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

  • 제41권2호
  • /
  • Pages.142-149
  • /
  • 2013
  • /
  • 1225-1348(pISSN)
  • /
  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
권호 표지
DOI QR코드

DOI QR Code

UAV용 유체역학적 추력편향 노즐의 고 정확도 다분력 시험장치 개발

Development of the High-Accuracy Multi-Component Balance for Fluidic Thrust Vectoring Nozzle of UAV

  • Song, Myung-Jun (Department of Aerospace & Mechanical Engineering, Graduate School, Korea Aerospace University) ;
  • Chang, Hong-Been (Department of Aerospace & Mechanical Engineering, Graduate School, Korea Aerospace University) ;
  • Cho, Yong-Ho (Microfriends, Inc.) ;
  • Lee, Yeol (School of Aerospace & Mechanical Engineering, Korea Aerospace University)
  • 투고 : 2012.09.03
  • 심사 : 2013.01.31
  • 발행 : 2013.02.01
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

추력편향 제어기술은 무인기의 고기동성 확보에 있어 필수적이다. 본 연구에서는 동축 코안다 효과를 이용한 초음속 사각노즐 유동의 추력편향 특성을 정량적으로 측정할 수 있는 다분력 시험장치를 개발하였다. 엄밀한 보정 및 자세한 자료분석 과정을 통하여 본 연구에서 개발된 시험장치의 로드셀 상호간섭에 의한 측정오차는 약 5% 미만임이 관찰되었고, 또한 고압 연결튜브에 의한 오차는 거의 무시할 수 있음이 판명되었다. 아울러 개발된 시험장치를 이용하여 본 연구의 동축 코안다 효과를 이용한 사각노즐의 추력편향 특성에 관한 기초적인 실험결과가 얻어졌다.

The thrust vector control technique is essential for high maneuverability of unmanned aerial vehicles. In the present study, a multi-component balance was developed to quantitatively evaluate the thrust-vectoring performance of a supersonic rectangular nozzle based on the Coanda coflowing effect. Precise calibration and detailed data analysis were performed during the development. It was found that the cross-talk errors between load cells in the balance were less than 5%, and that the unwanted errors due to high-pressure supply tubes were almost negligible, which contributed to the high accuracy of the present balance design. Some preliminary test results of the thrust-vectoring performance of the present nozzle design were also obtained and analyzed.

키워드

참고문헌

  1. Deere, K. A., "Summary of Fluidic Thrust Vectoring Research Conducted at NASA Langley Research Center," AIAA 2003-3800, 2003.
  2. Chiarelli, C., Johnsen, R. K., Shieh, C. F., Wing, D. J., "Fluidic Scale Model Multi-Plane Thrust Vector Control Test Results," AIAA-93-2433, 1993.
  3. Diaz-Guardamino, I. E., "Combining Suction Control and Transverse Jets for Fluidic Thrust Vector Control," ProQuest, MS Thesis, The State University of New York, 2008.
  4. Wing, D. J., "Static Investigation of Two Fluidic Thrust-Vectoring Concepts on a Two-Dimensional Convergent Divergent Nozzle," NASA Technical Memorandum 4574, 1994.
  5. Flamm, J. D., "Experimental Study of a Nozzle Using Fluidic Counterflow for Thrust Vectoring," AIAA 98-3255, 1998.
  6. Crowther, W. J., Wilde, P. I. A., Gill, K., Michie, S. M., "Towards Integrated Design of Fluidic Flight Controls for a Flapless Aircraft," The Aeroanutical Journal, Vol. 113, No. 1149, pp.699-713, 2009. https://doi.org/10.1017/S0001924000003365
  7. Banazadeh, A., Saghafi, F., Ghoreyshi, M., Pilidis, P., "Experimental and Computational Investigation into the Use of Co-flow Fluidic Thrust Vectoring on a Small Gas Turbine," The Aeroanutical Journal, Vol. 112, No. 1127, pp.17-25.
  8. Yoon, S. H., Jun, D. H., et al., "Experimental Study of Thrust Vectoring of Supersonic Jet Utilizing Co-flowing Coanda Effects," J. KSAS, Vol. 40, No. 11, pp.927-933, 2012. https://doi.org/10.5139/JKSAS.2012.40.11.927
  9. Neely, A. J., Gesto, F. N., Young, J., "Performance Studies of Shock Vector Control Fluidic Thrust Vectoring," AIAA 2007-5086, 2007.
  10. Lee, K. J., Park, I. S., Choi, Y. K., "Design Method of the High Accuracy Thrust Stand," J. KSPE, Vol. 10, No. 1, pp. 9-17, 2006.
  11. Ramaswamy, M. A., Alvi, F. S., Krothapalli, A., "Special 6-Component Jet Rig Balance for Studying New Thrust Vectoring Concepts," Record International Congress on Instrumentation in Aerospace Simulation Facilities, pp. 202-213, 1997.
  12. Runyan, R.B., Rynd, Jr., J. P., Seely, J. F., "Thrust Stand Design Principles," AIAA 92-3976, 1992.
  13. Berton, J. J., "Divergence Thrust Loss Calculations for Convergent-Divergent Nozzles: Extensions to the Classical Case," NASA Technical Memorandum 105176, 1991.

피인용 문헌

  1. An Experimental Study on the Characteristics of Rectangular Supersonic Jet on a Flat Plate vol.17, pp.3, 2016, https://doi.org/10.5139/IJASS.2016.17.3.324
  2. Thrust Vectoring of Sonic Jet by Using Coanda Flap and Solenoid Valve vol.54, pp.9, 2016, https://doi.org/10.2514/1.J054993
  3. Bidirectional Thrust Vectoring Control of a Rectangular Sonic Jet 2018, https://doi.org/10.2514/1.J056598
  4. Application of Backstep Coanda Flap for Supersonic Coflowing Fluidic Thrust-Vector Control vol.52, pp.10, 2014, https://doi.org/10.2514/1.J052971
  5. Experimental Study of the Quantitative Characteristics of Fluidic Thrust Vectoring Nozzle for UAV vol.42, pp.9, 2014, https://doi.org/10.5139/JKSAS.2014.42.9.723