航空学报 > 2022, Vol. 43 Issue (3): 225053-225053   doi: 10.7527/S1000-6893.2021.25053

基于压力插值/力等效混合的火箭结构流-固载荷转换方法

樊一达1, 毛玉明2, 舒忠平2, 王吉飞2, 张洋洋3, 于哲峰1   

  1. 1. 上海交通大学 航空航天学院, 上海 200240;
    2. 上海宇航系统工程研究所, 上海 201109;
    3. 上海飞机设计研究院, 上海 201210
  • 收稿日期:2020-12-04 修回日期:2021-01-25 出版日期:2022-03-15 发布日期:2021-01-26
  • 通讯作者: 于哲峰 E-mail:yuzf@sjtu.edu.cn

Hybrid fluid-to-solid loads transformation based on pressure-interpolation/force-equivalence for launch vehicles

FAN Yida1, MAO Yuming2, SHU Zhongping2, WANG Jifei2, ZHANG Yangyang3, YU Zhefeng1   

  1. 1. School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai 200240, China;
    2. Shanghai Institute of Aerospace System Engineering, Shanghai 201109, China;
    3. Shanghai Aircraft Design and Research Institute, Shanghai 201210, China
  • Received:2020-12-04 Revised:2021-01-25 Online:2022-03-15 Published:2021-01-26

摘要: 在进行火箭结构分析时,需要将气动载荷转换为结构载荷。使用压力插值的转换法可保证局部载荷等效,但这种方法需要结构模型外形与气动模型保持一致,而结构模型往往只保留主要承力结构,忽略整流罩等表面细节。针对这一问题,提出一种基于压力插值和力等效的流-固载荷混合转换方法。对于表面有凸起的火箭模型,可通过对比某个气动压力点与其附近的结构单元中心点到火箭轴心的距离,从而判断该气动压力点处的结构模型是否与气动模型外形一致,划分出结构模型表面一致和不一致的区域。之后对于外形一致的区域采用压力插值法,对于外形不一致区域采用力等效法。对某火箭模型的计算结果表明,载荷转换前后的合力、合力矩误差均小于3%。本方法具有适用范围广、转换过程自动化的特点,具有较好的工程应用潜力。

关键词: 压力插值, 样条插值, 力等效法, 火箭结构, 流-固载荷转换

Abstract: Structural analysis of rockets entails conversion of aerodynamic loads into structural loads.The transformation method of pressure interpolation can ensure the equivalence of the local loads, meanwhile requiring the shape of the structural model to be consistent with that of the aerodynamic model.However, the structural model usually retains only the main load-bearing structures while neglecting the fairing and other surface details.To solve this problem, this paper proposes a hybrid fluid-to-solid load conversion method based on pressure interpolation and force equivalence.For the rocket model with protuberance on its surface, comparison of the distances between a certain aerodynamic pressure point and the center point of its nearby structural elements to the rocket axis can be conducted to judge whether the structural model near the aerodynamic pressure point is consistent with the aerodynamic model in shape, thereby differentiating the consistent and inconsistent areas on the surface of the structural model.Then the pressure interpolation method is used for the area with the consistent shape, while the force equivalent method is adopted for that with the inconsistent shape.The calculation results of a rocket model show that both the errors of the resultant force and moment before and after the load conversion are smaller than 3%.This method exhibits good engineering applicability potential with characteristics such as wide application range and automatic conversion process.

Key words: pressure interpolation, spline interpolation, force equivalent method, launch vehicle structure, fluid-to-solid load conversion

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