飞翼布局组合舵面航向控制特性综合研究

doi:10.7527/S1000-6893.2019.23422

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

飞翼布局组合舵面航向控制特性综合研究

周铸, 余永刚, 刘刚, 陈作斌, 何开锋

中国空气动力研究与发展中心, 绵阳 621000

收稿日期:2019-09-02 修回日期:2019-09-21 出版日期:2020-06-15 发布日期:2019-10-24
通讯作者: 余永刚 E-mail:lenkoo@tom.com

Comprehensive study on yaw control characteristic of combined control surfaces of flying wing configuration

ZHOU Zhu, YU Yonggang, LIU Gang, CHEN Zuobin, HE Kaifeng

China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2019-09-02 Revised:2019-09-21 Online:2020-06-15 Published:2019-10-24

摘要/Abstract

摘要： 寻求高效实用的航向控制措施一直是飞翼布局飞行器设计的难点。提出了一种由外翼上翼面嵌入式阻力舵和其相对应的后缘副翼组成的组合舵航向控制措施，通过CFD方法、风洞试验和模型飞行试验3种研究手段，综合研究了单独部件和组合舵在低速、亚声速时的航向控制特性。结果表明：单独阻力舵的航向控制能力比较强，但与纵横向力矩耦合严重，需与其他舵组合使用；单独副翼的航向控制能力很弱，且与纵横向力矩耦合非常严重，建议不单独作为航向控制措施使用；组合舵的航向控制能力强，选取阻力舵与副翼的舵偏角角度差在0°~5°范围的组合舵方案，可以大幅度削弱与纵横向的力矩耦合程度，实现操纵舵面解耦设计；无论单独部件，还是组合舵，舵偏角为0°~6°范围的力矩变化规律较差，建议通过预置舵偏角等方式避开此角度区域。

关键词: 飞翼, 嵌入式阻力舵, 副翼, 航向控制, 亚声速, CFD方法, 风洞试验, 模型飞行试验

Abstract: Searching for effective and practical yaw control measures has always been a difficult point in the design of flying-wing aircraft. This paper presents a yaw control method of combined rudder consisting of a spoiler drag rudder on the upper surface of the outer wing and its corresponding trailing aileron. The yaw control characteristics of single component and combined rudder at low and subsonic speeds are studied comprehensively by three means of CFD, wind tunnel test, and model flight test. Research results show that the yaw control ability of the single drag rudder is relatively strong, but its coupling with the longitudinal and lateral moments is severe, and needs to be combined with other rudders. It is suggested that the aileron should not be used alone as a yaw control measure because of its weak yaw control capability and serious coupling with longitudinal and lateral moments. The combined rudder has strong yaw control ability. Selecting the scheme of combined rudder with the difference of rudder deviation between drag rudder and aileron in the range of 0°-5° can greatly reduce the coupling degree of longitudinal and lateral moments and realize the decoupling design of control rudder. Whether single component or combined rudder, the moment regularity of the rudder deviation angle in the range of 0°-6° is poor, and it is suggested to avoid this angle area by presetting the rudder deviation angle.

Key words: flying wing, spoiler drag rudder, aileron, yaw control, subsonic velocity, CFD method, wind tunnel test, model flight test

中图分类号:

V211

周铸, 余永刚, 刘刚, 陈作斌, 何开锋. 飞翼布局组合舵面航向控制特性综合研究[J]. 航空学报, 2020, 41(6): 523422-523422.

ZHOU Zhu, YU Yonggang, LIU Gang, CHEN Zuobin, HE Kaifeng. Comprehensive study on yaw control characteristic of combined control surfaces of flying wing configuration[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(6): 523422-523422.

