• Journal of Multimedia Information System
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• 제6권4호
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• pp.293-302
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• 2019

In the past, there was a theory that influenza wasn't transmitted directly from birds but was infected to humans via swains. Recently, molecular level research has progressed, and it was confirmed that the avian influenza virus can directly infected to human lung and intestinal epithelial cells. Three pandemicsin the past 100 years were also infected to humans directly from birds. In view of such scientific background, we are developing a method for screening sick birds by monitoring the physiological characteristics of birds in a contactless manner with sensors. Here, the movement of respiratory muscles and abdominal muscles under autonomic innervation was monitored using a magnet and Hall sensor sewn on the thoracic wall, and other multimedia devices. This paper presents and discusses the results of experiments involving continuous periodic noise discovered during flight experiments with a data logger mounted on a Japanese pheasant from 2012 to 2015. A brief summary is given as the below: 1. Magnet and Hall sensor sewn to the left and right chest walls, bipolar electrocardiograms between the thoracic walls, posterior thoracic air sac pressure, angular velocity sensors sewn on the back and hips, and optical reflection of LEDs (blue and green) from the skin of the hips allow observation of periodic vibrations(fasciculations) in the waves. No such analysis has been reported before. 2. These fasciculations are presumed to be derived from muscle to maintain and control air sac pressure. 3. Since each muscle fiber is spatially Gaussian distributed from the sympathetic nerve, the envelope is assumed to plot a Gaussian curve. 4. Since avian trunk muscles contract periodically at all time, we assume that the sympathetic nerve dominates in their control. 5. The technique of sewing a magnet to the thoracic wall and measuring the strength of the magnetic field with a Hall sensor can be applied to screen for early stage of avian influenza, with a sensor attached to the chicken enclosure.

• 한국항공우주학회지
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• 제42권3호
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• pp.229-236
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• 2014

본 논문에서는 유도형 활공 탄약의 유도 법칙 및 제어기에 대해서 연구하였다. 기존의 유도형 탄약은 활공 없이 목표물을 타격하기 위한 유도 단계만 있지만, 유도형 활공 탄약은 사거리 증가를 위한 날개를 장착하고 활공하기 때문에 활공 유도 단계가 추가 되어야 한다. 본 논문에서는 벡터필드를 이용하여 탄약의 진입각을 만족시키기 위한 경로점까지 유도하였고, 종말 유도에서는 목표물 타격을 위해 비례항법유도 기법을 적용하였다. 또한 각 활공 영역별로 운동 모델을 선형화하고 각각에 맞는 제어기를 설계한 후, 선형 보간법을 이용하여 제어기의 이득 값을 계산한 뒤 제어에 사용하였다.

• 한국항공우주학회지
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• 제43권3호
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• pp.224-231
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• 2015

람다 날개 형상의 공력 계수에 대한 실험적 연구를 국방과학연구소의 중형아음속 풍동에서 수행하였다. 본 연구의 주목적은 옆미끄럼각의 변화에 따라 다양한 공력 계수가 어떻게 변화하는지를 조사하는 것이다. 옆미끄럼각이 $0^{\circ}C$인 경우, 피칭 모멘트가 급격히 불안정해지는 현상을 확인하였으며, 옆미끄럼각이 증가함에 따라 pitch break 현상이 더 높은 받음각에서 발생하는 것을 확인하였다. 롤링 모멘트는 옆미끄럼각이 있는 경우 pitch break와 유사한 특성을 보여준다. 이런 경향은 옆미끄럼각이 증가할수록 더 심하게 나타났다. 요잉 모멘트는 높은 받음각에서 옆미끄럼각에 따라 기울기가 크게 변화하였고 불안정한 방향 안정성이 뚜렷이 나타났다. 모멘트의 이런 특성들은 비행 제어를 위해서는 보다 효과적인 조종성 증가 장치가 필수적이란 것을 의미하고 있다.

