• 한국항공우주학회지
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• 제46권12호
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• pp.986-993
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• 2018

측 추력 제트는 유도무기의 자세제어 및 궤도 천이 기동을 하는 데 있어 기존의 핀과 같이 제어 면을 이용한 방식보다 우수한 기동성을 갖는다. 하지만 초음속 영역에서 비행 시 측 추력 제트로 인한 제트 간섭 유동이 발생하며 충격파와 경계층 유동, 와류 유동의 상호 작용으로 인해 매우 복잡한 유동 구조를 나타낸다. 특히 직격 파괴(hit-to-kill) 방식의 요격체의 경우 정밀한 제어 및 기동이 요구되기 때문에 제트 간섭 유동이 미치는 영향에 대한 분석이 필요하다. 기존의 제트 간섭 해석은 저고도 운용 조건에서 주로 수행되었으나 중고도 운용 조건의 경우 해석 사례가 많지 않으며 대기 조건으로 인해 분사 제트 유동이 상대적으로 크게 발달하는 특징을 갖는다. 본 연구에서는 중고도에서 비행하는 요격체 형상에 대해 받음각 조건에 따라 제트 간섭 유동 해석을 수행하였다. 해석 결과를 바탕으로 유동장의 구조적인 변화 특성을 분석하였으며, 공력 계수의 변화를 비교하였다.

• 대한조선학회논문집
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• 제59권6호
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• pp.423-431
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• 2022

In this paper, the results of Planar Motion Mechanism (PMM) test for a 1/15 scaled model of the MARIN Joubert BB2 submarine is dealt with to derive the maneuvering coefficients for surface condition. For the depth of surface navigation, the top of the sail was exposed 0.46 m above the water surface in the model scale, and it corresponds to 6.9 m in the full scale. The resistance and self-propulsion tests were conducted, and the model's self-propulsion point was obtained for 1.328 m/s, which corresponded to 10 knots in the full scale. The maneuvering tests were performed at the model's self-propulsion point, and the maneuvering coefficients were obtained. Based on the maneuvering coefficients, a turning simulation was performed for starboard 30 degree of stern fins. The straight-line stability and control effectiveness in the horizontal plane were analyzed using the maneuvering coefficients and compared with the appropriate range. For the analysis of the neutral fin angle of the X-type stern fin, the stern fin test with drift angles was carried out. As a result, the flow straightening effect at lower and upper parts of the stern fin was discussed.

• 한국가스학회지
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• 제26권6호
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• pp.24-29
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• 2022

이 논문은 LPG 자동차의 캠축베어링 시일의 오일누설, 컴퓨터커넥터 핀 손상에 의한 접촉불량, 베이퍼라이저 배부불량으로 인한 고장사례에 대하여 현상을 분석, 연구한 것이다. 첫 번째 사례는 실린더 헤드를 분해하여 확인한 결과 타이밍 시스템에서 가까운 엔진의 흡기캠축의 베어링과 시일의 조립부 손상으로 인해 이 부위로 엔진오일이 누설되는 것을 확인하였다. 두 번째 사례는 엔진컴퓨터로 공급되는 자동차의 시동을 제어하는 전원선의 커넥터 핀이 손상되어, 전원이 공급되지 않아 시동이 꺼진 것을 확인하였다. 세 번째 사례는 베이퍼라이저 내부에 이물질의 퇴적으로 인해 가스의 흐름이 원활하지 못하여 엔진의 부조화현상이 발생되었다. 결국, 베이퍼라이저에서 믹서로 적은 양의 가스를 공급하게 되고, 믹서의 스로틀 열림량을 제어하는 컴퓨터는 그 열림량만큼 공기를 공급하게 됨으로써 연소실에서 혼합기는 희박한 상태가 되어 엔진의 적정출력을 내지 못하는 것을 확인하였다. 따라서, 자동차가 최적의 운전조건이 될 수 있도록 자동차관련 시스템의 관리를 철저하게 해야한다.

• International Journal of Air-Conditioning and Refrigeration
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• 제13권4호
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• pp.196-205
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• 2005

In this paper, recent research trend on heat transfer in impinging jet is reviewed. We focused on submerged jet that air issued into air or liquid issued into liquid. To control and enhance the heat transfer in single jet, researchers have performed a lot of experiments by considering the nozzle geometry, impinging surface and active method such as jet vibration, secondary injection and suction flow. The studies on multiple jet have been mainly focused on finding out the optimum condition and on investigating many different factors concerned with application condition (crossflow, rotation and geometry etc.) and combined techniques (rib turbulator, pin fin, dimple and effusion hole etc.). All most experiments showed the detailed heat transfer data by using liquid crystal method, infrared camera technique and naphthalene sublimation method. Many numerical calculations have been performed to investigate the flow and heat transfer characteristics in laminar jet region. Various turbulence models such as $k-\varepsilon-\bar{\nu^2}$, modified $k-\varepsilon-f_{\mu}$ were applied to the calculation for turbulent jet and the predicted results showed a good agreement with the experimental data. Although a lot of studies on impinging jet have performed consistently up to recently, further studies are still required to understand the flow and heat transfer characteristics more accurately, and to give a guideline for optimum impinging jet design in various applications.

