Path: CubeSat/AttitudeControl
% Simulate a rigid body with 3-axis attitude control.
Since version 8.
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Form:
data = AttitudeControlSimRWA( qEB0, wB0, qEBDes, t, inrBody, inrWhl, ...
maxRate, control );
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Inputs
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qEB0 (4,1) Initial ECI to Body quaternion
qEBDes (4,:) Desired ECI to Body quaternion over time
t (1,:) Time vector (sec)
inrBody (3,3) Inertia matrix for the rigid body
inrWhl (3,1) Wheel inertias. Enter a scalar if all the same.
maxRate (1,1) Maximum slew rate (rad/s)
control (.) Control data structure with fields:
.a A matrix of discretestate space controller
.b B matrix of discretestate space controller
.c C matrix of discretestate space controller
.d D matrix of discretestate space controller
.tSamp Sampling time (sec)
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Outputs
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data (.) Data structure with fields:
.t (1,:) Time vector (intervals at tSamp)
.qEB (4,:) ECI to Body quaternion
.wB (3,:) Body rate (rad/s)
.torque (3,:) Body torque (Nm)
.wW (3,:) Wheel rates (rad/s)
.power (3,:) Required power draw (Watts)
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Common: Control/C2DelZOH Common: Control/PIDMIMO Common: Quaternion/AU2Q Common: Quaternion/Q2AU Common: Quaternion/QMult Common: Quaternion/QPose Math: Integration/RK4 SC: Dynamics/FRB
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