Path: Orbit/ThreeBody
% Right-hand-side for the forced circular restricted three body problem.
The state includes mass.
- X is along primary - secondary body line
- Z is normal to plane of motion
- Y completes right-hand system
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Form:
xDot = FCRTBPRHS( x, t, mu, a, uE )
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Inputs
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x (7,1) The state vector [r;v;m]
t (1,1) Time (unused)
mu (1,1) Non-dimensional mass parameter.
Smaller mass divided by total mass of system.
a (3,1) Acceleration applied to body in rotating frame
uE (1,1) Exhaust velocity (non-dimensional)
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Outputs
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xDot (7,1) The derivative of the state vector
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