• Title/Summary/Keyword: aircraft wing

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A Study on the Development of Helicopter Accident Prevention Program by Spatial Disorientation (비행착각에 의한 헬리콥터 사고 예방 프로그램 개발에 관한 연구)

  • Young-jin Cho
    • Journal of Advanced Navigation Technology
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    • v.27 no.1
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    • pp.8-15
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    • 2023
  • According to the results of a survey of pilots, 92% or 230 out of 252 respondents said they had experienced flight errors during flight. As so many pilots are experiencing Spatial Disorientation, and this is one of the main causes of aircraft accidents and loss of life, so it is important to understand accurately. However, in Korea, training equipment for fixed-wing pilots has already been developed and trained, or recently developed, and some equipment for helicopter pilots is available in the Korea Air Force, but there is no environment for helicopter pilots to receive training in Spatial Disorientation prevention. Therefore, we intend to produce a helicopter-only simulator, present a program to prevent possible Spatial Disorientation during flights for helicopter pilots, and propose legal and institutional measures based on future training data.

A Study on the Upset Prevention & Recovery Training Method for Navy Fixed Wing Pilots Using P-3 Simulator (P-3C 시뮬레이터를 활용한 해군 고정익조종사 UPRT 훈련 방안에 대한 연구)

  • Jung-bong Lee
    • Journal of Advanced Navigation Technology
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    • v.27 no.3
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    • pp.293-299
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    • 2023
  • UPRT(Upset Prevention And Recovery Training) is an accident prevention training program developed over a three-year period after the main cause of aircraft accidents in commercial aviation between 2001 and 2011 was analyzed as LOC-I(Loss Of Control Flight). In 2014, ICAO presented UPRT for fixed-wing aircraft through Doc.10011(Manual On Aeroplane Upset Prevention And Recovery Training) and recommended mandatory implementation to Contracting States from March 2019. Since naval P-3C is a major mission of maritime patrol and anti-submarine warfare, it takes a lot of time to fly at low altitude (70-600 m), and the majority of P-3C pilots have experienced spatial disorientation, so Upset prevention and recovery training is essential for naval P-3C pilots. To this end, this study intends to present measures for UPRT from limited conditions using the P-3C simulator owned by the Navy.

Fire Safety Analysis of Fire Suppression System for Aircraft Maintenance Hangar Using Fault Tree Method (Fault Tree를 활용한 항공기 격납고 소화시스템의 화재 안전성 분석)

  • Lee, Jong-Guk
    • Fire Science and Engineering
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    • v.31 no.6
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    • pp.67-73
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    • 2017
  • An aircraft maintenance hangar is a building that stores, maintains, and inspects expensive aircraft. The frequency of fire occurrence is low, but the resulting human and material damage can be very serious. Therefore, in this study, we conducted a qualitative analysis of the fire safety of the currently operating fire suppression systems for aircraft maintenance hangars using the Fault Tree method, and then performed a quantitative analysis using the failure rate data for the derived basic events and analyzed the importance of the minimal cut sets. As a result of the qualitative analysis by the minimal cut set, it was found that there were 14 accident paths that could be expanded to a large fire, due to the fire control failure of the aircraft hangar fire suppression system. The quantitative analysis revealed that, the probability of the fire expanding into a large one is $2.08{\times}E-05/day$. The analysis of the importance of the minimal cut set shows that four minimal cut sets, namely the fire detector and foam head action according to the zone and blocking of the foam by the aircraft wing and the fire plume, had the same likelihood of causing the fire to develop into a large one, viz. 24.95% each, which together forms the majority of the likelihood. It was confirmed for the first time by fault tree method that the fire suppression system of aircraft maintenance hangars is not suitable for fires under the aircraft wings and needs to be improved.

