EI、Scopus 收录
中文核心期刊
Quick Search Issue Search Advanced Search
Volume 54 Issue 5
Apr.  2022
Turn off MathJax
Article Contents
Abstract
References
Related Articles
Zhao Zhijie, Luo Zhenbing, Liu Jiefu, Deng Xiong, Peng Wenqiang, Li Shiqing. Flight test of aircraft three-axis attitude control without rudders based on distributed dual synthetic jets. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(5): 1220-1228. DOI: 10.6052/0459-1879-21-586
Citation: Zhao Zhijie, Luo Zhenbing, Liu Jiefu, Deng Xiong, Peng Wenqiang, Li Shiqing. Flight test of aircraft three-axis attitude control without rudders based on distributed dual synthetic jets. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(5): 1220-1228. DOI: 10.6052/0459-1879-21-586
shu

FLIGHT TEST OF AIRCRAFT THREE-AXIS ATTITUDE CONTROL WITHOUT RUDDERS BASED ON DISTRIBUTED DUAL SYNTHETIC JETS

  • College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China

  • Received Date: November 09, 2021
  • Accepted Date: March 06, 2022
  • Available Online: March 07, 2022
    Graphical Abstract
    • Abstract
  • The autonomous and controllable dual synthetic jet actuators were integrated into an aircraft with a conventional layout and then, the three-axis flight tests without rudders were carried out to verify the ability of distributed three-axis dual synthetic jet actuators to control the attitudes of the aircraft during the cruising. First of all, the dual synthetic jet actuators were improved, and the distributed three-axis attitude control dual synthetic jet actuators were created. Moreover, roll circulation control actuators were installed on the trailing edge of both-side wings close to the wingtips, where their jet outlets were close to the pressure surface. Yaw reverse dual synthetic jet actuators, evenly arranged on the upper and lower surfaces along the span direction, were respectively installed at the 20% chord of the wing close to the wingtips on both sides. Pitch circulation control actuators, whose outlets were also close to the pressure surface, were installed on the trailing edge of the in-house flat tail under the V tail. Then, for an aircraft with a cruising speed of 30 m/s, the three-axis attitude control flight tests without rudders have been carried out during the cruising. Relevant flight attitude information shows that distributed dual synthetic jets could realize the three-axis attitude control of the aircraft without rudders during the cruising. What’s more, the coupling has been shown between the lateral and heading control. The two-way roll control of the aircraft could be realized by the roll circulation control actuators, and the maximum roll angular velocity that can be generated is 16.87°/s. In addition, yaw reverse dual synthetic jet actuators could achieve the two-way yaw control, and the maximum yaw angular velocity that can be generated is 9.09°/s. Pitch circulation control actuators could realize the longitudinal control of the aircraft, and the maximum pitch angular velocity that can be generated is 7.68°/s.
