diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/BNTR25k_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/BNTR25k_Config.cfg index a79860252b..5fcc2e51b3 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/BNTR25k_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/BNTR25k_Config.cfg @@ -4,28 +4,78 @@ // Manufacturer: Aerojet Rocketdyne // // ================================================================================= -// BNTR +// BNTR-25k // Hydrogen Mode // -// Dry Mass: 3670 kg +// Dry Mass: 3670 kg [4] TWR 3 // Thrust (SL): ??? kN -// Thrust (Vac): 111.6 kN -// ISP: 380 SL / 894 Vac -// Burn Time: 3600/56700 1.75 hrs burn/mission * 9 mission expected lifetime -// Chamber Pressure: 6.89 MPa +// Thrust (Vac): 111.6 kN [4] +// ISP: 1 SL / 894 Vac [4] sl calculated with RPA +// Burn Time: 3600/56700 [4] 1.75 hrs burn/mission * 9 mission expected lifetime +// Chamber Pressure: 6.89 MPa [4] 1000 psi +// Chamber Temp: 2650 K [4] 4770 R // Propellant: LH2 // Prop Ratio: N/A // Throttle: N/A -// Nozzle Ratio: 389 -// Ignitions: 60 +// Nozzle Ratio: 389 [4] +// Ignitions: 60? +// ================================================================================= +// TRITON +// Bipropellant mode +// +// Dry Mass: 3670 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 305.04 kN [1] same increase as 15klbf BNTR +// ISP: 25 SL / 626 Vac calculated with RPA +// Burn Time: ??? +// Chamber Pressure: 6.89 MPa [4] 1000 psi +// Chamber Temp: 2650 K [4] 4770 R +// Propellant: LOX / LH2 +// Prop Ratio: 3.0 from [1] +// Throttle: N/A +// Nozzle Ratio: 389 [4] +// Ignitions: 60? +// ================================================================================= +// BNTR-25k-Ammonia +// Speculative Ammonia config +// +// Dry Mass: 3670 kg [4] TWR 3 +// Thrust (SL): ??? kN +// Thrust (Vac): 226.24 kN assuming constant power +// ISP: 1 SL / 441 Vac calculated with RPA +// Burn Time: 3600/56700 [4] 1.75 hrs burn/mission * 9 mission expected lifetime +// Chamber Pressure: 6.89 MPa [4] 1000 psi +// Chamber Temp: 2650 K [4] 4770 R +// Propellant: LNH3 +// Prop Ratio: N/A +// Throttle: N/A +// Nozzle Ratio: 389 [4] +// Ignitions: 60? +// ================================================================================= +// BNTR-25k-Methane +// Speculative "Methane" config +// Methane/Ammonia mix prevents coking and gets better Isp +// +// Dry Mass: 3670 kg [4] TWR 3 +// Thrust (SL): ??? kN +// Thrust (Vac): 204.03 kN assuming constant power +// ISP: 6 SL / 489 Vac calculated with RPA +// Burn Time: 3600/56700 [4] 1.75 hrs burn/mission * 9 mission expected lifetime +// Chamber Pressure: 6.89 MPa [4] 1000 psi +// Chamber Temp: 2650 K [4] 4770 R +// Propellant: LNH3/LCH4 +// Prop Ratio: 2.33 NH3/CH4 +// Throttle: N/A +// Nozzle Ratio: 389 [4] +// Ignitions: 60? // ================================================================================= // Sources: -// "Bimodal" Nuclear Thermal Rocket (BNTR) Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20040182399.pdf -// AIAA - TRITON (TRImodal Thrust Optimized Nuclear rocket engine): http://alternatewars.com/BBOW/Space_Engines/AIAA-2004-3863_TRITON.pdf -// Crewed Mars Mission using Bimodal Nuclear Thermal Electric Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140009579.pdf -// LEU NTP Engine System Trades and Mission Options http://anstd.ans.org/NETS-2019-Papers/Track-2--Mission-Concepts-and-Logistics/abstract-29-0.pdf +// [1]"Bimodal" Nuclear Thermal Rocket (BNTR) Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20040182399.pdf +// [2]AIAA - TRITON (TRImodal Thrust Optimized Nuclear rocket engine): http://alternatewars.com/BBOW/Space_Engines/AIAA-2004-3863_TRITON.pdf +// [3]Crewed Mars Mission using Bimodal Nuclear Thermal Electric Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140009579.pdf +// [4]LEU NTP Engine System Trades and Mission Options http://anstd.ans.org/NETS-2019-Papers/Track-2--Mission-Concepts-and-Logistics/abstract-29-0.pdf // Used by: @@ -71,7 +121,7 @@ modded = False origMass = 3.470 //3670 kg - 200 kg fuel - primaryDescription = Hydrogen NTR + primaryDescription = NTR secondaryDescription = LOX-Augmented NTR toPrimaryText = Disable Thrust Augmentation toSecondaryText = Engage Thrust Augmentation @@ -113,8 +163,11 @@ atmosphereCurve { key = 0 894 - key = 1 300 + key = 1 1 } + %chamberNominalTemp = 2650 + %maxEngineTemp = 3100 + //LANTR was abandonded by this point, but why not add it anyway... SUBCONFIG { @@ -147,8 +200,8 @@ atmosphereCurve { - key = 0 620 - key = 1 320 + key = 0 626 + key = 1 25 } } TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -169,6 +222,133 @@ techTransfer = BNTR:20 } } + CONFIG + { + name = BNTR25k-Ammonia + description = Speculative version using Ammonia as propellant. No LOX-Augmentation on account of poor performance. + specLevel = speculative + minThrust = 226.24 + maxThrust = 226.24 + massMult = 1.0 + throttleResponseRate = 0.055 // Should be around 30 seconds to ramp up from 0% thrust to 100% thrust. + + ullage = True + pressureFed = False + ignitions = 60 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + PROPELLANT + { + name = LqdAmmonia + ratio = 1.0 + DrawGauge = True + } + + PROPELLANT + { + name = UraniumNitride + ratio = 1.0813e-15 + DrawGauge = False + ignoreForIsp = True + } + + atmosphereCurve + { + key = 0 441 + key = 1 1 + } + %chamberNominalTemp = 2650 + %maxEngineTemp = 3100 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedContinuousBurnTime = 3600 + ratedBurnTime = 56700 + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + + techTransfer = BNTR:20 + } + } + CONFIG + { + name = BNTR25k-Methane + description = Speculative version using Methane-Ammonia mix as propellant. No LOX-Augmentation on account of poor performance. + specLevel = sciFi //I don't know if RPA actually calculates this mixture dissociation correctly + minThrust = 204.03 + maxThrust = 204.03 + massMult = 1.0 + throttleResponseRate = 0.055 // Should be around 30 seconds to ramp up from 0% thrust to 100% thrust. + + ullage = True + pressureFed = False + ignitions = 60 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + PROPELLANT + { + name = LqdAmmonia + ratio = 0.5858 + } + PROPELLANT + { + name = LqdMethane + ratio = 0.4142 + DrawGauge = True + } + + PROPELLANT + { + name = UraniumNitride + ratio = 1.0813e-15 + DrawGauge = False + ignoreForIsp = True + } + + atmosphereCurve + { + key = 0 489 + key = 1 6 + } + %chamberNominalTemp = 2650 + %maxEngineTemp = 3100 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedContinuousBurnTime = 3600 + ratedBurnTime = 56700 + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + + techTransfer = BNTR:20 + } + } } MODULE diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/BNTR_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/BNTR_Config.cfg index 0e50daad0e..b778c35f14 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/BNTR_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/BNTR_Config.cfg @@ -10,13 +10,14 @@ // Dry Mass: 2270 Kg // Thrust (SL): ??? kN // Thrust (Vac): 66.72 kN -// ISP: 380 SL / 930 Vac -// Burn Time: 3600/36000 guess 10 hours lifespan? -// Chamber Pressure: 6.89 MPa +// ISP: 291 SL / 925 Vac [1] 2800 K, 2000 psi, 500:1 nozzle, sl calculated with RPA +// Burn Time: 3600/36000 [1] 10 hours lifespan at 2800 K +// Chamber Pressure: 13.79 MPa +// Chamber Temp: 2800 K // Propellant: LH2 // Prop Ratio: N/A -// Throttle: N/A -// Nozzle Ratio: ??? +// Throttle: 66% min throttle? +// Nozzle Ratio: 500 [1] // Ignitions: 60 // ================================================================================= // TRITON @@ -24,22 +25,56 @@ // // Dry Mass: 2270 Kg // Thrust (SL): ??? kN -// Thrust (Vac): 182.37 kN -// ISP: ??? SL / 645 Vac +// Thrust (Vac): 182.37 kN [1] based on estimated TWR of 8.2 +// ISP: 214 SL / 645 Vac [1] 2800 K, 2000 psi, 500:1 nozzle, sl calculated with RPA // Burn Time: ??? -// Chamber Pressure: 6.89 MPa +// Chamber Pressure: 13.79 MPa +// Chamber Temp: 2800 K // Propellant: LOX / LH2 -// Prop Ratio: 3.0 +// Prop Ratio: 3.0 from [1] // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 500 [1] +// Ignitions: 60 +// ================================================================================= +// BNTR-Ammonia +// Speculative Ammonia config +// +// Dry Mass: 2270 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 135.05 kN assuming constant power +// ISP: 141 SL / 457 Vac calculated with RPA +// Burn Time: 3600/36000 [1] 10 hours lifespan at 2800 K +// Chamber Pressure: 13.79 MPa +// Chamber Temp: 2800 K +// Propellant: LNH3 +// Prop Ratio: N/A +// Throttle: 66% min throttle? +// Nozzle Ratio: 500 [1] +// Ignitions: 60 +// ================================================================================= +// BNTR-Methane +// Speculative "Methane" config +// Methane/Ammonia mix prevents coking and gets better Isp +// +// Dry Mass: 2270 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 120.54 kN assuming constant power +// ISP: 159 SL / 512 Vac calculated with RPA +// Burn Time: 3600/36000 [1] 10 hours lifespan at 2800 K +// Chamber Pressure: 13.79 MPa +// Chamber Temp: 2800 K +// Propellant: LNH3/LCH4 +// Prop Ratio: 2.33 NH3/CH4 +// Throttle: 66% min throttle? +// Nozzle Ratio: 500 [1] // Ignitions: 60 // ================================================================================= // Sources: -// "Bimodal" Nuclear Thermal Rocket (BNTR) Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20040182399.pdf -// AIAA - TRITON (TRImodal Thrust Optimized Nuclear rocket engine): http://alternatewars.com/BBOW/Space_Engines/AIAA-2004-3863_TRITON.pdf -// Crewed Mars Mission using Bimodal Nuclear Thermal Electric Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140009579.pdf +// [1]"Bimodal" Nuclear Thermal Rocket (BNTR) Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20040182399.pdf +// [2]AIAA - TRITON (TRImodal Thrust Optimized Nuclear rocket engine): http://alternatewars.com/BBOW/Space_Engines/AIAA-2004-3863_TRITON.pdf +// [3]Crewed Mars Mission using Bimodal Nuclear Thermal Electric Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140009579.pdf // Used by: @@ -53,7 +88,7 @@ %category = Engine %title = #roBNTRTitle //Bimodal NTR %manufacturer = #roMfrAerojetRocketdyne - %description = #roBNTRDesc //Low thrust pump-fed