From fc67603cbdb22159abb265632abec581c7ac9502 Mon Sep 17 00:00:00 2001 From: Capkirk123 Date: Fri, 9 Jun 2023 01:58:46 -0400 Subject: [PATCH] Add RD-220, and alternate fuel mixes to RD253 and RD270 (#2856) * Add RD-220, and alternate fuel mixes to RD253 and RD270 Add the RD220 and RD221, predecessors to the RD253 and RD254. Add alternative RD253 configurations tested but never used for Proton, including AK27/UDMH and LOX/UDMH. Finally, consolidate the RD270 and RD270M into one config. This also includes many improvements to the RD270 config, correcting O/F ratios, and creating PB-1 for use in the RD-270M. * Add note regarding RD270 scale * Deprecate RD-270M Deprecate RD-270M engine type, as it is being moved to a RD-270 config (and almost certainly didn't exist anyway) * Update propellant ratios Update propellant ratios for RO v16 * Remove gimbal, add throttle Remove gimbal and add throttle instead for differential throttle on RD-220/221. * Remove mention of pentaborane Remove mention of pentaborane from RD-270 description, seeing as it was never actually proposed to use pentaborane * LqdOxygen, not LOX oops * Fix typo and add PB to stock tanks * Add PB to RO tanks too * Add dash, split RD-270M Use PB-1. Make RD-270M it's own config, not a subconfig, considering it has a much different MR and would probably need significant redesign. * Update RD270_Config.cfg --- .../Engine_Configs/RD220_Config.cfg | 166 ++++++++ .../Engine_Configs/RD221_Config.cfg | 166 ++++++++ .../Engine_Configs/RD253_Config.cfg | 370 ++++++++++++++++- .../Engine_Configs/RD254_Config.cfg | 381 +++++++++++++++++- .../Engine_Configs/RD270M_Config.cfg | 6 +- .../Engine_Configs/RD270_Config.cfg | 216 +++++++++- .../Localization/en-us-Engines.cfg | 14 +- GameData/RealismOverhaul/RO_RealFuels.cfg | 1 + GameData/RealismOverhaul/RO_Resources.cfg | 18 +- 9 files changed, 1295 insertions(+), 43 deletions(-) create mode 100644 GameData/RealismOverhaul/Engine_Configs/RD220_Config.cfg create mode 100644 GameData/RealismOverhaul/Engine_Configs/RD221_Config.cfg diff --git a/GameData/RealismOverhaul/Engine_Configs/RD220_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD220_Config.cfg new file mode 100644 index 0000000000..29e20e08b3 --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/RD220_Config.cfg @@ -0,0 +1,166 @@ +// ================================================== +// RD-220/112 +// +// Manufacturer: NPO Energomash +// +// ================================================================================= +// RD-112 +// R-20 1st stage +// +// Dry Mass: 790 Kg +// Thrust (SL): 961 kN +// Thrust (Vac): 1088.5 kN +// ISP: 304 SL / 344 Vac +// Burn Time: ??? +// Chamber Pressure: 14.7 MPa [2] +// Propellant: LOX / UDMH +// Prop Ratio: 1.704 [2],[5] +// Throttle: 100%-75% for differential throttle? +// Nozzle Ratio: 31.8 [2],[5] +// Ignitions: ??? +// ================================================================================= +// RD-220 +// Hypergolic version of RD-112? +// +// Dry Mass: 760 Kg +// Thrust (SL): 947.3 kN +// Thrust (Vac): 1074.0 kN +// ISP: 270 SL / 306 Vac +// Burn Time: ??? +// Chamber Pressure: 14.7 MPa [6] +// Propellant: AK27 / UDMH +// Prop Ratio: 2.8 [6] +// Throttle: 100%-75% for differential throttle? +// Nozzle Ratio: 31.8 [6] +// Ignitions: ??? +// ================================================================================= + +// Sources: + +// [1]http://www.npoenergomash.ru/netcat_files/File/Table_of_Engines.docx +// [2]http://www.b14643.de/Spacerockets/Specials/Russian_Rocket_engines/engines.htm +// [3]http://www.b14643.de/Spacerockets/Specials/R_and_UR-Missiles/Description/Frame.htm +// [4]http://www.lpre.de/energomash/RD-114/index.htm +// [5]http://www.astronautix.com/r/rd-112.html +// [6]http://www.astronautix.com/r/rd-220.html +// [7]http://epizodyspace.ru/bibl/glushko/izbran-rab-glushko/1/02.html + + +// Used by: + +// Notes: +// All data from [1] unless otherwise stated. +// Astronautix claims RD-107/108 derived. Drawings from b14643 show single chamber? +// Data on RD-220/221 fuzzy, but dimensions are exactly the same as RD-112/113, and other stats very close +// Pretty confident they were part of the same project. +// Almost certainly staged combustion, based on performance. +// R-20 is huge, 28 engines first stage, 7 engines second stage. +// According to [7], fixed engines. Assuming control achieved through differential throttle? +// Seems reasonable, considering number of engines on R-20 +// ================================================== +@PART[*]:HAS[#engineType[RD220]]:FOR[RealismOverhaulEngines] +{ + %title = #roRD220Title //RD-220/112 + %manufacturer = #roMfrOKB456 + %description = #roRD220Desc + + @tags ^= :$: USSR okb-456 glushko rd-112 rd-113 rd-220 rd-221 liquid pump booster upper udmh nitric acid oxygen + + %specLevel = concept + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + !MODULE[ModuleGimbal] {} //fixed? + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = RD-220 + origMass = 0.760 + modded = false + + CONFIG + { + name = RD-220 + description = First stage for R-20 project. + specLevel = concept + minThrust = 805.5 + maxThrust = 1074.0 + heatProduction = 100 + massMult = 1.0 + PROPELLANT + { + name = UDMH + ratio = 0.4090 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.5910 + } + atmosphereCurve + { + key = 0 306 + key = 1 270 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + SUBCONFIG + { + name = RD-112 + description = UDMH/LOX version. + specLevel = concept + minThrust = 816.4 + maxThrust = 1088.5 + massMult = 1.0395 + costOffset = 0 + PROPELLANT + { + name = UDMH + ratio = 0.4584 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5416 + } + atmosphereCurve + { + key = 0 344 + key = 1 304 + } + } + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 450 //same as Proton Uppers + ratedBurnTime = 110 //same as RD-111? + safeOverburn = true + ignitionReliabilityStart = 0.987116 + ignitionReliabilityEnd = 0.997966 + cycleReliabilityStart = 0.987116 + cycleReliabilityEnd = 0.997966 + techTransfer = RD-221:50 + } + } + } +} + diff --git a/GameData/RealismOverhaul/Engine_Configs/RD221_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD221_Config.cfg new file mode 100644 index 0000000000..b8368c5be9 --- /dev/null +++ b/GameData/RealismOverhaul/Engine_Configs/RD221_Config.cfg @@ -0,0 +1,166 @@ +// ================================================== +// RD-221/113 +// +// Manufacturer: NPO Energomash +// +// ================================================================================= +// RD-113 +// R-20 2nd stage +// +// Dry Mass: 1100 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 1137.6 kN +// ISP: 251 SL / 360 Vac //SL calculated with RPA +// Burn Time: ??? +// Chamber Pressure: 14.7 MPa [2] +// Propellant: LOX / UDMH +// Prop Ratio: 1.704 [2],[5] +// Throttle: 100%-75% for differential throttle? +// Nozzle Ratio: 119.8 [2],[5] +// Ignitions: ??? +// ================================================================================= +// RD-221 +// Hypergolic version of RD-113 +// +// Dry Mass: 1070 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 1117.9 kN +// ISP: 221 SL / 318 Vac //SL calculated with RPA +// Burn Time: ??? +// Chamber Pressure: 14.7 MPa [6] +// Propellant: AK27 / UDMH +// Prop Ratio: 2.8 [6] +// Throttle: 100%-75% for differential throttle? +// Nozzle Ratio: 119.8 [6] +// Ignitions: ??? +// ================================================================================= + +// Sources: + +// [1]http://www.npoenergomash.ru/netcat_files/File/Table_of_Engines.docx +// [2]http://www.b14643.de/Spacerockets/Specials/Russian_Rocket_engines/engines.htm +// [3]http://www.b14643.de/Spacerockets/Specials/R_and_UR-Missiles/Description/Frame.htm +// [4]http://www.lpre.de/energomash/RD-114/index.htm +// [5]http://www.astronautix.com/r/rd-112.html +// [6]http://www.astronautix.com/r/rd-220.html +// [7]http://epizodyspace.ru/bibl/glushko/izbran-rab-glushko/1/02.html + + +// Used by: + +// Notes: +// All data from [1] unless otherwise stated. +// Astronautix claims RD-107/108 derived. Drawings from b14643 show single chamber? +// Data on RD-220/221 fuzzy, but dimensions are exactly the same as RD-112/113, and other stats very close +// Pretty confident they were part of the same project. +// Almost certainly staged combustion, based on performance. +// R-20 is huge, 28 engines first stage, 7 engines second stage. +// According to [7], fixed engines. Assuming control achieved through differential throttle? +// Seems reasonable, considering number of engines on R-20 +// ================================================== +@PART[*]:HAS[#engineType[RD221]]:FOR[RealismOverhaulEngines] +{ + %title = #roRD221Title //RD-221/113 + %manufacturer = #roMfrOKB456 + %description = #roRD221Desc + + @tags ^= :$: USSR okb-456 glushko rd-112 rd-113 rd-220 rd-221 liquid pump booster upper udmh nitric acid oxygen + + %specLevel = concept + + @MODULE[ModuleEngines*] + { + %EngineType = LiquidFuel + } + + !MODULE[ModuleEngineConfigs],*{} + !MODULE[ModuleAlternator],*{} + !RESOURCE,*{} + + !MODULE[ModuleGimbal] {} //fixed? + + MODULE + { + name = ModuleEngineConfigs + type = ModuleEngines + configuration = RD-221 + origMass = 0.760 + modded = false + + CONFIG + { + name = RD-221 + description = Second stage for R-20 project. + specLevel = concept + minThrust = 838.4 + maxThrust = 1117.9 + heatProduction = 100 + massMult = 1.4079 + PROPELLANT + { + name = UDMH + ratio = 0.4090 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.5910 + } + atmosphereCurve + { + key = 0 318 + key = 1 221 + } + + ullage = True + pressureFed = False + ignitions = 1 + + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 1.0 + } + SUBCONFIG + { + name = RD-113 + description = UDMH/LOX version. + specLevel = concept + minThrust = 853.2 + maxThrust = 1137.6 + massMult = 1.4474 + costOffset = 0 + PROPELLANT + { + name = UDMH + ratio = 0.4584 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5416 + } + atmosphereCurve + { + key = 0 360 + key = 1 251 + } + } + + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 450 //same as Proton Uppers + ratedBurnTime = 250 //same as Proton Uppers? + safeOverburn = true + ignitionReliabilityStart = 0.989850 + ignitionReliabilityEnd = 0.998397 + cycleReliabilityStart = 0.989850 + cycleReliabilityEnd = 0.998397 + techTransfer = RD-220:50 + } + } + } +} + diff --git a/GameData/RealismOverhaul/Engine_Configs/RD253_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD253_Config.cfg index 196fcb7d9a..c0d7f64f7c 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD253_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD253_Config.cfg @@ -12,11 +12,41 @@ // Thrust (Vac): 1545 kN // ISP: 284.5 SL / 315.5 Vac // Burn Time: 148 -// Chamber Pressure: ??? MPa +// Chamber Pressure: 14.7 MPa // Propellant: NTO / UDMH // Prop Ratio: 2.67 // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 26.3 +// Ignitions: 1 +// ================================================================================= +// RD-222 (11D41) +// prototype, running on AK27/UDMH +// +// Dry Mass: 1080 Kg increasing mass by 100 kg to keep closer to production RD-253 +// Thrust (SL): ??? kN +// Thrust (Vac): 1633.8 kN +// ISP: 272 SL / 302 Vac +// Burn Time: 148 +// Chamber Pressure: 14.7 MPa +// Propellant: AK27 / UDMH +// Prop Ratio: 2.92 +// Throttle: N/A +// Nozzle Ratio: 26.3 +// Ignitions: 1 +// ================================================================================= +// RD-114 (11D31) +// prototype, running on LOX/UDMH +// +// Dry Mass: 1090 Kg increasing mass by 100 kg to keep closer to production RD-253 +// Thrust (SL): ??? kN +// Thrust (Vac): 1653.4 kN +// ISP: 307 SL / 341 Vac +// Burn Time: 148 +// Chamber Pressure: 14.7 MPa +// Propellant: LOX / UDMH +// Prop Ratio: 1.77 +// Throttle: N/A +// Nozzle Ratio: 26.3 // Ignitions: 1 // ================================================================================= // RD-253-Mk2 @@ -31,7 +61,7 @@ // Propellant: NTO / UDMH // Prop Ratio: 2.69 // Throttle: N/A -// Nozzle Ratio: 25.5? calculated with RPA +// Nozzle Ratio: 26.3 // Ignitions: 1 // ================================================================================= // RD-253-Mk3 @@ -46,7 +76,7 @@ // Propellant: NTO / UDMH // Prop Ratio: 2.69 // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 26.3 // Ignitions: 1 // ================================================================================= // RD-253-Mk4 @@ -61,7 +91,7 @@ // Propellant: NTO / UDMH // Prop Ratio: 2.69 // Throttle: N/A -// Nozzle Ratio: ??? +// Nozzle Ratio: 26.3 // Ignitions: 1 // ================================================================================= // RD-275 (14D14) @@ -102,6 +132,8 @@ // (3)http://www.lpre.de/energomash/RD-253/index.htm // (4)http://www.russianspaceweb.com/rd253.html // (5)http://www.npoenergomash.ru/eng/dejatelnost/engines/rd253/ +// (6)http://www.npoenergomash.ru/netcat_files/File/Table_of_Engines.docx +// (7)http://www.lpre.de/energomash/RD-114/index.htm // Used by: // OLDD @@ -109,6 +141,10 @@ // Squad // Notes: +// RD-253 originated from specification for 150 ton-force staged combustion engine to power the N-1. +// Contracts were given to develop engines running on AK27/UDMH, NTO/UDMH, LOX/UDMH, and LOX/Kerosene. +// Glushko took the first three, while the last was given to Kuznetsov. The first three became the +// RD-222/223, RD-253/254, and RD-114/115, while the last became the NK-15/NK-15V. // RD-253 versions have been attempted to be matched with their associated Proton versions // Although no source other than (1) mentions different RD-253 variants, several RD-253 @@ -150,7 +186,7 @@ CONFIG { name = RD-253 - description = Original RD-253 as used on the UR-500. + description = 11D43. Original RD-253 as used on the UR-500. specLevel = operational minThrust = 1545 maxThrust = 1545 @@ -181,6 +217,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-222 + description = 11D41. UDMH/AK27 version of RD-253. Higher thrust, at the cost of efficiency. + specLevel = prototype + minThrust = 1633.8 + maxThrust = 1633.8 + massMult = 1.0 + costOffset = 0 + PROPELLANT + { + name = UDMH + ratio = 0.3989 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6011 + } + atmosphereCurve + { + key = 0 302 + key = 1 272 + } + } + SUBCONFIG + { + name = RD-114 + description = 11D31. UDMH/LOX version of RD-253. Much higher performance, but requires cryogenic fuels. + specLevel = prototype + minThrust = 1653.4 + maxThrust = 1653.4 + massMult = 1.0093 + costOffset = 0 + PROPELLANT + { + name = UDMH + ratio = 0.4490 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5510 + } + atmosphereCurve + { + key = 0 341 + key = 1 307 + } + } //Most sources don't even acknowledge the different versions of the RD-253, or mention what Proton versions they were used on. //Failures are pretty heavily in the early protons though. Split data 4 ways, and failures 4:3:1:0 @@ -249,6 +337,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-222-Mk2 + description = Speculative upgrade. + specLevel = speculative + minThrust = 1728.9 + maxThrust = 1728.9 + massMult = 1.0 + costOffset = 0 + PROPELLANT //2.94 + { + name = UDMH + ratio = 0.3973 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6027 + } + atmosphereCurve + { + key = 0 302.5 + key = 1 272.5 + } + } + SUBCONFIG + { + name = RD-114-Mk2 + description = Speculative upgrade. + specLevel = speculative + minThrust = 1749.7 + maxThrust = 1749.7 + massMult = 1.0093 + costOffset = 0 + PROPELLANT //1.78 + { + name = UDMH + ratio = 0.4476 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5524 + } + atmosphereCurve + { + key = 0 341.5 + key = 1 307.5 + } + } //467 engines, 3 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -260,7 +400,7 @@ ignitionReliabilityEnd = 0.998397 cycleReliabilityStart = 0.989850 cycleReliabilityEnd = 0.998397 - techTransfer = RD-253:50 + techTransfer = RD-253,RD-220,RD-221:50 reliabilityMidH = 0.45 reliabilityDataRateMultiplier = 0.5 } @@ -300,6 +440,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-222-Mk3 + description = Speculative upgrade. + specLevel = speculative + minThrust = 1795.6 + maxThrust = 1795.6 + massMult = 1.0 + costOffset = 0 + PROPELLANT //2.94 + { + name = UDMH + ratio = 0.3973 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6027 + } + atmosphereCurve + { + key = 0 302.5 + key = 1 272.5 + } + } + SUBCONFIG + { + name = RD-114-Mk3 + description = Speculative upgrade. + specLevel = speculative + minThrust = 1817.1 + maxThrust = 1817.1 + massMult = 1.0093 + costOffset = 0 + PROPELLANT //1.78 + { + name = UDMH + ratio = 0.4476 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5524 + } + atmosphereCurve + { + key = 0 341.5 + key = 1 307.5 + } + } //466 engines, 1 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -311,7 +503,7 @@ ignitionReliabilityEnd = 0.999251 cycleReliabilityStart = 0.995253 cycleReliabilityEnd = 0.999251 - techTransfer = RD-253-Mk2,RD-253:50 + techTransfer = RD-253-Mk2,RD-253,RD-220,RD-221:50 reliabilityMidH = 0.45 reliabilityDataRateMultiplier = 0.5 } @@ -350,6 +542,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-222-Mk4 + description = Speculative upgrade. + specLevel = speculative + minThrust = 1848.5 + maxThrust = 1848.5 + massMult = 1.0 + costOffset = 0 + PROPELLANT //2.94 + { + name = UDMH + ratio = 0.3973 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6027 + } + atmosphereCurve + { + key = 0 302.5 + key = 1 272.5 + } + } + SUBCONFIG + { + name = RD-114-Mk4 + description = Speculative upgrade. + specLevel = speculative + minThrust = 1870.6 + maxThrust = 1870.6 + massMult = 1.0093 + costOffset = 0 + PROPELLANT //1.78 + { + name = UDMH + ratio = 0.4476 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5524 + } + atmosphereCurve + { + key = 0 341.5 + key = 1 307.5 + } + } //467 engines, 0 