• 충청수학회지
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• 제25권4호
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• pp.739-745
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• 2012

We show that if a symplectic diffeomorphism has the $C^1$-robustly orbital shadowing property, then the diffeomorphism is Anosov.

• 대한수학회보
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• 제53권2호
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• pp.581-588
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• 2016

Komuro [3] proved that geometric Lorentz attractor does not satisfy the shadowing property. In this paper we study the condition under which geometric Lorenz attractor has the orbital shadowing property that is weaker than the shadowing property.

• 소성∙가공
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• 제14권1호
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• pp.29-36
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• 2005

In this paper, a useful rigid-plastic finite element method with various numerical schemes is presented for simulation of an orbital forming process. A new approach to reduce volume change during simulation is presented and an approximation method to reduce computational time is also presented. An actual orbital forming process found in a bearing making industry is simulated by the presented approach. The simulated results of the orbital forming process are compared with the experimental results.

• 제어로봇시스템학회논문지
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• 제6권10호
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• pp.936-941
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• 2000

Advanced space transportation systems, such as the National Aerospace Plane or an Orbital Transfer Vehicle, have atmospheric maneuvering capabilities. For such vehicles the use of aeroassisted orbital transfer from a high Earth orbit to a low Earth orbit, with unpowered flight in the atmosphere, has the potential for significant fuel savings compared to exoatmospheric Hohmann transfer. However, to exploit the fuel savings that can be achieved by using the Earths atmosphere to reduce the vehicles energy, a guidance law is required, and it must be able to handle large unpredictable fluctuations in atmospheric density, on the order of ${\pm}$50% relative to the 1962 US Standard Atmosphere. In this paper aeroassisted orbital transfer is considered as a differential game, with Nature controlling the atmosphere density to yield a worst case (min-max fuel required) atmosphere, from which the guaranteed playable set boundary are achieved. Inside the playable set, it is guaranteed that the vehicle achieves the optimal atmospheric exit condition for the minimum fuel consumption regardless of the atmospheric density variations.

• Archives of Plastic Surgery
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• 제33권2호
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• pp.252-254
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• 2006

The dermoid cyst is the one of common space occupying orbital lesion. This lesion is regarded as a non-invasive tumor, but infrequently causes destruction of adjacent bony structure and displacement of adjacent tissue. We experienced a characteristic ovoid orbital dermoid cyst that occupied in the frontal sinus and causes displacement of the eyeball with well-defined lining. This 55-year-old male presented a mass in left orbit, which rapidly increased in size for past 12 months, and patient could not open left eyelid. We removed this tumor totally then reconstructed the orbital roof and frontal sinus with an iliac bone graft and polyethylene sheet(Medpor Newnan, USA). This patient was followed up for 12 months and patient obtained satisfactory result without any complication suck as recurrence or infection.

• 대한세포병리학회지
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• 제5권2호
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• pp.176-179
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• 1994

Orbital meningioma is a rare neoplasm that, even when suspected by CT or echographic examination, requires careful histologic study for precise identification. Fine needle aspiration(FNA) biopsy has become the diagnostic technique of choice in recent years for investigating orbital masses. There have been a few previous reports on FNA biopsy of orbital menigioma. We experienced a case of orbital meningioma in a 11-yr-old boy, diagnosed by FNA biopsy. The cytohistologic features of aspirated material (intranuclear inclusions, psammoma bodies, and cells arranged in whorls) made it easy to diagnose a meningloma.

• 천문학논총
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• 제30권2호
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• pp.69-71
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• 2015

In our previous work, we investigated the orbital dynamics of Asteroid 1934 CT (or 1989 AC or 4179 Toutatis) from epoch 2012-Jul-24 (JDE2456132.5) using the Mercury program package. Asteroid 4179 Toutatis has an Earth and Mars crossing orbit with semimajor axis a = 2.5292 AU and eccentricity e = 0.6294, and therefore the perihelion distance is q = 0.9373 AU and the aphelion distance is Q = 4.1211 AU. After more than 300,000 years, asteroid 4179 Toutatis will escape from the Solar System, but during this time, it will have close-encounters with other planets from Venus to Uranus. As a continuation of this project, we investigated its energy changes in each close encounter. We also determine the energy of this asteroid when it escapes from the Solar System. The result is that during its orbital evolution, the energy of this asteroid changes and gives us negative, zero and positive values.

• Bulletin of the Korean Chemical Society
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• 제3권3호
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• pp.98-103
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• 1982

Extended Huckel calculations have been performed to obtain molecular orbital energies and the corresponding eigenvectors for $[M(III)O_3S_3]$ type complexes [M(111) = V(111), Cr(III), Mn(III), Fe(III) and Co(III)] adopting the valence basis set orbital $(nP_z)$ and the hybridized atomic orbital of ligands. The effects of the hybridized atomic orbital of ligands on the calculated dipole moments and 10 $D_q$ values are investigated. The calculated 10 $D_q$ values and dipole moments are close to the experimental values when the hybridized atomic orbital of ligands is used to obtain the eigenvector for $[M(III)O_3S_3]$ type complexes.

• Nonlinear Functional Analysis and Applications
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• 제28권4호
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• pp.929-942
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• 2023

In this paper, we discuss topological ergodic shadowing property and topological pseudo-orbital specification property of iterated function systems(IFS) on uniform spaces. We show that an IFS on a sequentially compact uniform space with topological ergodic shadowing property has topological shadowing property. We define the notion of topological pseudo-orbital specification property and investigate its relation to topological ergodic shadowing property. We find that a topologically mixing IFS on a compact and sequentially compact uniform space with topological shadowing property has topological pseudo-orbital specification property and thus has topological ergodic shadowing property.

• Journal of Astronomy and Space Sciences
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• 제32권4호
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• pp.367-377
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• 2015

Atmospheric drag force is an important source of perturbation of Low Earth Orbit (LEO) orbit satellites, and solar activity is a major factor for changes in atmospheric density. In particular, the orbital lifetime of a satellite varies with changes in solar activity, so care must be taken in predicting the remaining orbital lifetime during preparation for post-mission disposal. In this paper, the System Tool Kit (STK$^{(R)}$) Long-term Orbit Propagator is used to analyze the changes in orbital lifetime predictions with respect to solar activity. In addition, the STK$^{(R)}$ Lifetime tool is used to analyze the change in orbital lifetime with respect to solar flux data generation, which is needed for the orbital lifetime calculation, and its control on the drag coefficient control. Analysis showed that the application of the most recent solar flux file within the Lifetime tool gives a predicted trend that is closest to the actual orbit. We also examine the effect of the drag coefficient, by performing a comparative analysis between varying and constant coefficients in terms of solar activity intensities.