Path: SC/Attitude
% Computes the new inertia and body rate when appendages change discretely.
Assumes a core with n appendages directly attached, i.e. solar arrays.
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Form:
[omega, inertiaTotal] = InertiaTotal( inertia, mass, rCM, rHinge, u,
omega, angle, inertiaTotal )
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Inputs
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inertia {:} 3-by-3 Inertia matrices {core array1 array2 ...}
mass (1,:) Masses
rCM (3,:) Reference vector to cm of each body from the hinge
rHinge (3,:) Hinge vectors
u (3,:) Unit vectors of rotation for {array1 ...
angle (1,:) Array angle
omega (3,1) Angular rate
inertiaTotal (3,3) Old 3-by-3 Inertia matrix
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Outputs
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omega (3,1) Angular rate
inertiaTotal (3,3) 3-by-3 Inertia matrix
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Common: Quaternion/AU2Q Common: Quaternion/Q2Mat Math: Linear/DupVect Math: Linear/SkewSq
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