• Title, Summary, Keyword: 비행경로

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Optimization of the Flapping Motion for the High Maneuverability Flight (기동성 비행을 위한 날갯짓 경로의 최적화)

  • Choi, Jung-Sun;Kim, Jae-Woong;Lee, Do-Hyung;Park, Gyung-Jin
    • Transactions of the Korean Society of Mechanical Engineers A
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    • v.36 no.6
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    • pp.653-663
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    • 2012
  • The study considers the high maneuverability flight and path optimization is conducted to investigate the appropriate generation of the lift and thrust considering the angle of the stroke plane. The path optimization problem is defined according to the various purposes of the high maneuverability flight. The flying purposes are to maximize thrust force, lift force and both lift and thrust forces. The flapping motion of the airfoil is made by a combined sinusoidal plunging and pitching motion in each problem. The optimization process is carried out by using well-defined surrogate models. The surrogate model is determined by the results of two-dimensional computational fluid dynamics analysis. The Kriging method is used to make the surrogate model and a genetic algorithm is utilized to optimize the surrogate model. The optimization results show the flapping motions for the high maneuverable flight. The effects on the generation of lift and thrust forces are confirmed by analyzing the vortex.

Waypoints Altitude Planning for Terrain Collision Avoidance and Maneuverability of an Unmanned Aerial Vehicle (지형 충돌 회피 및 기동성을 고려한 무인기 경로점 고도계획)

  • Lim, In-Geun;Ra, Sung-Woong
    • 한국정보기술학회논문지
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    • v.16 no.9
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    • pp.31-41
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    • 2018
  • We propose a method to plan the waypoints altitude so that the unmanned aerial vehicle can fly without collision with the terrain, fly at a given altitude in a specific mission performance section, and fly as close to the terrain as possible in the case of no altitude condition. Conventionally, the planner mainly used the method of manually designating the altitude of each of the waypoints, but it has a disadvantage that the results are different each time and it takes a lot of time. Recently, an automatic altitude planning method has been proposed, but it is a planning to fly a long distance at a high altitude to prevent terrain collision. Therefore, it is not suitable for performing missions where low altitude flight is required. We check the possibility of terrain collision by comparing the terrain elevation with the expected flight altitude in a segmentation. If there is a risk of terrain collision, adjust the waypoint altitude value in different ways according to the seven cases to raise the altitude only for the minium interval. The range of elevation or descent altitude was calculated by the distance of the front and rear waypoints. The waypoint altitude is finally determined by taking into account the altitude of the terrain as well as the maneuverability of the UAV.

Backward Path Following Under a Strong Headwind for UAV (강한 맞바람이 발생 했을 때 무인기의 후진경로추종에 관한 연구)

  • Byeon, Gwang-Yeol;Park, Sanghyuk
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.42 no.5
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    • pp.376-382
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    • 2014
  • This paper presents a method to enable a UAV in autonomous flight along a desired path to follow it backwards when a strong headwind prevents the vehicle from proceeding forward. The main purpose of the reverse path following in this study is to return to a mission quickly when the wind becomes weaker. When the nonlinear path following guidance law is used, there are two reference points available in the path following. One of the two points is selected considering a flight direction for calculating a straight-line distance(L) from the vehicle to the point for the path following. An initial heading angle with respect to the wind direction determines whether the reverse path following is feasible or not at the time of the wind is generated. The result of the proposed method based on kinematic model in this study is verified through simulations implemented in Matlab.

A Study on Autonomous Indoor Flight using Computer Vision System (컴퓨터비전을 활용한 실내 자동비행체에 관한 연구)

  • Choi, Young;Kim, Kye-Young
    • Proceedings of the Korea Information Processing Society Conference
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    • pp.590-593
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    • 2012
  • 본 논문에서는 실내 환경에서 특정한 장소를 찾아갈 수 있는 자동비행체를, 컴퓨터비전과 스마트폰, 헬륨을 사용하여 구현 하는 방법을 제안한다. 마커를 이용하여 빌딩 내 각 정점을 표시하며, 이를 활용하여 자동으로 최단의 경로를 찾아서 그 경로를 따라 비행하는 알고리즘과 비행체의 구조를 보인다. 실험 결과 다양한 방면으로 적용 가능한 유의미한 결과를 얻었다

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Guidance Law of Missiles for Control Impact-Time-and-Angle by Flight Path Angle in Three Dimensional Space (3차원 공간에서의 비행 경로각을 이용한 비행시간 및 충돌각 제어 유도법칙)

  • Jin, Sheng-Hao;Lee, Chun-Gi;Yang, Bin;Hwan, Chung-Won;Park, Seung-Yub
    • The Journal of Advanced Navigation Technology
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    • v.16 no.1
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    • pp.8-15
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    • 2012
  • This paper on the assumption that the target is stationary and the velocity of missile is fixed value. In three dimensional space. Using flight path angle to simultaneous control impact-time-and-angle base on a homing guidance law. The independent variable in the nonlinear engagement model is the flight path angle of the missile. The propose homing guidance law can see the controllability of impact-time-and-angle. And also can see the processing of the missile arrive at the target. It is applied to several salvo attack scenarios. The performance of the proposed guidance law is verified by simulations.

