LR79_Config.cfg

//	=================================================================================
//	LR79 series
//
//	Manufacturer: Rocketdyne
//
//	=================================================================================
//	S-3
//	Early version of the S-3D that was in development for the Thor launch vehicle.
//
//	Dry Mass: 945.3 kg (Source #4)
//	Thrust (SL): 135,000 lbf (all sources) = 600.51
//	Vacuum Thrust Estimate based on (600.51 / 667.23 S-3D known value) = 90% of total
//	Thrust (vac): Calculated by (766.34 S-3D value * 90%) = 696.6 kN
//	ISP: 247.62 SL (all sources) / 288 vac
//	Burn Time: 182 (burn time for Jupiter)
//	Chamber Pressure: 3.61? MPa
//	Propellant: LOX / RP1
//	Prop Ratio: 2.4
//	Throttle: N/A
//	Nozzle Ratio: 8
//	Ignitions: 1
//	=================================================================================
//	S-3D (LR79-NA-1?)
//
//	Dry Mass: 945.3 kg (Source #4)
//	Thrust (SL): 150,000 lbf (all sources) = 667.233 kN
//	Thrust (vac): Source #2: 773.99, Source #3: 758.7 = Average 766.345 kN
//	ISP: 247.62 SL (all sources) / 288 vac
//	Burn Time: 182 (burn time for Jupiter)
//	Flow Rate: 275.126 kg/s
//	Chamber Pressure: 3.61 MPa
//	Propellant: LOX / RP1
//	Ratio: 2.4
//	Throttle: N/A
//	Nozzle Ratio: 8
//	Ignitions: 1
//	=================================================================================
//	LR79-NA-9
//	Thor MB-3 Block I
//	Data from Source #5
//
//	Dry Mass: 933.66? kg		interpolated between S-3D and LR79-NA-13
//	Thrust (SL): 150,000 lbf = 667.233 kN
//	Thrust (Vac): 176,000 lbf = 782.886 kN
//	ISP: 245 SL / 284 vac
//	Burn Time: 165
//	Chamber Pressure: 3.65 MPa
//	Propellant: LOX / RP1
//	Ratio: ???
//	Throttle: N/A
//	Engine Nozzle: 1.16 m diameter
//	Nozzle Exit Area: 1640 in^2 = 41.656 m^2
//	Nozzle Ratio: 8
//	Ignitions: 1
//	=================================================================================
//	LR79-NA-11
//	Thor MB-3 Block II
//	Data from Source #5
//
//	Dry Mass: 923.56? kg		interpolated between S-3D and LR79-NA-13
//	Thrust (SL): 165,453 lbf = 735.9713437 kN
//	Thrust (Vac): 190,998 lbf = 849.6011236 kN
//	ISP: 248.3 SL / 286.2 vac
//	Burn Time: 165
//	Chamber Pressure: 3.69 MPa
//	Propellant: LOX / RP1
//	Ratio: 2.156 (2.15 including verniers)
//	Throttle: N/A
//	Engine Nozzle: 1.16 m diameter
//	Nozzle Exit Area: 1640 in^2 = 41.656 m^2
//	Nozzle Ratio: 8
//	Ignitions: 1
//	=================================================================================
//	S-3FH
//	Converted to run on UDMH for Juno IV
//	Juno IV called for 165klbf engine ready by 1961. LR79-NA-11 fits this description, so use it as basis.
//	If LR79-NA-9 is S-3E, LR79-NA-11 is S-3F?
//	Lower performance than orignal Hydrazine proposal, but much easier to build due to the properties of 
//	UDMH being much closer to Kerosene.
//
//	Dry Mass: 923.56? kg		same as LR79-NA-11
//	Thrust (SL): 165,453 lbf = 735.9713437 kN
//	Thrust (Vac): 190,998 lbf = 849.6011236 kN
//	ISP: 266.1 SL / 305.5 vac		Calculated with RPA, using estimate with straight hydrazine as correction factor
//	Burn Time: 182 (burn time for Jupiter)
//	Chamber Pressure: 3.69 MPa
//	Propellant: LOX / UDMH
//	Ratio: 1.5		Roughly same fuel and oxidizer load as normal Jupiter
//	Throttle: N/A
//	Nozzle Ratio: 8
//	Ignitions: 1
//	=================================================================================
//	LR79-NA-13
//	Thor MB-3 Block III
//	Data from Source #6
//
//	Dry Mass: 2011 lb = 912.17 kg (Source #7)
//	Thrust (SL): 170,000 lbf = 765.056 kN (Source #6/#7) +/- 3%
//	Thrust (Vac): 196,247 lbf = 872.94983 kN (Source #6)
//	ISP: 252.4 (#7) SL / 290.93 vac
//	Burn Time: 165
//	Chamber Pressure: 3.79 MPa
//	Propellant: LOX / RP1
//	Ratio: 2.156 (2.15 including verniers) +/- 1.02%
//	Throttle: N/A
//	Engine Nozzle: 1.16 m diameter
//	Nozzle Exit Area: 1640 in^2 = 41.656 m^2
//	Nozzle Ratio: 8
//	Ignitions: 1
//	=================================================================================
//
//	SOURCES
//	#1: Juno II Summary Report Volume II: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19630002376.pdf
//	#2: Alternate Wars: http://www.alternatewars.com/BBOW/Space_Engines/Rocketdyne_Engines.htm
//	#3: Norbert Bruuge: http://www.b14643.de/Spacerockets/Specials/U.S._Rocket_engines/engines.htm
//	#4: Smithsonian Museum: https://airandspace.si.edu/collection-objects/rocket-engine-liquid-fuel-s-3d-jupiter-missile
//	#5: NASA Launch Vehicle Handbook (1961): https://forum.nasaspaceflight.com/index.php?action=dlattach;topic=11323.0;attach=276498;sess=0
//	#6: NASA SP-4012 NASA Historical Data Book Volume II - Programs and Projects 1958-1968.PDF
//	#7: Design Information Report for the LV-2A Propulsion System (LR-79-NA-13 & LR-101-NA-11) - Rocketdyne (1963): http://www.alternatewars.com/BBOW/Space_Engines/YLR-79-NA-13_Specs.pdf
//
//	Used by:
//		FASA
//		Squad
//		BDB
//
//	FIXME: Did LR79 had the same gimbal range as the H-1 (8 degrees)?
//	=================================================================================