expander nuclear engine. Evolved from the original NERVA design, the Bimodal NTR, instead of wasting precious propellant mass on cooling the engine reactor, uses a Brayton cycle electricity generator unit to convert the waste thermal energy into useful electrical power. It also supports liquid oxygen injection (TRITON - trimodal operation) for increased thrust at the cost of lower overall efficiency. + %description = #roBNTRDesc @tags ^= :$: USA aerojet rocketdyne ajr bimodal ntr bntr nuclear pump upper lqdhydrogen lqdoxygen @@ -85,7 +120,7 @@ modded = False origMass = 2.160 //2215 kg - 55 kg fuel - primaryDescription = Hydrogen NTR + primaryDescription = NTR secondaryDescription = LOX-Augmented NTR toPrimaryText = Disable Thrust Augmentation toSecondaryText = Engage Thrust Augmentation @@ -126,9 +161,11 @@ atmosphereCurve { - key = 0 930 - key = 1 380 + key = 0 925 + key = 1 291 } + %chamberNominalTemp = 2800 + %maxEngineTemp = 3100 SUBCONFIG { @@ -161,7 +198,7 @@ atmosphereCurve { key = 0 645 - key = 1 390 + key = 1 214 } } TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -180,6 +217,128 @@ reliabilityMidTangentWeight = 0 } } + CONFIG + { + name = BNTR-Ammonia + description = Speculative version using Ammonia as propellant. No LOX-Augmentation on account of poor performance. + specLevel = speculative + minThrust = 135.05 + maxThrust = 135.05 + massMult = 1.0 + throttleResponseRate = 0.055 // Should be around 30 seconds to ramp up from 0% thrust to 100% thrust. + + ullage = True + pressureFed = False + ignitions = 60 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + PROPELLANT + { + name = LqdAmmonia + ratio = 1.0 + } + + PROPELLANT + { + name = EnrichedUranium + ratio = 1.0813e-15 + DrawGauge = False + ignoreForIsp = True + } + + atmosphereCurve + { + key = 0 457 + key = 1 141 + } + %chamberNominalTemp = 2800 + %maxEngineTemp = 3100 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedContinuousBurnTime = 3600 + ratedBurnTime = 36000 + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + } + } + CONFIG + { + name = BNTR-Methane + description = Speculative version using Methane-Ammonia mix as propellant. No LOX-Augmentation on account of poor performance. + specLevel = sciFi //I don't know if RPA actually calculates this mixture dissociation correctly + minThrust = 120.54 + maxThrust = 120.54 + massMult = 1.0 + throttleResponseRate = 0.055 // Should be around 30 seconds to ramp up from 0% thrust to 100% thrust. + + ullage = True + pressureFed = False + ignitions = 60 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + PROPELLANT + { + name = LqdAmmonia + ratio = 0.5858 + } + PROPELLANT + { + name = LqdMethane + ratio = 0.4142 + DrawGauge = True + } + + PROPELLANT + { + name = EnrichedUranium + ratio = 1.0813e-15 + DrawGauge = False + ignoreForIsp = True + } + + atmosphereCurve + { + key = 0 512 + key = 1 159 + } + %chamberNominalTemp = 2800 + %maxEngineTemp = 3100 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedContinuousBurnTime = 3600 + ratedBurnTime = 36000 + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + } + } } MODULE diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/INsTAR_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/INsTAR_Config.cfg index 57c729c4da..389787ee45 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/INsTAR_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/INsTAR_Config.cfg @@ -7,28 +7,81 @@ // INsTAR // // -// Dry Mass: 2900 Kg +// Dry Mass: 2900 kg [5] // Thrust (SL): ??? kN -// Thrust (Vac): 266.89 kN -// ISP: ??? SL / 1082 Vac +// Thrust (Vac): 266.89 kN [5] +// ISP: 363 SL / 1082 Vac [5] these numbers imply 3500K, but paper says 3300K? sl calculated with RPA // Burn Time: 3600/36000 guess, LEU should extend lifetime -// Chamber Pressure: 11.19 MPa +// Chamber Pressure: 11.19 MPa [5] 1623 psi +// Chamber Temp: 3500 K [5] // Propellant: LH2 // Prop Ratio: N/A // Throttle: N/A +// Nozzle Ratio: 389 same as BNTR25k? +// Ignitions: 60 +// ================================================================================= +// LAINsTAR +// Bipropellant mode +// +// Dry Mass: 2900 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 729.51 kN [1] same increase as 15klbf BNTR +// ISP: 232 SL / 688 Vac calculated with RPA +// Burn Time: ??? +// Chamber Pressure: 11.19 MPa [5] 1623 psi +// Chamber Temp: 3500 K +// Propellant: LOX / LH2 +// Prop Ratio: 3.0 from [1] +// Throttle: N/A // Nozzle Ratio: 389 +// Ignitions: 60? +// ================================================================================= +// INsTAR-Ammonia +// Speculative Ammonia config +// +// Dry Mass: 2900 kg [5] +// Thrust (SL): ??? kN +// Thrust (Vac): 544.85 kN assuming constant power +// ISP: 177 SL / 530 Vac calculated with RPA +// Burn Time: 3600/36000 guess, LEU should extend lifetime +// Chamber Pressure: 11.19 MPa [5] 1623 psi +// Chamber Temp: 3500 K [5] +// Propellant: LNH3 +// Prop Ratio: N/A +// Throttle: N/A +// Nozzle Ratio: 389 same as BNTR25k? +// Ignitions: 60 +// ================================================================================= +// INsTAR-Methane +// Speculative "Methane" config +// Methane/Ammonia mix prevents coking and gets better Isp +// +// Dry Mass: 2900 kg [5] +// Thrust (SL): ??? kN +// Thrust (Vac): 509.30 kN assuming constant power +// ISP: 191 SL / 569 Vac calculated with RPA +// Burn Time: 3600/36000 guess, LEU should extend lifetime +// Chamber Pressure: 11.19 MPa [5] 1623 psi +// Chamber Temp: 3500 K [5] +// Propellant: LNH3/LCH4 +// Prop Ratio: 4.00 NH3/CH4 +// Throttle: N/A +// Nozzle Ratio: 389 same as BNTR25k? // Ignitions: 60 // ================================================================================= // Sources: -// "Bimodal" Nuclear Thermal Rocket (BNTR) Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20040182399.pdf -// AIAA - TRITON (TRImodal Thrust Optimized Nuclear rocket engine): http://alternatewars.com/BBOW/Space_Engines/AIAA-2004-3863_TRITON.pdf -// Crewed Mars Mission using Bimodal Nuclear Thermal Electric Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140009579.pdf -// LEU NTP Engine System Trades and Mission Options http://anstd.ans.org/NETS-2019-Papers/Track-2--Mission-Concepts-and-Logistics/abstract-29-0.pdf +// [1]"Bimodal" Nuclear Thermal Rocket (BNTR) Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20040182399.pdf +// [2]AIAA - TRITON (TRImodal Thrust Optimized Nuclear rocket engine): http://alternatewars.com/BBOW/Space_Engines/AIAA-2004-3863_TRITON.pdf +// [3]Crewed Mars Mission using Bimodal Nuclear Thermal Electric Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140009579.pdf +// [4]LEU NTP Engine System Trades and Mission Options http://anstd.ans.org/NETS-2019-Papers/Track-2--Mission-Concepts-and-Logistics/abstract-29-0.pdf +// [5]https://www.projectrho.com/public_html/rocket/enginelist2.php // Used by: +// I'm not including LOX-Augmented Ammonia/Methane configs because they are worse all-round than a normal +// chemical engine // ================================================== @PART[*]:HAS[#engineType[INsTAR]]:FOR[RealismOverhaulEngines] @@ -68,7 +121,7 @@ modded = False origMass = 2.600 //2900 kg - 300 kg fuel - primaryDescription = Hydrogen NTR + primaryDescription = NTR secondaryDescription = LOX-Augmented NTR toPrimaryText = Disable Thrust Augmentation toSecondaryText = Engage Thrust Augmentation @@ -110,8 +163,10 @@ atmosphereCurve { key = 0 1082 - key = 1 300 + key = 1 363 } + %chamberNominalTemp = 3500 + %maxEngineTemp = 3700 //why not? SUBCONFIG @@ -145,8 +200,8 @@ atmosphereCurve { - key = 0 750 - key = 1 390 + key = 0 688 + key = 1 232 } } TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -167,6 +222,133 @@ techTransfer = BNTR25k,SNTPPFE100,SNTPPFE100-Prototype:20 } } + CONFIG + { + name = INsTAR-Ammonia + description = Speculative version using Ammonia as propellant. No LOX-Augmentation on account of poor performance. + specLevel = speculative + minThrust = 544.85 + maxThrust = 544.85 + massMult = 1.0 + throttleResponseRate = 0.1 //derived from SNTP core, should be around 10 secs too fully ramp up to 100% from 0%? + + ullage = True + pressureFed = False + ignitions = 60 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + PROPELLANT + { + name = LqdAmmonia + ratio = 1.0 + DrawGauge = True + } + + PROPELLANT + { + name = UraniumNitride + ratio = 1.0813e-15 + DrawGauge = False + ignoreForIsp = True + } + + atmosphereCurve + { + key = 0 530 + key = 1 177 + } + %chamberNominalTemp = 3500 + %maxEngineTemp = 3700 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedContinuousBurnTime = 3600 + ratedBurnTime = 36000 + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + + techTransfer = BNTR25k,SNTPPFE100,SNTPPFE100-Prototype:20 + } + } + CONFIG + { + name = INsTAR-Methane + description = Speculative version using Methane-Ammonia mix as propellant. No LOX-Augmentation on account of poor performance. + specLevel = sciFi //I don't know if RPA actually calculates this mixture dissociation correctly + minThrust = 544.85 + maxThrust = 544.85 + massMult = 1.0 + throttleResponseRate = 0.1 //derived from SNTP core, should be around 10 secs too fully ramp up to 100% from 0%? + + ullage = True + pressureFed = False + ignitions = 60 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + PROPELLANT + { + name = LqdAmmonia + ratio = 0.7080 + } + PROPELLANT + { + name = LqdMethane + ratio = 0.2920 + DrawGauge = True + } + + PROPELLANT + { + name = UraniumNitride + ratio = 1.0813e-15 + DrawGauge = False + ignoreForIsp = True + } + + atmosphereCurve + { + key = 0 569 + key = 1 191 + } + %chamberNominalTemp = 3500 + %maxEngineTemp = 3700 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedContinuousBurnTime = 3600 + ratedBurnTime = 36000 + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + + techTransfer = BNTR25k,SNTPPFE100,SNTPPFE100-Prototype:20 + } + } } MODULE diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/KIWIA24_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/KIWIA24_Config.cfg index 58bc60360e..1f0a0bd125 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/KIWIA24_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/KIWIA24_Config.cfg @@ -7,15 +7,15 @@ // Kiwi A24 // // Dry Mass: 12080 kg -// Thrust (SL): 29 kN -// Thrust (Vac): 21 kN -// ISP: 594 SL / 810 