Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Fault Detection of Small Turbojet Engine for UAV Using Unscented Kalman Filter and Sequential Probability Ratio Test

무향칼만필터와 연속확률비 평가를 이용한 무인기용 소형제트엔진의 결함탐지

  • Han, Dong Ju (Dept. of Aircraft Maintenance Engineering, Kukdong University)
  • 한동주 (극동대학교 항공정비학과)
  • Received : 2017.07.24
  • Accepted : 2017.08.28
  • Published : 2017.08.31
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Abstract

A study is performed for the effective detection method of a fault which is occurred during operation in a small turbojet engine with non-linear characteristics used by unmanned air vehicle. For this study the non-linear dynamic model of the engine is derived from transient thermodynamic cycle analysis. Also for inducing real operation conditions the controller is developed associated with unscented Kalman filter to estimate noises. Sequential probability ratio test is introduced as a real time method to detect a fault which is manipulated for simulation as a malfunction of rotational speed sensor contaminated by large amount of noise. The method applied to the fault detection during operation verifies its effectiveness and high feasibility by showing good and definite decision performances of the fault.

비선형특성을 갖고 있는 실제 무인기용 소형터보제트엔진의 운전 중 발생하는 결함을 효과적으로 탐지하기 위한 방안에 대해 연구하였다. 이를 위해서 동적 열역학 사이클해석을 통한 비선형 동특성 모델을 도출하였다. 실제적인 운전상황의 연출을 위해 잡음특성의 평가에 부합하는 무향칼만필터를 적용하였고 필터성능이 가미된 제어기를 설계하였다. 엔진회전수 센서의 결함을 통한 엔진 결함발생을 모사하였고, 발생된 결함의 실시간적인 탐지 방안으로 연속확률비 평가기법을 도입하였다. 이를 운전 중 엔진결함탐지에 적용한 결과 분명한 결정양상을 보임으로써 매우 효과적이고 유용함을 확인하였다.

Keywords

References

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