空间特性模拟的微小飞行器结构设计与动特性分析

Structural Design and Dynamic Characteristics Analysis of Micro-Aerospace for Space Feature Simulation

为研究空间碎片等非合作目标的可见光、红外及运动规律等空间特性,一般通过微小飞行器进行模拟,因此,对微小飞行器结构设计提出了小发射尺寸、大展开面积、轻质、高承载等技术需求。本文基于立方星架构思想,进行了空间特性模拟微小飞行器的结构方案设计。在分析卫星构型设计特点的基础上,结合设计要求、发射的重量及空间限制等约束,提出了舱段模块化、尺寸系列化堆叠式构型研制方案。通过三维建模设计和有限元分析,开展了多U微小飞行器的结构方案设计与动特性分析。结果表明结构方案合理、强度刚度满足指标要求,可作为结构优化及地面试验环境条件制定的依据。

In order to study space feature of visible light,infrared and motion laws of non-cooperative targets such as space debris,it is generally simulated by a micro-aerospace.Therefore,technical requirements are put forward for micro-aerospace structure design in small launch size,large expansion area,light weight,high load bearing and other aspects.Based on the idea of cube sat architecture,the structural scheme of space feature simulation micro-aerospace is designed in this paper.By analyzing the characteristics of satellite configuration design,combined with the con-straints of design requirements,launch weight and space constraints,the development scheme of stacked configuration with modular cabin and serialized size is proposed.The structural scheme design and dynamic characteristic analysis of multi-U micro-aerospace are carried out through three-dimensional modeling design and finite element analysis.The analysis results show that the structural scheme is reasonable.At the same time,the strength and stiffness meet the task requirements,which can be used as the basis for structural optimization and ground test environmental conditions.