• 제목/요약/키워드: aircraft turbulence

검색결과 68건 처리시간 0.024초

항공 운항에서의 허용된 위험 법리에 대한 연구 (A Study of the "erlaubtes Risiko" in Aviation)

  • 함세훈
    • 항공우주정책ㆍ법학회지
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    • 제25권2호
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    • pp.201-230
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    • 2010
  • 자동차, 철도, 광산업이 시작되면서 등장한 새로운 위험에 대하여 사회적 유용성을 이유로 활성화된 세계를 유지하고자 출발한 허용된 법리에 대하여 우리나라의 학계에서는 다수가 인정하고 있는 분위기인데 반하여 판례에서는 아직까지 기존의 과실론 체계로 해석하고 있다. 그러나 첨단 과학기술영역의 하나인 항공 운항에 있어서 사건이나 사고의 원인이 되는 청천난류(CAT)나 요란(turbulence)을 갖고 있는 뇌우는 환자의 불안전한 예후처럼 실시간 완벽한 탐지가 곤란하고 위험 발현 여부와 크기를 확정할 수 없으며 수시로 변화하는 이상 기상 현상이다. 이러한 이유가 있음에도 청천난류(CAT)가 존재할 수 있는 jet 기류의 이용은 시간과 연료를 대폭 절감하고 치명적 위험으로 발현되지 않은 뇌우가 있는 공항으로의 접근 착륙은 승객들의 정시 출 도착을 보장하기에 사회적 유용성이 높은 운항 형태라고 할 수 있다. 위험이 예견되고 회피할 수 있는 방법이 있으나 사회적 유용성을 이유로 개연성이 낮은 청천난류(CAT)나 요란(turbulence) 위험 지역을 운항하다가 발생한 사건이나 사고에 대하여는 허용된 위험의 법리를 적용하여 조종사들의 일정한 주의의무에 대한 완화가 필요하다.

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항공기(航空機) 사고조사제도(事故調査制度)에 관한 연구(硏究) (A Study on the System of Aircraft Investigation)

