Path: Orbit/StraightLine
% Fuel mass for a constant accel/power electric propulsion system
Assumes constant power and constant acceleration. The spacecraft slows to zero
velocity at its target. This uses a straight line model. This model assumes
power is constant. This means exhaust velocity increases as the mass drops.
There are two cases in the demo, one for a flyby mission and one for a
rendezvous.
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Form:
d = MassFuelElectricConstantPower(d0)
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Inputs
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d0 (.) Data structure
See StraightLineDataStructure
.mis '' Mission type, 'flyby' or 'stop'
.p (1) Power (W)
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Outputs
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d (.) Data structure with updated fields
.a (1) Acceleration (km/s2)
.mF (1) Fuel mass (kg)
.thrust (1) Thrust (N)
.uE (1) Exhaust velocity (N)
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See also MassFuelElectricConstantUE
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AC: ACData/ACTConstants Orbit: StraightLine/StraightLineConstantAccel Orbit: StraightLine/StraightLineDataStructure 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/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Math: Integration/RK4
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