Journal of the Korean Society for Aeronautical & Space Sciences (한국항공우주학회지)

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
권호 표지
DOI QR코드

DOI QR Code

Design and Test of Lateral/Directional Control Law of a Tailless UAV Using Spoilers

스포일러를 이용한 무미익 항공기의 횡방향축 제어기설계 및 시험

  • Received : 2019.02.26
  • Accepted : 2019.05.27
  • Published : 2019.06.01
Download PDF
⟨ Previous Next ⟩

Abstract

A tailless or Blended-Wing-Body(BWB) shaped configuration is highlighted for UCAV with low RCS characteristics. The BWB configuration is characterized by its directional static instability and low controllability. To control the directional movement of the BWB configured vehicle, directional thrust vectoring equipment or drag rudder typed control surfaces which utilize the drag differences of the wing can be considered. This paper deals with a BWB shaped configuration using a spoiler and describes the lateral-directional aerodynamic characteristics of the vehicle. In addition, it is shwon that the lateral-directional motion can be controlled effectively by using the classical PI control structure. This control law is verified by flight test and showed adequate for the tailless BWB shaped UAV.

수직미익이 없는 전익기 형상은 낮은 레이더반사면적(RCS) 특성으로 인해 최근 UCAV를 위한 대표적인 형상으로 대두되고 있다. 무미익 전익기 형상은 방향축 관점에서 보면 정적으로 불안정하면서도 이를 효과적으로 제어하기 위한 수직 조종면이 없다는 두 가지 난제를 모두 갖고 있다. 이같은 형상을 제어하기 위해서는 추력 벡터링을 적용하거나 날개의 항력차이를 이용하는 드래그 러더(Drag Rudder) 형태의 에일러론 또는 스포일러 등을 적용할 수 있다. 본 논문에서는 전익기 형상의 횡방향축 공력특성 및 드래그 러더 중 스포일러 형태의 조종면에 대한 공력특성을 설명한다. 또한, PI 구조의 제어설계 기법을 사용하여 전익기의 횡방향축 운동을 효과적으로 제어할 수 있음을 제시하고, 비행시험을 통하여 설계된 제어기로 안정적인 비행이 가능함을 보였다.

Keywords

References

  1. Yun, S. H., Lee, H. T., and Sim, H. C., "Improving the Stability and Maneuverability of Small Tailless BWB Unmanned Aircraft," Proceeding of The Korean Society for Aeronautical and Space Sciences Spring Conference, April, 2011, pp. 732-737.
  2. Brinker, S. J., "Autonomous Steering of the Joint Unmanned Combat Air Systems(J-UCAS) X-45A," Unmanned Unlimited Technical Conferene, Workshop and Exhibit, September, 2004.
  3. Morris, J. S., "Integrated Aerodynamics and Control System Design for Tailless Aircraft," AIAA Guidance, Navigation and Control Conference, August, 1992.
  4. Addington, A. G., and Myatt, H. J., "Control-Surface Deflection Effects on Aerodynamic Response Nonlinearities," Atmospheric Flight Mechanics Conference, 2000, pp. 435-444.
  5. Stenfelt, G., and Ringertz, U., "Lateral Stability and Control of a Tailless Aircraft Configuration," Journal of Aircraft, Vol. 46, No. 6, 2009, pp. 2161-2163. https://doi.org/10.2514/1.41092
  6. Stenfelt, G., and Ringertz, U., "Yaw Control of a Tailless Aircraft Configuration," Journal of Aircraft, Vol. 47, No. 5, 2010, pp. 1807-1810. https://doi.org/10.2514/1.C031017
  7. Nieto-Wire, C., and Sobel, K., "Flight Control Design for a Tailless Aircraft Using Eigenstructure Assignment," International Journal of Aerospace Engineering, 2011.
  8. Mark, V., Gianfranco, L. R., Frank, D., "Controllability of Blended Wing Body Aircraft," 26th International Congress of the Aeronautical Sciences, September, 2008.
  9. Hong, J. S., Hwang, S. Y., Lee, K. H., and Hur, G. B., "Design of laeral/directional control law of a tailless UAV using spoilers," Proceeding of The Korean Society for Aeronautical and Space Sciences Spring Conference, April, 2018, pp. 219-220.
  10. Hong, J. S., Hur, G. B., and Song, C. H., "Linear Control Allocation for an Experimental Blended Wing Body UAV," Asia-Pacific International Symposium on Aerospace Technology, November, 2012.