Study on buffeting test of large diameter fairing launch vehicles selection

被引：0
作者：
Wang G. [1 ]
Yan Z. [2 ]
Ji C. [3 ]
Tang W. [2 ]
Wei Y. [2 ]
机构：
[1] China Academy of Launch Vehicle Technology, Beijing
[2] Beijing Institute of Astronautical System Engineering, Beijing
[3] China Academy of Aerospace Aerodynamics, Beijing
来源：
Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2023年 / 49卷 / 12期
基金：
中国国家自然科学基金;
关键词：
buffeting; eigensystem realization algorithm; fairing; full-elastic model; launch vehicle; transonic; wind tunnel test;
D O I：
10.13700/j.bh.1001-5965.2022.0106
中图分类号：
学科分类号：
摘要：
The envelope size of the fairing will be recommended during the first stage of launch vehicle design in accordance with the satellite’s envelope size requirements, which also affects the launch vehicle’s basic configuration design. To predict the buffeting risk of this configuration, the aerodynamics design team will carry out transonic aerodynamic buffeting test research in the aspect of the specific launch vehicle configuration size, frequency, and stiffness data. In this paper, the buffeting test technology of the full elastic model is adopted, and the research goal is to carry out the buffeting test in two directions for three configurations of 5 m diameter fairing of a certain rocket. The buffeting risk of the three configurations is evaluated by using the eigen system realization algorithm. The research findings indicate that the first-order elastic model of the 5.2 m diameter faring + 3.35 m diameter three-stage configuration has a quick response to incoming flow and a small response amplitude, and that the aerodynamic damping values of the first and second free-free bending modes are both positive. As a result, it can be used as the shape design solution for the large-diameter fairing of the medium-sized launch vehicle in our country. © 2023 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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收藏
页码：3230 / 3236
页数：6
相关论文
共 16 条
  • [1] JI C, WU Y S, HOU Y Y., Experimental study of aerodynamic damping characteristics of a launch vehicle with boosters in transonic flow, Journal of Experiments in Fluid Mechanics, 34, 6, pp. 24-31, (2020)
  • [2] ZHAO R, RONG J L, LI Y J., An investigation of fluctuating pressure environment around rocket fairing with different curve-types, Acta Armamentarii, 38, 5, pp. 1020-1026, (2017)
  • [3] NI J M., Review of aerodynamic design of China’s launch vehicle, Proceedings of the Modern Aerodynamics Symposium, pp. 189-195, (2005)
  • [4] COLE H A, ERICKSON A L, RAINEY A G., Buffeting during atmospheric ascent: NASA-SP-8001, (1970)
  • [5] AZEVEDO J L F., Aeroelastic analysis of launch vehicles in transonic flight: AIAA 87-0708, (1987)
  • [6] LONG L H., General design of liquid missile and launch vehicle, pp. 546-548, (1989)
  • [7] COLE S R, HENNING T L., Buffet response of a hammerhead launch vehicle wind-tunnel model, Journal of Spacecraft and Rockets, 29, 3, pp. 24-30, (1992)
  • [8] SINCLAIR A J, FLOWERS G T., Low-order aeroelastic model of launch-vehicle dynamics: AIAA 2010-7725, (2010)
  • [9] BOMBARDIER G D., Final post-test report on seven percent transonic buffet model for various Titan Ⅲ configurations: SSD-CR-66-563, (1967)
  • [10] FENG M X, WANG Z A., Experiments of transonic derivatives and buffeting of rocket, Journal of Astronautics, 1, pp. 55-62, (1987)
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