Path: LunarMissions/LunarLanding
% Equality constraints for the landing for a 2D flat planet problem.
The constraint is the terminal altitude and velocities. They must
be zero. The function integrates the trajectory to find the values.
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Form:
[cIn, cEq, s, t] = LandingConst2D( x, d )
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Inputs
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x (:,1) [beta;dT]
d (.) Data structure describing spacecraft model
.hFinal (1,1) Final altitude
.a (1,1) Acceleration
.g (1,1) Gravity
.x (4,1) Initial condition
.n (1,1) Number of segments
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Outputs
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cIn (1,1) Inequality contraints, empty
cEq (3,1) Equality constraints, [altitude;x velocity;y velocity]
s (4,1) Final state
t (1,:) Corresponding times
See also: RHSPlanetTakeoff
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SCPro: DynamicalModels/RHSPlanetTakeoff Math: Integration/RK4
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