参考文献 25

[1]	余永刚, 黄勇, 周铸, 等.飞翼布局气动外形设计[J].空气动力学学报, 2017, 35(6):832-836,878. YU Y G, HUANG Y, ZHOU Z, et al. Aerodynamic design of a flying-wing aircraft[J]. Acta Aerodynamica Sinica, 2017, 35(6):832-836, 878(in Chinese).
[2]	BOWLUS J A, MULTHOPP D. Challenges and opportunities in tailless aircraft stability and control:AIAA-1997-3830[R]. Reston:AIAA, 1997.
[3]	DORSETT K M, MEIL D R. Innovative control effectors (ICE):WL-TR-96-3043[R]. 1996.
[4]	GILLARD W J. Innovative control effectors (configuration 101) dynamic wind tunnel test report rotary balance and force oscillation tests:AFRL-VA-WP-TP-1998-3043[R]. 1998.
[5]	STENFELT G, RINGELTZ U. Lateral stability and control of a tailless aircraft configuration[J]. Journal of Aircraft, 2009, 46(6):2161-2163.
[6]	NANGIA R K, BOELENS O J, TORMALM M. A tale of two UCAV wing designs:AIAA-2010-4397[R]. Reston:AIAA, 2010.
[7]	WOLF R, KRUGER, HOFFMANN D. Design considerations for a UCAV wing for subsonic and transonic aeroelastic and flight mechanic wind tunnel tests:ADA-478721[R].2007.
[8]	ZHANG F, KHALID M, BALL N. A CFD based study of UCAV 1303 model:AIAA-2005-4615[R]. Reston:AIAA, 2005.
[9]	CHOI S M, NGUYEN N V, et al. Multidisciplinary unmanned combat air vehicle system design using multi-fidelity analysis:AIAA-2010-0482[R]. Reston:AIAA, 2010.
[10]	刘刚, 邱玉鑫, 陈洪, 等. 无尾飞机布局方向制特性研究[J]. 流体力学实验与测量, 2003, 17(4):1-9. LIU G, QIU Y X, CHEN H, et al. Investigation of the direction control for the tailless aircraft configuration[J]. Experiments and Measurements in Fluid Mechanics, 2003, 17(4):1-9(in Chinese).
[11]	柴雪, 王钢林, 武哲. 大后掠飞翼布局无人机操纵面特性及控制研究[J]. 飞行力学, 2009,27(6):26-29. CHAI X, WANG G L, WU Z. Study on the control surface characteristics and flight control of the high sweepback flying wing UAV[J]. Flight Dynamics, 2009, 27(6):26-29(in Chinese).
[12]	李中剑, 马东立. 飞翼布局阻力类偏航操纵装置操纵特性分析[J]. 北京航空航天大学学报, 2014, 40(5):695-700. LI Z J, MA D L. Control characteristics analysis of drag yawing control devices of flying wing configuration[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(5):695-700(in Chinese).
[13]	马超, 李林, 王立新. 大展弦比飞翼布局飞机新型操纵面设计[J]. 北京航空航天大学学报, 2007, 33(1):149-152. MA C, LI L, WANG L X. Design of innovative control surfaces of flying wing aircrafts with large ratio aspect[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(1):149-152(in Chinese).
[14]	张子军, 黎军, 李天, 等. 开裂式方向舵对某无尾飞翼布局飞机气动特性影响的实验研究[J]. 实验流体力学, 2010, 24(3):63-66. ZHANG Z J, LI J, LI T, et al. Experimental investigation of split-rudder deflection on aerodynamic performance of tailless flying wing aircraft[J]. Journal of Experiments in Fluid Mechanics, 2010, 24(3):63-66(in Chinese).
[15]	屈晓波, 章卫国, 史静平, 等. 一种低速情况下无尾飞翼飞机航向控制方法[J]. 西北工业大学学报, 2015, 33(1):70-75. QU X B, ZHANG W G, SHI J P, et al. A yaw control method for tailless flying wing aircraft under low speed condition[J]. Journal of Northwestern Polytechnical University, 2015, 33(1):70-75(in Chinese).
[16]	王旭, 于冲, 苏新兵, 等. 开裂式方向舵在变前掠翼布局中的操纵性能研究[J]. 航空学报, 2013, 34(4):741-749. WANG X, YU C, SU X B, et al. Study of control characteristics for split rudder in variable forward swept wing configuration[J]. Acta Aeronautics et Astronautics Sinica, 2013, 34(4):741-749(in Chinese).
[17]	赵霞, 秦燕华. 一种飞翼布局横航向特性的控制研究[J]. 空气动力学学报, 2008, 26(2):234-238. ZHAO X, QIN Y H. An investigation on controlling lateral characteristics for a flying wing configuration[J]. Acta Aerodynamica Sinica, 2008, 26(2):234-238(in Chinese).
[18]	左林玄, 王晋军. 全动翼尖对无尾飞翼布局飞机气动特性影响的实验研究[J]. 空气动力学学报, 2010, 28(2):132-137. ZUO L X, WANG J J. Experimental study of the effect of AMT on aerodynamic performance of tailless flying wing aircraft[J]. Acta Aerodynamica Sinica, 2010, 28(2):132-137(in Chinese).
[19]	谢树联, 郑君若禹, 李军. 可弯折翼尖在飞翼布局中操纵性能研究[J]. 民机飞机设计与研究, 2018(1):24-33. XIE S L, ZHENG J R Y, LI J. Research on the control characteristics of the bendable wing tip in flying-wing aircraft[J]. Civil Aircraft Design & Research, 2018(1):24-33(in Chinese).
[20]	单继祥, 黄勇, 苏继川, 等. 小展弦比飞翼布局新型嵌入面航向控制特性研究[J]. 空气动力学学报, 2015, 33(3):296-301. SHAN J X, HUANG Y, SU J C, et al. Effect of the novel embedded control surfaces on direction control characteristic of low-aspect flying-wing configuration[J]. Acta Aerodynamica Sinica, 2015, 33(3):296-301(in Chinese).
[21]	李路路, 张彬乾, 李沛峰, 等. 大型客机无尾布局航向组合舵面控制技术研究[J]. 飞行力学, 2013, 31(5):450-454. LI L L, ZHANG B Q, LI P F, et al. Research on control technology of combined control surface for large tailless civil aircraft[J]. Flight Dynamics, 2013, 31(5):450-454(in Chinese).
[22]	张彬乾, 马怡, 褚胡冰, 等. 小展弦比飞翼布局航向控制的组合舵面研究[J]. 航空学报, 2013, 34(11):2435-2442. ZHANG B Q, MA Y, CHU H B, et al. Investigation on combined control surface for the yaw control of low aspect ratio flying wing configuration[J]. Acta Aeronautics et Astronautics Sinica, 2013, 34(11):2435-2442(in Chinese).
[23]	邓建, 陈斌. 线性引射阻力方向舵研究[J]. 航空科学技术, 2013, 25(1):33-36. DENG J, CHEN B. Research of linear ejector drag rudder[J]. Aeronautical Science & Technology, 2013, 25(1):33-36(in Chinese).
[24]	牟斌. 流动控制数值模拟研究[D]. 绵阳:中国空气动力研究与发展中心, 2006. MOU B. Research on numerical simulation technology of flow control[D]. Mianyang:China Aerodynamics Research and Development Center, 2006(in Chinese).
[25]	何开锋, 毛仲君, 汪清, 等. 缩比模型演示验证飞行试验及关键技术[J]. 空气动力学学报, 2017, 35(5):671-679. HE K F, MAO Z J, WANG Q, et al. Demonstration and validation flight test of scaled aircraft model and its key technologies[J]. Acta Aerodynamica Sinica, 2017, 35(5):671-679(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

