面对称无尾高超声速飞行器三通道耦合失稳判据

吕达; 张维桐; 张鲁民; 赵俊波; 张石玉; 苏浩秦

doi:10.7638/kqdlxxb-2022.0104

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面对称无尾高超声速飞行器三通道耦合失稳判据

研究论文 | 更新时间：2026-05-28

- 面对称无尾高超声速飞行器三通道耦合失稳判据
- Three-channel coupled instability criteria for symmetrical tailless hypersonic vehicles
- 空气动力学学报 2023年41卷第7期页码：74-83
- 作者机构：
  
  1. 中国航天空气动力技术研究院,北京,100074
  2. 北京航空航天大学宇航学院,北京,100191
  3. 国家计算流体力学实验室,北京,100191
- 作者简介：
  
  吕达*（1994-），男，山东人，博士生，工程师，研究方向：高超声速飞行器控制技术. E-mail：2442070076@qq.com
- 基金信息：
  
  国家重点基础研究发展计划（613272）
- DOI：10.7638/kqdlxxb-2022.0104
  中图分类号： V412
- 纸质出版：2023
- 稿件说明：
移动端阅览
吕达, 张维桐, 张鲁民, 等. 面对称无尾高超声速飞行器三通道耦合失稳判据[J]. 空气动力学学报, 2023, 41(7): 74−83.

LYU Da, ZHANG Weitong, ZHANG Lumin, et al. Three-channel coupled instability criteria for symmetrical tailless hypersonic vehicles[J]. 2023, 41(7): 74-83.
吕达, 张维桐, 张鲁民, 等. 面对称无尾高超声速飞行器三通道耦合失稳判据[J]. 空气动力学学报, 2023, 41(7): 74−83. DOI： 10.7638/kqdlxxb-2022.0104

LYU Da, ZHANG Weitong, ZHANG Lumin, et al. Three-channel coupled instability criteria for symmetrical tailless hypersonic vehicles[J]. 2023, 41(7): 74-83. DOI： 10.7638/kqdlxxb-2022.0104.

摘要

针对新一代面对称高超声速飞行器通常采用的无尾布局、小控制面设计而导致的飞行器稳定性大幅降低以及通道间控制耦合严重的问题，基于飞行器的六自由度动力学方程，利用线化小扰动理论，通过推导引入了飞行器三通道开环和闭环的气动稳定性耦合判据，其判据中包括了传统的气动静导数和动导数，组成了新的三通道耦合稳定性判据体系。相比现有判据，本研究新引入了俯仰和滚转通道静稳定性耦合判据，以及三通道的动稳定性耦合判据，并用数值仿真验证了本文引入的判据在判断无尾布局高超声速飞行器稳定特性中的有效性，为该类飞行器提供了快速有效的稳定性分析工具。

Abstract

Modern plane-symmetric hypersonic vehicles (HSV) typically feature a tailless configuration and small control surfaces

significantly reducing the vehicle’s stability and complicating the vehicle’s lateral and longitudinal control. This paper uses the linear small disturbance theory to develop three-channel open-loop and closed-loop coupled instability criteria for HSV. The criteria include the classical aerodynamic static and dynamic derivatives

forming a new group of three-channel coupled instability criteria. Compared with the existing criteria

this research introduces the static stability coupled criteria and the three-channel dynamic stability coupled criteria in the pitch and roll channels. The critical values of the lateral and longitudinal criteria are no longer zero as the classical criteria by considering dynamic derivative in the pitch channel. Moreover

the effectiveness of the three-channel coupled instability criteria is verified by numerical simulations. The new criteria improves the discrimination method for determining the static and dynamic stabilities and provides a fast and effective tool for stability analysis of this type of vehicle.

关键词

Keywords

references

WALKER S, SHERK J, SHELL D, et al. The DARPA/AF falcon program: the hypersonic technology vehicle #2 (HTV-2) flight demonstration phase[C]// 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Dayton, Ohio. Reston, Virginia: AIAA, 2008: 2539. doi: 10.2514/6.2008-2539

HANK J, MURPHY J, MUTZMAN R. The X-51A scramjet engine flight demonstration program[C]// 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Dayton, Ohio. Reston, Virginia: AIAA, 2008: 2540. doi: 10.2514/6.2008-2540

NORRIS G. X-51A waverider achieves hypersonic goal on final flight[J]. Aviation Week, 2013, 2.

