Path: Orbit/StraightLine
% Compute thrust for a minimum mass trajectory, with a fixed uE
The power is calculated from the thrust and thrust efficiency.
The engine mass is calculated from the specific power.
P = 0.5 T*uE/eta
mE = P/sigma
The total mass is
m0 = mP + (1 + f)*mF + mE
where mP is the mass of the payload, f is the fuel structural fraction,
and mE is the mass of the engine.
Type StraightLineOptimalFixedUE for a demo.
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Form:
d = StraightLineOptimalFixedUE( d0 )
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Inputs
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d0 (.) Data structure
See StraightLineDataStructure
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Outputs
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d (.) Results data structure
.thrust (1,1) Thrust (N)
.p (1,1) Power (W)
.mD (1,1) Dry mass (kg)
.mF (1,1) Fuel mass (kg)
.dV (1,1) Delta-V (km/s)
.dF (1,1) Final distance achieved (km)
.vF (1,1) Final velocity achieved (km/s)
.tS (1,1) Switch time
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See also StraightLineConstantThrust
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AC: ACData/ACTConstants Orbit: StraightLine/SimulateStraightLineTrajectory Orbit: StraightLine/StraightLineConstantThrust Orbit: StraightLine/StraightLineDataStructure Orbit: StraightLine/SwitchTime Orbit: StraightLine/UToMF SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/SwooshWatermark Common: CommonData/xSplashSmall Common: Database/Constant Common: General/CellToMat Common: General/DeleteCell Common: General/MatToCell Common: General/Watermark Common: Graphics/DistanceLabel Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Math: Integration/RK4
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