Study of aerodynamic and stealthy performance for a multifunctional morphing tail

MA Xiaoyong; SU Jichuan; ZHONG Shidong; HUANG Yong; ZHANG Yi

doi:10.7638/kqdlxxb-2018.0173

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Study of aerodynamic and stealthy performance for a multifunctional morphing tail

更新时间：2026-05-28

- Study of aerodynamic and stealthy performance for a multifunctional morphing tail
- Vol. 38, Issue 5, Pages: 896-900(2020)
- 作者机构：
  
  中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0173
  CLC： V225;O355
- Published：2020
- 稿件说明：
移动端阅览
马晓永, 苏继川, 钟世东, 黄勇, 张诣. 一种变体尾翼的气动-隐身特性研究[J]. 空气动力学学报, 2020, 38(5): 896-900.

MA Xiaoyong, SU Jichuan, ZHONG Shidong, et al. Study of aerodynamic and stealthy performance for a multifunctional morphing tail[J]. 2020, 38(5): 896-900.
马晓永, 苏继川, 钟世东, 黄勇, 张诣. 一种变体尾翼的气动-隐身特性研究[J]. 空气动力学学报, 2020, 38(5): 896-900. DOI： 10.7638/kqdlxxb-2018.0173.

MA Xiaoyong, SU Jichuan, ZHONG Shidong, et al. Study of aerodynamic and stealthy performance for a multifunctional morphing tail[J]. 2020, 38(5): 896-900. DOI： 10.7638/kqdlxxb-2018.0173.

摘要

飞翼布局具有较好的气动和隐身性能，但也存在航向稳定性缺失、航向操纵效能不足等先天缺点。针对一种小展弦比变体飞翼布局飞机，提出了多功能变体尾翼概念，可依据飞行和任务需求自适应改变飞机气动布局形式，以解决飞翼布局的横航向稳定性与控制问题，同时又兼顾全机的隐身特性。通过对多功能变体尾翼气动、隐身特性研究，以及风洞、微波暗室试验验证，表明该变体尾翼具有良好的气动-隐身综合性能。以马赫数0.9、迎角0°为例，尾翼打开45°后，偏航力矩系数对侧滑角导数值从-0.0001增大至0.0004，航向稳定性明显得到改善；马赫数0.9和2.0时，尾翼上反打开45°后，焦点分别后移1.0%和前移5.3%平均气动弦长；隐身特性方面，尾翼打开时隐身性能有所下降，尤其是对“垂直-垂直”极化影响较大，雷达散射面积峰值视角变宽，平均高出约5 dB（X~Ku频段）。对于小展弦比变体飞翼布局方案，提出的多功能变体尾翼概念较好地解决了飞翼横航向稳定性及控制问题，具有一定的应用价值。

Abstract

Flying wing has good aerodynamic and stealthy performance with defects of incompetent lateral-directional stability and control. In this paper

a multifunctional morphing tail for low-aspect-ratio flying wing configuration is presented which can automatically change aerodynamic configuration based on flight and missions condition. According to the analysis of aerodynamic and stealthy performance

the results of wind tunnel test

and compact antenna test

it is shown that the multifunctional morphing tail fins significantly improves the lateral static stability of the flying-wing. The

increased from -0.0001 to 0.0004 at

=0.9、

=0° with 45° opening tail fins. At

=0.9 and 2.0

the aerodynamic focus respectively moves backward 1.0%

and forward 5.3%

with 45° opening tail fins. The radar cross section(RCS) for scale model increases about 5dBsm(X~Ku band)

especialy for the vertical-vertical (VV) polarimetric scattering. The multifunctional morphing tail is useful for designing low-aspect-ratio flying wing configuration with lateral-directional stability and control.

关键词

Keywords

references

SUN Y J, SHEN G Z. Multidisciplinary optimization of control-aerodynamic-stealth for flying wing aircraft design[J]. Journal of Beijing University of Aeronautics and Astronautics, 2009, 35(11):1357-1360. (in Chinese)

CHEN F, ZHU Y T, LI G H, et al. An aircraft aerodynamic-stealth multi-disciplinary quick conceptual optimal design method[J]. Chinese Quarterly of Mechanics, 2010, 31(3):411-417. (in Chinese)

LIAO Y P, LIU L, LONG T. Multi-objective aerodynamic and stealthy performance optimization for Large-aspect-ratio Forward-swept wings[J]. Aeronautical Computing Technique, 2011, 41(3):5-9. (in Chinese)

LIU C Y, JIAO Y C, ZHANG P, et al. Research on RCS of a UAV formed in flying wing configuration[J]. Chinese Journal of Radio Science, 2009, 24(1):95-98. (in Chinese)

ROYSDON P F, KHALID M. Lateral-directional stability investigation of a blended-wing body[C ] //10th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference, Fort Worth, Texas. Reston, Virginia: AIAA 2010-9167. doi: 10.2514/6.2010-9167