    • FullText(HTML)
    • References (31)
  • [1]
    Zhao ZJ, Luo ZB, Xu B, et al. Novel lift enhancement method based on zero-mass-flux jets and its adaptive controlling laws design. Acta Mechanica Sinica, 2021, in press
    [2]
    王磊, 杜海, 李秋实等. 环量控制机翼增升及滚转控制特性研究. 空气动力学学报, 2021, 39(1): 43-51 (Wang Lei, Du Hai, Li Qiushi, et al. Research on the lift-enhancement and roll control characteristics of a circulation control wing. Acta Aerodynamica Sinica, 2021, 39(1): 43-51 (in Chinese)
    [3]
    Friedman C, Arieli R, Levy Y. Lift build-up on circulation control airfoils. Journal of Aircraft, 2016, 53(1): 231-242 doi: 10.2514/1.C033304
    [4]
    Xu HY, Qiao CL, Yang HQ, et al. Active circulation control on the blunt trailing edge wind turbine airfoil. AIAA Journal, 2018, 56(2): 554-570 doi: 10.2514/1.J056223
    [5]
    Warsop C, Crowther WJ. Fluidic flow control effectors for flight control. AIAA Journal, 2018, 56(10): 3808-3824 doi: 10.2514/1.J056787
    [6]
    Hoholis G, Steijl R, Badcock K. Circulation control as a roll effector for unmanned combat aerial vehicles. Journal of Aircraft, 2016, 53(6): 1875-1889 doi: 10.2514/1.C033642
    [7]
    曹永飞, 顾蕴松, 韩杰星. 流体推力矢量技术验证机研制及飞行试验研究. 空气动力学学报, 2019, 37(4): 593-599 (Cao Yongfei, Gu Yunsong, Han Jiexing. Development and flight testing of a fluidic thrust vectoring demonstrator. Acta Aerodynamica Sinica, 2019, 37(4): 593-599 (in Chinese) doi: 10.7638/kqdlxxb-2017.0202
    [8]
    Lee Y, Song M, Park S. Application of backstep Coanda flap for supersonic coflowing fluidic thrust-vector control. AIAA Journal, 2014, 52(10): 2355-2359 doi: 10.2514/1.J052971
    [9]
    Kowal HJ. Advances in thrust vectoring and the application of flow-control technology. Canadian Aeronautics & Space Journal, 2002, 48(2): 145-151
    [10]
    林泳辰, 徐惊雷, 韩杰星等. 气动推力矢量无舵面飞翼的飞行实验. 航空动力学报, 2019, 34(3): 701-707 (Lin Yongchen, Xu Jinglei, Han Jiexing et al. Flight test of a fluidic thrust vectoring flying wing without rudder. Journal of Aerospace Power, 2019, 34(3): 701-707 (in Chinese)
    [11]
    Kim D, Kara K, Morris PJ. Flow-separation control using sweeping jet actuator. AIAA Journal, 2018, 56(11): 4604-4613 doi: 10.2514/1.J056715
    [12]
    Gildersleeve S, Amitay M. Control of flow separation over a flapped airfoil using low-aspect-ratio circular pins. AIAA Journal, 2019, 57(2): 628-640 doi: 10.2514/1.J056883
    [13]
    Desalvo ME, Glezer A. Aerodynamic performance modification at low angles of attack by trailing edge vortices. AIAA Paper, 2004-2118, 2004
    [14]
    Amitay M, Glezer A. Role of actuation frequency in controlled flow reattachment over a stalled airfoil. AIAA Journal, 2002, 40(2): 209-216 doi: 10.2514/2.1662
    [15]
    许晓平, 周洲. 飞翼布局无人机流动分离控制及机理分析. 力学学报, 2014, 46(4): 497-504 (Xu Xiaoping, Zhou Zhou. Active separation control for the flying-wing UAV using synthetic jet. Chinese Journal of Theoretical and Applied Mechanics, 2014, 46(4): 497-504 (in Chinese) doi: 10.6052/0459-1879-13-344
    [16]
