A distributed collaborative control method for super-scale flexible spacecraft

Abstract

The invention discloses a super-size flexible spacecraft dispersion cooperative control method, and aims to achieve high stability and vibration inhibition control on a super-size flexible spacecraft. The method comprises the following steps: S1, dividing a super-size flexible spacecraft control system into a spacecraft posture control subsystem and a flexible attachment vibration subsystem, and designing corresponding partial robust controllers for the spacecraft posture control subsystem and the flexible attachment vibration subsystem respectively; and S2, designing a coordinate controller for overall properties of the super-size flexible spacecraft control system. The method has the advantages that according to the dynamic characteristics of the super-size flexible spacecraft, a dispersion cooperative control method is adopted, a partial structure is stably controlled through dispersion stability, overall high-precision performance indexes are achieved through the cooperative controller, high appointing precision and stability of postures and deformation control precision of a flexible component are achieved, and the method is widely applied to high-precision high-stability appointing control on a large-size flexible structure.

Description

technical field [0001] The invention relates to the technical field of high-precision attitude control of a super-scale flexible spacecraft, in particular to a distributed collaborative control method for a super-scale flexible spacecraft. Background technique [0002] The dynamic characteristics of ultra-large-scale flexible spacecraft are extremely complex, presenting as a flexible, multi-body, high-dimensional, multi-degree-of-freedom nonlinear dynamic system with the characteristics of large flexibility, low stiffness, weak damping, low frequency and dense modalities . These dynamic characteristics pose severe challenges to the stability design and high precision requirements of spacecraft, and sometimes even pose a great threat to the safety of spacecraft. [0003] Modern spacecraft often have windsurfing boards, antennas, and a variety of payloads to complete more scientific tasks. Considering the constraints of carrying efficiency and launch cost, these loads must b...

AI Technical Summary

Problems solved by technology

During the in-orbit operation of the spacecraft, it is also affected by uncertain disturbances such as environmental torque and internal disturbance, as well as the control torque. The coupling of the control effect will also cause disturbance to the attitude of the spacecraft, affect the stability and control accuracy of the attitude of the spacecraft, and even make the spacecraft unstable and even affect its safety

In addition, the control performance indicators of modern spacecraft have been greatly improved. The system not only requires attitude to have high pointing accuracy and stability, but also flexible loads to have high orientation accuracy and shape control accuracy. serious challenge

The traditional centralized control strategy controls the stable orientation of the overall spacecraft through the output of the actuator in the service module, but for the super-large-scale flexible load structure, due to the low structural stiffness and weak damping, only the output of the actuator in the service module is used for control. , the control energy cannot be uniformly and effectively transmitted to all areas of the flexible load structure, and it is difficult to realize the global directional control of the flexible load

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