Path: Interplanetary/OrbitInsertion
% Equality constraints for the 2D orbit insertion problem.
The constraint is the state.
The function integrates the trajectory to find the values.
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Form:
[cIn, cEq] = ApproachConst2DIneq( u, d, t, x0, xF )
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Inputs
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u (2,:) [phi;a]
d (.) Data structure describing spacecraft model
.phi angle
.a magnitude
t (1,:) Time steps
x0 (.) Initial state
xF (.) Final state
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Outputs
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cIn (1,1) Inequality contraints
cEq (3,1) Equality constraints
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Interplanetary: OrbitInsertion/RHS2DAnglePolarOrbit Math: Integration/RK4 Math: Linear/Mag
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