ROYSDON P F, KHALID M. Blended-wing-body lateral-directional stability investigation using 6DOF simulation[C ] //Infotech@Aerospace 2011, St. Louis, Missouri, Reston, Virigina: AIAA 20 11-1563. doi: 10.2514/6.2011-1563

TAN L L, WANG Z P, LIU J. Analyzing lateral and directional static derivatives of flying wing based on conceptual design[J]. Flight Dynamics, 2009, 27(2):16-19. (in Chinese)

LI L, WANG L X. Lateral-directional flying quality characteristics of high aspect-ratio combat flying wings[J]. Journal of Beijing University of Aeronautics and Astronautics, 2009, 35(6):661-664, 713. (in Chinese)

LI L, MA C, WANG L X. Stability features of low aspect-ratio flying wings[J]. Acta Aeronautica et Astronautica Sinica, 2007, 28(6):1312-1317. (in Chinese)

MA S H, WU C F, CHEN H M. Study on stability and manoeuvrability of flying wing aircraft[J]. Flight Dynamics, 2006, 24(3):17-21. (in Chinese)

STENFELT G, RINGERTZ U. Lateral stability and control of a tailless aircraft configuration[J]. Journal of Aircraft, 2009, 46(6):2161-2164. doi:10.2514/1.41092

STENFELT G, RINGERTZ U. Yaw control of a tailless aircraft configuration[J]. Journal of Aircraft, 2010, 47(5):1807-1811. doi:10.2514/1.C031017

ZHANG B Q, MA Y, CHU H B, et al. Investigation on combined control surfaces for the yaw control of low aspect ratio flying wing configuration[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(11):2435-2442. (in Chinese)

BOWLUS J, MULTHOPP D, BANDA S, et al. Challenges and opportunities in tailless aircraft stability and control[C ] //Proc of the Guidance, Navigation, and Control Conference, NewOrleans, LA. Reston, Virginia: AIAA 1997-3830. doi: 10.2514/6.1997-3830

SHAN J X, HUANG Y, SU J C, et al. Effect of the novel embedded control surfaces on direction control characteristic of low-aspect-ratio flying-wing configuration[J]. Acta Aerodynamica Sinica, 2015, 33(3):296-301. (in Chinese)

KOWAL H J. Advances in thrust vectoring and the application of flow-control technology[J]. Canadian Aeronautics and Space Journal, 2002, 48(2):145-151. doi:10.5589/q02-020

MU H R, YANG Q Z, DENG X J, et al. Research on dual throat fluidic thrust vectoring nozzle and flying wing layout UAV[J]. Aeronautical Computing Technique, 2014, 44(1):90-93. (in Chinese)

SU J C, HUANG Y, LI Y H, et al. Support interference of low-aspect-ratio flying-wing from subsonic to supersonic speed[J]. Acta Aerodynamica Sinica, 2015, 33(3):289-295. (in Chinese)

SU J C, HUANG Y, ZHONG S D, et al. Research on flow characteristics of low-aspect-ratio flying-wing at transonic speed[J]. Acta Aerodynamica Sinica, 2015, 33(3):307-312, 318. (in Chinese)

LI Y H, HUANG Y, WANG Y Q, et al. Wing-body thickness effects on aerodynamic and vortex flow characteristics of common low-aspect-raio flying-wing configuration at transonic flow[J]. Acta Aerodynamica Sinica, 2015, 33(3):302-306. (in Chinese)

ZHONG S D, LI W, MA X Y, et al. Jet influence of low-aspect-raio flying-wing configuration[C]//17th Computational fluid dynamic conference, Hangzhou, 2017: 440-444. CARS-2017-03-335.(in Chinese)

MA X Y, LIU H L, ZHONG S D, et al. Study of wind tunnel test method with tail support for flat-body aircraft[C]//The Chinese congress of theoretical and applied mechanics (CCTAM 2017), Beijing, 2017: CCTAM2017-A31-MS065-1865, 1437-1441. (in Chinese)

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Parametric construction of blade leading and trailing edges with arbitrary central angles using NURBS curves

Influence of windbreak distance on the aerodynamic performance of high-speed trains by large eddy simulation

Research progress on Reynolds number effects in the design of large aircraft

Flow characteristic analysis and optimization design of a bionic dragonfly vertical takeoff and landing nozzle

Influence of the number of blades on aerodynamic and noise characteristics of counter-rotating propeller

Related Author

CHEN Jianjun

XIA Yifan

XU Jingchao

NI Haonan

YANG Yonggang

LI Rui

JIA Yongxing

ZHAO Gaopeng

Related Institution

School of Aeronautics and Astronautics, Zhejiang University, Hangzhou

School of Mechanical and Electrical Engineering, Lanzhou Jiaotong University, Lanzhou

National Key Laboratory of Aircraft Configuration Design, Xi'an

School of Aeronautics, Northwestern Polytechnical University, Xi'an

The First Aircraft Institute, Aviation Industry Corporation of China, Ltd., Xi'an

AI问答

⁰