Path: Missions/LunarLanding
% Propagate the 3D state for the landing problem.
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Form:
xP = PropagateState3D( x, dT, d )
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Inputs
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x (7,:) Initial state [x;y;z;vX;vY;vZ;m]
dT (1,:) Delta time for each step
d (.) Data structure describing spacecraft model
.beta (1,:) Thrust angle in rv plane
.alpha (1,:) Thrust angle out of plane
.thrust (1,:) Thrust (N)
.accel (1,:) 'constant' or 'free'
.m0 (1,1) Dry mass
.radius (1,1) Planet radius
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Outputs
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xP (7,:) State
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Math: Integration/RK4 Math: Linear/Mag
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