Propulsion Functions

Propulsion Module

Directory List

Chemical Demos/Chemical Demos/Electric
Demos/Utilities Electric Gas
MultiStage Nuclear Rocket
Utilities


Chemical

Design an upper stage.
Computes molecular weight, ratio of specific heats and gas constant for
The lower heating value for fuels.
The lower heating value for a hydrocarbon fuel.
The lower heating value for H2 + 1/2 O2 -> H20.
H2/O2 rocket model.

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Demos/Chemical

Demonstrate cold gas propulsion
Demonstrate thruster design
Design a propulsion system for a low-earth orbit satellite
Demonstrate blow down. Most satellites use unregulated blowdown systems.
Demonstrate a solid rocket motor.

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Demos/Electric

Generate the optimal electric propulsion system.

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Demos/Utilities

Layout thrusters for the Orion capsule.

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Electric

Outputs atomic mass.
Convert electron volts to velocity.
Design a electric powered transfer vehicle.
Design an electric propulsion system.
Computes the total mass, fuel mass and power for an electric thruster.
Create a PPPL Hall thruster array picture.
Convert keV to J.
Finds an electric thrust propelled optimal vehicle.
Computes the thrust and specific impulse of an electric thruster.
Design an electric transfer vehicle.
Convert velocity to electron volts.

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Gas

Computes the area ratio from Mach Number.
Generates a blowdown curve of mass vs. pressure.
Computes the combustion temperature of a gas mixture.
Computes the ratio of specific heats of a gas mixture.
Generates a blowdown curve of mass vs. pressure.
Computes isentropic expansion.
Computes the Mach number from area ratio. The throat is at Mach 1.
Compute the Mach number
Computes the molecular weight of a gas mixture.
Compute the speed of sound.
Generates the final pressure

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MultiStage

Converts structural and payload ratios into masses.
Payload and structural mass ratios for parallel stages.
Converts masses to structural and payload ratios.
Converts total, final and payload masses to stage masses and ratios.
Converts stage and payload masses to total masses and final masses.
Computes the multistage tradeoff ratios.

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Nuclear

Compute the exhaust velocity for a nuclear rocket with H2 fuel.

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Rocket

Determines performance of a cold gas rocket.
Computes the thrust and exhaust velocity for an ideal rocket.
Compute specific impulse from exhaust velocity
Computes the constant mass that will produce the same delta-V.
Finds the minimum exhaust velocity based on the structural ratio.
Compute the plume forces and torques on a set of elemental areas.
Computes the thrust and exhaust velocity of a chemical rocket.
Computes the thrust and exhaust velocity as a function of pressure.
Compute masses for a single stage to produce the required delta-v.
Computes the thrust and exhaust velocity given one pair [uE0,t0].
Computes the right hand side of the dynamical equations for a solid
Computes the inertia and inertia derivative for a solid rocket.
Computes the ideal thrust coefficient for a nozzle with a diverging portion.
Computes throat area (A*) for a given thrust
Computes the ideal exhaust velocity of a rocket.
Computes the exhaust velocity of a O2/H2 rocket.
Computes the exhaust velocity of a rocket from fuel lower heating
Compute specific impulse from exhaust velocity
Computes the dimensions of a tank. Four types may be entered:

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Utilities

The rocket equation including special relativity.
Compute the height of fuel in a spherical fuel tank.
Tool for thruster layout.

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SVN Revision: 42425


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