• Title, Summary, Keyword: 비행경로

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Autonomous Aerobatic Flight for Fixed Wing Aircraft (고정익 항공기의 자율 곡예비행)

  • Park, Sang-Hyuk
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.37 no.12
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    • pp.1217-1224
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    • 2009
  • A simple and effective guidance and control scheme that enables autonomous three-dimensional path-following for a fixed wing aircraft is presented. The method utilizes the nonlinear path-following guidance law for the outer loop that creates steering acceleration command based on the desired flight path and the current position and velocity of the vehicle. The scheme considers the gravity in the guidance level, where it is subtracted from the acceleration command to form the specific force acceleration command which the aircraft is better suited to follow than the total acceleration command in the inner-loop. A roll attitude control scheme is also presented that enables inverted flight or sideslip maneuvers such as slow roll and knife-edge. A series of aerobatic maneuvers are demonstrated through simulations to show the potential of the proposed scheme.

무인항공기의 제어기술개발 동향

  • Gang, Yeong-Sin;Park, Beom-Jin;Yu, Chang-Seon
    • Current Industrial and Technological Trends in Aerospace
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    • v.4 no.2
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    • pp.55-67
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    • 2006
  • 20세기에 탄생한 동력비행기는 인간의 이동능력을 비약적으로 향상시켰다. 인류의 미개척지였던 항공분야의 발전은 지속적인 기술개발을 통해 더 빨리, 더 멀리, 더 높이 향하기 위해서 계속 나아가고 있다. 이러한와중에 최근에 괄목할 만한 성장을 이룬 컴퓨터와 소프트웨어 산업의 발전은 비행임무에 따라 위험성이 높거나, 사람이 하기 힘든 반복적이고 지루한 비행을 대신하기위한 로봇 비행체 즉, 무인항공기의 개발을 가능하게 하였다. 무인항공기의 탄생 초기에는 조종사의 희생을 줄이기 위해 군사 분야에서 주로 사용되었으나, 산림감시나 해안정찰, 기상관측, 재난관측, 조난자 수색 등 민수분야의 임무로 점차 활동영역이 넓혀지고 있다. 현재 무인항공기에 탑재된 인공지능의 수준은 안정된 비행이 가능하도록 하는 자동조종(autopilot)과 주어진 비행경로를 추종하기위한 항법유도(Navigation & Guidance)정도이며, 비행 중 발생하는 비상상황에 대처하기 위한 의사판단은 지상의 조종자에 의해 결정된다. 앞으로는 계획되지 않은 상황을 맞이했을 때 무인기 스스로 판단하여 경로를 변경하고, 동시에 여러 무인기들과 협력하여 임무를 수행함으로써 임무효율을 높이는 방향으로 인공지능의 수준이 향상될 것이다. 본 논문에서는 최근의 무인항공기 개발추세와 이들 무인기에 고려되고 있는 제어기에 대해 살펴보고, 향후 무인항공기에 적용될 자율비행 알고리듬과 제어기 시스템의 개발동향에 대해 고찰하였다.

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A Study on the Safe Separation of En-route Airway under altitude of 500 ft for the Flight Safety of Small UAVs (소형무인기 저고도 안전 비행을 위한 순항 경로 분리 간격 고찰)

  • Bae, Jung-Won;Lee, Sang-Jeong
    • 한국항공운항학회:학술대회논문집
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    • pp.39-47
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    • 2016
  • 150미터(500피트) 이하의 공역에서 무인기 택배 등의 활용을 목적으로 고속 비행이 요구되는 소형무인기(드론)의 순항을 가정하여 안전 분리 간격을 고려한 고속 비행 공역을 제안하고, 해당 경로에서 무인기간의 충돌방지를 위한 항법시스템의 성능요구조건과 안전한 분리 간격에 대한 선행 연구 분석과 고찰 결과를 제시한다.

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인공위성 편대비행의 최적 경로 산출을 위한 Parameter Optimization 기법 적용 연구

  • 임형철;박필호;박종욱;조정호;이우경
    • Bulletin of the Korean Space Science Society
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    • pp.58-58
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    • 2004
  • 인공위성 편대비행에서는 위성간 거리가 수 미터에서 수 킬로미터에 달하기 때문에 궤도 배치 및 재배치시 위성간 충돌의 문제는 매우 중요하다. 따라서 궤도 배치 및 재배치 단계에서 위성간 충돌을 피하고, 연료소모를 최소화시키면서 목적한 최종 배치를 만족시키는 최적경로를 산출하는 방법이 최근들어 연구되고 있다. 최적 경로를 산출하는 궤적 최적화 (Trajectory optimization) 문제를 풀기 위한 방법으로 크게 직접적인 (Direct) 방법과 간접적인 (Indirect) 방법이 있다. (중략)

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A Rendezvous Node Selection Scheme Considering a Drone's Trajectory for Reliable Data Collection (안정적인 데이터 수집을 위해 드론의 비행경로를 고려한 랑데부 노드 선정 기법)

  • Min, Hong;Jung, Jinman;Kim, Bongjae;Heo, Junyoung
    • KIISE Transactions on Computing Practices
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    • v.24 no.2
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    • pp.77-81
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    • 2018
  • Many studies that improve the efficiency of data collection and a network's lifetime by using a mobile sink have been conducted using wireless sensor networks. If a drone is used as a mobile sink, the drone can collect data more efficiently than can existing mobile sinks operating on the ground because the drone can minimize the effects of obstacles and the terrain. In this paper, we propose a rendezvous node selection scheme which considers estimated drone's trajectory and data collection latency of sensor networks for reliable data collection, when a drone whose trajectory is not predetermined works with terrestrial wireless sensor networks. A selected rendezvous node on the ground collects data from the entire network and it sends then collected data to the drone via direct communication. We also verify that the proposed scheme is more reliable than previous schemes without considering the drone's trajectory and data collection latency.

