• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2001년도 춘계학술대회논문집
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• pp.96-102
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• 2001

High intensity vibro-acoustic testing is the appropriate method for flight qualification testing of space flight vehicle which must ensure the acoustic environment of launch. Growing demand for satellites and launch vehicles in korea has resulted in a recent increase in the demand for high intensity vibro-acoustic test facility. The test facility is designed to provide an acoustic environment of 152 ㏈( re 20 ${\mu}$Pa) overall sound pressure level over the band width of 30 Hz to 10,000 Hz in the reverberant chamber. The reverberant chamber has a volume of 1,000 ㎥ with interior dimensions of 8.7m${\times}$l0m${\times}$12m, which can accommodate not only satellites but also launch vehicle payload fairing. Korea Aerospace Research Institute and Korean industries have been carrying out the development of the reverberant chamber and auxiliary devices, such as automatic control system, monitoring/safety device, and jet nozzle, etc. This paper presents the detailed description of High Intensity Acoustic Chamber of KARI, which will be the first and unique testing facility in Korea.

• 한국군사과학기술학회지
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• 제22권4호
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• pp.501-508
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• 2019

In this paper, a study on a wireless check-up method of test equipment for captive flight test(CFT) was conducted. For CFT, test equipment is mounted on a POD, and check-up is carried on the test equipment's. For check-up the POD wirelessly, battery, power distribution unit, wireless communication devices were designed within the POD, and a check-up device is designed outside of the POD. Once the external check-up device sends a 'start signal' to the POD, it performs the overall check-up procedures and transmits the 'end signal' to the external check-up device. Detailed check-up results are stored in an internal storage device, and are possible to read from external check-up device if necessary, thereby improving the reliability of the wireless check-up. By implementing and applying these wireless check-up system, the reliability of the check-up was enhanced by dynamical and movable check-up, and safety is guaranteed as the check-up was carried without access to the aircraft.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2005년도 추계학술발표대회 논문집
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• pp.179-184
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• 2005

In the present study, conceptual design of the main wing for 20 seats WIG{wing in Ground Effect) flight vehicle, which will be a high speed maritime transportation system for the next generation, was performed. The high stiffness and strength Carbon-Epoxy material was used for the major structure and the skin-spar with a foam sandwich structural type was adopted for improvement of lightness and structural stability. As a design procedure for this study, firstly the design load was estimated with maximum flight load, and then flanges of the front and the rear spar from major bending load and the skin structure and the webs of the spars were preliminarily sized using the netting rules and the rule of mixture. In order to investigate the structural safety and stability, stress analysis was performed by Finite Element Codes such as NASTRAN/PA TRAN[6] and NISA II [7]. From the stress analysis results, it was confirmed that the upper skin structure between the front spar and rear spar was very unstable for the buckling. Therefore in order to solve this problem, a middle spar and the foam sandwich structure at the upper skin and the web were added. After design modification, even thought the designed wing weight was a little bit heavier than the target wing weight, the structural safety and stability of the final design feature was confirmed. Moreover, in order to fix the wing structure at the fuselage, the insert bolt type structure with six high strength bolts was adopted for easy assembly and removal.

• 한국항행학회논문지
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• 제25권4호
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• pp.273-279
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• 2021

무인항공기에 적용되는 비행제어컴퓨터는 safety-critical 구성품으로, 내결함성을 확보함으로써 운용의 신뢰성을 높이기 위해 다중화 구조로 설계되고 있다. 이러한 다중화 구조가 적용된 비행제어컴퓨터는 각각의 독립적인 연산/제어 장치가 동일한 시점에 동일한 작업을 수행할 수 있도록 설계되어야 하며, 이를 위해 각 연산/제어 장치 간의 작업 동기화를 위한 동기화 알고리즘이 포함되어야 한다. 본 논문에서는 무인기에 적용되는 이중화 비행제어컴퓨터간의 동기화를 위한 소프트웨어 설계 방법을 제안한다. 제안하는 동기화 방법은 고장률 감소를 위해 최소의 하드웨어 리소스만을 사용하여 동기화할 수 있도록 설계하였고, 동기화에 사용되는 하드웨어 타이머의 동작 방식을 고려하여 설계함으로써 타이머 동작에 따른 동기화 오차를 최소화 할 수 있도록 설계하였다.

• 한국항공운항학회지
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• 제25권4호
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• pp.124-129
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• 2017

Clouds are an important factor in aircraft flight. In particular, a significant impact on small aircraft flying at low altitude. Therefore, we have verified and characterized the low level cloud prediction data of the Unified Model(UM) - based Local Data Assimilation and Prediction System(LDAPS) operated by KMA in order to develop cloud forecasting service and contents important for safety of low-altitude aircraft flight. As a result of the low level cloud test for seven airports in Korea, a high correlation coefficient of 0.4 ~ 0.7 was obtained for 0-36 leading time. Also, we found that the prediction performance does not decrease as the lead time increases. Based on the results of this study, it is expected that model-based forecasting data for low-altitude aviation meteorology services can be produced.

