• Journal of the Korean Society of Propulsion Engineers
• /
• v.13 no.4
• /
• pp.30-35
• /
• 2009

Effective-pivot effects on the thrust vector control performance of the flexible seal nozzle to be used to control the flight direction of missile were investigated by computer simulation. $2^3$-Design of experiment technique was applied and ADMAS was used for the surrogate technique. As a result, radial pivot position had more influence upon the nozzle actuating performance than axial pivot position. Connecting method of actuator was also important factor in determining effective-pivot effects on the thrust vector control performance of the flexible seal nozzle.

• Journal of Advanced Marine Engineering and Technology
• /
• v.22 no.3
• /
• pp.337-342
• /
• 1998

In this paper the lubrication performances of line pivoted pad thrust bearing and point pivoted pad thrust bearing are studied by a numerical analysis. The running characteristic parameters such as nondimensional load carrying capacity nondimensional friciton power loss nondimensional flow rate and film thickness ratios are calculated for various circumferential pivot positions. The results provide a usdful data for the selection of pivot position in a pivoted and thrust bearing.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.9 no.4
• /
• pp.73-80
• /
• 2005

In general, the performance of movable nozzle used for thrust vector control in solid rocket motor is estimated on the basis of the effective pivot of nozzle. However, it is nearly impossible to define the exact effective pivot by the mathematical model or experimental technique owing to pivot dynamics. In this paper, pivot dynamic properties were investigated by ADAMS simulation technique and trajectory of the exact effective pivot was modelled by the artificial neural network. Comparison of the proposed method was made with the virtual movable nozzle (computer simulation) to verify the method, and showed good agreement. Therefore, the proposed method will be applicable to predict the effective pivot of movable nozzle during bench or ground test.

• 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 Advanced Marine Engineering and Technology
• /
• v.22 no.1
• /
• pp.85-91
• /
• 1998

In this paper, an influence of inlet pressure on the running characteristics of tilting pad thrust bearing is studied by a numerical analysis. The inlet pressure is obtained from the extended Bernoulli equation including the loss coefficient which is varied with the operating conditions. The running characteristic parameters such as the minimum film thickness, the film pressure and the film thickness ratios are calculated for various runner speeds with constant load in particular two pivot positions. The results are shown that the inlet pressure has a large influence on the minimum film thickness and other running characteristic parameters.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.150.2-150.2
• /
• 2012

로켓 엔진용 짐벌 마운트는 발사체 발사 후 자세 제어를 위해 발사체와 엔진사이에 장착된 TVC(Thrust Vector Control) 구동기의 작동으로 짐벌 운동을 수행하며 기구학적으로 자세 제어를 하는데 있어 매우 중요한 역할을 하는 요소이다. 이러한 짐벌 마운트는 엔진 추력을 발사체에 전달하는 기능 이외에 지정된 위치에 엔진을 고정시키는 역할과 위치 고정 후 발사체 단과 엔진의 정확한 추력 전달을 위한 기계적 불일치 보정 기능, 짐벌 구동에 대한 피봇 기능을 동시에 수행하여야 하는 복합적인 기능을 가지고 있다. 특히, 이중에서도 물리적으로 고 추력의 하중을 전달하는 요소로서 충분한 강도와 강성을 지녀야 하므로 본 연구에서는 이와 관련된 초기 설계 요구도 분석을 바탕으로 설계 규격에 부합하는 짐벌 마운트의 구조적 검토를 통해 로켓 엔진용 짐벌 마운트 설계 형상을 개념적으로 제시하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.39 no.7
• /
• pp.682-687
• /
• 2011

Calibration mirror mechanism has been widely used for on-board calibration with black body. The calibration mirror is deployed to reflect the radiation energy from the black body to the image sensor for calibrating the sensor system. After the calibration, the calibration mirror is stowed not to hide a main optical path. It also has a fail-safe function which can stow the mirror by just removing the input power of motor when the calibration mirror is stopped at certain position during the calibration. In the present work, the operation concept, design, torque analysis and functional test results of the calibration mirror mechanism with the aforementioned function have been introduced and investigated.

• KIISE Transactions on Computing Practices
• /
• v.23 no.8
• /
• pp.498-503
• /
• 2017

SIMD (Single Instruction Multiple Data) is a representative parallelization architecture that processes multiple data loaded in a SIMD register with a single instruction. Quicksort is a sorting algorithm that picks an element as a pivot from the array and reorders the array such that all elements having the values less than the pivot value are located in the left side on the pivot as well as all elements having the value greater than the pivot value are located in the right side on the pivot and then the algorithm performs the same task on both sublist recursively. In this paper, we propose an efficient Quicksort algorithm applying the SIMD instructions which minimally invokes conditional branches to avoid the performance degradation incurred by branch misprediction in a pipeline architecture. In addition, we improve the performance of the Quicksort algorithm by fetching data into a SIMD register as a byte unit to apply VBP (Vertical Bit Parallel) and the early pruning technique.