• 한국정밀공학회지
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• 제33권10호
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• pp.829-835
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• 2016

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.

• 한국안전학회지
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• 제32권6호
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• pp.89-97
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• 2017

The tuned mass damper (TMD) system was first proposed as an efficient vibration control method for high-rise buildings, and multiple TMD (MTMD) system was then proposed for the purpose of improving the robust performance. Thereafter, the active TMD (ATMD) is proposed to improve the vibration control performance over the TMD and MTMD systems. However, this system may experience an system-instability problem in case of the actuator malfunction. In order to overcome such limitations of actuator malfunction causing the instability of the structural system, in this study, we investigate the feasibility of the multiple ATMD (MATMD) system that facilitates both advantages of the MTMD and ATMD. Numerical example demonstrates that, when the proposed system is designed to have the same capacity as the ATMD, it shows a similar control performance to the ATMD, but also has very good adaptive control performance against the emergency situations such as actuator failures.

• 전기전자학회논문지
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• 제23권1호
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• pp.266-272
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• 2019

멀티콥터는 수직 이착륙 할 수 있다는 장점 때문에 활용이 증가하고 있으며 이러한 멀티콥터의 정상적인 동작을 위해서는 고장 검출과 분리 문제가 매우 중요하다. 본 논문에서는 해석적 방법에 기반하여 헥사콥터 구동기의 고장을 검출하고 분리하는 새로운 방법을 제안한다. 제안한 방법에서는 헥사콥터의 수학적 모델로부터 추정한 구동기의 각속도를 이용하여 잔차를 새롭게 정의하고 생성된 잔차와 문턱값을 비교하여 구동기의 고장을 검출한다. 고장이 검출되면 헥사콥터의 동역학 모델과 생성된 잔차를 결합하여 고장을 분리한다. 제안한 방법은 수학적 모델을 기반으로 하여 간단하면서도 효과적이다. 헥사콥터 구동기의 단일 고장 상황을 가정한 시뮬레이션을 통해 제안한 방법의 유효성을 검증하였다.

• 대한기계학회논문집A
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• 제36권1호
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• pp.91-96
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• 2012

착륙장치 접개 작동기는 항공기 이착륙 시 착륙장치를 항공기 동체 내로 접어 올리거나 동체 밖으로 펼쳐 내려주는 역할을 한다. 접개 작동기 내부에는 착륙장치 펼침 상태에서 외란에 의해 착륙장치가 접히게 되는 것을 방지하기 위한 별도의 잠금장치가 장착된다. 이 잠금장치는 작동기 내부에 공급되는 유압을 통해 작동기 내부 구성품과 기계적으로 구속됨으로써 작동기 잠금 기능을 수행하게 된다. 착륙장치 접힘/펼침에 따라 잠금장치의 잠김/풀림이 반복되므로, 잠금장치는 항공기 운용 중 반복되는 동일 하중을 받게 되며, 이로 인한 피로 파괴의 가능성이 존재하게 된다. 본 논문에서는 잠금장치에 대한 피로해석 과정 및 결과를 제시하고, 피로시험을 통해 그 결과의 타당성을 검증하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.1853-1856
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• 2003

This paper considers the problem of longitudinal control of a platoon of automotive vehicles on a straight lane of a highway and proposes control laws in the event of loss of communication between the lead vehicle and the other vehicles in the platoon. Since safety plays a key role in the development of an Automated Highway System, fault-tolerant control is vital. In this paper, we develop a control algorithm in vehicle platooning and prove that this control algorithm is stable for certain class of faults such as parameter uncertainties. The performance of the controller is demonstrated through a series of simulations incorporating various vehicles and AHS faults. Results of simulation shows that the vehicles have good performance in spite of simple automotive and AHS failure, such as actuator failure,that is to say, engine input failure, communication failure between lead vehicle and the another vehicles.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2008년도 추계학술대회A
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• pp.244-249
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• 2008

It happened a failure on special bolt which supported main landing gear actuator up-lock rod of 00 aircraft. Fracture was occurred at end of center drilled hole and thread machined on bolt. Metallographic, fractographic, and other characteristics of embrittlement analysis and experiments carried out on the failed bolt to find out the reason. Bolt surface was cadmium electroplated(EP) to give lubrication and provide excellent corrosion resistance. Resultly, Bolt was failed due to cadmium embrittlement occurred during baking treatment as well as center drilled hole. for the failure that are relevant to failure analysis and prevention. For their successful functional application, cadmium EP bolts require proper and adequate baking treatment after electroplating, and is complete with no center drilled hole

• 한국군사과학기술학회지
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• 제13권5호
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• pp.769-774
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• 2010

It happened fractures on special bolt which supported main landing gear actuator up-lock rod of aircraft. Cracks were initiated mainly from the center hole and the external thread of the special bolt. To find out failure root causes, metallographic, fractographic analyses as well as test work were carried out. From the fractographic study by SEM work, fracture occurred by a brittle intergranular type failure. The fracture could be occurred primarily by solid-metal-induced embrittlement due to cadmium embrittler penetrated into the flaw existed after machining work for center hole and thread on the bolt during baking treatment processing to eliminate hydrogen. For its successful application, cadmium EP bolts require proper and adequate baking treatment after electroplating, and make no more drilled center hole on the bolt to prevent same failure.

• KSTLE International Journal
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• 제4권2호
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• pp.37-42
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• 2003

One of the obstacles for a magnetic bearing to be used in the wide range of industrial applications is the failure modes associated with magnetic bearings, which we don't expect for conventional passive bearings. These failure modes include electric power outage, power amplifier faults, position sensor faults, and the malfunction of controllers. Fault-tolerant magnetic bearing systems have been proposed so that the system can operate in spite of some faults in the system. In this paper, we designed a fault-tolerant magnetic bearing system for a turbo-molecular vacuum pump. The system can cope with the actuator/amplifier faults which are the most common faults in a magnetic bearing system. We implemented the existing fault-tolerant algorithms to experimentally prove the adequacy of the algorithms for industrial applications. As it turns out, the system can operate even with three simultaneously failing poles out of eight actuator poles.

• Journal of Chest Surgery
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• 제35권7호
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• pp.548-552
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• 2002

한국형 인공심장(AnyHeart)은 single moving actuator mechanism을 이용한 일체형 및 이식형 양심실 박동펌프이다. 저자 등은 양심 부전증에 의한 말기 심장병 환자에서 구난의료 차원으로 시도된 한국형 인공심장 (AnyHeart) 이식 1례를 경험하였기에 그 결과를 보고한다.

• Journal of Electrical Engineering and Technology
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• 제13권4호
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• pp.1740-1751
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• 2018

This paper proposes a novel fault tolerant tracking control (FTTC) scheme for a class of nonlinear systems with actuator failures based on the policy iteration (PI) algorithm and the adaptive fault observer. The estimated actuator failure from an adaptive fault observer is utilized to construct an improved performance index function that reflects the failure, regulation and control simultaneously. With the help of the proper performance index function, the FTTC problem can be transformed into an optimal control problem. The fault tolerant tracking controller is composed of the desired controller and the approximated optimal feedback one. The desired controller is developed to maintain the desired tracking performance at the steady-state, and the approximated optimal feedback controller is designed to stabilize the tracking error dynamics in an optimal manner. By establishing a critic neural network, the PI algorithm is utilized to solve the Hamilton-Jacobi-Bellman equation, and then the approximated optimal feedback controller can be derived. Based on Lyapunov technique, the uniform ultimate boundedness of the closed-loop system is proven. The proposed FTTC scheme is applied to reconfigurable manipulators with two degree of freedoms in order to test the effectiveness via numerical simulation.