• Title/Summary/Keyword: 비정상 비행상황 방지

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Real-time Aircraft Upset Detection and Prevention Based On Extended Kalman Filter (확장칼만필터를 이용한 항공기 비정상 비행상황 판단 및 방지를 위한 실시간 대처법 연구)

  • Woo, Beomki;Park, On;Kim, Seungkeun;Suk, Jinyoung;Kim, Youdan
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.45 no.9
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    • pp.724-733
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    • 2017
  • Accidents caused by upset condition leads to fatal damage to both manned and unmanned aircraft. This paper deals with real-time detection of these aircraft upset situations to prevent further severe situations. Firstly, the difference between sensor measurement and predicted measurement from Extended Kalman filter is monitored to determine whether a target aircraft goes into an upset condition or not. In addition, repeating the time update stage of the Extended Kalman filter for a specific length of time can enable future upset situation prediction. The results of aforementioned both the approaches will build a bridge to upset prevention for future generation of manned/unmanned aircraft.

A study on the burn-in test to accomplish high quality cockpit air of an ultra-sonic aircraft in the early stage of production (생산 초기 초음속 항공기 조종석의 고품질 공기 확보를 위한 burn-in test 연구)

  • Shin, Jae Hyuk;Park, Sung Jae;Seo, Dong Yeon;Jeong, Suheon
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.44 no.10
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    • pp.871-876
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    • 2016
  • Abnormal odor similar with burning smell often appears at the cockpit in the beginning of ultra-sonic aircraft without air filter due to the heating of production materials remained at the bleed air duct. Sources of the odor should be removed by burn-in test before test flight in order to prevent pilot confuses order with emergency such as fire of engine. However, the present method cannot prevent abnormal odor completely at the high altitude flight because maximum temperature of flight is higher than it of burn-in-test. This paper suggests burn-in test improved based on the analysis of thermal conditions of high altitude flight. It is verified that the existing burn-in test cannot cover thermal conditions of high altitude flight due to the discontinuous flow control, high change rate of temperature per unit time and difference between limit temperature of condenser and turbine. In order to overcome the limitations of current methods, the new burn-in test with continuous flow control are suggested. The continuous flow control are achieved by ram air inlet control. The effect of suggested method are verified by ground tests and flight tests. The results show the bleed air temperature can cover the temperature of high altitude flight and prevent abnormal odor at the flight test.