    Fielding JP, Lawson CP, Rui MP, et al. Design, build and flight of the Demon demonstrator UAV. AIAA Paper, 2011-6963, 2011
    [17]
    Warsop C, Crowther WJ, Shearwood T. NATO AVT-239: Flight demonstration of fluidic flight controls on the MAGMA subscale demonstrator aircraft. AIAA Paper, 2019-0282, 2019
    [18]
    Chen K, Shi ZW, Zhu JC, et al. Roll aerodynamic characteristic study of an unmanned aerial vehicle based on circulation control technology. Part G: Journal of Aerospace Engineering, 2019, 233(3): 871-882
    [19]
    Shi ZW, Zhu JC, Dai XX, et al. Aerodynamic characteristics and flight testing of a UAV without control surfaces based on circulation control. Journal of Aerospace Engineering, 2019, 32(1): 04018134 doi: 10.1061/(ASCE)AS.1943-5525.0000947
    [20]
    孙全兵, 史志伟, 耿玺等. 基于主动流动控制技术的无舵面飞翼布局飞行器姿态控制研究. 航空学报, 2021, 41(2): 190-199 (Sun Quanbing, Shi Zhiwei, Geng Xi, et al. Attitude control study of a flying wing aircraft without control surfaces based on active flow control. Acta Aeronautica et Astronautica Sinica, 2021, 41(2): 190-199 (in Chinese)
    [21]
    Smith BL, Glezer A. The formation and evolution of synthetic jets. Physics of Fluids, 1998, 10(9): 2281-2297 doi: 10.1063/1.869828
    [22]
    Glezer A, Amitay M. Synthetic jets. Annual Review of Fluid Mechanics, 2002, 34: 503-529 doi: 10.1146/annurev.fluid.34.090501.094913
    [23]
    Amitay M, Cannelle F. Evolution of finite span synthetic jets. Physics of Fluids, 2006, 18(5): 54101 doi: 10.1063/1.2196093
    [24]
    Amitay M, Washburn AE, Anders SG, et al. Active flow control on the stingray uninhabited air vehicle: Transient behavior. AIAA Journal, 2004, 42(11): 2205-2215 doi: 10.2514/1.5697
    [25]
    Xu XP, Zhou Z. Study on longitudinal stability improvement of flying wing aircraft based on synthetic jet flow control. Aerospace Science and Technology, 2015, 46: 287-298 doi: 10.1016/j.ast.2015.07.022
    [26]
    Luo ZB, Xia ZX, Liu B. New generation of synthetic jet actuators. AIAA Journal, 2006, 44(10): 2418-2420 doi: 10.2514/1.20747
    [27]
    Luo ZB, Zhao ZJ, Liu JF, et al. Novel Roll effector based on zero-mass-flux dual synthetic jets and its flight test. Chinese Journal of Aeronautics, 2021, in press
    [28]
    罗振兵, 赵志杰, 彭文强等. 一种双压电振子驱动的矢量射流装置. 发明专利, 专利申请号: 202110457017. X
    [29]
    Kim W, Kim C, Jung JK. Separation control characteristics of synthetic jets depending on exit con-figuration. AIAA Journal, 2012, 50(3): 559-570 doi: 10.2514/1.J051223
    [30]
    赵志杰, 罗振兵, 刘杰夫等. 合成双射流逆向吹吸控制对翼型流动特性影响. 空气动力学学报, 2021, 39(6): 165-174 (Zhao Zhijie, Luo Zhenbing, Liu Jiefu, et al. Effect of reverse blowing and suction control by dual synthetic jets on airfoil flow characteristics. Acta Aerodynamica Sinica, 2021, 39(6): 165-174 (in Chinese) doi: 10.7638/kqdlxxb-2021.0213
    [31]
    Li SQ, Luo ZB, Deng X, et al. Lift enhancement based on virtual aerodynamic shape using a dual synthetic jet actuator. Chinese Journal of Aeronautics, 2021, in press
    • Related Articles

