• 제목/요약/키워드: Flight Type

검색결과 400건 처리시간 0.024초

A Study on Longitudinal Phugoid Mode Affected by Application of Nonlinear Control Laws

  • Kim, Chong-Sup;Hur, Gi-Bong;Kim, Seung-Jun
    • International Journal of Aeronautical and Space Sciences
    • /
    • 제8권1호
    • /
    • pp.21-31
    • /
    • 2007
  • Relaxed Static Stability (RSS) concept has been applied to improve aerodynamic performance of modern version supersonic jet fighter aircraft. The T-50 advanced supersonic trainer employs the RSS concept in order to improve the aerodynamic performance. And the flight control system stabilizes the unstable aircraft and provides adequate handling qualities. The T-50 longitudinal control laws employ a proportional-plus-integral type controller based on a dynamic inversion method. The longitudinal dynamic modes consist of short period with high frequency and phugoid mode with low frequency. The design goal of longitudinal control law is optimization of short period damping ratio and frequency using Lower Order Equivalent System (LOES) complying the requirement of MIL-F-8785C. This paper addresses phugoid mode characteristics such as damping ratio and natural frequency that is affected by the nonlinear control laws such as angle of attack limiter, auto pitch attitude command system and autopilot of pitch attitude hold.

Part 23 급 항공기 엔진인증 비행시험 절차 조사 (Research of Part 23 Level Aircraft Engine Certificate Flight Test Procedure)

  • 류승현;박영훈;문희장
    • 한국항공운항학회지
    • /
    • 제25권1호
    • /
    • pp.35-39
    • /
    • 2017
  • The engine is the most significant and essential part of the aircraft. As a result, systematical handling in the aircraft development stage is required from engine design to implementation to the full-scale airframe. This survey demonstrates the procedures demanded by the KAS 23 Civil Aircraft to acquire the engine Type Certification and the flight test procedures for ensuring the operational stability. Surveys were conducted on domestic and international aircraft engine certifications, technical regulations and documentations related to the Means of Compliance for flight test development stage. In addition, organized reference items that should be considered for the certification of engine flight test procedures were reviewed based on the KC-100.

Development of Flight Control System and Troubleshooting on Flight Test of a Tilt-Rotor Unmanned Aerial Vehicle

  • Kang, Youngshin;Park, Bum-Jin;Cho, Am;Yoo, Chang-Sun;Koo, Sam-Ok;Tahk, Min-Jea
    • International Journal of Aeronautical and Space Sciences
    • /
    • 제17권1호
    • /
    • pp.120-131
    • /
    • 2016
  • The full results of troubleshooting process related to the flight control system of a tilt-rotor type UAV in the flight tests are described. Flight tests were conducted in helicopter, conversion, and airplane modes. The vehicle was flown using automatic functions, which include speed-hold, altitude-hold, heading-hold, guidance modes, as well as automatic take-off and landing. Many unexpected problems occurred during the envelope expansion tests which were mostly under those automatic functions. The anomalies in helicopter mode include vortex ring state (VRS), long delay in the automatic take-off, and the initial overshoot in the automatic landing. In contrast, the anomalies in conversion mode are untrimmed AOS oscillation and the calibration errors of the air data sensors. The problems of low damping in rotor speed and roll rate responses are found in airplane mode. Once all of the known problems had been solved, the vehicle in airplane mode gradually reached the maximum design speed of 440km/h at the operation altitude of 3km. This paper also presents a comprehensive detailing of the control systems of the tilt-rotor unmanned air vehicle (UAV).

다비행체 편대비행을 위한 유도법칙 및 시뮬레이션에 관한 연구 (A Study on Guidance Law Design and Simulation of Multiple UAV Formation Flying)

  • 노태수;전경언
    • 한국항공우주학회지
    • /
    • 제36권9호
    • /
    • pp.859-866
    • /
    • 2008
  • 본 논문에서는 다수 비행체의 편대 비행 시 상호 기하학적 관계 유지에 필요한 유도 법칙과 비선형 시뮬레이션 결과를 제시하였다. 편대 내의 각 비행체는 편대 Leader를 제외하고 모두 Leader와 Follower의 역할을 동시에 맡으며, Leader에 의한 명령은 모든 Follower에게 분배되고 따라서 편대를 이루는 모든 비행체들의 동시기동비행(Synchronized Flight)을 가능하게 한다. 편대 비행 유도 법칙은 가까운 미래 시각에 예상되는 기하학적 오차 그리고 Lyapunov 안정성 이론에 근거하여 도출하였고, 정찰과 감시 임무 예제에 관한 고정밀 비선형 시뮬레이션 결과를 통하여 제안된 유도 법칙의 성능을 검증하였다

비행시험을 통한 경비행기의 속도계 보정 (Airspeed Calibration of a Light Airplane via Flight Test)

  • 이정훈;류시융;이장호
    • 제어로봇시스템학회논문지
    • /
    • 제14권7호
    • /
    • pp.629-634
    • /
    • 2008
  • This paper presents the flight test procedure and the results for the airspeed indicator calibration of a light airplane the name of ChangGong-91, which is the first type certified aircraft from Korean Ministry of Construction and Transportation, as a part of the flight test validation to get the certification. The flight tests for airspeed position error calibrations are conducted using tower fly by method in order to calibrate swivel head testboom which is attached to the right wing tip of the airplane. Also system to system method is applied in order to calibrate the airspeed indicator of the cockpit. The flight test is conducted at the basis of the 'Korean Airworthiness Standard' which is the regulation of Korean Ministry of Construction and Transportation. The airspeed error range for the testboom and the airspeed indicator are determined to $-0.75{\sim}+0.75$ knot and to $-4.0{\sim}+2.0$ knots, respectively. The calibration results are applied to ChangGong-91 Flight Operation Manual.

