一种给定容积空间的乘波构型参数化设计方法

吴乔; 卢笙; 叶友达; 张启明

doi:10.7638/kqdlxxb-2018.0113

欢迎来到能源电力期刊网！

English Version 期刊登录

您当前的位置：

首页 >

文章列表页 >

一种给定容积空间的乘波构型参数化设计方法

研究论文 | 更新时间：2026-05-28

- 一种给定容积空间的乘波构型参数化设计方法
- A parametric design method for the waverider configuration with given volume
- 空气动力学学报 2019年37卷第5期页码：754-761
- 作者机构：
  
  1. 北京航空航天大学宇航学院,北京,100086
  2. 国家计算流体力学实验室,北京,100086
- 作者简介：
  
  吴乔(1993-), 男, 河北保定人, 硕士研究生, 研究方向:高超声速飞行器设计.E-mail:wuqiaobuaa@qq.com
  卢笙(1962-), 女, 四川自贡人, 副研究员, 硕士生导师, 研究方向:计算机软件开发, 飞行器飞行仿真, 计算空气动力学数值模拟.E-mail:lusheng@buaa.edu.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0113
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
移动端阅览
吴乔, 卢笙, 叶友达, 张启明. 一种给定容积空间的乘波构型参数化设计方法[J]. 空气动力学学报, 2019, 37(5): 754-761.

WU Qiao, LU Sheng, YE Youda, et al. A parametric design method for the waverider configuration with given volume[J]. 2019, 37(5): 754-761.
吴乔, 卢笙, 叶友达, 张启明. 一种给定容积空间的乘波构型参数化设计方法[J]. 空气动力学学报, 2019, 37(5): 754-761. DOI： 10.7638/kqdlxxb-2018.0113.

WU Qiao, LU Sheng, YE Youda, et al. A parametric design method for the waverider configuration with given volume[J]. 2019, 37(5): 754-761. DOI： 10.7638/kqdlxxb-2018.0113.

摘要

乘波构型高超声速飞行器布局具有高升阻比的优点，但有效容积低和尖锐前缘使其在实际工程应用中受限。为弥补乘波构型飞行器有效容积低的不足，提出了一种乘波构型上表面参数化设计方法，同时开展了前缘钝化研究，采用增加前缘材料的方法进行钝化。分析了上表面不同设计参数对乘波构型飞行器容积率和气动性能的影响，研究了飞行器气动特性随迎角和马赫数的变化规律。计算结果表明，钝化后的经给定容积上表面设计的乘波构型有效提升了有效容积及容积率，并且仍能保持良好的乘波特性。数值仿真结果表明容积效率和气动性能是相互矛盾的关系，需要根据实际情况进行权衡。对于给定有效容积上表面设计的乘波构型高超声速飞行器，适合在一定范围的正迎角下飞行，并且能在较大的马赫数范围内保持优良的气动特性。研究可为提升高超声速乘波飞行器有效容积提供参考，提高了乘波构型飞行器的工程应用性。

Abstract

Waverider is an effective configuration for hypersonic aerocraft with high lift-to-drag ratios. But its insufficient effective volume and sharp leading edge lead to difficulties in the engineering application of waverider. To expand effective volume of waveriders

a parametric upper surface design method was created and discussed. The blunt method was analyzed in this work

and the influence of different design parameters of upper surface design on effective volume and aerodynamic performance were discussed. The influence of attack angle and Mach number on the aerodynamic characteristics of upper surface design with the consideration of practical application was also analyzed. The results show that the design method can expand volume effectively. The analysis of flow field indicated that the blunted waverider with upper surface design can maintain the "wave rider" characteristic well. The relationship between the effective volume and the aerodynamic performance is inconsistent

which needs to be considered on the basis of different practical situations. The upper surface design waverider performed well at positive attack angle within limits and Mach numbers in wide range. A new method of upper surface design was proposed and studied about relative scientific problems. Based on the results

some useful advice can be obtained for expanding effective volume of waverider

which may improve waverider from an academic concept into a practical engineering application.

关键词

Keywords

references

ZHAO G L, HU L, WEN J, et al. An overview of the research on waveriders and waverider-derived hypersonic vehicles[J]. Advances in Mechanics, 2003, 33(3):357-374. (in Chinese)

NONWEILER T R F. Aerodynamic problems of manned space vehicles[J]. Aeronautical Journal, 1959, 63(585):521-528.

