• 전기의세계
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• v.45 no.9
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• pp.9-17
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• 1996

1970년 미국의 코닝글라스사(Corning Glass Company)에서 광섬유가 최초로 제조된 이래 광섬유는 통신분야에 많은 공헌을 해오고 있다. 1976년 Kinsley, Davies 등에 의해 광섬유를 이용한 전기적 위상변이 효과가 발표된 이후로 광섬유 특성을 이용한 센서연구가 많이 진행되어 왔다. 즉, 광파이버의 실현과 반도체 레이저와 발광 및 수광 다이오드의 성능 향상에 의하여 광파이버 응용 계측 기술이 현저하게 진보하여 그 다양성과 실현성도 두드러지게 증가되었다. 이것은 레이저와 수광소자 등의 광소자의 개발, 마이크로컴퓨터를 비롯한 전자기술의 진보, 또한 최근의 전력 계통과 철강, 석유 화학 등의 각종 공업 플랜트의 대규모화, 고도화에 따른 고품위의 계측 제어시스템에 대한 수용의 증대에 의한 것이다. 이에 따라서 광대역, 저손실, 고절연성, 내잡음성, 안전방폭성 등이 우수한 광파이버를 신경망으로 하는 광파이버 응용 계측 제어 시스템이 공장자동화에 있어서 중요한 역할을 담당하게 될 것이다. 이의 설계와 제어를 위해 가장 중요한 부분은 정보 수집을 하는 센서 즉, 광속도, 회전 각속도 등 많은 종류의 광섬유 센서의 연구 개발이 미국, 일본, 유럽 및 국내의 여러 기관에서도 게속적인 연구가 진행되고 있으며, 부분적으로 서서히 실용화되어 가고 있다[3-4].

• Journal of Advanced Marine Engineering and Technology
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• v.39 no.7
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• pp.722-728
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• 2015

The demand for shipboard energy management is expected to gradually increase based on ship energy efficiency management plans (SEEMPs), which have been in use since January 1, 2013. Therefore, the fuel consumption of the main engine, which occupies the greatest portion of the energy used, along with elements related to the engine power, should be strictly monitored. There are many different methods for indicating the engine power. However, this study performed an experiment to monitor the status of a ship's engine power in real time using an encoder and a proximate switch, which are economical to purchase and easy to install. In the experiment, the angular velocity during one cycle of a two-stroke low-speed engine was measured, and the measured data were converted to the torque fluctuation. The angular velocity during an abnormal firing condition in the cylinder was also measured, and the torque fluctuation as a result of a misfire was considered. The results were compared with sea trial data to determine the reliability. In this study, the status of the engine power was determined using the torque fluctuation of the main engine in an operating ship.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.5
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• pp.405-412
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• 2015

This paper represents a filter design to estimate the airspeed of a spin-stabilized, trajectory-correctible artillery ammunition. Due to the limited power and space in operational point of view, the airspeed sensor is not installed, and thus the airspeed need to be estimated using limited sensor measurements. The only IMU measurements(three-axis specific forces and angular rates) are used in this application. The extended Kalman filter algorithm is applied since a linear filter can not cover the its wide operational range in airspeed and altitude. In the implementation of the EKF, the state and measurement equations are transformed into the no-roll frame for simple form of Jacobian matrix. The simulation study is conducted to evaluate the performance of the filter under various environment conditions of sensor noise and wind turbulence. In addition, the effect of the choice in filter design parameters, i.e. process error covariance matrices is analyzed on the performance of the estimation of airspeed and angular rates.

• Journal of the Institute of Electronics Engineers of Korea SC
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• v.46 no.4
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• pp.70-76
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• 2009

We proposed the device to control a computer mouse with only head movements and eye blinks so that disabilities by car or other accidents can use a computer. The mouse position were estimated from a gyro-sensor which can measure head movements, and the mouse events such as click/double click were from opto sensors which can detect the eyes flicker, respectively. The sensor was mounted on the goggle in order not to disturb the visual field. There was no difference in movement speed between ours and a general mouse, but it required 3$\sim$4 more times in the result of the experiment to evaluate spatial movements and events detection of the proposed mouse because of the low accuracy. We could eliminate cumbersome work to periodically remove the accumulated error and intuitively control the mouse using non-linear relative point method with dead zones. Optical sensors are used in the event detection circuitry designed to remove the influence of the ambient light changes, therefore it was not affected in the change of external light source.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.11
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• pp.921-933
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• 2018

There is a method to enhance the pure navigation performance of INS(Inertial Navigation System) through the rotation of inertial measurement unit to compensate error sources of inertial sensors each other and that INS using this principle of operation is called rotational INS. In this paper, the exact error analysis of rotational INS based on ring laser gyro considering the coupling effect with gravity and earth rate is performed to evaluate the navigation performance by inertial sensor error sources. And error analysis and performance evaluation result confirmed by modelling and simulation is also proposed in this paper.

