• 한국항공우주학회지
• /
• 제48권9호
• /
• pp.691-701
• /
• 2020

본 논문은 전기 추진 수직이착륙 무인기의 형상에 적합하도록 회전익 모드에서 추진시스템이 고장난 상황을 대처하기 위한 컨벡스 최적화 기법 기반의 믹서를 제시한다. 각 모터 및 프로펠러의 고장 영향성을 분석하기 위하여 컨벡스 함수 성질을 이용하여 가용 조종력 집합을 계산하였으며 이를 도시하는 방법을 기술하였다. 조종력 할당을 최적화 문제로 정의하고, 실시간으로 최적해를 구하기 위하여 컨벡스 함수로 문제를 재정의하였다. 컨벡스 최적화 솔버를 사용하여 수직 이착륙 비행 모드의 믹서를 구현하였으며 조종력 할당 기법들의 성능을 가용 조종력 범위 집합으로 비교하였다. 최종적으로 비선형 6자유도 시뮬레이션을 통하여 타기법(의사역행렬 기법, 재분배의사역행렬 기법)과 비교 분석하였다.

• Journal of Chest Surgery
• /
• 제25권3호
• /
• pp.220-231
• /
• 1992

We have performed 28 single lung transplantation in mongrel dogs transplanting the left lung exclusively from November 1989 to September 1991, in the department of thoracic surgery of Seoul National University Hospital. In the donor dogs, the main pulmonary artery was divided proximal to its bifurcation, and the left atrium was incised freeing the left veins with a generous atrial cuff. We used cold saline in the first 7 transplantations and Euro-Collins or modified Euro-Collins solution in the remaining 17 transplantations as a lung preservatives. The bronchus was divided at two cartilage rings proximal to the upper lobe bronchus take off. In the recipient procedure, we used a Fogarty catheter as a bronchus block. Left atrial anastomosis was performed first using 5-O prolene and the pulmonary artery was anastomosed using 6-O prolene. The bronchus was anastomosed next with 4-O vicryl interruptedly and covered with a greater omentum which had been prepared previously. All dogs received cyclosporin A and azathioprine as immunosuppressants and were divided into two group. In the 10 Group I dogs, they survived within 6 days, mean survival time was 66.8$\pm$53.4 hours. In remainder 14 Group lI dogs, they survived above 6 days, mean survival time was 9. 5$\pm$5.6 days. The cause of death were as follows: 2 cases of sacrifice, 2 cases of respiratory insufficiency during operation, 2 cases of arrhythmia immediate postoperatively, 2 cases of bleeding, others in Group I, and 6 cases of sacrifice, 4 cases of sepsis, 3 cases of bleeding, others in Group lI. Results of bronchoscopic findings were obstruction above 50% in 12 cases of 16 performance cases within 5th day. Early chest radiologic haziness were showed, and total lung perfusion defect was frequently showed in both group within 7th day. Main autopsy findings were left atrial and pulmonary arterial thrombi and bronchial obstruction The major histologic findings of Group I were pleural exudate, hemorrhagic infarct, pulmonary congestion, and interesting histologic findings of Group II were 3 cases of perivascular or peribronchial lymphocyte infiltration, 3 cases of hemorrhage infarct, 2 cases of interstitial pneumonitis. The structual change of bronchioles, suggesting bronchiolitis obliterans was not observed due to improper preparation of proximal pulmonary tissue and short term survival times.

• 한국항공운항학회지
• /
• 제15권4호
• /
• pp.9-16
• /
• 2007

Tilt rotor aircraft can take off and land vertically and cruise faster than any other helicopter. A scaled flight demonstration model of a tilt rotor aircraft has been developed by KARI. Because the flight characteristics of tilt rotor are not well known, the developed scaled model would be helpful to evaluate flight control algorithm of a full scale aircraft. The tethered hover test has been performed in order to improve hover flight characteristics of tilt rotor aircraft prior to flight test of the small scaled model. During the tethered hover test, the performance of rotor speed governor, rate SAS (Stability Augmentation System) and control surface mixers have been evaluated. We expect that the results of real flight hover test would be quite same as tethered hover test. Therefore the tethered hover test results will reduce the risk of flight test properly by fixing some of hidden problems which might occur during the flight test. This paper presents the results of tethered hover test in detail and shows how it could be final ground test before flight test. The control mixer gain and rate SAS feedback gains were modified in order to get higher controllability and stability during the tethered hover flight. The rotor governor showed that it could keep rotor RPM constant with very small deviation even during severe pilot collective input change. The tethered hover test results gave pilot and engineers confirmation and experience about the scheduled flight test.

