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Path: Propulsion/Chemical
% Design an upper stage.
Creates four components, oxidizer tank, fuel tank, shell and engine
nozzle. The origin is at the base of the nozzle.
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Form:
g = DesignUpperStage( d, fileName )
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Inputs
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d (.) Data structure
.name (1,:) Model name
.mR (1,1) Mixture ratio fuel/oxidizer
.sR (1,1) Structural ratio
.mF (1,1) Fixed mass including payload
.rhoO (1,1) Density oxidizer
.rhoF (1,1) Density fuel
.iSp (1,1) Specific impulse
.dV (1,1) Delta-V (km/s)
.nD (1,1) Nozzle diameter
.nL (1,1) Nozzle Length
.eR (1,1) Nozzle exit ratio
.aR (1,1) Vehicle length/width
fileName (1,:) Create an obj file filename.obj
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Outputs
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g (1,1) CAD data structure
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AeroUtils: CAD/BuildCADModel AeroUtils: CAD/CreateBody AeroUtils: CAD/CreateComponent AeroUtils: CAD/ExportOBJ Propulsion: Rocket/RocketMass
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