NTR overhaul (#2888)

Improve NTR configs, revising calculated performance, and adding alternative propellant configs. Also add configs for RD-0411 and Small Engine
KSP-RO · Aug 6, 2023 · 6a9a88e · 6a9a88e
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diff --git 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