Path: Orbit/OrbitCoord
% Given the reference absolute state, converts a relative orbit state to absolute.
Consistent with Hills equations.
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Form:
x1 = RelState2Absolute( x0, xRel )
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Inputs
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x0 (6,1) [r;v] ECI frame
xH (6,n) [r;v] Hills frame
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Outputs
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x1 (6,n) [r;v] ECI frame
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Reference: Kaplan, M., Modern Spacecraft Dynamics and Control, p. 111.
Valado, D., Fundamentals of Astrodynamics and Applications,
Orbital Maneuvering, Relative Motion.
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Common: Transform/Eul2Mat Math: Linear/Cross Math: Linear/Dot Math: Linear/Mag
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