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -361,7 +605,7 @@ ignitionReliabilityEnd = 0.999679 cycleReliabilityStart = 0.997970 cycleReliabilityEnd = 0.999679 - techTransfer = RD-253-Mk3,RD-253-Mk2,RD-253:50 + techTransfer = RD-253-Mk3,RD-253-Mk2,RD-253,RD-220,RD-221:50 } } CONFIG @@ -399,6 +643,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-222M + description = Speculative upgrade. + specLevel = speculative + minThrust = 1846.4 + maxThrust = 1846.4 + massMult = 0.99074 + costOffset = 0 + PROPELLANT //2.94 + { + name = UDMH + ratio = 0.3973 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6027 + } + atmosphereCurve + { + key = 0 302.5 + key = 1 274.4 + } + } + SUBCONFIG + { + name = RD-114M + description = Speculative upgrade. + specLevel = speculative + minThrust = 1868.5 + maxThrust = 1868.5 + massMult = 0.99995 + costOffset = 0 + PROPELLANT //1.78 + { + name = UDMH + ratio = 0.4476 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5524 + } + atmosphereCurve + { + key = 0 341.5 + key = 1 309.7 + } + } //Proton-M Blok-DM-2 (8K82K 11S861): 6 flights, 0 failures //Proton-M Blok-DM-03 (8K82K 11S861-03): 5 flights, 0 failures @@ -415,7 +711,7 @@ ignitionReliabilityEnd = 0.999289 cycleReliabilityStart = 0.995498 cycleReliabilityEnd = 0.999289 - techTransfer = RD-253-Mk4,RD-253-Mk3,RD-253-Mk2,RD-253:50 + techTransfer = RD-253-Mk4,RD-253-Mk3,RD-253-Mk2,RD-253,RD-220,RD-221:50 } } CONFIG @@ -453,6 +749,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-222M1 + description = Speculative upgrade. + specLevel = speculative + minThrust = 1935.2 + maxThrust = 1935.2 + massMult = 0.99074 + costOffset = 0 + PROPELLANT //2.94 + { + name = UDMH + ratio = 0.3973 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6027 + } + atmosphereCurve + { + key = 0 302.3 + key = 1 275.3 + } + } + SUBCONFIG + { + name = RD-114M1 + description = Speculative upgrade. + specLevel = speculative + minThrust = 1958.4 + maxThrust = 1958.4 + massMult = 0.99995 + costOffset = 0 + PROPELLANT //1.78 + { + name = UDMH + ratio = 0.4476 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5524 + } + atmosphereCurve + { + key = 0 341.3 + key = 1 310.8 + } + } //Proton-M Briz-M (8K82KM 14S43) (Phase I mod. 1): 2 flights, 0 failures //Proton-M Briz-M (8K82KM 14S43) (Phase I mod. 2): 3 flights, 0 failures @@ -470,7 +818,7 @@ ignitionReliabilityEnd = 0.999663 cycleReliabilityStart = 0.997865 cycleReliabilityEnd = 0.999663 - techTransfer = RD-275,RD-253-Mk4,RD-253-Mk3,RD-253-Mk2,RD-253:50 + techTransfer = RD-275,RD-253-Mk4,RD-253-Mk3,RD-253-Mk2,RD-253,RD-220,RD-221:50 } } } diff --git a/GameData/RealismOverhaul/Engine_Configs/RD254_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD254_Config.cfg index 12d0af6db3..77f321bb9d 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD254_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD254_Config.cfg @@ -10,13 +10,43 @@ // Dry Mass: 1450 Kg // Thrust (SL): ??? kN // Thrust (Vac): 1622 kN -// ISP: 241 SL / 327 Vac SL calculated with RPA +// ISP: 239 SL / 327 Vac SL calculated with RPA // Burn Time: 225 // Chamber Pressure: 14.71? MPa // Propellant: NTO / UDMH // Prop Ratio: 2.67 // Throttle: N/A -// Nozzle Ratio: ??? (81.3?) +// Nozzle Ratio: 86.2? +// Ignitions: 1 +// ================================================================================= +// RD-223 (11D42) +// prototype, running on AK27/UDMH +// +// Dry Mass: 1440 Kg increasing mass by 200 kg to keep closer to production RD-253 +// Thrust (SL): ??? kN +// Thrust (Vac): 1696.6 kN +// ISP: 230 SL / 314 Vac SL calculated with RPA +// Burn Time: 225 +// Chamber Pressure: 14.71? MPa +// Propellant: AK27 / UDMH +// Prop Ratio: 2.92 +// Throttle: N/A +// Nozzle Ratio: 86.2 +// Ignitions: 1 +// ================================================================================= +// RD-115 (11D32) +// prototype, running on LOX/UDMH +// +// Dry Mass: 1450 Kg increasing mass by 100 kg to keep closer to production RD-253 +// Thrust (SL): ??? kN +// Thrust (Vac): 1726.0 kN +// ISP: 259 SL / 357 Vac SL calculated with RPA +// Burn Time: 225 +// Chamber Pressure: 14.71? MPa +// Propellant: LOX / UDMH +// Prop Ratio: 1.77 +// Throttle: N/A +// Nozzle Ratio: 86.2 // Ignitions: 1 // ================================================================================= // RD-254-Mk2 @@ -25,7 +55,7 @@ // Dry Mass: 1450 Kg // Thrust (SL): ??? kN // Thrust (Vac): 1716 kN //Since the RD253-Mk2 appears to match listed RD-253 stats, reference the RD-254 to it. -// ISP: 242 SL / 327.8 Vac SL calculated with RPA +// ISP: 240 SL / 327.8 Vac SL calculated with RPA // Burn Time: 225 // Chamber Pressure: 14.71 MPa // Propellant: NTO / UDMH @@ -40,7 +70,7 @@ // Dry Mass: 1450 Kg // Thrust (SL): ??? kN // Thrust (Vac): 1782 kN -// ISP: 242 SL / 327.8 Vac SL calculated with RPA +// ISP: 240 SL / 327.8 Vac SL calculated with RPA // Burn Time: 225 // Chamber Pressure: ??? MPa // Propellant: NTO / UDMH @@ -55,7 +85,7 @@ // Dry Mass: 1450 Kg // Thrust (SL): ??? kN // Thrust (Vac): 1834 kN -// ISP: 242 SL / 327.8 Vac SL calculated with RPA +// ISP: 240 SL / 327.8 Vac SL calculated with RPA // Burn Time: 225 // Chamber Pressure: ??? MPa // Propellant: NTO / UDMH @@ -70,7 +100,7 @@ // Dry Mass: 1436 Kg // Thrust (SL): ??? kN // Thrust (Vac): 1834 kN -// ISP: 242 SL / 327.8 Vac SL calculated with RPA +// ISP: 243 SL / 327.8 Vac SL calculated with RPA // Burn Time: 225 // Chamber Pressure: 15.69 MPa // Propellant: NTO / UDMH @@ -85,7 +115,7 @@ // Dry Mass: 1436 Kg // Thrust (SL): ??? kN // Thrust (Vac): 1922 kN -// ISP: 242 SL / 327.8 Vac SL calculated with RPA +// ISP: 245 SL / 327.8 Vac SL calculated with RPA // Burn Time: 225 // Chamber Pressure: 16.6 MPa // Propellant: NTO / UDMH @@ -100,6 +130,8 @@ // http://lpre.de/energomash/index.htm // http://www.astronautix.com/r/rd-254.html // http://www.b14643.de/Spacerockets/Specials/R_and_UR-Missiles/Gallery/UR-700/UR-700.htm +// http://www.npoenergomash.ru/netcat_files/File/Table_of_Engines.docx +// http://www.lpre.de/energomash/RD-114/index.htm // Used by: @@ -165,7 +197,7 @@ atmosphereCurve { key = 0 327.3 - key = 1 241 + key = 1 239 } ullage = True @@ -177,6 +209,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-223-11D42 + description = 11D42. UDMH/AK27 version of RD-254. Higher thrust, at the cost of efficiency. + specLevel = prototype + minThrust = 1696.6 + maxThrust = 1696.6 + massMult = 0.9931 + costOffset = 0 + PROPELLANT + { + name = UDMH + ratio = 0.3989 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6011 + } + atmosphereCurve + { + key = 0 314 + key = 1 230 + } + } + SUBCONFIG + { + name = RD-115-11D32 + description = 11D32. UDMH/LOX version of RD-254. Much higher performance, but requires cryogenic fuels. + specLevel = prototype + minThrust = 1726.0 + maxThrust = 1726.0 + massMult = 1.0 + costOffset = 0 + PROPELLANT + { + name = UDMH + ratio = 0.4490 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5510 + } + atmosphereCurve + { + key = 0 357 + key = 1 259 + } + } //Due to the RD-253 and 254 being almost identical, just use RD-253 data for the RD-254. //Most sources don't even acknowledge the different versions of the RD-253, or mention what Proton versions they were used on. @@ -210,6 +294,7 @@ cycleReliabilityEnd = 0.997966 reliabilityMidH = 0.55 reliabilityDataRateMultiplier = 0.5 + techTransfer = RD-253,RD-221,RD-220:50 } } CONFIG @@ -234,7 +319,7 @@ atmosphereCurve { key = 0 327.8 - key = 1 242 + key = 1 240 } ullage = True @@ -246,6 +331,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-223-11D42-Mk2 + description = UDMH/AK27 version of RD-254. Higher thrust, at the cost of efficiency. + specLevel = speculative + minThrust = 1764.9 + maxThrust = 1764.9 + massMult = 0.9931 + costOffset = 0 + PROPELLANT //2.94 + { + name = UDMH + ratio = 0.3973 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6027 + } + atmosphereCurve + { + key = 0 314.8 + key = 1 231 + } + } + SUBCONFIG + { + name = RD-115-11D32-Mk3 + description = UDMH/LOX version of RD-254. Much higher performance, but requires cryogenic fuels. + specLevel = speculative + minThrust = 1826.0 + maxThrust = 1826.0 + massMult = 1.0 + costOffset = 0 + PROPELLANT //1.78 + { + name = UDMH + ratio = 0.4476 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5524 + } + atmosphereCurve + { + key = 0 357.9 + key = 1 260 + } + } //467 engines, 3 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -257,7 +394,7 @@ ignitionReliabilityEnd = 0.998397 cycleReliabilityStart = 0.989850 cycleReliabilityEnd = 0.998397 - techTransfer = RD-254-11D44:50 + techTransfer = RD-253-Mk2,RD-254-11D44,RD-253,RD-221,RD-220:50 reliabilityMidH = 0.45 reliabilityDataRateMultiplier = 0.5 } @@ -285,7 +422,7 @@ atmosphereCurve { key = 0 327.8 - key = 1 242 + key = 1 240 } ullage = True @@ -297,6 +434,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-223-11D42-Mk3 + description = UDMH/AK27 version of RD-254. Higher thrust, at the cost of efficiency. + specLevel = speculative + minThrust = 1863.9 + maxThrust = 1863.9 + massMult = 0.9931 + costOffset = 0 + PROPELLANT //2.94 + { + name = UDMH + ratio = 0.3973 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6027 + } + atmosphereCurve + { + key = 0 314.8 + key = 1 231 + } + } + SUBCONFIG + { + name = RD-115-11D32-Mk3 + description = UDMH/LOX version of RD-254. Much higher performance, but requires cryogenic fuels. + specLevel = speculative + minThrust = 1896.3 + maxThrust = 1896.3 + massMult = 1.0 + costOffset = 0 + PROPELLANT //1.78 + { + name = UDMH + ratio = 0.4476 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5524 + } + atmosphereCurve + { + key = 0 357.9 + key = 1 260 + } + } //466 engines, 1 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -308,7 +497,7 @@ ignitionReliabilityEnd = 0.999251 cycleReliabilityStart = 0.995254 cycleReliabilityEnd = 0.999251 - techTransfer = RD-254-11D44-Mk2,RD-254-11D44:50 + techTransfer = RD-253-Mk3,RD-254-11D44-Mk2,RD-253-Mk2,RD-254-11D44,RD-253,RD-221,RD-220:50 reliabilityMidH = 0.45 reliabilityDataRateMultiplier = 0.5 } @@ -335,7 +524,7 @@ atmosphereCurve { key = 0 327.8 - key = 1 242 + key = 1 240 } ullage = True @@ -347,6 +536,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-223-11D42-Mk4 + description = UDMH/AK27 version of RD-254. Higher thrust, at the cost of efficiency. + specLevel = speculative + minThrust = 1918.4 + maxThrust = 1918.4 + massMult = 0.9931 + costOffset = 0 + PROPELLANT //2.94 + { + name = UDMH + ratio = 0.3973 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6027 + } + atmosphereCurve + { + key = 0 314.8 + key = 1 231 + } + } + SUBCONFIG + { + name = RD-115-11D32-Mk4 + description = UDMH/LOX version of RD-254. Much higher performance, but requires cryogenic fuels. + specLevel = speculative + minThrust = 1951.6 + maxThrust = 1951.6 + massMult = 1.0 + costOffset = 0 + PROPELLANT //1.78 + { + name = UDMH + ratio = 0.4476 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5524 + } + atmosphereCurve + { + key = 0 357.9 + key = 1 260 + } + } //467 engines, 0 failures TESTFLIGHT:NEEDS[TestLite|TestFlight] @@ -358,7 +599,7 @@ ignitionReliabilityEnd = 0.999679 cycleReliabilityStart = 0.997970 cycleReliabilityEnd = 0.999679 - techTransfer = RD-254-11D44-Mk3,RD-254-11D44-Mk2,RD-254-11D44:50 + techTransfer = RD-253-Mk4,RD-254-11D44-Mk3,RD-253-Mk3,RD-254-11D44-Mk2,RD-253-Mk2,RD-254-11D44,RD-253,RD-221,RD-220:50 } } @@ -385,7 +626,7 @@ atmosphereCurve { key = 0 327.8 - key = 1 242 + key = 1 243 } ullage = True @@ -397,6 +638,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-223M-11D42M + description = UDMH/AK27 version of RD-254. Higher thrust, at the cost of efficiency. + specLevel = speculative + minThrust = 1918 + maxThrust = 1918 + massMult = 0.9839 + costOffset = 0 + PROPELLANT //2.94 + { + name = UDMH + ratio = 0.3973 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6027 + } + atmosphereCurve + { + key = 0 314.8 + key = 1 234 + } + } + SUBCONFIG + { + name = RD-115M-11D32M + description = UDMH/LOX version of RD-254. Much higher performance, but requires cryogenic fuels. + specLevel = speculative + minThrust = 1951.6 + maxThrust = 1951.6 + massMult = 0.99074 + costOffset = 0 + PROPELLANT //1.78 + { + name = UDMH + ratio = 0.4476 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5524 + } + atmosphereCurve + { + key = 0 357.9 + key = 1 263 + } + } //Proton-M Blok-DM-2 (8K82K 11S861): 6 flights, 0 failures //Proton-M Blok-DM-03 (8K82K 11S861-03): 5 flights, 0 failures @@ -413,7 +706,7 @@ ignitionReliabilityEnd = 0.999289 cycleReliabilityStart = 0.995498 cycleReliabilityEnd = 0.999289 - techTransfer = RD-254-11D44-Mk4,RD-254-11D44-Mk3,RD-254-11D44-Mk2,RD-254-11D44:50 + techTransfer = RD-275,RD-254-11D44-Mk4,RD-253-Mk4,RD-254-11D44-Mk3,RD-253-Mk3,RD-254-11D44-Mk2,RD-253-Mk2,RD-254-11D44,RD-253,RD-221,RD-220:50 } } CONFIG @@ -439,7 +732,7 @@ atmosphereCurve { key = 0 327.8 - key = 1 242 + key = 1 245 } ullage = True @@ -451,6 +744,58 @@ name = ElectricCharge amount = 1.0 } + SUBCONFIG + { + name = RD-223M1-11D42M1 + description = UDMH/AK27 version of RD-254. Higher thrust, at the cost of efficiency. + specLevel = speculative + minThrust = 2010.0 + maxThrust = 2010.0 + massMult = 0.9839 + costOffset = 0 + PROPELLANT //2.94 + { + name = UDMH + ratio = 0.3973 + DrawGauge = True + } + PROPELLANT + { + name = AK27 + ratio = 0.6027 + } + atmosphereCurve + { + key = 0 314.8 + key = 1 236 + } + } + SUBCONFIG + { + name = RD-115M1-11D32M1 + description = UDMH/LOX version of RD-254. Much higher performance, but requires cryogenic fuels. + specLevel = speculative + minThrust = 2045.2 + maxThrust = 2045.2 + massMult = 0.99074 + costOffset = 0 + PROPELLANT //1.78 + { + name = UDMH + ratio = 0.4476 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.5524 + } + atmosphereCurve + { + key = 0 357.9 + key = 1 265 + } + } //Proton-M Briz-M (8K82KM 14S43) (Phase I mod. 1): 2 flights, 0 failures //Proton-M Briz-M (8K82KM 14S43) (Phase I mod. 2): 3 flights, 0 failures @@ -468,7 +813,7 @@ ignitionReliabilityEnd = 0.999663 cycleReliabilityStart = 0.997865 cycleReliabilityEnd = 0.999663 - techTransfer = RD-277-14D16,RD-254-11D44-Mk4,RD-254-11D44-Mk3,RD-254-11D44-Mk2,RD-254-11D44:50 + techTransfer = RD-275M,RD-277-14D16,RD-275,RD-254-11D44-Mk4,RD-253-Mk4,RD-254-11D44-Mk3,RD-253-Mk3,RD-254-11D44-Mk2,RD-253-Mk2,RD-254-11D44,RD-253,RD-221,RD-220:50 } } } diff --git a/GameData/RealismOverhaul/Engine_Configs/RD270M_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD270M_Config.cfg index b4a7941801..3364db7b39 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD270M_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD270M_Config.cfg @@ -29,16 +29,19 @@ // Notes: +// RD-270M has been changed to be a config for the RD-270. Also, the RD-270M didn't even exist, as detailed +// in RD-270 config. // ================================================== @PART[*]:HAS[#engineType[RD270M]]:FOR[RealismOverhaulEngines] { %title = #roRD270MTitle //RD-270M %manufacturer = #roMfrKBEnergomash - %description = #roRD270MDesc //Modification of the RD-270 to use highly toxic pentaborane as fuel. Although the M variant boasts higher thrust and isp, the fuel mixture is much, much more toxic than even UDMH. + %description = Deprecated, do not use @tags ^= :$: USSR kb energomash glushko rd-270 liquid pump booster pentaborane nto %specLevel = concept + RODeprecated = true @MODULE[ModuleEngines*] { @@ -67,6 +70,7 @@ { name = RD-270M specLevel = concept + RODeprecated = true minThrust = 6443.1 maxThrust = 7159 heatProduction = 225 diff --git a/GameData/RealismOverhaul/Engine_Configs/RD270_Config.cfg b/GameData/RealismOverhaul/Engine_Configs/RD270_Config.cfg index 2aa638df9a..76349c6821 100644 --- a/GameData/RealismOverhaul/Engine_Configs/RD270_Config.cfg +++ b/GameData/RealismOverhaul/Engine_Configs/RD270_Config.cfg @@ -4,8 +4,8 @@ // Manufacturer: NPO Energomash // // ================================================================================= -// RD-270 -// UR-900 +// RD-270 (8D420) +// UR-700 // // Dry Mass: 4470 Kg // Thrust (SL): 6272 kN @@ -16,26 +16,63 @@ // Propellant: NTO / UDMH // Prop Ratio: 2.67 // Throttle: 105% to 95% -// Nozzle Ratio: ??? +// Nozzle Ratio: 30.2 [5] 0.8 atm at nozzle exit +// Ignitions: 1 +// ================================================================================= +// RD-270M (8D420M) +// UR-700 +// +// Dry Mass: 4470 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 7159 kN +// ISP: 340 SL / 365 Vac +// Burn Time: ??? +// Chamber Pressure: 26.08 MPa +// Propellant: 98% HTP / PB-1 (94% Pentaborane, 6% T-1) +// Prop Ratio: 2.05? //based on proposed HTP/PB-1 conversion of RD-862 [6] +// Throttle: 105% to 95% +// Nozzle Ratio: 30.2? +// Ignitions: 1 +// ================================================================================= +// RD-116 ([5] 8D420K, [4] 11D120) +// UR-700M +// +// Dry Mass: 4800 Kg +// Thrust (SL): ??? kN +// Thrust (Vac): 6325.3 kN +// ISP: 310 SL / 333 Vac +// Burn Time: ??? +// Chamber Pressure: 20.0 MPa +// Propellant: LOX / RG-1 +// Prop Ratio: 2.65 +// Throttle: 105% to 95% +// Nozzle Ratio: 23.4 [5] 0.96 atm at nozzle exit // Ignitions: 1 // ================================================================================= // Sources: -// http://www.b14643.de/Spacerockets/Specials/Russian_Rocket_engines/engines.htm -// http://www.astronautix.com/r/rd-270.html -// http://www.lpre.de/energomash/RD-270/index.htm +// [1]http://www.b14643.de/Spacerockets/Specials/Russian_Rocket_engines/engines.htm +// [2]http://www.astronautix.com/r/rd-270.html +// [3]http://www.lpre.de/energomash/RD-270/index.htm +// [4]http://www.npoenergomash.ru/netcat_files/File/Table_of_Engines.docx +// [5]http://epizodsspace.airbase.ru/bibl/glushko/izbran-rab-glushko/1/04.html +// [6]http://epizodsspace.airbase.ru/bibl/glushko/izbran-rab-glushko/1/05.html +// [7]http://epizodyspace.ru/bibl/glushko/izbran-rab-glushko/1/03.html // Used by: // Notes: +// According to [4], RD-270 with sea level nozzle had a nozzle diameter of 2.37 m. Mounting hardware +// brought total diameter to 3.3 m, and total height to 4.85 m. Vacuum version had nozzle diameter of +// 3.06 m and height of 5.85 m. // ================================================== @PART[*]:HAS[#engineType[RD270]]:FOR[RealismOverhaulEngines] { %title = #roRD270Title //RD-270 %manufacturer = #roMfrKBEnergomash - %description = #roRD270Desc //The largest single-chamber engine ever built in the Soviet Union, the RD-270 was fueled by an NTO/UDMH mixture combined under some of the highest pressures ever encountered in an ignition chamber. Never flown but extensively tested. + %description = #roRD270Desc @tags ^= :$: USSR kb energomash glushko rd-270 liquid pump booster udmh nto @@ -62,11 +99,66 @@ name = ModuleEngineConfigs type = ModuleEngines origMass = 4.47 - configuration = RD-270 + configuration = RD-270-11D420 modded = false CONFIG { name = RD-270 + description = Deprecated, do not use this. + RODeprecated = true + specLevel = prototype + minThrust = 6041 + maxThrust = 6713 + heatProduction = 205 + PROPELLANT + { + name = UDMH + ratio = 0.4042 + DrawGauge = True + } + PROPELLANT + { + name = NTO + ratio = 0.5958 + } + atmosphereCurve + { + key = 0 322 + key = 1 301 + } + + ullage = True + ignitions = 1 + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + //no data, never flew + //using early RD-253 data + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 450 //same as Proton Uppers + ratedBurnTime = 148 + safeOverburn = true + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + ignitionReliabilityStart = 0.989829 + ignitionReliabilityEnd = 0.997966 + cycleReliabilityStart = 0.989829 + cycleReliabilityEnd = 0.997966 + techTransfer = RD-253-Mk3,RD-253-Mk2,RD-253:25 + } + } + CONFIG + { + name = RD-270-8D420 specLevel = prototype minThrust = 6041 maxThrust = 6713 @@ -117,5 +209,113 @@ techTransfer = RD-253-Mk3,RD-253-Mk2,RD-253:25 } } + CONFIG + { + name = RD-270M-8D420M + specLevel = altHist //Yeah this one is just an astronautix special. No original Russian source mentions a "RD-270M". Only mention of RD-270 and Pentaborane is as a 10 ton thrust upper stage engine, with the 11D420 mentioned later in that same sentence as a booster engine [7]. RD-270 designation was presumably used for a pentaborane upper stage concept before being assigned to the 11D420, leading to confusion. + minThrust = 6443.1 + maxThrust = 7159 + heatProduction = 205 + PROPELLANT + { + name = PB-1 + ratio = 0.5256 + DrawGauge = True + } + PROPELLANT + { + name = HTP + ratio = 0.4744 + } + atmosphereCurve + { + key = 0 365 + key = 1 340 + } + + ullage = True + ignitions = 1 + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + //no data, never flew + //using early RD-253 data + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 450 //same as Proton Uppers + ratedBurnTime = 148 + safeOverburn = true + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + ignitionReliabilityStart = 0.989829 + ignitionReliabilityEnd = 0.997966 + cycleReliabilityStart = 0.989829 + cycleReliabilityEnd = 0.997966 + techTransfer = RD-270-8D420:50&RD-253-Mk3,RD-253-Mk2,RD-253:25 + } + } + CONFIG + { + name = RD-116-8D420K + description = RD-270 converted to run on kerosene and liquid oxygen, proposed to replace N-1 first stage engines, or power UR-700M. + specLevel = concept + minThrust = 5692.8 + maxThrust = 6325.3 + heatProduction = 205 + massMult = 1.0738 + PROPELLANT + { + name = RG-1 + ratio = 0.3408 + DrawGauge = True + } + PROPELLANT + { + name = LqdOxygen + ratio = 0.6592 + } + atmosphereCurve + { + key = 0 333 + key = 1 310 + } + + ullage = True + ignitions = 1 + IGNITOR_RESOURCE + { + name = ElectricCharge + amount = 0.5 + } + + //no data, never flew + //using early RD-253 data + TESTFLIGHT:NEEDS[TestLite|TestFlight] + { + testedBurnTime = 450 //same as Proton Uppers + ratedBurnTime = 148 + safeOverburn = true + + // assume roughly exponential relationship between chamber pressure and lifespan + thrustModifier + { + key = 0.00 0.05 0 0 + key = 1.00 1.00 3 3 + } + ignitionReliabilityStart = 0.989829 + ignitionReliabilityEnd = 0.997966 + cycleReliabilityStart = 0.989829 + cycleReliabilityEnd = 0.997966 + techTransfer = RD-270-8D420:50&RD-270M-8D420M,RD-253-Mk3,RD-253-Mk2,RD-253:25 + } + } } } diff --git a/GameData/RealismOverhaul/Localization/en-us-Engines.cfg b/GameData/RealismOverhaul/Localization/en-us-Engines.cfg index e43b7a16d4..4345a2f560 100644 --- a/GameData/RealismOverhaul/Localization/en-us-Engines.cfg +++ b/GameData/RealismOverhaul/Localization/en-us-Engines.cfg @@ -385,7 +385,7 @@ Localization #roNK9VDesc = Staged combustion kerolox upper/vacuum engine. Designed by Kuznetsov for the Korolev GR-1 projet. Reused (as NK-19) on the N1, upgraded for the N1F with restart capability as NK-31. // NK33 #roNK33Title = NK-15/33 - #roNK33Desc = The NK-15 and NK-33 were originally built in the 1960s/early 1970s for the Soviet N1 and then N1F rocket, respectively. Though the N1F was scrapped, the engines survived. Aerojet acquired several NK-33 engines in the 1990s and refurbished them as AJ26-62 engines for Orbital Science's Antares launch vehicle. Modifications made by Aerojet included increasing rated thrust and equipping the engines to support gimballing. + #roNK33Desc = Soviet staged combustion booster engine. Developed as part of a Soviet initiative to build a 150 ton thrust booster engine for the N-1, the NK-15 was ultimately chosen to power the N-1, and the NK-33 developed to power the upgraded N-1F. Though the N-1F was scrapped, the engines survived. Aerojet acquired several NK-33 engines in the 1990s and refurbished them as AJ26-62 engines for Orbital Science's Antares launch vehicle. Modifications made by Aerojet included increasing rated thrust and equipping the engines to support gimballing. // NK43 #roNK43Title = NK-15V/43 #roNK43Desc = Originally designed and built for the