• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.209-212
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• 2006

Insect and birds in nature flap their wings to generate fluid dynamic forces that are required for the locomotion. Most of the previous published papers discussed mainly on the effect of flapping parameters such as flapping frequency and amplitude on the thrust at a fixed Reynolds number. However, it is not much known on the values of the flapping parameters that the flapping wing requires to generate the thrust at the low Reynolds number flow. In this paper, the onset of the thrust generation is investigated using the lattice Boltzmann method. The wake patterns and velocity profiles behind a flat plate in heaving oscillation are investigated for the heaving amplitude of 0.5C. The time-averaged thrust coefficient value is investigated by changing the reduced frequency from 0.125 to 3.0 for three values of heaving amplitude (h/C=0.25, 0.325, 0.50). It is also found that the critical Strouhal number over which the flat plate starts to produce the thrust is around 0.1 and the thrust is an exponential function of the Strouhal number.

• 대한기계학회논문집
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• 제17권11호
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• pp.2762-2772
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• 1993

The paper deals with the flutter of a cantilevered beam subjected to a rocket thrust generated by a solid rocket motor. It is saaumed that the rocket thrust is to be a constant follower thrust, and produced by the installation of a solid rocket motor to the tip end of the cantilevered beam. The rocket motor is considered to be a rigid body having finite sizes, but not a mass point as it has been assumed so far. Governing equations are derived through the extended Hamilton's principle, and finite element method is applied to obtain the theoretical prediction for critical follower thrust. The maximum follower thrust is also calculated through the change of shear deformation parameter of the beam in the numerical simulation. The theoretical prediction for flutter or stability is verified by experiment. The experimental results show that critical follower thrust in theory agrees well with the experimental value taking account of the magnitude, rotary inertia of the rocket motor and the distance from the tip end of the beam to the center of gravity of the rocket motor.

• 한국전기전자재료학회:학술대회논문집
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• 한국전기전자재료학회 2003년도 하계학술대회 논문집 Vol.4 No.1
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• pp.227-232
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• 2003

Usually, the thrust of a Linear Pulse Motor(LPM) is calculated by magnetic equivalent circuit modelling method. Analytical thrust deviation exists to calculating magnetic flux density by using Permeance Modelling Method, Finite Element Method, and Velocity Electric Motive Force Method. For calculating accuracy thrust by using these every method, the thrust is calculated and compared by Lorentz Force Method, Magnetic Coenergy Method, and Maxwell correspondence force Method. And that becomes important factor at the comparison of each capacity and parameter of motor. So this study wants to compare and analyze measurement data and calculating data of the static thrust of LPM. and then we can get more accuracy method, calculating the static thrust of LPM.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.192-197
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• 2004

Recently, fluidic thrust vectoring methods have been preferably employed to control the movement of propulsive systems due to relatively simpler design and lower cost than mechanical thrust vectoring methods. For An application of the thrust vectoring to flight bodies, it is necessary to understand very complicated exhaust flows which are often subject to shock waves and boundary layer separation. But researches for the thrust vector control using counterflow have been few. In the present study, experiments have been performed to investigate the characteristics of supersonic jets controlled by a thrust vectoring method using counterflow. The primary jet is expanded through a two-dimensional primary nozzle shrouded by collars, and is deflected by the suction of the air near nozzle into an upper slot placed between the primary nozzle and the upper collar. A shadowgraph method is used to visualize the supersonic jet flowfields. Primary nozzle pressure ratios and suction nozzle pressure ratios are varied from 3.0 to 5.0, and from 0.2 to 1.0 respectively. The present experimental results showed that, for a given primary nozzle pressure ratio, a decrease in the suction nozzle pressure ratio produced an increased thrust vector angle. As the suction nozzle pressure ratios were increased and decreased, the hysteresis of the thrust vectoring was observed through the wall pressure distributions

• 한국해양공학회지
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• 제23권4호
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• pp.47-51
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• 2009

Thrust is one of the important performance characteristics of an AUV. At the design stage, the resistance of an AUV at its maximum speed is estimated and then the thrust system is designed, including the propeller diameter, propeller rpm, driving system, and required power. However, it is not possible to be certain that the thrust system has been correctly designed until the AUV is launched and its speed is measured. If data from a propeller open-water test is available, the thrust and torque of the propeller at a certain speed can be estimated. In addition, if the motor's torque characteristics are available, the maximum speed saturated by the induced propeller torque can be estimated. In this paper, an easy technique for estimating the maximum speed of an AUV will be shown, even in a case where additional resistance is gained from appendages not considered at the design stage. Furthermore, the thrust performance changes by adjusting the diameter of the propeller can be easily investigated.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년도 제31회 추계학술대회논문집
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• pp.55-59
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• 2008