STARKEY R, LEWIS M. A simple analytical model for parametric studies of hypersonic waveriders[C]. AIAA International Space Planes and Hypersonic Systems and Technologies Conference. 2013: 516-523

STARKEY R P, LEWISM J. Analytical off-design lift-to-drag-ratio analysis for hypersonic waveriders[J]. Journal of Spacecraft Rockets, 2015, 37(37):684-691.

ZHANG J, WANG F M. Parametric waveriders design method study[J]. Acta Aerodynamica Sinica, 2008, 26(1):115-118. (in Chinese)

RASMUSSEN M L. Analysis of cone-derived waverider by hypersonic small-disturbance theory[C]//Proc of International Hypersonic Waverider Symp, 1990.

OHTA T, MATSUZAKI R. Flow visualization on lower surfaces of wave rider configurations at Mach 5.5[J]. Journal of Spacecraft Rockets, 2012, 35(3):405-407.

OHTA T, MIYAGAWA T, MATSUZAKI R. Experimental study of cone-derived waveriders at Mach 5.5[J]. Journal of Spacecraft Rockets, 2015, 34(4):445-448.

LIU J M, HOU Z Q, SONG G B, et al. Optimization design and aerodynamic characteristic analysis of waverider based hypersonic cruise missile configuration[J]. Acta Aerodynamica Sinica, 2011, 29(1):118-123. (in Chinese)

LIU J X, HOU Z X, CHENX Q. Research on geometry design for hypersonic glide vehicle[J]. Missiles and Space Vehicles, 2011(3):1-5. (in Chinese)

HE X Z, NI H L. Osculating curved cone (OCC) waverider:design methods and performance analysis[J]. Chinese Journal of Theoretical and Applied Mechanics, 2011, 43(6):1077-1082. (in Chinese)

WU Y C, HE Y Y, HE W, et al. The design of osculating curved cone waverider based hypersonic vehicle[J]. Acta Aerodynamica Sinica, 2014, 32(1):8-13. (in Chinese)

CHEN B Y, LIU C Z, JIC Q. Waverider design and analysis based on shock-fitting method[J]. Acta Aerodynamica Sinica, 2017, 35(3):421-428. (in Chinese)

LIU J M, HOU Z Q, SONG G B, et al. Blunted method for waverider and its effect on performance[J]. Journal of Astronautics, 2011, 32(5):966-974. (in Chinese)

SANTOS W. Bluntness impact on lift-to-drag ratio of hypersonic wedge flow[J]. Journal of Spacecraft Rockets, 2009, 46(2):329-339.

CHEN X Q, HENG G H, JIANG Z R, et al. Blunt methods for the leading edge of waverider[J]. Acta Aerodynamica Sinica, 2017, 35(1):108-114. (in Chinese)

HAN H Q, ZHANG C A, WANG F M. Study on multi-physical effects of hypersonic gliding waverider vehicles[J]. Acta Aerodynamica Sinica, 2014, 32(1):101-108. (in Chinese)

XU D J, CAI G B, XU X, et al. Design studies for three-dimensional forebody of hypersonic vehicle based on PNS optimization procedure[C]. 58th International Astronautical Congress, IAC-07-C4. 5. 02, 2007.

LIU J X. Study on aerodynamic and aero-heating basic problems of hypersonic nonuniform blunt waverider[D]. Changsha: National University of Defense Technology, 2013. (in Chinese)

LOBBIA M, SUZUKI K. Design and analysis of payload-optimized waveriders[C]. AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference. 2001.

LYU Z J. Research on aerodynamic configuration design technology of horizontal takeoff and landing hypersonic launch vehicle[D]. Nanjing: Nanjing University of Aeronautics and Astronautics. (in Chinese)

COCKRELL C E Jr. Interpretation of waverider performance data using computational fluid dynamics[J]. Journal of Aircraft, 1994, 31(5).

COCKRELL C E Jr, HUEBNER L D, FINLEY D B. Aerodynamic performance and flow-field characteristics of two waverider-based hypersonic cruise configurations[R]. AIAA-95-0736, 1995.

HE X, RASMUSSEN M L. Computational analysis of off-design waveriders[J]. Journal of Aircraft, 2015, 31(2):345-353.

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

考虑近距离海洋下垫面影响的对称风机翼型静气动特性

翼尖链翼组合式无人机气动特性研究

基于透气结构的海鸥仿生翼型气动特性

基于GPR模型的多保真气动力建模方法

湍流工况涡流发生器对风力机翼型气动特性影响的试验研究