@PART[*]:HAS[#engineType[LR79]]:FOR[RealismOverhaulEngines]
{
	%title = #roLR79Title	//LR79
	%manufacturer = #roMfrRocketdyne
	%description = #roLR79Desc	//A long-lasting US kerolox gas-generator booster engine. The same components and broadly the same performance as the LR89, the LR79 (also known as S-3D in Jupiter / Juno II) powered the Jupiter, Thor, and Thor-Delta (Delta) rockets.

	@tags ^= :$: USA rocketdyne s-3 lr79 mb liquid pump booster kerosene lqdoxygen

	%specLevel = operational

	@MODULE[ModuleEngines*]
	{
		%EngineType = LiquidFuel
	}

	!MODULE[ModuleEngineConfigs],*{}
	!MODULE[ModuleAlternator],*{}
	!RESOURCE,*{}

	@MODULE[ModuleGimbal],*
	{
		%gimbalRange = 8
		%useGimbalResponseSpeed = True
		%gimbalResponseSpeed = 16
	}

	MODULE
	{
		name = ModuleEngineConfigs
		type = ModuleEngines
		configuration = S-3
		origMass = 0.945	// See above for reference information on the S-3D weight
		literalZeroIgnitions = True

		CONFIG
		{
			name = S-3
			description = Main R&D engine for the early Thor DM-18 variant
			specLevel = operational
			// See calculation above. Previous reference from Ed Kyle was correct, but was SL thrust only
			minThrust = 696.6
			// OLD REFERENCE-NO LONGER USED: https://forum.nasaspaceflight.com/index.php?PHPSESSID=br6ak5uvm7sfiqsbqv53ej40g4&topic=40733.0
			maxThrust = 696.6
			heatProduction = 100
			massMult = 1.0
			
