Earticle

수중촬영을 위해서는 촬영자가 장비를 갖추고 수중으로 진입하여 촬영해야 한다. 촬영자가 직접 수중에 진입하기 때문에 수중에 존재하는 다양한 장애물이나 깊은 수심으로 인해 안전사고가 빈번하게 발생하고 있다. 이러한 문제점을 해 결하기 위해 본 논문에서는 수중 입체촬영을 위한 수면호버링 드론에 대해 제안하였다. 레이저 센서를 이용한 수위측정을 통해 드론이 일정 높이의 수면에서 호버링한 상태에서 촬영부만 수중으로 이동시켜 수중상태를 입체로 촬영하는 최적의 기법에 대해 기술하였다. 제안한 수중 입체촬영기법은 수중촬영에 드론을 사용함으로써 촬영자가 직접 수중으로 진입하지 않아도 되기 때문에 안전사고에 대한 문제점을 해결할 수 있으며 저비용으로 수중입체영상을 획득할 수 있는 장점을 갖고 있다. 입체촬영용으로 제안한 캠의 촬영각을 분석하여 적정한 입체영상의 시청이 가능한 조건을 수중 18cm높이에서 바닥 면 거리가 41.4cm 일 때로 규정하고 수면호버링 드론의 엘리베이션 체인에 의해 하강하는 촬영부의 높이를 조정하도록 제안하였다.

In order to shoot underwater, the photographer must be equipped with shooting equipment and enter into the water. Since the photographer directly enters the water, safety accidents occur frequently due to various obstacles or deep water in the water. The proposed underwater stereo photography technique can solve the safety accident problem caused by the entry of the photographer into the water by using the drone for underwater photographing. In addition, this technique has the advantage of obtaining underwater images at low cost. In this study, the angle of the proposed cam for stereoscopic photography was analyzed and the condition that the proper stereoscopic image can be viewed was defined as the distance from the floor of 18cm to the floor distance of 41.4cm. This provision is proposed to be used to adjust the height of the shooting area descended by the elevation chain of the water surface hovering drones.

This paper describes the conceptual design and performance evaluation of a personal air vehicle(PAV), which is selected as one of the major futuristic individual transportation. In this study, blade element theory(BET) was used to find a standard rotate speed, and a computational fluid dynamics (CFD) simulation was used to see the difference of the thrust performance in terms of rotor axis distance of quadcopter shape PAV in hover mode. The commercial ANSYS-FLUENT program was used to generate the CFD data. Modal analysis was used to calculate rotor dynamics and make Campbell diagram to find critical speed. The results showed that changes in the rotor axis distance clearly affect the aerodynamics thrust and critical speed of a quadcopter PAV.

In this study, a numerical analysis was performed as steady-state analysis to investigate the effect of interference between the propellers of the hexa-copter. As the distance increases, there is little change in thrust, but when a propeller close to the reference propeller rotates, it was confirmed that the thrust decreased due to the interference effect. Unsteady state analysis was performed to confirm the influence of the hexa-copter fuselage. If there is a fuselage, the thrust was predicted to increase by about 4.97% due to the ground effect. If the design parameters are established considering the effect of the fuselage of the hexa-copter, it is expected to be used for basic design and application design in the future.

The underwater hovering of submarine is to keep and alter depth at zero speed, which is a complex nonlinear process. Traditional control methods affect the effect because of lacking of adaptive capability, while fuzzy control can solve the problem well. Here the structure of fuzzy controller was set up based on the principle of fuzzy control. Then the rule for hovering control was carried out according to the classic step response. At last, the anti-jamming differentiator was set up by Simulink. The result of two basic working condition simulation showed that fuzzy controller was able to fix the submarine depth well, and had the advantage of fast and robust.