Tight Path Following PID Controller for a Vehicle with Time Delay (비행체 시간지연을 고려한 정밀경로추종 PID 제어기법)

  • Rhee, Ihn-Seok;Park, Sang-Hyuk;Lee, Kyoung-Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.39 no.7
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    • pp.618-626
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    • 2011
  • In order to complete missions in a complicated terrain or highly dangerous area, an unmanned aerial vehicle(UAV) needs a fine controller to precisely follow the desired path. A PID controller used for the path following feeds forward path curvature information to the control input to improve the path following performance. High gain for PID controller is necessary to follow path tightly. However the high gain could cause instability or performance degradation when the vehicle has slow dynamics. We present PID controller design method which considers response delay of vehicle as well as path curvature. In order to obtain path curvature the desired path is described as a 3rd order polynomial by applying cubic spline interpolation. We apply the proposed controller to the path following of a UAV which is operated in high altitude and has very slow lateral dynamics. The lateral dynamics are modelled as a first order delayed system in the controller design. Nonlinear simulation shows the UAV with proposed controller follows an arbitrary path very tightly.

The Study on the Flight Route of linked Airparks for LSA (경량항공기 이착륙장 연계 비행경로에 대한 연구)

  • Shin, Dai-Won;Im, Sauk-Hoon
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.20 no.3
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    • pp.57-62
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    • 2012
  • In this study, changes depending on the Airparks for LSA(Light Sport Aircraft) and Ultralight vehicle flight restricted areas, the flight route for LSA in Korea was redesigned. Considerations for LSA operating limits of VFR and complex airspace conditions in Korea, and that links the Airparks for LSA is to redesign the proposed.

3-Dimensional Path Planning and Guidance using the Dubins Curve for an 3-DOF Point-Mass Aircraft Model (Dubins 곡선을 이용한 항공기 3자유도 질점 모델의 3차원 경로계획 및 유도)

  • O, Su-Heon;Ha, Cheol-Su;Gang, Seung-Eun;Go, Sang-Ho;Lee, Yong-Won
    • 한국항공운항학회:학술대회논문집
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    • pp.247-251
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    • 2015
  • 본 논문에서는 항공기의 3자유도 질점 모델과 Dubins 곡선을 이용한 3차원 경로생성 알고리즘 및 비선형 경로추종 유도기법을 통합하여 항공기의 경로계획을 위해 적용한 경로생성 알고리즘을 검증하고, 경로추종 성능과 항공교통관리를 위한 시뮬레이션에 3자유도 질점 항공기 모델 사용의 타당성을 확인하였다. 최적경로 생성을 위해 사용된 Dubins 곡선의 경우 계산속도가 빠르고 경로계획에 바로 적용이 가능하다는 장점이 있다. 하지만 주로 2차원 상의 경로문제를 다루기 때문에 이를 3차원 비행경로로 확장시킨 알고리즘을 사용하였다. 경로추종을 위한 유도제어법칙은 Specific Acceleration 명령을 통해 자세를 제어하는 비선형 경로추종 유도법칙을 활용하였으며, 이에 대한 결과를 확인하였다.

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3D Flight Path Creation using Sketch Input and Linear Spline Curves (스케치 입력과 선형 스플라인 곡선을 이용한 3D 항공경로 생성 방법)

  • Choi, Jung-Il;Park, Tae-Jin;Sohn, Ei-Sung;Jeon, Jae-Woong;Choy, Yoon-Chul
    • Journal of Korea Multimedia Society
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    • v.13 no.9
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    • pp.1373-1381
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    • 2010
  • Current flight maneuver diagram used by pilots is based on 2D spatial presentation, so it has limitation on display 3D flight information and hard to understand it instinctively. Flight animation authoring tools for this diagram are complex to use and lack useful features like non-linear editing of flight path and real-time interactivity on multiple aircrafts. This research focuses on 3D flight path generation method in the animation system for flight maneuver education. This research combines initial sketch input on 2D diagram with the thrust of an aircraft to generate 3D linear spline as close as to real flight. Using suggested linear spline creation method, the flight path can be visualized, edited, and animated in real-time at the flight maneuver briefing and debriefing.

A Study on Routing Problems in Drone Delivery Systems - Considering the Loading Capacity of Drone - (드론 운송 시스템에서 적재량에 따른 운송 경로 문제에 관한 연구)

  • Jeong, Hwi-Sang;Kim, Won-Sik;Cha, Sang-Hyun;Choi, Young-Won;Ha, Jeong-Hun;Kim, Jin-Il
    • Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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    • pp.584-585
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    • 2017
  • 본 연구는 드론 운송시스템에서 드론에 적재되어 있는 화물의 무게에 따른 비행가능거리의 변화를 운송 경로 문제에 적용시킨다. 드론에 적재된 무게에 따른 비행속도와 비행가능거리를 실험을 통해 사전에 수집하고, 이를 고려한 적합도 함수를 유전 알고리즘에 적용한다. 실험 결과 드론의 평균비행가능거리만을 이용한 것 보다 총소요시간을 단축시켜 효율적인 드론 운송시스템의 적용이 가능할 것이다.

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