• Journal of Astronomy and Space Sciences
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• 제25권4호
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• pp.481-490
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• 2008

반작용휠은 인공위성의 기동 및 자세제어에 사용되는 주요 구동기 중의 하나로 회전체의 속도를 변화시켜 발생하는 토크로 위성의 자세제어를 수행하므로 정밀한 자세제어를 위해서는 정확한 회전속도의 측정이 요구된다. 타코 펄스를 이용한 고속 회전모터의 대표적인 속도 측정방법에는 Elapsed-time측정방법과 Pulse-count측정방법의 두 가지가 있으며 이 연구에서는 반작용휠의 속도 측정을 하는 동안 발생할 수 있는 속도 측정의 오차 및 정밀도를 두 가지 방법에 대해 분석, 비교하였다. 그 결과 Pulse-count측정방법은 반작용휠의 등속 구동 시 회전속도에 상관없는 일정한 오차를 가지는데 비해 Elapsed-time측정방법은 회전속도가 작을수록 오차가 줄어드나 저속일 때 오차가 현저히 커질 수 있음을 해석적으로 확인하였다.

• 한국항공우주학회지
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• 제43권11호
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• pp.998-1007
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• 2015

방사형 인공위성 경우, 관성곱이 커서 단일 입 출력 가정이 불가능하기 때문에 고전적 제어기 설계방법을 사용하기 어렵다. 본 논문에서 현대 제어 이론인 $H_{\infty}$ 제어기 설계이론을 사용하여 방사형 인공위성의 자세 제어기 설계를 수행하였다. 설계 알고리즘으로 보다 안정적인 LMI 방법이 사용되었고, 설계 결과에 대한 안정성과 성능에 대한 강건성 해석을 위해 ${\mu}$-해석 방법이 적용되었다. 설계 결과, 일반적인 경우와 다르게 제어기가 포함되지 않은 개루프보다 제어기가 포함된 개루프의 cross-over frequency가 더 낮게 설계되는 것이 관측되었다. 즉 상대적으로 큰 관성곱 영향 때문에 단지 weighting 함수 조정으로 위성 기동성을 증가시키는데 한계가 있는 것으로 해석된다. ${\mu}$-해석을 위해 +/-5%의 관성모멘트 변화를 가정하였다. 안정성 및 성능에 대한 강건성 해석결과, +/-7% 관성모멘트 변화까지 시스템 안정성 및 성능이 보장됨이 확인되었고, 관성곱 변화보다 주관성모멘트 변화가 안정성 및 성능 저하에 더 영향을 주는 것으로 확인되었다.

• Journal of Astronomy and Space Sciences
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• 제36권4호
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• pp.235-248
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• 2019

This paper suggests a relative orbit control strategy for the CubeSat Astronomy by NASA and Yonsei using Virtual Telescope Alignment eXperiment (CANYVAL-X) mission whose main goal is to demonstrate an essential technique, which is an arrangement among two satellites and a specific celestial object, referred to as inertial alignment, for a next-generation virtual space telescope. The inertial alignment system is a relative orbit control system and has requirements for the relative state. Through the proposed orbit control strategy, consisting of separation, proximity keeping, and reconfiguration, the requirements will be satisfied. The separation direction of the two CubeSats with respect to the orbital plane is decided to provide advantageous initial condition to the orbit controller. Proximity keeping is accomplished by differential atmospheric drag control (DADC), which generates acceleration by changing the spacecraft's effective cross section via attitude control rather than consuming propellant. Reconfiguration is performed to meet the requirements after proximity keeping. Numerical simulations show that the requirements can be satisfied by the relative orbit control strategy. Furthermore, through numerical simulations, it is demonstrated that the inertial alignment can be achieved. A beacon signal had been received for several months after the launch; however, we have lost the signal at present.

• 한국공작기계학회논문집
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• 제14권5호
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• pp.41-48
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• 2005

The Rotating transmission is made up of belts, mass disks and gears. This transmission is controlled electro-mechanically by the motor and operation program. The control strategy of the system can be to change belts' stiffness and the masses of mass disk and gear. This system can be modeled as a rigid body, and also finds broad application in such diverse fields as machine tools, the cruise control system In automobiles, and control in the attitude and gimbals of spacecraft. This Transmission proves the necessity and effect of a closed loop control. The study of the Rotating Transmission excited by its base motion is able not only to predict the rotational performance, but to obtain the fundamental data for vibration isolation. In this research, we compared the response characteristics of the two controllers by means of the experiments on PD controller and PID controller added on integral action. Furthermore, we studied the response abilities such as steady state error, overshoot, and ect. and the response velocities such as rising time, settling time, and ect. in the rotating transmission.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2005년도 추계학술대회 논문집
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• pp.715-720
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• 2005

The rotating transmission is made up of belts, mass disks and gears. This precise piece of equipment is controlled electro-mechanically by the mote. and operation program. The control strategy and the transmission can be changed by belts' stiffness and change of the mass and gear. This transmission can be modeled as a rigid body, and also finds broad application in such diverse fields as machine tools, the cruise control system in automobiles, and control in the attitude and gimbals of spacecraft. The study of the rotating transmission excited by its base motion is not only able to predict the rotational performance, but obtain the fundamental data for vibration isolation. In this thesis, we studied the response abilities such as steady overshoot, undershoot and ect. and the response velocities such as rising time, settling time, and ect. in the rotating transmission through PD control experiment.