• 한국항공운항학회:학술대회논문집
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• 2004.11a
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• pp.302-307
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• 2004

무인 항공기는 지상 조종 또는 자동 비행으로 원격제어, 각종 정찰, 수송, 및 공격 등의 다양한 임무를 수행할 수 있는 비행체 및 이를 포함한 시스템을 의미한다. 무인기의 자율 운항을 위해서는 위치, 속도 및 자세 등의 항법 정보를 제공하는 항법 시스템이 반드시 필요하며 크기가 작은 무인기를 위해서는 탑재체의 중량이 적은 항법 시스템이 반드시 필요하다. 최근에는 반도체 MEMS 기술을 이용한 저가형 관성 센서들이 많이 개발 되고 있으며 이를 이용한 소형, 저전력, 고정밀 항법 시스템들이 많이 연구 개발되고 있다. GPS/AHRS 결합 시스템은 자세각, 각속도, 가속도 정보 및 GPS를 이용한 위치, 슥도 정보 제공이 가능한 시스템으로 비행체의 자율비행을 위한 정보 제공이 가능한 시스템이다. 본 논문에서는 MEMS 센서를 기반으로한 GPS/AHRS 결합 항법 시스템 설계하고 차량을 이용하여 성능을 평가한 결과를 보여준다.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• v.2
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• pp.471-474
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• 2006

GPS수신기는 항법센서로서 여러 분야에서 널리 사용되고 있다. 단일 안테나 GPS수신기로부터 일반적으로 위치와 속도 및 시간 정보를 얻을 수 있다. 그러나 고정익 항공기의 운동 특성을 고려하여 단일 안테나 GPS수신기의 측정치로부터 무인항공기의 자세를 추정할 수 있다. 이로써 단일안테나 GPS수신기를 이용하여 무인항공기의 자동 제어가 가능함을 이전 논문에서 보인 바 있다. 본 논문에서는 단일 안테나 GPS수신기를 무인항공기의 기본 센서로 사용하여 자동 이착륙이 가능함을 비행실험을 통해 보인다. 무인항공기의 반응속도와 강건성을 향상시키기 위해 rate gyros의 각속도 측정치를 이용한다. 또한 활주로에 자동착륙하기 위해서는 높은 정확도의 위치 정보가 필요하므로 DGPS를 이용하였다. 비행 실험 동안 무인항공기는 이륙에서 착륙까지 모든 과정을 자동 제어로 수행한다. 대부분 비행은 경로 제어로 이루어진다. 비행 실험 결과를 바탕으로 단일안테나 GPS수신기가 General Aviation 항공기나 무인항공기의 백업이나 저가의 제어 시스템을 위한 주 센서로서 사용이 가능할 것으로 판단된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.4
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• pp.324-332
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• 2016

In this paper, the terminal homing loop with a IIR-type strapdown seeker and a roll rate gyroscope is proposed. Basically, the proposed homing loop is based on the look-angle-control guidance. Since the range of the seeker is strictly limited, the missile is delivered to a point to lock the target on the seeker via non-guided flight during the midcourse guidance. The non-standard firing table is developed to compensate the wind and the target movement. To secure the delay margin is very important to prevent the instability of the homing loop when the time delay of the seeker is included. To validate the proposed homing loop, the 6-DOF nonlinear simulation is performed, and the Monte-Carlo simulation is also done for checking the robustness for the various kinds of uncertainty.

• Current Research on Agriculture and Life Sciences
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• v.32 no.2
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• pp.79-84
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• 2014

The precision aerial application of agricultural unmanned helicopters has become a new paradigm for small farms with orchards, paddy, and upland fields. The needs of agricultural applications require easy and affordable control systems. Recent developments of MEMS technology based on inertial sensors and high speed DSP have enabled the fabrication of low-cost attitude system. Therefore, this study evaluates inertial MEMS sensors for estimating the attitude of an agricultural unmanned helicopter. The accuracies and errors of gyro and acceleration sensors were verified using a pendulum system. The true motion values were calculated using a theoretical estimation and absolute encoder measurement of the pendulum, and then the sensor output was compared with reference values. When comparing the sensor measurements and true values, the errors were determined to be 4.32~5.72%, 3.53~6.74%, and 3.91~4.16% for the gyro rate and x-, z- accelerations, respectively. Thus, the measurement results confirmed that the inertial sensors are effective for establishing an attitude and heading reference system (AHRES). The sensors would be constructed in gimbals for the estimating and proving attitude measurements in the following paper.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.34 no.4
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• pp.355-364
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• 2010

Filiform hairs that respond to movements of the surrounding medium are the mechanoreceptors commonly found in arthropods and vertebrates. In these creatures, the filiform hairs function as a sensory system for raider detection. Parametric analyses of the motion response of filiform hairs are conducted by using a mathematical model of an artificial flow sensor to understand the possible operating ranges of a microfabricated device. It is found that the length and diameter of the sensory hair are the major parameters that determine the mechanical sensitivities and responses in a mean flow with an oscillating component. By changing the hair length, the angular displacement, velocity, and acceleration could be detected in a wide range of frequencies. Although the torques due to drag and virtual mass are very small, they are also very influential factors on the hair motion. The resonance frequency of the hair decreases as the length and diameter of the hair increase.