• 항공우주시스템공학회지
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• 제6권2호
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• pp.28-34
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• 2012

Structural integrity evaluation is important item in the aircraft certification. Recently, it is designed for limit load, material weakness about fatigue and corrosion, damage by bird strike in flight to evaluate structural integrity of aircraft. And static/fatigue analysis are performed to secure structural integrity, it was verified by static and fatigue tests. To evaluate the structural integrity of small aircraft tail, structural integrity was calculated by the finite element analysis. In the present study, finite element analysis are performed to pick out load cases in flight occurrence, and secure margin of safety to evaluate structural integrity of KC-100 tail unit. The proprieties of finite element analysis results are compared with the static structure test results. The estimation process of structural integrity for small aircraft tail may help the design.

• 한국항공운항학회지
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• 제29권2호
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• pp.111-116
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• 2021

Normal Operation Safety Survey (NOSS) is a safety management tool used by air traffic control organizations to measure data related to threats and errors to proactively prevent accidents before they occur. NOSS was developed to be applied to the air traffic control field according to the concept of Line Operation Safety Audit (LOSA) conducted by airlines to reduce human errors in the cockpits. Safety management based on data is crucial for the prevention of control-related accidents, and the competency of observers for this is important for the successful implementation of NOSS. Based on LOSA implementation experiences and expert interviews, this paper introduces the international NOSS methods and discusses the key factors required for effective observation and the implementation methods and implications of NOSS observer training.

• 전기전자학회논문지
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• 제16권2호
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• pp.145-152
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• 2012

This paper is the Software Hazard Analysis (SWHA) which will study the managerial process and the technical methode and techniques inherent in the performance of software safety task within the Military Aircraft System Safety program. This SWHA identifies potential hazardous effects on the software intensive systems and provides a comprehensive and qualitative assessment of the software safety. The purpose of this paper is to identify safety critical functions of software in Military A/C. The identified software hazards associated with the design or function will be evaluated for risks and operational constraint to further improve the software design requirement, analysis and testing efforts for safety critical software. This common SWHA, the first time analysis in KOREA, was review all avionics OFP(Operational Flight Program), and focus only on software segments which are safety critical. This paper provides a important understanding between the customer and developer as to how the software safety for the Military A/C will be accomplished. It will also provide the current best solution which may as one consider the necessary step in establishing a credible and cost-effective software safety program.

• 한국경영과학회:학술대회논문집
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• 대한산업공학회/한국경영과학회 1994년도 춘계공동학술대회논문집; 창원대학교; 08월 09일 Apr. 1994
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• pp.587-595
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• 1994

The use of flight training simulators has been increased remarkably during the past 20 years stimulated by the benefit that simulators can contribute to safety and training efficiency. Simulators have incorporated higher and higher levels of reality to provide more realistic training. Now, however, users are beginning to question how such reality is enough. Especially, it has raised question about the need for a notion system in the aircraft simulator. To help answer this question, this report describes notion cue requirements and types of motion system, and finally presents the assessment of the effectiveness of three different notion system alternatives.

• 융합정보논문지
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• 제9권12호
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• pp.141-146
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• 2019

국내외의 여러 경제 분석에서도 드론 시장이 날로 성장할 것이라는 예측을 하고 있으며, 그중에서 완구 및 취미용 드론 시장의 성장이 점진적으로 확대가 될 것으로 예측되고있다. 시장의 성장으로 발생하는 경제적 순기능으로 드론의 기대가치는 높아져 가고 있으나, 관리 및 운용 미숙으로 발생하는 사고 또한 증가하고 있다. 완구용 드론의 성능 차이는 산업용 드론과 비교할 수 없을 정도로 낮지만, 일반 구매자는 그 성능의 여부를 알 수 없어 사용상에 사고를 유발할 수 있다. 본 연구에 사용된 완구용 드론은 KC와 CE 인증을 받고 국내에서 판매되고 있는 20종을 사용하였으며, 비행시간 및 조종 거리 측정에 사용되었다. 비행이 가능한 시간 범위는 최소 3분~최대 12분까지로 측정되었으며, 조종 가능한 거리는 최소 20m~최대 약 380m까지로 측정되었다. 따라서 완구용 드론의 전파출력에 대한 샘플링 검사를 통한 제품 안전성 확보가 필요하며, 한계 비행거리를 넘었을 때는 자동으로 고도를 낮추거나 호버링을 하는 알고리즘 탑재가 필요하다. 향후 연구 방향으로는 완구용 드론의 실제 고도 테스트와 충격량 테스트를 통한 완구용 드론의 안전기준 제정을 위한 자료 구축을 할 예정이다.