• International Journal of Aeronautical and Space Sciences
• /
• 제16권4호
• /
• pp.581-589
• /
• 2015

This paper describes a monocular vision-based formation flight technology using two fixed wing unmanned aerial vehicles. To measuring relative position and attitude of a leader aircraft, a monocular camera installed in the front of the follower aircraft captures an image of the leader, and position and attitude are measured from the image using the KLT feature point tracker and POSIT algorithm. To verify the feasibility of this vision processing algorithm, a field test was performed using two light sports aircraft, and our experimental results show that the proposed monocular vision-based measurement algorithm is feasible. Performance verification for the proposed formation flight technology was carried out using the X-Plane flight simulator. The formation flight simulation system consists of two PCs playing the role of leader and follower. When the leader flies by the command of user, the follower aircraft tracks the leader by designed guidance and a PI control law, and all the information about leader was measured using monocular vision. This simulation shows that guidance using relative attitude information tracks the leader aircraft better than not using attitude information. This simulation shows absolute average errors for the relative position as follows: X-axis: 2.88 m, Y-axis: 2.09 m, and Z-axis: 0.44 m.

• 한국군사과학기술학회지
• /
• 제25권6호
• /
• pp.586-595
• /
• 2022

In this paper, we propose a formation control algorithm for multi-USVs according to COLREGs. First, we applied the Dynamic Window Approach algorithm that can reflect the kinematic characteristics for the path movement of USVs. Then, we propose a virtual structure-based virtual leader-follower method that applies the advantages of leader-follower and virtual structure methods among conventional formation control algorithms for stability. Next, we proposed a collision avoidance algorithm according to all COLREGs when encountering an opposing ship by adding COLREGs situational conditions to the virtual leader, and finally confirmed the feasibility of the proposed method through simulation.

• 한국정보통신학회논문지
• /
• 제19권1호
• /
• pp.26-34
• /
• 2015

본 논문에서는 이동 로봇의 군집 제어를 위해 퍼지 보상된 PID 제어 시스템을 제안한다. 제어 시스템은 선도-추종기법에 기반한 기구학 제어기와 이동 로봇의 동역학적 영향을 고려한 동역학 제어기로 구성되어 있다. 이동 로봇의 대형 유지를 위해 동역학 제어기는 PID제어기로 구성되었다. 하지만 PID 제어기는 비선형 또는 환경 변화에 취약점을 가진다. 이러한 문제를 보완하기 위해 퍼지 보상기를 추가하였다. 마지막으로 개선된 성능을 보이기 위해 컴퓨터 시뮬레이션을 통해 제안된 제어기를 평가하였다.

• Journal of Astronomy and Space Sciences
• /
• 제20권4호
• /
• pp.365-374
• /
• 2003

Satellite formation flying is currently an active area of research in the aerospace engineering. So it has been researched by various authors. In this study, a tracking controller using sliding mode techniques was designed to control a satellite for the satellite formation flying. In general, Hill's equations are used to describe the relative motion of the follower satellite with respect to the leader satellite. However the modified Hill's equations considering the $J_2$ perturbation were used for the design of sliding mode controller. The extended Kalman filter was applied to estimate the state vector based on the measurements of relative distance and velocity between two satellites. The simulation results show that the follower satellite tracks the desired trajectory well by thruster operations based on the sliding mode control law.

• 제어로봇시스템학회논문지
• /
• 제16권11호
• /
• pp.1038-1043
• /
• 2010

In this paper, an adaptive sliding-mode formation control and collision avoidance are proposed for electrically driven nonholonomic mobile robots with model uncertainties and external disturbances. A sliding surface based on the leader-follower approach is developed to achieve the desired formation in the presence of model uncertainties and disturbances. Moreover, by using the collision avoidance function, the mobile robots can avoid the obstacles successfully. Finally, simulations illustrate the effectiveness of the proposed control system.

