• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.7
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• pp.647-654
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• 2010

In this study, an efficient ornithopter aerodynamic model, which is applicable to ornithopter wing design considering fluid-structure interaction or ornithopter flight dynamics and control simulation, was proposed and experimentally validated through the wind tunnel experiments. Due to the ornithopter aerodynamics governed by unsteady low Reynolds number flow, an experimental device was specially designed and developed. A part of the experimental device, 2-axis loadcell, was situated in the non-inertial frame; the dynamic calibration method was established to compensate the inertial load for pure aerodynamic load measurements. The characteristics of proposed aerodynamic model were compared with the experimental data in terms of mean and root-mean-square values of lift and drag coefficients with respect to the flow speed, flapping frequency, and fixed angle of attack.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.7
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• pp.523-528
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• 2020

A lateral type MEMS inertial switch was designed on the same principle as spring-mass system. The MEMS switch is used for arming mechanism of the arm-fire device by sensing the applied acceleration. We analyzed the switching capability of the MEMS switch under various acceleration conditions via performance model. Simulation results showed that the MEMS switch works very well at 10 g when the applied acceleration slope does not exceed 10 g/msec. On the other hand, the threshold operating acceleration level simulation exceeded the requirement (10±2 g) due to the width and length of the spring by considering 10% tolerance of the design values. Design modification of doubling the width of the spring, which is difficult to reduce less than 10% tolerance in fabrication process, was proposed after confirming the simulation results comply the requirement.

• Journal of rehabilitation welfare engineering & assistive technology
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• v.8 no.4
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• pp.313-318
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• 2014

In this paper, we propose a method for correcting the measurement axis twist that occurs in the process of wearing and each estimation method of joint in which the inertial measurement unit based in health arm by the method of operation upper limb rehabilitation equipment of hemiplegic patients. In order to verify the proposed method, it is fitted with a inertial measurement unit of the upper arm and forearm of the experimenter left arm, verified by comparing actual joint angle is detected by photographing the arbitrary posture, the angle that the estimated joint. Then, it was verified by comparing the applied front / rear techniques for correcting the measurement axis twist. A result of the experiment, before applying the measurement axis twist correction, joint, after but each match rate showed a weak concordance rate in 89.16% and were corrected, measurement axis twist, each concordance rate of joint agreement of 93.28% I understand that it has been 4.12% improvement in the rate.

• Journal of the Korea Institute of Military Science and Technology
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• v.9 no.4
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• pp.71-80
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• 2006

Strapdown Inertial navigation systems consist of an inertial sensor assembly(ISA), electronic modules to process sensor data, and a navigation computer to calculate attitude, velocity and position. In the ISA, most gryoscopes such as RLGs and FOGs, have digital output, but typical accelerometers use current as an analog output. For a high precision inertial navigation system, sufficient stability and resolution of the accelerometer board converting the analog accelerometer output into digital data needs to be guaranteed. To achieve this precision, the asymmetric error and A/D reset scale error of the accelerometer board must be properly compensated. If the relation between the acceleration error and the errors of boards are exactly known, the compensation and estimation techniques for the errors may be well developed. However, the A/D Reset scale error consists of a pulse-train type term with a period inversely proportional to an input acceleration additional to a proportional term, which makes it difficult to estimate. In this paper, the effects on the acceleration output for auto-pilot situations and the effects of A/D reset scale errors during horizontal alignment are qualitatively analyzed. The result can be applied to the development of the real-time compensation technique for A/D reset scale error and the derivation of the design parameters for accelerometer board.

• Journal of the Korean Geophysical Society
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• v.9 no.2
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• pp.77-86
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• 2006

Aplications of the real-time kinematic GPS surveying and inertial measurement unit have been beingRTK GPS allows the use of a static base station and remote rover unit to allow for data collectionwithin several seconds and in real time. It is useful for monitoring the behaviors of massive structureslike bridges. And this study purposed to implement a method of deciding the acurate dynaimc attitudeof structures by IMU. In this study, among GPS methods, we used RTK GPS to analyze the precisionof monitoring and then on the basis of it, we developed a monitoring system using RTK GPS anda deviation betwen observation values, X axis was 1mm, Y axis was 1mm and Z axis 2.2mm. I tturned out that it was possible to monitor and measure structures by RTK GPS and IMU.

