Path: StraightLine/ConstantThrust
% Optimal straight-line trip time for an ideal rocket
Computes optimal trip time for distance given engine specific power
and specific impulse. This is a numerical process. This formulation
neglects fuel tank fraction.
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Form:
OptimalTripTime; % demo
[T,lambda,iter] = OptimalTripTime( d )
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Inputs
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d (.) Straight 2D structure
.dF
.eta
.sigma
.uE
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Outputs
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T (1,1) Time
lambda (1,1) Payload ratio
iter (1,1) Iterations
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Reference: Craig Williams, An Analytic Approximation to Very High
Specific Impulse and Specific Power Interplanetary Space Mission
Analysis, AAS Space Flight Mechanics Meeting, 1996
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StraightLine: ConstantThrust/ComputePayloadFraction StraightLine: ConstantThrust/OptimalCharacteristicVelocity StraightLine: ConstantThrust/Straight2DStructure Common: Database/Constant
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