Vac +// Thrust (SL): ??? kN +// Thrust (Vac): 29.3 kN +// ISP: 369 SL / 768 Vac calculated with RPA // Burn Time: 360 -// Chamber Pressure: 1.4 MPa +// Chamber Pressure: 1.415 MPa +// Chamber Temp: 2300 K // Propellant: LH2 // Prop Ratio: N/A -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? +// Throttle: N/A // Nozzle Ratio: 24 // Ignitions: 2 // ================================================================================= @@ -35,6 +35,7 @@ { @title = #roKIWIA24Title //Kiwi A3 Atomic Rocket Motor @manufacturer = #roMfrWestinghouse + %description = #roKIWIA24Desc @tags ^= :$: USA westinghouse aerojet kiwi a24 nuclear pump upper lqdhydrogen @@ -76,8 +77,8 @@ } atmosphereCurve { - key = 0 810 - key = 1 594 + key = 0 768 + key = 1 369 } %chamberNominalTemp = 2300 %maxEngineTemp = 2650 diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/KIWIB48_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/KIWIB48_Config.cfg index 6ed5278fb1..149411abc1 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/KIWIB48_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/KIWIB48_Config.cfg @@ -1,21 +1,21 @@ // ================================================== -// Kiwi A24 +// Kiwi B48 // // Manufacturer: Aerojet & Westinghouse // // ================================================================================= -// Kiwi A24 +// Kiwi B48 // // Dry Mass: 14890 kg // Thrust (SL): 220 kN // Thrust (Vac): 170 kN -// ISP: 695 SL / 898 Vac +// ISP: 431 SL / 830 Vac calculated with RPA // Burn Time: 750 -// Chamber Pressure: 3.6 MPa +// Chamber Pressure: 3.61 MPa +// Chamber Temp: 2473 K // Propellant: LH2 // Prop Ratio: N/A -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? +// Throttle: N/A // Nozzle Ratio: 66 // Ignitions: 4 // ================================================================================= @@ -24,6 +24,7 @@ { @title = #roKIWIB48Title //Kiwi B4E Atomic Rocket Motor @manufacturer = #roMfrWestinghouse + %description = #roKIWIB48Desc @tags ^= :$: USA westinghouse aerojet kiwi b48 nuclear pump upper lqdhydrogen @@ -65,8 +66,8 @@ } atmosphereCurve { - key = 0 898 - key = 1 695 + key = 0 831 + key = 1 431 } %chamberNominalTemp = 2473 %maxEngineTemp = 2573 diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/LRCLNTR_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/LRCLNTR_Config.cfg index bbaeaaa736..e34cace212 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/LRCLNTR_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/LRCLNTR_Config.cfg @@ -10,14 +10,15 @@ // Dry Mass: 7424 Kg // Thrust (SL): ??? kN // Thrust (Vac): 145.6 kN -// ISP: ??? SL / 1400 Vac +// ISP: 989 SL / 1400 Vac sl calculated with RPA (please do not use at SL) // Burn Time: 3600 // Chamber Pressure: 20.0 MPa +// Chamber Temp: 5060 K // Propellant: LH2 // Prop Ratio: N/A // Throttle: N/A -// Nozzle Ratio: ??? -// Ignitions: ??? +// Nozzle Ratio: 145? study didn't look at nozzles, assume enough for 99.9% recombination +// Ignitions: 10? // ================================================================================= // Sources: @@ -118,8 +119,11 @@ atmosphereCurve { key = 0 1400 - key = 1 500 + key = 1 989 } + %chamberNominalTemp = 5060 + %maxEngineTemp = 5580 + TESTFLIGHT:NEEDS[TestLite|TestFlight] { ratedBurnTime = 3600 diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVAII_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVAII_Config.cfg index 24766213e7..9c593d7446 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVAII_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVAII_Config.cfg @@ -9,13 +9,13 @@ // Dry Mass: 12940 kg // Thrust (SL): 867 kN // Thrust (Vac): 387 kN -// ISP: 380 SL / 850 Vac +// ISP: 390 SL / 850 Vac calculated with RPA // Burn Time: 36000 s (60m max per cycle) // Chamber Pressure: 4.3 MPa +// Chamber Temp: 2500 K // Propellant: LH2 // Prop Ratio: N/A -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? +// Throttle: N/A // Nozzle Ratio: 100 // Ignitions: 60 // ================================================================================= @@ -37,7 +37,7 @@ { @title = #roNERVAIITitle //NERVA II @manufacturer = #roMfrAerojet - @description = #roNERVAIIDesc //A later 70s atomic engine with relatively low TWR but high ISP and a power generation of 4200 MW. Derived from the Phoebus 2A ground demonstrator, tested in 1968. + @description = #roNERVAIIDesc @tags ^= :$: USA aerojet nerva II nuclear pump upper lqdhydrogen @@ -81,7 +81,7 @@ atmosphereCurve { key = 0 850 - key = 1 380 + key = 1 390 } %chamberNominalTemp = 2500 %maxEngineTemp = 2870 diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVANRX_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVANRX_Config.cfg index 4b917da438..c07585c138 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVANRX_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVANRX_Config.cfg @@ -7,16 +7,16 @@ // NERVA NRX // // Dry Mass: 11330 kg -// Thrust (SL): 243 kN -// Thrust (Vac): 190 kN -// ISP: 693 SL / 885 Vac +// Thrust (SL): ??? kN +// Thrust (Vac): 243 kN +// ISP: 529 SL / 848 Vac calculated with RPA // Burn Time: 3720 -// Chamber Pressure: 4.1 MPa +// Chamber Pressure: 4.15 MPa +// Chamber Temp: 2550 K // Propellant: LH2 // Prop Ratio: N/A -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? -// Nozzle Ratio: 100 +// Throttle: N/A +// Nozzle Ratio: 50 // Ignitions: 30 // ================================================================================= @@ -35,6 +35,7 @@ { @title = #roNERVA_NRXTitle //NERVA NRX @manufacturer = #roMfrAerojet + @description = #roNERVA_NRXDesc @tags ^= :$: USA aerojet westinghouse nerva nrx nuclear pump upper lqdhydrogen @@ -76,10 +77,10 @@ } atmosphereCurve { - key = 0 885 - key = 1 693 + key = 0 848 + key = 1 529 } - %chamberNominalTemp = 2555 + %chamberNominalTemp = 2550 %maxEngineTemp = 2870 TESTFLIGHT:NEEDS[TestLite|TestFlight] diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVAXE_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVAXE_Config.cfg index 762c6f9829..2dae72f368 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVAXE_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVAXE_Config.cfg @@ -7,15 +7,15 @@ // NERVA XE Prime // // Dry Mass: 10380 kg -// Thrust (SL): 239 kN -// Thrust (Vac): 178 kN -// ISP: 669 SL / 898 Vac +// Thrust (SL): ??? kN +// Thrust (Vac): 239 kN +// ISP: 348 SL / 850 Vac calculated with RPA // Burn Time: 3720 -// Chamber Pressure: 4.1 MPa +// Chamber Pressure: 3.81 MPa +// Chamber Temp: 2500 K // Propellant: LH2 // Prop Ratio: N/A -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? +// Throttle: N/A // Nozzle Ratio: 100 // Ignitions: 60 // ================================================================================= @@ -77,9 +77,11 @@ } atmosphereCurve { - key = 0 898 - key = 1 669 + key = 0 850 + key = 1 348 } + %chamberNominalTemp = 2500 + %maxEngineTemp = 2870 TESTFLIGHT:NEEDS[TestLite|TestFlight] { diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVA_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVA_Config.cfg index 6bce61632a..8296eab04b 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVA_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/NERVA_Config.cfg @@ -7,15 +7,48 @@ // Nerva I // // Dry Mass: 10117 kg -// Thrust (SL): 334 kN -// Thrust (Vac): 153 kN -// ISP: 380 SL / 900 Vac //estimated +// Thrust (SL): ??? kN +// Thrust (Vac): 334 kN +// ISP: 285 SL / 900 Vac calculated with RPA // Burn Time: 36000 s (60m max per cycle) // Chamber Pressure: 3.1 MPa +// Chamber Temp: 2700 K as opposed to 2360 K of ground tests // Propellant: LH2 // Prop Ratio: N/A -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? +// Throttle: 66% min throttle? +// Nozzle Ratio: 100 +// Ignitions: 60 +// ================================================================================= +// Nerva I - Ammonia +// speculative Ammonia config +// +// Dry Mass: 10117 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 684.8 kN assuming constant thrust power +// ISP: 139 SL / 439 Vac calculated with RPA +// Burn Time: 36000 s (60m max per cycle) +// Chamber Pressure: 3.1 MPa +// Chamber Temp: 2700 K as opposed to 2360 K of ground tests +// Propellant: LNH3 +// Prop Ratio: N/A +// Throttle: 66% min throttle? +// Nozzle Ratio: 100 +// Ignitions: 60 +// ================================================================================= +// Nerva I - Methane +// speculative "Methane" config +// Methane/Ammonia mix prevents coking and gets better Isp +// +// Dry Mass: 10117 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 630.18 kN assuming constant thrust power +// ISP: 148 SL / 477 Vac calculated with RPA +// Burn Time: 36000 s (60m max per cycle) +// Chamber Pressure: 3.1 MPa +// Chamber Temp: 2700 K as opposed to 2360 K of ground tests +// Propellant: LNH3/LCH4 +// Prop Ratio: 4.88 NH3/CH4 +// Throttle: 66% min throttle? // Nozzle Ratio: 100 // Ignitions: 60 // ================================================================================= @@ -33,13 +66,16 @@ // NERVA requirements specified 825s minimum Isp. However, NRX and XE tests demonstrated over 850 s. // Considering flight NERVA engines were to run hotter, and use more efficient full-flow "topping" // cycle, 900 seconds was estimated as the achievable performance. + +// I guess we're assuming 2860 R (2700 K) core temps to achieve that performance, which is at the edge of +// NERVA performance limits. // ================================================== @PART[*]:HAS[#engineType[NERVA]]:FOR[RealismOverhaulEngines] { @title = #roNERVATitle //NERVA I @manufacturer = #roMfrAerojet - @description = #roNERVADesc //A 1970s low TWR vacuum engine, the NERVA (Nuclear Engine for Rocket Vehicle Applications) is designed for orbital tugs and large rocket upper stages. + @description = #roNERVADesc @tags ^= :$: USA aerojet nerva nuclear pump upper lqdhydrogen @@ -82,10 +118,137 @@ atmosphereCurve { key = 0 900 - key = 1 380 + key = 1 285 + } + %chamberNominalTemp = 2700 + %maxEngineTemp = 2888 + + // http://www.alternatewars.com/BBOW/Space_Engines/NERVA_PV.png + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + //design parameters called for very short time between starts, but most mission plans coasted for hours or days between restarts + ratedBurnTime = 36000 // 10 hours + ratedContinuousBurnTime = 3600 //1 