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NTR overhaul #2888

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Aug 6, 2023
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NTR overhaul #2888

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212 changes: 196 additions & 16 deletions GameData/RealismOverhaul/Engine_Configs/Nuclear_Engine_Configs/BNTR25k_Config.cfg
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Original file line number Diff line number Diff line change
Expand Up @@ -4,28 +4,78 @@
// Manufacturer: Aerojet Rocketdyne
//
// =================================================================================
// BNTR
// BNTR-25k
// Hydrogen Mode
//
// Dry Mass: 3670 kg
// Dry Mass: 3670 kg [4] TWR 3
// Thrust (SL): ??? kN
// Thrust (Vac): 111.6 kN
// ISP: 380 SL / 894 Vac
// Burn Time: 3600/56700 1.75 hrs burn/mission * 9 mission expected lifetime
// Chamber Pressure: 6.89 MPa
// Thrust (Vac): 111.6 kN [4]
// ISP: 1 SL / 894 Vac [4] sl calculated with RPA
// Burn Time: 3600/56700 [4] 1.75 hrs burn/mission * 9 mission expected lifetime
// Chamber Pressure: 6.89 MPa [4] 1000 psi
// Chamber Temp: 2650 K [4] 4770 R
// Propellant: LH2
// Prop Ratio: N/A
// Throttle: N/A
// Nozzle Ratio: 389
// Ignitions: 60
// Nozzle Ratio: 389 [4]
// Ignitions: 60?
// =================================================================================
// TRITON
// Bipropellant mode
//
// Dry Mass: 3670 Kg
// Thrust (SL): ??? kN
// Thrust (Vac): 305.04 kN [1] same increase as 15klbf BNTR
// ISP: 25 SL / 626 Vac calculated with RPA
// Burn Time: ???
// Chamber Pressure: 6.89 MPa [4] 1000 psi
// Chamber Temp: 2650 K [4] 4770 R
// Propellant: LOX / LH2
// Prop Ratio: 3.0 from [1]
// Throttle: N/A
// Nozzle Ratio: 389 [4]
// Ignitions: 60?
// =================================================================================
// BNTR-25k-Ammonia
// Speculative Ammonia config
//
// Dry Mass: 3670 kg [4] TWR 3
// Thrust (SL): ??? kN
// Thrust (Vac): 226.24 kN assuming constant power
// ISP: 1 SL / 441 Vac calculated with RPA
// Burn Time: 3600/56700 [4] 1.75 hrs burn/mission * 9 mission expected lifetime
// Chamber Pressure: 6.89 MPa [4] 1000 psi
// Chamber Temp: 2650 K [4] 4770 R
// Propellant: LNH3
// Prop Ratio: N/A
// Throttle: N/A
// Nozzle Ratio: 389 [4]
// Ignitions: 60?
// =================================================================================
// BNTR-25k-Methane
// Speculative "Methane" config
// Methane/Ammonia mix prevents coking and gets better Isp
//
// Dry Mass: 3670 kg [4] TWR 3
// Thrust (SL): ??? kN
// Thrust (Vac): 204.03 kN assuming constant power
// ISP: 6 SL / 489 Vac calculated with RPA
// Burn Time: 3600/56700 [4] 1.75 hrs burn/mission * 9 mission expected lifetime
// Chamber Pressure: 6.89 MPa [4] 1000 psi
// Chamber Temp: 2650 K [4] 4770 R
// Propellant: LNH3/LCH4
// Prop Ratio: 2.33 NH3/CH4
// Throttle: N/A
// Nozzle Ratio: 389 [4]
// Ignitions: 60?
// =================================================================================

// Sources:

// "Bimodal" Nuclear Thermal Rocket (BNTR) Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20040182399.pdf
// AIAA - TRITON (TRImodal Thrust Optimized Nuclear rocket engine): http://alternatewars.com/BBOW/Space_Engines/AIAA-2004-3863_TRITON.pdf
// Crewed Mars Mission using Bimodal Nuclear Thermal Electric Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140009579.pdf
// LEU NTP Engine System Trades and Mission Options http://anstd.ans.org/NETS-2019-Papers/Track-2--Mission-Concepts-and-Logistics/abstract-29-0.pdf
// [1]"Bimodal" Nuclear Thermal Rocket (BNTR) Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20040182399.pdf
// [2]AIAA - TRITON (TRImodal Thrust Optimized Nuclear rocket engine): http://alternatewars.com/BBOW/Space_Engines/AIAA-2004-3863_TRITON.pdf
// [3]Crewed Mars Mission using Bimodal Nuclear Thermal Electric Propulsion: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140009579.pdf
// [4]LEU NTP Engine System Trades and Mission Options http://anstd.ans.org/NETS-2019-Papers/Track-2--Mission-Concepts-and-Logistics/abstract-29-0.pdf

