Path: Orbit/LowEnergyManeuver
% Compute the time derivative of a state at a collinear libration point, using the equations of motion (up to 3rd order) for the circular restricted three-body problem. Formatted for MATLAB's ode integrators. -------------------------------------------------------------------------- Form: xDot = LibrationRHSODE45( ~, x, ~, c2, c3, c4 ) -------------------------------------------------------------------------- ------ Inputs ------ t (1,1) Time (not used, but included for consistency with ode45 call) x (6,1) Current state [x;y;z;dxdt;dydt;dzdt] junk (1,1) Place holder for call to ode45, not used c2 (1,1) Coefficient on 1st order terms c3 (1,1) Coefficient on 2nd order terms c4 (1,1) Coefficient on 3rd order terms ------- Outputs ------- xDot (6,1) Time derivative of the state --------------------------------------------------------------------------
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