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Volume 42 Issue 11
Nov.  2016
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Journal of Beijing University of Aeronautics and Astronautics  > 2016  >  42(11): 2349-2357.
TAN Jianfeng, WU Chao, WANG Haowen, et al. Analysis on influence of rotor/empennage aerodynamic interaction on helicopter trim characteristic[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(11): 2349-2357. doi: 10.13700/j.bh.1001-5965.2015.0770(in Chinese)
Citation: TAN Jianfeng, WU Chao, WANG Haowen, et al. Analysis on influence of rotor/empennage aerodynamic interaction on helicopter trim characteristic[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(11): 2349-2357. doi: 10.13700/j.bh.1001-5965.2015.0770(in Chinese)
shu

Analysis on influence of rotor/empennage aerodynamic interaction on helicopter trim characteristic

doi: 10.13700/j.bh.1001-5965.2015.0770
  • 1.

    School of Mechanical and Power Engineering, Nanjing Tech University, Nanjing 211816, China

  • 2. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

  • 3. School of Aerospace, Tsinghua University, Beijing 10008

  • 4. Institute of Aircraft Design, AVIC Harbin Aircraft Industry Group Corporation, Harbin 150066, China

  • Received Date: 23 Nov 2015
  • Rev Recd Date: 27 Jan 2016
  • Publish Date: 20 Nov 2016
    Abstract
  • Unsteady aerodynamic interaction of rotor and empennage is the core content of helicopter trim model and flight dynamic model. The rotor/empennage aerodynamic interaction effect was considered indirectly through rotor inflow or induced velocity of rotor wake in classical trim method. However, the nonlinear airload induced by the unsteady aerodynamic interaction was not fully taken into account, and it is then difficult to reflect the influence of the rotor/empennage aerodynamic interaction on the trim characteristic. Therefore, based on unsteady panel/viscous vortex particle method, a rotor/empennage unsteady aerodynamic interactional model is established by adding an unsteady pressure term into empennage panel which is induced by unsteady interaction of rotor and empennage wake, and the nonlinear airload on empennage is simulated. The helicopter trim characteristic analysis method under rotor/empennage aerodynamic interaction is then established by coupling with helicopter trim method based on GA/LM hybrid optimization. The control of rotor and attitude of fuselage of UH-60A are simulated and compared with the flight test data to validate the present method. Compared with the result of the classic helicopter trim method in which rotor/empennage aerodynamic interaction is indirectly accounted through induced velocity, it is shown that the increase of longitudinal control and fuselage attitude is not simulated by the classic helicopter trim method; however, the phenomenon is captured by the present method, and is consistent with the tested characteristics of OH-6A, EH-101, etc. The influence of empennage's type on helicopter trim characteristic is then analyzed, and it is shown that the increase of rotor longitudinal control is great with low-set empennage, forward-set empennage in low-speed forward flight, and high-set empennage in high-speed forward flight. Start-set empennage for right revel rotor is useful to decrease the increasement of longitudinal control and fuselage attitude in low-speed forward.

     

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