			ullage = True
			pressureFed = False
			ignitions = 0

			IGNITOR_RESOURCE
			{
				name = ElectricCharge
				amount = 0.5
			}

			IGNITOR_RESOURCE
			{
				name = TEATEB
				amount = 1
			}

			PROPELLANT
			{
				name = RP-1
				ratio = 0.3707
				DrawGauge = True
			}

			PROPELLANT
			{
				name = LqdOxygen
				ratio = 0.6293
			}

			atmosphereCurve
			{
				key = 0 288
				key = 1 248
			}

			//give all navaho derivatives 350 seconds max safe burn time, based on LR105
			//Jupiter R&D: 30 flights, 5 failures
			//30 engines, 5 failed
			TESTFLIGHT:NEEDS[TestLite|TestFlight]
			{
				testedBurnTime = 350
				ratedBurnTime = 182
				safeOverburn = true
				ignitionReliabilityStart = 0.765054
				ignitionReliabilityEnd = 0.962903
				cycleReliabilityStart = 0.765054
				cycleReliabilityEnd = 0.962903
				techTransfer = A-7,A-6H,A-6,XLR43-NA-1:20&XLR43-NA-3:50	//Direct derivative of LR43
			}
		}
		
		CONFIG
		{
			name = S-3D
			description = Main engine for the Jupiter / Juno II launch vehicle
			specLevel = operational
			minThrust = 766.34
			maxThrust = 766.34
			heatProduction = 100
			massMult = 1.0

			ullage = True
			pressureFed = False
			ignitions = 0

			IGNITOR_RESOURCE
			{
				name = ElectricCharge
				amount = 0.5
			}

			IGNITOR_RESOURCE
			{
				name = TEATEB
				amount = 1
			}

			PROPELLANT
			{
				name = RP-1
				ratio = 0.3707
				DrawGauge = True
			}

			PROPELLANT
			{
				name = LqdOxygen
				ratio = 0.6293
			}

			atmosphereCurve
			{
				key = 0 288
				key = 1 248
			}

			//Jupiter: 7 flights, 0 failures
			//Juno-2: 10 flights, 2 failures (not counting guidance failures)
			//17 engines, 2 failed
			TESTFLIGHT:NEEDS[TestLite|TestFlight]
			{
				testedBurnTime = 350
				ratedBurnTime = 182
				safeOverburn = true
				ignitionReliabilityStart = 0.806481
				ignitionReliabilityEnd = 0.969444
				cycleReliabilityStart = 0.806481
				cycleReliabilityEnd = 0.969444
				techTransfer = A-7,A-6H,A-6,XLR43-NA-1:20&S-3,XLR43-NA-3:50
			}
		}

		CONFIG
		{
			name = LR79-NA-9
			description = Main engine for MB-3-I propulsion system
			specLevel = operational
			minThrust = 783
			// SAME REFERENCE, BUT WHOEVER DID THE MATH DID IT WRONG
			// 176,000 lbf * 0.00444822 = 782.88672 kN
			// 1961 NASA Launch Vehicle Handbook.  See RO/Github #804 for details
			maxThrust = 783
			heatProduction = 100
			// Linear steps from S-3 to LR79-NA-9 to LR79-NA-11 to LR79-NA-13
			// Only known two masses are S-3 and LR79-NA-13
			massMult = 0.988

			ullage = True
			pressureFed = False
			ignitions = 0

			IGNITOR_RESOURCE
			{
				name = ElectricCharge
				amount = 0.5
			}

			IGNITOR_RESOURCE
			{
				name = TEATEB
				amount = 1
			}

			PROPELLANT
			{
				name = RP-1
				ratio = 0.3707
				DrawGauge = True
			}

			PROPELLANT
			{
				name = LqdOxygen
				ratio = 0.6293
			}

			atmosphereCurve
			{
				// Source #5 - NASA Launch Vehicle Handbook (1961)
				key = 0 284	// See RO/Github #804 for details
				key = 1 245
			}

