• 한국항해항만학회지
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• 제31권9호
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• pp.751-757
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• 2007

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.

• 한국항해항만학회지
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• 제28권8호
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• pp.653-657
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• 2004

이 논문은 자유자이로의 방향보존성을 이용하여 위치를 결정하는 방법을 이론적으로 유도한 것이다. 즉, 임의 위치에서 두 대의 자유자이로 회전축의 경사각과 기준 위치로부터 측정한 경과 시간을 기본 요소로 하여 위치를 결정하는 시스템을 제시하고 이 시스템을 구축할 때 나타나는 문제점을 열거하였다.

• 제어로봇시스템학회논문지
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• 제12권6호
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• pp.608-613
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• 2006

Any input acceleration that bends RLG dithering axis causes flexure error, which is a source of the noncommutative error that can not be compensated by simply using integrated gyro sensor output. This paper introduces noncommutative error equations that define attitude errors caused by flexure errors. In this paper, flexure error is classified as sensor level error if the sensing axis coincides with the dithering axis and as system level error if the two axes do not coincide. The relationship between gyro output and the rotation vector is introduced and is used to define the coordinate transformation matrix and angular motion. Equations are derived for both sensor level and system level flexure error analysis. These equations show that RLG based INS attitude error caused by flexure is directly proportional to time, amount of input acceleration and the dynamic frequency of the vehicle.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2004년도 ICCAS
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• pp.1747-1753
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• 2004

CMG(Control Momentum Gyro) is a control device being used for spacecraft attitude control constructing relatively large amount of torque compared to conventional body-fixed reaction wheels. The CMG produces gyroscopic control torque by continuously varying the angular momentum vector direction with respect to the spacecraft body. The VSCMG(Variable Speed Control Momentum Gyro) has favorable advantages with variable speed to lead to better control authority as well as singularity avoidance capability. Attitude dynamics with a VSCMG mounted on a two-axis gimbal system are derived in this study. The dynamic equation may be considered as an extension of the single-axis counterpart. Also, a feedback control law design is addressed in conjunction with the dynamic equations of motion.

• 제어로봇시스템학회논문지
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• 제2권3호
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• pp.242-247
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• 1996

In this paper, an optimal coning compensation algorithm for strapdown system is proposed by minimizing the coning error. The proposed algorithm is derived as a generalized form in that it contains the class of the existing coning algorithms and allows the design of optimal algorithm for various combinations of gyro samples. It is shown the magnitude of resulting algorithm errors depends mainly on the total number of gyro samples including present and previous gyro samples. Based on the results, the proposed algorithm enables the algorithm designers to develop the effective coning compensation algorithm according to their attitude computation specifications with ease. In addition, the multirate method which can efficiently implement the algorithm is presented.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2007년도 심포지엄 논문집 정보 및 제어부문
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• pp.352-354
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• 2007

This paper presents a method to estimate the position of a mobile robot by using a gyro sensor and accelerometer sensors on it. Together with contact sensors we propose a mapmaking algorithm for an indoor environment where the robot moves. The direction of robot can be estimated through a gyro sensor and the distance is founded out by accelerometers. Then one can presume the position of robot. Using the direction and distance values vector-based mapmaking job can be performed. Tactile sensors help the robot recognize the boundary limit value of indoor environment and decide outer wall line of the map.

• 한국항공우주학회지
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• 제34권1호
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• pp.81-88
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• 2006

본 논문에서는 RLG를 사용하는 관성항법시스템에서 자이로 출력의 적분 과정에서 유발되는 비교환 오차를 정의하고 이에 대한 해석을 수행한다. 이를 위하여 RLG를 사용하는 관성항법시스템에 나타나는 진동성 운동, 원추운동, AV 마운트에 의하여 유발되는 ISA 운동, 항체의 실제 운동 등을 살펴보고, 각각의 운동에 의하여 유발되는 비교환 오차를 해석한다. 비교환 오차 해석은 회전벡터와 자이로 출력 사이의 관계식과 좌표변환행렬과 각속도 벡터 사이의 관계식을 이용하여 유도된다.

• 우주기술과 응용
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• 제3권4호
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• pp.322-332
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• 2023

Satellite attitude-control actuators are equipped with a reaction wheel for three-axis attitude control. The reaction wheel rotates a motor inside the actuator to generate torque in the vector direction. When using the reaction wheel, there are restrictions on the torque values generated as the motor rotates. The torque value of the reaction wheels mounted on small satellites is approximately 10 mNm, and high values are not used. Therefore, three-axis attitude control of a small satellite is possible using a reaction wheel, but this method is not suitable for missions that require rapid attitude control at a specific time. As a technology to overcome the small torque value of the reaction wheel, the control moment gyro (CMG) is currently in wide use as a rapid attitude-control actuator in space satellites. The CMG has an internal gimbal mounted at a right angle to the rotation motor and generates a large torque value. In general, when the gimbal operates, a torque value approximately 100 times greater is generated, making it suitable for rapid posture maneuvering. Currently, we are developing a technology for mounting a controlled moment gyro on a small satellite, and here we share the development status of an 800 mNm CMG.

• 한국항공우주학회지
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• 제43권2호
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• pp.133-140
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• 2015

본 논문에서는 단일 저가형 범용 GPS 수신기와 롤 축 각속도계를 이용하여 롤 회전 비행체의 롤 자세각을 결정하는 기법을 제안한다. 비행체에 부착된 GPS 수신기의 신호 수신강도는 GPS안테나가 향하는 방향과 비행체의 종축이 이루는 평면 내에 GPS위성이 존재할 때 최대가 된다. 비행체의 종축이 속도벡터와 일치한다고 가정하면, 비행체에 대한 GPS위성의 상대위치벡터를 이용하여 GPS 안테나 신호가 최대일 때의 롤 각을 결정할 수 있다. 롤 각 결정의 정밀도를 높이기 위해 롤 축 각속도계를 이용한 칼만필터를 구성하였다. 6-자유도 시뮬레이션을 통해 제안된 방법의 성능을 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.