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무인 무미익 항공기의 무게중심 변화를 고려한 L1 적응제어 비행제어 법칙 설계 및 성능 검증
고동현(Dong-hyeon Ko),강지수(Ji-soo Kang),최기영(Keeyoung Choi) 한국항공우주학회 2019 韓國航空宇宙學會誌 Vol.47 No.2
무미익 항공기는 꼬리 날개가 없기 때문에 일반적인 형태의 항공기에 비해 피탐성 낮으나 안정성이 좋지 않아 제어기를 설계하는 것이 쉽지 않다. 특히 비행 중에 임무장비 투하나 연료 소모 등에 의해 무게중심의 위치가 변화하는 것을 고려한다면 제어기 설계는 더욱 더 어렵게 된다. 본 논문에서는 이러한 문제점을 극복하기 위한 방법으로 L1 적응제어 방식을 제안하며 비선형 시뮬레이션을 통하여 제어기의 안정성과 성능을 검증하였다. 설계지표 선정을 위해 RPV Flying Quality Design criteria의 내용을 참고하였다. 시뮬레이션을 이용하여 급격한 관성량의 변화에 대해 설계된 적응제억기가 무미익 항공기 안정성을 유지하는 것을 보이고, 이득 스케쥴링 기법과 함께 사용 시 계산량이 줄어들 수 있음을 확인하였다. Tailless aircraft have advantages of low visibility compared to conventional aircraft, but drawback of poor stability as well which makes designing controller difficult. The controller design is more difficult, especially when the center of gravity moves due to store release or fuel consumption during flight. In this paper, an L1 adaptive controller is proposed as a way to overcome these problems. The reliability and performance of the controllers were verified by non-linear simulations. RPV Flying Quality Design criteria were used for design criteria. Using the simulation, it is shown that the adaptive controller maintains stability of the unmanned aircraft for sudden large change in the inertial properties. It is also shown that the calculation burden can be reduced when it is used with the gain scheduling method.
역설계 기반 제조기술 설계를 통한 방탄용 부가장갑킷트 개발에 관한 연구
고동현 ( Ko Dong Hyeon ),문태상 ( Moon Tae Sang ),김영기 ( Kim Young Ki ) 한국품질경영학회 2021 품질경영학회지 Vol.49 No.3
Purpose: The study focused on localization of the enhanced applique armor kit (EAAK), which are applied to Korea Assault Amphibious Vehicle (KAAV). Methods: For this propose, we developed the manufacturing technology by analyzing the original products. Considering the conditions used in the military, we made the test evaluation criteria. Results: In results, The EAAK developed through this research performs equivalent performance compared to Rafael, Co. Thus, It is possible not only stably supply a parts of EAAK for maintenance, but also to reduce costs due to import substitution effect. Conclusion: It is expected that the manufacturing technology and test evaluation criteria accumulated through this study can be used in the localization of similar parts.
탐색적 요인분석을 활용한 소규모 방산업체의 프로세스 검토 항목 도출
고동현(Ko, Dong Hyeon),남윤욱(Nam, Yoon Wook),윤준호(Yoon, Joon Ho) 한국서비스경영학회 2024 서비스경영학회지 Vol.25 No.2
The purpose of the study is to derive process review items suitable for small-scale enterprises in defense industry to improve the quality of defense service quality. The scope of the process review is established by reviewing of process review manual of DTaQ(Defense Agency for Technology and Quality) and analyzing small-scale enterprises in defense industry. In addition, exploratory factor analysis is used to derive items suitable for small-scale enterprises in defense industry among special defense requirements. For analysis, a survey is conducted targeting small-scale enterprises in defense industry in charge of land systems team 4 of DTaQ. After a data coding process, 130 pieces of survey data are used for analysis. As a result of the analysis, 3 factors consisting of 12 items were derived. If the items derived through this sturdy are utilized, it is expected that a process review plan that can be practically applied to small-scale enterprises in defense industry will be developed.
