火箭整流罩脉动压力环境数值模拟与优化设计

樊宇翔; 于洋; 席柯; 赵瑞; 任方

doi:10.7638/kqdlxxb-2021.0314

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火箭整流罩脉动压力环境数值模拟与优化设计

研究论文 | 更新时间：2026-05-28

- 火箭整流罩脉动压力环境数值模拟与优化设计
- Numerical simulation and optimization design of fluctuation pressure environment of a rocket fairing
- 空气动力学学报 2022年40卷第6期页码：29-37
- 作者机构：
  
  1. 北京理工大学宇航学院,北京,100081
  2. 北京强度环境研究所可靠性与环境工程技术重点实验室,北京,100076
  3. 中国兵器工业导航与控制技术研究所,北京,100089
- 作者简介：
  
  樊宇翔（1998-），男，山西忻州人，硕士研究生，研究方向：飞行器壁面脉动压力环境. E-mail：ffanyuxiang@163.com
  赵瑞*，副教授，研究方向：计算流体力学研究. E-mail：zr@bit.edu.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0314
  中图分类号： V421.1
- 纸质出版：2022
- 稿件说明：
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樊宇翔, 于洋, 席柯, 等. 火箭整流罩脉动压力环境数值模拟与优化设计[J]. 空气动力学学报, 2022, 40(6): 29−37.

FAN Yuxiang, YU Yang, XI Ke, et al. Numerical simulation and optimization design of fluctuation pressure environment of a rocket fairing[J]. 2022, 40(6): 29-37.
樊宇翔, 于洋, 席柯, 等. 火箭整流罩脉动压力环境数值模拟与优化设计[J]. 空气动力学学报, 2022, 40(6): 29−37. DOI： 10.7638/kqdlxxb-2021.0314

FAN Yuxiang, YU Yang, XI Ke, et al. Numerical simulation and optimization design of fluctuation pressure environment of a rocket fairing[J]. 2022, 40(6): 29-37. DOI： 10.7638/kqdlxxb-2021.0314.

摘要

采用雷诺平均N-S方程（RANS）求解流场与非线性噪声方程（NLAS）求解声场相结合的方法（RANS/NLAS），对跨声速条件下火箭整流罩外部的脉动压力环境进行数值模拟与气动外形优化设计研究。通过与国内外文献及风洞试验结果对比发现，使用NLAS方法能够利用较少的网格量准确模拟脉动压力的传播历程。同时，结果表明：跨声速流动中，在火箭整流罩的头锥肩部会出现激波/边界层干扰，而在后部倒锥部位会产生大分离区，因此在肩部和倒锥区域脉动压力环境最为恶劣；随着迎角的增加，背风面头锥肩部的脉动压力环境更加恶劣，倒锥区域减缓。为抑制倒锥区域的脉动压力，新设计了直线外形、正弦曲线外形、“切线弧+圆弧”外形三种倒锥轮廓线方案，对比分析了不同方案的倒锥区域时均摩擦力系数、分离区、均方根脉动压力系数，得出了“切线弧+圆弧”外形最有利于优化其脉动压力环境的结论。

Abstract

The RANS/NLAS coupling method is used to simulate and optimize the fluctuating pressure environment of a rocket fairing under transonic conditions. The results indicate that the RANS/NLAS method can accurately simulate the fluctuating pressure with less grids. When transonic flow passes the rocket fairing

shock waves/boundary layer interaction occurs at the shoulder

and a large separation region is formed at the inverted cone

thus the fluctuating pressure environment is severe on both the shoulder and the inverted cone. With the increase of the attack angle

the fluctuating pressure environment on the leeward side of th

e shoulder becomes severe

but that on the inverted cone region tends to be alleviated. To optimize the fluctuating pressure environment at the inverted cone

three new outline profiles of the inverted cone are designed

i.e. the straight line shape

the sinusoidal line shape and the “tangent arc + circular arc” shape

respectively. The time-averaged friction coefficient

separation region

root-mean-square pressure coefficient

_rms

of the three designs are compared

and the result shows that the “tangent arc + circular arc” design is the most effective in optimizing the fluctuating pressure environment.

