가상현실이란 디지털로 표현된 가상 환경을 뜻하며 인터넷 쇼핑, 아바타 등 기본적으로 디지털 환경을 일컫는 단어이며, 최근에는 머리에 장착하는 디스플레이(HMD : Head Mounted Display)의 등장으로 사용자가 현실과 유사한 환경을 직접 경험하는 체험형 콘텐츠로서 의미를 확장했다. 현재 가상현실은 게임을 비롯한 힐링 콘텐츠, 관광, 군사 시뮬레이션 다양한 분야에서 주목받고 있으며 HMD의 보급 또한 활발하다. 사용자가 가상현실 콘텐츠를 체험하기 위해서는 몇 가지 제약이 발생하는데, 사용자의 시야가 차단되 현실공간감각이 상실된다. 따라서 기존에 사용되었던 입력장치인 키보드, 마우스 등의 사용에 어려움이 있으며 HMD를 개발하는 개발사들은 위의 문제를 해결하고자 가상현실 체험에 특화된 핸드트래킹 디바이스를 제공한다. 하지만 이 또한 상호작용, 이동, 제스처가 손에 집중되어있어 가상환경에 익숙하지 않은 이용자의 사용자 편의가 낮다. 본 논문은 이러한 이동의 문제를 아두이노를 통해 제작한 발 트레킹 디바이스로 이동을 분리시켜 해결하고자 하였다. IMU의 각속도계와 가속도계를 이용해 다리의 궤적을 측정하려 하였고, 이때 발생한 오차는 상보필터를 통해 해결하였다. 또한 기본적으로 발생하는 센싱-통신-연산 과정에서의 노이즈는 두가지 이동평균기법과 생략평균값을 이용해 안정화 시켰다. 사용자는 해당 장비와 Oculus Rift를 착용하고 Unity3d환경으로 구축된 실험환경에서 임무 수행 속도, 이동방향 오차율등을 측정해 기존 HMD컨트롤러와 본 논문에서 제시하는 컨트롤러를 비교 검증했다. 실험 결과 임무 수행 속도와 이동 오차율 모두에서 본 논문에서 제시하는 장치가 우수한 데이터를 제공하였다. 본 실험 결과를 토대로 이동조작 분리가 높은 접근성을 제공한다는 것을 확인하였다. 본 논문은 HMD 이동 컨트롤러를 포함한 이후 개발되는 다양한 사용자 제스처 인식 컨트롤러에도 적용 가능할것으로 보인다.

본 연구에서는 교통사고나 뇌졸중 등에 의해 상지의 장애를 가지는 장애인을 대상으로 하여, 인터넷의 브라우저와 같은 소프트웨어를 사용 할 수 있는 컴퓨터 인터페이스로서 자이로센서를 이용한 무선 자이로 마우스시스템를 개발하고, 임상평가를 통해 그 유용성을 확인하고자 한다. 시스템 개발에 있어서 주안점은, 첫째, 장애인의 경우 휠체어나 침대에 누워서 마우스 조작을 할 수 있도록 시스템의 무선화하는 것, 둘째, 착탈의 용이성과 미관을 위하여 센서를 헤드 밴드에 삽입하는 것, 셋째, 컴퓨터 운영체제에게 클릭신호를 전달하기 위하여, C5~C6 환자들의 경우에는 클릭 스위치를 사용하고, C4환자의 경우에는 고개의 끄덕임을 검출하도록 하는 것이다. 개발된 시스템을 척수손상으로 인한 상지 장애인을 대상으로 평가실험을 실시하였다. 그 결과 시행횟수가 증가할수록 상하/좌우 이동시의 목표위치에 대한 실제위치의 오차가 감소하고, 1분당 클릭률이 증가하는 경향을 확인하였다. 이로부터, 개발된 무선 자이로마우스 시스템은 환자의 반복사용을 통해 그 유용성이 증가할 것을 알 수 있다.

This paper introduces a Feedback Linearization (FL) controller to eliminate the gyro effect on a quadrotor UAV. In order to control the attitude of the quadrotor, the second model equation was differentiated to the 4-th order to induce the control input to be revealed, and then a new control input was derived based on the attitude transformation equation with a gyro effect. For the initial quick posture control of the quadrotor, the existing yaw control was replaced with a separate controller. The simulation was conducted with an experiment in which FL control to remove the gyro effect was applied to the quadrotor and an experiment without removing the gyro effect, from the experimental results, the maximum error seen in each axial direction of the quadrotor was x = 0.22 m, y = 0.20 m, z = 0.16 m. Through the proposed method, the effect of the FL controller for controlling the gyro effect of the quadrotor was confirmed.

This study proposes a measurement method using angular sensors to measure deformation and displacement of bridges. The proposed measurement method consists of gyroscope sensors and data processor to transform angular to vertical displacement. This study contains experimental evaluation to verify the applicability of the proposed method. 3-points bending tests were conducted on a small-sized girder specimen. The displacements were measured with both conventional LVDT and gyroscope sensor to compare the accuracy of the proposed method. It is estimated that the method using gyroscope shows some noise in data, but the method using gyroscope has advantages to measure the vertical displacement. Therefore if the sampling rate and synchronizing problems can be approved, it can be a good alternative measuring method for the deformation of the bridges.