• 한국항공우주학회지
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• 제49권5호
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• pp.389-397
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• 2021

인공위성의 자세제어 구동기인 제어모멘트자이로의 고장에 따른 제어 특성을 분석하였다. 특히, 4개 중에 한 개가 고장난 상황을 고려하였다. 가장 많이 사용되는 피라미드와 box-90 구조를 고려하였으며, 고장 발생 이후의 특이점 및 특이면을 분석하고 비교하였다. 모듈이 고장나고 휠 속도를 줄이는 과정에 대한 동역학 방정식을 유도하였다. 정상인 세 모듈이 고장난 모듈의 모멘텀을 흡수하면서 위성의 각속도를 안정화하는 과정을 분석하였는데, 특이형상에서 나머지 CMG가 교착되거나 과도하게 요동할 수 있는데, 짐벌각 재조정을 통하여 방지할 수 있음을 제시한다.

• Advances in aircraft and spacecraft science
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• 제2권1호
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• pp.45-56
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• 2015

The attitude aerodynamic control is an important subject in the design of an aerospace plane. Usually, at high altitudes, this control is fulfilled by thrusters so that the implementation of an aerodynamic control of the vehicle has the advantage of reducing the amount of thrusters fuel to be loaded on board. In the present paper, the efficiency of a wing-flap has been evaluated considering a NACA 0010 airfoil with a trailing edge flap of length equal to 35% of the chord. Computational tests have been carried out in hypersonic, rarefied flow by a direct simulation Monte Carlo code at the altitudes of 65 and 85 km, in the range of angle of attack 0-40 deg. and with flap deflection equal to 0, 15 and 30 deg.. Effects of the flap deflection have been quantified by the variations of the aerodynamic force and of the longitudinal moment. The shock wave-boundary layer interaction and the shock wave-shock wave interaction have been also considered. A possible interaction of the leading edge shock wave and of the shock wave arising from the vertex of the convex corner, produced on the lower surface of the airfoil when the flap is deflected, generates a shock wave whose intensity is stronger than those of the two interacting shock waves. This produces a consistent increment of pressure and heat flux on the lower surface of the flap, where a thermal protection system is required.

• 천문학논총
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• 제15권spc2호
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• pp.57-64
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• 2000

It is realized that the extraterrestrial matter is in ionized state, plasma, so the matter of this kind behaves as not expected because of its sensitiveness to electric and magnetic fields and its ability to carry electric currents. This kind of subtle change can be observed by an instrument for the magnetic field measurement, the magnetometer usually mounted on the rocket and the satellite, and based on the ground observatory. The magnetometer is a useful instrument for the spacecraft attitude control and the Earth's magnetic field measurements for the scientific purpose. In this paper, we present the preliminary design and the test results of the two onboard magnetometers of KARl's (Korea Aerospace Research Institute) sounding rocket, KSR­III, which will be launched during the period of 2001-02. The KSR-III magnetometers consist of the fluxgate magnetometer, MAG/AIM (Attitude Information Magnetometer) for acquiring the rocket flight attitude information, and of the search-coil magnetometer, MAG/SIM (Scientific Investigation Magnetometer) for the observation of the Earth's magnetic field fluctuations. With the MAG/AIM, the 3-axis attitude information can be acquired by the comparison of the resulting dc magnetic vector fields with the IGRF (International Geomagnetic Reference Field). The Earth's magnetic field fluctuations ranging from 10 to 1,000 Hz can also be observed with the MAG/SIM measurement.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2005년도 제25회 추계학술대회논문집
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• pp.426-430
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• 2005

통신해양기상위성(COMS)는 국내 최초로 개발되는 3축 안정화 복합위성으로 2008년에 지구정지궤도(GEO, Geostationary Earth Orbit)에 발사될 예정이다. 통신해양기상위성 추진시스템은 위성체의 지구정지궤도 진입, 자세 및 궤도 제어/조정을 위하여 요구되는 추력과 토오크를 제공한다. 본 논문은 통신해양기상위성 추진시스템의 시스템 설계 및 주요 부품의 성능에 관하여 기술하고자 한다.

• International Journal of Aeronautical and Space Sciences
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• 제6권1호
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• pp.61-70
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• 2005

The currently developed propulsion system(PS) is composed of propellant tank, valves, thrusters, interconnecting line assembly and thermal hardwares to prevent propellant freezing in the space environment. Comprehensive engineering analyses in the structure, thermal, flow and plume fields are performed to evaluate main design parameters and to verify their suitabilities concurrently at the design phase. The integrated PS has undergone a series of acceptance tests to verify workmanship, performance, and functionality prior to spacecraft level integration. After all the processes of assembly, integration and test are completed, the PS is integrated with the satellite bus system successfully. At present, the severe environmental tests have been carried out to evaluate functionality performances of satellite bus system. This paper summarizes an overall development process of monopropellant propulsion system for the attitude and orbit control of LEO(Low Earth Orbit) observation satellite from the design engineering up to the integration and test.