  • 김두환
    • 항공우주정책ㆍ법학회지
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    • 제9권
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    • pp.85-143
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    • 1997
  • The main purpose of the investigation of an accident caused by aircraft is to be prevented the sudden and casual accidents caused by wilful misconduct and fault from pilots, air traffic controllers, hijack, trouble of engine and machinery of aircraft, turbulence during the bad weather, collision between birds and aircraft, near miss flight by aircrafts etc. It is not the purpose of this activity to apportion blame or liability for offender of aircraft accidents. Accidents to aircraft, especially those involving the general public and their property, are a matter of great concern to the aviation community. The system of international regulation exists to improve safety and minimize, as far as possible, the risk of accidents but when they do occur there is a web of systems and procedures to investigate and respond to them. I would like to trace the general line of regulation from an international source in the Chicago Convention of 1944. Article 26 of the Convention lays down the basic principle for the investigation of the aircraft accident. Where there has been an accident to an aircraft of a contracting state which occurs in the territory of another contracting state and which involves death or serious injury or indicates serious technical defect in the aircraft or air navigation facilities, the state in which the accident occurs must institute an inquiry into the circumstances of the accident. That inquiry will be in accordance, in so far as its law permits, with the procedure which may be recommended from time to time by the International Civil Aviation Organization ICAO). There are very general provisions but they state two essential principles: first, in certain circumstances there must be an investigation, and second, who is to be responsible for undertaking that investigation. The latter is an important point to establish otherwise there could be at least two states claiming jurisdiction on the inquiry. The Chicago Convention also provides that the state where the aircraft is registered is to be given the opportunity to appoint observers to be present at the inquiry and the state holding the inquiry must communicate the report and findings in the matter to that other state. It is worth noting that the Chicago Convention (Article 25) also makes provision for assisting aircraft in distress. Each contracting state undertakes to provide such measures of assistance to aircraft in distress in its territory as it may find practicable and to permit (subject to control by its own authorities) the owner of the aircraft or authorities of the state in which the aircraft is registered, to provide such measures of assistance as may be necessitated by circumstances. Significantly, the undertaking can only be given by contracting state but the duty to provide assistance is not limited to aircraft registered in another contracting state, but presumably any aircraft in distress in the territory of the contracting state. Finally, the Convention envisages further regulations (normally to be produced under the auspices of ICAO). In this case the Convention provides that each contracting state, when undertaking a search for missing aircraft, will collaborate in co-ordinated measures which may be recommended from time to time pursuant to the Convention. Since 1944 further international regulations relating to safety and investigation of accidents have been made, both pursuant to Chicago Convention and, in particular, through the vehicle of the ICAO which has, for example, set up an accident and reporting system. By requiring the reporting of certain accidents and incidents it is building up an information service for the benefit of member states. However, Chicago Convention provides that each contracting state undertakes collaborate in securing the highest practicable degree of uniformity in regulations, standards, procedures and organization in relation to aircraft, personnel, airways and auxiliary services in all matters in which such uniformity will facilitate and improve air navigation. To this end, ICAO is to adopt and amend from time to time, as may be necessary, international standards and recommended practices and procedures dealing with, among other things, aircraft in distress and investigation of accidents. Standards and Recommended Practices for Aircraft Accident Injuries were first adopted by the ICAO Council on 11 April 1951 pursuant to Article 37 of the Chicago Convention on International Civil Aviation and were designated as Annex 13 to the Convention. The Standards Recommended Practices were based on Recommendations of the Accident Investigation Division at its first Session in February 1946 which were further developed at the Second Session of the Division in February 1947. The 2nd Edition (1966), 3rd Edition, (1973), 4th Edition (1976), 5th Edition (1979), 6th Edition (1981), 7th Edition (1988), 8th Edition (1992) of the Annex 13 (Aircraft Accident and Incident Investigation) of the Chicago Convention was amended eight times by the ICAO Council since 1966. Annex 13 sets out in detail the international standards and recommended practices to be adopted by contracting states in dealing with a serious accident to an aircraft of a contracting state occurring in the territory of another contracting state, known as the state of occurrence. It provides, principally, that the state in which the aircraft is registered is to be given the opportunity to appoint an accredited representative to be present at the inquiry conducted by the state in which the serious aircraft accident occurs. Article 26 of the Chicago Convention does not indicate what the accredited representative is to do but Annex 13 amplifies his rights and duties. In particular, the accredited representative participates in the inquiry by visiting the scene of the accident, examining the wreckage, questioning witnesses, having full access to all relevant evidence, receiving copies of all pertinent documents and making submissions in respect of the various elements of the inquiry. The main shortcomings of the present system for aircraft accident investigation are that some contracting sates are not applying Annex 13 within its express terms, although they are contracting states. Further, and much more important in practice, there are many countries which apply the letter of Annex 13 in such a way as to sterilise its spirit. This appears to be due to a number of causes often found in combination. Firstly, the requirements of the local law and of the local procedures are interpreted and applied so as preclude a more efficient investigation under Annex 13 in favour of a legalistic and sterile interpretation of its terms. Sometimes this results from a distrust of the motives of persons and bodies wishing to participate or from commercial or related to matters of liability and bodies. These may be political, commercial or related to matters of liability and insurance. Secondly, there is said to be a conscious desire to conduct the investigation in some contracting states in such a way as to absolve from any possibility of blame the authorities or nationals, whether manufacturers, operators or air traffic controllers, of the country in which the inquiry is held. The EEC has also had an input into accidents and investigations. In particular, a directive was issued in December 1980 encouraging the uniformity of standards within the EEC by means of joint co-operation of accident investigation. The sharing of and assisting with technical facilities and information was considered an important means of achieving these goals. It has since been proposed that a European accident investigation committee should be set up by the EEC (Council Directive 80/1266 of 1 December 1980). After I would like to introduce the summary of the legislation examples and system for aircraft accidents investigation of the United States, the United Kingdom, Canada, Germany, The Netherlands, Sweden, Swiss, New Zealand and Japan, and I am going to mention the present system, regulations and aviation act for the aircraft accident investigation in Korea. Furthermore I would like to point out the shortcomings of the present system and regulations and aviation act for the aircraft accident investigation and then I will suggest my personal opinion on the new and dramatic innovation on the system for aircraft accident investigation in Korea. I propose that it is necessary and desirable for us to make a new legislation or to revise the existing aviation act in order to establish the standing and independent Committee of Aircraft Accident Investigation under the Korean Government.

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Design and Implementation of UAV's Autopilot Controller

  • Lee, Jeong-Hwan;Lee, Ki-Sung;Jeong, Tae-Won
    • 제어로봇시스템학회:학술대회논문집
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    • 제어로봇시스템학회 2004년도 ICCAS
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    • pp.52-56
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    • 2004
  • Unmanned Aerial Vehicles (UAVs) are remotely piloted or self-piloted aircraft by inputted program in advance or artificial intelligence. In this study Aileron and Elevator are used to control the movement of airplane for horizontal and vertical flights about its longitudinal and lateral axis. In an introduction, the drone was linearly modeled by extracting aerodynamic parameter through flight test and simulation, lift and drag coefficient corresponding to angle of attack, changes of pitching moment coefficient. In the main subject, the flight simulation was performed after constructing hardware using TMS320F2812 from TI company and PID with lateral and longitudinal controller for horizontal and vertical flights. Flying characteristics of two system were estimated and compared through real flight test with hardware equipped algorithm and adaptive algorithm that was applied to consider external factors such as turbulence. In conclusion the control performance of the controller with proposed algorithm was streamlined at lateral and longitudinal controller respectively, we will discuss guidance command to pass way point.

