Propulsion Module 

DesignUpperStage  Design an upper stage using RocketMass and create a CAD model. 
Fuels  Computes molecular weight, ratio of specific heats and gas constant 
MassVolH2O2  H2/O2 mass and volume. 
QRFuel  The lower heating value for fuels. 
QRHydrocarbon  The lower heating value for a hydrocarbon fuel. 
QRHydrogen  The lower heating value for H2 + 1/2 O2 > H20. 
RocketH2O2  H2/O2 rocket model. 
ColdGasDemo  Demonstrate cold gas propulsion 
DesignThruster  Demonstrate thruster design 
PropulsionSystemDesignLEO  Design a propulsion system for a lowearth orbit satellite 
TBlodown  Demonstrate blow down. Most satellites use unregulated blowdown systems. 
TSolid  Demonstrate a solid rocket motor. 
ElectricPropulsionDemo  Design an electric powered transfer vehicle. 
OptimalElectricSpacecraft  Generate the optimal electric propulsion system for a given deltaV. 
OrionPropulsionDesign  Layout thrusters for the Orion capsule. 
EVToV  Convert electron volts to velocity. 
ElectricPropulsionDesign  Design an electric propulsion system. 
ElectricThrust  Compute the electric propulsion thrust from power and specific impulse. 
ElectricThrusterPower  Compute the electric propulsion power from thrust and specific impulse. 
FElectricPropulsion  Computes the total mass, fuel mass and power for an electric thruster. 
HallThrusterArray  Create a PPPL Hall thruster array picture. 
KEVToJ  Convert keV to J. 
OptimalVehicle  Finds an electric thrust propelled massoptimal vehicle. 
SpecificPower  Computes the specific power of engine/power plant combinations 
TElec  Computes the thrust and specific impulse of an electric thruster. 
TVDesign  Design an electric transfer vehicle from deltaV. 
VToEV  Convert velocity to electron volts. 
AreaRatioFromMach  Computes the area ratio from Mach Number. 
BloDownMass  Generates a blowdown curve of mass vs pressure. 
CombTemp  Computes the combustion temperature of a gas mixture. 
Gamma  Computes the ratio of specific heats of a gas mixture. 
GasMass  Generates a blowdown curve of mass vs pressure. 
IsentropicExpansion  Computes isentropic expansion. 
MachFromAreaRatio  Computes the Mach number from area ratio. The throat is at Mach 1. 
MachNumber  Compute the Mach number 
MolWt  Computes the molecular weight of a gas mixture. 
SpeedSnd  Compute the speed of sound. 
VolumeToPressureBD  Generates the final pressure 
EP2M  Converts structural and payload ratios into masses. 
EPPS  Payload and structural mass ratios for parallel stages. 
M2EP  Converts masses to structural and payload ratios. 
M2MS  Converts total, final and payload masses to stage masses and ratios. 
MS2M  Converts stage and payload masses to total masses and final masses. 
MSTOR  Computes the multistage tradeoff ratios. 
NuclearThermalUE  Compute the exhaust velocity for a nuclear rocket with H2 fuel. 
ColdGas  Determines performance of a cold gas rocket. 
IdealRkt  Computes the thrust and exhaust velocity for an ideal rocket. 
Isp2V  Compute specific impulse from exhaust velocity 
MassEquivalentDV  Computes the constant mass that will produce the same deltaV. 
MinimumExhaustVelocity  Finds the minimum exhaust velocity based on the structural ratio. 
Plume  Compute the plume forces and torques on a set of elemental areas. 
RocketChemical  Computes the thrust and exhaust velocity of a chemical rocket. 
RocketFromUEAndT  Computes the thrust and exhaust velocity as a function of pressure. 
RocketMass  Compute masses for a single stage to produce the required deltav. 
RocketVariableUEAndT  Computes the thrust and exhaust velocity given one pair [uE0,t0]. 
SolidR  Computes the right hand side of the dynamical equations for a solid rocket engine 
SolidRocketInertia  Computes the inertia and inertia derivative for a solid rocket. 
TCoeff  Computes the ideal thrust coefficient for a nozzle with a diverging portion. 
ThrustToAStar  Computes throat area (A*) for a given thrust 
UE  Computes the ideal exhaust velocity of a rocket. 
UEO2H2  Computes the exhaust velocity of a O2/H2 rocket. 
UEQR  Computes the exhaust velocity of a rocket from fuel lower heating value 
V2Isp  Compute specific impulse from exhaust velocity 
VolumeToDimension  Computes the dimensions of a tank. Four types may be entered: 
RocketEquationRelativistic  The rocket equation including special relativity. 
SphericalTankFluidHeight  Compute the height of fuel in a spherical fuel tank. 
ThrusterLayout  Tool for thruster layout. 
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