Anti-interference attitude control method for Mars lander with uncertain rotational inertia
A technology of moment of inertia and attitude control, applied in the direction of the guidance device of space navigation vehicle, can solve the problem of inability to guarantee the attitude control accuracy of the lander, and achieve the effect of improving engineering application value, anti-interference and adaptability
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[0049] Such as figure 1 As shown, the specific implementation steps of the present invention are as follows (the following takes the Mars lander attitude control system as an example to illustrate the specific implementation of the method):
[0050] 1. Build the attitude kinematics and dynamics model of the Mars lander with uncertain moment of inertia
[0051] The posture kinematics and dynamics model of Mars lander with uncertain moment of inertia is constructed as follows:
[0052] X 1 : J ω · e = - [ ( ω e + R ( σ e ) ω d ) X ] J ( ω e + R ( σ e ) ω d ) + J ( [ ω e X ] R ( σ e ) ω d - R ( σ e ) ω · d ) + u + d
[0053] X 2 : σ · e = G ( σ e ) ω e
[0054] X 3 : G ( σ e ) = 1 2 ( 1 - σ e T σ e 2 I 3 +
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