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Keywords

references

黄寿康. 流体动力·弹道·载荷·环境[M]. 北京: 宇航出版社, 1991.

LIU Z H, REN F. Review on numerical computation of spacecraft pressure fluctuations[J]. Structure Environment Engineering, 2013, 40(6): 45-50. (in Chinese)

RAINEY A G. Progress on the launch-vehicle buffeting problem[J]. Journal of Spacecraft and Rockets, 1965, 2(3): 289-299. DOI:10.2514/3.28174

SUN M, PAN Z W. Noise environment prediction and anti-acoustic design of payload fairing[J]. Missiles and Space Vehicles, 2008(4): 6-10. (in Chinese)

PLOTKIN K J, ROBERTSON J E. Prediction of space-shuttle fluctuating pressure environments, including rocket plume effects[R]. NASA-CR-124347, June 1973.

J. E. Robertson, 刘志珩, 万音. 飞行中脉动压力环境(包括突起物引起的流动)的预示方法[J]. 国外导弹技术, 1979(6): 18-67.

TSUTSUMI S, TAKAKI R, TAKAMA Y, et al. Hybrid LES/RANS simulations of transonic flowfield around a rocket fairing[C]// 30th AIAA Applied Aerodynamics Conference, New Orleans, Louisiana. Reston, Virigina: AIAA, 2012. doi: 10.2514/6.2012-2900

SHUR M L, SPALART P R, STRELETS M K, et al. A hybrid RANS-LES approach with delayed-DES and wall-modelled LES capabilities[J]. International Journal of Heat and Fluid Flow, 2008, 29(6): 1638-1649. DOI:10.1016/j.ijheatfluidflow.2008.07.001

ZHAO R, RONG J L, REN F, et al. Large eddy simulation of the aeroacoustic environment of a rocket fairing[J]. Journal of Astronautics, 2015, 36(9): 988-994. (in Chinese)

ZHAO R, RONG J L, REN F, et al. Improvement of the fluctuating pressure empirical functions for a body of revolution at transonic Mach numbers[J]. Journal of Astronautics, 2016, 37(10): 1179-1184. (in Chinese)

ZHAO R, RONG J L, LI Y J, et al. An investigation of fluctuating pressure environment around rocket fairing with different curvetypes[J]. Acta Armamentarii, 2017, 38(5): 1020-1026. (in Chinese)

SHI X P, ZHAO R, RONG J L, et al. Numerical simulation of fluctuating pressure environment of Mars entry capsule[J]. Journal of Astronautics, 2018, 39(5): 482-490. (in Chinese)

SHI X P, ZHAO R, RONG J L, et al. Numerical simulation of fluctuating pressure environment of Mars entry capsule under forced oscillation[J]. Journal of Astronautics, 2019, 40(2): 148-155. (in Chinese)

BATTEN P, RIBALDONE E, CASELLA M, et al. Towards a generalized non-linear acoustics solver[C]//Proc of the 10th AIAA/CEAS Aeroacoustics Conference, Manchester, GREAT BRITAIN. Reston, Virigina: AIAA, 2004. doi: 10.2514/6.2004-3001

MORRIS P J, LONG L N, BANGALORE A, et al. A parallel three-dimensional computational aeroacoustics method using nonlinear disturbance equations[J]. Journal of Computational Physics, 1997, 133(1): 56-74. DOI:10.1006/jcph.1997.5646

KRAICHNAN R H. Diffusion by a random velocity field[J]. Physics of Fluids, 1970, 13(1): 22. DOI:10.1063/1.1692799