고동현(Dong-Hyeon Ko),남윤욱(Yoon-Wook Nam),김현민(Hyun-Min Kim),주용원(Yong-Won Joo) 한국산학기술학회 2023 한국산학기술학회논문지 Vol.24 No.9
본 연구는 소규모 사업체 규모별 국방 서비스품질 향상을 위해 개선이 필요한 국방 서비스품질 요소 도출을 목적으로 한다. Kano 모델을 활용하여 품질속성을 분류하고, Timko의 고객만족계수를 통해 각 요소가 고객의 만족과 불만족 정도에 미치는 수준을 분석하였으며, 나아가 PCSI 지수를 통해 우선 개선요소를 도출하였다. Kano 모델을 활용한 서비스품질 요소 분류결과 100인 미만 50인 이상의 사업체에서 일원적 품질(O)로 분류되었던 항목이 50인 미만의 사업체에서는 매력적 품질(A)로 분류되었다. 고객만족계수 분석결과 규모가 커짐에 따라 만족계수(S)는 떨어지고, 불만족계수(D)는 높아졌다. PCSI 지수에 따른 규모별 우선 개선 순위 분석 결과 규모에 따라 개선이 필요한 국방 서비스품질 요소에 차이가 있음을 알게 되었다. 본 연구를 통해 도출한 결과를 바탕으로 정부품질보증 활동 시 소규모 사업체의 규모별 특성에 맞게 국방 서비스품질을 제공한다면 고객만족도가 기존보다 크게 향상될 것으로 기대된다. This study aimed to derive service quality factors for business improvement according to the company size. The components of defense service quality were first classified based on the Kano model and then computed the customer satisfaction coefficient suggested by Timko (1993). Finally, the Potential Customer Satisfaction Improvement (PCSI) Index was also calculated to determine potentially improvable customer satisfaction using the current satisfaction level of quality elements classified using the Kano model. The Kano model classified the quality factors as one-dimensional in businesses with less than 100 people but more than 50 people and attractive factors in businesses with less than 50 people. In addition, the satisfaction and dissatisfaction coefficients decreased as the business size increased. Through this study, classifying the defense service quality property differs according to the company size. Moreover, there were differences in defense service quality factors that needed improvement depending on the company size. Based on the results derived from analysis by the company size, customer satisfaction is expected to increase significantly if service quality is provided according to the characteristics of each size during defense quality assurance activities.
고동현(Dong-hyeon Ko),모하마드 라히미(Mohamad Rahimy),최기영(Keeyoung Choi) 한국항공우주학회 2019 韓國航空宇宙學會誌 Vol.47 No.11
회전익 항공기는 기체 자체로는 불안정하기 때문에 안정적인 운영을 위해서는 flybar와 같은 안전장치가 필요하다. 최근에는 센서 기술이 발달하여, flybar 대신 기체의 안정성을 향상 시킬 수 있는 안정성 증대 장치(SAS : Stability Augmentations System)를 사용하고 있다. 안정성 증대 장치가 포함된 회전익 항공기를 무인으로 활용하기 위해서는 안정성 증대 장치 기능을 포함한 비행제어 컴퓨터가 반드시 필요하다. 본 논문에서는 역 설계를 활용하여 상용 안전성 증대 장치의 알고리즘을 예측하였다. 그리고 그 결과를 비행제어컴퓨터에 활용하여 무인회전익 시스템을 만드는 방법을 제안한다. 그리고 알고리즘을 검증하기 위해 상용 안정성 증대 장치의 출력과 개발한 알고리즘의 출력 비교하였다. 최종적으로 검증된 알고리즘을 활용하여 자동 비행이 가능한 무인 회전익시스템을 체계를 구축하였다. Because rotorcraft is unstable, it needs a stability system such as flybar. Recently, sensor technology has been developed, it uses a stability augmentation system to improve stability instead of flybar. To use of these rotorcraft which include stability augmentations system for unmanned system, flight control computer, include stability augmentations system function, must be required. In this paper, a reverse-engineering method of estimating Algorithm of Commercial Stability Augmentation System is proposed, the result is applied in the flight computer to make an unmanned rotorcraft system. Finally using a validated algorithm, it is possible to establish a system of unmanned automatic rotorcraft system.
내연기관 이륜차에서 전기 이륜차 전환을 위한 충돌해석 및 구조해석에 관한 연구
김희대(Hee Dae Kim),고동현(Dong-Hyeon Ko),이상찬(Sang-Chan Lee) 한국기계가공학회 2023 한국기계가공학회지 Vol.22 No.12
The aluminum frame of the internal combustion engine was used for structural and crash studies to transform the internal combustion engine into an electric two-wheeled vehicle. Structural analysis was performed on the load induced by the change in the position of the part throughout the modification process, and structural safety was ensured through design improvement. The collision analysis was divided into two scenarios: head-on and side-on. In the event of a collision at 60 km/h, the safety of the battery was tested and studied using the stress distribution of the frame to analyze the reverse design process required for adjustment.
김도균(Do-Kuen Kim),고동현(Dong-Hyeon Ko),이상찬(Sang-Chan Lee) 한국기계가공학회 2021 한국기계가공학회지 Vol.20 No.12
Reducing the weight of automobiles is a significant global developmental task. Two materials are used to lighten automobiles: aluminum and CFRP frames. Aluminum is a non-ferrous metal, and CFRP is a composite material. They are lighter and harder than other materials. The two materials were used for the collision analysis. Subsequently, the two cases were compared. Three cases were considered for the collision analysis: head-on collision, partial head-on collision, and side collision at a speed of 60 km/h. The three cases were compared and analyzed considering the materials used to understand the difference between aluminum and CFRP and their collision characteristics.