Flexible spacecraft attitude control system and flexible spacecraft attitude control method in allusion to flywheel low-speed friction

Abstract

The invention relates to a flexible spacecraft attitude control system and a flexible spacecraft attitude control method in allusion to flywheel low-speed friction. The system comprises six modules which are a flexible spacecraft dynamics real-time simulation module with actuating mechanism characteristics, a flexible spacecraft kinematics real-time simulation module, an attitude measurement module, an attitude determination module, an attitude control module and an executing mechanism module, wherein the flexible spacecraft dynamics real-time simulation module with the executing mechanism characteristics comprises a spacecraft body, a flywheel and flexible appendage dynamics; the flexible spacecraft kinematics real-time simulation module can select different types of attitude description modes according to task requirements; the attitude measurement module can select different real sensors and sensor simulators according to the task requirements; the attitude control module comprises a conventional PID control method, a robust control method and the flexible spacecraft attitude control method in allusion to flywheel low-speed friction, and switching can be carried out according to the task requirements of the system; and the executing mechanism module comprises a real flywheel and a thruster simulator.

Description

technical field [0001] The invention relates to a flexible spacecraft attitude control system and method aimed at flywheel low-speed friction, which is suitable for spacecraft attitude control systems with flexible accessories and using flywheels as actuators, and belongs to the field of spacecraft attitude control. Background technique [0002] The reliability and long-term working stability of the spacecraft attitude control system have always been the key technologies in the development of spacecraft. As the tasks undertaken by the spacecraft become more and more complex, the solar panels on the spacecraft are required to provide more energy, and the spacecraft is required to have a larger antenna to receive weak signals at a long distance. These requirements make the spacecraft The appendages are getting bigger and bigger. In terms of launch cost and technical implementation difficulty, the above-mentioned appendages are usually designed with low-mass, low-rigidity flexi...

AI Technical Summary

Problems solved by technology

[0003] Most of the traditional spacecraft control systems are built for a specific task and model. The loops of the spacecraft control system are composed of a single control method, a single attitude description method, and fixed sensors, which lack versatility for scientific research. In addition, the design of the attitude control system in the past research process is not closely related to the characteristics of the actuator, ignoring the dynamic characteristics of the actuator, resulting in the design of the control method is not accurate enough, affecting the attitude accuracy and accuracy of the spacecraft system. Stability; in addition, for spacecraft systems with flexible attachments, the control method usually used is mainly to suppress interference, and does not make full use of the known information of interference, resulting in a lack of accuracy in spacecraft attitude control

Images