From 2d5f60eb315a1c45dae656b759f2ff5e676e0ddd Mon Sep 17 00:00:00 2001 From: Capkirk123 Date: Sun, 28 Jan 2024 21:19:14 -0500 Subject: [PATCH] Chinese engine configs (+Kerwis) (#2932) * Long March 1 * Long March 2 * Long March 3 * Long March 5 * kerwis compat --------- Co-authored-by: NovemberOrWhatever --- .../Jet_Engine_Configs/R11_Config.cfg | 249 ++++++++++++- .../Jet_Engine_Configs/RD9_Config.cfg | 246 ++++++++++++- .../Jet_Engine_Configs/WS10_Config.cfg | 253 +++++++++++++ .../Engine_Configs/YF100_Config.cfg | 159 +++++++++ .../Engine_Configs/YF1_Config.cfg | 255 +++++++++++++ .../Engine_Configs/YF20_Config.cfg | 334 ++++++++++++++++++ .../Engine_Configs/YF22_Config.cfg | 263 ++++++++++++++ .../Engine_Configs/YF23_Config.cfg | 186 ++++++++++ .../Engine_Configs/YF3_Config.cfg | 191 ++++++++++ .../Engine_Configs/YF40_Config.cfg | 252 +++++++++++++ .../Engine_Configs/YF75_Config.cfg | 240 +++++++++++++ .../{YF-77.cfg => YF77_Config.cfg} | 56 +-- .../Localization/en-us-Engines.cfg | 38 +- .../Localization/en-us-Mfr.cfg | 1 + .../RO_SuggestedMods/Kerwis/Kerwis_RO.cfg | 165 +++++++++ 15 files changed, 2861 insertions(+), 27 deletions(-) create mode 100644 GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/WS10_Config.cfg create mode 100644 GameData/RealismOverhaul/Engine_Configs/YF100_Config.cfg create mode 100644 GameData/RealismOverhaul/Engine_Configs/YF1_Config.cfg create mode 100644 GameData/RealismOverhaul/Engine_Configs/YF20_Config.cfg create mode 100644 GameData/RealismOverhaul/Engine_Configs/YF22_Config.cfg create mode 100644 GameData/RealismOverhaul/Engine_Configs/YF23_Config.cfg create mode 100644 GameData/RealismOverhaul/Engine_Configs/YF3_Config.cfg create mode 100644 GameData/RealismOverhaul/Engine_Configs/YF40_Config.cfg create mode 100644 GameData/RealismOverhaul/Engine_Configs/YF75_Config.cfg rename GameData/RealismOverhaul/Engine_Configs/{YF-77.cfg => YF77_Config.cfg} (57%) create mode 100644 GameData/RealismOverhaul/RO_SuggestedMods/Kerwis/Kerwis_RO.cfg diff --git a/GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/R11_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/R11_Config.cfg index b3921116a2..047e429363 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/R11_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/R11_Config.cfg @@ -67,11 +67,102 @@ // Exhaust Mixer: false // Adjustable Nozzle: true // ================================================================================= +// WP-7 +// 1966, J-7 +// +// Dry Mass: 1151 kg +// Thrust (Dry): 38.25 kN +// Thrust (Wet): 56.39 kN +// SFC (Dry): 0.989 lb/lbf-hr +// Area: 0.25 m^2 //Compressor Area +// BPR: 0.0 //Bypass Ratio +// CPR: 8.85 //Compressor Pressure Ratio +// FPR: 0.0 //Fan Ratio +// Mdes: 0.9 M //Mach Design Point +// Tdes: 250 K //Temp Design Point +// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance +// FHV: 30000000 J //Fuel heat of burning +// TIT: 1188 K //Combustion peak temp temperature increased by 100 C +// TAB: 1988* K //Afterburner peak temp +// maxT3: 750 K //Turbine max temperature +// Exhaust Mixer: false +// Adjustable Nozzle: true +// ================================================================================= +// WP-7A +// 1969, J-8 +// +// Dry Mass: 1158 kg +// Thrust (Dry): 43.15 kN +// Thrust (Wet): 58.84 kN +// SFC (Dry): 0.997 lb/lbf-hr +// Area: 0.25 m^2 //Compressor Area +// BPR: 0.0 //Bypass Ratio +// CPR: 8.85 //Compressor Pressure Ratio +// FPR: 0.0 //Fan Ratio +// Mdes: 0.9 M //Mach Design Point +// Tdes: 250 K //Temp Design Point +// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance +// FHV: 30000000 J //Fuel heat of burning +// TIT: 1288 K //Combustion peak temp temperature increased by 100 C +// TAB: 1844* K //Afterburner peak temp +// maxT3: 750 K //Turbine max temperature +// Exhaust Mixer: false +// Adjustable Nozzle: true +// ================================================================================= +// WP-7B +// 1978, J-7/IIM, JJ-7, F-7BK/M, J-8I +// +// Dry Mass: 1191 kg +// Thrust (Dry): 43.15 kN +// Thrust (Wet): 59.82 kN +// SFC (Dry): 1.03 lb/lbf-hr +// Area: 0.25 m^2 //Compressor Area +// BPR: 0.0 //Bypass Ratio +// CPR: 8.85 //Compressor Pressure Ratio +// FPR: 0.0 //Fan Ratio +// Mdes: 0.9 M //Mach Design Point +// Tdes: 250 K //Temp Design Point +// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance +// FHV: 30000000 J //Fuel heat of burning +// TIT: 1288 K //Combustion peak temp +// TAB: 1906* K //Afterburner peak temp +// maxT3: 750 K //Turbine max temperature +// Exhaust Mixer: false +// Adjustable Nozzle: true +// ================================================================================= +// WP-7BM? (a.k.a. WP-7C?, WP-7BB?) +// 1982, J-7I/II/IIH, F-7A/B +// +// Dry Mass: 1174 kg weight reduced by 17 kg +// Thrust (Dry): 43.15 kN +// Thrust (Wet): 60.60 kN +// SFC (Dry): 1.014 lb/lbf-hr 1.5% improved fuel consumption? +// Area: 0.25 m^2 //Compressor Area +// BPR: 0.0 //Bypass Ratio +// CPR: 8.85 //Compressor Pressure Ratio +// FPR: 0.0 //Fan Ratio +// Mdes: 0.9 M //Mach Design Point +// Tdes: 250 K //Temp Design Point +// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance +// FHV: 30000000 J //Fuel heat of burning +// TIT: 1288 K //Combustion peak temp +// TAB: 1956* K //Afterburner peak temp +// maxT3: 800 K //Turbine max temperature +// Exhaust Mixer: false +// Adjustable Nozzle: true +// ================================================================================= // Sources: // http://www.leteckemotory.cz/motory/r-11/ // https://www.jet-engine.net/miltfspec.htm +// https://en.wikipedia.org/wiki/List_of_Chengdu_J-7_variants +// https://zh.wikipedia.org/wiki/%E6%AD%BC-7 +// https://www.globalsecurity.org/military/world/china/wp7b.htm +// https://baike.baidu.com/item/%E6%B6%A1%E5%96%B7-7/3320215 +// https://www.toutiao.com/article/7279380979536888374/?wid=1702343967612 +// https://www.bilibili.com/read/cv12544738/ +// Aviation World 2015.1 - The Heroic Heart - A brief discussion of China's military aviation engines // Used by: @@ -85,7 +176,7 @@ %manufacturer = #roMfrOKB300 %description = #roR11Desc - @tags ^= :$: ussr okb300 r11 r-11 afterburning turbojet + @tags ^= :$: ussr prc china okb300 r11 r-11 wp7 wp-7 afterburning turbojet %specLevel = operational //operational, prototype, concept, speculative, altHist, sciFi @@ -226,6 +317,162 @@ drySFC = 0.95 throttleResponseMultiplier = 0.30 //60s double-spool, 0.30 + PROPELLANT + { + name = Kerosene + ratio = 1.0 + DrawGauge = True + } + } + CONFIG + { + name = WP-7 + description = Afterburning R-11 derivative, as used on the J-7. Temperature Mach limit at 15 km: 2.54. + specLevel = operational + massMult = 1.004 + + Area = 0.25 //Compressor Area + BPR = 0.0 //Bypass Ratio + CPR = 8.85 //Compressor Pressure Ratio + FPR = 0.0 //Fan Ratio + Mdes = 0.9 //Mach Design Point + Tdes = 250 //Temp Design Point + eta_c = 0.95 //Efficiency at burner inlet + eta_t = 0.98 //Efficiency at burner exit + eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance + FHV = 30000000 //Fuel heat of burning (joules?) + TIT = 1188 //Combustion peak temp + TAB = 1988 //Afterburner temp? + maxT3 = 750 //Turbine max temperature + exhaustMixer = False + adjustableNozzle = True + thrustUpperLimit = 120 + + // Engine fitting params + defaultTPR = 0.85 + dryThrust = 38.25 + wetThrust = 56.39 + maxThrust = 56.39 //Just to let MEC know thrust + drySFC = 0.989 + throttleResponseMultiplier = 0.30 //60s 2-spool/variable vanes: 0.30 + + PROPELLANT + { + name = Kerosene + ratio = 1.0 + DrawGauge = True + } + } + CONFIG + { + name = WP-7A + description = Afterburning R-11 derivative, as used on the J-8. Temperature Mach limit at 15 km: 2.54. + specLevel = operational + massMult = 1.010 + + Area = 0.25 //Compressor Area + BPR = 0.0 //Bypass Ratio + CPR = 8.85 //Compressor Pressure Ratio + FPR = 0.0 //Fan Ratio + Mdes = 0.9 //Mach Design Point + Tdes = 250 //Temp Design Point + eta_c = 0.95 //Efficiency at burner inlet + eta_t = 0.98 //Efficiency at burner exit + eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance + FHV = 30000000 //Fuel heat of burning (joules?) + TIT = 1288 //Combustion peak temp + TAB = 1844 //Afterburner temp? + maxT3 = 750 //Turbine max temperature + exhaustMixer = False + adjustableNozzle = True + thrustUpperLimit = 120 + + // Engine fitting params + defaultTPR = 0.85 + dryThrust = 43.15 + wetThrust = 58.84 + maxThrust = 58.84 //Just to let MEC know thrust + drySFC = 0.997 + throttleResponseMultiplier = 0.30 //60s 2-spool/variable vanes: 0.30 + + PROPELLANT + { + name = Kerosene + ratio = 1.0 + DrawGauge = True + } + } + CONFIG + { + name = WP-7B + description = Afterburning R-11 derivative, as used on the J-7IIM, JJ-7, F-7BK/M and J-8I. Temperature Mach limit at 15 km: 2.54. + specLevel = operational + massMult = 1.039 + + Area = 0.25 //Compressor Area + BPR = 0.0 //Bypass Ratio + CPR = 8.85 //Compressor Pressure Ratio + FPR = 0.0 //Fan Ratio + Mdes = 0.9 //Mach Design Point + Tdes = 250 //Temp Design Point + eta_c = 0.95 //Efficiency at burner inlet + eta_t = 0.98 //Efficiency at burner exit + eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance + FHV = 30000000 //Fuel heat of burning (joules?) + TIT = 1288 //Combustion peak temp + TAB = 1906 //Afterburner temp? + maxT3 = 750 //Turbine max temperature + exhaustMixer = False + adjustableNozzle = True + thrustUpperLimit = 120 + + // Engine fitting params + defaultTPR = 0.85 + dryThrust = 43.15 + wetThrust = 59.82 + maxThrust = 59.82 //Just to let MEC know thrust + drySFC = 1.03 + throttleResponseMultiplier = 0.60 //70s: 0.60 + + PROPELLANT + { + name = Kerosene + ratio = 1.0 + DrawGauge = True + } + } + CONFIG + { + name = WP-7BM + description = Afterburning R-11 derivative, as used on the J-7IIH and F-7A/B. Temperature Mach limit at 15 km: 2.77. + specLevel = operational + massMult = 1.024 + + Area = 0.25 //Compressor Area + BPR = 0.0 //Bypass Ratio + CPR = 8.85 //Compressor Pressure Ratio + FPR = 0.0 //Fan Ratio + Mdes = 0.9 //Mach Design Point + Tdes = 250 //Temp Design Point + eta_c = 0.95 //Efficiency at burner inlet + eta_t = 0.98 //Efficiency at burner exit + eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance + FHV = 30000000 //Fuel heat of burning (joules?) + TIT = 1288 //Combustion peak temp + TAB = 1956 //Afterburner temp? + maxT3 = 800 //Turbine max temperature + exhaustMixer = False + adjustableNozzle = True + thrustUpperLimit = 120 + + // Engine fitting params + defaultTPR = 0.85 + dryThrust = 43.15 + wetThrust = 60.60 + maxThrust = 60.60 //Just to let MEC know thrust + drySFC = 1.014 + throttleResponseMultiplier = 0.80 + PROPELLANT { name = Kerosene diff --git a/GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/RD9_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/RD9_Config.cfg index edece4adb5..a967908935 100644 --- a/GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/RD9_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/RD9_Config.cfg @@ -67,11 +67,97 @@ // Exhaust Mixer: false // Adjustable Nozzle: true // ================================================================================= +// WP-6 +// 1959, J-6 +// +// Dry Mass: 708 kg +// Thrust (Dry): 25.49 kN +// Thrust (Wet): 31.87 kN +// SFC (Dry): 0.99 lb/lbf-hr +// Area: 0.14 m^2 //Compressor Area +// BPR: 0.0 //Bypass Ratio +// CPR: 7.14 //Compressor Pressure Ratio +// FPR: 0.0 //Fan Ratio +// Mdes: 0.8 M //Mach Design Point +// Tdes: 270 K //Temp Design Point +// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance +// FHV: 22000000 J //Fuel heat of burning +// TIT: 1143 K //Combustion peak temp +// TAB: 1375* K //Afterburner peak temp +// maxT3: 650 K //Turbine max temperature +// Exhaust Mixer: false +// Adjustable Nozzle: true +// ================================================================================= +// WP-6A +// 1965, J-6A/B/C/I/II/III, JJ-6, JZ-6, F-6/A/C, FT-6, FR-6 +// +// Dry Mass: 725 kg +// Thrust (Dry): 29.4 kN +// Thrust (Wet): 36.8 kN +// SFC (Dry): 1.00 lb/lbf-hr +// Area: 0.14 m^2 //Compressor Area +// BPR: 0.0 //Bypass Ratio +// CPR: 7.44 //Compressor Pressure Ratio +// FPR: 0.0 //Fan Ratio +// Mdes: 0.8 M //Mach Design Point +// Tdes: 270 K //Temp Design Point +// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance +// FHV: 22000000 J //Fuel heat of burning +// TIT: 1193 K //Combustion peak temp +// TAB: 1439* K //Afterburner peak temp +// maxT3: 675 K //Turbine max temperature +// Exhaust Mixer: false +// Adjustable Nozzle: true +// ================================================================================= +// WP-6A-III +// 1984, Q-5I/IA/II/IV/D/E/F/G/L/N, JQ-5J, A-5/IIA/IIK/IIIA/C/M +// +// Dry Mass: 725 kg +// Thrust (Dry): 29.4 kN +// Thrust (Wet): 36.8 kN +// SFC (Dry): 0.985 lb/lbf-hr 1.5% improved fuel consumption +// Area: 0.14 m^2 //Compressor Area +// BPR: 0.0 //Bypass Ratio +// CPR: 7.44 //Compressor Pressure Ratio +// FPR: 0.0 //Fan Ratio +// Mdes: 0.8 M //Mach Design Point +// Tdes: 270 K //Temp Design Point +// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance +// FHV: 22000000 J //Fuel heat of burning +// TIT: 1193 K //Combustion peak temp +// TAB: 1439* K //Afterburner peak temp +// maxT3: 800 K //Turbine max temperature +// Exhaust Mixer: false +// Adjustable Nozzle: true +// ================================================================================= +// WP-6Z +// 1971, J-12I +// +// Dry Mass: 750 kg? +// Thrust (Dry): 24.5 kN +// Thrust (Wet): 39.7 kN +// SFC (Dry): 1.02 lb/lbf-hr +// Area: 0.14 m^2 //Compressor Area +// BPR: 0.0 //Bypass Ratio +// CPR: 7.44 //Compressor Pressure Ratio +// FPR: 0.0 //Fan Ratio +// Mdes: 0.9 M //Mach Design Point +// Tdes: 250 K //Temp Design Point +// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance +// FHV: 22000000 J //Fuel heat of burning +// TIT: 1193 K //Combustion peak temp +// TAB: 2412* K //Afterburner peak temp +// maxT3: 700 K //Turbine max temperature +// Exhaust Mixer: false +// Adjustable Nozzle: true +// ================================================================================= // Sources: // http://www.leteckemotory.cz/motory/rd-9b/ // https://www.jet-engine.net/miltfspec.htm +// https://xueqiu.com/6702987851/163891477 +// Aviation World 2015.1 - The Heroic Heart - A brief discussion of China's military aviation engines // Used by: @@ -85,7 +171,7 @@ %manufacturer = #roMfrOKB300 %description = #roRD9Desc - @tags ^= :$: ussr okb300 soyuz rd9 rd-9 afterburning turbojet + @tags ^= :$: ussr prc china okb300 soyuz rd9 rd-9 wp6 wp-6 afterburning turbojet %specLevel = operational //operational, prototype, concept, speculative, altHist, sciFi @@ -119,7 +205,7 @@ CONFIG { name = RD-9B - description = Early afterburning RD-9, as used on the MiG-19/S/PF/PM. Temperature Mach limit at 15 km: 2.0. + description = Early afterburning RD-9, as used on the MiG-19/S/PF/PM and early J-7 models. Temperature Mach limit at 15 km: 2.0. specLevel = operational massMult = 1.00 @@ -226,6 +312,162 @@ drySFC = 1.02 throttleResponseMultiplier = 0.20 // 60s 1-spool: 0.20 + PROPELLANT + { + name = Kerosene + ratio = 1.0 + DrawGauge = True + } + } + CONFIG + { + name = WP-6 + description = Afterburning RD-9 derivative, as used on early J-6 models. Temperature Mach limit at 15 km: 2.12. + specLevel = operational + massMult = 1.0187 + + Area = 0.14 //Compressor Area + BPR = 0.0 //Bypass Ratio + CPR = 7.14 //Compressor Pressure Ratio + FPR = 0.0 //Fan Ratio + Mdes = 0.8 //Mach Design Point + Tdes = 270 //Temp Design Point + eta_c = 0.95 //Efficiency at burner inlet + eta_t = 0.98 //Efficiency at burner exit + eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance + FHV = 22000000 //Fuel heat of burning (joules?) + TIT = 1143 //Combustion peak temp + TAB = 1375 //Afterburner temp? + maxT3 = 650 //Turbine max temperature + exhaustMixer = False + adjustableNozzle = True + thrustUpperLimit = 60 + + // Engine fitting params + defaultTPR = 0.95 + dryThrust = 25.49 + wetThrust = 31.87 + maxThrust = 31.87 //Just to let MEC know thrust + drySFC = 0.99 + throttleResponseMultiplier = 0.20 // 60s 1-spool: 0.20 + + PROPELLANT + { + name = Kerosene + ratio = 1.0 + DrawGauge = True + } + } + CONFIG + { + name = WP-6A + description = Afterburning RD-9 derivative, as used on most J-6 models and early Q-5 models. Temperature Mach limit at 15 km: 2.23. + specLevel = operational + massMult = 1.0432 + + Area = 0.14 //Compressor Area + BPR = 0.0 //Bypass Ratio + CPR = 7.44 //Compressor Pressure Ratio + FPR = 0.0 //Fan Ratio + Mdes = 0.8 //Mach Design Point + Tdes = 270 //Temp Design Point + eta_c = 0.95 //Efficiency at burner inlet + eta_t = 0.98 //Efficiency at burner exit + eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance + FHV = 22000000 //Fuel heat of burning (joules?) + TIT = 1193 //Combustion peak temp + TAB = 1439 //Afterburner temp? + maxT3 = 675 //Turbine max temperature + exhaustMixer = False + adjustableNozzle = True + thrustUpperLimit = 60 + + // Engine fitting params + defaultTPR = 0.95 + dryThrust = 29.4 + wetThrust = 36.8 + maxThrust = 36.8 //Just to let MEC know thrust + drySFC = 1.00 + throttleResponseMultiplier = 0.20 // 60s 1-spool: 0.20 + + PROPELLANT + { + name = Kerosene + ratio = 1.0 + DrawGauge = True + } + } + CONFIG + { + name = WP-6A-III + description = Afterburning RD-9 derivative, as used on the Q-5I, A-5 and JQ-5J. Temperature Mach limit at 15 km: 2.84. + specLevel = operational + massMult = 1.0432 + + Area = 0.14 //Compressor Area + BPR = 0.0 //Bypass Ratio + CPR = 7.44 //Compressor Pressure Ratio + FPR = 0.0 //Fan Ratio + Mdes = 0.8 //Mach Design Point + Tdes = 270 //Temp Design Point + eta_c = 0.95 //Efficiency at burner inlet + eta_t = 0.98 //Efficiency at burner exit + eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance + FHV = 22000000 //Fuel heat of burning (joules?) + TIT = 1193 //Combustion peak temp + TAB = 1439 //Afterburner temp? + maxT3 = 800 //Turbine max temperature + exhaustMixer = False + adjustableNozzle = True + thrustUpperLimit = 60 + + // Engine fitting params + defaultTPR = 0.95 + dryThrust = 29.4 + wetThrust = 36.8 + maxThrust = 36.8 //Just to let MEC know thrust + drySFC = 0.985 + throttleResponseMultiplier = 0.60 //variable stators and modern engine control system installed? + + PROPELLANT + { + name = Kerosene + ratio = 1.0 + DrawGauge = True + } + } + CONFIG + { + name = WP-6Z + description = Afterburning RD-9 derivative, as used on the J-12I. Temperature Mach limit at 15 km: 2.36. + specLevel = operational + massMult = 1.0791 + + Area = 0.14 //Compressor Area + BPR = 0.0 //Bypass Ratio + CPR = 7.44 //Compressor Pressure Ratio + FPR = 0.0 //Fan Ratio + Mdes = 0.8 //Mach Design Point + Tdes = 270 //Temp Design Point + eta_c = 0.95 //Efficiency at burner inlet + eta_t = 0.98 //Efficiency at burner exit + eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance + FHV = 22000000 //Fuel heat of burning (joules?) + TIT = 1193 //Combustion peak temp + TAB = 2412 //Afterburner temp? + maxT3 = 700 //Turbine max temperature + exhaustMixer = False + adjustableNozzle = True + thrustUpperLimit = 70 + + // Engine fitting params + defaultTPR = 0.95 + dryThrust = 24.5 + wetThrust = 39.7 + maxThrust = 39.7 //Just to let MEC know thrust + drySFC = 1.02 + throttleResponseMultiplier = 0.60 //variable stators and modern engine control system installed? + PROPELLANT { name = Kerosene diff --git a/GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/WS10_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/WS10_Config.cfg new file mode 100644 index 0000000000..6f9a21cec0 --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/WS10_Config.cfg @@ -0,0 +1,253 @@ +// ================================================== +// Engine: WS-10 +// +// Manufacturer: Aero Engine Corporation of China +// +// ================================================================================= +// WS-10A +// 2004, J-11B +// +// Dry Mass: 1794 kg +// Thrust (Dry): 89.17 kN +// Thrust (Wet): 132 kN +// SFC (Dry): 0.695 lb/lbf-hr +// Area: 0.3 m^2 //Compressor Area +// BPR: 0.78 //Bypass Ratio +// CPR: 30.5? //Compressor Pressure Ratio +// FPR: 3.4 //Fan Ratio +// Mdes: 0.8 M //Mach Design Point +// Tdes: 250 K //Temp Design Point +// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance +// FHV: 32000000 J //Fuel heat of burning +// TIT: 1747 K //Combustion peak temp +// TAB: 1929* K //Afterburner peak temp +// maxT3: 1000 K //Turbine max temperature +// Exhaust Mixer: true +// Adjustable Nozzle: true +// ================================================================================= +// WS-10B +// 2008, J-10C +// Slightly enlarged fan for more thrust? Repackaged for same external dimensions +// +// Dry Mass: 1794? kg +// Thrust (Dry): 99.87? kN +// Thrust (Wet): 144 kN +// SFC (Dry): 0.695 lb/lbf-hr +// Area: 0.31 m^2 //Compressor Area +// BPR: 0.87? //Bypass Ratio +// CPR: 30.5? //Compressor Pressure Ratio +// FPR: 3.4 //Fan Ratio +// Mdes: 0.8 M //Mach Design Point +// Tdes: 250 K //Temp Design Point +// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance +// FHV: 32000000 J //Fuel heat of burning +// TIT: 1747 K //Combustion peak temp +// TAB: 1770* K //Afterburner peak temp +// maxT3: 1100 K //Turbine max temperature +// Exhaust Mixer: true +// Adjustable Nozzle: true +// ================================================================================= +// WS-10B-III +// 2018, J-10B (TVC demonstrator), J-20? +// TVC version +// +// Dry Mass: 1844? kg 50 kg for TVC? +// Thrust (Dry): 99.87? kN +// Thrust (Wet): 144 kN +// SFC (Dry): 0.695 lb/lbf-hr +// Area: 0.31 m^2 //Compressor Area +// BPR: 0.87? //Bypass Ratio +// CPR: 30.5? //Compressor Pressure Ratio +// FPR: 3.4 //Fan Ratio +// Mdes: 0.8 M //Mach Design Point +// Tdes: 250 K //Temp Design Point +// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance +// FHV: 32000000 J //Fuel heat of burning +// TIT: 1747 K //Combustion peak temp +// TAB: 1770* K //Afterburner peak temp +// maxT3: 1100 K //Turbine max temperature +// Exhaust Mixer: true +// Adjustable Nozzle: true +// ================================================================================= + +// Sources: + +// http://www.leteckemotory.cz/motory/chinese-engines/ +// https://www.jet-engine.net/miltfspec.htm +// https://zh.wikipedia.org/wiki/%E6%B6%A1%E6%89%87-10#%E7%9B%B8%E9%97%9C%E9%96%8B%E7%99%BC +// https://zh.wikipedia.org/wiki/%E6%B6%A1%E6%89%87-15 +// https://en.wikipedia.org/wiki/Shenyang_WS-10#Specifications_(WS-10A) +// https://dictionary.sensagent.com/Shenyang%20WS-10/en-en/ +// https://baike.baidu.com/item/%E5%A4%AA%E8%A1%8C%E5%8F%91%E5%8A%A8%E6%9C%BA/3961947 +// https://zhuanlan.zhihu.com/p/563422250 + +// Used by: + +// Notes: + +// ================================================== +@PART[*]:HAS[#engineType[WS10]]:FOR[RealismOverhaulEngines] +{ + + %title = #roWS10Title //WS-10 Low-Bypass Turbofan + %manufacturer = #roMfrAECC + %description = #roWS10Desc + + @tags ^= :$: prc china aecc aero engine corporation of china ws10 ws-10 afterburning low bypass turbofan + + %specLevel = operational //operational, prototype, concept, speculative, altHist, sciFi + + @MODULE[ModuleEngines*] + { + @name = ModuleEnginesAJEJet + %EngineType = Turbine + @PROPELLANT[LiquidFuel] + { + @name = Kerosene + } + } + + @MODULE[ModuleGimbal] + { + @gimbalRange = 15 //? + @gimbalResponseSpeed = 60 //60 degree/s? + @useGimbalResponseSpeed = true + } + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEnginesAJEJet + configuration = WS-10A + modded = false + origMass = 1.794 + + CONFIG + { + name = WS-10A + description = WS-10, as used on the J-10B, J-11B, J-15 and J-16. Temperature Mach limit at 15 km: 2.64. + specLevel = operational + massMult = 1.00 + + Area = 0.30 //Compressor Area + BPR = 0.78 //Bypass Ratio + CPR = 30.5 //Compressor Pressure Ratio + FPR = 3.4 //Fan Ratio + Mdes = 0.8 //Mach Design Point + Tdes = 250 //Temp Design Point + eta_c = 0.95 //Efficiency at burner inlet + eta_t = 0.98 //Efficiency at burner exit + eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance + FHV = 32000000 //Fuel heat of burning (joules?) + TIT = 1747 //Combustion peak temp + TAB = 1929 //Afterburner temp? + maxT3 = 1000 //Turbine max temperature + exhaustMixer = True + adjustableNozzle = True + thrustUpperLimit = 260 + gimbalRange = 0 + + // Engine fitting params + defaultTPR = 0.85 + dryThrust = 89.17 + wetThrust = 132 + maxThrust = 132 //Just to let MEC know thrust + drySFC = 0.695 + throttleResponseMultiplier = 0.8 + + PROPELLANT + { + name = Kerosene + ratio = 1.0 + DrawGauge = True + } + } + CONFIG + { + name = WS-10B + description = WS-10B, as used on the J-10C and J-20 prototypes. Temperature Mach limit at 15 km: 3.1. + specLevel = operational + massMult = 1.0 + + Area = 0.31 //Compressor Area + BPR = 0.87 //Bypass Ratio + CPR = 30.5 //Compressor Pressure Ratio + FPR = 3.4 //Fan Ratio + Mdes = 0.8 //Mach Design Point + Tdes = 250 //Temp Design Point + eta_c = 0.95 //Efficiency at burner inlet + eta_t = 0.98 //Efficiency at burner exit + eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance + FHV = 32000000 //Fuel heat of burning (joules?) + TIT = 1747 //Combustion peak temp + TAB = 1770 //Afterburner temp? + maxT3 = 1100 //Turbine max temperature + exhaustMixer = True + adjustableNozzle = True + thrustUpperLimit = 240 + gimbalRange = 0 + + // Engine fitting params + defaultTPR = 0.85 + dryThrust = 99.87 + wetThrust = 144 + maxThrust = 144 //Just to let MEC know thrust + drySFC = 0.695 + throttleResponseMultiplier = 0.90 + + PROPELLANT + { + name = Kerosene + ratio = 1.0 + DrawGauge = True + } + } + CONFIG + { + name = WS-10B-III + description = WS-10B with thrust vectoring, as used on a J-10B demonstrator and some J-20 variants. Temperature Mach limit at 15 km: 3.1. + specLevel = operational + massMult = 1.0279 + + Area = 0.31 //Compressor Area + BPR = 0.87 //Bypass Ratio + CPR = 30.5 //Compressor Pressure Ratio + FPR = 3.4 //Fan Ratio + Mdes = 0.8 //Mach Design Point + Tdes = 250 //Temp Design Point + eta_c = 0.95 //Efficiency at burner inlet + eta_t = 0.98 //Efficiency at burner exit + eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance + FHV = 32000000 //Fuel heat of burning (joules?) + TIT = 1747 //Combustion peak temp + TAB = 1770 //Afterburner temp? + maxT3 = 1100 //Turbine max temperature + exhaustMixer = True + adjustableNozzle = True + thrustUpperLimit = 240 + gimbalRange = 10 //??? + + // Engine fitting params + defaultTPR = 0.85 + dryThrust = 99.87 + wetThrust = 144 + maxThrust = 144 //Just to let MEC know thrust + drySFC = 0.695 + throttleResponseMultiplier = 0.90 + + PROPELLANT + { + name = Kerosene + ratio = 1.0 + DrawGauge = True + } + } + } +} + ++PART[aje_al31]:BEFORE[RealismOverhaulEngines] +{ + @name = RO-WS10 + @engineType = WS10 +} + diff --git a/GameData/RealismOverhaul/Engine_Configs/YF100_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/YF100_Config.cfg new file mode 100644 index 0000000000..710c7923f8 --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/YF100_Config.cfg @@ -0,0 +1,159 @@ +// ================================================== +// YF-100 +// +// Manufacturer : AALPT +// +// ================================================================================= +// YF-100 +// Long March 5, 6, 7, 8 +// +// Dry Mass: 1900 kg from kerwis +// Thrust (SL): ??? kN +// Thrust(Vac): 1340 kN +// ISP: 299.9 SL / 335 Vac +// Burn Time: 173? +// Chamber Pressure: 18.0 MPa +// Propellant: LOX / RP-1 +// Prop Ratio: 2.6 +// Throttle: 105%-65% +// Nozzle Ratio: 35 +// Ignitions: 1 +// ================================================================================= +// YF-100K +// Long March 10? +// +// Dry Mass: 1900 kg from kerwis +// Thrust (SL): ??? kN +// Thrust(Vac): 1397 kN +// ISP: 301.5 SL / 337 Vac +// Burn Time: 173? +// Chamber Pressure: 18.0? MPa +// Propellant: LOX / RP-1 +// Prop Ratio: 2.6? +// Throttle: 105%-65% +// Nozzle Ratio: 35? +// Ignitions: 1 +// ================================================================================= + +// Sources: + +// https://en.wikipedia.org/wiki/YF-100 +// https://web.archive.org/web/20160304055915/http://www.shenkong.net/Explore/1410/ZGXYDYYMYFDJ3-YF100-115ZYTX26045110.htm +// https://en.wikipedia.org/wiki/Long_March_10 + +// Used by: + +// Notes: + +// ================================================== +@PART[*]:HAS[#engineType[YF100]]:FOR[RealismOverhaulEngines] +{ + %title = #roYF100Title //YF-100 + %manufacturer = #roMfrAALPT + %description = #roYF100Desc + + @tags ^= :$: prc china aalpt yf100 yf-100 liquid pump booster kerosene lqdoxygen + + %specLevel = operational + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + @MODULE[ModuleGimbal] + { + %gimbalRange = 5 + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + origMass = 1.9 + modded = false + configuration = YF-100 + CONFIG + { + name = YF-100 + specLevel = operational + minThrust = 829.2 + maxThrust = 1340.5 + heatProduction = 100 + PROPELLANT + { + name = RP-1 + ratio = 0.3522 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.6478 + } + atmosphereCurve + { + key = 0 335 + key = 1 299.9 + } + + //Long March 5: 10 flights, 0 failures + //Long March 6: 11 flights, 0 failures + //Long March 7: 13 flights, 1 failures (1 cycle?) + //Long March 8: 2 flights, 0 failures? + //122 engines, 1 failure + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 2200 //Same as RD-120 + ratedBurnTime = 173 + safeOverburn = true + ignitionReliabilityStart = 0.981978 + ignitionReliabilityEnd = 0.997154 + cycleReliabilityStart = 0.981978 + cycleReliabilityEnd = 0.997154 + } + } + CONFIG + { + name = YF-100K + specLevel = prototype //??? + minThrust = 829.2 + maxThrust = 1397.0 + heatProduction = 100 + PROPELLANT + { + name = RP-1 + ratio = 0.3522 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.6478 + } + atmosphereCurve + { + key = 0 337 + key = 1 301.5 + } + + //Same as YF-100 + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 4400 + ratedBurnTime = 173 + safeOverburn = true + ignitionReliabilityStart = 0.981978 + ignitionReliabilityEnd = 0.997154 + cycleReliabilityStart = 0.981978 + cycleReliabilityEnd = 0.997154 + } + } + } +} diff --git a/GameData/RealismOverhaul/Engine_Configs/YF1_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/YF1_Config.cfg new file mode 