• 제어로봇시스템학회논문지
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• 제19권11호
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• pp.1004-1010
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• 2013

In this paper, a simple design of a DOB (Disturbance Observer) for attitude control of a quad-rotor system is presented. A modified DOB structure from the conventional DOB is introduced to eliminate time-delay in the calculation. The proposed simple modification in the DOB configuration provides an efficiency in the calculation of the disturbance term such that the delayed calculation is not required. The performance of the modified DOB is evaluated through simulation studies. To confirm the simulation results, experimental studies of the attitude control of a quad-rotor system are conducted.

• 한국산학기술학회논문지
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• 제15권4호
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• pp.2335-2342
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• 2014

미래 유통 혁신 및 도심에서의 긴급 차량 운행에 도움을 주고자 차량 이동 정보 등이 포함된 실시간 교통 상황 정보 및 긴급 정보 제공 등을 위하여 무인 쿼드로터의 사용하고자 할 경우 무인 쿼드로터의 사용 안전성을 충분히 고려해야 한다. 따라서 본 연구에서는 4개의 모터를 가지고 있고 시스템적으로 구조적 균형이 잘 잡혀있는 무인 쿼드로터 시스템의 안전성 증대를 위하여 도심에서의 안전 착륙 제어에 대한 연구를 무인 쿼드로터 시스템의 비선형 특성을 고려한 운동학 및 동역학적 모델 기반 및 외란이나 시스템 비선형성에 강인한 Fuzzy 제어기를 통하여 진행하고자 하며, 이를 컴퓨터 시뮬레이션을 통하여 분석 하였다.

• 항공우주시스템공학회지
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• 제2권4호
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• pp.19-24
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• 2008

In this study gives detail on the composition and process of Quad-rotor blade Vehicle. It may seem simple but we have many trouble because of many subtleties. Unless designed carefully, it is very difficult to control of stability by reason of disturbances in the air and unbalance in the motor. We want to have a more stable output so add other electronics supplement, and change the battery in oder to increasing thrust. It cannot be done quickly, nor cheaply because it is more difficult than first ideas that control of Quad-rotor. But we complete manufacture of basically controllable vertical takeoff and landing aircraft.

• 대한전자공학회:학술대회논문집
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• 대한전자공학회 2008년도 하계종합학술대회
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• pp.1127-1128
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• 2008

In this paper, we propose a control method to improve control performance for a Quad-rotor Unmanned Aerial Vehicle's stabilization. The proposed method is the Fuzzy+I control that contains a fuzzy controller which processes signals from the error and the change of error, and generates the control signal by summing up fuzzy output signal and integral signal. We simulated and experimented on the fuzzy+I control method by implementing Quad-rotor UAV that is able to hovering, for the purpose of verifying the effectiveness of the proposed fuzzy+I control method in comparison with general PID control, and we found out that fuzzy+I controller improved control performance of the system.

• International Journal of Aeronautical and Space Sciences
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• 제12권3호
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• pp.252-259
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• 2011

This paper is focused on dynamic modeling and control system design as well as vision based collision avoidance for multi-rotor unmanned aerial vehicles (UAVs). Multi-rotor UAVs are defined as rotary-winged UAVs with multiple rotors. These multi-rotor UAVs can be utilized in various military situations such as surveillance and reconnaissance. They can also be used for obtaining visual information from steep terrains or disaster sites. In this paper, a quad-rotor model is introduced as well as its control system, which is designed based on a proportional-integral-derivative controller and vision-based collision avoidance control system. Additionally, in order for a UAV to navigate safely in areas such as buildings and offices with a number of obstacles, there must be a collision avoidance algorithm installed in the UAV's hardware, which should include the detection of obstacles, avoidance maneuvering, etc. In this paper, the optical flow method, one of the vision-based collision avoidance techniques, is introduced, and multi-rotor UAV's collision avoidance simulations are described in various virtual environments in order to demonstrate its avoidance performance.

