• 한국콘텐츠학회논문지
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• 제12권8호
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• pp.264-273
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• 2012

본 연구는 아급성 뇌졸중 환자를 대상으로 컴퓨터화된 시각적 되먹임 균형 훈련 및 평가 장비인 space balance 3D와 기능적 검사인 tinetti mobility test (TMT)의 신뢰도 및 버그균형척도와의 동시타당도를 분석하기 위해 실시하였다. 아급성 뇌졸중 환자 총 23명을 대상으로 하였고 대상자에게 space balance 3D, TMT, 버그균형척도를 이용해 균형 능력 평가를 실시하였다. 검사-재검사간 신뢰도에서 space balance 3D의 정적균형과 동적균형은 중등도의 신뢰도를 보인반면, TMT의 세가지 점수와 버그균형척도는 높은 신뢰도를 보였다. 동시타당도에서 TMT의 세가지 점수, 버그균형척도, space balance 3D의 정적균형간에 각각 중등도의 유의한 (p<.01) 양의 상관관계를 보였다. TMT의 세가지 점수와 버그균형척도는 space balance 3D의 동적균형의 후좌측, 전좌측 방향과는 각각 유의한 (p<.05) 낮은 양의 상관관계를 보였지만 나머지 방향과는 유의한 상관관계를 보이지 않았다. 따라서 space balance 3D와 TMT의 균형 능력 평가는 아급성 뇌졸중 환자의 균형 능력을 평가하는데 유용하게 쓰일 수 있을 것으로 보이나 space balance 3D의 동적균형 평가는 한계점이 있었다.

• PNF and Movement
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• 제13권1호
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• pp.47-53
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• 2015

Purpose: This study examined the effects of space fabric type air insole pressure differences on young adults' dynamic balance ability. Method: The subjects of this study were 17 young female adults without musculoskeletal system disease. Balance ability was measured by dividing the subjects into three groups: an experimental group which did not wear an air insole (insole-off group), an experimental group which wore an air insole to which air pressure of $0.55kg/cm^2$ was applied (insole-0.55 group), and an experimental group which wore an air insole to which air pressure of $0.75kg/cm^2$ was applied (insole-0.75 group). For dynamic balance, the subjects stood on a balance pad, and perimeter length and medium speed were measured three times. The averaged values were recorded and statistically processed. Result: There were significant differences in average speed, and the insole-0.75 group's average speed decreased compared to the insole-off group and the insole-0.55 group. Although the total movement distance did not statistically differ, the insole-75 group's movement distance decreased compared to the insole-off group and the insole-0.55 group. Conclusion: Application of a space fabric type air insole, in particular insole-0.75, was helpful in improving balance ability. This is considered to occur because the space fabric structure was conducive to decreasing sway and producing balance.

• Journal of Power Electronics
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• 제16권6호
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• pp.2109-2118
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• 2016

Based on the space vector pulse width modulation (SVPWM) theory, this paper realizes an easier SVPWM strategy, which is equivalently implemented by CBSPWM with zero-sequence voltage injection. The traditional SVPWM strategy has no effect on controlling the neutral-point voltage balance. In order to solve the neutral-point voltage unbalance problem for neutral-point-clamped (NPC) three-level inverters, this paper proposes a neutral-point voltage balance controller. The proposed controller realizes controlling the neutral-point voltage balance by dynamically calculating the offset superimposed to the three-phase modulation waves of an equivalent SVPWM strategy. Compared with the traditional SVPWM strategy, the proposed neutral-point voltage balance controller has a strong ability to balance the neutral-point voltage, has good steady-state performance, improves the output waveforms quality and is easy for digital implementation. An experiment has been carried out on a NPC three-level inverter prototype based on a digital signal processor-complex programmable logic device (DSP-CPLD). The obtained experimental results verify the effectiveness of the proposed neutral-point voltage balance controller.

• International Journal of Aeronautical and Space Sciences
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• 제1권2호
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• pp.68-74
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• 2000

A comparative wind tunnel testing of an airplane model was performed at the Korea Aerospace Research Institute Low Speed Wind tunnel(KARI LSWT). The model used for the comparative test was a seaplane model from the Glenn L. Martin Wind(GLM) Tunnel of University of Maryland, U.S.A. The 6-component external balance used in force and moment measurement is pyramidal type, which is a precision device that has strain gauge-type load cell inside of balance and the virtual center of the balance coincides with the tunnel centerline. Image method is adopted to eliminate the tare and interference of the model support, and to correct the flow angularity to the model also. Test results from KARI LSWT were compared with the results from GLM tunnel.