• Journal of the Korea Institute of Military Science and Technology
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• v.22 no.2
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• pp.189-196
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• 2019

The inertial sensor errors in SDINS(Strapdown Inertial Navigation System) can be compensated by rotating the inertial measurement unit and it is called RINS(Rotational Inertial Navigation System). It is assumed that the error of the inertial sensor in RINS is a static bias. However, the error of the inertial sensor actually developed and produced is not a static bias due to the change of the temperature applied to the sensor and the influence of the earth's gravity acceleration. In this paper, we propose a six-position gyro bias calibration method to evaluate the gyro bias required for RINS and present the test results of applying it to a ring laser gyro inertial navigation system under development.

• Journal of Energy Engineering
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• v.9 no.4
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• pp.342-347
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• 2000

최근 산업계에서 급증하는 전력수요와 부하의 다양화는 전원의 안정도에 악영항을 미치고 있다. 이는 전압강하는 역률 저하 유/무효 전력의 변동을 초래하고 타부하에 영향을 미치게 되므로 이를 효과적으로 보상할 수 있는 종합적인 보상 시스템이 필요하다. 본 논문에서는 이러한 전력보상 시스템중의 하나로서 플라이휠을 장착한 권선형 유도기의 2차 여자방식을 제시한다. 본 시스템은 전동기 2차 여자방식을 이용함으로서 기존의 정지형 보상기에 비하여 인버터의 용량을 기존의 것보다 수배 감소시킬 수 있는 장점이 있으며 히스테리시스 전류제어기를 사용하여 직접 전류제어기를 사용하여 직접전류 제어방식을 이용하므로 기존의 시스템과 비교하여 PI제어기의 게인선정의 어려움을 극복하고 제어 알고리즘을 간략화 할 수 있는 특징을 가지고 있다. 또한 전력을 보상하기 위한 에너지 저장요소로 플라이휠의 관성에너지를 사용함으로서 기존의 배터리 방식의 무정전 전원공급장치를 대신하는 효과를 보인다. 설계된 시스템과 제어방식은 시뮬레시션을 통하여 입증하였다.

• Proceedings of the KIEE Conference
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• 2011.07a
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• pp.1254-1255
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• 2011

최근 무선통신기반 열차제어시스템의 국산화 개발이 진행 중에 있으며, 이동폐색 및 열차간격의 효율적인 제어를 위해서는 열차에 서 직접 열차의 이동위치와 속도를 정확하게 실시간으로 파악할 수 있어야 한다. 하지만 기존 철도시스템에서는 열차의 위치 및 속도확인을 위해 궤도회로와 타코메터를 이용하고 있으며, 효율적인 열차제어를 위해 지상설비의 도움없이 안전하고 정확한 열차위치정보의 확보가 필요하다. 따라서 본 논문에서는 위성항법수신기, 관성센서, 도플러레이더센서, 타코메터와 같이 열차에 탑재 가능한 위치 및 속도센서를 통합 적용하여 단독으로 열차 위치 및 속도파악이 가능한 차상기반 열차위치검지 장치를 구성하고, 한국형 틸팅열차 탑재시험을 통해 위치정확성을 평가하고 철도운영 환경에서의 적용성을 확인한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.10
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• pp.48-55
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• 2006

A multi-filter fusion technique is proposed and this technique is applied to the INS/GPS integrated system. IIR-type EKF and FIR-type RHKF filter are fused to provide the advantages of these filters based on the adaptive mixing probability calculated by the residuals and the residual covariance matrices of the filters. In the INS/GPS, this fusion filter can provide more robust navigation information than the conventional stand-alone filter.

• Proceedings of the KIPE Conference
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• 2003.07b
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• pp.876-879
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• 2003

본 논문은 전동차용 추진제어장치의 재점착제어에 관한 것이다. 본 연구에서는 공전검지 방법에 대하여 기술하고, 등가 관성량을 이용한 추정재점착제어에 관하여 제시한다. 서울시 6호선 국산화 전동차(609편성)와 광주도시철도 1호선 전동차에 적용하여 재점착 제어성의 우수함과 안정성을 검증 하고자 한다.