Design And Test Of Deployable Plane Structure For Spaceborne Platform

Due to its light weight, low cost, short development cycle and other advantages, small satellite is paid more and more attention to by research institutes.It is, particularly, put more emphases on by laboratories in universities.However, it limits the functions for the small satellite because of the lack of the carrying platform. In order to broaden the applications of the small satellite,it is given to priority that there is a kind of platform structure what is large and able to carry all kinds of payload. Considering these requirements, deployable structure can be suitable for the small satellite, because it can be folded into small size during the launch phase while it can be deployed into large platform at the beginning of the work phase.In this paper, a kind of deployable structure design is firstly stated for the carry platform of the small satellite according to the requirements of actual functions. Then the designs of each sub-system in thie structure are demonstrated in details.Secondly, Equivalent Cable Analysis Method are employed to conduct the modal analyses of this deployable structure. The analysis results are compared to the experimental results. Then several suggestions of stiffness improvement are given to be the design guide.Thirdly, the simulation of the deployment process is described by the ADAMS software. The analysis results are also contrasted with the experimental results. Then the deployment process of this deployable structure connected with the small satellite is analyzed and the trends of dynamics parameters in the process are also illustrated for the design improvement.Moreover, the planeness measurement formula is derived by using the tilt angle between the bar and the reference plane as the characterization on the basis of the non-contact photogrammetry system. Then three different methods of gravity eliminating are discussed to contrast their impacts on the planeness and their merits and drawbacks. Some measures are given to ensure the planess precision for the design guide. Finally the fundamental frequency scanning test, the low-frequency sinusoidal vibration test and random vibration test of the deployable structure connected with the small satellite in folded state are conducted to verify the safety of the structure.