  • Related Articles

    [1]Wang Rong, Liu Haojun, Liu Jianing, Wu Ying. STIFFNESS AND DAMPING FEATURES OF BRAIN COMPLEX NETWORKS[J]. Chinese Journal of Theoretical and Applied Mechanics, 2024, 56(10): 3002-3011. DOI: 10.6052/0459-1879-24-176
    [2]Zhang Wanjie, Niu Jiangchuan, Shen Yongjun, Yang Shaopu, Wang Li. DYNAMICAL ANALYSIS ON A KIND OF SEMI-ACTIVE VIBRATION ISOLATION SYSTEMS WITH DAMPING CONTROL[J]. Chinese Journal of Theoretical and Applied Mechanics, 2020, 52(6): 1743-1754. DOI: 10.6052/0459-1879-20-147
    [3]Shen Tao, Zhang Chongfeng, Wang Weijun, Feng Wenbo, Qiu Huayong. DYNAMIC SIMULATION ANALYSIS OF CAPTURE AND BUFFER SYSTEM BASED ON CLAW-TYPE DOCKING MECHANISM[J]. Chinese Journal of Theoretical and Applied Mechanics, 2020, 52(6): 1590-1598. DOI: 10.6052/0459-1879-20-108
    [4]Chen Ju, Guo Yongxin, Liu Shixing, Mei Fengxiang. DYNAMICAL CONTROL OF STABILITY FOR BIRKHOFFIAN SYSTEM[J]. Chinese Journal of Theoretical and Applied Mechanics, 2020, 52(4): 928-931. DOI: 10.6052/0459-1879-19-367
    [5]Hongnan Li, Jun Li, Gangbing Song. Improved suboptimal Bang-Bang control of aseismic buildings with variable friction dampers[J]. Chinese Journal of Theoretical and Applied Mechanics, 2007, 23(1): 101-109. DOI: 10.6052/0459-1879-2007-1-2005-601
    [6]Zongmin Hu, Zonglin Jiang. Wave dynamic processes in cellular detonation reflection from wedges[J]. Chinese Journal of Theoretical and Applied Mechanics, 2007, 23(1): 33-41. DOI: 10.6052/0459-1879-2007-1-2005-431
    [7]A DYNAMIC CONTROL MODEL OF PIEZOELECTRIC CANTILEVERED BEAM-PLATE BASED ON WAVELET THEORY[J]. Chinese Journal of Theoretical and Applied Mechanics, 1998, 30(6): 719-727. DOI: 10.6052/0459-1879-1998-6-1995-182
    [8]A TIME DOMAIN BOUNDARY ELEMENT METHOD FOR SYSTEMS WITH DAMPING[J]. Chinese Journal of Theoretical and Applied Mechanics, 1997, 29(5): 627-630. DOI: 10.6052/0459-1879-1997-5-1995-276
    [9]有孔隙的耦合热弹性体动力学的一些基本原理[J]. Chinese Journal of Theoretical and Applied Mechanics, 1996, 28(1): 55-65. DOI: 10.6052/0459-1879-1996-1-1995-302
    [10]基于变形动力学模型的黏弹性材料本构关系[J]. Chinese Journal of Theoretical and Applied Mechanics, 1993, 25(3): 375-379. DOI: 10.6052/0459-1879-1993-3-1995-655

  • Cited by

    Periodical cited type(5)

    1. 李鑫，唐贞云，杜修力. 半无限介质多自由度频响函数离散时间有理近似的稳定参数识别. 工程力学. 2024(08): 1-10 .
    2. 孟想，赵晔. 基于微波反射法的配电网电缆线路绝缘在线检测. 能源与环保. 2022(05): 204-209 .
    3. 吴利华，赵密，杜修力. 多层波导中矢量波动的时域人工边界条件. 力学学报. 2021(02): 554-567 . 本站查看
    4. 邢浩洁，李小军，刘爱文，李鸿晶，周正华，陈苏. 波动数值模拟中的外推型人工边界条件. 力学学报. 2021(05): 1480-1495 . 本站查看
    5. 孔曦骏，邢浩洁，李鸿晶，周正华. 多次透射公式飘移问题的控制方法. 力学学报. 2021(11): 3097-3109 . 本站查看

    Other cited types(6)

Catalog

    Get Citation
    PDF
    XML

    Article Metrics

    Article views (902) PDF downloads (109) Cited by(11)
    Related

    Download Center

    Author Center

    Copyright © Editorial Office of the Chinese Journal of Mechanics   京ICP备05039218号-1

    Address：15 Beishihuan Xi Lu, Haidian District, Beijing, China   China Pos：100190

    Tel：010-62536271

    Email：lxxb@cstam.org.cn

    微信公众号
    RSS

    Supported by: Beijing Renhe Information Technology Co., Ltd.  Baidu Analytics

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return