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Add more apogee motors (#2968)
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* Add manufacturer to X-1 cockpit

* Update sources, add SVM1/2

* Create SR28_Config.cfg

* Star-20A, SVM-4/5, FW-5

* Update FW5.cfg

* Star-12, Star-13D, and minor fixes
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@Capkirk123
Capkirk123 authored Jun 19, 2024
1 parent 7a37e20 commit 7830f68
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47 changes: 24 additions & 23 deletions GameData/RealismOverhaul/Engine_Configs/AltairIII_Config.cfg
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@@ -1,46 +1,46 @@
// ==================================================
// Altair III (FW4S)
// Altair III (FW-4S, SR57-UT-1, Star 20)
//
// Manufacturer: United Aircraft
//
// =================================================================================
// Altair III
// FW-4S
// FW-4S, SR57-UT-1, Star 20
//
// Dry Mass: 23.16585 kg
// Dry Mass: 23.75 kg based on average expended mass from [1]
// Thrust (SL): ??? kN
// Thrust (Vac): 25.227 kN
// ISP: ??? SL / 284.5 Vac
// Burn Time: 31.5
// Chamber Pressure: 5.92 MPa
// Propellant: CTPB
// Thrust (Vac): 29.36 kN (26.29 kN average) [2]
// ISP: ??? SL / 284.22 Vac average of [1]
// Burn Time: 32 maximum manufacturer-specified action time [1]
// Chamber Pressure: 5.49 MPa [2]
// Propellant: PBAN [2]
// Prop Ratio: N/A
// Throttle: N/A
// Nozzle Ratio: ???
// Nozzle Ratio: 53 [2]
// Ignitions: 1
// =================================================================================

// Sources:

// Source: NASA CR-145136 Scout Nozzle Data Book: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19770010201.pdf
// Source 1: NASA CR-165950 Scout Launch Vehicle Final Report.PDF)
// Source 2: Performance of a UTC FW-4S Solid-Propellant Rocket Motor
// https://apps.dtic.mil/dtic/tr/fulltext/u2/a002149.pdf
// [1] NASA CR-165950 Scout Launch Vehicle Final Report.PDF)
// [2] https://apps.dtic.mil/sti/citations/ADA002149
// [3] https://ntrs.nasa.gov/api/citations/19720026092/downloads/19720026092.pdf

// Used by:

// Notes:

// Fiber-wound casing
// Dimensions: 1.484122 x 0.508 m
// Propellant Mass: 274.4232 kg
// Expended weight: 275.62 kg
// ===============================================================
@PART[*]:HAS[#engineType[Altair-III]]:FOR[RealismOverhaulEngines]
{
@title = #roAltair-IIITitle //Altair III FW-4S
@manufacturer = #roMfrUA
@description = #roAltair-IIIDesc //A small solid kick motor. Developed from the Altair, this final version was used on later Scout B launch vehicles. It was used to circularize at apogee or perform a final payload kick. Maximum thrust 25.6kN, burn time 31 seconds.

@tags ^= :$: USA united aircraft united technologies star 20 altair iii 3 fw-4s te-m-640-1 solid upper pban
@tags ^= :$: USA united aircraft united technologies star 20 altair iii 3 fw-4s sr57 solid upper pban

%specLevel = operational

Expand All @@ -60,14 +60,14 @@
{
name = ModuleFuelTanks
type = PBAN
volume = 154.8664
volume = 155.54
basemass = -1

TANK
{
name = PBAN
amount = 154.8664
maxAmount = 154.8664
amount = 155.54
maxAmount = 155.54
}
}