액체로켓엔진의 성능 검증에 있어서 가장 큰 비중을 차지하는 것 중 하나는 정확한 추력 측정이다. 본 연구에서는 기존의 추력 측정 장치를 보완한 저추력 액체로켓엔진의 추력 측정 장치를 개발하여 작은 추력을 발생하는 로켓엔진의 보다 정확한 추력 측정을 가능하도록 하였다. 또한, 추력 측정 장치의 추력 측정 평가 시 고려되는 주요 인자들에 대한 연구를 수행하여 추력 측정 장치의 신뢰도 평가에 관한 기법 및 절차 수립의 기반을 마련하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2012년도 제38회 춘계학술대회논문집
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• pp.249-252
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• 2012

7톤급 연소기 헤드부에 대한 구조설계를 수행하였다. 액체로켓엔진 연소기 헤드부는 추진제로 사용되는 산화제와 연료에 의하여 고압의 하중뿐만 아니라 추력 하중을 받기 때문에 구조적인 안정성은 매우 중요한 요소이다. 7톤급 연소기 헤드부 구조설계를 위하여 먼저 구조설계 요구조건을 설정하고, 이를 바탕으로 기본형상을 설계하였다. 구조설계에 사용된 재료는 국내에서 개발된 고강도 스테인리스강을 적용하였다. 설계된 기본형상에서 구조적으로 가장 효과적인 형상을 도출하기 위하여 총 12종류의 해석모델에 대하여 구조해석을 수행하고, 그 결과들로부터 구조적으로 가장 안정한 형상을 선정하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2011년도 제36회 춘계학술대회논문집
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• pp.167-174
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• 2011

고체추진기관은 구조가 비교적 간단하고 장기적 저장성이 우수한 반면에 일반적으로 추력의 조절 등에 한계성을 가지고 있다. 본 논문에서는 핀틀 밸브 등과 같은 특수한 노즐을 사용하는 가변추력 고체추진기관의 압력 및 추력 제어 알고리즘을 제안한다. 이를 위해 질량보존만을 고려한 추진기관의 연소기 내 압력변화 모델에 대하여 고전적인 비례-적분 제어기와 모델의 비선형성을 피드백을 통해 제거하고 이를 선형모델로 대치하는 피드백 선형화 제어기를 설계하고, 압력제어모델의 추력계산식을 얻어내어 추력제어모델을 제시한다. 운용점에 대해 선형화하여 비례-적분 제어기를 설계하고, 시뮬레이션을 통하여 모델의 성능을 분석한다.

• 제어로봇시스템학회논문지
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• 제18권2호
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• pp.103-109
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• 2012

Fish generates large thrust through an oscillating motion with a compliant joint of caudal fin. The compliance of caudal fin affects the thrust generated by the fish. Due to the flexibility of the fish, the fish can generate a travelling wave motion which is known to increase the efficiency of the fish. However, a detailed research on the relationship between the flexible joint and the thrust generation is needed. In this paper, the compliant joint of a caudal fin is implemented in the driving mechanism of a robotic fish. By varying the driving frequency and stiffness of the compliant joint, the relationship between the thrust generation and the stiffness of the flexible joint is investigated. In general, as the frequency increases, the thrust increases. When higher driving frequency is applied, higher stiffness of the flexible joint is needed to maximize the thrust. The bending angles between the compliant joint and the caudal fin are compared with the changes of the thrust in one cycle. This result can be used to design the robotic fish which can be operated at the maximum thrust condition using the appropriate stiffness of the compliant joint.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2012년도 제38회 춘계학술대회논문집
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• pp.457-460
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• 2012

본 연구는 7톤급 연소기용 분사기 검증을 위한 축소형 연소기의 설계 및 제작에 관한 것이다. 7톤급 연소기의 헤드부는 90개의 동축 와류형 분사기로 구성되며, 연소실은 케로신 재생냉각 일체형 연소기이다. 7톤급 연소기에 적용할 분사기로 차압 및 리세스 수를 달리한 분사기를 설계하였다. 설계된 분사기를 실물형 연소기에 적용하기 전 축소형 연소기에 먼저 적용하여 분사기 작동성 및 성능검증을 하고자 한다. 축소형 연소기는 분사기 19개로 구성되며, 연소압력 70 bar, 총 추진제 유량은 4.3 kg/s, 혼합비는 2.45이다.