• 한국항공우주학회지
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• 제42권3호
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• pp.243-253
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• 2014

본 논문은 플랜트 파라미터의 불확실성에도 불구하고 강인성을 보장하는 정량적 궤환 이론에 대해 다루고 있다. 정량적 궤환 이론은 플랜트의 파라미터와 외란의 불확실성에 대해 주파수 영역에서 설계 사양의 강인성을 보장한다. 정량적 궤환 이론을 이용하기 위해 선정한 플랜트는 기동성이 뛰어나며 헬리콥터와 같이 수직 이착륙이 가능한 4-회전익 비행체를 이용하였으며, 4개의 블레이드를 구동하는 모터의 파라미터 불확실성을 설정하여 요구사양에 맞는 자세 제어가 가능함을 실험하였다. 또한, 자세 제어에는 4-회전익 비행체의 파라미터 변동 범위와 동작 범위를 고려한 전필터를 사용하였다. 이를 위해 MATLAB에서 정량적 궤환 이론에 의해 제어기를 설계할 수 있는 QFT control toolbox인 QFTCT를 사용하여 각 설계 단계에 대해 소개하고 있다.

• 전기전자학회논문지
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• 제17권4호
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• pp.440-445
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• 2013

본 논문은 쿼드로터의 최단거리 복귀 시 위치인식을 위해 확장칼만필터를(EKF) 이용한 저가형 GPS/INS 융합시스템과 셀 분할 알고리즘이 결합된 위치추정시스템을 제안한다. 연구에서는 저가형 GPS가 가지는 위치오차와 INS가 가지는 가속도 값의 계속적인 적분으로 인한 누적 오차를 줄이기 위해 확장칼만필터를 이용하여 GPS/INS 융합시스템을 구성한다. 또한 쿼드로터는 원점 복귀 명령 시 최단거리의 경로 지점에 대한 위치 경로 측정이 가능하기 때문에 위치 경로를 기준으로 셀 분할 알고리즘을 적용하여 GPS/INS 결합 데이터 중 실제 위치와 근접한 데이터를 결정함으로써 위치오차를 더욱 줄인다. 본 논문에서 제안하는 기법의 성능은 실외에서 쿼드로터 복귀 중 GPS, GPS/INS 결합, 셀 분할 알고리즘 적용 각각의 실험 결과를 비교함으로써 평가된다.

• International Journal of Fuzzy Logic and Intelligent Systems
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• 제16권4호
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• pp.318-322
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• 2016

A quad-copter or quad rotor system is an unmanned flying machine having four engines, which their thrust force is produced by four propellers. Its stable control is very important and has widely been studied. It is a typical example of a nonlinear system. So, it is difficult to get a desired control performance by conventional control algorithms. In this paper, we propose the design of a vectored sum defuzzification based fuzzy logic system for the hovering control of a quad-copter. We first summarize its dynamics and introduce a vectored sum defuzzification scheme. And then we design a vectored sum defuzzification based fuzzy logic system. for the hovering control of the quad-copter. Finally, in order to check the feasibility of the proposed system we present some simulation examples.

• 제어로봇시스템학회논문지
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• 제19권2호
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• pp.158-163
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• 2013

The fusion of the GPS (Global Positioning System) and DR (Dead Reckoning) is widely used for position and latitude estimation of vehicles such as a mobile robot, aerial vehicle and marine vehicle. Among the many types of aerial vehicles, grater focus is given on the quad-rotor and accuracy of the position information is becoming more important. In order to exactly estimate the position information, we propose the fusion method of GPS and Gyroscope sensor using the DEKF (Dual Extended Kalman Filter). The DEKF has an advantage of simultaneously estimating state value and a parameter of dynamical system. It can also be used even if state value is not available. In order to analyze the performance of DEKF, the computer simulation for estimating the position, the velocity and the angle in a circle trajectory of quad-rotor was done. As it can be seen from the simulation results using own proposed DEKF instead of EKF on own fusion method in the navigation of a quad-rotor gave better performance values.

• 제어로봇시스템학회논문지
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• 제22권10호
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• pp.779-787
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• 2016

A nonlinear control law for the quad-rotor of a low-complexity, global approximation-free from system uncertainties and external disturbances are described in this paper. The control law guarantees convergence to a small bounded error using a prescribed performance function. The stability of the proposed nonlinear control system is also proven by the Lyapunov stability theorem. The advantage of this technique is that it has a simpler form than any other nonlinear compensators and is applicable to any nonlinear systems without precise knowledge of the systems. In this paper, the proposed approach is applied to attitude/altitude control of a quad-rotor. Numerical simulations are performed to investigate the proposed nonlinear attitude control law by applying it to an uncertain quadcopter system with external disturbances.