100644 index 0000000000..b233a992e8 --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/YF1_Config.cfg @@ -0,0 +1,255 @@ +// ================================================== +// YF-1 +// +// Manufacturer: AALPT +// +// ================================================================================= +// YF-1 +// DF-3-01 +// +// Dry Mass: 295 kg from kerwis +// Thrust (SL): ??? kN +// Thrust (Vac): 261.63 kN +// ISP: 235 SL / 259.8 Vac +// Burn Time: 140 +// Chamber Pressure: 6.57 MPa [B] +// Propellant: AK27 / UDMH +// Prop Ratio: 2.46 [B] +// Nozzle Ratio: 10:1 +// Ignitions: 1 +// ================================================================================= +// YF-1A +// DF-3-02, DF-4, CZ-1 +// +// Dry Mass: 295 kg from kerwis +// Thrust (SL): ??? kN +// Thrust (Vac): 282.93 kN +// ISP: 239 SL / 265.6 Vac +// Burn Time: 140 +// Chamber Pressure: 6.57 MPa [B] +// Propellant: AK27 / UDMH +// Prop Ratio: 2.46 [B] +// Nozzle Ratio: 10:1 +// Ignitions: 1 +// ================================================================================= +// YF-1B +// DF-3A, DF-4A, CZ-1D +// +// Dry Mass: 295 kg from kerwis +// Thrust (SL): ??? kN +// Thrust (Vac): 303.6 kN +// ISP: 242 SL / 267.2 Vac +// Burn Time: 131.5 +// Chamber Pressure: 6.57 MPa [B] +// Propellant: NTO / UDMH +// Prop Ratio: 2.299? same volume ratio? +// Nozzle Ratio: 10:1 +// Ignitions: 1 +// ================================================================================= + +// Sources: + +// [1] http://lpre.de/kbhm/index.htm +// [2] https://web.archive.org/web/20151017052030/http://www.b14643.de/Spacerockets/Diverse/DF-3/index.htm +// [3] https://www.b14643.de/Spacerockets_1/China/CZ-1/Propulsion/engines.htm +// [4] https://web.archive.org/web/20150717192824/http://www.b14643.de/Spacerockets/Diverse/Asian_Rocket_engines/engines.htm +// [5] https://web.archive.org/web/20151123104048/http://sinodefence.com/rocketry/df3/ +// [6] http://www.astronautix.com/d/df-3.html +// [7] https://web.archive.org/web/20120801025217/http://www.5school.com/wap.aspx?nid=12900&p=2&cid=100&sp=87 +// [A] History of Liquid Propellant Rocket Engines +// [B] 世界导弹与航天发动机大全 + +// Used by: + +// Notes: +// Four YF-1 units comprise YF-2. Thrust vanes used for TVC. +// ================================================== +@PART[*]:HAS[#engineType[YF1]]:FOR[RealismOverhaulEngines] +{ + %title = #roYF1Title //YF-1 + %manufacturer = #roMfrAALPT + %description = #roYF1Desc + + @tags ^= :$: prc china aalpt yf1 yf-1 yf2 yf-2 liquid pump booster udmh nitric acid nto + + %specLevel = operational + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + @MODULE[ModuleGimbal] + { + %gimbalRange = 4 //thrust vanes + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = YF-1 + origMass = 0.295 + modded = false + CONFIG + { + name = YF-1 + description = Early YF-1, used on DF-3 Batch 01. + specLevel = operational + minThrust = 261.63 + maxThrust = 261.63 + massMult = 1.0 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4407 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.5593 + } + atmosphereCurve + { + key = 0 259.8 + key = 1 235 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //DF-3 Batch 01: 4 flights, 2 failures (3 cycle, 0 ignition) + //16 engines, 3 failed + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 195 //[2] 195 seconds life + ratedBurnTime = 140 + safeOverburn = true + ignitionReliabilityStart = 0.750000 + ignitionReliabilityEnd = 0.955882 + cycleReliabilityStart = 0.750000 + cycleReliabilityEnd = 0.955882 + //techTransfer = RD-214-8D59:25 //related to RD-211? + } + } + CONFIG + { + name = YF-1A + description = Used on DF-3 Batch 02, DF-4, and CZ-1. + specLevel = operational + minThrust = 282.93 + maxThrust = 282.93 + massMult = 1.0 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4407 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.5593 + } + atmosphereCurve + { + key = 0 265.6 + key = 1 239 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //DF-3 Batch 02: 8 flights, 0 failures (0 cycle, 0 ignition) + //DF-4: 13 flights, 0 failures + //CZ-1: 3 flights, 0 failures (1 unrelated) + //96 engines, 0 failed + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 500 //[2] 500 seconds life + ratedBurnTime = 140 + safeOverburn = true + ignitionReliabilityStart = 0.990206 + ignitionReliabilityEnd = 0.998454 + cycleReliabilityStart = 0.990206 + cycleReliabilityEnd = 0.998454 + techTransfer = YF-3,YF-1:50 + } + } + CONFIG + { + name = YF-1B + description = Used on DF-3A, DF-4A, and CZ-1D. + specLevel = operational + minThrust = 303.6 + maxThrust = 303.6 + massMult = 1.0 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4407 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5593 + } + atmosphereCurve + { + key = 0 267.2 + key = 1 242 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //DF-3A: 2 flights, 0 failures + //DF-4A: 4 flights, 0 failures? (1 unrelated) + //CZ-1D: 2 flights, 0 failures + //32 engines, 0 failed + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 500 //[2] 500 seconds life + ratedBurnTime = 132 + safeOverburn = true + ignitionReliabilityStart = 0.971212 + ignitionReliabilityEnd = 0.995455 + cycleReliabilityStart = 0.971212 + cycleReliabilityEnd = 0.995455 + techTransfer = YF-3A,YF-1A,YF-3,YF-1:50 + } + } + } +} diff --git a/GameData/RealismOverhaul/Engine_Configs/YF20_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/YF20_Config.cfg new file mode 100644 index 0000000000..622e1d36eb --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/YF20_Config.cfg @@ -0,0 +1,334 @@ +// ================================================== +// YF-20 +// +// Manufacturer: AALPT +// +// ================================================================================= +// YF-20 +// FB-1, DF-5, CZ-2A +// +// Dry Mass: 737.5 kg [B] +// Thrust (SL): 696.2 kN [4/B] +// Thrust (Vac): 778.2 kN [4/B] +// ISP: 259 SL / 289.5 Vac [B] +// Burn Time: 130? +// Chamber Pressure: 6.98 MPa [B] +// Propellant: NTO / UDMH +// Prop Ratio: 2.10 [3/B] +// Nozzle Ratio: 12.69:1 [A/B] +// Ignitions: 1 +// ================================================================================= +// YF-20B +// DF-5A, CZ-2C +// +// Dry Mass: 737.5 kg [B] +// Thrust (SL): 740.4 kN [3/4] +// Thrust (Vac): 822.2 kN +// ISP: 260.7 SL / 289.5? Vac [4] +// Burn Time: 132 +// Chamber Pressure: 7.96? MPa [B] +// Propellant: NTO / UDMH +// Prop Ratio: 2.12 [3] +// Nozzle Ratio: 12.69:1 [A] +// Ignitions: 1 +// ================================================================================= +// YF-20C +// CZ-2C/D/E/F, CZ-3A/B/C/E, CZ-4 +// +// Dry Mass: 737.5 kg [B] +// Thrust (SL): 756.1 kN from kerwis +// Thrust (Vac): 839.6 kN +// ISP: 260.7? SL / 280.8 Vac [3] +// Burn Time: 159 +// Chamber Pressure: 7.96? MPa +// Propellant: NTO / UDMH +// Prop Ratio: 2.12 [3] +// Nozzle Ratio: 12.69:1 [A] +// Ignitions: 1 +// ================================================================================= +// YF-25K +// CZ-2E/F, CZ-3B/C/E (strap-on, no gimbal) +// +// Dry Mass: 673? kg no gimbal? +// Thrust (SL): ??? kN +// Thrust (Vac): 839.6? kN +// ISP: 260.7? SL / 280.8 Vac [3] +// Burn Time: 126 +// Chamber Pressure: 7.96? MPa +// Propellant: NTO / UDMH +// Prop Ratio: 2.12 [3] +// Nozzle Ratio: 12.69:1? +// Ignitions: 1 +// ================================================================================= + +// Sources: + +// [1] http://lpre.de/kbhm/index.htm +// [2] https://web.archive.org/web/20170621135027/http://www.b14643.de/Spacerockets_1/China/CZ-2/Description/Frame.htm +// [3] https://web.archive.org/web/20150717192824/http://www.b14643.de/Spacerockets/Diverse/Asian_Rocket_engines/engines.htm +// [4] http://www.braeunig.us/space/specs/lgmarch.htm +// [5] https://www.globalsecurity.org/space/world/china/cz-2e.htm +// [6] http://www.globalsecurity.org/space/library/report/1999/lm3bchapter2.pdf +// [7] http://www.globalsecurity.org/space/library/report/1999/lm2echapter2.pdf +// [A] History of Liquid Propellant Rocket Engines +// [B] 世界导弹与航天发动机大全 + +// Used by: + +// Notes: +// Four YF-20 units comprise YF-21. Single-axis gimbal? No gimbal on strap-on version. +// ================================================== +@PART[*]:HAS[#engineType[YF20]]:FOR[RealismOverhaulEngines] +{ + %title = #roYF20Title //YF-20 + %manufacturer = #roMfrAALPT + %description = #roYF20Desc + + @tags ^= :$: prc china aalpt yf20 yf-20 yf21 yf-21 liquid pump booster udmh nto + + %specLevel = operational + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + @MODULE[ModuleGimbal] + { + %gimbalRange = 10 + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = YF-20 + origMass = 0.7375 + modded = false + CONFIG + { + name = YF-20 + description = YF-20, used on FB-1, DF-5 and CZ-2A. + specLevel = operational + minThrust = 778.2 + maxThrust = 778.2 + massMult = 1.0 + gimbalRange = 10 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4631 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5369 + } + atmosphereCurve + { + key = 0 289.5 + key = 1 259 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //DF-5: 16 flights, 0 failures? + //FB-1: 11 flights, 1 failure? (1 cycle) + //CZ-2A: 4 flights, 1 failure (1 unrelated) + //124 engines, 1 failure + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 500 + ratedBurnTime = 130 + safeOverburn = true + ignitionReliabilityStart = 0.982267 + ignitionReliabilityEnd = 0.997200 + cycleReliabilityStart = 0.982267 + cycleReliabilityEnd = 0.997200 + techTransfer = YF-22,YF-1B,YF-3A,YF-1A,YF-3,YF-1:50 //related to YF-1? + } + } + CONFIG + { + name = YF-20B + description = Used on DF-5A and early CZ-2C. + specLevel = operational + minThrust = 822.2 + maxThrust = 822.2 + massMult = 1.0 + gimbalRange = 10 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4608 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5392 + } + atmosphereCurve + { + key = 0 289.5 + key = 1 260.7 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //DF-5A: 5 flights, 0 failures + //CZ-2C (early): 11 flights, 0 failures? + //64 engines, 0 failed + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 500 + ratedBurnTime = 132 + safeOverburn = true + ignitionReliabilityStart = 0.985385 + ignitionReliabilityEnd = 0.997692 + cycleReliabilityStart = 0.985385 + cycleReliabilityEnd = 0.997692 + techTransfer = YF-22B,YF-20,YF-22,YF-1B,YF-3A,YF-1A,YF-3,YF-1:50 + } + } + CONFIG + { + name = YF-20C + description = Used on CZ-2C/D/E/F, CZ-3B and CZ-4. + specLevel = operational + minThrust = 839.6 + maxThrust = 839.6 + massMult = 1.0 + gimbalRange = 10 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4608 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5392 + } + atmosphereCurve + { + key = 0 289.5 + key = 1 260.7 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //CZ-2C: 63 flights, 0 failures + //CZ-2D: 85 flights, 0 failures + //CZ-2E: 7 flights, 1 failures (1 unrelated) + //CZ-2F: 21 flights, 0 failures + //CZ-3: 13 flights, 0 failures + //CZ-3A: 27 flights, 0 failures + //CZ-3B: 93 flights, 1 failures (1 unrelated) + //CZ-3C: 18 flights, 0 failures + //CZ-4A: 2 flights, 0 failures + //CZ-4B: 48 flights, 0 failures + //1508 engines, 0 failed + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 500 + ratedBurnTime = 159 + safeOverburn = true + ignitionReliabilityStart = 0.999370 + ignitionReliabilityEnd = 0.999901 + cycleReliabilityStart = 0.999370 + cycleReliabilityEnd = 0.999901 + techTransfer = YF-25K,YF-22C,YF-20B,YF-22B,YF-20,YF-22,YF-1B,YF-3A,YF-1A,YF-3,YF-1:50 + } + } + CONFIG + { + name = YF-25K + description = Used on CZ-3B strap-on boosters. No gimbal. + specLevel = operational + minThrust = 839.6 + maxThrust = 839.6 + massMult = 0.9123 + gimbalRange = 0 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4608 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5392 + } + atmosphereCurve + { + key = 0 289.5 + key = 1 260.7 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //CZ-2E: 7 flights, 1 failures (1 unrelated) + //CZ-2F: 21 flights, 0 failures + //CZ-3B: 93 flights, 1 failures (1 unrelated) + //CZ-3C: 18 flights, 0 failures + //520 engines, 0 failed + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 500 + ratedBurnTime = 126 + safeOverburn = true + ignitionReliabilityStart = 0.998177 + ignitionReliabilityEnd = 0.999712 + cycleReliabilityStart = 0.998177 + cycleReliabilityEnd = 0.999712 + techTransfer = YF-20C,YF-22C,YF-20B,YF-22B,YF-20,YF-22,YF-1B,YF-3A,YF-1A,YF-3,YF-1:50 + } + } + } +} diff --git a/GameData/RealismOverhaul/Engine_Configs/YF22_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/YF22_Config.cfg new file mode 100644 index 0000000000..0fbcaf6f0d --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/YF22_Config.cfg @@ -0,0 +1,263 @@ +// ================================================== +// YF-22 +// +// Manufacturer: AALPT +// +// ================================================================================= +// YF-22 +// FB-1, DF-5, CZ-2A +// +// Dry Mass: 800 kg from kerwis +// Thrust (SL): ??? kN +// Thrust (Vac): 719.8 kN [B] +// ISP: 254 SL / 288.9 Vac [B] +// Burn Time: 110? +// Chamber Pressure: 6.52 MPa [B] +// Propellant: NTO / UDMH +// Prop Ratio: 2.18 [B] +// Nozzle Ratio: 12.69:1 [B] +// Ignitions: 1 +// ================================================================================= +// YF-22B +// DF-5A, CZ-2C +// +// Dry Mass: 800 kg +// Thrust (SL): ??? kN +// Thrust (Vac): 742.2 kN [3] +// ISP: 237 SL / 298 Vac [4] +// Burn Time: 115 +// Chamber Pressure: 6.52? MPa +// Propellant: NTO / UDMH +// Prop Ratio: 2.18? +// Nozzle Ratio: 22? +// Ignitions: 1 +// ================================================================================= +// YF-22E +// CZ-2C/D/E/F, CZ-3B, CZ-4 +// +// Dry Mass: 824 kg larger nozzle? +// Thrust (SL): ??? kN +// Thrust (Vac): 784.5 kN [3] +// ISP: 220? SL / 303 Vac [3] +// Burn Time: 300 +// Chamber Pressure: 6.52? MPa +// Propellant: NTO / UDMH +// Prop Ratio: 2.18 [3] +// Nozzle Ratio: 31? later YF-22s have larger nozzle +// Ignitions: 1 +// ================================================================================= + +// Sources: + +// [1] http://lpre.de/kbhm/index.htm +// [2] https://web.archive.org/web/20170621135027/http://www.b14643.de/Spacerockets_1/China/CZ-2/Description/Frame.htm +// [3] https://web.archive.org/web/20150717192824/http://www.b14643.de/Spacerockets/Diverse/Asian_Rocket_engines/engines.htm +// [4] http://www.braeunig.us/space/specs/lgmarch.htm +// [5] https://www.globalsecurity.org/space/world/china/cz-2e.htm +// [6] http://www.globalsecurity.org/space/library/report/1999/lm3bchapter2.pdf +// [7] http://www.globalsecurity.org/space/library/report/1999/lm2echapter2.pdf +// [A] History of Liquid Propellant Rocket Engines +// [B] 世界导弹与航天发动机大全 + +// Used by: + +// Notes: +// YF-22 main engine and YF-23 vernier comprise YF-24 engine unit +// ================================================== +@PART[*]:HAS[#engineType[YF22]]:FOR[RealismOverhaulEngines] +{ + %title = #roYF22Title //YF-22 + %manufacturer = #roMfrAALPT + %description = #roYF22Desc + + @tags ^= :$: prc china aalpt yf22 yf-22 yf23 yf-23 yf24 yf-24 liquid pump upper udmh nto + + %specLevel = operational + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + !MODULE[ModuleGimbal],*{} + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = YF-22 + origMass = 0.80 + modded = false + CONFIG + { + name = YF-22 + description = YF-22, used on FB-1, DF-5 and CZ-2A. + specLevel = operational + minThrust = 719.8 + maxThrust = 719.8 + massMult = 1.0 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4539 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5461 + } + atmosphereCurve + { + key = 0 288.9 + key = 1 254 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //Also counting YF-23 + //DF-5: 16 flights, 0 failures? + //FB-1: 10 flights, 3 failures (3 cycle?) + //CZ-2A: 3 flights, 0 failures + //58 ignitions, 0 failures + //58 cycles, 3 failures + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 500 + ratedBurnTime = 110 + safeOverburn = true + ignitionReliabilityStart = 0.983898 + ignitionReliabilityEnd = 0.997458 + cycleReliabilityStart = 0.919492 + cycleReliabilityEnd = 0.987288 + techTransfer = YF-20,YF-1B,YF-3A,YF-1A,YF-3,YF-1:50 //related to YF-1? + } + } + CONFIG + { + name = YF-22B + description = Used on DF-5A and early CZ-2C. + specLevel = operational + minThrust = 742.2 + maxThrust = 742.2 + massMult = 1.00 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4539 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5461 + } + atmosphereCurve + { + key = 0 298 + key = 1 237 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //Also counting YF-23 + //DF-5A: 5 flights, 0 failures + //CZ-2C (early): 11 flights, 0 failures? + //32 ignitions, 0 failures + //32 cycles, 0 failures + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 500 + ratedBurnTime = 115 + safeOverburn = true + ignitionReliabilityStart = 0.971212 + ignitionReliabilityEnd = 0.995455 + cycleReliabilityStart = 0.971212 + cycleReliabilityEnd = 0.995455 + techTransfer = YF-20B,YF-22,YF-20,YF-1B,YF-3A,YF-1A,YF-3,YF-1:50 + } + } + CONFIG + { + name = YF-22E + description = Used on CZ-2D/E/F, CZ-3B and CZ-4. + specLevel = operational + minThrust = 784.5 + maxThrust = 784.5 + massMult = 1.03 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4539 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5461 + } + atmosphereCurve + { + key = 0 298 + key = 1 213 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //CZ-2C: 63 flights, 1 failures (1 cycle) + //CZ-2D: 85 flights, 0 failures + //CZ-2E: 6 flights, 0 failures + //CZ-2F: 21 flights, 0 failures + //CZ-3: 13 flights, 0 failures + //CZ-3A: 27 flights, 0 failures + //CZ-3B: 92 flights, 0 failures + //CZ-3C: 18 flights, 0 failures + //CZ-4A: 2 flights, 0 failures + //CZ-4B: 48 flights, 0 failures + //754 ignitions, 0 failures + //754 cycles, 1 failures + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 500 + ratedBurnTime = 300 + safeOverburn = true + ignitionReliabilityStart = 0.998742 + ignitionReliabilityEnd = 0.999801 + cycleReliabilityStart = 0.997064 + cycleReliabilityEnd = 0.999536 + techTransfer = YF-20C,YF-25K,YF-22B,YF-20B,YF-22,YF-20,YF-1B,YF-3A,YF-1A,YF-3,YF-1:50 + } + } + } +} diff --git a/GameData/RealismOverhaul/Engine_Configs/YF23_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/YF23_Config.cfg new file mode 100644 index 0000000000..16a42d5426 --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/YF23_Config.cfg @@ -0,0 +1,186 @@ +// ================================================== +// YF-23 +// +// Manufacturer: AALPT +// +// ================================================================================= +// YF-23 +// FB-1, DF-5, CZ-2A +// +// Dry Mass: 75 kg [B] +// Thrust (SL): ??? kN +// Thrust (Vac): 46.1 kN [B] +// ISP: 181 SL / 279.5 Vac [B] +// Burn Time: 300 +// Chamber Pressure: 3.29 MPa [B] +// Propellant: NTO / UDMH +// Prop Ratio: 1.57 [B] +// Nozzle Ratio: 24.21:1 [A/B] +// Ignitions: 1 +// ================================================================================= +// YF-23B +// DF-5A, CZ-2C/D/E/F, CZ-3B, CZ-4 +// +// Dry Mass: 75 kg [B] +// Thrust (SL): ??? kN +// Thrust (Vac): 47.2 kN [3] +// ISP: 198 SL / 296.8 Vac [3] +// Burn Time: 715 +// Chamber Pressure: 3.29? MPa +// Propellant: NTO / UDMH +// Prop Ratio: 1.57 [3] +// Nozzle Ratio: 24.21:1? +// Ignitions: 1 +// ================================================================================= + +// Sources: + +// [1] http://lpre.de/kbhm/index.htm +// [2] https://web.archive.org/web/20170621135027/http://www.b14643.de/Spacerockets_1/China/CZ-2/Description/Frame.htm +// [3] https://web.archive.org/web/20150717192824/http://www.b14643.de/Spacerockets/Diverse/Asian_Rocket_engines/engines.htm +// [4] http://www.braeunig.us/space/specs/lgmarch.htm +// [5] https://www.globalsecurity.org/space/world/china/cz-2e.htm +// [6] http://www.globalsecurity.org/space/library/report/1999/lm3bchapter2.pdf +// [7] http://www.globalsecurity.org/space/library/report/1999/lm2echapter2.pdf +// [A] History of Liquid Propellant Rocket Engines +// [B] 世界导弹与航天发动机大全 + +// Used by: + +// Notes: +// YF-22 main engine and YF-23 vernier comprise