농용무인 헬리콥터는 벼농사는 물론 전작, 과수 등 소규모 필지의 정밀방제에 이용되고 있으며 농작업의 새로운 패러다임으로 자리 잡고 있다. 본 연구의목적은 농용헬리콥터의 비상시퀀스에서 정지비행 중 측풍에 의해서 비상착륙자리를 이탈하지 않고 위치를 유지하는 편류제어 모듈과 알고리즘의 성능을 평가하는데 있다편류제어의 목적은 비상착륙과 연동되어있는데, 비상조건에 도달하게 되면 호버링을 하면서 비상대처 알고리즘이 작동하게 된다. 그러나 관성 제어 는등속운동에서기체의 움직임을 감지하지 못하게 되고 측풍에 의하여 비상지점으로부터 편류를 하게 되어 착륙 목표지점으로부터 멀어질 수 있다.GPS 모듈을 기초로 개발한 편류제어모듈을 시험하였다.알고리즘 및 실효성을 고려하여 5 m 직경 내에 위치를벗어나지 않는지에 대한 기준을 적용하였다. 초기에는 2~4m/s의 측풍 교란에 대하여 과민하게 반응하였지만 이후5 m직경 내에서 위치를 벗어나지 않고 자세 및 요의 방향을 유지 하였다. 목도의 관찰에서는 전후좌우 흔들림을인지하기 어려운 정도이지만, 데이터에서 보인 편위는GPS 수신기의 특성에 기인하는 것으로 판단한다. 이와같은 편류제어는 비상착륙이나 호버링을 유지하려 할 때의도하지 않는 편류를 제어하는데 사용될 수 있다.

The precision aerial application of small farms, such as paddy, upland and orchard fields using agricultural unmanned helicopters became a new paradigm. The objective of this study was to evaluate the performance of a GPS module and algorithm, controlling drift of agricultural helicopter by the crosswind and maintaining the position for emergency landing. Purpose of the drift control, of which an algorithm works while hovering is related with the emergency sequence that coping with abnormal conditions of rotorcraft system. However, the inertial attitude control cannot detect a drifting motion of fuselage moving at the constant velocity, thus the crosswind takes the helicopter away from the landing position. Performance of the drift control module, based on the GPS that a hovering position did not deviate within 5m in diameter, were tested and evaluated. Initially, the reaction against a disturbing gust wind was sensitive, soon the helicopter maintained its locking position and azimuth within 5m in diameter. It was, however, difficult for the helicopter to recognize the swaying and nodding, the some deviation was expected due to the discrepancy characteristics of the GPS signal. The performance of the drift control proved the effectiveness of the module to maintain the position against an unintended drift during the emergency landing or hovering.

본 논문에서는 약간의 가정하에 리모트 제어용 모형 헬리콥터의 동역학방정식을 유도하였으며, 이를 토대로하여 헬리콥터의 자세안정을 위한 제어 알고리듬을 제안하였다. 제어이론으로서는 파라메타의 변화및 외란에 강인한 가변구조 제어이론을 활용하였다. 본 제어 알고리듬에서는 헬리콥터의 위치이동 제어에 대하여서는 다루지를 못하였으며, 단지 헬리콥터의 hovering 상태에서의 자세 안정화에만 촛점을 두어 제어 알고리듬을 제안하였다. 컴퓨터 모사를 통하여, 제안된 제어 제어 알고리듬의 타당성을 보였으며, 약 2-3초의 시간이 경과된 이후 자세가 안정화 됨을 볼 수 있었다.

This paper describes the design and control of a hovering AUV test-bed and analyzes the dynamic performance of the vehicle using simulation programs. The main purpose of this vehicle is to carry out fundamental tests of its station keeping, attitude control, and desired position tracking. Its configuration is similar to the general appearance of an ROV for underwater operations, and its dimensions are $0.75m{\times}0.5m{\times}0.5m$. It has four 450-W thrusters for longitudinal/lateral/vertical propulsion and is equipped with a pressure sensor for measuring the water depth and a magnetic compass for measuring its heading angle. The navigation of the vehicle is controlled by an onboard Pentium III-class computer, which runs with the help of the Windows XP operating system. This provides an appropriate environment for developing the various algorithms needed for developing and advancing a hovering AUV.

This paper describes a procedure to design a hovering flight controller for a model helicopter using LQG theory. Parameters of the model helicopter in hover are obtained using direct measurements and calculations proposed by other research. A feedback co is by using digital LQG theory. First, a full state feedback controller is designed to the discretized system taking desirable transient response and other assumptions into account. Then a full-state estimator is designed and revised until desirable response is obtained while global stability is maintained. Performance of the controller is tested by computer simulations. Experiments have been performed using a 3-degree-of-freedom gimbal that holds the model helicopter, and the controller exhibited stable hover capability.

