• 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.

• 한국항공운항학회지
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• 제23권4호
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• pp.140-145
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• 2015

An on-board reaction wheel is payload of small satellite for space environment test. The reaction wheel is designed for considering physical, electrical, and environmental requirements. In this paper, we report design, manufacturing process and operation performance verification. Furthermore, the specifications of environmental test are performed under environmental conditions for guarantee of stability and reliability. The operation and environment test results are presented to meet the requirements at the reaction wheel flight model.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.56.5-56
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• 2001

In the three axis control of satellite by using reaction wheel and gyro, a reaction wheel produces the control torque by the wheel speed or momentum, and a gyro carries out measuring of the attitude angle and the attitude angular velocity In this study, dynamic modelling of the Low Earth Orbit (LEO) is consisted of the one from the rotational motion of the satellite with the basic rigid body and a flexible body model, and the gyro in addition to the reaction wheel model. The results obtained by the robust controller are compared with those of the PI (Proportional and Integration) controller which is commonly used for the stabilizing satellite.

• International Journal of Aeronautical and Space Sciences
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• 제15권2호
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• pp.190-198
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• 2014

The pyramidal reaction wheel arrangement is one of the configurations that can be used in attitude control simulators for evaluation of attitude control performance in satellites. In this arrangement, the wheels are oriented in a pyramidal configuration with a tilt angle. In this paper, a study of pyramidal reaction wheel arrangement is carried out in order to find the optimum tilt angle that minimizes total power consumption of the system. The attitude control system is analyzed and the pyramidal configuration is implemented in numerical simulation. Optimization is carried out by using an iterative process and the optimum tilt angle that provides minimum system power consumption is obtained. Simulation results show that the system requires the least power by using optimum tilt angle in reaction wheels arrangement.

• 한국항공우주학회지
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• 제32권3호
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• pp.45-50
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• 2004

위성의 성공적인 임무 수행을 위한 자세 안정화와 성능요구조건을 만족하기 위해서 반작용휠 제어로직의 설계가 중요하다. 실제 위성궤도 상에서 발생하는 여러 가지 불확실성으로 인해 지상실험을 통해 획득한 모델 파라미터 값들만으로 제어로직을 설계하는데 한계가 있다. 그러므로 위성이 궤도상에 있을 때의 반작용휠 입력 및 출력 데이터를 이용하여 모델 파라미터를 보정하고 자세제어기에 반영하는 것이 요구된다. 본 논문에서는 다목적실용위성의 Telemetry 데이터를 활용한 시스템인식 (System Identification)을 수행하였고, 이를 통한 반작용휠의 모델 파라미터를 추출한다. 또한, 반작용휠을 모델링 하고 또한 제어기설계에 사용된 모델 파라미터를 추출하여 지상실험 데이터와 비교분석한다.

• Journal of Biosystems Engineering
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• 제25권3호
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• pp.179-186
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• 2000

Interactions between wheel lug surfaces and soil were analyzed through wheel motion. In this paper, lug surfaces such as trailing and leading lug sides and a lug face were analyzed and reported. The interactions between the surfaces and soil were expressed as the horizontal and vertical directions of resultant forces acting on the surfaces. There analysis indicated qualitatively that (1) the trailing lug side is mainly related to produce motion resistance and reaction to dynamic load, (2) the lug face is related to produce not only the motion resistance, the reaction to the dynamic load but also the traction and (3) the leading lug side is mainly related to produce the traction and the reaction to the dynamic load. Experiments were conducted to prove the results of the motion analysis. Normal and tangential forces acting on the surfaces were measured, and the traction, the motion resistance and the reaction to the dynamic load were calculated with wheel rotational and lug design angles. The experiments proved that the results of wheel motion analyses above mentioned as (1), (2) and obtained from the analysis were correct.

• 전자공학회논문지SC
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• 제46권6호
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• pp.9-13
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• 2009

반작용과 자이로를 사용하는 저궤도 위성체의 3축 제어에서 반작용휠은 휠 속도나 운동량으로 제어토크를 만들고 자이로는 자세각과 자세각속도를 측정한다. 본 논문에서 저궤도 위성체의 다이나믹 모델링은 기본적인 본체만을 고려한 강체에 태양전지판 등을 고려한 연성체의 회전운동방정식과 반작용휠로 구성된다. 강인제어기$(H_\infty)$는 외란에 의한 모델이 가변될 수 있는 강체 및 연성체를 포함한 플랜트를 안정화시키기 위해 적용하였으며, 기존 저궤도 위성체를 안정화시키기 위해 사용된 PI 제어기와 성능을 비교하여 자세제어에 필요한 위상제어의 우수성을 보여주는데 있다.

• 항공우주기술
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• 제13권2호
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• pp.47-53
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• 2014

본 논문은 위성의 정밀 자세제어를 위해 사용하는 반작용 휠에 대한 소프트웨어 모델을 시뮬링크로 구현한 것에 대한 소개문서이다. 반작용 휠의 전기적인 특성 파라미터를 셋팅하고, 위성에 반작용 휠들이 장착되는 장착 각을 설정할 수 있는 기계적인 항목들 또한 포함하고 있다. 반작용 휠의 모델 방정식을 전기적 모터 방정식으로부터 유도하여, 이를 정리하였다. 또한, 구현한 반작용 휠 시뮬링크 모델을 강체에 적용하여 구동결과를 보여주고 있다.

• 한국소음진동공학회논문집
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• 제26권4호
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• pp.391-397
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• 2016

Vibration disturbances induced by the reaction wheels can severely degrade the performance of high precision payloads on board satellites with high pointing stability requirements. The unwanted disturbances produced by the reaction wheels are composed of fundamental harmonic disturbances due to the flywheel imbalance and sub/higher harmonic disturbances due to bearing irregularities, motor imperfections and so on. Because the wheel speed is constantly changed during the operation of a reaction wheel, the vibration disturbance induced by the reaction wheels can magnify the satellite vibration when the rotating frequency of wheel meets the natural frequency of satellite structure. In order to provide an effective isolation of the reaction wheel disturbances, isolation performance of a hybrid vibration isolator is investigated. In this paper, hybrid vibration isolator that combines passive and active components is developed and its hybrid isolation performance using notch filter control is evaluated in single-axis. The hybrid isolation performance using notch filter control show additional performance improvement compared to the results using only passive components.

• 한국항공우주학회지
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• 제45권11호
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• pp.967-974
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• 2017

반작용휠은 저속구간에서 마찰로 인해서 비선형 토크 응답을 보인다. 따라서 이 구간에서는 위성의 정밀한 자세제어를 달성하기 어렵다. 기존 연구들은 마찰력 보상이나 디더명령을 인가하는 방법을 사용하여 본 문제를 해결하려 하였다. 하지만 마찰력 모델링의 어려움이나 휠속도의 빈번한 영점 교차 때문에, 이러한 방법을 실제 위성 자세제어에 적용하기에는 어려움이 있다. 이를 해결하기 위해서, 자세오차에 따라서 자세제어기의 이득값을 조절하는 방법을 제안한다.