Satellite multiple attitude control mode test system based on double gimbal control moment gyroscope (DGCMG) structure

Abstract

The invention relates to a satellite multiple attitude control mode test system based on a double gimbal control moment gyroscope (DGCMG) structure. Performance of three satellite attitude control systems which are based on a DGCMG, a single gimbal control moment gyroscope (CMG) and a flywheel is tested and verified through a DGCMG actuating mechanism. The satellite multiple attitude control mode test system based on the DGCMG structure comprises a platform system, the satellite attitude control system, a space environment simulation system and a ground station system. The platform system is composed of a tri-axial air bearing table, a satellite service comprehensive management system, a power source and a wireless bridge and used for simulating satellite dynamic characteristics and information management. The satellite attitude control system is composed of a jet propulsion system, the DGCMG, a fiber-optic gyroscope, a star sensor, a sun sensor and a global position system (GPS) receiver and used for determination of an attitude and an orbit and control of a satellite platform. The space environment simulation system is composed of a GPS simulator, a sliding block which is of a pyramidal structure, a sun simulator and a star simulator and used for simulating space interference torque, and part performance of a GPS satellite and a celestial body. The satellite multiple attitude control mode test system based on the DGCMG structure can provide ground testing and verification for multiple attitudes of a satellite.

Description

technical field [0001] The invention relates to a satellite multi-attitude control mode test system based on a DGCMG (dual frame control moment gyro) configuration, which is suitable for three types of attitude control actuators based on double frame control moment gyroscopes, single frame control moment gyroscopes and reaction flywheels. Design of satellite attitude control schemes under different configurations. Background technique [0002] In the 21st century, with the rapid development of space science and technology, the maneuverability of satellites has been greatly improved. Various satellites such as small agile maneuverable satellites and high-precision and stable satellites to the ground have attracted many institutions to conduct a lot of research. The attitude actuators of the satellite mainly include jet propulsion, control moment gyroscope and reaction flywheel, etc. In previous studies, such as the ground simulation device and method for small satellite atti...

AI Technical Summary

Problems solved by technology

The control torque gyroscope has a variety of classic configurations as an attitude actuator, and its application is relatively mature. At present, most of the control torque gyroscopes use a certain configuration, and the installation configuration cannot be changed after it is determined.

If you need to use other configurations of control torque gyroscope as the attitude actuator, you can only disassemble it, and then rebuild the control torque gyro group of the desired configuration, which is very cumbersome and wastes a lot of time and economic costs.

Images