This paper describes the design and development of a hovering AUV constructed at Cheju National University and analyses the dynamic performance of the vehicle using simulation programs. The main purpose of this AUV is to carry out fundamental tests in its station keeping, attitude control, and desired position tracking. Its configuration is similar to the general ROV appearance for underwater works and its dimensions are 0.75m*0.5m*0.5m. It has 4 thrusters of 450 watts for longitudinal/lateral/vertical propulsion and is equipped with a pressure sensor for measuring water depth and a magnetic compass for measuring heading angle. The navigation of the vehicle is controlled by an on-board Pentium III-class computer, which runs with the help of the Windows XP operating system. These give us an appropriate environment for developing various algorithms needed for developing and advancing Hovering AUV.

A QRT(Quad-Rotor Type) hovering robot system is developed for quick detection and observation of the circumstances under calamity environment such as indoor fire spots. The UAV(Unmanned Aerial Vehicle) is equipped with four propellers driven by each electric motor, an embedded controller using a DSP, INS(Inertial Navigation System) using 3-axis rate gyros, a CCD camera with wireless communication transmitter for observation, and an ultrasonic range sensor for height control. The developed hovering robot shows stable flying performances under the adoption of RIC(Robust Internal-loop Compensator) based disturbance compensation and the vision based localization method. The UAV can also avoid obstacles using eight IR and four ultrasonic range sensors. The VTOL(Vertical Take-Off and Landing) flying object flies into indoor fire spots and sends the images captured by the CCD camera to the operator. This kind of small-sized UAV can be widely used in various calamity observation fields without danger of human beings under harmful environment.

Numerical simulations are conducted to investigate the mechanism of hovering flight with an inclined stroke. The Reynolds numbers considered are 150 and 1000 based on the maximum translational velocity and wing chord length. Three mechanisms responsible for high vertical force generation, suggested by Dickinson et al. (1999), are confirmed and more elaborated in the present study. First, we show that the vertical force during downstroke is larger than that from the quasi-steady analysis due to the delayed stall mechanism. Second, the wing-wake interaction of reducing the negative vertical force during the stroke reversal is explained in terms of the reattachment of the vortex, shed previously during downstroke, on the wing, by which the wing is submerged in a low pressure region during up stroke and has a smaller negative vertical force. Finally, the rotational circulation is explained by advancing the rotation timing of the wing at supination using both the numerical simulation and inviscid potential theory.

UAV are widely used in such affected areas of lifesaving, delivery and aerial photography. The most important thing in the function of unmanned aircraft equipped is to ensure stability. As the accident rate of a drone reaches 100 times that of general aircraft, the operation at the low altitude has caused the collisions with a number of structures. Therefore, studies for ensuring the safety of an unmanned aircraft, have become an important field. In this paper, the touch on measures to ensure the safety of the unmanned aircraft is covered. The most basic is implementation of reliable hovering in safety. Hovering has a method of using a GPS signal. However, hovering cannot be available when the GPS signal is lost or it has a room flight. In this paper, a possible stable hovering manner based on the optical flow is suggested. Therefore, the operation was tested, using the setting program, after an optical flow sensor is set to flight control board APM2.5. Then, the actual travel distance of the unmanned aircraft was calculated by implementing an algorithm for correcting the error in moving distance corresponding the altitude. Finally, using the calculated X and the Y coordinate value, it corrected the position of the unmanned aircraft. Position correction is adjusted by using the Roll and Pitch values. As a result, stable hovering in capable unmanned aircraft was implemented even if it was impossible to use the GSP signal under indoor flight.

The three-dimensional flows in the Weis-Fogh mechanism are studied by flow visualization and numerical simulation by the vortex method. The vortex method. especially the vortex stick method, is employed to investigate the vortex structure in the wake of the two wings. The pressure is estimated by the Bernoulli equation, and the lift on the wing are also obtained. As the results the eddies near the leading edge of each wing in the fling stage take a convex shape because the eddies shed from both tips entrain the flows and the downwash in the rotating stage is deflected toward the outside because the outside tip vortex is stronger than the inside one. And the lift coefficient on the wings in this mechanism is almost independent of the Reynolds number.

