乘波概念应用于吸气式高超声速飞行器机体/进气道一体化设计方法研究综述

丁峰; 柳军; 沈赤兵; 刘珍; 陈韶华; 黄伟

doi:10.11729/syltlx20180080

乘波概念应用于吸气式高超声速飞行器机体/进气道一体化设计方法研究综述

丁峰^{1, 2,},
柳军^{1, 2, ,},
沈赤兵^{1, 2},
刘珍^{1, 2},
陈韶华^{1, 2},
黄伟^{1, 2}

1.
国防科技大学空天科学学院, 长沙 410073
2.
国防科技大学高超声速冲压发动机技术重点实验室, 长沙 410073

基金项目:

国家自然科学基金项目 11702322

湖南省自然科学基金项目 2018JJ3589

详细信息

作者简介:
丁峰(1988-), 男, 山东梁山人, 博士, 讲师。研究方向:高超声速飞行器气动设计、进气道设计以及机体/推进一体化。通信地址:湖南省长沙市开福区德雅路109号(410073)。E-mail:dingcuifengdcf@163.com

通讯作者:
柳军, E-mail:liujun@nudt.edu.cn

中图分类号: V130.25
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出版历程
- 收稿日期: 2018-06-03
- 修回日期: 2018-10-31
- 刊出日期: 2018-12-24

An overview of waverider design concept in airframe-inlet integration methodology for air-breathing hypersonic vehicles

Ding Feng^{1, 2,},
Liu Jun^{1, 2, ,},
Shen Chibing^{1, 2},
Liu Zhen^{1, 2},
Chen Shaohua^{1, 2},
Huang Wei^{1, 2}

1.
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
2.
Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China

摘要

摘要: 乘波体构型应用于吸气式高超声速飞行器设计主要有两大优势：一是可以高效地捕获预压缩后的气流；二是通过优化，可以实现飞行器的高升阻比性能设计。基于这两个优势，乘波概念应用于高超声速飞行器机体/进气道气动一体化设计可分为两大类：乘波前体/进气道一体化设计和乘波机体/进气道一体化设计，前者主要利用乘波体高效捕获预压缩气流的特性，而后者则同时利用乘波设计的两个优势。本文总结了国内外学者将乘波概念应用于机体/进气道一体化设计的两大类方法，对其进行了较为细致的分类，归纳总结出"通过设计基准流场进行流向设计、应用吻切理论或几何拼接方法进行展向设计"的总体设计思路，分析了今后的研究发展趋势。
- 高超声速飞行器 /
- 乘波体 /
- 机体/进气道一体化 /
- 气动设计
Abstract: As a waverider can possess high lift-to-drag ratio characteristics as well as an ideal pre-compression surface of the inlet system, it has become one of the most promising designs for air-breathing hypersonic vehicles. There are two classes of general methodologies for utilizing the waverider concept in a hypersonic vehicle design. In the first class, the waverider is used only as the forebody of a vehicle, and it behaves as the pre-compression surface to efficiently provide the inlet system with the required compression flow field. In the second class, in order to take advantage of the waverider's high lift-to-drag ratio characteristics as well as the ideal pre-compression surface for the engine, the waverider design is used as the basis for the design of the entire vehicle, and the engine is generated within the pristine waverider definition while maintains the bow shock wave attaching to the leading edge. In this paper, the waverider applications by the domestic and overseas scholars in the airframe-inlet integration methodology for the air-breathing hypersonic vehicles are reviewed and classified. The idea for the design of a waverider-derived hypersonic vehicle can be summarized as follows:the modeling of the basic flow is used to design the waverider along the stream direction, and the osculating theory or the geometric design method is used to design the waverider along the spanwise direction.
- hypersonic vehicle /
- waverider /
- airframe-inlet integration /
- aerodynamic design

HTML全文

图 1 乘波前体作为第一级预压缩面的前体/进气道一体化构型^[15]

Fig. 1 Waverider forebody used as the first pre-compression surface^[15]

