Path: Orbit/OrbitMechanics
% Solves the Lambert time of flight problem using Battin's method.
Type LambertTOF for a demo
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Form:
[vT, a, p, tol] = LambertTOF( r1, r2, dT, orbitType, mu, tol, maxIter )
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Inputs
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r1 (3,1) Initial position vector
r2 (3,1) Final position vector
dT (1,1) Time between position 2 and 1 (s)
orbitType (1,:) 'direct' (1) or 'retrograde' (-1)*
mu (1,1) Gravitational parameter*
tol (1,1) Desired tolerance [1e-10]*
maxIter (1,1) Maximum number of iterations [20]*
* optional
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Outputs
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vT (3,2) Transfer velocity at beginning and end of
the transfer ellipse
a (1,1) Semi-major axis of the trajectory
p (1,1) The parameter for the orbit
tol (1,1) Achieved tolerance
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Reference: Battin, R. H. "An Introduction to the Mathematics and Methods
of Astrodynamics", AIAA Education Series.
Vallado, D. A. Fundamentals of Astrodynamics and Applications.
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Math: Linear/Cross Math: Linear/Unit
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