N1F, the NK-43 is a derivative of the NK-33 with longer bell and restart capability for upper stages. @@ -525,6 +525,12 @@ Localization // RD219 #roRD219Title = RD-219 #roRD219Desc = A Soviet dual chamber gas generator engine. Designed in the late 1950s to use storable propellants for ICBMs because the cryogenic propellants in the current R-7 could not be stored for long periods, requiring lengthy fuelling before launch. Used on the R-16 and R-36 ICBMs, and Tsiklon-2 and Tsiklon-3 LVs. + // RD220 + #roRD220Title = RD-220/112 + #roRD220Desc = An early Soviet hypergolic staged combustion booster engine. Designed for the first stage of the enormous R-20 project, versions were designed using Nitric Acid or Liquid Oxygen as an oxidizer, with UDMH as fuel. Although it was never used, it formed the basis of the much more successful RD-253 used on Proton. + // RD221 + #roRD220Title = RD-221/113 + #roRD220Desc = An early Soviet hypergolic staged combustion vacuum engine. Designed for the second stage of the enormous R-20 project, versions were designed using Nitric Acid or Liquid Oxygen as an oxidizer, with UDMH as fuel. Although it was never used, it formed the basis of the much more successful RD-253 used on Proton. // RD0225 #roRD0225Title = RD-0225 #roRD0225Desc = Soviet pressure-fed vacuum engine. A pair were used as manuevering engines on the Almaz space stations. @@ -551,16 +557,16 @@ Localization #roRD0243Desc = Staged combustion booster engine module. Developed as the first stage engine of the R-29RM Submarine-Launched Ballistic Missile, the RD-0243 consists of an RD-0244 main engine and RD-0245 vernier engine. In order to save space, the engine is submerged within the fuel tank of the R-29RM, with the rear bulkhead of the missile welded to the engine nozzle. Also used on the Shtil' launch vehicle, a unique smallsat launcher capable of being deployed from Delta IV submarines. // RD253 #roRD253Title = RD-253/RD-275 - #roRD253Desc = A high thrust engine designed for use with storable propellants. In use with the Proton series of rockets. + #roRD253Desc = Soviet hypergolic staged combustion booster engine. Developed as part of a Soviet initiative to build a 150 ton thrust booster engine for the N-1, versions were created burning Nitric Acid, Nitrogen Tetroxide, or Liquid Oxygen with UDMH. Although the NK-15 was ultimately selected to power the N-1, the RD-253, using Nitrogen Tetroxide, was chosen to power the UR-500/Proton, becoming the workhorse of the Soviet space program. // RD254 #roRD254Title = RD-254 - #roRD254Desc = A high thrust staged combustion engine designed for use with storable propellants. The vacuum version of the Proton's RD-253 first stage engines, intended first as an upper stage engine for the N-1, and then as an upper stage engine for the UR-700. Tested, but ultimately cancelled with the UR-700. + #roRD254Desc = Soviet hypergolic staged combustion vacuum engine. Developed as part of a Soviet initiative to build a 150 ton thrust vacuum engine for the N-1, versions were created burning Nitric Acid, Nitrogen Tetroxide, or Liquid Oxygen with UDMH. Although the NK-15V was ultimately selected to power the N-1, the RD-254, using Nitrogen Tetroxide, was chosen to power the upper stages of the UR-700. Unlike it's sibling, the RD-253, the RD-254 was cancelled with the rest of the UR-700 project and never flew. // RD263 #roRD263Title = RD-263/RD-268 #roRD263Desc = A staged combustion hypergolic booster engine designed to replace the RD-250 engines used on the R-36. Also used for the MR-UR-100. // RD270 #roRD270Title = RD-270 - #roRD270Desc = The largest single-chamber engine ever built in the Soviet Union, the RD-270 was fueled by an NTO/UDMH mixture combined under some of the highest pressures ever encountered in an ignition chamber. Never flown but extensively tested. + #roRD270Desc = The largest single-chamber engine ever built in the Soviet Union, and the first engine to ever use full-flow staged combustion, the RD-270 was fueled by an NTO/UDMH mixture combined under some of the highest pressures ever encountered in an ignition chamber. Intended to power the first and second stages of the UR-700, it was cancelled with the rest of the UR-700 project, despite efforts to convert it to kerosene for use on the N-1 instead. Never flown but extensively tested. // RD270M #roRD270MTitle = RD-270M #roRD270MDesc = Modification of the RD-270 to use highly toxic pentaborane as fuel. Although the M variant boasts higher thrust and isp, the fuel mixture is much, much more toxic than even UDMH. diff --git a/GameData/RealismOverhaul/RO_RealFuels.cfg b/GameData/RealismOverhaul/RO_RealFuels.cfg index c78c7f99de..d8ba74eaf1 100644 --- a/GameData/RealismOverhaul/RO_RealFuels.cfg +++ b/GameData/RealismOverhaul/RO_RealFuels.cfg @@ -905,6 +905,7 @@ PARTUPGRADE &insulationConduction = 0.02 } %TANK[Pentaborane] {} //{ %temperature = 337.2 } //from https://pubchem.ncbi.nlm.nih.gov/compound/Pentaborane + %TANK[PB-1] {} //{ %temperature = 337.2 } //same as pentaborane? %TANK[RG-1] {} %TANK[CooledRG-1] {} %TANK[RP-1] {} diff --git a/GameData/RealismOverhaul/RO_Resources.cfg b/GameData/RealismOverhaul/RO_Resources.cfg index 7fc6f454d6..381d81a978 100644 --- a/GameData/RealismOverhaul/RO_Resources.cfg +++ b/GameData/RealismOverhaul/RO_Resources.cfg @@ -69,7 +69,23 @@ RESOURCE_DEFINITION transfer = PUMP isTweakable = True isVisible = true - ksparpicon = RealFuels/Resources/ARPIcons/ASCENT + ksparpicon = RealFuels/Resources/ARPIcons/MHF3 +} + +//Create PB-1 (Pentaborane Mix 1, 94% Pentaborane, 6% T-1 by weight) +//PB-1 +RESOURCE_DEFINITION +{ + name = PB-1 + density = 0.0006301 //weighted average of Pentaborane and Kerosene? + unitCost = 0.0001 //placeholder + hsp = 2336 //assume same as pentaborane + conductivity = 0.16074 + flowMode = STACK_PRIORITY_SEARCH + transfer = PUMP + isTweakable = True + isVisible = true + ksparpicon = RealFuels/Resources/ARPIcons/PB-1 } //Create core material