SMIRNOV A, SHI S, CELIK I. Random flow generation technique for large eddy simulations and particle-dynamics modeling[J]. Journal of Fluids Engineering, 2001, 123(2): 359-371. DOI:10.1115/1.1369598

WANG Y D, GUO L, TONG M B, et al. Active control and nonlinear numerical simulation for oscillating pressure of high-speed aircraft cavity[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1): 213-222. (in Chinese)

CHEN B Q, WANG Y D. Nonlinear numerical simulation for oscillating pressure in cavity and passive control research[J]. International Journal of Aerospace Engineering, 2019, 2019: 4153287. DOI:10.1155/2019/4153287

MA L X, LI E Y, SUN S X, et al. Numerical simulation of transonic cavity acoustic properties[J]. Journal of Civil Aviation University of China, 2020, 38(5): 10-16. (in Chinese)

SUN Z X, SONG J J, AN Y R. Numerical simulation of aerodynamic noise generated by high speed trains[J]. Engineering Applications of Computational Fluid Mechanics, 2012, 6(2): 173-185. DOI:10.1080/19942060.2012.11015412

LIU F F, CHEN G, LI Y M. An RANS/NLAS-based numerical simulation for the prediction of aerodynamic noise due to vortex-structure interaction of airfoil[J]. Journal of Xi'an Jiaotong University, 2015, 49(9): 141-146. (in Chinese)

YU L, SONG W P. Aerodynamic noise prediction for wind turbine airfoils using non-linear acoustics solvers[J]. Acta Aerodynamica Sinica, 2013, 31(2): 266-272. (in Chinese)

SILVA C, ALMEIDA O, BATTEN P. Investigation of an axi-symmetric subsonic turbulent jet using computational aeroacoustics tools[C]// 13th AIAA/CEAS Aeroacoustics Conference (28th AIAA Aeroacoustics Conference), Rome, Italy. Reston, Virigina: AIAA, 2007. doi: 10.2514/6.2007-3656

REN S J, ZHANG S Y, YAN G R. A prediction of fluctuation pressure conditions with transonic rocket by RANS/NLAS method[J]. Journal of Solid Rocket Technology, 2011, 34(4): 418-422. (in Chinese)

BATTEN P, GOLDBERG U, CHAKRAVARTHY S. Interfacing statistical turbulence closures with large-eddy simulation[J]. AIAA Journal, 2004, 42(3): 485-492. DOI:10.2514/1.3496

BATTEN P, GOLDBERG U, CHAKRAVARTHY S. Sub-grid turbulence modeling for unsteady flow with acoustic resonance[C]//Proc of the 38th Aerospace Sciences Meeting and Exhibit, Reno, NV. Reston, Virginia: AIAA, 2000: 473. doi: 10.2514/6.2000-473

PALANISWAMY S, GOLDBERG U, PEROOMIAN O, et al. Predictions of axial and transverse injection into supersonic flow[J]. Flow Turbulence and Combustion, 2001, 66(1): 37-55. DOI:10.1023/A: 1011479002452

GOLDBERG U, PEROOMIAN O, PALANISWAMY S, et al. Anisotropic k-epsilon model for adverse pressure gradient flow[C]// 37th Aerospace Sciences Meeting and Exhibit, Reno, NV, USA. Reston, Virigina: AIAA, 1999. doi: 10.2514/6.1999-152

LUAN Y G. Research on performance of duct moisture separator with high efficiency[D]. Harbin: Harbin Engineering University, 2006 (in Chinese).

PENG K. Accurate and rapid method of aircraft aero-forceAero-heating calculation and research on applications[D]. Changsha: National University of Defense Technology, 2016 (in Chinese).

OUYANG H. Research on the unsteady combustion process in scramjet combustor[D]. Changsha: National University of Defense Technology, 2018 (in Chinese).

GAO F. Research on microjet used for flow vector active control[D]. Xi'an: Northwestern Polytechnical University, 2003 (in Chinese).

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