飞翼布局组合舵面航向控制特性综合研究

Comprehensive study on yaw control characteristic of combined control surfaces of flying wing configuration

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献 25

相关文章 15

编辑推荐

Metrics

本文评价

[1]	徐善劼, 吕宏强, 刘中臣, 冷岩, 刘学军. 基于概率模型的声爆试验数据分析[J]. 航空学报, 2023, 44(2): 626269-626269.
[2]	刘中臣, 钱战森, 李雪飞, 冷岩, 郭大鹏. 发动机喷管羽流对近场声爆特性影响的风洞试验技术[J]. 航空学报, 2023, 44(2): 626952-626952.
[3]	束珺, 徐东光, 韩志熔, 李斯, 黄雄. 结冰风洞过冷大水滴试验中混合翼设计[J]. 航空学报, 2023, 44(1): 627182-627182.
[4]	罗凯, 王永海, 汪球, 栗继伟, 李峥, 聂春生, 李铮. 高焓风洞中等离子体激励流动控制试验[J]. 航空学报, 2022, 43(S2): 89-96.
[5]	杜海, 杨乐杰, 李铮, 徐悦, 孙京阳, 王宇航. 多级环量控制技术增升机理及能效分析[J]. 航空学报, 2022, 43(S2): 54-66.
[6]	刘传振, 孟旭飞, 刘荣健, 白鹏. 双后掠乘波体高超声速试验与数值分析[J]. 航空学报, 2022, 43(9): 126015-126015.
[7]	陈浩, 华如豪, 袁先旭, 唐志共, 毕林. 基于自适应笛卡尔网格的飞翼布局流动模拟[J]. 航空学报, 2022, 43(8): 125674-125674.
[8]	刘俊, 罗新福, 王显圣. 前缘形状对空腔模型气动特性影响试验[J]. 航空学报, 2022, 43(7): 125235-125235.
[9]	陈宪, 陈诚, 黄江涛, 陈其盛, 余龙舟, 钟世东. 腹部襟翼对飞翼布局飞行器起降气动特性的影响[J]. 航空学报, 2022, 43(3): 125028-125028.
[10]	张桢锴, 贾思嘉, 宋晨, 杨超. 柔性变弯度后缘机翼的风洞试验模型优化设计[J]. 航空学报, 2022, 43(3): 226071-226071.
[11]	侯英昱, 李齐, 季辰, 刘子强. 超声速低频大抖振气动弹性载荷试验[J]. 航空学报, 2022, 43(3): 626454-626454.
[12]	曾开春, 寇西平, 杨兴华, 余立, 查俊. 跨声速风洞试验模型主动减振结构优化设计[J]. 航空学报, 2022, 43(2): 224944-224944.
[13]	衣秉立, 刘博宇, 王争取, 张铁军, 鲁丹, 赵彦. 1.2 m高速风洞双天平支撑试验技术[J]. 航空学报, 2022, 43(11): 526794-526794.
[14]	王浩, 钟敏, 华俊, 钟海, 杨体浩, 王猛, 雷国东. 自然层流飞行测试翼套的仿真和试验[J]. 航空学报, 2022, 43(11): 526785-526785.
[15]	陈艺夫, 王一雯, 邓一菊, 王波, 白俊强, 卢磊. 自然层流机翼的翼套试验及数值方法[J]. 航空学报, 2022, 43(11): 526793-526793.