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Energy-efficient flow control around blunt bodies

  • Yurchenko, Nina F.
    • Advances in aircraft and spacecraft science
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    • 제1권1호
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    • pp.15-25
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    • 2014
  • The developed concept of smart flow control based on turbulence scale modification was applied to control a flow around a circular cylinder. The concept was realized using arrays of vortex-generators regularly spaced along a cylinder generatrix with a given step. Mechanical and thermal vortex-generators were tested, the latter having been based on the localized surface heating or plasma discharges initiated with microwave radiation near the surface. Thus depending on a particular engineering solution, flow transport properties could be modified in passive or active ways. Matched numerical and experimental investigations showed a possibility to delay flow separation and, accordingly, to improve the aerodynamic performance of blunt bodies.

전산해석을 이용한 고양력장치의 동특성 고찰 (Computational Study on Dynamic Characteristics of a Flapped Airfoil)

  • 이융교;김철완
    • 한국전산유체공학회:학술대회논문집
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    • 한국전산유체공학회 2011년 춘계학술대회논문집
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    • pp.206-209
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    • 2011
  • During landing approach, an airplane could experience dynamic unstable motion by the combination of a gust and elevator control to cancel the disturbances. This situation is dangerous and could lead to a loss of an airplane. In this paper, numerical analysis was used to study the effect of pitch oscillating 2-D high lift devices in a landing condition. Experimental data on a pitching naca0012 airfoil was used for code validation. Dynamic characteristics of an airfoil, single slotted flap for mid-class passenger aircraft were analyzed. Unsteady Navier-Stokes analysis was performed with Spalart-Allmaras turbulence model for separation dominant low speed flow. As a result, flow hysteresis of a flapped airfoil was more complex than that of an oscillating airfoil. So, dynamic analysis of a flap in a landing condition is very important for operational safety.

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Numerical investigation of detonation combustion wave propagation in pulse detonation combustor with nozzle

  • Debnath, Pinku;Pandey, K.M.
    • Advances in aircraft and spacecraft science
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    • 제7권3호
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    • pp.187-202
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    • 2020
  • The exhaust nozzle serves back pressure of Pulse detonation combustor, so combustion chamber gets sufficient pressure for propulsion. In this context recent researches are focused on influence of nozzle effect on single cycle detonation wave propagation and propulsion performance of PDE. The effects of various nozzles like convergent-divergent nozzle, convergent nozzle, divergent nozzle and without nozzle at exit section of detonation tubes were computationally investigated to seek the desired propulsion performance. Further the effect of divergent nozzle length and half angle on detonation wave structure was analyzed. The simulations have been done using Ansys 14 Fluent platform. The LES turbulence model was used to simulate the combustion wave reacting flows in combustor with standard wall function. From these numerical simulations among four acquaint nozzles the highest thrust augmentation could be attained in divergent nozzle geometry and detonation wave propagation velocity eventually reaches to 1830 m/s, which is near about C-J velocity. Smaller the divergent nozzle half angle has a significant effect on faster detonation wave propagation.

Reynolds stress correction by data assimilation methods with physical constraints

  • Thomas Philibert;Andrea Ferrero;Angelo Iollo;Francesco Larocca
    • Advances in aircraft and spacecraft science
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    • 제10권6호
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    • pp.521-543
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    • 2023
  • Reynolds-averaged Navier-Stokes (RANS) models are extensively employed in industrial settings for the purpose of simulating intricate fluid flows. However, these models are subject to certain limitations. Notably, disparities persist in the Reynolds stresses when comparing the RANS model with high-fidelity data obtained from Direct Numerical Simulation (DNS) or experimental measurements. In this work we propose an approach to mitigate these discrepancies while retaining the favorable attributes of the Menter Shear Stress Transport (SST) model, such as its significantly lower computational expense compared to DNS simulations. This strategy entails incorporating an explicit algebraic model and employing a neural network to correct the turbulent characteristic time. The imposition of realizability constraints is investigated through the introduction of penalization terms. The assimilated Reynolds stress model demonstrates good predictive performance in both in-sample and out-of-sample flow configurations. This suggests that the model can effectively capture the turbulent characteristics of the flow and produce physically realistic predictions.