The Study on the Flight Route of Light Sport Aircraft in Yecheon TMA (예천TMA내 경량항공기 비행경로에 대한 연구)

  • Shin, Dai-Won;Shin, Hong-Chul
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.18 no.2
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    • pp.35-40
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    • 2010
  • In this study, we surveyed the operating status of the Light Sport Aircraft(LSA) in Korea, and reconstructed the flight route for Light Sport Aircraft in Yecheon TMA. Amended flight routes are LS095(Danyang Airpark $\Leftrightarrow$ Yeongju Airpark), LS096(Andong Airpark $\Leftrightarrow$ Yeongju Airpark), LS098(Yeongdeok Airpark $\Leftrightarrow$ Yeongju Airpark) and LS099(Yeongdeok Airpark $\Leftrightarrow$ Andong Airpark).

A Study on Autonomous Indoor Flight using Computer Vision System and Smartphone (컴퓨터비전과 스마트폰을 활용한 실내 자동비행체에 관한 연구)

  • Choi, Young;Kim, Kye-Young
    • KIPS Transactions on Software and Data Engineering
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    • v.2 no.5
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    • pp.353-358
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    • 2013
  • In this paper, we present an implementation of indoor flight to navigate to the designated places capable of hands-off autonomous operation within indoor environments. Our flight requires computer vision technique and smartphone device to allow it to be flown indoors without high-performance sensors which are too expensive to commercialization. The experimental result show that proposed implementation is fairly meaningful in a general building.

Waypoints Guidance of the Nonlinear Helicopter using the SDRE Technique (SDRE 기법을 이용한 비선형 헬리콥터의 비행 경로점 유도제어)

  • Kim, Min-Jae;Yang, Chang-Deok;Hong, Ji-Seung;Kim, Chang-Joo
    • Transactions of the Korean Society of Mechanical Engineers A
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    • v.33 no.9
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    • pp.922-929
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    • 2009
  • This paper deals with the State-Dependent Riccati Equation (SDRE) Technique for the design of helicopter nonlinear waypoint guidance controller. To generate the flight guidance through multiple waypoints, we use the trigonometric spline. The controller design and its validation is based upon a level 2 simulation helicopter model and the designed SDRE controller is applied to the trajectory tracking problems. To validate the designed SDRE controller, the simulation environment of high fidelity helicopter model is developed using three independent computers. This paper focuses on the validation the present SDRE controller through the helicopter waypoint guidance simulation.

Noise Analysis and Countermeasures of Training Aircraft(C172) According to Flight Course (비행경로에 따른 훈련용 항공기(C172)의 소음 분석 및 대책)

  • Jeon, Seung-Joon;Kim, Woo-Jin
    • The Journal of the Korea Contents Association
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    • v.18 no.6
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    • pp.235-242
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    • 2018
  • This study has been conducted for current situation of and countermeasures for aircraft noise. Aircraft noise is difficult to control, because of its wide-range effects, and it needs a great deal of funding for noise prevention like removal airport or land purchasing. And, in effort of determine whether aircraft noise can have health effects such as hearing loss, hypertension and psychological stress. This study, which uses of noise data around flight training airports in Korea, tries to understand and confirm related laws and regulations, and present civil application and situation of countermeasures. And, by measuring data of flight training airport, the situation of training aircraft noise problem have tried to confirm. To overcome these limitations and establish appropriate measures against noise, we made noise map with INM version 7.0, FAA aircraft noise prediction program, and evaluated aircraft noise. To overcome these limitations and establish appropriate measures against noise, we made noise map with INM version 7.0, FAA aircraft noise prediction program, and evaluated aircraft noise. In particular, the FAA's Integrated Noise Model(INM) is widely used by the civilian aviation community for evaluating aircraft noise impacts in the vicinity of airports. We analyzed noise impact by applying several scenarios. As these analysis, we suggest flight route without overlapping with residential area and without affecting flight safety.

Quantitative Analysis of Initial Dispersion Condition Effects on Randomness of Magnus Rotor Bomblet (Magnus Rotor 자탄의 초기 방출조건이 분산도에 미치는 영향에 대한 정량적 분석)

  • Bai, Ikhyun
    • Journal of the Korea Society for Simulation
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    • v.28 no.3
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    • pp.83-89
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    • 2019
  • This research describes quantitative effects of initial dispersion conditions upon the dispersion randomness of Magnus rotor bomblets. Ratios of the missile spin rate to the missile velocity, a, flight path angles, ${\gamma}$ and altitudes, h, were changed to investigate their effects on dispersion randomness. Dispersion was analyzed through calculation of 6 degree of freedom motion equation with aerodynamic coefficients from wind tunnel experiments. In order to analyze the randomness, regression analysis is adopted to calculate the coefficient of determination. The optimized ratio of the missile spin rate to the missile velocity and flight path angle were obtained and the dispersion altitudes had more effect on the dispersion diameter and had less effect on dispersion than other parameters.