Control characteristics analysis of split rudder of elastic forward swept wing

被引：0
|
作者：
Ma B. [1 ]
Su X. [1 ]
Feng H. [1 ,2 ]
Wang N. [1 ]
Zhang Y. [1 ]
机构：
[1] College of Aeronautics and Astronautics Engineering, Air Force Engineering University, Xi'an
[2] Unit 93427, The Chinese People's Liberation Army, Beijing
来源：
Su, Xinbing (sxinbing01@163.com) | 1849年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 43期
基金：
中国国家自然科学基金;
关键词：
Computational fluid dynamics/computational structural dynamics (CFD/CSD) loose coupling; Control characteristics; Elastic deformation; Forward swept wing (PSW); Split rudder;
D O I：
10.13700/j.bh.1001-5965.2017.0142
中图分类号：
学科分类号：
摘要：
Aimed at the influence of elastic deformation on the control characteristics of split rudder for the forward swept wing (FSW) aircraft, the computational fluid dynamics/computational structural dynamics (CFD/CSD) loose coupling static aeroelastic numerical calculation method was adopted. The calculation and analysis on control characteristics of the split rudder with rigid and elastic wings were performed under the subsonic condition. The simulation had highlighted the influence of wing deformation on the control characteristics of the rudder. The calculation result shows that, when the right side split rudder opens, compared with rigid wing, the stall attack angle of the elastic wing advances about 2°, the attack angle of maximum lift-drag ratio advances about 1°, the yaw effect at small attack angle is enhanced, the “pits” phenomenon of right-roll moment and roll moment appears, and the trend of yaw at high angle of attack advances about 8° with more violent roll action; under the influence of sideslip, the decrease extent of the yawing moment with the increase of sideslip angle is larger than that of the rigid wing, and the roll moment has completely opposite result; under the action of down moment proving by rudder, the increase extent of the yawing moment with the increase of sideslip angle is larger than that of the rigid wing. By comparison, the control characteristics of split rudder for the elastic FSW have a distinct difference with rigid FSW. © 2017, Editorial Board of JBUAA. All right reserved.
引用
收藏
页码：1849 / 1858
页数：9
相关论文
共 25 条
  • [1] Saltzman E.J., Hicks J.W., In-flight-lift drag characteristics for a forward swept wing aircraft: NASA TP-3414, (1994)
  • [2] Zhang B.Q., Laschka B., On forward-swept wing's aerodynamic characteristics, Journal of Northwestern Poly Technical University, 7, 3, pp. 321-328, (1989)
  • [3] Spacht G., The forward swept wing-A unique design challenge: AIAA-1980-1885, pp. 1-5, (1980)
  • [4] Wu L.X., Zuo Z., Liu P.S., Et al., Tailless flying wing aerodynamic configuration being optimal selection in UCAV general layout design, Hongdu Science and Technology, 1, pp. 1-5, (2003)
  • [5] Mcmasters J.H., Cummings R.M., Airplane design-past, present, and future, Journal of Aircraft, 39, 1, pp. 10-17, (2002)
  • [6] Liu W.F., Wang X., Mi K., A new aerodynamic configuration of UAV with variable forward-swept wing, Acta Aeronautica et Astronautica Sinica, 30, 5, pp. 832-836, (2009)
  • [7] Sun J., Zhang B., Yang G., Concept investigation of 'W' tailless configuration: AIAA-2005-4602, (2005)
  • [8] Dorsett K.M., Mehl D.R., Innovative control effectors (ICE): WL-TR-96-3043, (1996)
  • [9] Gillard W.J., Innovative control effectors (configuration 101) dynamic wind tunnel test report. Rotary balance and forced oscillation tests: AFRL-VA-WP-TR-1998-3043, (1998)
  • [10] Campbell J.P., Seacord C.L., Determination of the stability and control characteristics of a tailless all-wing airplane model with sweepback in the langley free-flight tunnel: NACA ACR-L5A13, (1947)
123