GRANTZ A. X-37B orbital test vehicle and derivatives[C]// AIAA SPACE 2011 Conference Exposition, Long Beach, California. Reston, Virginia: AIAA, 2011: 7315. doi: 10.2514/6.2011-7315

ZHU L G, ZHAO J B, YE Y D. Coupling departure analysis and applications of high speed aircrafts[M]. Beijing: National Defense Industry Press, 2015. (in Chinese)

ZHANG J, LI H G, ZHENG H T, et al. Review on out of control inducement and criteria of operation and stability of high speed vehicle[J]. Physics of Gases, 2021, 6(6): 1-12. (in Chinese)

PARK J, CHOI J Y, JO Y, et al. Stability and control of tailless aircraft using variable-fidelity aerodynamic analysis[J]. Journal of Aircraft, 2017, 54(6): 2148-2164. DOI:10.2514/1.c034052

FU J C, HUANG J, SONG L, et al. Experimental study of aircraft achieving Dutch roll mode stability without weathercock stability[J]. International Journal of Aerospace Engineering, 2020, 2020: 8971275. DOI:10.1155/2020/8971275

FU J Q, SHI Z W, GONG Z, et al. Virtual flight test techniques to predict a blended-wing-body aircraft in-flight departure characteristics[J]. Chinese Journal of Aeronautics, 2022, 35(1): 215-225. DOI:10.1016/j.cja.2021.01.006

FU J Q, SHI Z W, CHEN J, et al. Departure characteristics of blended-wing-body aircraft[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(6): 32-37. (in Chinese)

SHEN L, HUANG D, WU G X. An investigation of lateral-directional departure behavior based on yawing–rolling coupled wind tunnel tests[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2018, 232(16): 2989-3000. DOI:10.1177/0954410017723361

SHEN L, DA HUANG, WU G X. Effects of yaw-roll coupling ratio on the lateral-directional departure prediction and restraint[J]. Chinese Journal of Aeronautics, 2019, 32(10): 2239-2253. DOI:10.1016/j.cja.2019.04.007

CHEN G, TANG Z G, WANG W Z, et al. Application of Weissman criterion in the design of lift reentry vehicle[J]. Flight Dynamics, 2019, 37(3): 68-73. (in Chinese)

CAI S. Aerodynamic shape optimization and lateral-directional stability analysis for vertical-tailless aircraft[D]. Hangzhou: Zhejiang University, 2018. (in Chinese)

ZHANG S Y, ZHAO J B, ZHANG Q Q, et al. Weissman chart analysis of tailless lifting body by flight dynamics simulation[J]. Physics of Gases, 2021, 6(6): 13-19. (in Chinese)

ZHANG Q Q, ZHANG S Y, ZHAO J B, et al. Lateral-direction stability analysis on aerodynamic shape parameters for a lifting-body configuration[J]. Physics of Gases, 2021, 6(6): 20-28. (in Chinese)

WANG Y, MIN C W, WANG Y D, et al. Study on Lateral-Directional Control Strategy for the polarity change of LCDP in flight[C]// 21st AIAA International Space Planes and Hypersonics Technologies Conference, Xiamen, China. Reston, Virginia: AIAA, 2017: 2319. doi: 10.2514/6.2017-2319

LIU X M, WANG Y, MIN C W, et al. Lateral-directional stability analysis and control for the symmetry plane Aircrafts[C]// IECON 2016 - 42nd Annual Conference of the IEEE Industrial Electronics Society, Florence. IEEE, : 5437-5442. doi: 10.1109/IECON.2016.7793023

CHAI X, WANG G L, WU Z. Flight control system design for the flying-wing aircraft by using intelligent optimal seeking method[C]// 2010 2nd International Asia Conference on Informatics in Control, Automation and Robotics (CAR 2010), Wuhan, China. IEEE, : 429-432. doi: 10.1109/CAR.2010.5456588

SHOU Y X, XU B, GUO Y Y, et al. Coordinated adaptive control of hypersonic reentry vehicle considering channel coupling[J]. Mathematical Methods in the Applied Sciences, 2022. DOI:10.1002/mma.8071

SHEARWOOD T R, NABAWY M R, CROWTHER W, et al. A control allocation method to reduce roll-yaw coupling on tailless aircraft[C]// AIAA Scitech 2021 Forum, VIRTUAL EVENT. Reston, Virginia: AIAA, 2021: 1826. doi: 10.2514/6.2021-1826

WANG Y, MIN C W, LIU X M, et al. Study on lateral-directional stable design of HTV-2 like vehicle[J]. Journal of Astronautics, 2017, 38(6): 583-589. (in Chinese)

DING J Y, ZHENG H T, SHAO G, et al. Lateral-directional modal control effectiveness for symmetrical aircraft with strong-coupling dynamics[J]. Physics of Gases, 2021, 6(6): 29-36. (in Chinese)

方振平, 陈万春, 张曙光. 航空飞行器飞行动力学[M]. 北京: 北京航空航天大学出版社, 2005.

Qing G. Study on lateral-directional stability of hypersonic lifting-configuration[D]. Beijing: China Academy of Aerospace Aerodynamics, 2013. (in Chinese)

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