Structure Analysis And Optimization Of A Light Small Frame-type Satellite

With the developing of space technology,the small satellite is supposed to be miniature and lightweight,and will be suffered from a vile mechanics environment.Therefore it is significant to perform structure analysis and optimization design on the satellite.A light small frame-type satellite is considered in this paper.Key techniques of Modeling methods,structure simulation analysis,structure optimization and so on are researched.The main work and achievements are summarized as follows:A 3-D finite element model of a light small frame-type satellite is established.Many types of connection are simulated.Modeling methods of stiffened panels and connected beams are researched.Best modeling types of stiffened panels and connected beams under different conditions are determined with comparing workload and accuracy.Modal analysis,static analysis,frequency response analysis and random response analysis are performed on the satellite with FEA software MSC.Nastran.Moreover,different factors with effects on calculations are researched.The parameterized modeling programme of the satellite stiffened panels and connected beams is designed by using PCL.Taking the minimum weight of stiffened panels and connected beams as objective function,the single-objective optimization is executed by using GA and PCL parameterized model established before.Also,an modal experiment is conducted to test the effectiveness of single-objective optimization.Taking the minimum weight and the maximum fundamental frequency of a stiffened panel as objective function,the multi-objective optimization is executed by using Kriging surrogate-model.A software for structure analysis and optimization of a light small frame-type satellite is developed.The modal analysis module,the frequency response analysis module and the structure optimization module are included in the software.This software make it generalized to simulation analysis and structure optimization.In conclusion,the structure optimization and parameterized modeling of the satellite are successfully executed in this dissertation.The result can be taken as technology instruction to the improving design of the satellite and the method can be applied to the research of similar complex structure.