类AHW助推滑翔飞行器气动布局优化设计分析

刘深深; 冯毅; 杨肖峰; 唐伟; 桂业伟

doi:10.7638/kqdlxxb-2016.0105

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类AHW助推滑翔飞行器气动布局优化设计分析

研究论文 | 更新时间：2026-05-28

- 类AHW助推滑翔飞行器气动布局优化设计分析
- Study on the optimization and aerodynamics characteristics analysis for AHW analog boost gliding vehicle
- 空气动力学学报 2019年37卷第2期页码：226-233
- 作者机构：
  
  中国空气动力研究与发展中心计算空气动力研究所,绵阳,621000
- 作者简介：
  
  刘深深(1990-), 女, 硕士, 研究方向:高超声速飞行器气动布局设计及气动力/热/结构多场耦合.E-mail:lsssml1990@126.com
- 基金信息：
  
  国家自然科学基金（11702315，11702311）
- DOI：10.7638/kqdlxxb-2016.0105
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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刘深深, 冯毅, 杨肖峰, 唐伟, 桂业伟. 类AHW助推滑翔飞行器气动布局优化设计分析[J]. 空气动力学学报, 2019, 37(2): 226-233.

LIU Shenshen, FENG Yi, YANG Xiaofeng, et al. Study on the optimization and aerodynamics characteristics analysis for AHW analog boost gliding vehicle[J]. 2019, 37(2): 226-233.
刘深深, 冯毅, 杨肖峰, 唐伟, 桂业伟. 类AHW助推滑翔飞行器气动布局优化设计分析[J]. 空气动力学学报, 2019, 37(2): 226-233. DOI： 10.7638/kqdlxxb-2016.0105.

LIU Shenshen, FENG Yi, YANG Xiaofeng, et al. Study on the optimization and aerodynamics characteristics analysis for AHW analog boost gliding vehicle[J]. 2019, 37(2): 226-233. DOI： 10.7638/kqdlxxb-2016.0105.

摘要

AHW作为美国首飞即成功完成高超声速助推滑翔飞行试验的飞行器受到越来越多的关注。本文针对该类钝双锥十字形小尺寸弹翼外形气动布局阶段的共性问题进行了研究。基于参数化方法建立的基本外形和工程气动力估算模型，采用正交设计方法进行了参数敏感性分析，并对正交优化结果进行了数值模拟验证分析，在此基础上利用多目标优化方法完成了弹体布局的进一步优化。同时在优化外形基础上考虑气动特性以及总体和防热需求，对操纵面的类型、质心与操纵面尺寸配置以及操纵效率进行了探讨分析，给出了气动布局建议。研究表明，该类布局方式可以获得较高的配平升力、配平升阻比及容积率，并且合理的质心位置/舵面尺寸的组合可以实现操纵性需求，是高超声速滑翔飞行器的一种潜在布局方案。

Abstract

AHW has been attracting more and more attention since its first hypersonic boost-glide flight test by the United States succeeds. In this paper

studies were performed on aerodynamics configuration optimization about biconic body with cruciform small size flaps. The basic configuration was generated by parameterized modeling method and the orthogonal design was adopted to conduct the parameter sensitivity analysis. Numerical simulations were performed to verify the results and analysis of the optimization. In addition to

the optimized biconic body was achieved by multi-objective optimization method. Based on the optimized configuration

the analysis of aerodynamic characteristics and the aerodynamic control surface matching

press center

mass center location

corresponding control efficiency under global constraint condition

and heat protection requirement are conducted. Moreover

the configuration design advice was given. The analysis shows that the proposed vehicle is optimized with higher lift

lift to drag ratio and volumetric efficiency

as well as better trimming and control efficiency. The result indicates that a glide vehicle with biconic body and cruciform small size flaps is one of the possible choices for hypersonic boost glide. The configuration needs to be further investigated.

关键词

Keywords

references

US Army Space and Missile Defense Command/Army Forces Strategic Command. Advanced hypersonic weapon program environmental assessment[Z]. 2011.

GAO Q, ZHAO J B, LI Q. Study on lateral-directional stability of HTV-2 like configuration[J]. Journal of Astronautics, 2014, 35(6):657-662. (in Chinese)

ZHAN P G. Aerodynamic analysis of US army advanced hypersonic weapon[J]. Aeronautical ScienceTechnology, 2015, 26(1):07-11. (in Chinese)

FENG Y, TANG W, GUI Y W. Optimization of configuration and trajectory for hypersonic vehicles[J]. Acta Aerodynamica Sinica, 2014, 32(6):800-805.

FENG Y, TANG W, GUI Y W. Aerodynamic configuration optimization by the integration of aerodynamics, aerothermodynamics and trajectory for hypersonic vehicles[J]. Chinese Science Bulletin, 2014, 59(33):4608-4615.

