• Proceedings of the Korean Society of Precision Engineering Conference
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• 2009.10a
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• pp.405-406
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• 2009

• Journal of Astronomy and Space Sciences
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• v.36 no.1
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• pp.11-20
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• 2019

Being a torque free motion of the rotating Earth, Chandler wobble is the major component in the Earth's polar motion with amplitude about 0.05-0.2 arcsec and period about 430-435 days. Free core nutation, also called nearly diurnal free wobble, exists due to the elliptical core-mantle boundary in the Earth and takes almost the whole part of un-modelled variation of the Earth's pole in the celestial sphere beside precession and nutation. We hereby present a brief summary of their theories and report their recent features acquired from updated datasets (EOP C04 and ECMWF) by using Fourier transform, modelling, and wavelet analysis. Our new findings include (1) period-instability of free core nutation between 420 and 450 days as well as its large amplitude-variation, (2) re-determined Chandler period and its quality factor, (3) fast decrease in Chandler amplitude after 2010.

• Proceedings of the KIEE Conference
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• 1994.07a
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• pp.125-128
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• 1994

One of the abnormal motions of the projectile in the coil gun is spinning. It is found that the spinning force is closely related with air gap distance. Modified and detail analysis for the spinning is suggested in this paper. Two reasons for spinning force and Lorentz force affecting on the spinning are introduced. Nutation, which is a result of spinning, is explained there after.

• International Journal of Aeronautical and Space Sciences
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• v.18 no.1
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• pp.99-107
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• 2017

In this work, the nutation control of rigid spacecraft with only two momentum wheels is addressed by applying the feedback linearization technique. In this strategy, the primary performance index is to regulate the nutational angle by the momentum control of wheels. The spacecraft attitude equations of motion are transformed to a general linearized form by feedback linearization technique, including a guaranteed control law promising the internal dynamics stability to accomplish the nutation angle small. It is proven that the configuration of inertia properties plays a key role in analyzing spacecraft energy level. The behavior of the momentum wheels is also studied analytically and numerically. Finally, the effectiveness of the proposed nonlinear control law for the momentum transfer is verified by conducting numerical simulations.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2007.11a
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• pp.159-162
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• 2007

뉴테이션(Nutation, 장동)은 자이로스코프와 같은 큰 축 대칭 물체의 회전축에 대해 작은 불규칙적인(어원적으로 "nodding") 운동이다. 위성체가 회전상태에 돌입하게 될 때 위성체가 순수한 회전 운동이 아닌 뉴테이션 운동을 일으킬 경우, 이를 제거하기 위하여 뉴테이션댐퍼(NutationDamper)를 사용한다. 유도탄에 들어가는 부품 중에서 자이로조립체 내에 들어 있는 뉴테이션댐퍼의 개발을 하고자 본 연구를 수행 하게 되었으며, 자이로조립체 내에서 뉴테이션댐퍼의 역할은 자이로조립체의 원주상에 환형 튜브 형상으로 장착되어 자이로조립체가 세차운동(Precession)을 할 때 부가적으로 수반되는 바람직하지 못한 떨림(Wobble motion)인 뉴테이션을 감쇠시키는 기능을 수행한다.

• Bulletin of the Korean Chemical Society
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• v.19 no.5
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• pp.519-524
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• 1998

In this work, we applied the 1D 11B nutation NMR method for the analysis of the local structural environments in powdered borosilicates (SiO2-B2O3). Spin dynamics during a rf irradiation for spin I=3/2 was analytically calculated with a density matrix formalism. Spectral simulation programs were written in MATLAB on a PC. Two borosilicates prepared by the sol-gel process at different stabilization temperature were used for the 1D 11B nutation NMR experiment. The 11B NMR parameters, quadrupole coupling constants (e2qQ/h) and asymmetry parameters (η), for each borosilicate were extracted from the nonlinear least-squares fitting. The effects of heat treatments on the local structures of boron sites in borosilicates were discussed.

• Journal of The Korean Astronomical Society
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• v.40 no.2
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• pp.49-60
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• 2007

This paper deals with the theory for rotational motion of a two-layer Earth model (an inelastic mantle and liquid core) including the dissipation in the mantle-core boundary(CMB) along with tidal effects produced by Moon and Sun. An analytical solution being derived using Hori's perturbation technique at a second order Hamiltonian. Numerical nutation series will be deduced from the theory.

• Journal of Astronomy and Space Sciences
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• v.11 no.2
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• pp.281-295
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• 1994

In this paper, the Variable Structure System(VSS) theory with new continuous switching dynamic equation is used to design an automatic controller for the active nutation damping in momentum bias stabilized spacecraft. In the application of VSS theory to a linearized multivariable system with the nutation damping systems, there exist some disadvantages such as how to determine the switching gains and how to reduce the chattering phenomina and reaching phase in input and state trajectories. To solve these drawbacks, this paper presents the continuous switching dynamic equation instead of the discontinuous switching logics to obtain the sliding mode. The new design approach is much simpler than the VSS theory. And there do not exist chattering phenomina in this method because the obtained control inputs are continuous. Simultaneously the reaching phase is reduced by a suitable choice of design factor.

• Journal of Korean Physical Therapy Science
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• v.2 no.2
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• pp.545-562
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• 1995

The purpose of this paper was to provide the understanding of theory, technique, clinical use about arthro kinematic approach. Difference between AKA and Joint mobilization was seen through Table 1, and the relation between AKA and Athro kinematics was seen through Table 2. Examples of AKA techniques were as follow ; 1. Cervical intervertebral joint, left $C_{2/3}$ 2. Thoracic intervertebral joint, left $T_{5/6}$ 3. Sacroiliac joint, left (1) Nutation-upward gliding (2) Nutation-downward gliding (3) Superior distraction (4) Inferior distraction 4. 1st. costovertebral joint, left 5. 2nd. sternocostal joint, left 6. AKA-streching exercise 7. AKA - resistive exercise Symptoms, diagnosis, treatment were discribed for clinical use, and they were expected further that clinical application of AKA might clarify many of joint dysfunction.

• 제어로봇시스템학회:학술대회논문집
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• 1996.10b
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• pp.1099-1102
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• 1996

In this paper, roll/yaw attitude control of spacecraft using a double gimbaled wheel is discussed with two feedback controllers designed. One is a PD controller with no phase difference between roll and yaw control input. The other is a PD controller with a phase lag compensator about the yaw control input. The phase lag compensator is designed as a first order system and a lag parameter is designed for the yaw angle control. There are two case simulations for each controller ; constant disturbance torques and initial errors of nutation at motion. We obtain the results through simulations that steady-state error and rising time of yaw angle are determined by the compensator. Simulation parameters used in this study are the values of KOREASAT F1.