Spacecraft attitude tracking low-complexity preset property controlling method
A technology with preset performance and low complexity, applied in attitude control, space navigation equipment, space navigation equipment, etc., can solve the problems of inability to guarantee the transient and steady state performance of attitude tracking process, high system parameter requirements, etc. The effect of strong engineering application value, high theoretical significance, and low complexity characteristics
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[0095] For the spacecraft attitude tracking task, the simulation parameters are as follows: The inertia matrix J of the spacecraft is
[0096]
[0097] The initial attitude quaternion is:
[0098]
[0099] The initial attitude angular velocity is:
[0100] ω(0)=[-0.34 0.37 -0.43] T (14)
[0101] The unknown external interference is designed as:
[0102]
[0103] The desired posture is designed as:
[0104]
[0105] The preset performance indicators are selected as: β i =0.08,δ i = 0.2, the controller parameters are designed as: k = 200, Q = diag (0.05, 0.05, 0.2).
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