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Adaptive Compensation Method for Actuator Sign Uncertainty in Satellite Attitude Control System

A satellite attitude control and adaptive compensation technology, applied in attitude control and other directions, can solve the problems of continuous jumping of control signals and poor transient response

Active Publication Date: 2017-10-31
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0006] The technical problem to be solved by the present invention is to provide an adaptive compensation method for the uncertainty of the driving sign of the satellite attitude control system actuator in view of the defects of continuous jumping of the control signal and poor transient response in the control method based on Nussbaum gain , so that the system attitude angular velocity asymptotically tracks the desired signal

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  • Adaptive Compensation Method for Actuator Sign Uncertainty in Satellite Attitude Control System
  • Adaptive Compensation Method for Actuator Sign Uncertainty in Satellite Attitude Control System
  • Adaptive Compensation Method for Actuator Sign Uncertainty in Satellite Attitude Control System

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Embodiment Construction

[0061] The technical solution of the present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

[0062] In the present invention, an adaptive compensation method for the uncertainty of actuator drive symbols in a satellite attitude control system, the dynamic equation of the satellite attitude control system is:

[0063]

[0064]

[0065]

[0066] where: ω x , ω y , ω z is the component of satellite space rotation angular velocity on the principal inertia axis; is ω x , ω y , ω z Derivative; J x 、J y 、J z is the unknown moment of inertia parameter of the principal axis of inertia; u x , u y , u z is the control torque generated by the actuator,

[0067] It is characterized in that, comprising the steps of:

[0068] Step 1. According to the working condition of the actuator of the satellite attitude control system, the uncertainty of its driving symbol is modeled to form a set of ac...

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Abstract

The invention discloses an adaptive compensation method for the uncertainty of the driving symbol of the actuator of the satellite attitude control system, which belongs to the field of aerospace, and comprises the following steps: (1) modeling the uncertainty of the driving symbol of the actuator to form the actuator (2) Design different adaptive estimators for different driving symbol patterns in the established actuator driving symbol pattern set to form an adaptive estimator set; (3) use the adaptive estimator set output, design the adaptive controller set; (4) use the output of the adaptive estimator set to design the control switching mechanism between the adaptive controllers, and select the appropriate adaptive controller from the adaptive controller set to generate the control signal to drive the actuator. The adaptive compensation method can effectively guarantee the control accuracy of the satellite attitude control system when the actuator drive sign is uncertain, and make the system obtain satisfactory working quality.

Description

technical field [0001] The invention belongs to the technical field of satellite attitude control, in particular to an adaptive compensation method for the uncertainty of driving symbols of an actuator in a satellite attitude control system. Background technique [0002] Aerospace technology is one of the fastest-growing cutting-edge technologies in modern science and technology. Among them, the development of modern satellite technology plays a very important and positive role in promoting human civilization and social progress. As the most important part of a modern satellite, the attitude control system plays a decisive role in its performance, safety and reliability. The satellite is a complex structural system, and it works for a long time in the environment of vacuum, weightlessness, high and low temperature and strong radiation. Sensors, actuators and system components will inevitably fail. Minor failures will affect the stability of the system. If the satellite is d...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
Inventor 马亚杰姜斌陶钢程月华
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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