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10,000 lbf-in급 힌지라인 이중화 전기식 구동장치 설계 및 성능평가
정승호(Seuhg-Ho Jeong),설진운(Jin-Woon Seol),허석행(Seok-Haeng Heo),이병호(Byung-Ho Lee),조영기(Young-Ki Cho) 한국항공우주학회 2019 韓國航空宇宙學會誌 Vol.47 No.2
항공기용 전기식 구동장치는 유압식 구동장치에 비해 소형/경량화에 유리하고, 힌지라인 형태의 구동장치는 공기저항이 작고 스텔스 등의 특수 목적에 적합한 특징을 가지고 있다. 본 논문에서는 10,000 lbf-in급 힌지라인 이중화 전기식 구동장치의 동작성능시험을 위한 시스템 설계 내용을 기술하였다. 영구자석전동기의 자속 기준 제어와 이중화 구동기의 torque fighting을 고려한 제어기를 설계하고, 구동장치 시스템 모델을 수립하여 성능 시뮬레이션을 수행하였다. 성능시험을 수행하여 시뮬레이션 결과와 비교하였으며 목표성능 만족여부를 확인하였다. Electro-mechanical actuator system for aircraft has advantages in compactness and its lightweight, compared to the hydraulic actuator system. Hinge line actuator has low air resistance and is suitable for special purpose such as stealth. This paper describes design contents of 10,000 lbf-in class dual redundant hinge line electro-mechanical actuator system for performance test. The control structure was designed to minimize impact of torque fighting. A mathematical model is proposed to analyze and validate the performances of actuator by comparison with experiment results.
김태형(Taehyung Kim),설진운(Jin Woon Seol),허석행(Seok Haeng Huh),백주현(Joo Hyun Baek) Korean Society for Precision Engineering 2017 한국정밀공학회지 Vol.34 No.9
In this paper, a study on the effectiveness of micro-peening was accomplished for improvement of fatigue characteristics for reduction gear of manned and unmanned aircraft. The Almen saturation curve was obtained by various peening injection pressure supplied from a commercial air jet peening machine. The effective micro-peening process condition was adopted as five bar. The four points rotary bending fatigue test was conducted by using test specimen made of AISI alloy that was carburized based on AMS standard in this work. From the fatigue test result, the fracture life of specimen peened by nozzle pressure with five bar and six bar was higher than the un-peened specimen by approximately 323 percent and 146 percent respectively. However, the fracture life of specimen peened by the nozzle pressure with six bar was lower by approximately 221 percent than the peened specimen by five bar. For this reason, the peening nozzle pressure with five bar was decided as the optimum micro-peening condition. Effectiveness of micro-peening was validated and this micropeening technique will be used for real manned and unmanned aircraft gear parts or other durability mechanical parts.
Accelerated Life Analysis and Endurance Verification of Electro-Mechanical Actuator
허석행(Seok Haeng Huh),이병호(Byung Ho Lee),설진운(Jin Woon Seol),백주현(Joo Hyun Baek),양명석(Myung Seok Yang),권준용(Jun Young Kwon) Korean Society for Precision Engineering 2016 한국정밀공학회지 Vol.33 No.10
Electro-Mechanical Actuator installed on the aircraft plays a key role in an aircraft’s flight control through flight control computer. Reliable prediction of the actuator is important for the aircraft. To estimate the lifetime of a product, it is necessary to test full target life. However, it is very difficult to perform it due to the long life time of actuator but short period of development time with increasing cost. Therefore, accelerated life test has been used to reduce the test time for various reasons such as reducing product’s development cycle and cost. In this paper, to predict the lifetime of the actuator, we analyzed the flight profile of aircraft and adapted the method of accelerated life test in order to accelerate failure modes that might occur under user conditions. We also set up an endurance test equipment for validating the demanded lifetime of an actuator and performed accelerated life test.
다중 센서 데이터를 이용한 무인기 유성감속기의 고장진단 연구
박형준(Hyung Jun Park),조성희(Seong Hee Cho),장경환(Kyung-Hwan Jang),설진운(Jin-Woon Seol),권병기(Byung-Gi Kwon),권준용(Jun-Yong Kwon),최주호(Joo-Ho Choi) 한국신뢰성학회 2020 신뢰성응용연구 Vol.20 No.4
Purpose: The harsh operating conditions of unmanned aerial vehicles cause crack propagation in the gear teeth in the actuator, which eventually leads to breakdown. For the prevention of service delays or failure because of crack propagation, a diagnostic process based on the built-in and add-on sensors’ signals is proposed for the planetary gearbox of unmanned aerial vehicles. Methods: A planetary gearbox test rig is constructed, and the motor current, the position and vibration signals are acquired for the normal and crack-induced states. Features representing the health state are extracted and selected by using a suitable performance measure. Subsequently, the K-Nearest Neighbor algorithm is applied to the selected features, from which the classifications of the normal and fault states are performed. Results: Among the acquired signals, the vibration signal obtained from add-on sensor showed better performance (100%, J₃ = 46.6) than the motor current (88.7%, J₃ = 3.89) and angular position (100%, J₃ = 5.88) acquired from the built-in sensor. In the features of the vibration signal, those in the frequency band with strong energy concentration showed outstanding separability. Conclusion: The proposed method successfully classifies the fault from the normal in the planetary gearbox in the basis of the frequency-domain features of the vibration signal.
인공신경망을 이용한 고장 심각도에 따른 무인기용 유성감속기의 고장진단 연구
박형준(Hyung Jun Park),심진우(Jinwoo Sim),장재원(Jaewon Jang),장경환(Kyung-Hwan Jang),설진운(Jin-Woon Seol),권준용(Jun-Yong Kwon),최주호(Joo-Ho Choi) 한국신뢰성학회 2021 신뢰성응용연구 Vol.21 No.4
Purpose: Gear teeth in the rotary geared actuator of the unmanned aerial vehicle, experience crack propagation because of its harsh operating conditions. To prevent the failure of catastrophic events, this study proposes a diagnostic approach for various gear crack levels based on the built-in and add-on sensor signal. Methods: A downsized planetary gearbox test rig was prepared, in which the motor position, current, and vibration signals were acquired for the normal and 4 different crack-induced states. Signals were filtered around the region of resonance frequencies by spectral kurtosis and the features for the health state were extracted. Then, feature selection was conducted based on the correlation with fault levels. Finally, the Artificial Neural Network (ANN) model was constructed to identify different fault sizes of the cracks, and K-fold validation was adopted to optimize the parameters of the ANN model. Results: Among the various signals, the vibration from the add-on sensor and a position from the built-in sensor exhibited high performance compared to the current signal. The features after band-pass filtering yielded a high correlation with fault severity. Conclusion: The proposed method successfully diagnosed different fault severities of gear cracks in the planetary gearbox by using both the built-in and add-on signals.