Path: StraightLine/Straight2D
% Compute exhaust velocity and thrust for a minimum mass trajectory
Computes the exhaust velocity that optimizes the payload fraction for the
desired mission distance and time. 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. If the time is not sufficient given the other
engine parameters the function with throw an error.
Type StraightLineOptimal for a demo to Alpha Centauri
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Form:
[uE, thrust, data] = StraightLineOptimal( d, doPlot )
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Inputs
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d (.) Data structure with dF and tF
doPlot (1,1) Display report
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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 OptimalExhaustVelocity, ZeroPayloadTime, ComputeThrust
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StraightLine: ConstantThrust/SimulateStraightLineTrajectory StraightLine: Straight2D/ComputeThrust StraightLine: Straight2D/OptimalExhaustVelocity StraightLine: Straight2D/Straight2DStructure StraightLine: Straight2D/ZeroPayloadTime
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