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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页码：3230 / 3236
页数：6
相关论文
共 16 条
  • [11] BAI K, FENG M X., Aeroelastic model and the buffet experimental technique, Experiments and Measurements in Fluid Mechanics, 13, 1, pp. 38-42, (1999)
  • [12] JI C, RAN J H, LI F, Et al., The aerodynamic damping test of elastic launch vehicle model in transonic flow, Proceedings of the 64th International Astronautical Congress, (2013)
  • [13] JI C, WU Y S, HE G, Et al., Experimental study on aerodynamic damping wind tunnel of launch vehicle, Proceedings of the 12th National Aeroelasticity Conference, pp. 466-470, (2011)
  • [14] LIU Z Q., Transonic aerodynamics non-damped phenomenon of elastic coupling, (2001)
  • [15] LONG L H., General design of liquid missile and launch vehicle, pp. 9-11, (1989)
  • [16] JUANG J N, PAPPA R S., An eigensystem realization algorithm for modal parameter identification and model reduction, Journal of Guidance, Control, and Dynamics, 8, 5, pp. 620-627, (1985)
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