• 한국항공우주학회지
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• 제35권9호
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• pp.850-857
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• 2007

인공위성 전력계의 설계 분석은 위성 전체의 무게, 크기 및 성능을 결정하는 중요 변수로 작용한다. 특히 위성체 에너지 균형 분석의 경우 전력 시스템의 용량, 설계 제한 조건의 결정 및 위성체 운영 성공 여부를 결정할 수 있는 중요한 분석이다. 본 논문에서는 저궤도 위성 개발을 위한 새로운 에너지 균형 분석 프로그램을 소개하고 타 저궤도 위성 설계 자료를 이용한 시험 결과를 일례로 기술하였다. 시험 결과 본 논문에서 제안한 에너지 균형 분석 프로그램은 위성체 전력계의 최적 사이징 뿐 아니라 위성체 운영 기간 동안 궤도상에서의 위성체 에너지 균형 상황 예측에도 활용할 수 있음을 보였다.

• 한국항공우주학회지
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• 제38권12호
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• pp.1153-1161
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• 2010

본 연구에서는 주기적 비정상 유동 해석을 위해 푸리에 변환을 이용하는 조화 균형법의 효율적인 해법을 제안한다. 내재적으로 유속항을 처리하고 외재적으로 조화 원천항을 처리하였다. 외재적 조화 균형법 보다 더 빠르게 수렴 시킬 수 있으며 내재적 조화 균형법을 적용할 때 추가되는 자코비안 행렬을 처리할 필요가 없다. 또한 완전 내재적 기법에 상응하는 수준의 수렴안정성을 확인할 수 있었다. 2차원 비정상 유동 문제로 피칭하는 NACA0012 익형에 적용하였으며 이중 시간 적분법 및 외재적 Runge-Kutta기법의 해와 매우 일치하는 결과를 얻었다.

• Journal of Astronomy and Space Sciences
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• 제34권3호
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• pp.225-235
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• 2017

The energy balance in a satellite needs to be designed properly for the satellite to safely operate and carry out successive missions on an orbit. In this study, an analysis program was developed using the MATLAB(R) graphic user interface (GUI) for nanosatellites. This program was used in a simulation to confirm the generated power, consumed power, and battery power in the satellites on the orbit, and its performance was verified with applying different satellite operational modes and units. For data transmission, STK(R)-MATLAB(R) connectivity was used to send the generated power from STK(R) to MATLAB(R) automatically. Moreover, this program is general-purpose; therefore, it can be applied to nanosatellites that have missions or shapes that are different from those of the satellites in this study. This power simulation tool could be used not only to calculate the suitable power budget when developing the power systems, but also to analyze the remaining energy balance in the satellites.

• 한국항공우주학회지
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• 제37권3호
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• pp.301-306
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• 2009

본 연구에서는 축소형 로터 실험 장치에서 로터 회전면에 수직으로 작용하는 추력(Fz)과 평행으로 작용하는 2축 모멘트(Mx, My)를 측정할 수 있는 3분력 Rotating Balance를 설계, 제작하고 성능실험을 통하여 검증하였다. Rotating Balance에 장착된 스트레인게이지의 미세신호는 로터와 함께 회전하는 신호증폭기를 거쳐 증폭되어 slip ring을 통하여 데이터 취득장치로 전달되어진다. 정적 보정법을 통하여 얻어진 보정행렬식의 적합성 여부를 판단하기 위하여 기존에 개발된 reaction type balance를 사용하여, 로터가 회전시 발생하는 추력을 비교함으로서 측정 정밀도를 확인하였다. 또한, Rotating Balance의 확장 불확도는 A형 불확도와 B형 불확도를 계산하였고, 계산 결과로 부터 $2.82\times10^{-1}$의 값을 얻음으로서 신뢰성을 확인하였다.

• Journal of Electrical Engineering and Technology
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• 제6권5호
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• pp.697-705
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• 2011

In this paper, a closed-loop system constructed with a linear plant and nonlinearity in the feedback connection is considered to argue against its planar orbital stability. Through a state space approach, a main result that presents a sufficient stability criterion of the limit cycle predicted by solving the harmonic balance equation is given. Preliminarily, the harmonic balance of the nonlinear feedback loop is assumed to have a solution that determines the characteristics of the limit cycle. Using a state-space approach, the nonlinear loop equation is reformulated into a linear perturbed model through the introduction of a residual operator. By considering a series of transformations, such as a modified eigenstructure decomposition, periodic averaging, change of variables, and coordinate transformation, the stability of the limit cycle can be simply tested via a scalar function and matrix. Finally, the stability criterion is addressed by constructing a composite Lyapunov function of the transformed system.

• Journal of Astronomy and Space Sciences
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• 제32권4호
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• pp.419-425
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• 2015

In this study, a new idea for developing a space scale for measuring mass in a microgravity environment was proposed by using the inertial force properties of an object to measure its mass. The space scale detected the momentum change of the specimen and reference masses by using a load-cell sensor as the force transducer based on Newton's laws of motion. In addition, the space scale calculated the specimen mass by comparing the inertial forces of the specimen and reference masses in the same acceleration field. By using this concept, a space scale with a capacity of 3 kg based on the law of momentum conservation was implemented and demonstrated under microgravity conditions onboard International Space Station (ISS) with an accuracy of ${\pm}1g$. By the performance analysis on the space scale, it was verified that an instrument with a compact size could be implemented and be quickly measured with a reasonable accuracy under microgravity conditions.