Design And Research Of High Stiffness Solar Wing Deployment And Support Mechanism For Agile Satellites

The agile satellites to be studied in this paper have the function of fast and sensitive imaging,which can adjust the attitude according to the imaging content.It has the ability of left and right pendulum,front and back pendulum,accurate pendulum,fast pendulum,continuous observing and imaging of the region of interest.As the small agile attitude of the satellite constantly changing,the vibration of the flexible components on the planet is very easy to arouse.Most of the international small satellite using a single solar panel directly connected through the hinge around the satellite body.The other end of the solar panel is the free end,similar to the simply supported beam with typical flexibility characteristics.When vibration is not suppressed,vibration will seriously impact on satellites rapid agility and agile imaging,so solar panel of agile satellites must meet the requirements of rigidity and fundamental frequency.In this paper,the deployment mechanism of the tape springs hinge is designed,and the buckling performance of the spring is realized to realize the auto-locking with the high rigidity and flexural rigidity.The mechanism has the advantage of lightweight,simple structure and large locking force.The tape springs support structure is designed to compensate the flexural defects of the hinge structure and to increase the rigidity and fundamental frequency of solar panels which meet the requirement of fundamental frequency for satellites.The tape springs hinge can avoid stuck with the reliability of deployment.According to the design of deployment and support mechanism,chapter 1 conducts the research status of deployment and support mechanism at home and abroad is discussed,and the research and application status of tape springs is discussed.In chapter 2,the structural modeling of tape springs deployment and support mechanism with detailed design is discussed.In chapter 3,the mechanical properties of tape springs and hinges are studied.The finite element modeling method is used to analyze the effect of geometric parameters on buckling performance,and the relationship between mechanical properties and design factors is obtained.In chapter 4,the supporting position of the solar panel support mechanism is modeled,and the single variable method is used to optimize the support.In chapter 5,dynamic modeling and ADAMS simulation of deployment mechanism are carried out in combination with engineering practice.The development time and impact force of solar panel are analyzed.Chapter 6 mainly conducts the torque measurement of tape springs hinge,the model measurement of unsupported and supported,and the deployment measurement.The test results show that the fundamental frequency of the support is 9.4Hz,which is twice that of 4.7Hz with support.The test results are in accordance with the fundamental frequency of the simulation analysis,which verifies the correctness of the analysis and design of this paper for supporting mechanism.Moreover,the results can provide guidance for the later optimization design.