HPA Structure Design and Power Measurement (인간동력항공기 구조설계와 동력측정)

  • Lee, Chung-Ryul;Park, Ju-Won;Go, Eun-Su;Choi, Jong-Soo;Kim, In-Gul;Kim, Byoung-Soo
    • Aerospace Engineering and Technology
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    • v.12 no.2
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    • pp.209-220
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    • 2013
  • The process of designing and building a human-powered aircraft (HPA) and its performance analysis are introduced in this paper. Light Bros, the Chungnam National University HPA team, has developed Volante, a HPA, to compete in the 2012 exhibition of human-powered aircraft hosted by Korea Aerospace Research Institute. The power train system is composed of a two-blade propeller and Bevel-type gear and the ground test bed is built to simulate the operation. A study has been made to find a efficient propeller based upon the test result of thrust and power available from a pilot under various propeller conditions and running time. The load and structural analysis is conducted for the glider-shaped wing made of composite material which has very high aspect ratio. The spar is analyzed using finite element modeling followed by the comparison of its displacement and strain on structural test. As a result, the performance and safety is confirmed.

A Study on the Quality Improvement of Electrical Master Box in Aircraft Vibration Environment (항공기 진동 환경에서의 전원분배장치 품질개선 연구)

  • Seo, Youngjin;Lee, Yoonwoo;Jang, Minwook;Jo, Jihyung
    • Journal of the Korea Academia-Industrial cooperation Society
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    • v.20 no.8
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    • pp.181-189
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    • 2019
  • An aircraft power distribution device distributes and controls the power generated by the generator and provides overcurrent protection. There are many defect phenomena that make AC power distribution impossible during flight, which poses a problem in because some electronic equipment cannot be operated. We describe a process of deriving the root cause of defects by using vibration testing equipment to simulate the vibration conditions during aircraft flight, which result in defects. The results show that the cause of the defect is internal wiring damage caused by the vibration of the contactor of the AC power distribution device. Therefore, the shape of the contactor was improved to solve this problem. We also improved the test procedure by performing defect detection tests using vibration testing equipment to detect a faulty contactor. As a result of the improvements, a component certification test and flight test proved that the defect phenomena of the AC electrical master box were improved.

A Convergent Investigation on the Air Flow Analysis of a Light Aircraft Propeller (경비행기 프로펠러의 공기 유동해석에 관한 융합 연구)

  • Choi, Kye-Kwang;Cho, Jae-Ung
    • Journal of the Korea Convergence Society
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    • v.11 no.12
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    • pp.131-135
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    • 2020
  • In this study, the models with three, five and ten wings of the propeller which made a light aircraft fly were performed by air flow analyses. As for the flow model A with the shape with five wings, Model A can be seen to be the most ideal flow of air. The flow of air through the number of wings, which is not too many or too few, shows the most smooth flowing form. The smaller the number of propeller blades, the smaller the flow of air. Model A is applied under pressure of up to 0.5631 MPa at the front of air flow. Also, models B and C are applied under pressures of 0.5758 MPa and 0.5589 MPa, respectively. Comparing the pressure contours for each model of flux, model B can be shown to have the highest pressure distribution. The result of this study can be used to investigate the air flow without actual testing. It also seems to be helpful in the aesthetic convergent design of light aircraft propeller.

Design and Performance Test of Cooling-Air Test Equipment for the Environmental Control System in Aircraft (항공기 ECS 냉각공기 시험장비 설계 및 성능 시험)

  • So, Jae-uk;Kim, Jin-sung;Kim, Jae-woo;Kim, Jin-bok
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.49 no.2
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    • pp.147-154
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    • 2021
  • In this paper, the configuration and design of the test equipment are presented to examine the impact of rapid temperature change in cooling-air that may occur during the operation of the fixed wing aircraft Environmental Control System (ECS) on avionic electronic equipment. At the start of the ECS, the temperature of the air supplied by the aircraft ECS may be increased to 5.0℃ per second. In order to ensure operating of the avionic electronic equipment that is mounted on the aircraft and receives cooling-air from the ECS, testing equipment that can implement the cooling-air characteristic test environment is required. During design of test equipment was verified cooling-air rapid rate of temperature change by performing a thermal/flow analysis, performance of the test equipment implemented was verified by applying an avionic electronic equipment.

