• Proceedings of the Acoustical Society of Korea Conference
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• autumn
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• pp.193-196
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• 2001

본 연구에서는 원활한 정재파 생성과 양방향 구동이 가능한 새로운 형태의 초음파 리니어 모터를 제작하고, 그 특성을 평가하였다 본 연구에서 제안한 모터는 $\lambda/4$ 간격으로 이빨 구조를 가지는 스테이터의 상, 하부에 압전소자를 $90^\circ$ 의 위치 위상차를 갖도록 부착한 형태의, 상, 하부 압전소자에 각각 동위상, 180도의 시간 위상차를 가지는 교류 전압을 인가함으로써 양방향 구동이 가능하도록 하였다. 또한 원활한 정재파를 생성할 수 있는 최적의 구조를 결정하기 위해, 여러 가지 형태의 경계조건들에 대해 유한요소해석법을 이용하여 모델링하여 각 이빨들의 변위를 관찰함으로써 각각의 구조에 대해 타당성을 검증하였다. 위 결과를 바탕으로 세 종류의 초음파 리니어 모터를 제작하여 구동실험을 하였고, 실험 결과에 따라 속도와 추력 및 양방항성이 가장 우수한 최적의 구조를 결정하였다. 본 연구에서 제작한 모터는 최대 82.4cm/s의 속도와 0.46N의 추력을 가졌다.

• Proceedings of the KIEE Conference
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• 2006.07b
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• pp.879-880
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• 2006

횡자속의 기본원리는 릴럭턴스 전동기와 같다. 발생한 힘밀도는 공극과 극간격에 반비례하고 기자력의 자성에 비례한다. 이러한 횡자속 선형전동기를 적용할 경우 추력의 변화로 인해서 진동과 힘의 불평형이 발생하는 것이 일반적이다. 본 논문에서는 이러한 추력 불평형과 진동특성을 향상시킬 수 있는 방법이 다상형으로 구동하는 방법이 있으며 힘을 균일하게 할 수 있고 전동기의 체적을 줄이고 진동특성을 저감시킬 수 있다는 것이라고 판단된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.35-35
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• 2000

추력 편향제어(Thrust Vector Control)는 위성 발사체나 대륙간 탄도 미사일과 같이 공기가 희박한 고 고도에서의 비행자세 제어와 궤도수정, 지대공이나 함대공 유도탄처럼 발사 직후 저속에서 임의의 방향으로 급선회해야 할 경우에 노즐의 배출가스 방향을 직접 조절하여 모멘트를 발생시키는 제어방식을 말한다. 이 방식 중 널리 사용되고 있는 제트 베인 추력 편향제어방식은 베인이 직접 고온, 고속의 가스 흐름내에서 작용하기 때문에 재료는 내열성과 제트 베인 주위에 형성되는 유동 특성, 그리고 베인간의 유동 간섭이 중요한 인자이다. 그러므로, 제트 베인의 실용화는 수치해석에 의존하던 개발 초기나 중기의 설계 단계에서 벗어나 실제 크기나 축소모델의 유동 모사 시험에 의해 성능이 검증되어야 한다.(중략)

• Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
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• v.22 no.12
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• pp.130-141
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• 2008

This paper presents the flow characteristics in the fluid circulation loop using the tubular type linear induction motor(TLIM) electromagnetic pump. A TLIM of thrust 40[N] is analyzed using the equivalent and genetic algorithm for the system The flow characteristics are analyzed by coupling the Maxwell equations with the Navier-Stokes equation with the thrust. The analysis algorithm is developed for analyzing the liquid metal flow in the system for laminar and turbulent flow. And the effect of thrust is analyzed for the flow characteristics.

• Bulletin of the Korean Space Science Society
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• 2005.10a
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• pp.58-58
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• 2005

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.10
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• pp.955-965
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• 2010

The MH-75 propeller for the MAV propulsion is designed using a free vortex design method which considers design parameters such as the hub-tip ratio, the twist angle distribution, the maximum camber location and the chord length of the propeller blade. Aerodynamic characteristics of the MH-75 propeller are predicted by changing the flight speed using the frequency domain panel method. And, the thrust characteristics of the MH-75 propeller are measured using the balance system of the subsonic wind tunnel for the validation of numerical results. The performance characteristics of the MH-75 propeller satisfied with design requirements. Numerical results of the MH-75, which are predicted by the frequency domain panel method, are more agree with experimental results compare with XFOIL.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.4
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• pp.328-341
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• 2017

In the control actuator system of a launch vehicle based on thrust vectoring, the interaction between electro-mechanical position servo and inertial load are combined with the dynamic characteristics of the flexible vehicle support to generate synthetic resonance. This occurred resonance is fed back to the attitude control system and can influence stability of launch vehicle. In this study, we proposed a simulation model to analyze synthetic resonance of electro-mechanical actuation system for thrust vector control and explained the results of simulation and test using dynamic force feedback control which improves dynamic characteristics of servo actuation system by reducing synthetic resonance.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.2
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• pp.95-105
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• 2018

Increasing cruise speed is an important issue for the development of the next generation rotorcraft. Among several concepts proposed by previous research, the rotorcraft with ducted fan demonstrates its possibility of high-speed flight. In this study, numerical simulations are conducted to investigate the aerodynamic and flow characteristics of multi-ducted fan in forward flight. The aerodynamic efficiency around front ducted fan is determined by interaction between free-stream velocity and the induced velocity. While flow characteristics of rear ducted fan are dominantly influenced by the front ducted fan. Separation in the front ducted fan occurs faster than that of rear ducted fan, and the separation at duct inlet induces an increase of fan thrust. As a result of interaction effect between each ducted fan, relatively aligned inflow enters to the rear ducted fan. Therefore, thrust of the rear fan is decreased steadily before separation, and sudden changes of thrust in fans occur simultaneously. Due to the pressure decrease on lower surface, the normal force of rotorcraft is reduced with forward speed.

• Journal of Aerospace System Engineering
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• v.17 no.6
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• pp.63-71
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• 2023

In the present study, the effect of pitch amplitude on the unsteady aerodynamics of a NACA 0012 airfoil is numerically investigated. When the frequency ratio is equal to 1.0, airfoil pitching with 20 and 30 degrees of pitch amplitude shows almost small lift generation, but the lift is significantly increased in case of 10-degree pitch amplitude. When the frequency is 0.5, the lift coefficients have large values, and the lift increases with a decrease in pitch amplitude. When the frequency ratio is 1.0, the airfoil generates large thrust. The thrust decreases as the pitch amplitude decreases. When the frequency ratio is 0.5, drag is generated for the 30-degree pitch amplitude, but the thrust is generated for 10-degree pitch amplitude. In future, the effect of heave amplitude on the unsteady aerodynamics of the airfoil will be studied.

• The Transactions of the Korean Institute of Power Electronics
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• v.4 no.4
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• pp.318-324
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• 1999

In this paper. a control method based on finite element analysis is presented to improve the control characteristics of t the permanent magnet linear synchronous motor (PMLSM). In the control method. additional compensation current is a added to the conventional control current according to the position of mover. The characteristics of thrust ripple a according to the position of mover and the current are analyzed by using finite element method (FEM). And. the value of current to compensate the thrust ripple due to the cog밍ng force is calculated from the analysis results. The c characteristics according to control method are compared in case of speed control. and to conform the validity of the p presented method, a test set is built and experiments are performed.