Expand All @@ -78,13 +78,14 @@
configuration = Altair-III
modded = false

origMass = 0.0232
origMass = 0.02375
CONFIG
{
name = Altair-III
description = A.K.A FW-4S, SR57-UT-1 or Star 20
specLevel = operational
minThrust = 31
maxThrust = 31
minThrust = 29.36
maxThrust = 29.36
heatProduction = 100
PROPELLANT
{
Expand All @@ -94,7 +95,7 @@
}
atmosphereCurve
{
key = 0 284.5
key = 0 284.22
key = 1 200
}
// guesses (note: max is above nominal * thrust_curve_max)
Expand Down Expand Up @@ -141,7 +142,7 @@
// 73 cycles, 1 failures
TESTFLIGHT:NEEDS[TestLite|TestFlight]
{
ratedBurnTime = 31
ratedBurnTime = 32
ignitionReliabilityStart = 0.970444
ignitionReliabilityEnd = 0.995333
cycleReliabilityStart = 0.970045
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151 changes: 151 additions & 0 deletions GameData/RealismOverhaul/Engine_Configs/FW5_Config.cfg
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// ==================================================
// FW-5
//
// Manufacturer: United Aircraft
//
// =================================================================================
// FW-5
// HS-333
//
// Dry Mass: 28.57 kg (expended weight) [1]
// Thrust (SL): ??? kN
// Thrust (Vac): 24.91 kN (22.51 kN average) [1]
// ISP: ??? SL / 284.8 Vac
// Burn Time: 39
// Chamber Pressure: 6.25 MPa
// Propellant: PBAN
// Prop Ratio: N/A
// Throttle: N/A
// Nozzle Ratio: 60
// Ignitions: 1
// =================================================================================

// Sources:

// [1] https://ntrs.nasa.gov/api/citations/19720026092/downloads/19720026092.pdf
// [2] https://www.planet4589.org/space/book/lv/engines/motorlist/fw5.html
// [3] https://www.planet4589.org/space/book/lv/engines/kick/USMOTORSINTHE1960S.html

// Used by:

// Notes:

// Fiber-wound casing
// Propellant Mass: 263.99 kg
// ===============================================================
@PART[*]:HAS[#engineType[FW5]]:FOR[RealismOverhaulEngines]
{
@title = #roFW5Title //FW-5
@manufacturer = #roMfrUA
@description = #roFW5Desc

@tags ^= :$: USA united aircraft united technologies fw5 fw-5 solid upper pban

%specLevel = operational

!MODULE[ModuleGimbal] {}
!MODULE[ModuleFuelTanks],* {}
!MODULE[ModuleAlternator],*{}
!RESOURCE,*{}

@MODULE[ModuleEngines*]
{
%EngineType = SolidBooster
%allowShutdown = False
%throttleLocked = True
}

MODULE
{
name = ModuleFuelTanks
type = PBAN
volume = 148.98
basemass = -1

TANK
{
name = PBAN
amount = 148.98
maxAmount = 148.98
}
}

MODULE
{
name = ModuleEngineConfigs
type = ModuleEngines
configuration = FW-5
modded = false

origMass = 0.02857
CONFIG
{
name = FW-5
specLevel = operational
minThrust = 24.91
maxThrust = 24.91
heatProduction = 100
PROPELLANT
{
name = PBAN
ratio = 1
DrawGauge = True
}
atmosphereCurve
{
key = 0 284.8
key = 1 150
}
// guesses (note: max is above nominal * thrust_curve_max)
// Same as FW-4S?
curveResource = PBAN
thrustCurve
{
key = 1.00000 0.66667 -5.20777 0.00000
key = 0.98656 0.73333 -4.73446 -4.73536
key = 0.97184 0.80000 -4.34000 -4.34063
key = 0.95584 0.86667 -4.00621 -4.00667
key = 0.93856 0.93333 0.31002 -3.72043
key = 0.88528 0.91667 0.31566 0.31566
key = 0.83296 0.90000 -0.57870 0.32150
key = 0.77429 0.93333 -0.55803 -0.55804
key = 0.71349 0.96667 -0.53879 -0.53880
key = 0.65056 1.00000 0.00000 -0.52084
key = 0.45856 1.00000 0.69445 0.00000
key = 0.41136 0.96667 0.71839 0.71839
key = 0.36576 0.93333 0.74405 0.74404
key = 0.32176 0.90000 0.77161 0.77160
key = 0.27936 0.86667 0.50080 0.80128
key = 0.24640 0.85000 0.51062 0.51062
key = 0.21408 0.83333 0.00000 0.52083
key = 0.15008 0.83333 1.04168 0.00000
key = 0.11872 0.80000 0.81381 1.08506
key = 0.08848 0.77500 0.84006 0.84005
key = 0.05920 0.75000 6.75379 0.86805
key = 0.04573 0.65278 7.76113 7.75451
key = 0.03413 0.55556 9.12262 9.10984
key = 0.02440 0.45833 11.06643 11.03824
key = 0.01653 0.36111 14.07522 13.99902
key = 0.01053 0.26389 19.40953 19.11637
key = 0.00640 0.16667 13.12500 30.03214
key = 0.00284 0.11111 20.25463 19.37500
key = 0.00071 0.05556 50.48073 37.61574
key = 0.00000 0.01000 0.00000 139.51675
}

