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An adaptive compensation method for out-of-control actuator failure of satellite attitude control system

A satellite attitude control and adaptive compensation technology, applied in the field of satellite attitude control, can solve the problems of reducing the amount of control calculations and the singularity of the estimated matrix, and achieve the effects of solving the problem of singularity of the estimated matrix, reducing the amount of calculations, and avoiding control signal switching

Active Publication Date: 2021-06-15
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

It not only solves the problem of singularity of the estimated matrix, but also effectively reduces the amount of control calculations and avoids the problem of control switching

Method used

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  • An adaptive compensation method for out-of-control actuator failure of satellite attitude control system
  • An adaptive compensation method for out-of-control actuator failure of satellite attitude control system
  • An adaptive compensation method for out-of-control actuator failure of satellite attitude control system

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Embodiment Construction

[0048] Below in conjunction with accompanying drawing, technical scheme of the present invention is described in further detail:

[0049] figure 1 It is a block flow diagram of an embodiment of the self-adaptive compensation method for the out-of-control fault of the actuator of the satellite attitude control system in the present invention. Such as figure 1 As shown, in the embodiment method of the present invention, the dynamic equation of the satellite attitude control system is:

[0050]

[0051] Where: ω=[ω x ω y ω z ] T is the angular velocity vector of satellite space rotation, ω x , ω y , ω z is the component of ω on the x-axis, y-axis, and z-axis; is the derivative of ω; [·] T Represents the transpose operation of a vector or matrix within parentheses; is the moment of inertia matrix of the satellite, J xx 、J yy 、J zz is the moment of inertia of the satellite around the x-axis, y-axis, and z-axis, J xy =J yx 、J yz =J zy 、J xz =J zx is the ...

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Abstract

The invention discloses an adaptive compensation method for out-of-control failure of an actuator of a satellite attitude control system, comprising: (1) modeling the out-of-control failure according to the working status of the actuator of the satellite attitude control system, and generating the actuator of the satellite attitude control system Runaway failure model. (2) Based on the out-of-control failure model of the satellite attitude control system actuator established in the described step 1, the assembly matrix of the satellite attitude control system actuator is used to construct the inverse matrix of the new control gain matrix, and the satellite attitude control system is parameterized change. (3) Design an adaptive law to directly estimate the inverse matrix of the new control gain matrix constructed in the second step and the uncertainty of the satellite attitude control system. (4) Use the estimated value obtained in step 3 to construct an adaptive controller. The present invention can directly deal with the system uncertainty brought by the fault without multi-model switching. It not only solves the singularity problem of the estimation matrix, but also can effectively reduce the amount of calculation required for control, and can ensure good asymptotic tracking performance of the satellite attitude angular velocity.

Description

technical field [0001] The invention belongs to the technical field of satellite attitude control, and relates to an adaptive compensation method for out-of-control failure of an actuator in a satellite attitude control system. Background technique [0002] Since the beginning of the 21st century, with the increasing development of aerospace technology, modern satellites are required to have high pointing accuracy, high maneuverability, high attitude tracking and long service life to be competent for different working modes in order to complete various delicate and complex space tasks. For example, after the "Malaysian Airlines" incident in 2013, in order to search for the crashed airliner, the satellites of various countries need to maneuver from the normal orbit to a specific orbit for search, which also requires rapid maneuvering of the satellite attitude, so as to ensure that the payload can play its role . However, due to the long-term operation in orbit, the internal ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 马亚杰姜斌陶钢程月华
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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