• 한국의류산업학회지
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• 제14권1호
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• pp.24-36
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• 2012

This study examines consumer's acceptance intention of sensor-based smart clothing empolying the extended TAM. Technology innovativeness, information innovativeness and trust were used as external variables and perceived palyfulness was included in the extetended TAM. Data were collected from the adults over 20 years old living in Daegu from March 14 to 18, 2011. 193 useful copies of data were analyzed to investigate a structural model and test research hypotheses using AMOS 7.0. The study results showed that the extended TAM for smart clothing was validated empirically in predicting the individual's acceptance of sensor-based smart clothing and 10 hypotheses among 12 hypotheses were supported. Technology innovation, information innovation, and trust were confirmed as antecedent variables in affecting extended TAM. Perceived usefulness and perceived playfulness directly influenced acceptance intention and indirectly influenced acceptance intention mediating attitude. Perceived usefulness affected perceived playfulness and attitude affected acceptance intention. This study will help marketers and managers of fashion companies devise effective tools in planning marketing strategies related to smart clothing.

• 한국자동차공학회논문집
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• 제24권4호
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• pp.408-415
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• 2016

The vehicle attitude and sideslip is critical information to control the vehicle to prevent from unintended motion. Many of estimation strategy use bicycle model or IMU integration, but both of them have limits on application. The main purpose of this paper is development of vehicle orientation estimator which is robust to various vehicle state and road shape. The suggested estimator use 3-axis magnetometer, yaw rate sensor and lateral acceleration sensor to estimate three Euler angles of vehicle. The estimator is composed of two individual observers: First, comparing the known magnetic field and gravity with measured value, the TRIAD algorithm calculates optimal rotational matrix when vehicle is in static or quasi-static condition. Next, merging 3-axis magnetometer with inertial sensors, the extended Kalman filter is used to estimate vehicle orientation under dynamic condition. A validation through simulation tools, Carsim and Simulink, is performed and the results show the feasibility of the suggested estimation method.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1993년도 한국자동제어학술회의논문집(국내학술편); Seoul National University, Seoul; 20-22 Oct. 1993
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• pp.185-188
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• 1993

The goal of this paper is to develop an on-board controller for a model helicopter's hovering attitude control, using i8096 one-chip microcontroller. Required controller algorithm is programmed in ASM-96 assembly language and downloaded into an i8096 microcontroller. The performance of hovering flight using this system is verified by experiments with the model helicopter mounted on an instrumented flight stand where 3 potentiometers and an optical proximity sensor measure te attitude and main rotor speed of the helicopter.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.177.2-177
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• 2001

The asynchronous gyro outputs in the 3-axis navigation system are defined as each of gyros has its own output frequency. In this case, the navigation system has gyro outputs concurrently with the sensor mechanical frequency instead of the attitude frequency. So, there is an asynchronous error between gyro outputs and attitude calculation. In this paper, we analyze the gyro output error caused by the asynchronous gyro and present the high speed sampling technique and the extrapolation and interpolation of gyro outputs for synchronizing the gyro outputs.

• 한국통신학회논문지
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• 제19권3호
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• pp.505-514
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• 1994

무궁화 위성체는 10년 수명기간 동안 통신 및 직접방송 위성서비스에 필요한 빔의 지향성을 유지하기 위하여 정확하고 신뢰성있는 자세제어 시스팀을 요구하고 있다. 본고에서는 무궁화 위성체가 정지궤도에서 정상운용모드로 동작하는데 요구되는 자세제어부속시스팀에 대한 상세설계기법 및 성능에 대해서 기술하고자 한다.

• 한국항공우주학회지
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• 제34권8호
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• pp.63-70
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• 2006

초소형 비행체는 초소형, 초경량이기 때문에 매우 작고 가벼운 MEMS형 센서만이 초소형 비행체 자동 비행 장치에 적용될 수 있다. 본 논문에서는 이러한 MEMS 형 관성센서의 항법 성능을 향상시키기 위해 가속도계와 자이로를 혼합하는 알고리즘으로 자세 비교 보상을 이용한 혼합 방법을 제시하고 기존의 퍼지 추정을 이용한 혼합 방법과 시뮬레이션을 통해 성능을 비교한다. 이를 통하여 자세 비교 보상 방법을 이용한 혼합 방법이 기존의 퍼지를 기반으로 하는 혼합 방법보다 초소형 비행체 자세 추정에 보다 더 우수한 성능을 가짐을 보인다.