YF-24 engine unit +// This config represents all 4 chambers, set engineTypeMult to 0.25 to get a single chamber +// ================================================== +@PART[*]:HAS[#engineType[YF23]]:FOR[RealismOverhaulEngines] +{ + %title = #roYF23Title //YF-23 + %manufacturer = #roMfrAALPT + %description = #roYF23Desc + + @tags ^= :$: prc china aalpt yf22 yf-22 yf23 yf-23 yf24 yf-24 liquid pump upper udmh nto + + %specLevel = operational + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + @MODULE[ModuleGimbal] + { + %gimbalRange = 60 + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = YF-23 + origMass = 0.075 + modded = false + CONFIG + { + name = YF-23 + description = YF-23, used on FB-1, DF-5 and CZ-2A. + specLevel = operational + minThrust = 46.1 + maxThrust = 46.1 + massMult = 1.0 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.5357 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.4643 + } + atmosphereCurve + { + key = 0 279.5 + key = 1 181 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //Same as YF-22 + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 900 + ratedBurnTime = 300 + safeOverburn = true + ignitionReliabilityStart = 0.983898 + ignitionReliabilityEnd = 0.997458 + cycleReliabilityStart = 0.919492 + cycleReliabilityEnd = 0.987288 + techTransfer = YF-22:50 //related to YF-1? + } + } + CONFIG + { + name = YF-23B + description = Used on DF-5A CZ-2C/D/E/F, CZ-3B, and CZ-4. + specLevel = operational + minThrust = 47.2 + maxThrust = 47.2 + massMult = 1.00 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.5357 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.4643 + } + atmosphereCurve + { + key = 0 296.8 + key = 1 198 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //Same as YF-22E + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 1400 + ratedBurnTime = 715 + safeOverburn = true + ignitionReliabilityStart = 0.998742 + ignitionReliabilityEnd = 0.999801 + cycleReliabilityStart = 0.997064 + cycleReliabilityEnd = 0.999536 + techTransfer = YF-23,YF-22E,YF-22B,YF-22:50 + } + } + } +} diff --git a/GameData/RealismOverhaul/Engine_Configs/YF3_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/YF3_Config.cfg new file mode 100644 index 0000000000..9ea73391f0 --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/YF3_Config.cfg @@ -0,0 +1,191 @@ +// ================================================== +// YF-3 +// +// Manufacturer: AALPT +// +// ================================================================================= +// YF-3 +// CZ-1, DF-4 +// +// Dry Mass: 350 kg from kerwis +// Thrust (SL): ??? kN +// Thrust (Vac): 294.2 kN +// ISP: 217 SL / 280 Vac +// Burn Time: 116 +// Chamber Pressure: 6.31 MPa [B] +// Propellant: AK27 / UDMH +// Prop Ratio: 2.48 [B] +// Nozzle Ratio: 23? +// Ignitions: 1 +// ================================================================================= +// YF-3A +// DF-4A +// +// Dry Mass: 350 kg from kerwis +// Thrust (SL): ??? kN +// Thrust (Vac): 320.2 kN +// ISP: 221 SL / 286.9 Vac +// Burn Time: 116 +// Chamber Pressure: 6.31 MPa [B] +// Propellant: NTO / UDMH +// Prop Ratio: 2.318? same volume ratio? +// Nozzle Ratio: 23? +// Ignitions: 1 +// ================================================================================= + +// Sources: + +// [1] http://lpre.de/kbhm/index.htm +// [2] https://web.archive.org/web/20151017052030/http://www.b14643.de/Spacerockets/Diverse/DF-3/index.htm +// [3] https://www.b14643.de/Spacerockets_1/China/CZ-1/Propulsion/engines.htm +// [4] https://web.archive.org/web/20150717192824/http://www.b14643.de/Spacerockets/Diverse/Asian_Rocket_engines/engines.htm +// [5] https://web.archive.org/web/20151123104048/http://sinodefence.com/rocketry/df3/ +// [6] http://www.astronautix.com/d/df-3.html +// [7] https://web.archive.org/web/20120801025217/http://www.5school.com/wap.aspx?nid=12900&p=2&cid=100&sp=87 +// [A] History of Liquid Propellant Rocket Engines +// [B] 世界导弹与航天发动机大全 + +// Used by: + +// Notes: +// Thrust vanes used for TVC. +// ================================================== +@PART[*]:HAS[#engineType[YF3]]:FOR[RealismOverhaulEngines] +{ + %title = #roYF3Title //YF-3 + %manufacturer = #roMfrAALPT + %description = #roYF3Desc + + @tags ^= :$: prc china aalpt yf3 yf-3 liquid pump upper udmh nitric acid nto + + %specLevel = operational + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + @MODULE[ModuleGimbal] + { + %gimbalRange = 4 //thrust vanes + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = YF-3 + origMass = 0.350 + modded = false + CONFIG + { + name = YF-3 + description = Vacuum version of YF-1, used on CZ-1 and DF-4. + specLevel = operational + minThrust = 294.2 + maxThrust = 294.2 + massMult = 1.0 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4387 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.5613 + } + atmosphereCurve + { + key = 0 280 + key = 1 217 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //same as YF-3A due to small sample size + //DF-4: 13 flights, 0 failures + //CZ-1: 3 flights, 1 failures (1 unrelated) + //DF-4A: 4 flights, 0 failures? (1 unrelated) + //19 ignitions, 0 failed + //19 cycles, 0 failed + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 500 //[2] 500 seconds life + ratedBurnTime = 116 + safeOverburn = true + ignitionReliabilityStart = 0.952500 + ignitionReliabilityEnd = 0.992500 + cycleReliabilityStart = 0.952500 + cycleReliabilityEnd = 0.992500 + techTransfer = YF-1A,YF-1:50 + } + } + CONFIG + { + name = YF-3A + description = Used on DF-4A and CZ-1D. + specLevel = operational + minThrust = 320.2 + maxThrust = 320.2 + massMult = 1.0 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4387 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5613 + } + atmosphereCurve + { + key = 0 286.9 + key = 1 221 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + + //same as YF-3 + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 500 //[2] 500 seconds life + ratedBurnTime = 116 + safeOverburn = true + ignitionReliabilityStart = 0.952500 + ignitionReliabilityEnd = 0.992500 + cycleReliabilityStart = 0.952500 + cycleReliabilityEnd = 0.992500 + techTransfer = YF-1B,YF-1A,YF-1:50 + } + } + } +} diff --git a/GameData/RealismOverhaul/Engine_Configs/YF40_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/YF40_Config.cfg new file mode 100644 index 0000000000..176162496f --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/YF40_Config.cfg @@ -0,0 +1,252 @@ +// ================================================== +// YF-40 +// +// Manufacturer: AALPT +// +// ================================================================================= +// YF-40 +// CZ-1D +// +// Dry Mass: 70 kg [4] +// Thrust (SL): ??? kN +// Thrust (Vac): 49.05 kN [3] +// ISP: 200 SL / 295 Vac [3] +// Burn Time: 365 [2] +// Chamber Pressure: 4.41 MPa [B] +// Propellant: NTO / UDMH +// Prop Ratio: 2.14? [3] same as YF-40A? +// Nozzle Ratio: 30? +// Ignitions: 1? +// ================================================================================= +// YF-40A +// CZ-4A +// +// Dry Mass: 70 kg [4] +// Thrust (SL): ??? kN +// Thrust (Vac): 49.05 kN [3] +// ISP: 173 SL / 303 Vac [3] +// Burn Time: 321 [4] +// Chamber Pressure: 4.48 MPa [3] +// Propellant: NTO / UDMH +// Prop Ratio: 2.14 [3] +// Nozzle Ratio: 55 [3] +// Ignitions: 1? +// ================================================================================= +// YF-40B +// CZ-4B/C +// +// Dry Mass: 83 kg [7] +// Thrust (SL): ??? kN +// Thrust (Vac): 50.4 kN [3] +// ISP: 175 SL / 305 Vac [3] +// Burn Time: 412 [4] +// Chamber Pressure: 4.48 MPa [3] +// Propellant: NTO / UDMH +// Prop Ratio: 2.14 [3] +// Nozzle Ratio: 55 [3] +// Ignitions: 2? [4] +// ================================================================================= + +// Sources: + +// [1] http://lpre.de/kbhm/index.htm +// [2] https://www.b14643.de/Spacerockets_1/China/CZ-1/Propulsion/engines.htm +// [3] https://web.archive.org/web/20150717192824/http://www.b14643.de/Spacerockets/Diverse/Asian_Rocket_engines/engines.htm +// [4] http://www.braeunig.us/space/specs/lgmarch.htm +// [5] https://en.wikipedia.org/wiki/YF-40 +// [A] History of Liquid Propellant Rocket Engines +// [B] 世界导弹与航天发动机大全 + +// Used by: + +// Notes: + +// ================================================== +@PART[*]:HAS[#engineType[YF40]]:FOR[RealismOverhaulEngines] +{ + %title = #roYF40Title //YF-40 + %manufacturer = #roMfrAALPT + %description = #roYF40Desc + + @tags ^= :$: prc china aalpt yf40 yf-40 liquid pump upper udmh nto + + %specLevel = operational + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + @MODULE[ModuleGimbal] + { + %gimbalRange = 4.5 + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = YF-40 + origMass = 0.070 + modded = false + CONFIG + { + name = YF-40 + description = Used on CZ-1D + specLevel = operational + minThrust = 49.05 + maxThrust = 49.05 + massMult = 1.0 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4585 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5415 + } + atmosphereCurve + { + key = 0 295 + key = 1 200 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //same as YF-40B due to lack of data + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 1100 + ratedBurnTime = 365 + safeOverburn = true + ignitionReliabilityStart = 0.997159 + ignitionReliabilityEnd = 0.999432 + cycleReliabilityStart = 0.982227 + cycleReliabilityEnd = 0.996445 + } + } + CONFIG + { + name = YF-40A + description = Used on CZ-4A. + specLevel = operational + minThrust = 49.05 + maxThrust = 49.05 + massMult = 1.0 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4585 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5415 + } + atmosphereCurve + { + key = 0 303 + key = 1 173 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //same as YF-40B due to lack of data + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 1100 + ratedBurnTime = 321 + safeOverburn = true + ignitionReliabilityStart = 0.997159 + ignitionReliabilityEnd = 0.999432 + cycleReliabilityStart = 0.982227 + cycleReliabilityEnd = 0.996445 + techTransfer = YF-40:50 + } + } + CONFIG + { + name = YF-40B + description = Used on CZ-4B/C, with restart capability. + specLevel = operational + minThrust = 50.4 + maxThrust = 50.4 + massMult = 1.1857 + heatProduction = 100 + PROPELLANT + { + name = UDMH + ratio = 0.4585 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5415 + } + atmosphereCurve + { + key = 0 305 + key = 1 175 + } + + ullage = True + pressureFed = False + ignitions = 2 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + + //Using all YF-40 variants due to lack of data + //CZ-1D: 2 flights, 0 failures + //CZ-4(A): 2 flights, 0 failures + //CZ-4B: 48 flights, 1 failures (1 cycle) + //CZ-4C: 53 flights, 2 failures (1 cycle, 1 unknown) + //CZ-4C flights have 2 ignitions? + //263 ignitions, 0 failures? + //210 cycles, 3 failures? + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 1200 + ratedBurnTime = 412 + safeOverburn = true + ignitionReliabilityStart = 0.997159 + ignitionReliabilityEnd = 0.999432 + cycleReliabilityStart = 0.982227 + cycleReliabilityEnd = 0.996445 + techTransfer = YF-40A,YF-40:50 + } + } + } +} diff --git a/GameData/RealismOverhaul/Engine_Configs/YF75_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/YF75_Config.cfg new file mode 100644 index 0000000000..3a228a30c0 --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/YF75_Config.cfg @@ -0,0 +1,240 @@ +// ================================================== +// YF-75 +// +// Manufacturer: AALPT +// +// ================================================================================= +// YF-75 +// Long March 3A/B/C +// +// Dry Mass: 305.5 kg [B] +// Thrust (SL): ??? kN +// Thrust(Vac): 78.45 kN [B] +// ISP: 193? SL / 439.6 Vac [B] +// Burn Time: 481 [B] +// Chamber Pressure: 3.67 MPa [B] +// Propellant: LOX / LH2 +// Prop Ratio: 5.0 [B] +// Throttle: N/A +// Nozzle Ratio: 80 [B] +// Ignitions: 2 [B] +// ================================================================================= +// YF-75D +// Long March 5 +// +// Dry Mass: 265 kg [7] +// Thrust (SL): ??? kN +// Thrust(Vac): 88.36 kN [7] +// ISP: 211? SL / 442.6 Vac [7] +// Burn Time: 780 +// Chamber Pressure: 4.1 MPa [7] +// Propellant: LOX / LH2 +// Prop Ratio: 6.0 [7] +// Throttle: N/A +// Nozzle Ratio: 80 [7] +// Ignitions: 8 [8] tested to 8 starts +// ================================================================================= +// YF-75E +// Long March 10? +// +// Dry Mass: 305? kg 40 kg for nozzle extension? (based on RL10C-3) +// Thrust (SL): ??? kN +// Thrust(Vac): 92.11 kN [7] +// ISP: 80? SL / 451.1 Vac [7] +// Burn Time: 780? +// Chamber Pressure: 4.1 MPa [7] +// Propellant: LOX / LH2 +// Prop Ratio: 6.0 [7] +// Throttle: N/A +// Nozzle Ratio: 175 [7] +// Ignitions: 8 [8] tested to 8 starts +// ================================================================================= + +// Sources: + +// [1] http://lpre.de/kbhm/index.htm +// [2] https://web.archive.org/web/20170621153836/http://www.b14643.de/Spacerockets_1/China/CZ-3/Description/Frame.htm +// [3] https://web.archive.org/web/20150717192824/http://www.b14643.de/Spacerockets/Diverse/Asian_Rocket_engines/engines.htm +// [4] http://www.braeunig.us/space/specs/lgmarch.htm +// [5] http://www.globalsecurity.org/space/library/report/1999/lm3bchapter2.pdf +// [6] http://www.globalsecurity.org/space/library/report/1999/lm2echapter2.pdf +// [7] https://en.wikipedia.org/wiki/YF-75D +// [8] https://forum.nasaspaceflight.com/index.php?topic=8447.msg1104075#msg1104075 +// [A] History of Liquid Propellant Rocket Engines +// [B] 世界导弹与航天发动机大全 + +// Used by: + +// Notes: + +// ================================================== +@PART[*]:HAS[#engineType[YF75]]:FOR[RealismOverhaulEngines] +{ + %title = #roYF75Title //YF-75 + %manufacturer = #roMfrAALPT + %description = #roYF75Desc + + @tags ^= :$: prc china aalpt yf75 yf-75 liquid pump upper lqdhydrogen lqdoxygen + + %specLevel = operational + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + @MODULE[ModuleGimbal] + { + %gimbalRange = 10 + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + origMass = 0.3055 + modded = false + configuration = YF-75 + CONFIG + { + name = YF-75 + description = Used on 3rd stage of CZ-3A/B/C + specLevel = operational + minThrust = 78.45 + maxThrust = 78.45 + heatProduction = 100 + ullage = True + pressureFed = False + ignitions = 2 + massMult = 1.0 + PROPELLANT + { + name = LqdHydrogen + ratio = 0.7631 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.2369 + } + atmosphereCurve + { + key = 0 439.6 + key = 1 193 + } + + //CZ-3A: 27 flights, 0 failures + //CZ-3B: 92 flights, 3 failures (1 ignition, 1 cycle, 1 unrelated) + //CZ-3B: 18 flights, 0 failures + //274 ignitions, 1 failures + //273 cycles, 1 failures (+1 unrelated) + //271 restarts, 0 failures + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 3000 //[8] + ratedBurnTime = 481 + safeOverburn = true + ignitionReliabilityStart = 0.995940 + ignitionReliabilityEnd = 0.999359 + ignitionDynPresFailMultiplier = 10.0 + cycleReliabilityStart = 0.991910 + cycleReliabilityEnd = 0.998723 + techTransfer = YF-73:50 + } + } + CONFIG + { + name = YF-75D + description = Converted to expander cycle for better performance. Used on second stage of CZ-5/A. + specLevel = operational + minThrust = 88.36 + maxThrust = 88.36 + heatProduction = 100 + ullage = True + pressureFed = False + ignitions = 8 + massMult = 0.8674 + PROPELLANT + { + name = LqdHydrogen + ratio = 0.7286 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.2714 + } + atmosphereCurve + { + key = 0 442.6 + key = 1 211 + } + + //CZ-5: 6 flights, 0 failures? (1 unrelated) + //Use YF-75 data + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 4320 //[8] + ratedBurnTime = 780 + safeOverburn = true + ignitionReliabilityStart = 0.995940 + ignitionReliabilityEnd = 0.999359 + ignitionDynPresFailMultiplier = 10.0 + cycleReliabilityStart = 0.991910 + cycleReliabilityEnd = 0.998723 + techTransfer = YF-75,YF-73:50 + } + } + CONFIG + { + name = YF-75E + description = YF-75D with nozzle extension, intended for third stage of CZ-10. + specLevel = prototype + minThrust = 92.11 + maxThrust = 92.11 + heatProduction = 100 + ullage = True + pressureFed = False + ignitions = 8 + massMult = 0.9984 + PROPELLANT + { + name = LqdHydrogen + ratio = 0.7286 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.2714 + } + atmosphereCurve + { + key = 0 451.1 + key = 1 80 + } + + //Use YF-75 data + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 4320 //[8] + ratedBurnTime = 780 + safeOverburn = true + ignitionReliabilityStart = 0.995940 + ignitionReliabilityEnd = 0.999359 + ignitionDynPresFailMultiplier = 10.0 + cycleReliabilityStart = 0.991910 + cycleReliabilityEnd = 0.998723 + techTransfer = YF-75D,YF-75,YF-73:50 + } + } + } +} diff --git a/GameData/RealismOverhaul/Engine_Configs/YF-77.cfg b/GameData/RealismOverhaul/Engine_Configs/YF77_Config.cfg similarity index 57% rename from GameData/RealismOverhaul/Engine_Configs/YF-77.cfg rename to GameData/RealismOverhaul/Engine_Configs/YF77_Config.cfg index 4287aa5de5..efdc8d26b6 100644 --- a/GameData/RealismOverhaul/Engine_Configs/YF-77.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/YF77_Config.cfg @@ -1,4 +1,4 @@ -// ============================ +// ================================================== // YF-77 // // Manufacturer : AALPT @@ -7,12 +7,12 @@ // YF-77 // Long March 5 // -// Dry Mass: 1375 Kg +// Dry Mass: 1050 kg from kerwis // Thrust (SL): ??? kN // Thrust(Vac): 700 kN -// ISP: 310.2 SL / 426 Vac -// Burn Time: 465 -// Chamber Pressure: 10.2 MPa +// ISP: 316.7 SL / 428 Vac +// Burn Time: 492 +// Chamber Pressure: 10.1 MPa // Propellant: LOX / LH2 // Prop Ratio: 5.5 // Throttle: N/A @@ -33,17 +33,33 @@ { %title = #roYF77Title //YF-77 %manufacturer = #roMfrAALPT - %description = #roYF77Desc //A hydrolox engine used on the Long March 5 Rocket. + %description = #roYF77Desc - @tags ^= :$: china aalpt yf-77 liquid pump sustainer lqdhydrogen lqdoxygen + @tags ^= :$: prc china aalpt yf-77 liquid pump sustainer lqdhydrogen lqdoxygen %specLevel = operational + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + @MODULE[ModuleGimbal] + { + %gimbalRange = 10 + %useGimbalResponseSpeed = true + %gimbalResponseSpeed = 16 + } + MODULE { name = ModuleEngineConfigs type = ModuleEngines - origMass = 1.375 + origMass = 1.05 modded = false configuration = YF-77 CONFIG @@ -56,32 +72,32 @@ PROPELLANT { name = LqdHydrogen - ratio = 0.8459 // 5.5:1 + ratio = 0.7454 DrawGauge = True } PROPELLANT { name = LqdOxygen - ratio = 0.1541 + ratio = 0.2546 } atmosphereCurve { - key = 0 426 - key = 1 310 + key = 0 428 + key = 1 316.7 } - //Long March 5: 7 flights, 1 failure - //14 engines, 1 failed + //Long March 5: 10 flights, 1 failure + //20 engines, 1 failed + //using Vulcain 1 data TESTFLIGHT:NEEDS[TestLite|TestFlight] { testedBurnTime = 3600 //Modern Hydrolox engines pretty durable, assume 1 hour - ratedBurnTime = 465 + ratedBurnTime = 492 safeOverburn = true - ignitionReliabilityStart = 0.883333 - ignitionReliabilityEnd = 0.976667 - ignitionDynPresFailMultiplier = 10.0 - cycleReliabilityStart = 0.883333 - cycleReliabilityEnd = 0.976667 + ignitionReliabilityStart = 0.932692 + ignitionReliabilityEnd = 0.986538 + cycleReliabilityStart = 0.932692 + cycleReliabilityEnd = 0.986538 } } } diff --git a/GameData/RealismOverhaul/Localization/en-us-Engines.cfg b/GameData/RealismOverhaul/Localization/en-us-Engines.cfg index a4717d2c1c..c170bc90f7 100644 --- a/GameData/RealismOverhaul/Localization/en-us-Engines.cfg +++ b/GameData/RealismOverhaul/Localization/en-us-Engines.cfg @@ -967,9 +967,36 @@ Localization #roXRS2200Title = XRS-2200 #roXRS2200Desc = A linear aerospike engine developed for NASA's X-33 sub-scale SSTO technology demonstrator. Like the toroidal J-2T engines, the XRS-2200 used machinery derived from the J-2S. //Y + // YF1 + #roYF1Title = YF-1 + #roYF1Desc = A Chinese hypergolic gas generator booster engine. Derived from the Isayev S2.1100 Burya booster engine, four YF-1 engines form the YF-2 booster used on the first stage of the DF-3, DF-4, and Long March 1 rockets. + // YF3 + #roYF3Title = YF-3 + #roYF3Desc = A Chinese