• Journal of Biosystems Engineering
• /
• 제39권4호
• /
• pp.274-282
• /
• 2014

Purpose: In this study, a hybrid power system was developed for agricultural machines with a 20-KW output capacity, and it was attached to a multi-purpose cultivator to improve the performance of the cultivator, which was evaluated using output tests. Methods: The hybrid system combined heterogeneous sources: an internal-combustion engine and an electric power motor. In addition, a power splitter was developed to simplify the power transmission structure. The cultivator using the hybrid system was designed to have increased fuel efficiency and output power and reduced exhaust gas emissions, while maintaining the functions of existing cultivators. Results: The fuel consumption for driving the cultivator in the hybrid engine vehicle (HEV) mode was 341 g/KWh, which was 36% less than the consumption in the engine (ENG) mode for the same load. The maximum power take off output of the hybrid power system was 12.7 KW, which was 38% more than the output of the internal-combustion engine. In the HEV mode, harmful exhaust gas emissions were reduced; i.e., CO emissions were reduced by 36~41% and NOx emissions were reduced by 27~51% compared to the corresponding emissions in the ENG mode. Conclusions: The hybrid power system improved the fuel efficiency and reduced exhaust gas emissions in agricultural machinery. Lower exhaust gas emissions of the hybrid system have considerable advantages in closed work environments such as crop production facilities; therefore, agricultural machinery with less exhaust gas emissions should be commercialized. However, the high manufacturing cost and complexity of the proposed system are challenges which need to be solved in the future.

• 한국정보과학회논문지:소프트웨어및응용
• /
• 제32권8호
• /
• pp.819-833
• /
• 2005

하나의 instruction으로 여러 메모리 블록을 읽거나 쓰는 MLS(Multiple Load/store) 명령어를 사용하면 전체 코드에서 메모리 명령어의 수를 최소화해서 코드 사이즈를 축소할 수 있다. 이러한 장점 때문에 많은 마이크로 프로세서에서 이 명령어를 지원하고 있으나 현재까지 개발되어 있는 컴파일러들은 MLS 명령어의 장점을 효과적으로 이용하고 있지 못하고 있고 오직 제한적인 용도로 MLS 명령어를 사용하고 있다. 기존의 컴파일러에서 MLS 명령어를 효율적으로 지원하지 못하는 것은 일반적으로 MLS 명령어를 효과적으로 이용하기 위해서 해결해야 할 문제가 NP-hard의 범주에 속하기 때문이다. 이것은 stack frame에서 변수들에 대한 최적의 메모리 옵셋을 찾는 문제와 레지스터 할당에 관련된 복합적인 문제이다. 본 논문에서는 heuristic 기법을 효율적으로 이용하여 위에 언급된 문제를 polynomial time bound에 해결할 수 있는 기법을 제안한다.

• 한국항공우주학회지
• /
• 제45권9호
• /
• pp.711-723
• /
• 2017

본 연구에서는 재형상 특성을 지닌 유기적 비행 어레이의 비행 제어 시스템 설계에 대한 내용을 제안하였다. 단일 덕티드팬의 결합과 분리를 기반으로 구성되는 유기적 비행어레이는 주어진 임무나 주변 상황에 대해 유기적으로 어레이 형상을 변화시킬 수 있는 장점을 가진다. 이와 더불어 덕티드팬 비행체 기반이기 때문에 호버링이 가능하여 실내 정찰, 통신 중계, 레이더 재밍과 같은 미션에 유용하게 사용 된다. 비행 어레이의 동역학모델링은 단일 덕티드팬 비행체의 동역학 모델을 기반으로 구성되며, 비선형 제어기법을 적용하기 위해 어파인 형태의 동역학 식에 대한 유도를 수행한다. 비행체 자세 제어를 위해 Backstepping 제어기법을 적용하였으며 PID 제어기법을 통해 위치 제어 루프를 구현한다. 또한 수치 시뮬레이션을 통해 제안 된 제어기가 주어진 상황에서 충분한 성능을 보이는지를 검증하였다.

