More SRM configs and cleanup (#2963)

KSP-RO · May 9, 2024 · 22cd866 · 22cd866
1 parent 2b262bc
commit 22cd866
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Showing 15 changed files with 1,839 additions and 25 deletions.
diff --git a/...verhaul/Engine_Configs/Alcyone_Config.cfg → ...rhaul/Engine_Configs/Alcyone1A_Config.cfg b/...verhaul/Engine_Configs/Alcyone_Config.cfg → ...rhaul/Engine_Configs/Alcyone1A_Config.cfg
@@ -20,11 +20,11 @@
 //
 //	===============================================================
 
-@PART[*]:HAS[#engineType[Alcyone]]:FOR[RealismOverhaulEngines]
+@PART[*]:HAS[#engineType[Alcyone1A]]:FOR[RealismOverhaulEngines]
 {
-	@title = #roAlcyoneTitle	//Alcyone 1A BE-3A
+	@title = #roAlcyone1ATitle	//Alcyone 1A BE-3A
 	@manufacturer = #roMfrHercules
-	@description = #roAlcyoneDesc	//A very small solid kick motor developed for use as the 5th stage on the Scout launch vehicles. It was only ever launched once, on the Scout E-1 used for Explorer 52. Maximum thrust 27.5kN, burn time 9 seconds.
+	@description = #roAlcyone1ADesc
 
 	@tags ^= :$: USA hercules alcyone 1a be-3a solid upper pban
 
@@ -61,13 +61,13 @@
 	{
 		name = ModuleEngineConfigs
 		type = ModuleEngines
-		configuration = Alcyone
+		configuration = Alcyone-1A
 		modded = false
 
 		origMass = 0.0111
 		CONFIG
 		{
-			name = Alcyone
+			name = Alcyone-1A
 			specLevel = operational
 			minThrust = 27.491
 			maxThrust = 27.491
@@ -84,8 +84,6 @@
 				key = 1 200
 			}
 			// guesses (note: max is above nominal * thrust_curve_max)
-			%chamberNominalTemp	 = 1400
-			%maxEngineTemp = 1520
 			curveResource = PBAN
 			thrustCurve
 			{
@@ -105,8 +103,8 @@
 				ignitionReliabilityEnd = 0.994828
 				cycleReliabilityStart = 0.974138
 				cycleReliabilityEnd = 0.994828
-
 				reliabilityDataRateMultiplier = 2
+				techTransfer = Alcyone-1:50
 