hypergolic gas generator vacuum engine. Derived from the Isayev S2.1100 Burya booster engine, the YF-3 is a vacuum variant created for the second stage of the DF-4 and Long March 1. + // YF20 + #roYF20Title = YF-20 + #roYF20Desc = A Chinese hypergolic gas generator booster engine. Four YF-20 engines form the YF-21 booster used on the first stage of the DF-5, FB-1, and Long March 2/3/4 rockets, as well as the strap-on boosters for the Long March 2/3. + // YF22 + #roYF22Title = YF-22 + #roYF22Desc = A Chinese hypergolic gas generator vacuum engine. A YF-22 engine and YF-23 vernier form the YF-24 engine unit used on the second stage of the DF-5, FB-1, and Long March 2/3/4 rockets. + // YF23 + #roYF23Title = YF-23 + #roYF23Desc = A Chinese hypergolic gas generator vacuum engine. A YF-22 engine and YF-23 vernier form the YF-24 engine unit used on the second stage of the DF-5, FB-1, and Long March 2/3/4 rockets. + // YF24 + #roYF23Title = YF-24 + #roYF23Desc = A Chinese hypergolic gas generator vacuum engine with verniers. A YF-22 engine and YF-23 vernier form the YF-24 engine unit used on the second stage of the DF-5, FB-1, and Long March 2/3/4 rockets. + // YF40 + #roYF40Title = YF-40 + #roYF40Desc = A Chinese hypergolic gas generator vacuum engine, created for the 3rd stage of the Long March 4. Later versions had restart capability. + // YF75 + #roYF75Title = YF-75 + #roYF75Desc = A Chinese hydrolox gas generator vacuum engine, created to replace the YF-73. Used on the third stage of the Long March 3A/B/C. It was converted to expander cycle to create the YF-75D, which is used on the second stage of Long March 5. // YF77 #roYF77Title = YF-77 - #roYF77Desc = A hydrolox engine used on the Long March 5 Rocket. + #roYF77Desc = A Chinese hydrolox gas generator sustainer engine. Used on the first stage of the Long March 5. + // YF100 + #roYF100Title = YF-100 + #roYF100Desc = A Chinese kerolox staged combustion booster engine. Based on the RD-120, it is the first staged combustion engine developed in China, and is used on the boosters of the Long March 5, as well as the boosters and first stage of the Long March 6, 7, and 8. // ============================================================================ // Jet Engine Config Localizations @@ -1042,7 +1069,7 @@ Localization #roJ58Desc = Designed in the late 1950s, the J58 was redesigned and repurposed for one use: Mach 3+ aircraft like the A-12 / SR-71A/B / YF-12A. Also known by it's civilian designation, JT11. // J75 #roJ75Title = J75 Turbojet - #roJ75Desc = Essentially a larger J57, the P&W J75 saw extensive military and civilian use. It was used on the F-105, F-106, F-107, XF8U-3, A-12, U-2, P6M, and the 707 and DC-8 as the JT4A. + #roJ75Desc = Essentially a larger J57, the P&W J75 saw extensive military and civilian use. It was used on the F-105, F-106, F-107, XF8U-3, A-12, U-2, P6M, and the 707 and DC-8 as the JT4A. // J79 #roJ79Title = J79 Turbojet #roJ79Desc = The first US "Mach 2" engine, the J79 saw extensive service, powering the B-58, F-4, A-5, and F-104. @@ -1072,7 +1099,7 @@ Localization #roOlympus593Desc = A late 1960s turbojet. The ultimate version of the Olympus turbojet, designed for sustained Mach 2 operation to power Concorde. Although thirsty at sea level, when mated to a well-optimized intake this engine can supercruise at Mach 2, achieving relatively good efficiency. // R-11 #roR11Title = R-11 Turbojet - #roR11Desc = A late 50s turbojet, the R-11 was developed in parallel with the less sophisticated RD-9. It became the powerplant for the MiG-21, Yak-28 and Su-15. + #roR11Desc = A late 50s turbojet, the R-11 was developed in parallel with the less sophisticated RD-9. It became the powerplant for the MiG-21, Yak-28 and Su-15. It was reverse-engineered in China and built as the WP-7, where it powered the JJ-7, J/F-7, and J-8. // R-15 #roR15Title = R-15 Turbojet #roR15Desc = A late 50s turbojet originally developed for the Tu-121 cruise missile, the R-15 was modified instead for use on the MiG-25, which became the fastest serially produced fighter, capable of reaching Mach 3.2, although at the risk of severe engine damage. @@ -1081,7 +1108,7 @@ Localization #roR25Desc = A late 60s turbojet. Developed to replace the R-11 and R-13, the R-25 added an extremely powerful "extra-power" afterburner, that allowed it to nearly double it's thrust for short periods of time. // RD-9 #roRD9Title = RD-9 Turbojet - #roRD9Desc = An early 50s turbojet. Developed as a scaled down Mikulin AM-3, the RD-9 was designed for fighter aircraft and powered the Yak-25, 26, 27, 28, and MiG-19. + #roRD9Desc = An early 50s turbojet. Developed as a scaled down Mikulin AM-3, the RD-9 was designed for fighter aircraft and powered the Yak-25, 26, 27, 28, and MiG-19. It was license-built in China as the WP-6, where it powered the JJ-6, J/F-6, Q/A-5, and J-12. // RD-36 #roRD36Title = RD-36 Turbojet #roRD36Desc = The RD-36 was a 1970s turbojet, developed to power the Tu-144. The RD-36 replaced the underperforming NK-144 engines, allowing the Tu-144 to achieve its intended range. Ultimately, the Tu-144 was taken out of service shortly after being upgraded due to costs. The RD-36 powered the Tu-144D and M-17. @@ -1094,5 +1121,8 @@ Localization // Welland #roWellandTitle = Welland Turbojet #roWellandDesc = The Welland was an early 1940s turbojet, developed from Frank Whittle's original jet engine, the W.1. It was used on the Meteor F.1, but was quickly replaced by later, more powerful jet engines. + // WS-10 + #roWS10Title = WS-10 Low-Bypass Turbofan + #roWS10Desc = The WS-10 is a modern low-bypass afterburning turbofan, and the first successful Chinese turbofan design. Developed from the earlier experimental WS-6 turbofan, the WS-10 was designed to replace the Russian AL-31 engines used in some Chinese aircraft. The WS-10 powers the J-8II, J-10B/C, J-11B, J-15, J-16, and J-20/A. } } \ No newline at end of file diff --git a/GameData/RealismOverhaul/Localization/en-us-Mfr.cfg b/GameData/RealismOverhaul/Localization/en-us-Mfr.cfg index eb7a015adb..50aa1f92cc 100644 --- a/GameData/RealismOverhaul/Localization/en-us-Mfr.cfg +++ b/GameData/RealismOverhaul/Localization/en-us-Mfr.cfg @@ -281,6 +281,7 @@ Localization // ============================================================================ // Chinese Manufacturers #roMfrAALPT = Academy of Aerospace Liquid Propulsion Technology (AALPT) //(1970-present) + #roMfrAECC = Aero Engine Corporation of China (AECC) #roMfrARMT = Academy of Rocket Motors Technology (ARMT) //(1962-present) #roMfrCALT = China Academy of Launch Vehicle Technology (CALT) //(1957-present) #roMfrCASC = China Aerospace Science and Technology Corporation (中国航天) //(1999-present) diff --git a/GameData/RealismOverhaul/RO_SuggestedMods/Kerwis/Kerwis_RO.cfg b/GameData/RealismOverhaul/RO_SuggestedMods/Kerwis/Kerwis_RO.cfg new file mode 100644 index 0000000000..dca27755c7 --- /dev/null +++ b/GameData/RealismOverhaul/RO_SuggestedMods/Kerwis/Kerwis_RO.cfg @@ -0,0 +1,165 @@ +//Long March 1 +@PART[YF2_Engine]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF1 + %engineTypeMult = 4 + %clusterMultiplier = 4 +} +@PART[YF2_Engine]:FOR[RealismOverhaulEnginesPost] +{ + @title = YF-2 (no gimbal) +} + +@PART[YF2_with_shell]:NEEDS[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF1 + %engineTypeMult = 4 + %clusterMultiplier = 4 + %massOffset = 0.50 +} +@PART[YF2_with_shell]:FOR[RealismOverhaulEnginesPost] +{ + @title = YF-2 with Boattail +} + +@PART[YF3_Engine]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF3 +} +@PART[YF3_Engine]:FOR[RealismOverhaulEnginesPost] +{ + @title = YF-3 (no gimbal) +} + +@PART[YF3_with_shell]:NEEDS[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF3 + %engineTypeMult = 4 + %clusterMultiplier = 4 + %massOffset = 0.30 +} +@PART[YF3_with_shell]:FOR[RealismOverhaulEnginesPost] +{ + @title = YF-3 with Boattail +} + +//Long March 2 +@PART[YF21_Engine]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF20 + %engineTypeMult = 4 + %clusterMultiplier = 4 +} +@PART[YF21_Engine]:FOR[RealismOverhaulEnginesPost] +{ + @title = YF-21 +} + +@PART[YF21_with_shell_*]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF20 + %engineTypeMult = 4 + %clusterMultiplier = 4 + %massOffset = 0.90 +} +@PART[YF21_with_shell_CZ-2]:FOR[RealismOverhaulEnginesPost] +{ + @title = YF-21 with CZ-2 Boattail +} +@PART[YF21_with_shell_CZ-2C]:FOR[RealismOverhaulEnginesPost] +{ + @title = YF-21 with CZ-2C Boattail +} +@PART[YF21_with_shell_CZ-2D]:FOR[RealismOverhaulEnginesPost] +{ + @title = YF-21 with CZ-2D Boattail +} + +@PART[YF22_Engine]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF22 +} + +@PART[YF23_Engine]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF23 + %engineTypeMult = 0.25 + %clusterMultiplier = 0.25 +} + +//Long March 3 +@PART[YF20_Engine]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF20 +} + +@PART[YF25K_Engine]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF20 + %engineTypeMult = 1 + %clusterMultiplier = 1 + %massOffset = 0.20 +} +@PART[YF25K_Engine]:FOR[RealismOverhaulEnginesPost] +{ + @title = YF-20 with Boattail (no gimbal) +} + +@PART[YF75_Engine]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF75 + %engineTypeMult = 2 + %clusterMultiplier = 2 +} + +//Long March 5 +@PART[YF100_Engine_S]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF100 +} +@PART[YF100_Engine-double-withShell2]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF100 + %engineTypeMult = 2 + %clusterMultiplier = 2 + %massOffset = 4.0 +} +@PART[YF100_Engine-double-withShell2]:FOR[RealismOverhaulEnginesPost] +{ + @title = YF-100 with CZ-5 Boattail +} +@PART[YF77_Engine]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF77 +} +@PART[YF77_Engine-double-withShell]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF77 + %engineTypeMult = 2 + %clusterMultiplier = 2 + %massOffset = 0.65 +} +@PART[YF77_Engine-double-withShell]:FOR[RealismOverhaulEnginesPost] +{ + @title = YF-77 with CZ-5 Boattail +} +@PART[YF75D_Engine]:FOR[RealismOverhaul] +{ + %RSSROConfig = True + %engineType = YF75 +}