• Title/Summary/Keyword: 인공 결빙 비행시험

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A Study on the Parameters for Icing Airworthiness Flight Tests of Surion Military Helicopter (수리온 군용헬기의 결빙 감항인증 비행시험을 위한 파라미터 고찰)

  • Hur, Jang-Wook;Kim, Chan-Dong;Jang, Jae-Sang
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.43 no.6
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    • pp.526-532
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    • 2015
  • In order to relieve limitation of flight operation under icing condition and verify its operation in adverse weather condition for Surion, military helicopter developed in Korea, airworthiness certification in icing condition is required. The process of Surion icing certification should be considered by implementation of four methods by step such as CFD analysis, simulated flight tests, artificial icing flight tests, and natural icing flight tests. For Surion icing flight tests, these are required 20~30 sorties and 20~23 hours in artificial icing condition; 20~30 sorties and 20~22 hours in natural icing condition. In addition, to proceed with efficient flight tests, it is necessary to implement artificial icing flight tests in LWC $0.5{\sim}1.0g/m^3;$ natural icing flight tests in less than LWC $0.5g/m^3$.

Indirect Verification of the Icing Test Condition Using Ice Thickness (얼음두께를 이용한 결빙시험조건의 간접 확인기법)

  • Kim, Yoo Kyung;Park, Nameun;Choi, Gio
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.46 no.11
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    • pp.944-951
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    • 2018
  • 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.