// 12 flown with 0 failures
TESTFLIGHT:NEEDS[TestLite|TestFlight]
{
ratedBurnTime = 39
ignitionReliabilityStart = 0.942308
ignitionReliabilityEnd = 0.988462
cycleReliabilityStart = 0.942308
cycleReliabilityEnd = 0.988462
techTransfer = Altair-III,Altair-II,Altair:50
reliabilityDataRateMultiplier = 2

isSolid = True
}
}
}
}
130 changes: 130 additions & 0 deletions GameData/RealismOverhaul/Engine_Configs/SR28_Config.cfg
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// ==================================================
// SR28-JPL-3
//
// Manufacturer: JPL
//
// =================================================================================
// SR28-JPL-3
// ATS 1/2/3?
//
// Dry Mass: 41.37 kg (loaded weight 860 lbs - expended weight) [1]
// Thrust (SL): ??? kN
// Thrust (Vac): 27.06 kN (24.46 kN average) [1]
// ISP: ??? SL / 278.0 Vac [1]
// Burn Time: 45 total burn time, action time ~42.8 seconds [1]
// Chamber Pressure: 1.79 MPa peak [2]
// Propellant: PUPE JPL-540 used polyurethane binder [3]
// Prop Ratio: N/A
// Throttle: N/A
// Nozzle Ratio: 35 [2]
// Ignitions: 1
// =================================================================================

// Sources:

// [1] https://apps.dtic.mil/sti/citations/tr/AD0802218
// [2] https://ntrs.nasa.gov/api/citations/19720026092/downloads/19720026092.pdf
// [3] https://ntrs.nasa.gov/api/citations/19680012396/downloads/19680012396.pdf

// Used by:

// Notes:

// -1 uses steel case, -3 uses titanium
// total expended mass 348.72 kg
// ==================================================
@PART[*]:HAS[#engineType[SR28]]:FOR[RealismOverhaulEngines]
{
%title = #roSR28Title //SR28
%manufacturer = #roMfrJPL
%description = #roSR28Desc

@tags ^= :$: USA jpl jet propulsion laboratory sr28 sr-28 solid srm upper pupe

%specLevel = operational

@MODULE[ModuleEngines*]
{
%EngineType = SolidBooster
%allowShutdown = False
%throttleLocked = True
%exhaustDamage = True
}

!MODULE[ModuleEngineConfigs],*{}
!MODULE[ModuleAlternator],*{}
!RESOURCE,*{}
!MODULE[ModuleFuelTanks],*{}

!MODULE[ModuleGimbal],*{}

MODULE
{
name = ModuleFuelTanks
volume = 197.02
type = PUPE
basemass = -1
TANK
{
name = PUPE
amount = 197.02
maxAmount = 197.02
}
}

MODULE
{
name = ModuleEngineConfigs
type = ModuleEngines
configuration = SR28-JPL-3
modded = false
origMass = 0.04137
CONFIG
{
name = SR28-JPL-3
specLevel = operational
minThrust = 27.06
maxThrust = 27.06
heatProduction = 100
PROPELLANT
{
name = PUPE
ratio = 1.0
DrawGauge = True
}
atmosphereCurve
{
key = 0 278.0
key = 1 150
}
curveResource = PUPE
//Estimated from [1]
thrustCurve
{
key = 0 0.03 19 19
key = 0.03 0.6 11.57143 11.57143
key = 0.1 0.89 2.871429 2.871429
key = 0.15 0.97 0.9250003 0.9250003
key = 0.27 1 0.02499983 0.02499983
key = 0.52 0.95 -0.4333333 -0.4333333
key = 0.73 0.81 -0.8333334 -0.8333334
key = 0.89 0.65 -1.269231 -1.269231
key = 0.955 0.55 -2.880341 -2.880341
key = 1 0.36 -4.22222 -4.22222
}

//ATS-1: 1 flight, 0 failures
//ATS-3: 1 flight 0 failures
//Using Star-13E data I guess
TESTFLIGHT:NEEDS[TestLite|TestFlight]
{
ratedBurnTime = 45
ignitionReliabilityStart = 0.985849
ignitionReliabilityEnd = 0.997170
cycleReliabilityStart = 0.985849
cycleReliabilityEnd = 0.997170
isSolid = True
}
}
}
}
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