• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2006년도 제27회 추계학술대회논문집
• /
• pp.271-274
• /
• 2006

Polyethylene-GOX 추진제를 이용한 소형 하이브리드 로켓 모터의 성능 예측 모델에 대한 연구를 수행하였다. 제안된 모델에서 연소실 전체에 걸친 상태량을 단일 변수로 가정하여 내탄도 모델 식을 풀어 연소실 내 압력을 예측할 수 있었으며, 실험을 통해 측정된 값과 비교하여 모델의 정확도를 고찰하였다.

• Advances in aircraft and spacecraft science
• /
• 제9권3호
• /
• pp.195-215
• /
• 2022

The increasing interest in CubeSat platforms ant their capability of enlarging the frontier of possible missions impose technology improvements. Miniaturized electrical propulsion (EP) systems enable new mission for multi-unit CubeSats (6U+). While electric propulsion systems have achieved important level of knowledge at equipment level, the investigation of the mutual impact between EP system and CubeSat technology at system level can provide a decisive improvement for both the technologies. The interaction between CubeSat and EP system should be assessed in terms of electromagnetic emissions (both radiated and conducted), thermal gradients, high electrical power management, surface chemical deposition, and quick and reliable data exchanges. This paper shows how a versatile CubeSat Test Platform (CTP), together with standardized procedures and specialized facilities enable the acquisition fundamental and unprecedented information. Measurements can be taken both by specific ground support equipment placed inside the vacuum facility and by dedicated sensors and subsystems installed on the CTP, providing a completely new set of data never obtained before. CTP is constituted of a 6U primary structure hosting the EP system, representative CubeSat avionics and batteries. For the first test campaign, CTP hosts the ambipolar plasma propulsion system, called Regulus and developed by T4I. After the integration and the functional test in laboratory environment, CTP + Regulus performed a Test campaign in relevant environment in the vacuum chamber at CISAS, University of Padua. This paper is focused on the test campaign description and the main results achieved at different power levels for different duration of the firings.

• 한국지반공학회논문집
• /
• 제18권4호
• /
• pp.105-117
• /
• 2002

철탑기초, 해양 플랫폼 등은 파랑과 풍하중을 반복적으로 받게 되어 주기적인 인발하중이 작용한다. 본 연구에서는 해양 구조물 기초로 사용되는 현장 타설말뚝의 단방향 인발 주기 하중 패턴에 대한 거동특성을 분석하기위해 실내 모형타설말뚝에 대한 인발시험을 실시하였다. 특히 인장하중이 말뚝의 선단과 두부에 직접 가하여 질 때 즉, 인장하중 최초 전달지점의 차이로 인한 하중전달 메카니즘의 차이를 실험을 통해 분석하였다. 가압이 가능한 모형토조 내에 조성된 다져진 화강 풍화토 지반에 소형 현장타설말뚝을 타설하여 인발 시험, 크리프 시험, 반복 인발시험을 수행하였다. 시험 결과, 말뚝 선단인발시의 극한 인발지지력이 말뚝 두부인발시에 비해 약 30%크게 계산되었다. 또한 선단 인발시의 말뚝이 크리프 변형에 대해 매우 안정적인 거동을 보였으며 선행 인발을 실시하면 수직 크리프 변형에 대해 보다 더 안정적일 것으로 판단된다. 반복재하 횟수가 늘어남에 따라 반복 할선탄성계수 값은 점차 증가하는 경향을 보였으며 선단 인발시 그 효과가 더 큰 것으로 밝혀졌다.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2005년도 제24회 춘계학술대회논문집
• /
• pp.139-143
• /
• 2005

액체로켓엔진의 성능 및 냉각특성 연구를 위한 연소시험장치가 개발되었다. 본 시험장치는 액체산소와 케로신을 추진제로 사용하는 추력 1 KN 이하의 액체로켓엔진의 성능 및 냉각 특성연구가 가능하며, 일련의 연소시험을 통해 정상적인 작동을 확인할 수 있다. 또한 케로신 중심 분사 방식의 동축형 인젝터를 사용하는 엔진에 대해 물 냉각 연소시험을 수행하고 연소시험과 CEC86을 이용한 연소해석 결과를 통해 액체로켓엔진 성능 인자로서, 특성속도, 비추력 관점에서, 추진제 혼합비 및 연소실 압력의 영향을 분석한다.

• 한국유체기계학회 논문집
• /
• 제4권1호
• /
• pp.30-37
• /
• 2001

The experimental study on the effect of axial clearance between the tip of impeller blades and stationary shroud has been performed. The investigated compressor, which is a part of a small auxiliary power unit engine, consists of a curved inlet, a centrifugal impeller, a channel diffuser and a plenum chamber. It was designed for a total pressure ratio of 4.3 and an efficiency of $77\%$ at design speed of 60,000 rpm. The experiments are carried out in an open-loop centrifugal compressor test rig driven by a turbine. For the four different clearance ratios Cr(clearance/impeller tip width) of 6.25, 10.93, 15.60 and 20.30 percent, the overall performance data are obtained at $97\%,\;90\%$ and $80\%$ of the design speed. The results show the overall pressure ratio decrease of $7.7\%$ and the efficiency loss of $8.7\%$ across the variation of clearance ratio near the design speed. It also indicates that the influence of tip clearance became weaker as the flow rate is reduced and the stable operating range is not significantly influenced by the change of clearance ratio.

