remain + //101 ignitions, 0 failures + //101 cycles, 0 failures //Assuming 2 ignitions per flight average - //48 restarts, 0 failed + //101 restarts, 0 failed TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 9000 //Another major revision with plan for reuse in future, give ~2.5 hours (CECE rated time) ratedBurnTime = 1130 //is modified RL10B-2 safeOverburn = true - ignitionReliabilityStart = 0.990206 - ignitionReliabilityEnd = 0.998454 - cycleReliabilityStart = 0.980612 - cycleReliabilityEnd = 0.996939 + ignitionReliabilityStart = 0.995320 + ignitionReliabilityEnd = 0.999261 + cycleReliabilityStart = 0.990686 + cycleReliabilityEnd = 0.998529 ignitionDynPresFailMultiplier = 0.08 techTransfer = RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 } } CONFIG + { + name = RL10C-1A + specLevel = operational + minThrust = 102.78 + maxThrust = 102.78 + heatProduction = 100 + description = Cost-reduced model with modern production techniques, used in single or double engine configurations on Atlas V. + PROPELLANT + { + name = LqdHydrogen + ratio = 0.7454 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.2546 //5.5 + } + atmosphereCurve + { + key = 0 453.8 + key = 1 116 + } + massMult = 1.1497 + + ullage = True + ignitions = 20 + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + //Atlas V flew with C-1, C-1A, and C-1-1, unclear which flight had which + //same as C-1, use same data for both + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 9000 //Another major revision with plan for reuse in future, give ~2.5 hours (CECE rated time) + ratedBurnTime = 1130 //is modified RL10B-2 + safeOverburn = true + ignitionReliabilityStart = 0.995320 + ignitionReliabilityEnd = 0.999261 + cycleReliabilityStart = 0.990686 + cycleReliabilityEnd = 0.998529 + ignitionDynPresFailMultiplier = 0.08 + techTransfer = RL10C-1,RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 + } + } + CONFIG { name = RL10C-1-1 - specLevel = prototype - minThrust = 105.9 - maxThrust = 105.9 + specLevel = operational + minThrust = 106.0 + maxThrust = 106.0 heatProduction = 100 - description = Planned upgrade of RL10C-1 for use on Vulcan-Centaur, OmegA, and later Atlas V launches + description = Upgrade of RL10C-1 for use on Vulcan-Centaur, OmegA, and later Atlas V launches PROPELLANT { name = LqdHydrogen @@ -1234,39 +1333,89 @@ atmosphereCurve { key = 0 453.8 - key = 1 123 + key = 1 122 } - massMult = 1.1272 + massMult = 1.1257 - %ullage = True - %ignitions = 20 - %IGNITOR_RESOURCE + ullage = True + ignitions = 20 + IGNITOR_RESOURCE { - %name = ElectricCharge - %amount = 0.5 + name = ElectricCharge + amount = 0.5 } - //no data, never flown + //Vulcan VC2: 1 flight, 0 failures + //Atlas V flew with C-1, C-1A, and C-1-1, unclear which flight had which + //same as C-1, use same data for both + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 9000 //Another major revision with plan for reuse in future, give ~2.5 hours (CECE rated time) + ratedBurnTime = 1200 //Set to allow full burning of 54 T of propellant (Centaur V full load) with 2x engines + safeOverburn = true + ignitionReliabilityStart = 0.995320 + ignitionReliabilityEnd = 0.999261 + cycleReliabilityStart = 0.990686 + cycleReliabilityEnd = 0.998529 + ignitionDynPresFailMultiplier = 0.08 + techTransfer = RL10C-1A,RL10C-1,RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 + } + } + CONFIG + { + name = RL10C-2 + specLevel = operational + minThrust = 110.1 + maxThrust = 110.1 + heatProduction = 100 + description = RL10B-2 using RL10C-1 components and modified for use on ICPS. + PROPELLANT + { + name = LqdHydrogen + ratio = 0.7396 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.2604 //5.70 + } + atmosphereCurve + { + key = 0 465.6 + key = 0.915 1 + } + massMult = 1.8263 + + ullage = True + ignitions = 15 + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + //SLS Block 1: 1 flight, 0 failures //using C-1 data TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 9000 //Another major revision with plan for reuse in future, give ~2.5 hours (CECE rated time) - ratedBurnTime = 1200 //Set to allow full burning of 54 T of propellant (Centaur V full load) with 2x engines + ratedBurnTime = 1175 safeOverburn = true - ignitionReliabilityStart = 0.990206 - ignitionReliabilityEnd = 0.998454 - cycleReliabilityStart = 0.980612 - cycleReliabilityEnd = 0.996939 + ignitionReliabilityStart = 0.995320 + ignitionReliabilityEnd = 0.999261 + cycleReliabilityStart = 0.990686 + cycleReliabilityEnd = 0.998529 ignitionDynPresFailMultiplier = 0.08 - techTransfer = RL10C-1,RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 + techTransfer = RL10C-2-1,RL10C-1-1,RL10C-1A,RL10C-1,RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 } } CONFIG { name = RL10C-2-1 //Mentioned as identical to the B-2, probably a cost-reduced drop-in replacement for DCSS specLevel = operational - minThrust = 111.2 - maxThrust = 111.2 + minThrust = 110.1 + maxThrust = 110.1 heatProduction = 100 description = RL10B-2 using RL10C-1 components to reduce cost. PROPELLANT @@ -1285,7 +1434,7 @@ key = 0 465.5 key = 0.915 1 } - massMult = 1.659 + massMult = 1.7964 %ullage = True %ignitions = 15 @@ -1295,27 +1444,27 @@ %amount = 0.5 } - //no data, never flown + //This was flown at most 4 times before Delta IV was retired //using C-1 data TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 9000 //Another major revision with plan for reuse in future, give ~2.5 hours (CECE rated time) - ratedBurnTime = 1130 //is modified RL10B-2 + ratedBurnTime = 1130 safeOverburn = true - ignitionReliabilityStart = 0.990206 - ignitionReliabilityEnd = 0.998454 - cycleReliabilityStart = 0.980612 - cycleReliabilityEnd = 0.996939 + ignitionReliabilityStart = 0.995320 + ignitionReliabilityEnd = 0.999261 + cycleReliabilityStart = 0.990686 + cycleReliabilityEnd = 0.998529 ignitionDynPresFailMultiplier = 0.08 - techTransfer = RL10C-1-1,RL10C-1,RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 + techTransfer = RL10C-2,RL10C-1-1,RL10C-1A,RL10C-1,RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 } } CONFIG { name = RL10C-3 specLevel = prototype - minThrust = 108.5 - maxThrust = 108.5 + minThrust = 108.3 + maxThrust = 108.3 heatProduction = 100 description = Man-rated for use on the EUS for Lunar missions. PROPELLANT @@ -1332,16 +1481,16 @@ atmosphereCurve { key = 0 460.1 - key = 1 52 + key = 1 45 } - massMult = 1.38 + massMult = 1.3114 - %ullage = True - %ignitions = 15 - %IGNITOR_RESOURCE + ullage = True + ignitions = 15 + IGNITOR_RESOURCE { - %name = ElectricCharge - %amount = 0.5 + name = ElectricCharge + amount = 0.5 } //no data, never flown @@ -1349,24 +1498,24 @@ TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 9000 //Another major revision with plan for reuse in future, give ~2.5 hours (CECE rated time) - ratedBurnTime = 1350 //Set to allow full burning of 129 T of propellant (EUS full load) with 4x engines + ratedBurnTime = 1275 safeOverburn = true - ignitionReliabilityStart = 0.990206 - ignitionReliabilityEnd = 0.998454 - cycleReliabilityStart = 0.980612 - cycleReliabilityEnd = 0.996939 + ignitionReliabilityStart = 0.995320 + ignitionReliabilityEnd = 0.999261 + cycleReliabilityStart = 0.990686 + cycleReliabilityEnd = 0.998529 ignitionDynPresFailMultiplier = 0.08 - techTransfer = RL10C-2-1,RL10C-1-1,RL10C-1,RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 + techTransfer = RL10C-2-1,RL10C-2,RL10C-1-1,RL10C-1A,RL10C-1,RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 } } CONFIG { - name = RL10C-X + name = RL10E-1 specLevel = prototype - minThrust = 107.291 - maxThrust = 107.291 + minThrust = 107.3 + maxThrust = 107.3 heatProduction = 100 - description = Planned upgrade of RL10C-1-1 for use on Vulcan-Centaur and potentially the Exporation Upper Stage + description = Extensive upgrade of the RL-10, with an additively manufactured Copper-Chrome combustion chamber and C-Sic nozzle extension. PROPELLANT { name = LqdHydrogen @@ -1381,16 +1530,16 @@ atmosphereCurve { key = 0 460.9 - key = 1 52 + key = 1 24 } - massMult = 1.377 + massMult = 1.3593 - %ullage = True - %ignitions = 15 - %IGNITOR_RESOURCE + ullage = True + ignitions = 25 + IGNITOR_RESOURCE { - %name = ElectricCharge - %amount = 0.5 + name = ElectricCharge + amount = 0.5 } //no data, never flown @@ -1400,12 +1549,62 @@ testedBurnTime = 9000 //Another major revision with plan for reuse in future, give ~2.5 hours (CECE rated time) ratedBurnTime = 1130 safeOverburn = true - ignitionReliabilityStart = 0.990206 - ignitionReliabilityEnd = 0.998454 - cycleReliabilityStart = 0.980612 - cycleReliabilityEnd = 0.996939 + ignitionReliabilityStart = 0.995320 + ignitionReliabilityEnd = 0.999261 + cycleReliabilityStart = 0.990686 + cycleReliabilityEnd = 0.998529 + ignitionDynPresFailMultiplier = 0.08 + techTransfer = RL10C-1-1,RL10C-1A,RL10C-1,RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 + } + } + CONFIG + { + name = RL10E-3EL + specLevel = prototype + minThrust = 108.1 + maxThrust = 108.1 + heatProduction = 100 + description = RL10E-1 modified for extremely long life to allow for 50 earth-moon trips on a commercial passenger transport vehicle. + PROPELLANT + { + name = LqdHydrogen + ratio = 0.7741 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.2259 //4.7 + } + atmosphereCurve + { + key = 0 470.5 + key = 1 24 + } + massMult = 1.6287 + + ullage = True + ignitions = 260 + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + //no data, never flown + //using C-1 data + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 180000 //50 hours life + ratedBurnTime = 1350 //idk, no more than 22 minute single burn? Same as C-3 + safeOverburn = true + overburnPenalty = 1.1 //Nearly infinite fatigue life + ignitionReliabilityStart = 0.995320 + ignitionReliabilityEnd = 0.999261 + cycleReliabilityStart = 0.990686 + cycleReliabilityEnd = 0.998529 ignitionDynPresFailMultiplier = 0.08 - techTransfer = RL10C-1-1,RL10C-1,RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 + techTransfer = RL10E-1,RL10C-1-1,RL10C-1A,RL10C-1,RL10B-2,RL10A-4-2N,RL10A-4-1N,RL10A-4-1-2,RL10A-4N,RL10A-4,RL10A-3-3A,RL10A-3-3,RL10A-3-1,RL10A-1:50 } } CONFIG