Master-slave cooperation non-contact satellite platform and control system and method thereof

Abstract

The invention discloses a master-slave cooperation non-contact satellite platform, and a control system and method thereof; the satellite platform comprises a loading cabin, a service cabin, and a magnetic suspension mechanism; the bottom of the loading cabin is provided with a payload; the loading cabin is provided with a star sensor, a gyro and a payload control unit; the service cabin comprises general satellite modules, and is provided with a drive mechanism, a thruster, a momentum wheel, a solar battery array and a relative attitude control unit; the magnetic suspension mechanism comprises a permanent magnet end and a coil end; the permanent magnet end is fixedly connected with the loading cabin; the coil end is fixedly connected with the service cabin; the permanent magnet end and the coil end can use electromagnetism effect to generate electromagnetic force according to command needs; the control system is divided into independent and organically combined 3 closed loops; a sliding mode control method is employed so as to complete high precision high stability attitude control, and robustness is good; the control system and method can be applied to high resolution detection type high performance spacecrafts.

Description

technical field [0001] The invention relates to the field of non-contact satellite platforms, in particular to a master-slave cooperative non-contact satellite platform and its control system and control method. Background technique [0002] Traditional large satellites often carry flexible accessories such as large solar panels and expandable radiators, and their coupling torque to the satellite body greatly affects the attitude and pointing accuracy and stability; on the other hand, the flywheels, gyroscopes, drive The vibration induced by moving parts such as mechanisms is also the main reason for causing load vibration and reducing attitude pointing accuracy and stability. With the improvement of spacecraft performance requirements, the interference and flutter problems caused by the vibration of large flexible structures and moving parts have become the main factors restricting the accuracy of satellite attitude control. [0003] At present, there are mainly three supp...

AI Technical Summary

Problems solved by technology

The passive vibration isolation system has a simple structure, is stable and reliable, and does not consume extra space energy, and does not require measurement and driving devices. It is the most widely used in satellite engineering, but it is only effective for high-frequency vibrations, and its vibration isolation performance is limited; Theoretically, the vibration system has better performance, but it requires additional measurement and driving devices, the system design is complex, the reliability is poor, and it has not been widely used in satellites; active and passive vibration isolation is a combination of active and passive vibration isolation. The improved method cannot substantially solve the application problem of active vibration isolation

At the same time, foreign countries have proposed the concept of non-disturbance payload satellites, which can solve the platform vibration and interference problems to a certain extent, but the design of its attitude control system is complicated, and its practical application is difficult. Currently, it is limited to the stage of local verification in the laboratory

To sum up, whether it is traditional active, passive, hybrid vibration isolation methods, or foreign non-disturbance payload satellites, they are all based on the active control of the platform, and the design idea that the payload follows the platform passively has limitations.

[0004] At the same time, the traditional satellite structure adopts the integrated design form of the fixed connection of the payload platform. The payload itself cannot independently complete the autonomous attitude control, but the platform is the main body for control. In terms of methods, the PID algorithm is generally used to realize the satellite platform. Attitude control, although the PID algorithm is mature in engineering applications, but its control accuracy is low, which cannot meet the extremely high requirements of new satellite platforms for control accuracy

In addition, foreign undisturbed payload satellite platforms are still in the stage of conceptual demonstration, and do not involve the analysis of control methods for new concept satellite platforms

Images