Dynamic Interaction Analysis Of Space 4～10M Deployable Antenna And Its Test Technics

First this paper summarized the developing configuration of large space deployable antenna of world wide, especially various kinds of structure and the key techniques of high accurate deployable antennas. The paper also summarized the configurations of some Chinese space antennas, pointing out the problems in existence and the way of solution. At the end of paper, the developing scheme for Chinese large antenna in the near 10 years is presented.The paper presented in detail the developing technology of 4m-10m space deployable antennas, including design rule, analysis contents and required tests.The design rule includes the criterion and requirements from electronics, mechanics, thermal and space environments as well as interface limitation. The design configurations related to structure are listed in detail. The analysis contents include input/output date explanations, analysis methodology and software. The test scheme, test requirement and goal for large deployable antenna are explained concisely.A multi-body dynamic model of a rigid satellite with flexible antenna system and flexible solar array has been built. The flexible antenna system is a multi-body link. The satellite attitude control system is modeled into a close control loop with three momentum wheels on each axis. The antenna pointing control is open loop control without feedback. The antenna pointing errors due to antenna tracking motion and satellite attitude adjusting (trusting) were analyzed, as well as the influence of damping, tacking velocity and trusting time. For ka-band communication antenna, several classes of different satellite weight were considered and the critic first frequency of antenna system was given.It is the first time applying modal test to large composite-material antenna. The test methodology was defined according to the structural and material characters of space micro-strip antenna. The technical study was done to the center panel and rightwing of a space micro-strip array antenna. The study includes the influence of different measuring position, exciting method, supporting and type of sensor. The mechanical characters and test methodology are first concluded for large space deployable composite antenna.The mechanical characters of non-symmetrical sandwich panel were studied. Thestress-strain relation was founded the panel with extending-bending coupling. Based on minimized potential energy theory, equilibrium equation was founded using displacement method. The thermal distortion test of 5x8 sub-array panel was done in high temperature and normal pressure environment. The methodology, procedure and results of thermal distortion test are explained in detail. The test shows the differences between measuring results and FEA analyzing results are quite limited.The paper first summarized varies zero-gravitation off-loading equipments from both function and engineering aspects. The essential requirements for designing this kind of equipments are listed. For some common large deployable antennas, the zero-gravitation off-loading equipments are introduced in drawing. As an example, an off-loading equipment for 10 meter deployable panel array antenna is described in detail, including system design, active function and key components developing.A truss deployable parabolic wave antenna is introduced to show the developing procedure of large space deployable antenna. It has large ratio of deploying/stowed volume. It may be used as SAR antenna for small satellite or as other communication antenna of S or L band. The structural system configuration and key components design are described. The shape error distributing, thermal distortion and stiffness are analyzed. The primary test results getting from principle model show the design scheme is reasonable.