Path: SCPro/DynamicalModels
% Simulate separation of multiple satellites from a carrier.
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Form:
x = SeparationSim( x0, dT, tEnd, d )
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Inputs
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x0 (13,1) Core vehicle state
dT (1,1) Time step (sec)
tEnd (1,1) End time (sec)
d (1,1) Data structure
.t (3,n) Disturbance torques in body k frame
.f (3,n) Disturbance forces in ECI frame (kN)
.inr {n} Inertia matrix in body k frame
.m (n) Mass (kg)
.mu (1,1) Gravitational parameter
.lambda (:,n ) Vectors from hinge to cm in k frame
.kappa (:,n) Vectors from body 0 cm to hinges
.b {n } Transformation matrix from k to 1
.e0 (3,1) Location of body 0 cm (m)
.k (n,1) Spring Constant (N/m)
.u (3,n) Spring unit vectors
.lS (n,1) Spring lengths (m)
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Outputs
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x (13*n,nSim) State vector
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AerospaceUtils: Coord/QIToBDot Common: CommonData/SwooshWatermark Common: Control/C2DZOH Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Quaternion/Q2Mat Common: Quaternion/QTForm Math: Integration/RK4 Math: Linear/Cross Math: Linear/Mag Math: Linear/Skew Math: Linear/SkewSq Math: Linear/SkewSymm
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