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. -------------------------------------------------------------------------- Form: [cIn, cEq] = ApproachConst2D( u, d, t, x0, xF ) -------------------------------------------------------------------------- ------ Inputs ------ u (2,:) [phi;a] d (.) Data structure describing spacecraft model t (1,:) Time steps x0 (.) Initial state xF (.) Final state ------- Outputs ------- cIn (1,1) Inequality contraints cEq (3,1) Equality constraints --------------------------------------------------------------------------
Interplanetary: OrbitInsertion/RHS2DAnglePolarOrbit Math: Integration/RK4 Math: Linear/Mag
Back to the Interplanetary Module page