Lander soft landing posture control method
A technology of attitude control and lander, which is applied in the soft landing attitude control of the lander, and the landing attitude control field of the lander during the soft landing, which can solve the problems of attitude over-tolerance and poor control accuracy, so as to avoid measurement saturation and misdiagnosis The situation and method are simple and reliable
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[0053] (1) Lander inertia J=2000kgm 2 , ω=1rad / s, ξ=0.7, then: Kp=2000, Kd=2800, Ki=100, Kpv=2800, Kiv=500.
[0054] (2) Attitude control thruster moment Y max =240Nm, minimum pulse width t min =0.04s, attitude control accuracy θ min =0.2°, then: design Tm=2, H1=0.03, H2=0.01.
[0055] (3) Maximum capability of angular velocity measurement ω max =6° / s, then: dθr=3° / s, θm=4.2°.
[0056] (4) According to the above control parameters, dθg=3° / s and θeg=4° are obtained under the normally open fault of a thruster, then: design θ AF1 =3°, θ AF2 =9°, dθ AF1 =-1° / s, dθ AF2 =6° / s.
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