 				isSolid = True
 			}

diff --git a/GameData/RealismOverhaul/Engine_Configs/Alcyone1_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Alcyone1_Config.cfg
@@ -0,0 +1,128 @@
+//	==================================================
+//	BE-3 (Alcyone 1)
+//
+//	Manufacturer: Hercules
+//
+//	=================================================================================
+//	BE-3
+//	Ranger Soft Lander (1962), Sparta, Athena
+//
+//	Dry Mass: 9.22 kg	10.88 kg - 1.66 kg inert mass lost
+//	Thrust (SL): ??? kN
+//	Thrust (Vac): 26.69 kN		6000 lbf max thrust
+//	ISP: 150? SL / 270.4 Vac	average Isp including inert mass. 275.4 seconds propellant only
+//	Burn Time: 12
+//	Chamber Pressure: 3.38 MPa
+//	Propellant: NGNC	//aluminized NGNC
+//	Prop Ratio: N/A
+//	Throttle: N/A
+//	Nozzle Ratio: 19.1
+//	Ignitions: 1
+//	=================================================================================
+
+//	Sources:
+
+//	https://apps.dtic.mil/sti/citations/AD0328876
+
+//	Used by:
+
+//	Notes:
+
+//	190 lbs (86.18 kg) propellant plus 3.67 lbs inert mass lost (1.66 kg) for 87.8472 kg average mass lost
+//	==================================================
+@PART[*]:HAS[#engineType[Alcyone1]]:FOR[RealismOverhaulEngines]
+{
+	@title = #roAlcyone1Title	//Alcyone 1 BE-3
+	@manufacturer = #roMfrHercules
+	@description = #roAlcyone1Desc
+
+	@tags ^= :$: USA hercules alcyone 1 be-3 solid upper ngnc
+
+	%specLevel = operational
+
+	!MODULE[ModuleGimbal] {}
+	!MODULE[ModuleFuelTanks],* {}
+	!MODULE[ModuleAlternator],*{}
+	!RESOURCE,*{}
+
+	@MODULE[ModuleEngines*]
+	{
+		%EngineType = SolidBooster
+		%allowShutdown = False
+		%throttleLocked = True
+	}
+
+	MODULE
+	{
+		name = ModuleFuelTanks
+		type = NGNC
+		volume = 54.9045
+		basemass = -1
+
+		TANK
+		{
+			name = NGNC
+			amount = 54.9045
+			maxAmount = 54.9045
+		}
+	}
+
+	MODULE
+	{
+		name = ModuleEngineConfigs
+		type = ModuleEngines
+		configuration = Alcyone-1
+		modded = false
+
+		origMass = 0.00922
+		CONFIG
+		{
+			name = Alcyone-1
+			specLevel = operational
+			minThrust = 26.69
+			maxThrust = 26.69
+			heatProduction = 100
+			varyIsp = 0.0011	// 0.11%
+			residualsThresholdBase = 0.02	// 2%
+			PROPELLANT
+			{
+				name = NGNC
+				ratio = 1
+				DrawGauge = True
+			}
+			atmosphereCurve
+			{
+				key = 0 270.4
+				key = 1 150
+			}
+			// guesses (eyeballed from test cell graph)
+			curveResource = NGNC
+			thrustCurve
+			{
+				key = 0 0.025 6.058514 6.058514
+				key = 0.025 0.5 36.04658 23.46252
+				key = 0.05 0.8 5.127337 3.570706
+				key = 0.09 0.88 0.923574 0.923574
+				key = 0.2 0.9 -0.00272356 0.03736424
+				key = 0.45 0.916 0.04794613 0.280352
+				key = 0.7 1 1.825101E-06 -2.297998E-06
+				key = 0.89 0.916 -0.6226192 0.0253601
+				key = 0.955 0.95 -0.2041948 -0.05783054
+				key = 1 0.5 -16.80979 0
+			}
+
+			//Assumed same as Altair 1 due to very limited data
+			TESTFLIGHT:NEEDS[TestLite|TestFlight]
+			{
+				ratedBurnTime = 12
+				ignitionReliabilityStart = 0.982673
+				ignitionReliabilityEnd = 0.996535
+				cycleReliabilityStart = 0.992500
+				cycleReliabilityEnd = 0.998500
+				reliabilityDataRateMultiplier = 2
+
+				isSolid = True
+			}
+		}
+	}
+}
diff --git a/GameData/RealismOverhaul/Engine_Configs/M55_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/M55_Config.cfg
@@ -80,6 +80,10 @@
 			minThrust = 876
 			maxThrust = 876
 			heatProduction = 100
+			massMult = 1.0
+			ullage = False
+			pressureFed = False
+			ignitions = 1
 			PROPELLANT
 			{
 				name = PBAA