Controlled-Flight-Into-Terrain 항공 사고 예방에 관한 연구 - 괌사고, 목포사고, 김해사고 중심으로 - (A Study on Prevention as result of Controlled-Flight-Into-Terrain Accident - Focusing on Guam accident, Mokpo accident, Gimhae accident)

  • 변순철;송병흠;임세훈
    • 한국항공운항학회지
    • /
    • 제16권1호
    • /
    • pp.18-28
    • /
    • 2008
  • The purpose of this study is leading to prevent the major causes of commercial-aviation fatalities about controlled-flight-into-terrain(CFIT) in approach-and-landing accidents. The paper of major analysis for controlled flight into terrain(CFIT) was Guam accident, Mokpo accident and Gimhae accident in commercial transport-aircraft accidents from 1993 through 2002. CFIT occurs when an airworthy aircraft under the control of the flight crew is flown unintentionally into terrain, obstacles or water, usually with no prior awareness by the crew. This type of accident can occur during most phases of flight, but CFIT is more common during the approach-and-landing phase. Ninety-five percent of the Guam accident, Mokpo accident, and Gimhae accident where weather was known involved IMC, fog, and rain. The paper believed that prevention for CFIT accident was education and training for flying crew and upgrade for equipment such as EGPWS, and need more research for professional organizations of airlines, and accomplishing precision approaches should be a high priority.

  • PDF

통합항법 성능 분석을 위한 고정익, 회전익 무인항공기의 비행 시나리오 궤적 설계 (Flight Scenario Trajectory Design of Fixed Wing and Rotary Wing UAV for Integrated Navigation Performance Analysis)

  • 원대한;오정환;강우성;엄송근;이동진;김도윤;한상혁
    • 한국항공운항학회지
    • /
    • 제30권1호
    • /
    • pp.38-43
    • /
    • 2022
  • As the use of unmanned aerial vehicles increases, in order to expand the operability of the unmanned aerial vehicle, it is essential to develop an unmanned aerial vehicle traffic management system, and to establish the system, it is necessary to analyze the integrated navigation performance of the unmanned aerial vehicle to be operated. Integrated navigation performance is affected by various factors such as the type of unmanned aerial vehicle, flight environment, and guidance law algorithm. In addition, since a large amount of flight data is required to obtain high-reliability analysis results, efficient and consistent flight scenarios are required. In this paper, a flight scenario that satisfies the requirements for integrated navigation performance analysis of rotary and fixed-wing unmanned aerial vehicles was designed and verified through flight experiments.

운항품질보증프로그램 이벤트 유형 및 심각도 우선순위 조사 (Event Type and Severity Priority Survey of Airline Flight Operation Quality Assurance(FOQA) Program)

  • 김진호;이상기;문우춘;정현진
    • 한국항공운항학회지
    • /
    • 제29권3호
    • /
    • pp.84-99
    • /
    • 2021
  • Flight data from operational quality assurance programs plays a significant role in identifying factors as one of the key data in the development of proactive and preventive aviation safety management technologies based on data. The list of events in the flight quality assurance program recommended by the FAA differs from the list set and managed by airlines themselves and is based on the frequency of occurrence rather than the severity of individual events. In this work, we compared the list of FOQA events presented by the FAA with the list of some domestic airlines. We also investigate the severity priorities of events for airline captains and conduct research on how to improve the operation of the operational quality assurance program.

정기항공사 소속 조종사의 비행경력에 따른 시계접근능력 차이 분석 : 비모수 통계검정을 포함하여 (A Difference Analysis on Visual Approach Accessibility of Airline Pilots Based on Flight Experience including Non-parametric Statistical Test)

  • 이근영;황재갑;장지승
    • 한국항행학회논문지
    • /
    • 제23권2호
    • /
    • pp.104-113
    • /
    • 2019
  • 본 연구는 정기항공사 소속 조종사들을 대상으로 그들의 비행경력과 운항능력에 대한 실증연구를 하였다. 첫째, 정기항공사 소속 조종사들의 비행경력(비행시간 및 기종)에 따른 운항능력의 차이를 분석하였다. 이를 통해 신규로 항공운송용 조종사로 진입하고자 하는 인력들에 대해 항공사가 기대하는 조종사의 운항능력의 수준을 검증할 수 있었다. 분석결과 기장의 경우 해당기종 비행시간이 500시간이든 1500시간이든 시계비행 운항심사 결과 간의 차이가 없는 것으로 나타났다. 부기장은 1,500시간 이상부터는 시계비행 운항심사 결과의 차이가 나타났다. 부기장은 기장과 달리 해당기종 비행시간을 많이 가질수록 안정적인 시계접근을 할 수 있음이 판명된 것이다. 기종특성과 관련하여 cable 또는 fly-by-wire 기종에 따라 기장 집단은 시계비행 운항능력의 차이가없었다. 즉, 시계접근의 경우는 기종에 관계없이 기장급 조종사의 기량이 평가된다고 할 수 있겠다. 부기장집단에서는 기종 특성에 따른 유의한 차이가 있는 것으로 판명되었다.