Propulsion Module

Directory List

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 low-earth 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 delta-V.

Artemis Launch Analysis

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.
HallThrusterEfficiency	Hall thruster efficiency model with random walk
KEVToJ	Convert keV to J.
OptimalVehicle	Finds an electric thrust propelled mass-optimal 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 delta-V.
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.

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 delta-V.
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 delta-v.
RocketModel	Generic rocket model as a function of altitude.
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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