• International Journal of Aeronautical and Space Sciences
• /
• 제14권2호
• /
• pp.183-192
• /
• 2013

This paper presents formation reconfiguration using impulsive control input for spacecraft formation flying. Spacecraft in a formation should change the formation size and/or geometry according to the mission requirements and space environment. To modify the formation radius and geometry with respect to the leader spacecraft, the follower spacecraft generates additional control inputs; the two impulsive control inputs are general control type of the spacecraft system. For the impulsive control input, Lambert's problem is modified to construct the transfer orbit in relative motion, given two position vectors at the initial and final time. Moreover, the numerical simulation results show the transfer trajectories to resize the formation radius in the radial/along-track plane formation and in the along-track/cross-track plane formation. In addition, the maneuver characteristics are described by comparing the differential orbital elements between the reference orbit and transfer orbit in the radial/along-track plane formation and along-track/cross-track plane formation.

• 전기학회논문지
• /
• 제60권4호
• /
• pp.856-861
• /
• 2011

The mobile robot controller is designed to track the target and to maintain the formation at the same time. Formation control is included in mobile robot controller by extending the trajectory tracking algorithm. The dynamic model of mobile robot is used with kinematic model considering the practical physical parameters of mobile robot. The dynamic model of mobile robot transforms velocity control input of kinematic model into torque control input which is the practical control input of mobile robot. Formation controller of mobile robot is designed to satisfy Lyapunov stability by backstepping method. The designed formation controller is applied to the mobile robot for various target movements and simulated to confirm the Lyapunov stability.

• 한국항공우주학회지
• /
• 제46권12호
• /
• pp.1012-1020
• /
• 2018

한국항공우주연구원에서 개발된 틸트로터 무인기의 임무비행 능력을 높이기 위하여, 무인기의 자율화 기술 5단계 수준의 편대비행에 대한 연구가 수행되었다. 편대비행은 선행기와 추종기로 구성된 중앙 집중형 방식이 적용되었다. 편대비행 제어기는 3대의 추종기를 이용한 수치 시뮬레이션과 1대의 추종기를 이용한 하드웨어 기반 시뮬레이션을 통해 검증되었다. 본 논문에서는 제어기 설계 방법, 하드웨어 기반 시뮬레이션 시험, 그리고 시뮬레이션을 통한 성능 검증에 대해서 기술하였다.

• 한국정밀공학회지
• /
• 제31권11호
• /
• pp.1023-1030
• /
• 2014

This paper presents a new method to control swarm robots so that they can keep the formation while following a curved path. The main idea is to utilize the information on the instant center of gyration. For a given path, location of the instant center of the formation center is calculated, and individual robots follow the circular path around the calculated instant center. Performance of curvature-radius based method is compared with leader-follower referenced method via MATLAB simulation.

• 한국항공우주학회지
• /
• 제38권3호
• /
• pp.264-273
• /
• 2010

본 연구에서는 무인항공기의 편대비행을 위해서 먼저 단일 무인항공기의 기본적인 자세제어, 고도제어를 포함하는 유도제어시스템을 설계 제작하여 검증하고, 이 시스템을 바탕으로 먼저 선도기의 위치 정보를 이용하여 선도기와 추종기간의 앞뒤거리와 좌우 거리를 피드백하여 비례미분제어한 결과를 보여준다. 보다 안정적이고 성능이 우수한 편대 비행을 위하여 선도기의 위치와 자세 정보를 이용하여 추종기가 따라가야할 가상경로점을 실시간으로 계산하고 이를 바탕으로하여 추종기가 따라가도록 유도 명령을 생성하여 비행제어를 하고, 또한 선도기의 롤명령정보를 추종기의 최종 유도명령에 추가하여 편대 비행 성능을 향상시킬 수 있음을 보여준다. 이러한 과정은 여러 가지 경우에 대한 비행시험 결과를 분석하여 알고리즘을 점차 개선하는 방식을 취했으며 다소 실험적인 방식으로 최종 편대비행 알고리즘을 확립하였다. 최종적으로 채택한 기법을 이용하여 3대의 무인항 공기를 자동비행 상태에서 편대 비행을 수행한 결과를 보여준다.