			//Thor DM-18: 17 flights, 11 failures
			//Thor DM-18A: 50 flights, 6 failures
			//Thor DSV2D: 2 flights, 0 failures
			//Thor DSV2E: 8 flights, 4 failures
			//Thor DSV2F: 3 flights, 0 failures
			//Thor DSV2J: 18 flights, 1 failure
			//Thor-LV2D Burner-1: 2 flights, 0 failures
			//Thor-LV2D Burner-1 (2): 4 flights, 0 failures
			//Thor-LV2F Burner-2: 11 flights, 0 failures
			//Thor-LV2F Burner-2 Star-13A: 1 flight, 0 failures
			//Thor-LV2F Burner-2A: 8 flights, 1 failure
			//Thor-LV2F Star-37XE: 5 flights, 0 failures
			//Thor-DM18 Agena-A: 16 flights, 4 failures
			//Thor-DM-18 Able: 3 flights, 1 failure
			//Thor-DM-18 Able-1: 3 flights, 1 failure
			//Thor-DM-18 Able-2: 6 flights, 1 failure
			//Thor-DM-18 Able-2 (mod): 2 flights, 0 failures
			//Thor-DM-18 Able-3: 1 flight, 0 failures
			//Thor-DM-18 Able-4: 1 flight, 0 failures
			//Delta: 12 flights, 0 failures
			//Thor-LV2C Delta: 3 flights, 0 failures
			//176 engines, 37 failed
			//Adjusting end reliability upwards, early Thors were launched with known engine issues
			TESTFLIGHT:NEEDS[TestLite|TestFlight]
			{
				testedBurnTime = 350
				ratedBurnTime = 165
				safeOverburn = true
				ignitionReliabilityStart = 0.750000
				ignitionReliabilityEnd = 0.975
				cycleReliabilityStart = 0.750000
				cycleReliabilityEnd = 0.975
				techTransfer = A-7,A-6H,A-6,XLR43-NA-1:20&S-3D,S-3,XLR43-NA-3:50
			}
		}

		CONFIG
		{
			name = LR79-NA-11
			description = Main engine for MB-3-II propulsion system
			specLevel = operational
			minThrust = 850	// 1961 NASA Launch Vehicle Handbook.  See RO/Github #804 for details
			maxThrust = 850	// 1961 NASA Launch Vehicle Handbook.  See RO/Github #804 for details
			heatProduction = 100
			// Linear steps from S-3 to LR79-NA-9 to LR79-NA-11 to LR79-NA-13
			// Only known two masses are S-3 and LR79-NA-13
			massMult = 0.977  

			ullage = True
			pressureFed = False
			ignitions = 0

			IGNITOR_RESOURCE
			{
				name = ElectricCharge
				amount = 0.5
			}

			IGNITOR_RESOURCE
			{
				name = TEATEB
				amount = 1
			}

			PROPELLANT
			{
				name = RP-1
				ratio = 0.3967
				DrawGauge = True
			}

			PROPELLANT
			{
				name = LqdOxygen
				ratio = 0.6033
			}

			atmosphereCurve
			{
				// Source #5 - NASA Launch Vehicle Handbook (1961)
				key = 0 286.2	// See RO/Github #804 for details
				key = 1 248.3
			}

			//Thor-DM18C: 3 flights, 0 failures
			//Thor-DM21 Agena-B: 43 flights, 2 failures
			//Thor-DM21 Agena-D: 21 flights, 3 failures
			//Thor-DM21 Able-Star: 11 flights, 2 failures
			//Thor-DSV2A Able-Star: 8 flights, 0 failures
			//Delta-A: 2 flights, 0 failures
			//Delta-B: 9 flights, 0 failures
			//Delta-C: 11 flights, 0 failures
			//Delta-C1: 2 flights, 0 failures
			//110 engines, 7 failures
			TESTFLIGHT:NEEDS[TestLite|TestFlight]
			{
				testedBurnTime = 350
				ratedBurnTime = 165
				safeOverburn = true
				ignitionReliabilityStart = 0.911562
				ignitionReliabilityEnd = 0.986036
				cycleReliabilityStart = 0.911562
				cycleReliabilityEnd = 0.986036
				techTransfer = A-7,A-6H,A-6,XLR43-NA-1:20&LR79-NA-9,S-3D,S-3,XLR43-NA-3:50
			}
		}

