From c2115982f573d7428d0125ca6adf8e0b33797ff8 Mon Sep 17 00:00:00 2001 From: Capkirk123 Date: Tue, 29 Aug 2023 21:46:34 -0500 Subject: [PATCH] Add RD-0108, improve RD-0110 configs --- .../Engine_Configs/RD0110_Config.cfg | 151 ++++++++++++++---- 1 file changed, 120 insertions(+), 31 deletions(-) diff --git a/GameData/RealismOverhaul/Engine_Configs/RD0110_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD0110_Config.cfg index 241742a19c..c594f92d6e 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD0110_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD0110_Config.cfg @@ -7,7 +7,7 @@ // RD-0106 (8D715, RO-6) // R-9 // -// Dry Mass: 451? Kg +// Dry Mass: 410? Kg // Thrust (SL): ??? kN // Thrust (Vac): 304 kN // ISP: 194 SL / 326? Vac SL calculated with RPA @@ -19,10 +19,10 @@ // Nozzle Ratio: 82.2 // Ignitions: 1 // ================================================================================= -// RD-0107 +// RD-0107 (8D715K) // Vostok, Molnyia // -// Dry Mass: 451 Kg +// Dry Mass: 410 Kg // Thrust (SL): ??? kN // Thrust (Vac): 297.9 kN // ISP: 194 SL / 326 Vac SL calculated with RPA @@ -34,18 +34,33 @@ // Nozzle Ratio: 82.2 // Ignitions: 1 // ================================================================================= -// RD-0110 +// RD-0108 (8D715P) +// Voskhod, Molnyia-M +// +// Dry Mass: 410 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 297.9 kN +// ISP: 194 SL / 326 Vac SL calculated with RPA +// Burn Time: 240 +// Chamber Pressure: 6.82 MPa +// Propellant: LOX / T-1 +// Prop Ratio: 2.22? +// Throttle: 100% to 90.5% +// Nozzle Ratio: 82.2 +// Ignitions: 1 +// ================================================================================= +// RD-0110 (11D55) // Molnyia-M, Soyuz // -// Dry Mass: 451 Kg +// Dry Mass: 408.5 Kg // Thrust (SL): ??? kN -// Thrust (Vac): 298.2 kN +// Thrust (Vac): 318.78 kN 107% of 297.926 // ISP: 245 SL / 330.4 Vac SL calculated with RPA // Burn Time: 250 // Chamber Pressure: 15.53 MPa // Propellant: LOX / T-1 // Prop Ratio: 2.22 -// Throttle: 100% to 90.5% +// Throttle: 107% to 90.5% // Nozzle Ratio: 82.2 // Ignitions: 1 // ================================================================================= @@ -57,11 +72,19 @@ // http://arc.aiaa.org/doi/book/10.2514/4.866371 // https://missilery.info/missile/r-9a // https://rvsn.ruzhany.info/missile_ssystem_p01_16.html +// https://web.archive.org/web/20111014092851/http://www.kbkha.ru/?p=8&cat=8&prod=37 +// http://forums.airbase.ru/2017/11/t93498_5--s-zemli-na-lunu-istoriya-lyudi-tekhnika-1958-1976.html // Used by: // Notes: +// RD-0106 and RD-0107 are functionally identical, differed only in mounting hardware I guess. Give same +// stats and reliability? +// RD-0108 was only used for Voskhod launches (unmanned and manned) and the first few Molniya-M launches. +// Mostly the same as the 0106/0107, but had "improved reliability" for manned launches. Give 0107 stats +// with 0110 reliability? +// RD-0110 was a complete modernization, ran at higher pressures and had the option for 107% throttle. // ================================================== @PART[*]:HAS[#engineType[RD0110]]:FOR[RealismOverhaulEngines] { @@ -76,7 +99,7 @@ MODULE { name = ModuleEngineConfigs - origMass = 0.451 + origMass = 0.410 configuration = RD-0107 modded = false CONFIG @@ -84,8 +107,8 @@ name = RD-0106 description = Upper stage for the R-9. specLevel = operational - maxThrust = 304 - minThrust = 304 + maxThrust = 297.9 + minThrust = 269.69 //90.5% massMult = 1.0 PROPELLANT { @@ -117,30 +140,32 @@ amount = 1 } - //R-9 Early R&D: 30 flights, 12 failures - //R-9 R&D: 65 flights, 10 failures - //Blaming 1/3rd of failures on upper stage - //no good data on these. Assuming 4:1 cycle to ignition failures based on RD0109, RD119 - //80 ignitions, 2 failures - //78 cycles, 5 failures + //Same as RD-0107 TESTFLIGHT:NEEDS[TestLite|TestFlight] { - testedBurnTime = 500 //Tested to 3 times rated burn time? + testedBurnTime = 750 //Tested to 3 times rated burn time? ratedBurnTime = 165 safeOverburn = true - ignitionReliabilityStart = 0.956996 - ignitionReliabilityEnd = 0.993210 + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + ignitionReliabilityStart = 0.983890 + ignitionReliabilityEnd = 0.996778 ignitionDynPresFailMultiplier = 0.1 - cycleReliabilityStart = 0.907806 - cycleReliabilityEnd = 0.985443 + cycleReliabilityStart = 0.944915 + cycleReliabilityEnd = 0.988983 techTransfer = RD-0107:50 } } CONFIG { name = RD-0107 - description = Upper stage for the R-7. Used on Vostok and early Molniya rockets. + description = Upper stage for the R-7. Used on Vostok and Molniya rockets. specLevel = operational maxThrust = 297.9 minThrust = 269.69 //90.5% @@ -175,11 +200,15 @@ amount = 1 } + //R-9 Early R&D: 30 flights, 12 failures + //R-9 R&D: 65 flights, 10 failures + //Blaming 1/3rd of failures on upper stage + //Molniya (8K78): 39 flights, 8 failures //Voskhod (11A57): 299 flights, 13 failures //no good data on these. Assuming 4:1 cycle to ignition failures based on RD0109, RD119 - //338 ignitions, 4 failures - //334 cycles, 17 failures + //418 ignitions, 6 failures + //412 cycles, 22 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 750 //Tested to 3 times rated burn time? @@ -193,22 +222,82 @@ key = 1.00 1.00 3 3 } - ignitionReliabilityStart = 0.982252 - ignitionReliabilityEnd = 0.997198 + ignitionReliabilityStart = 0.983890 + ignitionReliabilityEnd = 0.996778 ignitionDynPresFailMultiplier = 0.1 - cycleReliabilityStart = 0.932886 - cycleReliabilityEnd = 0.989403 + cycleReliabilityStart = 0.944915 + cycleReliabilityEnd = 0.988983 techTransfer = RD-0106:50 } } CONFIG + { + name = RD-0108 + description = Upper stage for the R-7. Used on Voskhod and early Molniya-M rockets. + specLevel = operational + maxThrust = 297.9 + minThrust = 269.69 //90.5% + massMult = 1.0 + PROPELLANT + { + name = Kerosene + ratio = 0.3981 + DrawGauge = true + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.6019 + } + atmosphereCurve + { + key = 0 326 + key = 1 194 + } + + ullage = True + ignitions = 1 + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + IGNITOR_RESOURCE + { + name = TEATEB + amount = 1 + } + + //Same as RD-0110 + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 750 //Tested to 3 times rated burn time? + ratedBurnTime = 240 + safeOverburn = true + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + + ignitionReliabilityStart = 0.995052 + ignitionReliabilityEnd = 0.999219 + ignitionDynPresFailMultiplier = 0.1 + cycleReliabilityStart = 0.983540 + cycleReliabilityEnd = 0.997401 + techTransfer = RD-0107,RD-0106:50 + } + } + CONFIG { name = RD-0110 description = Developed for the upgraded Molniya-M, and later used on Soyuz. specLevel = operational - maxThrust = 298.2 + maxThrust = 318.78 //107% minThrust = 269.69 //90.5% - massMult = 1.0 + massMult = 0.9963 PROPELLANT { name = Kerosene @@ -270,7 +359,7 @@ ignitionDynPresFailMultiplier = 0.1 cycleReliabilityStart = 0.983540 cycleReliabilityEnd = 0.997401 - techTransfer = RD-0107,RD-0106:50 + techTransfer = RD-0108,RD-0107,RD-0106:50 } } }