Path: SCPro/DynamicalModels
% Spacecraft sun-nadir RHS with 4 RWA's and 2 solar arrays.
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Form:
xDot = RHSSNP( x, t, inr, invInr, tExt, inrW, uW, tW, eSAC )
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Inputs
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x (15,1) The state vector [q;solar array;body
rates;solar array rates;wheel rates]
t Time
d (.) Data structure
.inr (3,3) Inertia
.tExt (3,1) External torque
.inrW (6,1) [SA,RWA] inertias
.uW (3,6) [SA,RWA] unit vectors
.tW (6,1) [SA,RWA] torque
.eSAC (2,1) Solar array commanded angle
(always one step)
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Outputs
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xDot (15,1) The derivative of the state vector
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AerospaceUtils: Coord/QIToBDot Math: Linear/Cross
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