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Path: SCPro/DynamicalModels
% Computes the time derivative of n spacecraft.
Employs a simple central force model for gravity.
The first state vector is the reference point
Since version 8.
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Form:
xDot = RHSNSpacecraft( x, t, d )
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Inputs
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x (13*n,1) [R;V;Q;W;r0;v0;q0;w0;...rk;vk;qk;wk]
t (1,1) Time (not used)
d (1,1) Data structure
.mu (1,1) Gravitational parameter
.f (3,n) Force vectors in ECI frame
.t (3,n) Torque vectors in body frame
.lambda (3,n-1) Hinge vectors on body k
.kappa (3,n-1) Hinge vectors on body 1
.inr {n} Inertia matrices
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Outputs
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xDot (13*n,1) d[R;V;Q;W;r0;v0;q0;w0;...rk;vk;qk;wk]/dt
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AerospaceUtils: Coord/QIToBDot Common: Quaternion/QForm Math: Linear/Cross Math: Linear/Mag Math: Linear/Skew SCPro: DynamicalModels/ConstraintForceAndTorque
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