TANG W, ZHANG Y, LI W J, et al. Aerodynamic design and optimization for vehicles with conic cross section[J]. Optimization of configuration and trajectory for hypersonic vehicles[J]. Journal of Astronautics, 2004, 25(4):429-433. (in Chinese)

KULFAN B M. Recent extensions and applications of the "CST" universal parametric geometry representation[R]. AIAA 2007-7709, 2007.

KULFAN B M. A universal parametric geometry representation method-"CST"[R]. AIAA 2007-62, 2007.

FENG Y, TANG W, XIAO G M, et al. Aerodynamics configuration conceptual design for X-37 analog transporter[J]. Acta Aerodynamica Sinica, 2012, 31(1):94-98.

GENTRY A E, SMYTH D N, OLIVER W R. The mark IV supersoic/hypersonic arbitrary-body program, Vol.I[R]. McDonnell-Douglas Corp, Technical Report AFFDL-TR-73-159, 1973.

WON H, LEVINE S, PFAENDER H, et al. Using response surface metamodels to optimize the aerodynamic performance of a high speed stand of missile within a multi-disciplinary environment[R]. AIAA 2002-5855, 2002.

MICHAEL J G, ROBERT D B. Analytic hypersonic aerodynamics for conceptual design of entry vehicles[R]. AIAA 2010-1212, 2010.

LIU S S, XIE J, FENG Y, et al. Aerodynamic characteristics analysis for HX analog lifting body[J]. Acta Aerodynamica Sinica, 2017, 35(6):787-791. (in Chinese)

YANG X F, TANG W, GUI Y W. Aerodynamics configuration study for CSTS reentry capsule[J]. Acta Aerodynamica Sinica, 2014, 32(4):493-498. (in Chinese)

LIU D D, CHEN P C, TANG L, et al. Integrated hypersonic aerothermoelastic methodology for transatmospheric vehicle(TAV)/thermal protection system(TPS) structural design and optimization[R]. ZONA Technology, Inc, Technical Report AFRL-VA-WP-TR-2002-3047, 2002.

FENG Y, TANG W, REN J X, et al. Parametric geometry representation method for hypersonic vehicle configuration[J]. Acta Aerodynamica Sinica, 2012, 30(4):546-550. (in Chinese)

FENG Y, TANG W, XIAO G M, et al. Aerodynamics analysis for X-33 analog lifting body transporter[J]. Acta Aerodynamica Sinica, 2013, 31(4):473-476. (in Chinese)

XIAO G M, FENG Y, TANG W, et al. Aerodynamics conceptual design for ATLLAS-M6 analog transporter aircraft[J]. Acta Aerodynamica Sinica, 2012, 30(5):592-596. (in Chinese)

TANG W. Aerodynamic design study for new generation aeronautical maneuverable vehicle[D]. Northwestern Polytechnical University, 2005. (in Chinese)

HUANG Z C. Aerodynamics of hypersonic vehicle[M]. Beijing:National Defense Industry Press, 1995. (in Chinese)

TANG W, GUI Y W, FANG F. Aerodynamic configurations selection for lift reentry capsule. Optimization of Configuration and Trajectory for Hypersonic Vehicles[J]. Journal of Astronautics, 2008, 29(1):84-88. (in Chinese)

MA Q, TANG W, ZHANG L M. Engineering Prediction method for aerodynamics of biconic vehicle with flaps[J]. Journal of Astronautics, 2003, 24(6):552-554. (in Chinese)

TANG W, ZHANG Y, MA Q, et al. Aerodynamics configuration design for elliptical cross section vehicle with flaps[J]. Acta Aerodynamica Sinica, 2006, 24(2):223-226. (in Chinese)

TANG W, ZENG L, XIAO G M, et al. Aerodynamic configuration conceptional design for high maneuverable lift body with flaps[J]. Acta Aerodynamica Sinica, 2011, 29(3):370-373. (in Chinese)

TANG W, ZHANG Y, MA Q, et al. A study on conic maneuverability of a biconic vehicle with flaps[J]. Acta Aerodynamica Sinica, 2006, 24(1):80-84. (in Chinese)

TANG W, FENG Y, YANG X F, et al. Practices of aerodynamic configuration design for non-ballistic trajectory vehicles[J]. Physics of Gases, 2017, 2(1):1-12. (in Chinese)

DENG F, REN H Y, LI X G, et al. Rudder effect of near-space hypersonic gliding vehicle with different control surfaces[J]. Acta Aerodynamica Sinica, 2014, 32(2):240-245. (in Chinese)

LIU W L, ZHU G S. A study of the effects of cruciform configuration and bifurcate configuration on aerodynamic characteristics of maneuvering reentry vehicles[J]. Missiles and Space Vehicles, 2002, 4:33-38. (in Chinese)

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