• Journal of Advanced Marine Engineering and Technology
• /
• 제31권6호
• /
• pp.753-760
• /
• 2007

For protection of the cylinder wall of the ball mill for grinding raw ore. the inner side of the cylinder is covered with rubber liner. The rubber is easily worn down because the rubber relatively soft compared with raw ore. So the rubber liner in the ball mill cylinder must be replaced almost every year and the cost for replacing rubber liner formidable. In this paper, for reducing or excluding the cost of replacing rubber liner the basalt liner is designed. The basalt materials are generally harder than raw ore and the basalt liner in the ball mill does not wear down and so it can be used almost permanently. The concave surfaces are made on the liner of the ball mill and the liner in the cylinder wall plays also the role of raising the steel balls mixed in the raw ore. The section profiles of the concave surface have an important effect on the performance of the ball mill. The deep concave grooves raise the steel balls to high levels and give the large potential energy to the steel balls impacting to the raw ore. But if the concave grooves are too deep. the steel balls raised too high by the concave grooves fly along the parabolic path and reach to the other side of cylinder wall and so the steel balls do not play the roles of grinding the raw ore. The forces acting to a steel ball in a concave groove of the cylinder liner are also analyzed in this paper. The formulas calculating the height and the impact point of the steel ball are introduced and presented. Based to these formulas, the optimum section profiles of the basalt liner are presented.

• 제어로봇시스템학회논문지
• /
• 제21권5호
• /
• pp.447-452
• /
• 2015

A hybrid power system was developed for agricultural machines with a 20kW output capacity, and it was attached to a multi-purpose cultivator to improve the performance of the cultivator. The hybrid system combined heterogeneous sources: an internal-combustion engine and an electric power motor. In addition, a power splitter was developed to simplify the power transmission structure. The cultivator using a hybrid system was designed to have increased fuel efficiency and output power and reduced exhaust gas emissions, while maintaining the functions of existing cultivators. The fuel consumption for driving the cultivator in the hybrid engine vehicle (HEV) mode was 341g/kWh, which was 36% less than the consumption in the engine (ENG) mode for the same load. The maximum power take off output of the hybrid power system was 12.7kW, which was 38% more than the output of the internal-combustion engine. In the HEV mode, harmful exhaust gas emissions were reduced; i.e., CO emissions were reduced by 36~41% and NOx emissions were reduced by 27~51% compared to the corresponding emissions in the ENG mode. The hybrid power system improved the fuel efficiency and reduced exhaust gas emissions in agricultural machinery. The hybrid system's lower exhaust gas emissions have considerable advantages in closed work environments such as crop production facilities. Therefore, agricultural machinery with less exhaust gas emissions should be commercialized.

• 항공우주시스템공학회지
• /
• 제11권1호
• /
• pp.14-21
• /
• 2017

매우 큰 정안정성($C_{L{\alpha}}$)을 갖는 틸트덕트 운동모델에 대해 선형 파라미터를 갖는 Sigma-Pi 신경망(SPNN) 제어법칙을 적용하였다. 기존의 비례적분미분(PID) 제어기는 매우 큰 정안정성을 갖는 운동모델이 갖는 강한 기수숙임 문제를 해결하기 어려웠고 이로인해 제어성능을 높일 수 없었다. 이와 달리 외부루프와 내부루프에 모두 적용된 SPNN 제어기는 동역학역변환 및 모델오차를 줄일 수 있는 의사적응제어 명령을 이용해서 과도한 안정성을 개선할 수 있었다. 이를 검증하기 위해서 경로점 추종 시뮬레이션을 이용해서 PID제어 성능과 SPNN제어 성능을 비교하였다.

• 한국수소및신에너지학회논문집
• /
• 제23권4호
• /
• pp.300-309
• /
• 2012

Long endurance is a key issue in the application of unmanned aerial vehicles. This study presents feasibility test results when fuel cell system as an alternative to the conventional engine is applied for the power of the UAV after the 150W fuel cell system is developed and packaged to the 1/4 scale super cub airplane. Fuel cell system is operated by dead-end method in the anode part and periodically purged to remove the water droplet in flow field during the operation. Oxygen in the air is supplied to the stack by the two air blowers. And fuel cell stack is water cooled by cooling circuit to dissipate the heat generated during the fuel cell operation. Weight balance is considered to integrate the stack and balance of plant (BOP) in package layout. In flight performance test, we demonstrated 4 times standalone take-off and landing. In the laboratory test simulating the flight condition to quantify the energy flow, the system is analyzed in detail. Sankey diagram shows that electric efficiency of the fuel cell system is 39.2%, heat loss 50.1%, parasitic loss 8.96%, and unreacted purged gas 1.67%, respectively compared to the total hydrogen input energy. Feasibility test results show that fuel cell system is high efficient and appropriate for the power of UAV.