| In recent years,with the continuous breakthrough of ‘multi satellites launching in one rocket’ technology,the number of micro-satellites is increasing rapidly,mainly used in marine observation,ecological protection,urban planning and other fields.At present,the development of micro-satellites must have the characteristics of short development cycle,light weight,low cost,strong versatility and high reliability.The structure subsystem of micro-satellite needs to provide installation platform for each equipment,and meet its use requirements under harsh mechanical conditions,which also poses new challenges to the structure design of micro-satellite.In this background,this text taking‘M’ micro-satellite structure design as the starting point,has optimized and analyzed the whole satellite structure design,and has finished test to verify it.The specific research contents are as follows:(1)The characteristics,principles and external loads of the satellite structural design are studied,and the detailed structural design requirements are formulated according to the overall technical requirements.A layered structure of integrated board and frame with universal load space is proposed.Based on this structure,the overall layout,material selection,attitude control components and camera load field of view analysis are carried out in this paper.(2)An analysis method of the relationship between the design factors and the dynamic response of the whole satellite is proposed.By equivalenting the satellite model and analyzing conditions,modal,sinusoidal and random vibration responses are calculated based on dynamic theory.Then the relationship between design variables and dynamic response is obtained by using Matlab software.(3)The finite element theory and structural optimization theory are introduced,and the method of satellite grid division is described.Because the working quality of precision equipment is sensitive to the dynamic response,taking the dynamic response of the camera,momentum wheels and the first fundamental frequency of the whole satellite as constraints,Optistruct module of Hyper Mesh software is used to optimize the size of the key parts of the whole satellite.(4)The static,modal,sinusoidal and random vibration simulation analysis of the optimized structure is carried out by using Hypermesh software.The rationality of the structure design is proved by the simulation method,which provides the basis for the subsequent mechanical environment test of the whole satellite.(5)The mechanical environment test scheme of ‘M’ micro-satellite is designed and the test system is built.From X,Y,Z direction of the satellite,the sinusoidal vibration and random vibration test are performed.The results of simulation data and test data are analyzed to verify the effectiveness of structural optimization,simulation analysis method,and the rationality of structural design. |