diff --git a/GameData/RealismOverhaul/Engine_Configs/SIVUllageMotor_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/SIVUllageMotor_Config.cfg
@@ -0,0 +1,131 @@
+//	==================================================
+//	TX-280-10
+//
+//	Manufacturer: Huntsville Thiokol
+//
+//	=================================================================================
+//	TX-280-10
+//	S-IVB ullage motor
+//
+//	Dry Mass: 13.47 Kg
+//	Thrust (SL): ??? kN
+//	Thrust (Vac): 15.2 kN
+//	ISP: 85? SL / 222 Vac
+//	Burn Time: 3.8
+//	Chamber Pressure: ??? MPa
+//	Propellant: PSPC?
+//	Prop Ratio: N/A
+//	Throttle: N/A
+//	Nozzle Ratio: ???
+//	Ignitions: 1
+//	=================================================================================
+
+//	Sources:
+
+//	[1] https://www.enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml
+
+//	Used by:
+
+//	Notes:
+//	propellant mass 58.7 lbs
+//	==================================================
+@PART[*]:HAS[#engineType[SIVUllageMotor]]:FOR[RealismOverhaulEngines]
+{
+	%title = #roSIVUllageMotorTitle	//TX-280 Ullage Motor
+	%manufacturer = #roMfrThiokol
+	%description = #roSIVUllageMotorDesc
+
+	@tags ^= :$: USA thiokol tx280 tx-280 solid srm upper pspc
+
+	%specLevel = operational
+
+	@MODULE[ModuleEngines*]
+	{
+		%EngineType = SolidBooster
+		%allowShutdown = False
+		%throttleLocked = True
+	}
+
+	!MODULE[ModuleEngineConfigs],*{}
+	!MODULE[ModuleGimbal] {}
+	!MODULE[ModuleFuelTanks],* {}
+	!MODULE[ModuleAlternator],*{}
+	!RESOURCE,*{}
+
+	MODULE
+	{
+		name = ModuleFuelTanks
+		type = PSPC
+		volume = 15.3		//58.7 lbs propellant
+		basemass = -1
+	}
+
+	MODULE
+	{
+		name = ModuleEngineConfigs
+		type = ModuleEngines
+		configuration = TX-280
+		modded = false
+		origMass = 0.01347
+		CONFIG
+		{
+			name = TX-280
+			specLevel = operational
+			maxThrust = 15.2	//3420 lbf
+			minThrust = 15.2
+			heatProduction = 100
+			massMult = 1.0
+			PROPELLANT
+			{
+				name = PSPC
+				ratio = 1.0
+				DrawGauge = True
+			}
+			atmosphereCurve
+			{
+				key = 0 222	//58.7 lbs propellant for 3.81 second burn
+				key = 1 85
+			}
+			curveResource = PSPC
+			//Significant tail-off. Sep motors still visibly burning until ~8 seconds in AS-202 staging.
+			thrustCurve
+			{
+				key = 0 0.007467041 0 3.053555
+				key = 0.00095 0.07310704 12.41023 12.99596
+				key = 0.003565509 0.09227622 0.02760818 0
+				key = 0.08082595 0.09705795 0.01913727 0.0134879
+				key = 0.1060719 0.1863578 3.795439 4.807841
+				key = 0.1369827 0.3381339 4.128998 4.996992
+				key = 0.2055407 0.6038467 2.268262 2.419245
+				key = 0.37025 0.7948703 0.2438042 0.2563474
+				key = 0.6372364 0.815062 -0.01951 -0.01951
+				key = 0.8942021 0.8225991 0.08928865 0.0326228
+				key = 0.96207 0.874387 2.030076 3.47247
+				key = 0.98041 0.935927 3.24502 3.24479
+				key = 1 0.997467 3.0453 0
+			}
+			ullage = False
+			pressureFed = False
+			ignitions = 1
+			IGNITOR_RESOURCE
+			{
+				name = ElectricCharge
+				amount = 0.5
+			}
+
+			//never failed?
+			TESTFLIGHT:NEEDS[TestLite|TestFlight]
+			{
+				testedBurnTime = 9
+				ratedBurnTime = 4
+				safeOverburn = true
+				ignitionReliabilityStart = 0.99
+				ignitionReliabilityEnd = 0.999
+				cycleReliabilityStart = 0.99
+				cycleReliabilityEnd = 0.999
+				reliabilityDataRateMultiplier = 1
+				isSolid = True
+			}
+		}
+	}
+}