// Used by:

Expand Down Expand Up @@ -71,7 +121,7 @@
modded = False
origMass = 3.470 //3670 kg - 200 kg fuel

primaryDescription = Hydrogen NTR
primaryDescription = NTR
secondaryDescription = LOX-Augmented NTR
toPrimaryText = Disable Thrust Augmentation
toSecondaryText = Engage Thrust Augmentation
Expand Down Expand Up @@ -113,8 +163,11 @@
atmosphereCurve
{
key = 0 894
key = 1 300
key = 1 1
}
%chamberNominalTemp = 2650
%maxEngineTemp = 3100

//LANTR was abandonded by this point, but why not add it anyway...
SUBCONFIG
{
Expand Down Expand Up @@ -147,8 +200,8 @@

atmosphereCurve
{
key = 0 620
key = 1 320
key = 0 626
key = 1 25
}
}
TESTFLIGHT:NEEDS[TestLite|TestFlight]
Expand All @@ -169,6 +222,133 @@
techTransfer = BNTR:20
}
}
CONFIG
{
name = BNTR25k-Ammonia
description = Speculative version using Ammonia as propellant. No LOX-Augmentation on account of poor performance.
specLevel = speculative
minThrust = 226.24
maxThrust = 226.24
massMult = 1.0
throttleResponseRate = 0.055 // Should be around 30 seconds to ramp up from 0% thrust to 100% thrust.

ullage = True
pressureFed = False
ignitions = 60

IGNITOR_RESOURCE
{
name = ElectricCharge
amount = 0.5
}

PROPELLANT
{
name = LqdAmmonia
ratio = 1.0
DrawGauge = True
}

PROPELLANT
{
name = UraniumNitride
ratio = 1.0813e-15
DrawGauge = False
ignoreForIsp = True
}

atmosphereCurve
{
key = 0 441
key = 1 1
}
%chamberNominalTemp = 2650
%maxEngineTemp = 3100

TESTFLIGHT:NEEDS[TestLite|TestFlight]
{
ratedContinuousBurnTime = 3600
ratedBurnTime = 56700

explicitDataRate = True
ignitionReliabilityStart = 0.99
ignitionReliabilityEnd = 0.999997
ignitionDynPresFailMultiplier = 0.1
cycleReliabilityStart = 0.999
cycleReliabilityEnd = 0.999997
reliabilityMidV = 0.8
reliabilityMidH = 0.1
reliabilityMidTangentWeight = 0

techTransfer = BNTR:20
}
}
CONFIG
{
name = BNTR25k-Methane
description = Speculative version using Methane-Ammonia mix as propellant. No LOX-Augmentation on account of poor performance.
specLevel = sciFi //I don't know if RPA actually calculates this mixture dissociation correctly
minThrust = 204.03
maxThrust = 204.03
massMult = 1.0
throttleResponseRate = 0.055 // Should be around 30 seconds to ramp up from 0% thrust to 100% thrust.

ullage = True
pressureFed = False
ignitions = 60

IGNITOR_RESOURCE
{
name = ElectricCharge
amount = 0.5
}

PROPELLANT
{
name = LqdAmmonia
ratio = 0.5858
}
PROPELLANT
{
name = LqdMethane
ratio = 0.4142
DrawGauge = True
}

PROPELLANT
{
name = UraniumNitride
ratio = 1.0813e-15
DrawGauge = False
ignoreForIsp = True
}

atmosphereCurve
{
key = 0 489
key = 1 6
}
%chamberNominalTemp = 2650
%maxEngineTemp = 3100

TESTFLIGHT:NEEDS[TestLite|TestFlight]
{
ratedContinuousBurnTime = 3600
ratedBurnTime = 56700

explicitDataRate = True
ignitionReliabilityStart = 0.99
ignitionReliabilityEnd = 0.999997
ignitionDynPresFailMultiplier = 0.1
cycleReliabilityStart = 0.999
cycleReliabilityEnd = 0.999997
reliabilityMidV = 0.8
reliabilityMidH = 0.1
reliabilityMidTangentWeight = 0

techTransfer = BNTR:20
}
}
}

MODULE
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