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Add H-2 configs #2994

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Add H-2 configs #2994

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156 changes: 156 additions & 0 deletions GameData/RealismOverhaul/Engine_Configs/H1_Config.cfg
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Original file line number Diff line number Diff line change
Expand Up @@ -84,6 +84,40 @@
// Ignitions: 1
// Gimbal: 10.5
// =================================================================================
// H-2 250K
// 1968? SII concept [12]
// H-2 baseline performance at 250k matched H-1 188k.
// Assume 0.5 percentage point increase in combustion efficiency from tap-off cycle
//
// Dry Mass: 915 kg [12] SII engine section estimated weight only 0.44% heavier than SI
// Thrust (SL): 1112.1 kN 250,000 klbf sl [12]
// Thrust (Vac): 1260.7 kN
// ISP: 262.0 SL / 297 Vac calculated with RPA
// Burn Time: 155
// Chamber Pressure: 4.52 MPa same as 188k?
// Propellant: LOX / RP1
// Prop Ratio: 2.34?
// Throttle: N/A
// Nozzle Ratio: 8
// Ignitions: 1
// =================================================================================
// H-2 300K
// 1976? Uprated S-II concept
// H-2 baseline performance at 250k matched H-1 188k. Scale to 300k to get chamber pressure, etc.
// Assume 0.5 percentage point increase in combustion efficiency from tap-off cycle
//
// Dry Mass: 915 kg [12] SII engine section estimated weight only 0.44% heavier than SI
// Thrust (SL): 1334.5 kN 300,000 klbf sl [12]
// Thrust (Vac): 1480.6 kN
// ISP: 267.70 SL / 297 Vac calculated with RPA
// Burn Time: 155
// Chamber Pressure: 5.42? MPa
// Propellant: LOX / RP1
// Prop Ratio: 2.34?
// Throttle: N/A
// Nozzle Ratio: 8
// Ignitions: 1
// =================================================================================
// RS-27
// 1974
//
Expand Down Expand Up @@ -131,6 +165,8 @@
// [9] https://web.archive.org/web/20211229003426/http://www.alternatewars.com/BBOW/Space_Engines/H-1C-D_Manual.pdf
// [10] https://web.archive.org/web/20220531043804/https://www.alternatewars.com/BBOW/Space_Engines/Saturn_H-1_Design_Features.pdf
// [11] https://web.archive.org/web/20211229003426/http://www.alternatewars.com/BBOW/Space_Engines/Launch_Vehicles_Engines_PDP_1-JAN-1967.pdf
// [12] https://nsarchive2.gwu.edu/NSAEBB/NSAEBB479/docs/EBB-Moon01A_sm.pdf
// [13] http://heroicrelics.org/info/h-1/saturn-h-1-engine-design-features.html
// [A] History of Liquid Propellant Rocket Engines, George P. Sutton, Page 409 Table 7.8-1
// [A] History of Liquid Propelland Rocket Engines, George P. Sutton, Page 424

Expand Down Expand Up @@ -477,6 +513,126 @@
}
}

CONFIG
{
name = H-2-250K
description = Enhanced H-1 design, featuring an enlarged, tap-off cycle turbopump and simplified components to increase thrust and reduce cost. Intended to power the Saturn-II and later versions of the Saturn-I, but development was cancelled due to satisfactory performance of the H-1 at increased thrust levels.
specLevel = concept
minThrust = 1260.7
maxThrust = 1260.7
heatProduction = 100
massMult = 1.0044

ullage = True
pressureFed = False
ignitions = 1

IGNITOR_RESOURCE
{
name = ElectricCharge
amount = 0.5
}

IGNITOR_RESOURCE
{
name = TEATEB
amount = 1
}

PROPELLANT
{
name = RP-1
ratio = 0.3880
DrawGauge = True
}

PROPELLANT
{
name = LqdOxygen
ratio = 0.6120
DrawGauge = False
}

atmosphereCurve
{
key = 0 297
key = 1 262
}

//No data, same as 205K
TESTFLIGHT:NEEDS[TestLite|TestFlight]
{
testedBurnTime = 3600 //simplified and theoretically less stressed due to enlarged pumps
ratedBurnTime = 155
safeOverburn = true
ignitionReliabilityStart = 0.976829
ignitionReliabilityEnd = 0.996341
cycleReliabilityStart = 0.976829
cycleReliabilityEnd = 0.996341
techTransfer = S-3D,S-3:25&H-1-188K,H-1-165K:50
}
}

CONFIG
{
name = H-2-300K
description = Enhanced H-1 design, featuring an enlarged, tap-off cycle turbopump and simplified components to increase thrust and reduce cost. Intended to power the Saturn-II and later versions of the Saturn-I, but development was cancelled due to satisfactory performance of the H-1 at increased thrust levels.
specLevel = speculative //300klbf version only mentioned in passing for future uprating
minThrust = 1480.6
maxThrust = 1480.6
heatProduction = 100
massMult = 1.0044

ullage = True
pressureFed = False
ignitions = 1

IGNITOR_RESOURCE
{
name = ElectricCharge
amount = 0.5
}

IGNITOR_RESOURCE
{
name = TEATEB
amount = 1
}

PROPELLANT
{
name = RP-1
ratio = 0.3880
DrawGauge = True
}

PROPELLANT
{
name = LqdOxygen
ratio = 0.6120
DrawGauge = False
}

atmosphereCurve
{
key = 0 297
key = 1 267.7
}

//No data, same as 205K
TESTFLIGHT:NEEDS[TestLite|TestFlight]
{
testedBurnTime = 3600 //simplified and theoretically less stressed due to enlarged pumps
ratedBurnTime = 155
safeOverburn = true
ignitionReliabilityStart = 0.976829
ignitionReliabilityEnd = 0.996341
cycleReliabilityStart = 0.976829
cycleReliabilityEnd = 0.996341
techTransfer = S-3D,S-3:25&H-2-250K,H-1-205K,H-1-200K,H-1-188K,H-1-165K:50
}
}

CONFIG
{
name = RS-27
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