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Path: Orbit/ThreeBody
% Right-hand-side for the circular restricted three body problem.
X is along primary - secondary body line
Z is normal to plane of motion
Y completes right-hand system
Since version 10.
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Form:
xDot = CRTBPRHS( x, t, mu )
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Inputs
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x (6,1) The state vector [r;v]
t (1,1) Time (unused)
mu (1,1) Non-dimensional mass parameter.
Smaller mass divided by total mass of system.
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Outputs
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xDot (6,1) The derivative of the state vector
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