Path: StraightLine/Flyby
% Compute exhaust velocity and thrust for a minimum mass trajectory (fmincon)
The power is calculated from the thrust and thrust efficiency. The engine mass
is calculated from the specific power. Requires fmincon.
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 FlybyOptimal for a demo to Alpha Centauri.
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Form:
d = FlybyOptimal; % data
[uE, thrust, data] = FlybyOptimal( d, maxIter, iterDisp )
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Inputs
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d (.) Data structure
See StraightLineConstantThrust with additional fields:
.eta Thrust efficiency
.sigma Specific power (W/kg)
.thrustRange
.uERange
maxIter (1,1) Maximum number of iterations
iterDisp
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Outputs
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uE (1,1) Exhaust velocity (km/s)
thrust (1,1) Thrust (N)
data (.) Results data structure
.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)
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See also StraightLineConstantThrust, SimulateFlyby
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StraightLine: ConstantThrust/StraightLineConstantThrust StraightLine: ConstantThrust/StraightLineDataStructure StraightLine: ConstantThrust/UToMF StraightLine: Flyby/FlybyConstantThrust StraightLine: Flyby/SimulateFlyby
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