diff --git a/GameData/RealismOverhaul/Engine_Configs/A1_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/A1_Config.cfg new file mode 100644 index 0000000000..4f544f2c0c --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/A1_Config.cfg @@ -0,0 +1,148 @@ +// ================================================== +// Hermes A-1 Engine +// +// Manufacturer: GE +// +// ================================================================================= +// A-1 +// +// +// Dry Mass: 140 kg guess. Pretty high TWR for the time, very basic pressure-fed motor? +// Thrust (SL): 60.1 kN 13,500 lbf [A/1/10] +// Thrust (Vac): 71.2 kN ~16,000 lbf (see notes) +// ISP: 200 SL / 237 Vac estimated with RPA +// Burn Time: 40 Looks like around 35-40 seconds to burnout from [11] +// Chamber Pressure: 2.28 MPa same as XASR? +// Propellant: LOX / 75% Ethanol +// Prop Ratio: 1.12 //guess, same as A-3? [A] +// Throttle: N/A +// Nozzle Ratio: 5.6? based on shot of engine in [11] +// Ignitions: 1 +// ================================================================================= +// +// SOURCES +// [1] https://web.archive.org/web/20200229064126/http://www.alternatewars.com/BBOW/Space_Engines/GE_Engines.htm +// [2] https://www.designation-systems.net/dusrm/app1/ssm-a-16.html +// [3] https://web.archive.org/web/20070707183816/https://www.nasm.si.edu/spacecraft/RM-HermesA-3B.htm +// [4] https://web.archive.org/web/20030207120603/http://www.ufx.org/gfb/hermes.html +// [5] http://www.astronautix.com/h/hermesmissile.html +// [6] http://www.astronautix.com/h/hermesa-1.html +// [7] https://en.wikipedia.org/wiki/Hermes_program#The_Surface_to_Air_and_Surface_to_Surface_Missiles +// [8] https://wsmrmuseum.com/2020/08/24/the-hermes-program/ +// [9] https://weebau.com/rock_us/hermes-a1.php +// [10] http://heroicrelics.org/msfc/hermes/index.html +// [11] https://forum.nasaspaceflight.com/index.php?topic=43813.0 +// [A] History of Liquid Propellant Rocket Engines, George P. Sutton + +// Used by: + +// Notes: +// Two thrust levels quoted, 13,500 lbf by [A/1/10] and 16,000 lbf by [2/6] +// [11] quotes 19,000 lbf, likely a misreading of 16,000 lbf +// However, video of launch in [11] shows A-1 needs about 29 frames (1.21 seconds) to rise it's own height +// from the launch pad (300 inches), giving an acceleration of ~1.06 G and a liftoff TWR of 2.06 +// Assuming quoted wet mass of 6675 lbs is accurate, this agrees with 13500 lbf thrust at sea level +// 16000 lbf is probably vacuum thrust? Agrees with RPA-calculated numbers +// ================================================================================= + +@PART[*]:HAS[#engineType[A1]]:FOR[RealismOverhaulEngines] +{ + %title = #roA1Title //A-1 + %manufacturer = #roMfrGE + %description = #roA1Desc + + @tags ^= :$: us ge general electric a1 a-1 liquid pressure-fed booster ethanol liquid oxygen + + %specLevel = operational + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + @MODULE[ModuleGimbal] //thrust vanes + { + %gimbalRange = 3 + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = A-1 + origMass = 0.140 + literalZeroIgnitions = True + + CONFIG + { + name = A-1 + description = + specLevel = operational + minThrust = 71.2 + maxThrust = 71.2 + heatProduction = 100 + massMult = 1.0 + + ullage = True + pressureFed = True + ignitions = 0 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + PROPELLANT + { + name = Ethanol75 + ratio = 0.5476 + DrawGauge = True + } + + PROPELLANT + { + name = LqdOxygen + ratio = 0.4524 + } + + PROPELLANT + { + name = Helium + ratio = 34.2 + ignoreForIsp = True + DrawGauge = False + } + + atmosphereCurve + { + key = 0 237 + key = 1 200 + } + + //Hermes A-1: 5 flights, 1 failure (1 cycle) + //Flight #2 exploded after burnout [9] so probably not engine? + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 40 + ignitionReliabilityStart = 0.875000 + ignitionReliabilityEnd = 0.975000 + cycleReliabilityStart = 0.750000 + cycleReliabilityEnd = 0.941667 + techTransfer = Wasserfall:50 + } + } + } +} + ++PART[ROE-XLR10] +{ + @name = a1 + @engineType = A1 +} diff --git a/GameData/RealismOverhaul/Engine_Configs/A3_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/A3_Config.cfg new file mode 100644 index 0000000000..7279350683 --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/A3_Config.cfg @@ -0,0 +1,216 @@ +// ================================================== +// Hermes A-3 Engine +// +// Manufacturer: GE +// +// ================================================================================= +// A-3A +// RV-A-8 +// +// Dry Mass: 175 kg guess, pump-fed. Similar to XLR-10 +// Thrust (SL): 80.1 kN 18,000 lbf [A/1/10] +// Thrust (Vac): 94.9 kN +// ISP: 200 SL / 237 Vac estimated with RPA +// Burn Time: 70 same as A-3B? +// Chamber Pressure: 2.28 MPa same as A-1? +// Propellant: LOX / 75% Ethanol +// Prop Ratio: 1.12 [A] +// Throttle: N/A +// Nozzle Ratio: 5.6? same as A-1? +// Ignitions: 1 +// ================================================================================= +// A-3B +// SSM-A-16 +// +// Dry Mass: 165 kg guess. Simplified, and startup system moved from engine to launchpad. Closer to X-405 +// Thrust (SL): 93.4 kN 21,000 lbf [A/1/10] +// Thrust (Vac): 110.9 kN +// ISP: 203 SL / 241 Vac estimated with RPA +// Burn Time: 70 estimated from fuel load +// Chamber Pressure: 2.5 MPa guess, uprated +// Propellant: LOX / 75% Ethanol +// Prop Ratio: 1.12 [A] +// Throttle: N/A +// Nozzle Ratio: 5.6? same as A-1? +// Ignitions: 1 +// ================================================================================= +// +// SOURCES +// [1] https://web.archive.org/web/20200229064126/http://www.alternatewars.com/BBOW/Space_Engines/GE_Engines.htm +// [2] https://www.designation-systems.net/dusrm/app1/ssm-a-16.html +// [3] https://web.archive.org/web/20070707183816/https://www.nasm.si.edu/spacecraft/RM-HermesA-3B.htm +// [4] https://web.archive.org/web/20030207120603/http://www.ufx.org/gfb/hermes.html +// [5] http://www.astronautix.com/h/hermesmissile.html +// [6] http://www.astronautix.com/h/hermesa-3a.html +// [7] https://en.wikipedia.org/wiki/Hermes_program#The_Surface_to_Air_and_Surface_to_Surface_Missiles +// [8] https://wsmrmuseum.com/2020/08/24/the-hermes-program/ +// [9] https://weebau.com/rock_us/hermes-a1.php +// [10] http://heroicrelics.org/msfc/hermes/index.html +// [11] https://forum.nasaspaceflight.com/index.php?topic=43813.0 +// [12] https://wsmrmuseum.com/2020/10/06/the-v-2-program-operation-backfire-to-the-hermes-project/7/ +// [A] History of Liquid Propellant Rocket Engines, George P. Sutton + +// Used by: + +// Notes: + +// ================================================================================= + +@PART[*]:HAS[#engineType[A3]]:FOR[RealismOverhaulEngines] +{ + %title = #roA3Title //A-3 + %manufacturer = #roMfrGE + %description = #roA3Desc + + @tags ^= :$: us ge general electric a3 a-3 liquid pressure-fed booster ethanol liquid oxygen + + %specLevel = operational + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + @MODULE[ModuleGimbal] //gimbal + { + %gimbalRange = 5 //guess + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = A-3A + origMass = 0.175 + literalZeroIgnitions = True + + CONFIG + { + name = A-3A + description = Prototype engine, used on the Hermes A-3A (RV-A-8) test vehicle. + specLevel = operational + minThrust = 94.9 + maxThrust = 94.9 + heatProduction = 100 + massMult = 1.0 + + ullage = True + pressureFed = False + ignitions = 0 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + PROPELLANT + { + name = Ethanol75 + ratio = 0.5476 + DrawGauge = True + } + + PROPELLANT + { + name = LqdOxygen + ratio = 0.4524 + } + + PROPELLANT + { + name = HTP + ratio = 0.0108 // sqrt of fraction of X-405? + ignoreForIsp = True + DrawGauge = False + } + + atmosphereCurve + { + key = 0 237 + key = 1 200 + } + + //Hermes A-3A: 7 flights, 1 failure (1 cycle) + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 70 + ignitionReliabilityStart = 0.881250 + ignitionReliabilityEnd = 0.981250 + cycleReliabilityStart = 0.750000 + cycleReliabilityEnd = 0.956250 + techTransfer = A-1:50 + } + } + CONFIG + { + name = A-3B + description = Uprated engine for the Hermes A-3B (SSM-A-16) missile. + specLevel = operational + minThrust = 110.9 + maxThrust = 110.9 + heatProduction = 100 + massMult = 0.9429 + + ullage = True + pressureFed = False + ignitions = 0 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + PROPELLANT + { + name = Ethanol75 + ratio = 0.5476 + DrawGauge = True + } + + PROPELLANT + { + name = LqdOxygen + ratio = 0.4524 + } + + PROPELLANT + { + name = HTP + ratio = 0.0113 // sqrt of fraction of X-405? + ignoreForIsp = True + DrawGauge = False + } + + atmosphereCurve + { + key = 0 241 + key = 1 203 + } + + //Hermes A-3B: 6 flights, 0 failure + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + ratedBurnTime = 70 + ignitionReliabilityStart = 0.864286 + ignitionReliabilityEnd = 0.978571 + cycleReliabilityStart = 0.864286 + cycleReliabilityEnd = 0.978571 + techTransfer = A-3A,A-1:50 + } + } + } +} + ++PART[ROE-XLR10] +{ + @name = a3 + @engineType = A3 +} diff --git a/GameData/RealismOverhaul/Localization/en-us-Engines.cfg b/GameData/RealismOverhaul/Localization/en-us-Engines.cfg index 6142119689..cabab8c0f1 100644 --- a/GameData/RealismOverhaul/Localization/en-us-Engines.cfg +++ b/GameData/RealismOverhaul/Localization/en-us-Engines.cfg @@ -21,6 +21,12 @@ Localization #ro25KS18000Title = Aerojet 2.5KS-18000 #ro25KS18000Desc = A small but powerful solid fueled booster used as the first stage for the Aerobee line of sounding rockets. //A + // A-1 + #roA1Title = A-1 + #roA1Desc = A basic pressure-fed booster engine developed by General Electric to power American-built Wasserfall missiles for the Hermes program (CTV-G-5). Although the design was deemed unsuitable for military use, several Hermes A-1 missiles were still flown to gain experience in the construction and operation of large rockets. + // A-3 + #roA3Title = A-3 + #roA3Desc = A basic pump-fed booster engine developed as an improved version of the Hermes A-1 for the Hermes A-3 ballistic missile. Difficulties with development led the program being split into two parts, with the smaller A-3A testing the engine and guidance systems for the larger A-3B. Although it was evaluated for use by the US Army as the SSM-A-16, it was rejected due to poor performance and reliability. // A-4 #roA-4Title = A-4 #roA-4Desc = A Thiel alcolox engine used on the V-2 missile. Interim design, but went into production. Used 18 x 1.5 tonne thrust chambers that fed a common mixing chamber. Work began 1936, testing in 1939, and mass production from 1943-1945.