Design And Analysis Of Multi-Functional Structural Unte For Spacecraft

Light and miniaturization are the development directions of modern spacecraft.The installation of electronic devices seriously limits the light and miniaturization of spacecraft.In order to solve this problem,this paper presents a multi-functional structural unit which integrates the electronic equipment and cables into honeycomb sandwich panels to form a set of machines,electricity and heat.Due to the omission of boxes,cables and so on,the weight and volume of the satellite will be greatly reduced.Then,the electromagnetic shielding,thermal radiation and thermal structure coupling of the multi function structural unit embedded in the electronic device are analyzed in detail.Thinking of radiation problems the multifunctional structure unit will face in the space,this paper uses SRIM to analyze the shielding of electromagnetic shielding box of different materials.The material of the shielding box is optimized considering the different honeycomb panel materials,weight loss,thermal expansion coefficient matching and electromagnetic shielding of the spacecraft.Then,a typical structural model of multi-function structural unit is established.ABAQUS is used to study the temperature distribution of the structural element under the condition of steady heat source.After that,taking the core chip temperature as an evaluation indicator of passive heat dissipation effect,the main factors and secondary factors that affect the heat dissipation effect of the multifunctional structure units are found by the orthogonal analysis.The influence of temperature on the structural characteristics of an electronic device will not be neglected using embedded design.Then,the thermal stress and thermal deformation of the multifunctional structural element under the heat source are calculated by the method of sequential coupling and complete coupling,and the results of the two are compared.Finally,the modal analysis,frequency response analysis and random vibration analysis are carried out on the multi function structural unit under the normal temperature and the heat source,and the influence of temperature on the structural characteristics is found out.At the end of the paper,several important development directions of spacecraft multifunction integrated structure in the future are prospected.