한국군사과학기술학회지 (Journal of the Korea Institute of Military Science and Technology)

  • 제28권3호
  • /
  • Pages.264-270
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  • 2025
  • /
  • 1598-9127(pISSN)
  • /
  • 2636-0640(eISSN)
한국군사과학기술학회 (The Korea Institute of Military Science and Technology)
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유도무기 풍동시험 모형 조종면 각변위 자동화 방안 연구

Study of Automation for Missile Wind Tunnel Model's Control Surface Deflection Angle

  • 김남균 (국방과학연구소 제2기술연구원) ;
  • 조철영 (국방과학연구소 제2기술연구원) ;
  • 이종건 (국방과학연구소 제2기술연구원) ;
  • 양병국 ((주) 아산 에스앤테크 기술연구소) ;
  • 최동진 (퍼스텍(주) 유도사업부)
  • Namgyun Kim (The 2nd Research Center, Agency for Defense Development) ;
  • Cheolyoung Cho (The 2nd Research Center, Agency for Defense Development) ;
  • Jonggeon Lee (The 2nd Research Center, Agency for Defense Development) ;
  • Byeongguk Yang (Research Center, Asan S & Tech) ;
  • Dongjin Choi (Guided Weapon Business Div., Firstec Co., LTD.)
  • 투고 : 2024.11.04
  • 심사 : 2025.03.14
  • 발행 : 2025.06.05
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초록

In this study, we developed a device that can remotely change the deflection angle during the wind tunnel test by installing the small motors and a driving mechanism to set the angle of control surface for the missile. The torque of the motor required during the wind tunnel test is 0.6 Nm, and the maximum diameter of the motor is 20 mm. The motor can controled the angle within ±0.1 degree. After designing and manufacturing the device, the dummy weight was applied to confirm the driving torque and control requirements of the system.

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참고문헌

  1. Jewel B. Barlow, William H Rae, Jr., Alan Pope, "Low Speed Wind Tunnel Testing", John Wiley & Sons, Inc., New York., pp. 19-25, 1999.
  2. Seongki Ahn, "Missile : Aerodynamic/Windtunnel testing," Academy for Defense and Science Technology, Agency for Defense Development, pp. 250-253 2015.
  3. Aerospace Vehicles Division, "Engineering & Technical Services," NLR Wind tunnel Models, 2024.