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一、前言宇航器在各种工况下经受着许多复杂的动态环境,其中主要的是:起飞,跨音速飞行,最大动压飞行,级间分离,空间变轨及再入等。为了保证宇航器结构系统在动态载荷作用下的可靠性,在研制过程中必须认真处理有关动力学方面的问题。结构系统动力学方面的问题可归纳为以下三大类:1.已知输入(激振力)和结构系统特性求输出(响应)。2.已知输入和输出求结构系统特性——系统识别。3.已知输出和结构系统特性求载荷——环境预示。
I. INTRODUCTION The spacecraft is subjected to many complicated dynamic environments under various working conditions. The main ones are take-off, transonic speed flight, maximum dynamic pressure flight, interstage separation, spatial change and reentry. In order to ensure the reliability of the spacecraft structural system under the dynamic load, the related dynamics problems must be carefully dealt with in the development process. Structural system dynamics problems can be summarized into the following three categories: 1. Known input (excitation force) and structural system characteristics of the output (response). 2. Known input and output for structural system characteristics - system identification. 3. Known output and structural system characteristics Find load-environmental predictions.