Structure Design And Study On Shock Response Of Micro-nano Satellite

Under the traction of earth observation and resource exploration,on-board equipments have reduced size significantly while improved performance by breakthrough on microelectronics technology,MEMS systems and micro-nano processing.In recent years,micro-satellites have rapidly become an important part of the space system due to their features of light weight,small volume,short development cycle,low cost,high integration and mass production.So micro-nano satellites occupy the dominant position in space science research and teaching implementation,demonstration and verification of new technology,r emote sensing observation,space network.Satellite structure and configuration design run through the entire satellite development cycle as the core of satellite development.In this paper,a micro-nano satellite structure is designed to achieve luminous remote sensing,which gives full consideration to the structural characteristics,design constraints and shock and vibration environment.The main work mainly include research of satellite structural design and optimization,shock and vibration response characteristic analysis,and mechanical environment test verification.Firstly,a non-standard 6U main load-carrying structure is proposed according to the main tasks and performance requirements of the micro-nano satellite.The physical configuration,load layout and connection forms of overall satellite are designed in detail.According to the force transmission path,the corresponding satellite finite element model is established through the reasonable simplification of satellite structure.The low frequency mode is extracted and calculated which satisfies the fundamental frequency requirement of the carrier loading.Then,the shock response characteristics are studied as the focus of environment in the separation of the satellite and the rocket.Based on the principle of time domain synthesis of shock response spectrum,the impulse response spectrum signal in the frequency domain is transformed into the acceleration time history signal which can be used as the input of analysis load.It can simulate compli cated shock waves.The transient response is analyzed by using the synthesized time history signal as the shock load input condition.The rationality of the satellite structure is assessed according to the acceleration response and displacement damage criterion.Next,the vibration response characteristics of micro-nano satellite are analyzed.Based on the finite element method,the dynamic response of satellite structure under the action of sinusoidal excitation and random excitation is mainly solved,which take the vibration environment of the satellite in the process of launching and in orbit as the research object.And the response results are analyzed from the perspective of structural design.Finally,the vibration test of the initial sample satellite is carried out.The test scheme is designed mainly based on the simulation results under vibration excitation.The sweep frequency vibration test,sinusoidal vibration test and random vibration test under the acceptance level are carried out in X,Y,Z direction.The results show that the dynamic response value of the satellite structure satisfies the general requirements in the vibration environment,so the structure design is reasonable?...