hour + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + } + } + CONFIG + { + name = NERVA-I-Ammonia + description = Speculative version using Ammonia as propellant. + specLevel = speculative + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 432.1 + maxThrust = 648.8 + + ignitions = 60 + %ullage = True + %throttleResponseRate = 0.035 //should be around 30 secs too fully ramp up to 100% from 0%. + %throttleStartedMult = 0.8 + %throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdAmmonia + ratio = 1.0 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 439 + key = 1 139 + } + %chamberNominalTemp = 2700 + %maxEngineTemp = 2888 + + // http://www.alternatewars.com/BBOW/Space_Engines/NERVA_PV.png + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + //design parameters called for very short time between starts, but most mission plans coasted for hours or days between restarts + ratedBurnTime = 36000 // 10 hours + ratedContinuousBurnTime = 3600 //1 hour + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + } + } + CONFIG + { + name = NERVA-I-Methane + description = Speculative version using Methane-Ammonia mix as propellant. + specLevel = sciFi //I don't know if RPA actually calculates this mixture dissociation correctly + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 419.7 + maxThrust = 630.2 + + ignitions = 60 + %ullage = True + %throttleResponseRate = 0.035 //should be around 30 secs too fully ramp up to 100% from 0%. + %throttleStartedMult = 0.8 + %throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdAmmonia + ratio = 0.7474 + } + PROPELLANT + { + name = LqdMethane + ratio = 0.2526 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 477 + key = 1 148 } - %chamberNominalTemp = 2360 - %maxEngineTemp = 2870 + %chamberNominalTemp = 2700 + %maxEngineTemp = 2888 // http://www.alternatewars.com/BBOW/Space_Engines/NERVA_PV.png TESTFLIGHT:NEEDS[TestLite|TestFlight] diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/PEWEE100_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/PEWEE100_Config.cfg index e3720718f8..7f0f7bb6e6 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/PEWEE100_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/PEWEE100_Config.cfg @@ -7,15 +7,48 @@ // Peewee // // Dry Mass: 2230 kg -// Thrust (SL): 111 kN -// Thrust (Vac): 83 kN -// ISP: 712 SL / 947 Vac +// Thrust (SL): ??? kN +// Thrust (Vac): 111 kN +// ISP: 415 SL / 901 Vac calculated with RPA // Burn Time: 2400 -// Chamber Pressure: 4.3 MPa +// Chamber Pressure: 4.34 MPa +// Chamber Temp: 2750 K // Propellant: LH2 // Prop Ratio: N/A -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? +// Throttle: 20% min throttle? +// Nozzle Ratio: 100 +// Ignitions: 12 +// ================================================================================= +// Peewee-Ammonia +// speculative Ammonia config +// +// Dry Mass: 2230 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 227.3 kN +// ISP: 202 SL / 440 Vac calculated with RPA +// Burn Time: 2400 +// Chamber Pressure: 4.34 MPa +// Chamber Temp: 2750 K +// Propellant: LNH3 +// Prop Ratio: N/A +// Throttle: N/A +// Nozzle Ratio: 100 +// Ignitions: 12 +// ================================================================================= +// Peewee-Methane +// Speculative "Methane" version +// Methane/Ammonia mix prevents coking and gets better Isp +// +// Dry Mass: 2230 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 227.3 kN +// ISP: 214 SL / 480 Vac calculated with RPA +// Burn Time: 2400 +// Chamber Pressure: 4.34 MPa +// Chamber Temp: 2750 K +// Propellant: LNH3/LCH4 +// Prop Ratio: 4.00 NH3/CH4 +// Throttle: N/A // Nozzle Ratio: 100 // Ignitions: 12 // ================================================================================= @@ -32,8 +65,9 @@ // ================================================== @PART[*]:HAS[#engineType[PEWEE100]]:FOR[RealismOverhaulEngines] { - @title = Peewee 100 Atomic Rocket Motor + @title = #roPEWEE100Title //Peewee 100 Atomic Rocket Motor @manufacturer = #roMfrAerojet + @description = #roPEWEE100Desc @tags ^= :$: USA aerojet westinghouse nerva pewee 100 nuclear pump upper lqdhydrogen @@ -47,7 +81,7 @@ modded = false origMass = 2.208 //2230 kg - 22 kg - CONFIG + CONFIG { name = PEWEE100-Hydrogen specLevel = prototype @@ -77,8 +111,136 @@ } atmosphereCurve { - key = 0 947 - key = 1 712 + key = 0 901 + key = 1 415 + } + %chamberNominalTemp = 2750 + %maxEngineTemp = 3000 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 28800 //8 hours + ratedContinuousBurnTime = 2400 // 40 minutes + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + } + } + CONFIG + { + name = PEWEE100-Ammonia + description = Speculative version using Ammonia as propellant. + specLevel = speculative + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 45.46 + maxThrust = 227.3 + massMult = 1 + heatProduction = 12 + + ignitions = 12 + %ullage = True + %throttleResponseRate = 0.035 //should be around 30 secs too fully ramp up to 100% from 0%. + %throttleStartedMult = 0.8 + %throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdAmmonia + ratio = 1.0 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 440 + key = 1 202 + } + %chamberNominalTemp = 2750 + %maxEngineTemp = 3000 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 28800 //8 hours + ratedContinuousBurnTime = 2400 // 40 minutes + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + } + } + CONFIG + { + name = PEWEE100-Methane + description = Speculative version using Methane-Ammonia mix as propellant. + specLevel = sciFi //I don't know if RPA actually calculates this mixture dissociation correctly + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 45.46 + maxThrust = 227.3 + massMult = 1 + heatProduction = 12 + + ignitions = 12 + %ullage = True + %throttleResponseRate = 0.035 //should be around 30 secs too fully ramp up to 100% from 0%. + %throttleStartedMult = 0.8 + %throttleStartupMult = 5.0 + + + PROPELLANT + { + name = LqdAmmonia + ratio = 0.7080 + } + PROPELLANT + { + name = LqdMethane + ratio = 0.2920 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 480 + key = 1 214 } %chamberNominalTemp = 2750 %maxEngineTemp = 3000 diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/Phoebus1_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/Phoebus1_Config.cfg index 4ede56a1b9..0a63ca70be 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/Phoebus1_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/Phoebus1_Config.cfg @@ -7,15 +7,15 @@ // Phoebus 1B // // Dry Mass: 9140 kg -// Thrust (SL): 299 kN -// Thrust (Vac): 232 kN -// ISP: 643 SL / 828 Vac +// Thrust (SL): ??? kN +// Thrust (Vac): 299 kN +// ISP: 501 SL / 828 Vac calculated with RPA // Burn Time: 2700 -// Chamber Pressure: 3.8 MPa +// Chamber Pressure: 3.77 MPa +// Chamber Temp: 2445 K 4401 R? Only way the stated ISP numbers make sense // Propellant: LH2 // Prop Ratio: N/A -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? +// Throttle: N/A // Nozzle Ratio: 50 // Ignitions: 4 // ================================================================================= @@ -35,6 +35,7 @@ { @title = #roPhoebus1N50Title //Phoebus 1B Atomic Rocket Motor @manufacturer = #roMfrAerojet + @description = #roPhoebus1N50Desc @tags ^= :$: USA aerojet westinghouse phoebus 1b n50 nuclear pump upper lqdhydrogen @@ -77,9 +78,9 @@ atmosphereCurve { key = 0 828 - key = 1 643 + key = 1 501 } - %chamberNominalTemp = 2255 + %chamberNominalTemp = 2445 %maxEngineTemp = 2870 TESTFLIGHT:NEEDS[TestLite|TestFlight] diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/Phoebus2_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/Phoebus2_Config.cfg index 54b90ccaf6..118a43c185 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/Phoebus2_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/Phoebus2_Config.cfg @@ -7,15 +7,15 @@ // Phoebus 2A // // Dry Mass: 16970 kg -// Thrust (SL): 913 kN -// Thrust (Vac): 682 kN -// ISP: 632 SL / 846 Vac +// Thrust (SL): ??? kN +// Thrust (Vac): 913 kN +// ISP: 336 SL / 813 Vac calculated with RPA // Burn Time: 2700 -// Chamber Pressure: 3.8 MPa +// Chamber Pressure: 3.83 MPa +// Chamber Temp: 2310 K 4158 R? // Propellant: LH2 // Prop Ratio: N/A -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? +// Throttle: N/A // Nozzle Ratio: 100 // Ignitions: 8 // ================================================================================= @@ -35,6 +35,7 @@ { @title = #roPhoebus2N100Title //Phoebus 2A Atomic Rocket Motor @manufacturer = #roMfrAerojet + @description = #roPhoebus2N100Desc @tags ^= :$: USA aerojet westinghouse phoebus 2a n100 nuclear pump upper lqdhydrogen @@ -76,10 +77,10 @@ } atmosphereCurve { - key = 0 846 - key = 1 632 + key = 0 813 + key = 1 336 } - %chamberNominalTemp = 2245 + %chamberNominalTemp = 2310 %maxEngineTemp = 2870 TESTFLIGHT:NEEDS[TestLite|TestFlight] diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/PrincetonLNTR_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/PrincetonLNTR_Config.cfg index 17fa1a4be0..e7dcacb8f1 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/PrincetonLNTR_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/PrincetonLNTR_Config.cfg @@ -10,28 +10,30 @@ // Dry Mass: 3629 Kg // Thrust (SL): ??? kN // Thrust (Vac): 39.03 kN -// ISP: ??? SL / 1350 Vac +// ISP: 545 SL / 1350 Vac sl calculated with RPA // Burn Time: 3600 // Chamber Pressure: 10.0 MPa +// Chamber Temp: 4873 K // Propellant: LH2 // Prop Ratio: N/A // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 221? // Ignitions: ??? // ================================================================================= // PrincetonLNTR-WCH -// Original design with WCH core. Limited to 5023 K due to fuel loss. +// Improved design with WCH core. Limited to 5023 K due to fuel loss. // // Dry Mass: 3629 Kg // Thrust (SL): ??? kN // Thrust (Vac): 40.88 kN -// ISP: ??? SL / 1414 Vac +// ISP: 570 SL / 1414 Vac // Burn Time: 3600 // Chamber Pressure: 10.0 MPa +// Chamber Temp: 5023 K // Propellant: LH2 // Prop Ratio: N/A // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 221? // Ignitions: ??? // ================================================================================= @@ -131,8 +133,11 @@ atmosphereCurve { key = 0 1350 - key = 1 500 + key = 1 545 } + %chamberNominalTemp = 4873 + %maxEngineTemp = 