• 한국통신학회논문지
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• 제39C권11호
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• pp.1011-1022
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• 2014

현 공중노드의 무선네트워크 환경은 지상중계소 중심으로 구축되어 있는 반면에 한반도 환경여건은 전국토의 약 70% 정도가 산악지역으로 이루어져 있어 전파 음영지역(shadow zone)이 다수 존재하는 실정이다. 항공기가 중 저고도 임무 수행 도중 음영지역에 진입되어 통신 링크가 단절되지 않도록 효율적인 대응책 마련이 요구되고 있다. 따라서 본 논문에서는 Bezier Curve를 이용한 항공기 위치예측 및 음영지역 진입제어 방법을 제안한다. 제안된 방법은 항공기 이동경로 예측이 가능하여 음영지역 진입여부를 사전에 진단할 수 있으며 음영지역 진입 이전에 상황을 경고 전파하고 위험지역 이탈조치를 취하는 등 효율적인 제어가 가능하였다. 모의실험결과 제안된 방법은 항공기 위치예측 및 음영지역 진단이 용이하고 위험지역 진입 이전에 이탈조치 함으로써 항공작전 시 끊김 없는(seamless) 통신 지원이 가능한 것으로 나타나고 있다.

• 한국항공우주학회지
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• 제45권5호
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• pp.393-400
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• 2017

본 논문에서는 회전익 무인항공기의 조종성 평가를 수행하기 위한 가상모의시험용 프로그램을 MATLAB GUIDE(Graphic User Interface Development Environment)를 활용하여 개발하였다. ADS-33E에 기반을 둔 조종성 평가 프로그램은 비행제어시스템을 개발하고 조종성을 평가하는 데에 있어 시간과 비용을 경감시킬 수 있을 것으로 사료된다. 또한, Linear Quadratic Regulator(LQR)기반의 Linear Quadratic Tracker with Integrator(LQTI) 자세제어기를 BO-105C 회전익 항공기에 적용하여 조종성을 평가하고 Q와 R의 가중치에 따른 조종성에 대한 경향을 분석하였다.

• 한국항공우주학회지
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• 제33권2호
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• pp.84-91
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• 2005

오랜기간 비행선의 이착륙은 사람에 의한 수동으로 이루어졌으나, 자동제어시스템의 개발과 함께 이를 비행선에 적용하여 보다 정확한 이착륙의 필요성이 대두되었으며, 많은 알고리즘이 개발되고 있다. 본 논문에서는 기낭의 압력제어에 의한 비행선의 이착륙제어를 다룬다. 비행선의 운동방정식은 비선형 방정식으로 매우 복잡하여 우선 간단한 PID제어기에 의한 해법을 제시하였다. 그러나, 운항시 대기조건이 빠르게 변하므로 변하는 예측 불가능한 외란에 대해서는 만족스런 성능을 보이지 못하였다. 따라서, 본지에서는 인공 신경망을 이용한 학습알고리즘을 토대로 원하는 궤적에 빠르게 추종하도록 설계하였다. 일반적으로 인공신경망은 복잡한 문제에 있어서 많은 수의 은닉층과 뉴런이 필요하고 또한 훈련시간이 많이 걸리는 단점이 있기에 이를 해결하기 위해 비행선 이착륙 문제에 대한 일반적인 인공신경망 적용에 대해 연구하였다. 본지에서는 RBFN(radial basis function network)제어기를 설계하였고, 신경 회로망의 가중치는 외란이 인가되거나 부하특성이 비선형적으로 변화되는 것을 고려하도록 기준입력과 실제 비행선 모델의 출력사이의 오차를 최소화하는 방향으로 학습을 진행하였다. 그 결과 최대 15m의 오차를 보이는 PID제어기보다 양호한 결과를 얻었다.

• 한국군사과학기술학회지
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• 제18권3호
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• pp.213-219
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• 2015

Piezoelectric-based hydraulic actuator is a hybrid device consisting of a hydraulic pump driven by piezoelectric stacks that is coupled to a conventional hydraulic cylinder via a set of fast-acting valves. Nowadays, such hybrid actuators are being researched and developed actively in many developed countries by requirement of high performance and compact flight system. In this research, a piezoelectric hybrid actuator has been designed and tested. To achieve bi-directional capabilities in the actuator, solenoid valves were used to control the direction of output fluid. The experimental testing of the actuator in uni-directional and bi-directional modes was performed to examine performance issues related to the solenoid valves. The results showed that the bi-directional performance was slightly lower than uni-directional performance due to air bubble developed in the valve system. A new design to solve the vacuum problem has been proposed to improve the performance of the hybrid actuator.

