Path: Orbit/StraightLine
% Calculate masses for a spacecraft with an electric propulsion system.
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Form:
[m0, mF, mE, p] = UToMF( thrust, uE, d )
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Inputs
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thrust (1,1) Thrust (N)
uE (1,1) Exhaust velocity (km/s)
d (.) Data structure
.tF (1,1) Duration (s)
.eta (1,1) Power fraction converted to thrust
.mP (1,1) Payload mass (kg)
.sigma (1,1) Specific power (W/kg)
.f (1,1) Fuel tank fraction
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Outputs
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m0 (1,1) Initial mass (kg)
mF (1,1) Fuel mass (kg)
mE (1,1) Engine mass (kg)
p (1,1) Power (W)
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