| 多舱段航天器振动基频分配速算方法 |
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| 引用本文： | 李青, 逯运通, 赵会光. 多舱段航天器振动基频分配速算方法[J]. 航天器环境工程, 2020, 37(1): 25-30doi:10.12126/see.2020.01.004 |
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| 作者姓名： | 李青 逯运通 赵会光 |
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| 作者单位： | 北京空间飞行器总体设计部，北京 100094 |
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| 摘 要： | 多舱段航天器在研制阶段初期面临着如何分配各舱段基频以及确认基频分配方案是否满足运载火箭方要求的问题，但在这个阶段各舱段的设计尚未定型，建立航天器三维有限元模型缺少必要的输入且时间成本较高，无法满足设计迭代和优化的需求。文章采用多段杆模型模拟航天器的纵向振动特性，采用多段梁模型模拟航天器的横向振动特性，基于基频等效原则建立航天器舱段设计参数与梁杆模型参数的数学关系，分别推导多段杆和多段梁的振动频率方程，提出多舱段航天器振动基频分配速算方法。通过某月球探测器三维有限元模型模态分析数据和力学试验数据验证了该方法的有效性。所提出的方法可用于验证基频分配方案的正确性，并为开展设计优化提供了途径。
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| 关 键 词： | 多舱段航天器 振动特性 基频分配 梁杆模型 模态分析 力学试验 |
| 收稿时间： | 2019-05-25 |
| 修稿时间： | 2020-01-19 |
Rapid calculation of vibrational fundamental frequency assignment for multi-cabin spacecraft |
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| LI Q, LU Y T, ZHAO H G. Rapid calculation of vibrational fundamental frequency assignment for multi-cabin spacecraft[J]. Spacecraft Environment Engineering, 2020, 37(1): 25-30doi:10.12126/see.2020.01.004 |
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| Authors: | LI Qing LU Yuntong ZHAO Huiguang |
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| Affiliation: | Beijing Institute of Spacecraft System Engineering, Beijing 100094, China |
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| Abstract: | In the preliminary stage of the multi-cabin spacecraft development, it is often a problem how to assign the requirement of the vibrational fundamental frequency for each cabin and confirm the satisfaction of the global requirement advanced by launch vehicle designers. However, as the detailed design parameters of each cabin are not yet available in this stage, there is no necessary input to build a three-dimensional finite elements model of spacecraft and this will also be time-consuming, to meet the requirement in the design iteration and optimization. For solving the problem, a rapid calculation method of the vibrational fundamental frequency assignment for the multi-cabin spacecraft is proposed. A multi-section rod model is used to simulate the longitudinal vibration, and a multi-section beam model is used to simulate the transverse vibration. The mathematical relationships between the design parameters of the spacecraft cabins and the beam-rod model parameters are established based on the equivalence principle of the fundamental frequency. The vibration frequency equations of the multi-section rod model and the multi-section beam model are derived, respectively, to achieve a rapid calculation method of the vibrational fundamental frequency assignment for the multi-cabin spacecraft. The method is verified by comparing its results with the modal analysis results obtained by using the three-dimensional finite elements model and the mechanical test results in the sub-sequent stage of the spacecraft development. The proposed method confirms the validity of the fundamental frequency assignment, and makes it feasible for the design optimization. |
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| Keywords: | multi-cabin spacecraft vibration characteristics fundamental frequency assignment beam-rod model modal analysis mechanical test |
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