● Introduction ● System Identification ● PD Controller Design ● Verifying the Model & Simulation ● Experiment for Attitude Control ● Results ● Conculsions

Flutter is a dangerous phenomenon encountered in flexible structures subjected to aerodynamic forces. This includes aircraft, helicopter blades, engine rotors, buildings and bridges. Flutter occurs as a result of interactions between aerodynamic, stiffness, and inertia forces on a structure. The conventional method for designing a rotor blade to be free from flutter instability throughout the helicopter's flight regime is to design the blade so that the aerodynamic center (AC), elastic axis (EA) and center of gravity (CG) are coincident and located at the quarter-chord. While this assures freedom from flutter, it adds constraints on rotor blade design which are not usually followed in fixed wing design. Periodic Structures have been in the focus of research for their useful characteristics and ability to attenuate vibration in frequency bands called "stop-bands". A periodic structure consists of cells which differ in material or geometry. As vibration waves travel along the structure and face the cell boundaries, some waves pass and some are reflected back, which may cause destructive interference with the succeeding waves. In this work, we analyze the flutter characteristics of helicopter blades with a periodic change in their sandwich material using a finite element structural model. Results shows great improvements in the flutter rotation speed of the rotating blade obtained by using periodic design and increasing the number of periodic cells.

Aerodynamic characteristics of Coleoptera species of Epilachna quadricollis and Allomyrina dichotoma are experimentally and numerically investigated. Using digital high speed camera and smoke wire technique, we visualized the continuous wing kinematics and the flight motion of free-flying coleoptera. The experimental visualization shows that the elytra flapped concurrently with the main wing both in the downstroke and upstroke motions. The wing motion of Epilachna quadricollis was captured and analyzed frame by frame to identify the kinematics of the wings and to implement it in the movement of a model wing (thin plate) in the simulation. The two-dimensional simulation of Epilachna quadricollis hovering flight was performed by assuming the wing cross section shape as a thin plate, even though most of insect's wings are made of curved corrugated membrane. The effect of Reynolds number are investigated by the simulation. Meanwhile, in order to investigate the role and effect of elytra, the flow visualization of Allomyrina dichotoma was carried on using smoke wire visualization technique. Here, we confirmed that the vortex generated by elytra due to its movement is strongly influence the vortex dynamic generated by hind wings.

A helicopter is used in a variety of situations because of its usability. Its operation, needs human skill. The authors are working on automatization of human skill. Helicopter operation is one of such fields of practicing human skill. This is why the present paper deals with helicopter (model helicopter) operation. Full operation of a helicopter needs more complicated system in both aspects of software and hardware, and also requires more training for operation. From the purpose here that helicopter operation is for checking the applicability of the authors' idea for automatization based on experience, attitude regulation in hovering is the target. In the present paper, a human operator's operation is recorded as a time series of operation actions, and the record is reorganized as the correspondence between the helicopter's attitude and the proper operation action required in that particular situation.

In this paper, we describe the synthesis of robust and non-fragile $H^{\infty}$ state feedback controllers for linear systems with affine parameter uncertainties, as well as a static state feedback controller with poly topic uncertainty. The sufficient condition of controller existence, the design method of robust and non-fragile $H^{\infty}$ static state feedback controller with fuzzy compensator, and the region of controllers that satisfies non-fragility are presented. We show that the resulting controller guarantees the asymptotic stability and disturbance attenuation of the closed loop system in spite of controller gain variations within a resulted polytopic region.

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.

For a maneuvering unmanned autonomous helicopter, it is necessary to design a proper controller of each flight mode. In this paper, overall helicopter dynamics is derived and hovering model is linearized and transformed into a state equation form. However, since it is difficult to obtain parameters of stability derivatives in the state equation directly, a linear control model is derived by time-domain parametric system identification method with real flight data of the model helicopter. Then, two different controllers - a linear feedback controller with proportional gains and a robust controller - are designed and their performance is compared. Both proposed controllers show outstanding results by computer simulation. These validated controllers can be used to autonomous flight controller of a real unmanned model helicopter.