• 한국자동차공학회논문집
• /
• 제15권2호
• /
• pp.143-150
• /
• 2007

Ring and cylinder bore wear may not be a problem in most current automotive engines. However, a small change in ring face and cylinder bore diameter can significantly affect the lubrication characteristics and ring axial motion. This in turn can cause to change inter-ring pressure, blow-by and oil consumption in an engine. Therefore, by predicting the wear of piston ring face and cylinder bore altogether, the changed ring end gap and the changed volume of gas reservoir can be calculated. Then the excessive oil consumption can be predicted. Here, the oil amount through top ring gap into combustion chamber is estimated as engine oil consumption. Furthermore, the wear theories of ring and cylinder bore are included. The changed oil consumption caused by the new end gap and the new volume of oil reservoir around second land, can be calculated at some engine running interval. Meanwhile, the wear amount and oil consumption occurred during engine durability cycle are compared with the calculated values. The wear data of rings and cylinder bore are obtained from three engines after engine durability test. The calculated wear data of each part are turn out to be around the band of averaged test values or a little below. It is shown that the important factor regarding oil consumption increasement is the wear of ring face.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2005년도 제25회 추계학술대회논문집
• /
• pp.247-250
• /
• 2005

단위 분사기의 실물형 연소기 적용 시 실물형 연소기의 배열, 구성 분사기 수량, 연소압 등의 이유로 동작환경이나 분사기 형상의 변화를 필요로 한다. Jet-A1과 액체산소를 추진제로 하는 동축 와류형 분사기의 실물형 적용성을 검토하기위해 연소압 증가, 추진제 유량 감소와 분사기 길이 증가 조건에서 연소시험을 수행하였다. 시험결과 연소압 증가와 추진제 유량 감소, 노즐길이 증가 시 특성속도효율이 개선되었으며 이에 반해 압력섭동의 강도는 미미하였고 특정한 주파수 대역을 보이지 않아 실물형 적용성이 우수하였다.

• 한국지반공학회:학술대회논문집
• /
• 한국지반공학회 2008년도 춘계 학술발표회 초청강연 및 논문집
• /
• pp.605-612
• /
• 2008

The shear wave velocity ($V_s$) has been commonly used to evaluate the dynamic properties of soil. The field $V_s$ probe (FVP) was already developed to assess the shear stiffness of a soft clay. The objective of this study is to investigate the disturbance effects of the FVP due to the penetration. The laboratory tests are conducted in a large-scale consolidometer (calibration chamber). The reconstituted clay is mixed at the water content of 110% using a slurry mixer. The FVP and down-hole test are carried out every 1cm interval to compare the data. In addition, two square rods with transducers are also implemented to get the reference value. The shear waves evaluated by the FVP, dow-hole tests, and reference rods are closely matched. This study suggests that the disturbance effect of the FVP due to the penetration into the soft clay soils is small enough and the $V_s$ evaluated by the FVP reflects well the in-situ characteristics. Furthermore, the combination of the FVP and down-hole test shows the possibility of hybrid equipment.

• 한국국방경영분석학회지
• /
• 제3권1호
• /
• pp.83-96
• /
• 1977

The combustion chamber and nozzle of an end burning, small spherical rocket is designed. A spherical external shape has a number of advantages such as fixed center-of-gravity and minimum aerodynamic precession torques during flight and a better mass distribution for gyro-stabilization as contrasted to a conventional ogive rocket shape. It is shown that the cross-sectional variation of the end burning solid propellant with length is an exponential geometry to provide a constant thrust-weight ratio of the rocket device during the propellant burning period, and that the factors which affect the attainment of the constant relationship of thrust to weight in the design are the initial propellant area, initial weight of the rocket and propellant density. The measurement of the transient thrust in the ground static test using black powder propellant supports the predicted results. A wind tunnel having a $30{\times}30{\times}75cm$ test section and Mach number 0.11 is constructed, and a simple balance-type device is designed for the measurement of the drag of a spinning sphere. The experimental results indicate that the. spinning has no effect on the magnitude of the drag up to the Reynolds number $3{\times}10^5$. Numerical computation of the flight trajectories for various launching angles is presented, and the gyro-stabilization of spinning sphere is discussed.

• Journal of Mechanical Science and Technology
• /
• 제20권2호
• /
• pp.286-294
• /
• 2006

Flows in a ramjet inlet is simulated for the study of the rocket-ramjet transition. The flow is unsteady, two-dimensional axisymmetric, compressible and turbulent. Double time marching method is used for the unsteady calculation and HLLC method is used as a higher order MUSCL method. As for turbulent calculation, $\kappa-\omega$ SST model is used for more accurate viscous calculations. Sinusoidal pressure perturbation is given at the exit and the flow fields at the inlet is studied. The cruise condition as well as the ground test condition are considered. The pressure level for the ground test condition is relatively low and the effect of the pressure perturbation at the combustion chamber is small. The normal shock at the cruise condition is very sensitive to the pressure perturbation and can be easily detached from the cowl when the exit pressure is relatively high. The sudden decrease in the mass flux is observed when the inlet flow becomes subcritical, which can make the inlet incapable. The amplitude of travelling pressure waves becomes larger as the downstream pressure increases, and the wavelength becomes shorter as Mach number increases. The phase difference of the travelling perturbed pressure wave in space is 180 degree.