Path: FormationFlying/Control
% Generate an LQG controller for linearized relative orbit dynamics.
Outputs controller statespace matrices:
- 6 states
- 6 inputs (Hills frame pos & vel)
- 3 outputs (Hills frame acceleration)
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Form:
[aK,bK,cK,dK] = LinOrbLQG( el, QG, RG )
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Inputs
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el (1,6) Orbital Elements
QG (1) Scalar estimator gain (make small)
RG (1) Scalar regulator gain (make big)
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Outputs
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aK (6,6)
bK (6,12)
cK (3,6)
dK (3,12)
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FormationFlying: EccDynamics/FFEccLinOrb FormationFlying: Utility/NuDot Orbit: RHSOrbit/LinOrb SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: BasicOrbit/OrbRate Common: CommonData/SwooshWatermark Common: Control/C2DZOH Common: Control/QCE Common: Control/QCR Common: Control/Riccati Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/DupVect Math: MathUtils/Odd
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