• 항공우주정책ㆍ법학회지
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• 제12권
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• pp.210-245
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• 2000

This study is to review the problem concerned with aviation safety in Korea and suggest the solution to secure the aviation safety, in respect of regulation. At first, the definition and characteristics of aviation safety are studied, and then the endeavor for the aviation safety of ICAO and FAA are reviewed. All the fields of aviation safety area are included in the scope of this study; airworthiness in aircraft production and maintenance, flight operation, airport operation and air traffic control. The level of safety can be estimated by the frequency of accidents and seriousness. The causes of air accidents can be summarized as five factors; human factor, traffic environment. aircraft, weather, and unexpected incident. The activities to protect accidents are also can be summarized as five areas; man, machine, medium, mission and management. ICAO established the standards and recommends for the aviation safety, and adopted strategic action plan for 21st century. Federal Aviation Administration of USA also contributes for the aviation safety of world wide. Nowadays, ICAO and FAA tries to coordinate each other to set up efficient and effective ways for the aviation safety. ICAO developed safety oversight manual and FAA developed model regulations, individually. However, there has been trials to merge the results of each institute's studies. The direction of this endeavor is to meet the new environment related to globalization of air transport industry. It is necessary for our government to improve the aviation safety regulation system to address the new wave of aviation safety system pursued by international organization. A systematic and comprehensive measure should be devised by cooperation of all the related field and area.

• 한국항공운항학회지
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• 제21권4호
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• pp.119-125
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• 2013

Since year 2001 to the present time, the aircraft accidents and serious incidents in our country have surpassed 150 occurrences. The Boeing has published the statistical summary of commercial jet airplane accidents annually for the past 10 years on the basis of the occurrence categories defined by the CICTT(CAST/ICAO Common Taxonomy Team), and the number of occurrences is in order of loss of control(LOC-I), controlled flight into terrain(CFIT) and runway excursion (RE). Like the NTSB and the EASA, when fatal and non-fatal accidents are aggregated, though fatality rate is low, abnormal runway contact(ARC), system/component failure(SCF-PP/NP), ground handling(RAMP) rank high in the CICTT occurrence categories. With the less occurrence frequency, it is difficult to statistically analyze the aircraft accidents in our country, thus customarily the accidents and the serious incidents on aggregate are consolidated, and the statistical analysis is performed. This study categorizes the accidents and serious incidents to the domestic transportation aircraft in the past 10 years according to the CICTT occurrence categories, that is compared with foreign practices, and the implications have been discussed. From years 2001 through 2010, the accidents to the domestic transportation aircraft occurred in order of system failure(SCF-NP), ARC and power plant failure(SCF-PP), and when the accidents and the serious incidents are consolidated and analyzed, it is verified that a distribution appears similar to the European accident occurrence categories defined from 300 accident occurrence data.

• International Journal of Aeronautical and Space Sciences
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• 제16권4호
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• pp.520-528
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• 2015

The piezoelectric-hydraulic actuator is a hybrid device that consists of a hydraulic pump driven by a piezo-stack coupled to a conventional hydraulic cylinder. The actuator is of compact size, but can produce a moderate energy output. Such hybrid actuators are currently being researched and developed in many industrialized countries due to the requirement for high performance and compact flight systems. In a previous study, we designed and manufactured a unidirectional hybrid actuator. However, the blocking force was not as high as expected. Therefore, in this study, we redesigned the pump chamber and hydraulic cylinder and also improved the system by removing the air bubbles. Two different types of piezo-stacks were used. In order to achieve bidirectional capabilities in the actuator, commercial solenoid valves were used to control the direction of the output cylinder. Experimental testing of the actuator in unidirectional and bidirectional modes was performed to examine performance issues related to driving frequency, bias pressure, reed valve thickness, etc. The results showed that the maximum blocking force was measured as 970.2N when the frequency was 185Hz.