Path: Orbit/OrbitControl
% Right hand side for locally optimizing the Lambert time of flight problem.
Integrates FOrb using RK45. Calls LambertTOF.
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Form:
dV = FLambert( t, d )
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Inputs
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t (1,2) Start and transfer time
d Maneuver data
.r1, .v1 (6,1) Initial state
.r2, .v2 (3,1) Target state
.type (:) Type {'direct' 'retrograde'}
.dTMax (1,1) Maximum allowed transfer time (sec)
.rhs (:) RHS function, 'FOrb' or 'FOrbHF'
.mu (1,1) Gravitational parameter
.tol (1,1) Tolerance
g Gravity model struct, for FOrbKF
.mu Gravitational parameter
.s, .c, .j, .a Model parameters
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Outputs
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dV (1,1) Magnitude of delta-V
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Orbit: GravityModels/LoadGravityModel Orbit: OrbitMechanics/LambertTOF Math: Integration/RK45 Math: Linear/Cross Math: Linear/DupVect Math: Linear/Factorl Math: Linear/Mag Math: Linear/Unit
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