• Journal of Astronomy and Space Sciences
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• 제26권1호
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• pp.47-58
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• 2009

In this study, a Hardware-In-the-Loop (HIL) simulator using thrusters is developed to validate the spacecraft attitude system. To control the attitude of the simulator, eight cold gas thrusters are aligned with roll, pitch and yaw axis. Also linear actuators are applied to the HIL simulator for automatic mass balancing to compensate the center of mass offset from the center of rotation. The HIL simulator consists of an embedded computer (Onboard PC) for simulator system control, a wireless adapter for wireless network, a rate gyro sensor to measure 3-axis attitude of the simulator, an inclinometer to measure horizontal attitude, and a battery set to supply power for the simulator independently. For the performance test of the HIL simulator, a bang-bang controller and Pulse-Width Pulse-Frequency (PWPF) modulator are evaluated successfully. The maneuver of 68 deg. in yaw axis is tested for the comparison of the both controllers. The settling time of the bang -bang controller is faster than that of the PWPF modulator by six seconds in the experiment. The required fuel of the PWPF modulator is used as much as 51% of bang-bang controller in the experiment. Overall, the HIL simulator is appropriately developed to validate the control algorithms using thrusters.

• 한국항공우주학회지
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• 제43권7호
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• pp.609-618
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• 2015

CNUSAIL-1은 태양돛을 탑재한 3U 크기의 큐브위성이다. 저궤도에서 태양돛을 전개하고, 이에 따른 자세와 궤도에 대한 영향을 확인하는 임무를 수행한다. 본 논문에서는 CNUSAIL-1을 위한 자세결정 알고리즘의 구현 가능성을 제시하였다. 위성의 기준센서는 태양센서, 3축 지자기센서를 이용하며, 관성센서는 MEMS 자이로센서를 사용한다. 큐브위성용 센서는 상대적으로 저가이며, 성능 및 잡음특성이 좋지 않은 단점이 있다. 따라서 자세결정 알고리즘으로 노이즈 특성을 고려할 수 있는 확장칼만필터를 적용하였다. 또한 자세결정의 결정론적 방법인 QUEST 알고리즘과 비교하여 그 타당성을 검증하였다.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.296-299
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• 2004

KARI precision attitude determination system has been developed for high accurate geo-coding of KOMPSAT-2 image. Sensor data from two star trackers and a IRU are used as measurement and dynamic data. Sensor data from star tracker are composed of QUEST and unit vector filter. Filter algorithms consists of extended Kalman filter, unscented Kalman filter, and least square batch filter. The type of sensor data and filter algorithm can be chosen by user options. Estimated parameters are Euler angle from 12000 frame to optical bench frame, gyro drift rate bias, gyro scale factor, misalignment angle of star tracker coordinate frame with respect to optical bench frame, and misalignment angle of gyro coordinate frame with respect to optical bench frame. In particular, ground control point data can be applied for estimating misalignment angle of star tracker coordinate frame. Through the simulation, KPADS is able to satisfy the KOMPSAT-2 mission requirement in which geo-location accuracy of image is 80 m (CE90) without ground control point.

• 전자공학회논문지
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• 제54권2호
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• pp.106-114
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• 2017

본 논문에서는 센서 결합을 이용하여 공간상의 시스템 자세를 정확히 추정할 수 있는 확장 칼만 필터를 설계하는 방법에 대해서 제안한다. 시스템 자세는 쿼터니언 상태 변수를 이용하여 표현하며, 이는 Gauss-Newton방법을 적용하여 가속도 센서와 지자기 센서로 부터 강체의 자세를 획득 하게 된다. 측정된 쿼터니언 값과 속도 센서 값, ARVR_SDK에 의한 영상 정보 값을 이용함으로써, 상태 변화를 추정 하게 되는데, 자세 추정의 정밀도를 높이기 위해 입력 값에 대한 에러를 보정하는 과정을 추가하여 적응적으로 입력 값을 조절하는 확장 칼만 필터를 설계 적용 하였다. 그 결과, 설계된 필터에 입력 값에 대한 오차가 있어도 일정부분 이를 보정하여 추정 값에 대한 신뢰도를 높이는 결과를 실험적으로 확인 할 수 있었다.