Path: Interplanetary/LowEnergyManeuver
% Computes the time derivative of a state at a collinear libration point
Uses the equations of motion (up to 3rd order) for the circular
restricted three-body problem. Formatted for PSS RK4/RK45 integrators.
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Form:
xDot = LibrationRHS( x, t, c2, c3, c4 )
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Inputs
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x (6,1) Current state [x;y;z;dxdt;dydt;dzdt]
t (1,1) Time (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
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Outputs
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xDot (6,1) Time derivative of the state, x
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Reference: Farquar, Robert, "The Control and Use of Libration Point
Satellites", Goddard Space Flight Center, NASA TR R-346,
September 1970.
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