Path: Missions/LunarLanding
% Propagate the 2D state for the landing problem.
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Form:
xP = PropagateState( x, beta, dT, d )
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Inputs
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x (4,:) Initial state [x;y;vX;vY]
beta (1,:) Thrust angle (rad)
dT (1,:) Delta time for each step
d (.) Data structure describing spacecraft model
.a (1,1) Thrust acceleration (m/s^2)
.g (1,1) Gravitation acceleration (m/s^2)
.n (1,1) Number of steps
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Outputs
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xP (4,:) State
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SCPro: DynamicalModels/RHSPlanetTakeoff Math: Integration/RK4
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