Verification of Winglet Effect and Economic Analysis Using Actual Flight of A321 Sharklet Model (A321 Sharklet 모델의 운항실적을 이용한 윙렛 장착 효과 검증 및 경제성 분석)

  • Jang, Sungwoo;Lee, Youngjae;Kim, Kangwook;Yoo, Jae Leame;Yoo, Kwang Eui
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.49 no.4
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    • pp.273-279
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    • 2021
  • Winglets are specialized wingtip devices to reduce induced drag, and they have been installed on Boeing-made aircraft since the 1980s, Airbus has also developed a winglet named 'Sharklet' since 2009 and has started providing them as an option to the A320 Family. The winglet has the effect of improving take-off performance, reducing fuel consumption, increasing payload, and increasing flight distance by reducing the induced drag generated at the tip of the wing. The purpose of this study is to analyze the actual flight data of the sharklet-installed and non-sharklet-installed models of the A321 aircraft to verify the fuel efficiency improvement due to the winglet installation, and to analyze the economic analysis accordingly. Through this, it can be used to determine the winglet installation when introducing an aircraft or to make a decision for upgrading the existing aircraft. To this end, a case study on the aerodynamic characteristics and effects of the winglet installation was conducted, and the economic analysis was verified.

Comparison of wind data for review of take-off and landing directions of UAM port (UAM Port의 이·착륙 방향 검토를 위한 바람 자료 비교)

  • Jaewoo Park;GeonHwan Park;HyeJin Hong;SungKwan Ku
    • Journal of Advanced Navigation Technology
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    • v.26 no.6
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    • pp.393-403
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    • 2022
  • Various studies suggest that the initial operating form of UAM, which is being presented as a solution to the urban traffic problem, will be similar to VTOL aircraft among current aircraft. In a form similar to determining the direction of the runway where fixed-wing aircraft take off and land, the vertiport where take-off and landing of VTOL aircraft takes place determines the flight direction of departure and arrival in consideration of the direction of the wind. Unlike areas where airports are generally built, in the case of downtown areas, it is expected that the characteristics of wind may continuously change depending on the environment of changing terrain or obstacles such as the construction of new buildings. In this study, long-term actual observation data for reviewing the take-off and landing directions at the city center where the location of the vertiport is expected are compared using a wind speed map, and the characteristics of the ground wind and the possibility of change in the direction of the predominant wind depending on the observation period and observation location confirmed.

Analysis of Cable Protection of Duct in Lightning and HIRF Environment of UAM Aircraft and a Proposal for Certification Guidance (UAM 항공기 낙뢰 및 HIRF 환경에서 덕트의 케이블 보호 성능 분석 및 인증기술에 관한 연구)

  • Kim, Dong-Hyeon;Jo, Jae-Hyeon;Kim, Yun-Gon;Lee, Hakjin;Myong, Rho-Shin
    • Journal of Aerospace System Engineering
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    • v.16 no.3
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    • pp.23-34
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    • 2022
  • Cities around the world are increasing their demand for Urban Air Mobility (UAM) aircraft due to traffic congestion with population concentration. Aircraft with various shapes depending on fixed-wing and propulsion systems, are being prepared for commercialization. Airworthiness certification is required as it is a manned transportation vehicle that flies in the city center and transports people on board. UAM aircraft are vulnerable to lightning and HIRF environments due to the increasing use of composite materials, the use of electric motors, and use of electronic equipment. Currently, the development of certification technology, guidelines, and requirements in lightning and HIRF environments for UAM aircraft is incomplete. In this study, the certification procedures for lightning and HIRF indirect impacts of rotorcraft shown in AC 20-136B and AC 20-158A issued by the Federal Aviation Administration (FAA), were verified and applied to the computerized simulation of UAM aircraft. The impact of lightning and HIRF on ducted fan UAM aircraft was analyzed through computerized simulation, and the basis for establishing practical guidelines for certification of UAM aircraft to be operated in the future is presented.