GPS/IMU를 이용한 SAR 영상의 요동 보상 기법에 대한 연구 (SAR Motion Compensation Using GPS/IMU)

  • 김동현;박상홍;김경태
    • 한국전자파학회논문지
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    • 제22권1호
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    • pp.16-23
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    • 2011
  • 본 논문에서는 레이더 플랫폼의 요동에 의해서 흐려진 SAR(Synthetic Aperture Radar) 영상의 위상 오차를 보상하기 위하여 GPS(Global Positioning System)/IMU(Inertial Measurement Unit) 데이터를 이용한 요동 보상 기법을 소개한다. 실제 비행 궤적의 경우 대기의 왜란(turbulence)에 의한 항공기의 pitch, roll 및 yaw 운동에 의해 레이더의 플랫폼은 속도 변화가 생기고, 또한, 이상적인 궤적에서 벗어나게 된다. 이로 인한 along-track 속도 오차와 펄스간 위상 오차로 인해 SAR 영상은 흐려지게 된다. 요동 보상을 수행할 경우, 이러한 오차를 줄여서 영상의 품질을 개선할 수 있다. 시뮬레이션 결과, 레이더 플랫폼에 요동이 있을 경우 이 논문에서 소개한 요동 보상기법은 흐려진 SAR 영상의 품질을 개선하는데 효율적임을 알 수 있다.

무인항공기 자동조종장치의 강건성 해석에 관한 연구 (The Study of the Robustness Analysis of the autopilot for the UAV)

  • 임호;김기열;김호
    • 정보학연구
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    • 제4권3호
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    • pp.165-170
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    • 2001
  • 정보기술을 바탕으로 한 지도력의 역할은 지난 10년에 걸쳐서 많은 변화를 가져왔다. 이러한 변화에도 불구하고 최근에 정보기술이 지도력에 미치는 영향에 관한 경험적인 연구가 거의 되지 않고 있는 실정이다. 본 연구에서는 지도력에 있어서 정보를 제공하는 역할과 결정을 내릴 수 있는 역할 그리고 각 개인간의 역할과 같은 일반적인 지도력에 관련된 역할을 중심으로 하였다. 또한 직무의 특성별로 기획입안자, 직무 개선자, 연구개발 책임자, 마케팅 책임자, 관리자 및 운영 전략가 둥과 같은 분야에서 근무하고 있는 지도자들의 지도력에 미치는 영향을 조사하였다. 정보기술을 사용하는 정보시스템 관리자들은 개인간의 지도력의 역할범위에 따라 그 미치는 영향이 다를 수 있으며 정보시스템이 현재의 위치에서 시간이 지나매 따라 부정적인 영향을 미칠 수도 있지만 변화를 추구하는 지도자의 역할에 있어서는 시간이 흐름에 따라 정보기술 사용의 범위와 전략적 책임의 범위 및 기업과 조직의 수익에 지대한 영향을 미칠 것으로 사료된다. 비록 일반적인 지도력의 역할에 관해서는 그 중요성이 지금까지 연구한 바는 있지만 정보시스템 기술이 지도력에 미치는 영향에 관한 체계적인 연구는 아직 미흡하므로 이 분야에 대해서 연구 조사를 중심으로 하였다.

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터보프롭 항공기의 실속 특성 수치해석 (Numerical Analysis of Stall Characteristics for Turboprop Aircraft)

  • 박영민;정진덕
    • 항공우주기술
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    • 제11권2호
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    • pp.65-72
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    • 2012
  • 프로펠러와 고양력장치를 장착한 터보프롭 항공기에 대한 실속 특성 분석을 위해 수치 해석을 수행하였다. 항공기의 실속 특성은 프로펠러와 고양력 장치의 장착 조합에 따른 형상별 전산해석 결과를 통해 정성적으로 분석하였다. 실속 특성 해석은 Spalart-Allmaras 난류 모델을 기반으로 한 3차원 Navier-Stokes 방정식 해법을 이용하였으며 프로펠러의 회전은 슬라이딩 격자기법을 이용하여 모사하였다. 분석 결과 순항 형상의 경우 동체/날개 페어링에서 주요 유동박리가 발생하며 프로펠러 후류로 인해 점차 감소함을 알 수 있었다. 고양력장치를 장착한 경우 나셀 바깥쪽에서 주요 유동박리 현상이 발생하였고 프로펠러가 회전하는 경우에도 상대속도 감소와 유효 받음각 증가로 나셀 바깥쪽 날개 부분은 조기에 실속에 잠김을 알 수 있었다. 프로펠러는 날개의 inboard에서 하강하는 회전 방향이 프로펠러 후류로 인한 실속 지연 측면에서 유리함을 알 수 있었다.