5580 + TESTFLIGHT:NEEDS[TestLite|TestFlight] { ratedBurnTime = 3600 @@ -193,8 +198,11 @@ atmosphereCurve { key = 0 1414 - key = 1 500 + key = 1 570 } + %chamberNominalTemp = 5023 + %maxEngineTemp = 5580 + TESTFLIGHT:NEEDS[TestLite|TestFlight] { ratedBurnTime = 3600 diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/RD0410MID_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/RD0410MID_Config.cfg index 02c67d0e78..b2ca4b236a 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/RD0410MID_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/RD0410MID_Config.cfg @@ -10,13 +10,14 @@ // Dry Mass: 2000 Kg // Thrust (SL): ??? kN // Thrust (Vac): 35.3 kN -// ISP: 902 SL / 910 Vac +// ISP: 561 SL / 910 Vac sl calculated with RPA // Burn Time: ??? -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.00 MPa +// Chamber Temp: 3000 K [3],[4] 3000 K makes more sense for the advertised performance than 2700 K // Propellant: Hydrogen -// Prop Ratio: ??? -// Throttle: N/A -// Nozzle Ratio: ??? +// Prop Ratio: N/A +// Throttle: 50%? +// Nozzle Ratio: 46 // Ignitions: 10 // ================================================================================= // RD-0410 @@ -25,31 +26,74 @@ // Dry Mass: 2000 Kg // Thrust (SL): ??? kN // Thrust (Vac): 71.2 kN -// ISP: 336 SL / 438 Vac +// ISP: 249 SL / 438 Vac sl calculated with RPA // Burn Time: ??? -// Chamber Pressure: ??? MPa +// Chamber Pressure: 4.80 MPa +// Chamber Temp: 3000 K [3],[4] 3000 K makes more sense for the advertised performance than 2700 K // Propellant: CH4 -// Prop Ratio: ??? +// Prop Ratio: N/A // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 46 +// Ignitions: 10 +// ================================================================================= +// RD-0410 +// Ammonia +// +// Dry Mass: 2000 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 72.84 kN assuming constant power +// ISP: 271 SL / 441 Vac calculated with RPA +// Burn Time: ??? +// Chamber Pressure: 4.00 MPa +// Chamber Temp: 3000 K [3],[4] 3000 K makes more sense for the advertised performance than 2700 K +// Propellant: Hydrogen +// Prop Ratio: N/A +// Throttle: 50%? +// Nozzle Ratio: 46 +// Ignitions: 10 +// ================================================================================= +// RD-0410 +// "Methane" +// Methane/Ammonia mix prevents coking and gets better Isp +// +// Dry Mass: 2000 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 67.34 kN assuming constant power +// ISP: 281 SL / 477 Vac calculated with RPA +// Burn Time: ??? +// Chamber Pressure: 4.00 MPa +// Chamber Temp: 3000 K [3],[4] 3000 K makes more sense for the advertised performance than 2700 K +// Propellant: LNH3/LCH4 +// Prop Ratio: 2.33 NH3/CH4 +// Throttle: 50%? +// Nozzle Ratio: 46 // Ignitions: 10 // ================================================================================= // Sources: -// http://www.astronautix.com/r/rd-0410.html +// [1]http://www.astronautix.com/r/rd-0410.html +// [2]https://www.techinsider.ru/made-in-russia/5983-k-marsu-na-reaktore-vzryvnaya-sila/ +// [3]http://www.cosmoworld.ru/spaceencyclopedia/programs/index.shtml?yard.html +// [4]https://kbkha.ru/deyatel-nost/raketnye-dvigateli-ao-kbha/yadernyj-raketnyj-dvigatel-rd0410-rd0411/ +// [5]https://topwar.ru/156377-jadernyj-raketnyj-dvigatel-rd0410-smelaja-razrabotka-bez-perspektiv.html +// [6]https://ecoruspace.me/%D0%A0%D0%94-0410.html +// [7]http://tdla.ssau.ru/uop/vvedrd/module6.pdf // Used by: // Notes: - +// RPA shows the RD-0410-Methane is over 50% graphite in the throat. It would probably suffer immediate and +// catastrophic coking. +// Also I can find no source that mentions it // ================================================== @PART[*]:HAS[#engineType[RD0410MID]]:FOR[RealismOverhaulEngines] { %title = #roRD0410MIDTitle //RD-0410 %manufacturer = #roMfrKBKhA + %description = #roRD0410MIDDesc - @tags ^= :$: USSR KB Khimavtomatika rd-0410 nuclear pump upper lqdhydrogen lqdmethane + @tags ^= :$: USSR KB Khimavtomatika rd-0410 11b91 nuclear pump upper lqdhydrogen lqdmethane %specLevel = prototype @@ -83,7 +127,7 @@ specLevel = prototype exhaustDamage = True ignitionThreshold = 0.1 - minThrust = 0 + minThrust = 17.65 maxThrust = 35.3 massMult = 1 ignitions = 10 @@ -106,8 +150,10 @@ atmosphereCurve { key = 0 910 - key = 1 902 + key = 1 561 } + %chamberNominalTemp = 3000 + %maxEngineTemp = 3500 //no data, never flew TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -136,11 +182,12 @@ CONFIG { name = RD-0410MID-Methane - specLevel = prototype + description = RD-0410 version using Methane as propellant. Not much information is available, but carbon coking would have likely caused severe issues. + specLevel = sciFi //This would experience catastrophic coking issues, and no source I can find mentions it anyway. Unless further information is found, I'm tagging this sciFi exhaustDamage = True ignitionThreshold = 0.1 massMult = 1.02 //Stated in some places as dual mode also(heptane added in hydrogen mode) - minThrust = 0 + minThrust = 35.6 maxThrust = 71.2 ignitions = 10 @@ -163,9 +210,134 @@ atmosphereCurve { key = 0 438 - key = 1 336 + key = 1 249 } + %chamberNominalTemp = 3000 + %maxEngineTemp = 3500 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 36000 // 10 hours + ratedContinuousBurnTime = 3600 // 1 hour + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + } + } + CONFIG + { + name = RD-0410MID-Ammonia + description = Speculative version using Ammonia as propellant. + specLevel = speculative + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 36.42 + maxThrust = 72.84 + massMult = 1 + ignitions = 10 + %ullage = True + %throttleResponseRate = 0.035 //should be around 12 secs to fully ramp up to 100% from 0%. Actual ramp data may not be available. + %throttleStartedMult = 0.8 + %throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdAmmonia + ratio = 1.0 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 441 + key = 1 271 + } + %chamberNominalTemp = 3000 + %maxEngineTemp = 3500 + + //no data, never flew + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 36000 // 10 hours + ratedContinuousBurnTime = 3600 // 1 hour + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + } + } + CONFIG + { + name = RD-0410MID-MethaneSpec + description = Speculative version using Methane-Ammonia mix as propellant. + specLevel = sciFi //I don't know if RPA actually calculates this mixture dissociation correctly + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 33.67 + maxThrust = 67.34 + massMult = 1 + ignitions = 10 + %ullage = True + %throttleResponseRate = 0.035 //should be around 12 secs to fully ramp up to 100% from 0%. Actual ramp data may not be available. + %throttleStartedMult = 0.8 + %throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdAmmonia + ratio = 0.5858 + } + PROPELLANT + { + name = LqdMethane + ratio = 0.4142 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 477 + key = 1 281 + } + %chamberNominalTemp = 3000 + %maxEngineTemp = 3500 + + //no data, never flew TESTFLIGHT:NEEDS[TestLite|TestFlight] { ratedBurnTime = 36000 // 10 hours diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/RD0411_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/RD0411_Config.cfg new file mode 100644 index 0000000000..885f89f5ca --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/RD0411_Config.cfg @@ -0,0 +1,339 @@ +// ================================================== +// RD-0411 +// +// Manufacturer: KB Khimavtomatiki (KBKhA) +// +// ================================================================================= +// RD-0411 (11B92, RO-31?) +// Hydrogen +// +// Dry Mass: 7000 kg RD-0411 was 2.5-3 times larger than RD-0410? NERVA II TWR? +// Thrust (SL): ??? kN +// Thrust (Vac): 392.27 kN +// ISP: 444 SL / 925 Vac calculated with RPA +// Burn Time: ??? +// Chamber Pressure: 4.80 MPa +// Chamber Temp: 3000 K same as RD-0410 +// Propellant: LH2 +// Prop Ratio: N/A +// Throttle: 50%? +// Nozzle Ratio: 100 guess +// Ignitions: 60 same as NERVA +// ================================================================================= +// RD-0411 (11B92) +// Speculative Ammonia config +// +// Dry Mass: 7000 kg RD-0411 was 2.5-3 times larger than RD-0410? NERVA II TWR? +// Thrust (SL): ??? kN +// Thrust (Vac): 809.93 kN assuming constant power +// ISP: 214 SL / 448 Vac calculated with RPA +// Burn Time: ??? +// Chamber Pressure: 4.80 MPa +// Chamber Temp: 3000 K same as RD-0410 +// Propellant: LNH3 +// Prop Ratio: N/A +// Throttle: 50%? +// Nozzle Ratio: 100 guess +// Ignitions: 60 same as NERVA +// ================================================================================= +// RD-0411 (11B92) +// Speculative "Methane" version +// Methane/Ammonia mix prevents coking and gets better Isp +// +// Dry Mass: 7000 kg RD-0411 was 2.5-3 times larger than RD-0410? NERVA II TWR? +// Thrust (SL): ??? kN +// Thrust (Vac): 742.02 kN assuming constant power +// ISP: 224 SL / 489 Vac calculated with RPA +// Burn Time: ??? +// Chamber Pressure: 4.80 MPa +// Chamber Temp: 3000 K same as RD-0410 +// Propellant: LNH3/LCH4 +// Prop Ratio: 2.33 NH3/CH4 +// Throttle: 50%? +// Nozzle Ratio: 100 guess +// Ignitions: 60 same as NERVA +// ================================================================================= + +// Sources: + +// [1]http://www.astronautix.com/r/rd-0410.html +// [2]https://www.techinsider.ru/made-in-russia/5983-k-marsu-na-reaktore-vzryvnaya-sila/ +// [3]http://www.cosmoworld.ru/spaceencyclopedia/programs/index.shtml?yard.html +// [4]https://kbkha.ru/deyatel-nost/raketnye-dvigateli-ao-kbha/yadernyj-raketnyj-dvigatel-rd0410-rd0411/ +// [5]https://topwar.ru/156377-jadernyj-raketnyj-dvigatel-rd0410-smelaja-razrabotka-bez-perspektiv.html +// [6]https://ecoruspace.me/%D0%A0%D0%94-0410.html +// [7]http://forums.airbase.ru/2020/09/t8315_21--atomnyj-raketnyj-dvigatel.html + +// Used by: + +// Notes: +// Not much information on this, other than that it was a larger RD-0410. Assume it got better TWR from +// larger size and had a nozzle extension +// ================================================== +@PART[*]:HAS[#engineType[RD0411]]:FOR[RealismOverhaulEngines] +{ + %title = #roRD0411Title //RD-0411 + %manufacturer = #roMfrKBKhA + %description = #roRD0411Desc + + @tags ^= :$: USSR KB Khimavtomatika rd0411 11b92 ro31 nuclear