		CONFIG
		{
			name = S-3FH
			description = Main engine proposal for the Juno IV launch vehicle.
			specLevel = concept
			minThrust = 850
			maxThrust = 850
			heatProduction = 100
			// Linear steps from S-3 to LR79-NA-9 to LR79-NA-11 to LR79-NA-13
			// Only known two masses are S-3 and LR79-NA-13
			massMult = 0.977

			ullage = True
			pressureFed = False
			ignitions = 0

			IGNITOR_RESOURCE
			{
				name = ElectricCharge
				amount = 0.5
			}

			IGNITOR_RESOURCE
			{
				name = TEATEB
				amount = 1
			}

			PROPELLANT
			{
				name = UDMH
				ratio = 0.4902
				DrawGauge = True
			}

			PROPELLANT
			{
				name = LqdOxygen
				ratio = 0.5098
			}

			atmosphereCurve
			{
				key = 0 305.5
				key = 1 266.1
			}

			//Using LR79-NA-11 data, assuming improvements from Thor would be applied to Jupiter if Juno
			//program was continued
			TESTFLIGHT:NEEDS[TestLite|TestFlight]
			{
				testedBurnTime = 350
				ratedBurnTime = 182
				safeOverburn = true
				ignitionReliabilityStart = 0.911562
				ignitionReliabilityEnd = 0.986036
				cycleReliabilityStart = 0.911562
				cycleReliabilityEnd = 0.986036
				techTransfer = A-7,A-6H,A-6,XLR43-NA-1:20&LR79-NA-11,LR79-NA-9,S-3D,S-3,XLR43-NA-3:50
			}
		}

		CONFIG
		{
			name = LR79-NA-13
			description = Main engine for MB-3-III propulsion system
			specLevel = operational
			minThrust = 873	// Source #6
			maxThrust = 873	// Source #6
			heatProduction = 100
			massMult = 0.965 // Source #7

			ullage = True
			pressureFed = False
			ignitions = 0

			IGNITOR_RESOURCE
			{
				name = ElectricCharge
				amount = 0.5
			}

			IGNITOR_RESOURCE
			{
				name = TEATEB
				amount = 1
			}

			PROPELLANT
			{
				name = RP-1
				ratio = 0.3967
				DrawGauge = True
			}

			PROPELLANT
			{
				name = LqdOxygen
				ratio = 0.6033
			}

			atmosphereCurve
			{
				// Source #6: NASA SP-4012 NASA Historical Data Book Volume II - Programs and Projects 1958-1968
				key = 0 290.93
				key = 1 252.4
			}

			//Thor-SLV2A Agena-B: 2 flights, 0 failures
			//Thor-SLV2A Agena-D: 61 flights, 4 failures
			//Thorad-SLV2G Agena-D: 30 flights, 1 failure
			//Thorad-SLV2H Agena-D: 13 flights, 1 failure
			//Delta-D: 2 flights, 0 failures
			//Delta-E: 6 flights, 0 failures
			//Delta-E1: 17 flights, 0 failures
			//Delta-G: 2 flights, 0 failures
			//Delta-J: 1 flight, 0 failures
			//Delta-L: 2 flights, 1 failure
			//Delta-M: 12 flights, 0 failures
			//Delta-M6: 1 flight, 0 failures
			//Delta-N: 6 flights, 0 failures
			//Delta-N6: 3 flights, 0 failures
			//Delta-300: 3 flights, 1 failure
			//Delta-900: 3 flights, 0 failures
			//Delta-1410: 1 flight, 0 failures
			//Delta-1604: 2 flights, 0 failures
			//Delta-1900: 1 flight, 0 failures
			//Delta-1910: 1 flight, 0 failures
			//Delta-1913: 1 flight, 0 failures
			//Delta-1914: 2 flights, 0 failures
			//Delta-4925: 2 flights, 0 failures
			//N-1: 7 flights, 0 failures
			//N-2: 1 flight, 0 failures
			//N-2 Star-37E: 7 flights, 0 failures
			//H-1 (9 SO): 3 flights, 0 failures
			//H-1 UM-129A (6 SO): 1 flight, 0 failures
			//H-1 UM-129A (9 SO): 5 flights, 0 failures
			//198 engines, 7 failed
			TESTFLIGHT:NEEDS[TestLite|TestFlight]
			{
				testedBurnTime = 350
				ratedBurnTime = 260
				safeOverburn = true
				ignitionReliabilityStart = 0.950670
				ignitionReliabilityEnd = 0.992211
				cycleReliabilityStart = 0.950670
				cycleReliabilityEnd = 0.992211
				techTransfer = A-7,A-6H,A-6,XLR43-NA-1:20&LR79-NA-11,LR79-NA-9,S-3D,S-3,XLR43-NA-3:50
			}
		}
	}

	RESOURCE
	{
		name = TEATEB
		amount = 1
		maxAmount = 1
	}
}