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얼음두께를 이용한 결빙시험조건의 간접 확인기법

Indirect Verification of the Icing Test Condition Using Ice Thickness

  • 투고 : 2018.09.03
  • 심사 : 2018.10.11
  • 발행 : 2018.11.01

초록

회전익기의 결빙운용능력이 요구될 경우 자연결빙 비행시험전 풍동시험과 인공결빙시험을 선행하면 개발기간을 단축시킬수 있다. 한국형기동헬기의 경우 인공결빙 시험을 수행하여 각 시험조건에서 방 제빙기능의 정상작동을 확인 후 자연결빙시험을 수행하였다. 인공결빙시험에서 시험조건인 액적량(LWC)과 액적 평균직경(MVD)을 확인하기 위해 정밀센서인 구름기상정보관측기(CCP)를 사용하는데 시험환경, 장비오차등의 이유로 측정치의 불확실성이 존재할 수 있어 시험조건 확인이 다방면으로 필요하다. 동체에 착빙된 얼음두께로부터 LWC를 계산하여 측정값과 비교한 결과, 시험조건을 간접적으로 검증해 볼 수 있는 효과적인 방법임을 확인하였다.

Artificial icing test and wind tunnel test can be performed to reduce the development period when a rotorcraft is required operation under icing situations. Artificial icing test of the KUH(Korean Utility Helicopter) was performed in advance to verify anti-icing and de-icing performance before natural icing test. Although high-precision sensor, the CCP(Cloud Combination Probe) is used to measure icing test condition parameters such as LWC(Liquid Water Content) and MVD(Median Volume Diameter), the measured values need to be verified in various methods due to the possibility of uncertainties which are the test atmosphere environment, sensor errors, and etc. The calculated LWC from the ice thickness cumulated on the fuselage of the KUH is compared to the measured value by CCP, and the results show the effective indirect method to check the test conditions.

키워드

참고문헌

  1. Peterson, A. A., and Dadone, L. U., "Helicopter Icing Review," Boeing Vertol Company, September 1980.
  2. Ministry of Defence, "Defence Standard 00-970 Part 7 Section 2," Issue 6, July 2015, leaflet 711/2.
  3. 88PR0886, "Flight Test Report for KUH Artificial and Natural Icing Flight Test," May 2018.
  4. BOEING VERTOL MODEL 107 HELICOPTER ICING & WEATHER TESTS 30554b, YouTube.
  5. David N. Anderson, "Manual of Scaling Methods," NASA/CR-2004-212875, March 2004.
  6. An, Y. G., and Myong, R. S., "Scaling Methods for Icing Wind Tunnel Test," JASASS, 2016 pp. 146-156.
  7. Kim, K. S., Lee, J. H., Park, N. U., Kim, B. K., "De-icing Performance Study of Main Rotor Blade Through in Icing Flight Test", KSASS 2016 Conference, November 2016, pp. 1290-1291.
  8. Kim, Y. K., and Kim, B. K, "Improvement of De-icing Logic Sensitivity to Minimize Ice Accretion Effect of the Rotor Blade under LWC Variation", IEIE Conference, June 2018, pp. 770-773.
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  10. Society of Automotive Engineers, AS 5498, "Minimum Operational Performance Specification for Inflight Icing Detection Systems," October 2001, pp. 19.
  11. FAA FAR Part 29 Appendix C, "Airworthiness Standards: Transport Category Rotorcraft - Icing Certification."