pump upper lqdhydrogen + + %specLevel = prototype + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + @MODULE[ModuleGimbal] + { + %gimbalRange = 3 + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = RD-0411-Hydrogen + modded = false + origMass = 6.967 //7000 kg - 33 kg + + CONFIG + { + name = RD-0411-Hydrogen + specLevel = concept + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 196.14 + maxThrust = 392.27 + massMult = 1 + ignitions = 60 + %ullage = True + %throttleResponseRate = 0.035 //should be around 12 secs to fully ramp up to 100% from 0%. Actual ramp data may not be available. + %throttleStartedMult = 0.8 + %throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdHydrogen + ratio = 1.0 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 925 + key = 1 444 + } + %chamberNominalTemp = 3000 + %maxEngineTemp = 3500 + + //no data, never flew + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 36000 // 10 hours + ratedContinuousBurnTime = 3600 // 1 hour + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + + techTransfer = RD-0410MID-Hydrogen:20 + } + } + CONFIG + { + name = RD-0411-Ammonia + description = Speculative version using Ammonia as propellant. + specLevel = speculative + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 404.97 + maxThrust = 809.93 + massMult = 1 + ignitions = 60 + %ullage = True + %throttleResponseRate = 0.035 //should be around 12 secs to fully ramp up to 100% from 0%. Actual ramp data may not be available. + %throttleStartedMult = 0.8 + %throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdAmmonia + ratio = 1.0 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 448 + key = 1 214 + } + %chamberNominalTemp = 3000 + %maxEngineTemp = 3500 + + //no data, never flew + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 36000 // 10 hours + ratedContinuousBurnTime = 3600 // 1 hour + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + + techTransfer = RD-0410MID-Hydrogen:20 + } + } + CONFIG + { + name = RD-0411-Methane + description = Speculative version using Methane-Ammonia mix as propellant. + specLevel = sciFi //I don't know if RPA actually calculates this mixture dissociation correctly + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 371.01 + maxThrust = 742.02 + massMult = 1 + ignitions = 60 + %ullage = True + %throttleResponseRate = 0.035 //should be around 12 secs to fully ramp up to 100% from 0%. Actual ramp data may not be available. + %throttleStartedMult = 0.8 + %throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdAmmonia + ratio = 0.5858 + } + PROPELLANT + { + name = LqdMethane + ratio = 0.4142 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 448 + key = 1 214 + } + %chamberNominalTemp = 3000 + %maxEngineTemp = 3500 + + //no data, never flew + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 36000 // 10 hours + ratedContinuousBurnTime = 3600 // 1 hour + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + + techTransfer = RD-0410MID-Hydrogen:20 + } + } + } + MODULE + { + name = ModuleResourceConverter + ConverterName = Turbine Generator + StartActionName = Start + StopActionName = Stop + AlwaysActive = true + FillAmount = 1.000 + AutoShutdown = false + GeneratesHeat = false + TemperatureModifier = 2.000 + UseSpecializationBonus = false + DefaultShutoffTemp = 0.500 + + INPUT_RESOURCE + { + ResourceName = EnrichedUranium + Ratio = 3.1e-13 + } + + OUTPUT_RESOURCE + { + ResourceName = ElectricCharge + Ratio = 4.65 //same as NERVA-II? + } + + OUTPUT_RESOURCE + { + ResourceName = DepletedUranium + Ratio = 3.1e-13 + } + } + RESOURCE + { + name = EnrichedUranium + amount = 3.0 //32.9 kg (10 times RD-0410) + maxAmount = 3.0 + } + RESOURCE + { + name = DepletedUranium + amount = 0 + maxAmount = 3.0 + } +} diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/SNTPPFE_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/SNTPPFE_Config.cfg index c983f0fa18..2f7a1dfa95 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/SNTPPFE_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/SNTPPFE_Config.cfg @@ -10,13 +10,13 @@ // Dry Mass: 1504 kg // Thrust (SL): 160 kN // Thrust (Vac): 206 kN -// ISP: 733 SL / 940 Vac +// ISP: 564 SL / 940 Vac // Burn Time: 600 // Chamber Pressure: 6.8 MPa +// Chamber Temp: 3000 K // Propellant: LH2 // Prop Ratio: N/A -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? +// Throttle: 5:1 throttling // Nozzle Ratio: 100 // Ignitions: 5 // ================================================================================= @@ -26,14 +26,47 @@ // Dry Mass: 1504 kg // Thrust (SL): ??? kN // Thrust (Vac): 245 kN //Goal TWR of 25:1 -// ISP: 747 SL / 954 Vac +// ISP: 578 SL / 954 Vac // Burn Time: 1000 // Chamber Pressure: 6.8 MPa +// Chamber Temp: 3000 K // Propellant: LH2 // Prop Ratio: N/A -// Engine Nozzle: ??? -// Nozzle Exit Area: ??? -// Nozzle Ratio: 100 +// Throttle: 5:1 throttling +// Nozzle Ratio: 100? +// Ignitions: 15 +// ================================================================================= +// SNTP Production Ammonia +// Speculative Ammonia version +// +// Dry Mass: 1504 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 503.06 kN assuming constant power +// ISP: 281 SL / 465 Vac +// Burn Time: 1000 +// Chamber Pressure: 6.8 MPa +// Chamber Temp: 3000 K +// Propellant: LNH3 +// Prop Ratio: N/A +// Throttle: 5:1 throttling +// Nozzle Ratio: 100? +// Ignitions: 15 +// ================================================================================= +// SNTP Production Methane +// Speculative "Methane" version +// Methane/Ammonia mix prevents coking and gets better Isp +// +// Dry Mass: 1504 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 245 kN assuming constant power +// ISP: 292 SL / 499 Vac +// Burn Time: 1000 +// Chamber Pressure: 6.8 MPa +// Chamber Temp: 3000 K +// Propellant: LNH3/LCH4 +// Prop Ratio: 4.56 NH3/CH4 +// Throttle: 5:1 throttling +// Nozzle Ratio: 100? // Ignitions: 15 // ================================================================================= @@ -47,12 +80,14 @@ // Notes: -// +// Prototype and production model seem to have the same core temp. High isp in production model is due to +// higher turbine inlet temp requiring less hydrogen bleed, and maybe higher expansion ratio? // ================================================== @PART[*]:HAS[#engineType[SNTPPFE100]]:FOR[RealismOverhaulEngines] { @title = #roSNTPPFE100Title //SNTP-PFE100 Atomic Rocket Motor %manufacturer = #roMfrAerojet + %description = #roSNTPPFE100Desc @tags ^= :$: USA aerojet grumman sntp pfe100 timberwind nuclear pump upper lqdhydrogen @@ -75,7 +110,7 @@ maxThrust = 206 exhaustDamage = True ignitionThreshold = 0.1 - massMult = 1 + massMult = 1 ignitions = 5 %ullage = True %throttleResponseRate = 0.1 //should be around 10 secs too fully ramp up to 100% from 0%. Actual ramp data may not be available. @@ -96,9 +131,9 @@ atmosphereCurve { key = 0 940 - key = 1 733 + key = 1 564 } - %chamberNominalTemp = 2720 + %chamberNominalTemp = 3000 %maxEngineTemp = 3700 TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -128,7 +163,7 @@ CONFIG { name = SNTPPFE100-Hydrogen - description = Production engine predicted performance. Increased core temperature to 3000K and Carbon-Carbon turbopumps to handle higher flow rates and inlet temperatures + description = Production engine predicted performance. Carbon-Carbon turbines handle higher flow rates and inlet temperatures. specLevel = concept minThrust = 49 maxThrust = 245.2 @@ -155,7 +190,134 @@ atmosphereCurve { key = 0 954 - key = 1 747 + key = 1 578 + } + %chamberNominalTemp = 3000 + %maxEngineTemp = 3700 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + //coast for several hours. Needed to cool down between starts + ratedBurnTime = 7200 //fuel pellet erosion acceptable beyond 1 hour + ratedContinuousBurnTime = 1050 // 17.5 minutes + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + //reliabilityDataRateMultiplier = 10 // due to the burn time + techTransfer = SNTPPFE100-Prototype:50 + } + } + CONFIG + { + name = SNTPPFE100-Ammonia + description = Speculative version using Ammonia as propellant. No LOX-Augmentation on account of poor performance. + specLevel = speculative + minThrust = 100.61 + maxThrust = 503.06 + exhaustDamage = True + ignitionThreshold = 0.1 + massMult = 1 + ignitions = 15 + %ullage = True + %throttleResponseRate = 0.2 //should be around 5 secs too fully ramp up to 100% from 0%. Actual ramp data may not be available. + %throttleStartedMult = 0.8 + %throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdAmmonia + ratio = 1.0 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 465 + key = 1 281 + } + %chamberNominalTemp = 3000 + %maxEngineTemp = 3700 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + //coast for several hours. Needed to cool down between starts + ratedBurnTime = 7200 //fuel pellet erosion acceptable beyond 1 hour + ratedContinuousBurnTime = 1050 // 17.5 minutes + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + //reliabilityDataRateMultiplier = 10 // due to the burn time + techTransfer = SNTPPFE100-Prototype:50 + } + } + CONFIG + { + name = SNTPPFE100-Methane + description = Speculative version using Methane-Ammonia mix as propellant. + specLevel = sciFi //I don't know if RPA actually calculates this mixture dissociation correctly + minThrust = 93.76 + maxThrust = 468.78 + exhaustDamage = True + ignitionThreshold = 0.1 + massMult = 1 + ignitions = 15 + %ullage = True + %throttleResponseRate = 0.2 //should be around 5 secs too fully ramp up to 100% from 0%. Actual ramp data may not be available. + %throttleStartedMult = 0.8 + %throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdAmmonia + ratio = 0.7343 + } + PROPELLANT + { + name = LqdMethane + ratio = 0.2657 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 499 + key = 1 292 } %chamberNominalTemp = 3000 %maxEngineTemp = 3700 diff --git a/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/SmallEngine_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/SmallEngine_Config.cfg new file mode 100644 index 0000000000..bfaad03d6f --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/SmallEngine_Config.cfg @@ -0,0 +1,295 @@ +// ================================================== +// Los Alamos "Small Engine" +// +// Manufacturer: Aerojet +// +// ================================================================================= +// Small Engine +// +// Dry Mass: 2500 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 72.95 kN +// ISP: 270 SL / 875 Vac sl calculated with RPA +// Burn Time: 3600 1 hour runtime +// Chamber Pressure: 3.10 MPa +// Chamber Temp: 2633 K +// Propellant: Slush LH2 +// Prop Ratio: N/A +// Throttle: 20% min throttle? +// Nozzle Ratio: 100 +// Ignitions: 60? same as NERVA +// ================================================================================= +// Small Engine - Ammonia +// speculative Ammonia config +// +// Dry Mass: 2500 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 159.73 kN assuming constant thrust power +// ISP: 132 SL / 427 Vac calculated with RPA +// Burn Time: 3600 1 hour runtime +// Chamber Pressure: 3.10 MPa +// Chamber Temp: 2633 K +// Propellant: NH3 +// Prop Ratio: N/A +// Throttle: 20% min throttle? +// Nozzle Ratio: 100 +// Ignitions: 60? same as NERVA +// ================================================================================= +// Small Engine - Methane +// speculative "Methane" config +// Methane/Ammonia mix prevents coking and gets better Isp +// +// Dry Mass: 2500 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 147.63 kN +// ISP: 138 SL / 462 Vac calculated with RPA +// Burn Time: 3600 1 hour runtime +// Chamber Pressure: 3.10 MPa +// Chamber Temp: 2633 K +// Propellant: LNH3/LCH4 +// Prop Ratio: 4.88 NH3/CH4 +// Throttle: 20% min throttle? +// Nozzle Ratio: 100 +// Ignitions: 60? same as NERVA +// ================================================================================= + +// Sources: +// NASA - An Overview of Tested and Analyzed NTP Concepts: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19920001919.pdf +// Los Alamos National Laboratory - Experience Gained from the Space Nuclear Rocket Program (Rover): https://fas.org/nuke/space/la-10062.pdf + +// Used by: +// + +// Notes: +// +// ================================================== +@PART[*]:HAS[#engineType[SmallEngine]]:FOR[RealismOverhaulEngines] +{ + @title = #roSmallEngineTitle //Los Alamos "Small Engine" Atomic Rocket Motor + @manufacturer = #roMfrAerojet + @description = #roSmallEngineDesc + + @tags ^= :$: USA aerojet westinghouse nerva los alamos small engine nuclear pump upper lqdhydrogen + + %specLevel = concept + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = SmallEngine-Hydrogen + modded = false + origMass = 2.478 //2500 kg - 22 kg + + CONFIG + { + name = SmallEngine-Hydrogen + specLevel = concept + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 14.59 + maxThrust = 72.95 + massMult = 1 + + ignitions = 60 + ullage = True + throttleResponseRate = 0.035 //should be around 30 secs too fully ramp up to 100% from 0%. + throttleStartedMult = 0.8 + throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdHydrogen //We don't have Slush LH2 + ratio = 1.0 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 875 + key = 1 270 + } + chamberNominalTemp = 2633 + maxEngineTemp = 3000 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 36000 //10 hours? + ratedContinuousBurnTime = 3600 // 1 hour + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + } + } + CONFIG + { + name = SmallEngine-Ammonia + description = Speculative version using Ammonia as propellant. + specLevel = speculative + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 31.95 + maxThrust = 159.73 + massMult = 1 + + ignitions = 60 + ullage = True + throttleResponseRate = 0.035 //should be around 30 secs too fully ramp up to 100% from 0%. + throttleStartedMult = 0.8 + throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdAmmonia + ratio = 1.0 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 427 + key = 1 132 + } + chamberNominalTemp = 2633 + maxEngineTemp = 3000 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 36000 //10 hours? + ratedContinuousBurnTime = 3600 // 1 hour + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + } + } + CONFIG + { + name = SmallEngine-Methane + description = Speculative version using Methane-Ammonia mix as propellant. + specLevel = sciFi //I don't know if RPA actually calculates this mixture dissociation correctly + exhaustDamage = True + ignitionThreshold = 0.1 + minThrust = 29.53 + maxThrust = 147.63 + massMult = 1 + + ignitions = 60 + ullage = True + throttleResponseRate = 0.035 //should be around 30 secs too fully ramp up to 100% from 0%. + throttleStartedMult = 0.8 + throttleStartupMult = 5.0 + + PROPELLANT + { + name = LqdAmmonia + ratio = 0.7474 + } + PROPELLANT + { + name = LqdMethane + ratio = 0.2526 + DrawGauge = True + } + PROPELLANT + { + name = EnrichedUranium + ratio = 0.00000000001 + } + atmosphereCurve + { + key = 0 462 + key = 1 138 + } + chamberNominalTemp = 2633 + maxEngineTemp = 3000 + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 36000 //10 hours? + ratedContinuousBurnTime = 3600 // 1 hour + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + explicitDataRate = True + ignitionReliabilityStart = 0.99 + ignitionReliabilityEnd = 0.999997 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.999 + cycleReliabilityEnd = 0.999997 + reliabilityMidV = 0.8 + reliabilityMidH = 0.1 + reliabilityMidTangentWeight = 0 + reliabilityDataRateMultiplier = 100 // due to the burn time + } + } + } + + RESOURCE + { + name = EnrichedUranium + amount = 4.74 //52 kg + maxAmount = 4.74 + } + RESOURCE + { + name = DepletedUranium + amount = 0 + maxAmount = 4.74 + } + + @MODULE[ModuleGimbal] + { + %gimbalRange = 3 + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + !MODULE[ModuleAlternator] + { + } + !RESOURCE[ElectricCharge] + { + } +} diff --git a/GameData/RealismOverhaul/Localization/en-us-Engines.cfg b/GameData/RealismOverhaul/Localization/en-us-Engines.cfg index 7975514d01..75c13e5107 100644 --- a/GameData/RealismOverhaul/Localization/en-us-Engines.cfg +++ b/GameData/RealismOverhaul/Localization/en-us-Engines.cfg @@ -273,8 +273,10 @@ Localization #roKestrel_1BDesc = A methalox derivative of the original pressure-fed Kestrel engine used on the upper stage of the Falcon 1 launch vehicle. Features multi-ignition capability and a limited throttling range. // KIWIA24 #roKIWIA24Title = Kiwi A3 Atomic Rocket Motor + #roKIWIA24Desc = The "KIWI A" series is an older 132MW reactor with the lowest power density of all the rover tests. Most tests resulted in failure with shattered fuel elements or faulted test equipment however much was learned and the development of liquid hydrogen pumping is a major accomplishment. Its core is capable of starting up twice. An integral Tungsten shield is included and the whole assembly is regeneratively cooled. A secondary circuit runs the shutdown gasses through a small heat engine to minimize fuel loss and provide basic alternator power. This engine should be mounted two to six meters from the closest fuel tank. Fuel should shield any crew and crew positions when running should be six to nine meters from the engine. Additional shielding such as a water tank or high density fuel can somewhat reduce this amount. All subsequent US nuclear thermal rocket designs build off this concept. This version features a very small fixed regeneratively cooled nozzle with a 24:1 area expansion ratio. Nozzle Ae/A*=24 Chamber Temp=2300 Ideal ISP=874 Reactor Power=132MW(th) TWR=0.24 Chamber Pressure=1415kPa Ignitions =2 Tonnage including integral shadow shield: 12.08tons // KIWIB48 #roKIWIB48Title = Kiwi B4E Atomic Rocket Motor + #roKIWIB48Desc = The "KIWI B" series is an older 1100MW reactor with more than 10 times the power density of the A series. Most tests early resulted in failure with shattered fuel elements or faulted test equipment however much was learned and the development of advanced coatings chemical vapour deposition and heat pipes. The final test B4E ran smoothly and even restarted from a cold condition. The first Kiwi B test was run on gaseous hydrogen since hydrogen pumping and storage was in its infancy. Its core is capable of starting up four times. An integral Tungsten shield is included and the whole assembly is regeneratively cooled. A secondary circuit runs the shut down gasses through a small heat engine to minimize fuel loss and provide basic alternator power. This engine should be mounted three to six meters from the closest fuel tank. Fuel should shield any crew and crew positions when running should be eight to twelve meters from the engine. Additional shielding such as a water tank or high density fuel can somewhat reduce this amount. This rocket represents the basic and conservative solid core rocket design. The NERVA designs build off this concept. This version features a fixed regeneratively cooled nozzle with a 66:1 expansion ratio. Nozzle Ae=66 Chamber Temp=2473 Ideal ISP=864 Reactor Power=1166MW(th) TWR=2.04 Chamber Pressure=3606kPa Ignitions =4 Tonnage including integral shadow shield: 14.89tons // KRD61 #roKRD61Title = KRD-61 #roKRD61Desc = A Soviet gas generator hypergolic vacuum engine designed for the return stage of the E-8-5 lunar sample return probes. With only one ignition, a very precise trajectory is required. @@ -403,6 +405,7 @@ Localization #roNERVAIIDesc = A later 1970s atomic engine with relatively low TWR but high ISP and a power generation of 4200 MW. Derived from the Phoebus 2A ground demonstrator, tested in 1968. // NERVA_NRX #roNERVA_NRXTitle = NERVA NRX + #roNERVA_NRXDesc = The "Nerva NRX" series is a 1200MW reactor. A partial flight test prototype originally based on the KIWI B4E replacing the "Hot End Seal" with peripheral systems. Its core is capable of starting up thirty times. An integral Tungsten Boron composite shield is included and the whole assembly is regeneratively cooled. A secondary circuit runs the shut down gasses through a small heat engine to minimize fuel loss and provide basic alternator power. This engine should be mounted three to six meters from the closest fuel tank. Fuel should shield any crew and crew positions when running should be eight to ten meters from the engine. Additional shielding such as a water tank or high density fuel can somewhat reduce this amount. This rocket represents the beginnings of a more powerful and capable series of rocket. This version features a fixed regeneratively