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图 2 乘波前体作为整个预压缩面的前体/进气道一体化构型^[16-17]

Fig. 2 Waverider forebody used as the whole pre-compression surface^[16-17]

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图 3 变楔角楔导乘波前体^[20]

Fig. 3 Variable wedge angle forebody model

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图 4 二维曲面压缩基准流场结构图^[21]

Fig. 4 Basic flow field of 2D curved surface-compression flow^[21]

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图 5 二维曲面压缩乘波前体/进气道一体化设计方案三维视图^[21]

Fig. 5 2D curved surface-compression waverider forebody/inlet integration configuration^[21]

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图 6 曲面锥乘波前体波系结构^[26-27]

Fig. 6 Shock wave system of curved cone waverider forebody^[26-27]

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图 7 内锥流场结构示意图^{[29, 33]}

Fig. 7 Flow field structure of inward turning cone^{[29, 33]}

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图 8 楔-锥乘波体示意图

Fig. 8 Wedge-cone waverider

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图 9 三级压缩基准流场^[43]

Fig. 9 Schematic illustration of basic flow field of multistage compression waverider with three-stage compression ramps^[43]

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图 10 三级压缩吻切锥乘波体^[43]

Fig. 10 Geometric models of three-stage compression osculating-cone-derived waverider^[43]

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图 11 三级压缩吻切锥乘波前体/进气道一体化构型^[46]

Fig. 11 Three-stage compression osculating-cone-derived waverider forebody/inlet integration configuration^[46]

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图 12 曲面锥乘波前体/进气道一体化构型的数值模拟横截面激波形态^[17]

Fig. 12 Cross-section shock wave shapes obtained from numerical simulation for curved cone waverider/inlet integrated vehicle^[17]

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图 13 吻切内锥乘波前体/进气道一体化构型^{[29, 33]}

Fig. 13 Osculating inward turning cone waverider/inlet integrated vehicle^{[29, 33]}

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图 14 吻切平面外压缩激波流场结构示意图^[52]

Fig. 14 Rodi's basic flow field with an external compression shock wave in an osculating plane^[52]

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图 15 “双乘波”设计概念原理图^[53]

Fig. 15 Design principle of dual waverider concept^[53]

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图 16 单流道“双乘波”前体/进气道一体化构型^[53]

Fig. 16 Dual waverider forebody/inlet integrated vehicle with single flowpath^[53]

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图 17 两流道“双乘波”前体/进气道一体化构型^[54]

Fig. 17 Dual waverider forebody/inlet integrated vehicle with double flowpaths^[54]

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图 18 吻切锥乘波前体/两侧内收缩进气道一体化构型^[55]

Fig. 18 Integrated design of waverider forebody and lateral hypersonic inward turning inlets^[55]

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图 19 双乘波体旋转对拼式前体设计^[58]

Fig. 19 Design of airplane forebody by rotating and assembling two waveriders

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图 20 双乘波对拼式前体/进气道一体化构型^[58]

Fig. 20 Design example of double-flanking waverider forebody/inlet integration vehicle^[58]

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图 21 被圆锥激波包裹的锥导乘波机体/进气道一体化构型及发动机安装位置^[1]

Fig. 21 Cone-derived waverider airframe/inlet integration wrapped by conical shock wave and arrangement position of engine boxes^[1]

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图 22 楔导乘波机体/进气道一体化构型及发动机安装位置^[61]

Fig. 22 Wedge-derived waverider airframe/inlet integration and arrangement position of engine boxes^[61]

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图 23 基准流场相交式机体/进气道一体化设计^[63]

Fig. 23 Schematic representation of basic-flow-field-intersection waverider airframe/inlet integration^[63]

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图 24 “全乘波”机体/进气道一体化设计原理^[64]

Fig. 24 Schematic representation of full waverider airframe/inlet integration^[64]

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图 25 吻切锥乘波机体/两侧内收缩进气道一体化构型^[65]

Fig. 25 Osculating cone waverider airframe integrated with double inward turning inlets configuration^[65]

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