Propulsion Module |
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Directory List
Chemical
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. |
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Demos/Chemical
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Demos/Electric
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Demos/Rocket
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Demos/Utilities
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Electric
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Gas
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MultiStage
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. |
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Nuclear
NuclearThermalUE |
Compute the exhaust velocity for a nuclear rocket with H2 fuel. |
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Rocket
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: |
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Utilities
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