Integration Design Of A Direct Drive Joint And Application Research On Active Solar Panels System

The deployment and folding back of solar panes and its vibration control problems are becoming more and more important parts in the design of spacecraft,because they are directly related to the success of the mission of itself.To handle this problem,a new type of direct drive joint has been designed in this thesis,and deployment and vibration control experiments were manipulated to the solar panel system based on the novel active joint.The research work was started with magnetic analysis on some basic electromagnetic drving units.Then a novel active joint was proposed on the basis of these analysis and the specific design work were carried out,such as conceptual design,magnetic circuit design and optimization design.After that,a prototype of the joint was manufactured and some testing experiments of the performance of the prototype were finished.At last,the joint was applied to the solar panels,forming the active solar panel system.Deployment and folding back characteristics and vibrtion control function were studied of the system through the finite element analysis software,such as MATLAB and ADAMS.Further more,to compare with the simulaiton results of the software,experiments were performed on the active solar system.The main contents are summarized as follows:(1)In the prior research stage of designing the joint,methods of magnetic circuit analysis were summarized and applied to some basic linear and rotary electromagnetic drving units.A software was then developed using the matlab program language based on the anslysis work.This software can help calculating the values of some electromagnetic parameters and magnetic force and torque of some rotary electromagnetic drving devices,thus improving the design efficiency.(2)To handle the problem of the deployment and folding back of the solar panel system as well as vibration control,a new type of active joint was proposed and designed.The specific design work were carried out,such as conceptual design,magnetic circuit design,magnetic field modeling.Also the SQP algorithm was used to optimize the magnetic circuit structure.After that,a prototype of the joint was manufactured and experiments were done to get the performance parameters of the magnetic flux density in the air gap and drving torque of the prototype.(3)To further study the characteristic of the joint,we applied it to the slar panel system,thus forming the active solar panel system.The modal analysis of two panels' system and four panels' system with different torsional stiffness of the joint were completed respectively through ANSYS.(4)Simulink control system and ADAMS-MATLAB joint control system were used to simulate the performance of the deployment and folding back of the active solar panel system.Finally,an experiment testing platform of the system was set up by using a triangle bracket to balance the gravity of the solar panels,so as to simulate the microgravity environment in the space.More over,four fans were prepared to act as the interference sources.Based on all of this,the final tests of deployment and folding back and vibration control of the system were performed and verified.