Neural network backstepping sliding mode control method and system for spacecraft attitude tracking

Abstract

The present application relates to a neural network backstepping sliding mode control method, system, computer equipment and storage medium for spacecraft attitude tracking. The method includes: establishing a control-limited spacecraft attitude error dynamics model by giving the spacecraft's expected attitude and actual attitude, and including uncertain items in the control-limited spacecraft attitude error dynamics model; The control input in the dynamic model is limited to compensate, and the backstep sliding mode attitude tracking control law of the dynamic model is obtained by using the backstep sliding mode algorithm; the neural network approximator with the estimated value of the uncertain item as the output is constructed; The neural network approximator approximates the uncertain items in the dynamic model, and obtains the neural network backstepping sliding mode attitude tracking control law of the dynamic model, and realizes the attitude tracking of the spacecraft. The invention improves the control precision and adaptability of the posture tracking control system.

Description

technical field [0001] The present application relates to the technical field of automatic control, in particular to a neural network backstepping sliding mode control method, system, computer equipment and storage medium for spacecraft attitude tracking. Background technique [0002] With the development of aerospace technology, more and more space missions are performed by spacecraft, such as satellite surveillance, spacecraft formation flight, on-orbit service, rendezvous and docking, etc. High-precision attitude control, which puts forward higher requirements for the control accuracy of the spacecraft attitude control system. There are more and more factors affecting the accuracy of spacecraft attitude control, mainly including: gravity gradient moment, atmospheric disturbance moment and other space environment disturbance moments, and changes in spacecraft rotational inertia caused by fuel consumption. Because the spacecraft is affected by various disturbance moments a...

AI Technical Summary

Problems solved by technology

However, the above control method is carried out under some restrictive conditions, for example, it assumes that the system disturbance is bounded and the upper bound is known, and the spacecraft has sufficient control capability for attitude control

However, in the actual dynamic system, it is often difficult to obtain the upper bound of the system disturbance. In addition, the limitation of the control input of the spacecraft is also a common physical constraint of the actuator. stability

[0004] Therefore, the existing spacecraft attitude tracking technology has the problems of low control accuracy and poor adaptability

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