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

• Journal of the Korean Society of Propulsion Engineers
• /
• v.8 no.3
• /
• pp.1-9
• /
• 2004

We conducted the firing test with the regenerative cooling LRE and calculated the heat flux from measured coolant temperature, that was compared with the heat flux predicted by previously developed numerical analysis method. The difference between the measured heat flux and the numerical calculation value was within nine percents. Therefore, developed numerical analysis method can be applied to the design/fabrication of a real LRE system. and, it was investigated that combustion pressure and mixture ratio have an Influence on the heat flux with a constant relation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2003.10a
• /
• pp.53-56
• /
• 2003

This paper describes the general design procedure of cooling system for liquid rocket engine(LRE). From this design logic, cooling channels are designed and fabricated. The measured heat flux from firing test is similar to the heat flux predicted by design logic. Therefore, the proposed design procedure of cooling channel can be applied to real LRE system. Also the result of firing test indicates that combustion pressure and mixture ratio have an influence on the heat flux to be produced in combustion chamber.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2008.05a
• /
• pp.61-64
• /
• 2008

For the performance evaluation of liquid mono-propellant thruster, Vacuum Hot-fire test is necessarily required. An accurate flow measurement is one of the key parameters to the successful T&E program. This paper describes the characteristics of the coriolis flowmeter, explains the cold-flow test using simulant propellant (DIW), and presents the test results. Finally, the cold test results have been verified in comparison with the hot-fire test data.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.11a
• /
• pp.134-137
• /
• 2009

Combustion tests of a low thrust rocket engine was performed to get combustion characteristics, which used a high concentrated hydrogen peroxide and kerosene as the oxidizer and fuel. The engine consisted of multi injector(six coaxial swirl injectors), chamber, nozzle and catalyst ignition system. The test was carried out by changing O/F ratio from 3.8 to 11.0. The experimental results showed that combustion efficiency was highest at O/F ratio from 5 to 6 and pressure fluctuations of all the range were lower than 5%.

• Aerospace Engineering and Technology
• /
• v.12 no.2
• /
• pp.180-185
• /
• 2013

In this study, preliminary design of human powered aircraft was performed by considering the aerodynamic performance. For this, overall weight including the aircraft and pilot was determined. Then, the main wing and horizontal/vertical tail were designed with appropriate selection of the airfoils and planform shapes. Based on these, three dimensional flow was calculated to obtain lift and drag coefficients and the position of center of gravity (CG). Consequently, it was shown that the lift and power of the aircraft satisfied the constraints of the minimum required lift and the pilot's available power. Also, the CG of the aircraft was located at aerodynamic center (AC) of the main wing, which guaranteed 26% of the static margin.

• Transactions of the Korean Society of Mechanical Engineers
• /
• v.12 no.5
• /
• pp.1063-1070
• /
• 1988

The influence of the inlet pressure on bearing performance of tilting pad bearings in laminar regime is examined. A simple flow model is presented to calculate the inlet pressure in inlet flow that occurs at a short distance ahead of the bearing inlet. The bearing performances are obtained, load capacity, friction torque and lubricated flow-rate, etc, numerically for the inlet pressure boundary conditions with and without pressure jump. The computed results of both cases show that bearing performance and the optimum pivot position changes remarkably according to the bearing operating conditions. The influence of the inlet pressure on bearing performance must be considered to analyze the bearing performance precisely.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.6 no.4
• /
• pp.25-35
• /
• 2002

A calculation procedure for designing LRE regenerative cooling system is introduced. In LRE thrust chamber, heat is transfered from the hot gas to the wall by convection and radiation, then conduction through the wall and finally convection to the liquid coolant. A cooling channel is designed on the basis of heat transfer rate calculated by using criterial method and integral method. The result is compared with existing Russian cooling channel design code. Also a design logic and quantitative effect of various parameters were introduced to help better understanding for those who is not familiar to LRE system.

• Proceedings of the KIEE Conference
• /
• 2008.10b
• /
• pp.357-358
• /
• 2008

본 논문은 GPS를 이용한 무인 비행체의 자율비행에 관한 연구를 다루었다. 비행체의 종류는 크게 고정익기와 회전익기로 나뉘는데 본 연구에서는 회전익기의 형태를 가진 Quarter Vehicle을 사용하였다. Quarter Vehicle은 4개의 프로펠러에 의한 양력과 회전 반발력으로 비행을 한다. 이때의 양력은 수평면에 대해 수직으로 추력을 발생시키므로 다른 비행체보다 불안정하며 이를 안정하게 제어하기 위해 관성 센서를 적용하여 균형을 유지한다. 본 연구에서는 UAV의 자세와 균형을 안정적으로 유지하기 위해 관성센서를 적용하였으며 GPS를 활용하여 독립적인 자율비행이 가능하도록 하였다. 정확한 위치정보를 제공하는 GPS는 3개 이상의 위성으로부터 시간 및 위치 정보를 받아 좌표를 계산하고 비행체의 위치, 속도 및 방향을 결정하여 자율 비행이 가능하도록 한다. 또한 초형 지자기센서를 비행체에 적용하여 GPS의 방향 정보를 보완하도록 하였다. 본 논문에서는 무인 비행체의 자율비행의 기초가 되는 위치좌표 계산을 위한 GPS의 적용 방법과 비행경로계획 알고리즘을 제시 한다.

• The Journal of Korean Institute for Practical Engineering Education
• /
• v.4 no.1
• /
• pp.57-64
• /
• 2012

For design of a electrical Machine it is used conventional design methode to determine size with considering of magnetical circuit and windings. After this process, Flux density and Torque are calculated with FEM program. But most electrical machines are complicated in their configuration, therefore it is not easy to understand the design process and analyzing methode. We need to develop a educational material. In this paper using Linear force motor, which is relatively not complicated in their configuration and easy to understand the relationship between electro magnetics and force, will be explained the design process and calculating process with Finite element methode. And with FEM program will be calculated and illustrated flux density in each part and Force of the Linear force motor easy to understand.