cooled nozzle with a 50:1 expansion ratio. Nozzle Ae=50 Chamber Temp=2550 Ideal ISP=943 Reactor Power=1197MW(th) TWR=2.19 Chamber Pressure=4151kPa Ignitions =30 Tonnage including integral shadow shield: 11.33tons // NERVA_XE #roNERVA_XETitle = Nerva XE-Prime #roNERVA_XEDesc = The "Nerva XE" series is a 1550 MW reactor. A full flight test prototype originally based on the KIWI B4E. Its core is capable of starting up sixty times. An integral Tungsten Boron composite shield is included and the whole assembly is regeneratively cooled. A secondary circuit runs the shut down gasses through a small heat engine to minimize fuel loss and provide basic alternator power. This engine should be mounted three to six meters from the closest fuel tank. Fuel should shield any crew and crew positions when running should be eight to ten meters from the engine. Additional shielding such as a water tank or high density fuel can somewhat reduce this amount. This rocket represents the beginnings of a more powerful and capable series of rocket. This version features a fixed regeneratively cooled nozzle with a 100:1 expansion ratio. Nozzle Ae=100 Chamber Temp=2500 Ideal ISP=945 Reactor Power=1163MW(th) TWR=2.34 Chamber Pressure=3806kPa Ignitions =60 Tonnage including integral shadow shield: 10.38tons @@ -440,10 +443,13 @@ Localization #roP5Desc = Developed jointly by the AFRL and PEPL, the P5 is a dual-stage Hall thruster. This means it can more effectively lens the charged ions, giving you increased thrust above single-stage operation at the expense of efficiency. // PEWEE100 #roPEWEE100Title = Peewee 100 Atomic Rocket Motor + #roPEWEE100Desc = The "PEWEE" series is a smaller 572MW reactor with the highest power density of all the rover tests. It also recorded the Highest ISP ratings of the test at 901s. Its core is capable of starting up to 12 times. An integral Tungsten Boron Composite shield is included and the whole assembly is regeneratively cooled. A secondary circuit runs the shutdown gasses through a small heat engine to minimize fuel loss and provide basic alternator power. This engine should be mounted three to six meters from the closest fuel tank. Fuel should shield any crew and crew positions when running should be nine to twelve meters from the engine. Additional shielding such as a water tank or high density fuel can somewhat reduce this amount. Most modern NASA study reactors such as the BNTR are derived in turn from this test reactor. This version features a fixed regeneratively cooled nozzle. Nozzle Ae=100 Chamber Temp=2750 Ideal ISP=998 Reactor Power=572MW(th) TWR=5.07 Chamber Pressure=4344kPa Ignitions =12 Tonnage including integral shadow shield: 2.23tons // Phoebus1N50 #roPhoebus1N50Title = Phoebus 1B Atomic Rocket Motor + #roPhoebus1N50Desc = The "Phoebus 1" series is a 1500MW reactor. Most tests early resulted in failure from pumping or faulted test equipment however much was learned and the development of advanced coatings chemical vapour deposition and lighter materials. Its core is capable of starting up four times. An integral Tungsten Boron composite shield is included and the whole assembly is regeneratively cooled. A secondary circuit runs the shut down gasses through a small heat engine to minimize fuel loss and provide basic alternator power. This engine should be mounted three to six meters from the closest fuel tank. Fuel should shield any crew and crew positions when running should be eight to twelve meters from the engine. Additional shielding such as a water tank or high density fuel can somewhat reduce this amount. This rocket represents the beginnings of a more powerful and capable series of rocket. This version features a fixed regeneratively cooled nozzle with a 50:1 expansion ratio. Nozzle Ae=50 Chamber Temp=2445 Ideal ISP=881 Reactor Power=1500MW(th) TWR=3.33 Chamber Pressure=3772kPa Ignitions =4 Tonnage including integral shadow shield: 9.14tons // Phoebus2N100 #roPhoebus2N100Title = Phoebus 2A Atomic Rocket Motor + #roPhoebus2N100Desc = The "Phoebus 2" series is a 5000MW reactor. Most tests resulted in success proving new coatings worked well and existing at the time as the most powerful reactor core on the planet. Its core is capable of starting up eight times. An integral Tungsten Boron composite shield is included and the whole assembly is regeneratively cooled. A secondary circuit runs the shut down gasses through a small heat engine to minimize fuel loss and provide basic alternator power. This engine should be mounted three to six meters from the closest fuel tank. Fuel should shield any crew and crew positions when running should be ten to fifteen meters from the engine. Additional shielding such as a water tank or high density fuel can somewhat reduce this amount. This rocket represents a more powerful and capable series of rocket with a TWR of nearly 6. This version features a fixed regeneratively cooled nozzle with a 100:1 expansion ratio. Nozzle Ae=100 Chamber Temp=2245 Ideal ISP=889 Reactor Power=4182MW(th) TWR=5.48 Chamber Pressure=3825kPa Ignitions =8 Tonnage including integral shadow shield: 16.97tons // PITV #roPITVTitle = PIT Mk Va Pulsed Inductive Thruster #roPITVDesc = The pulsed inductive thruster uses a powerful magnetic pulse to ionize and accelerate gas. It can achieve impressive ISPs, and be scaled up simply by increasing the pulse rate. However, it consumes a considerable amount of power. The Mk V PIT was tested by TRW in 1993 with a variety of voltages, pulse sizes, and propellants. @@ -625,6 +631,10 @@ Localization #roRD301Desc = An exotic fuel-rich staged combustion vacuum engine. Developed as a high-energy upper stage for Proton by Glushko, the RD-301 burned liquid fluorine and ammonia, which gave very high performance and density. It was tested extensively, but never flew due to toxicity concerns. // RD0410MID #roRD0410MIDTitle = RD-0410 + #roRD0410MIDDesc = RD-0410 was a Soviet nuclear thermal rocket engine developed from 1965 through the 1994 using liquid hydrogen propellant. The engine was ground-tested at the Semipalatinsk Test Site, and its use was incorporated in the Kurchatov Mars 1994 manned mission proposal. Its moderator and fuel are quite different from the US designs and Metal Carbide (MC) versions of the fuel are rumoured to have reach as high as 3500K without melting in the early 1990's. Use of Heptane to reduce hydrogen corrosion of the carbides was critical to function (~1%). First run tests occurred in 1985. Some Russian sources list it as dual mode using not only Hydrogen but also liquid Methane without additives. During the SNTP program the US tried to acquire MC fuels from Russian sources but planned purchases fell through. This engine is very heavily built compared to US designs and incorporates a four lobed spiral fuel rod to eliminate risk of fuel being ejected if the rods shattered. This design uses a short regeneratively cooled nozzle and is intended as an upper stage. Design stats Nozzle Ae=46 Chamber Temp=3000 Ideal ISP=972 Reactor Power=173MW(th) TWR=1.73 Chamber Pressure=4000kPa Ignitions =10 Tonnage including integral shadow shield:2tons. In Methane mode the nozzle is slightly expanded by 12cm length and slightly enlarged. Nozzle Ae=46 Chamber Temp=3000 Ideal ISP=467 Reactor Power=173MW(th) TWR=3.56 Chamber Pressure=4800kPa Ignitions =10 Tonnage including integral shadow shield:2tons + // RD0411 + #roRD0411Title = RD-0411 + #roRD0411Desc = A Soviet nuclear thermal rocket engine. Developed in parallel with the RD-0410, the RD-0411 was a much larger engine, intended for upper stage use on the UR-700 or N-I. Using the same advanced Metal Carbide (MC) fuels and spiral fuel rods as the RD-0410, it achieves good performance for it's size. Unlike the RD-0410, no test articles were ever built, as the failure of the N-1 and cancellation of the UR-700 meant there would be no launch vehicle large enough to use it. It never progressed past the study stage, and much of it's performance is speculative. // RD510 #roRD510Title = RD-510 #roRD510Desc = A staged combustion kerosene and peroxide lander engine, developed for Soviet heavy manned moon landers. Derived from the earlier RD-502 project, the use of hydrogen peroxide with kerosene allowed for a very dense, storable, and non-toxic stage. Although tested extensively, and proposed for various lunar lander designs including the LK-700, it never flew. @@ -725,8 +735,12 @@ Localization // SIIUllageMotor #roSIIUllageMotorTitle = S-II Ullage Motor #roSIIUllageMotorDesc = The ullage motor of the Saturn V S-II stage. Attaches to the upper part of the S-II interstage in sets of 4 to 8. + // SmallEngine + #roSmallEngineTitle = Los Alamos "Small Engine" Atomic Rocket Motor + #roSmallEngineDesc = The Los Alamos "Small Engine" was a compact nuclear thermal rocket derived from the PEWEE core. Designed to be used as a Space Shuttle upper stage, it has a unique folding nozzle to reduce length. // SNTPPFE100 #roSNTPPFE100Title = SNTP-PFE100 Atomic Rocket Motor + #roSNTPPFE100Desc = The "SNTP-PFE" series is a 1000MW reactor. The reactor is a particle bed using metallic carbide coated uranium granules embedded in a graphite rod that hydrogen is passed through. This allows for power densities of up to 40MW/liter. Its core is capable of starting up five times. An integral Tungsten Boron Lithium Hydride composite shield is included and the whole assembly is regeneratively cooled. A secondary circuit runs the shut down gasses through a small heat engine to minimize fuel loss and provide basic alternator power. This engine should be mounted three to six meters from the closest fuel tank. Fuel should shield any crew and crew positions when running should be ten to fifteen meters from the engine. Additional shielding such as a water tank or high density fuel can somewhat reduce this amount. This rocket has impressive stats for its size (Nozzle Ae=100 Chamber Temp=3000 Ideal ISP=991 Reactor Power=1054MW(th) TWR=13.94 Chamber Pressure=6800kPa Ignitions =5 Tonnage including integral shadow shield:1.504tons ) The nozzle is a fixed ablatively cooled filament wound carbon-carbon design. // SPT-50 #roSPT50Title = SPT-50 Hall Effect Thruster #roSPT50Desc = An early Soviet Hall Effect thruster, used on Soviet and Russian weather satellites.