This paper is to develop the position error equations including the attitude errors, the errors of nadir and ship's heading, and the errors of ship's position in the free-gyro positioning and directional system. In doing so, the determination of ship's position by two free gyro vectors was discussed and the algorithmic design of the free-gyro positioning and directional system was introduced briefly. Next, the errors of transformation matrices of the gyro and body frames, i.e. attitude errors, were examined and the attitude equations were also derived. The perturbations of the errors of the nadir angle including ship's heading were investigated in each stage from the sensor of rate of motion of the spin axis to the nadir angle obtained. Finally, the perturbation error equations of ship's position used the nadir angles were derived in the form of a linear error model and the concept of FDOP was also suggested by using covariance of position error.

This paper presents a sensitivity optimization of a MEMS (microelectromechanical systems) gyroscope for a magnet-gyro system. The magnet-gyro system, which is a guidance system for a AGV (automatic or automated guided vehicle), uses a magnet positioning system and a yaw gyroscope. The magnet positioning system measures magnetism of a cylindrical magnet embedded on the floor, and AGV is guided by the motion direction angle calculated with the measured magnetism. If the magnet positioning system does not measure the magnetism, the AGV is guided by using angular velocity measured with the gyroscope. The gyroscope used for the magnet-gyro system is usually MEMS type. Because the MEMS gyroscope is made from the process technology in semiconductor device fabrication, it has small size, low-power and low price. However, the MEMS gyroscope has drift phenomenon caused by noise and calculation error. Precision ADC (analog to digital converter) and accurate sensitivity are needed to minimize the drift phenomenon. Therefore, this paper proposes the method of the sensitivity optimization of the MEMS gyroscope using DEAS (dynamic encoding algorithm for searches). For experiment, we used the AGV mounted with a laser navigation system which is able to measure accurate position of the AGV and compared result by the sensitivity value calculated by the proposed method with result by the sensitivity in specification of the MEMS gyroscope. In experimental results, we verified that the sensitivity value through the proposed method can calculate more accurate motion direction angle of the AGV.

This paper presents a new approach for mobile robot heading detection using MEMS Gyro north finding method in the indoor environment. Based on this, the robot heading angle measurement scheme is proposed; improved north finding theory and algorithm are also explained. Several approaches are applied to confirm system’s precision and effectiveness. In order to find out the heading angle, a single axis MEMS gyroscope to sense the angle between the robot heading direction and the north is used. To reach enough estimation accuracy and reduce detection time,the least square method (LSM) for the signal fitting and parameter estimation is applied. Through a turn‐table, we setup a carouseling system to decrease the substantial bias effect on gyroscope’s heading angle. For the evaluation of the proposed method, this system is implemented to the Pioneer robot platform. The performance and heading error are analyzed after the test. From the simulation and experimental results, system’s accuracy, usefulness and adaptability are shown.

The localization of vehicle is an important part of an unmanned vehicle control problem. Pseudolite ultrasonic system(PUS) is the method to find an absolute position with a high accuracy by using ultrasonic sensor. And Gyro is the inertial sensor to measure yaw angle of vehicle. PUS can be able to estimate the position of mobile robot precisely, in which errors are not accumulated. And Gyro is a more faster measure method than PUS. In this paper, we suggest a more accuracy method of calculating PUS which is numerical analysis approach named Newtonian method. And also propose the fusion method to increase the accuracy of estimated angle on moving vehicle by using PUS and Gyro integrated system by Kalman filtering. To control the 4WS unmanned vehicle, the trajectory following algorithm is suggested. And the new concept arbitration of goal controller is suggested. This method considers the desirability function of vehicle state. Finally, the performances of Newtonian method and designed controller were verified from the experimental results with the 4WS vehicle scaled 1/10.

The authors aim to establish the theory necessary for developing free gyro positioning system and focus on measuring the nadir angle by using the motion rate of a free gyro. The azimuth of a gyro vector from the North can be given by using the property of the free gyro. The motion rate of the spin axis in the gyro frame is transformed into the platform frame and again into the NED (north-east-down) navigation frame. The nadir angle of a gyro vector is obtained by using the North components of the motion rate of the spin axis in the NED frame. The component has to be transformed into the horizontal component of the gyro by using the azimuth of the gyro vector and then has to be integrated over the sampling interval.

This paper is to develop the position error equation of in the free-gyro positioning system by using two free gyros. First, the determination of a position is analyzed on the ellipsoid of the Earth and the type of the errors is defined Finally the position error equation is introduced and developed, based on the definition of the type of errors which may be involved in the FPS.

There are two different assertions on the rolling error in the solid-controlled gyro compass which contains two rotors in its inner gyro sphere. One assertion is that there is a rolling error and the other is that there is no rolling error. This paper examines the rolling error caused by the centrifugal force by the experiment to reveal that the first assertionis reasonable, and it also attempts to explain qualitatively how the rolling error occurs. The Hokushin-Plath gyro compass is chosen as a model. The rolling error is examined by the swing test in various periods. From the tests, the following results are obtained. As long as the swing is continued under the fixed condition of the ship's heading, the swinging period and the amplitude, no error appears. In case the gyro compass is affected by the swingings except those of the cardinal planes, the error starts to appear only after the swing is finished and it is increasing slowly. It takes about 20 minutes for the error to reach its maximum value. The type of this error is a quadrantal one which makes the ship's heading high in the first and third quarters and low in the second and fourth quarters. But in each case the experimental maximum error is greater than the theorectical one.