• 동력기계공학회지
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• 제11권1호
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• pp.70-75
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• 2007

Heat transfer coefficient and fin efficiency of a heat exchanger dispersed in the microelement of control volume were predicted with various flow patterns, conditions and material properties. A computational program was developed by using the method of efficiency-NTU(Number of transfer unit). The modelling was applied to heat exchangers, also was integrated in power pack cooling system in an armored vehicle. The compatibility and the generality were proved by comparing the prediction values with the test results. The developed program may be useful for the design of the cooling system in an armored vehicle.

• 한국전산유체공학회지
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• 제16권2호
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• pp.24-29
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• 2011

Immersed boundary lattice Boltzmann method has been applied to analyze the characteristics of the self-propelled fish motion swimming robot. The airfoil NACA0012 with caudal fin stroke model was considered to examine the characteristics. The foil in steady forward motion and a combination of steady-state harmonic deformation produces thrust through the formation of a flow downstream from the trailing edge. The harmonic motion of the foil causes unsteady shedding of vorticity from the trailing edge, while forming the vortices at the leading edge as well. The resultant thrust is developed by the pressure difference formed on the upper and lower surface of the airfoil. and the time averaged thrust coefficient increases as Re increase in the region of $Re{\leqq}700$. The suggested numerical method is suitable to develop the fish-motion model to control the swimming robot, however It would need to extend in 3D analysis to examine the higher Re and to determine the more detail mechanism of thrust production.

• 설비공학논문집
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• 제20권12호
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• pp.775-780
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• 2008

A dynamic model to simulate LNG reliquefaction process has been developed. The model was applied to two candidate cycles for LNG reliquefaction process, which are Reverse Brayton and Claude cycles. The simulation was intended to simulate the pilot plant under construction for operation of the two cycles and evaluate their feasibility. According to the simulation results, both satisfy control requirements for safe operation of brazed aluminum plate-fin type heat exchangers. In view of energy consumption, the Reverse Brayton cycle is more efficient than the Claude cycle. The latter has an expansion valve in addition to the common facilities sharing with the Reverse Brayton cycle. The expansion valve is a main cause to the efficiency loss. It generates a significant amount of entropy associated with its throttling and increases circulation flow rates of the refrigerant and power consumption caused by its leaking resulting in lowered pressure ratio. It is concluded that the Reverse Brayton cycle is more efficient and simpler in control and construction than the Claude cycle.

• International Journal of Air-Conditioning and Refrigeration
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• 제17권4호
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• pp.135-140
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• 2009

A dynamic model to simulate LNG reliquefaction process has been developed. The model was applied to two candidate cycles for LNG reliquefaction process, which are Reverse Brayton and Claude cycles. The simulation was intended to simulate the pilot plant under construction for operation of the two cycles and evaluate their feasibility. According to the simulation results, both satisfy control requirements for safe operation of brazed aluminum plate-fin type heat exchangers. In view of energy consumption, the Reverse Brayton cycle is more efficient than the Claude cycle. The latter has an expansion valve in addition to the common facilities sharing with the Reverse Brayton cycle. The expansion valve is a main cause to the efficiency loss. It generates a significant amount of entropy associated with its throttling and increases circulation flow rates of the refrigerant and power consumption caused by its leaking resulting in lowered pressure ratio. It is concluded that the Reverse Brayton cycle is more efficient and simpler in control and construction than the Claude cycle.

• 한국추진공학회지
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• 제25권1호
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• pp.29-41
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• 2021

공기 흡입식 극초음속 비행체인 스크램제트의 공력 데이터를 기반으로 하여 꼬리날개 각도와 발생추력을 제어 입력으로 가지는 PID 기반 제어기를 설계했다. 일정한 비행 동압을 가지는 상승궤적과 순항 이후 목표지점을 타격하는 궤적을 기준으로 입력하여 해당 궤적을 추종하는 비행 시뮬레이션을 수행했다. 시뮬레이션 결과에 대해서 초기 상승궤적과 순항 궤적에 대해 비행체 모델에 요구되는 추력을 계산하여 수소 연료 이중 모드 스크램제트 연소기에 요구되는 연료 유량 분석을 위한 연소해석을 진행했다. 본 연구의 연소해석은 독립적으로 개발된 흡입구, 연소기, 노즐, 외부 공력 모델을 통합한 모델에 대해 진행되어 공기 흡입식 극초음속 비행체 통합 설계에 대한 기반을 마련했다.

• 대한기계학회논문집B
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• 제23권11호
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• pp.1434-1443
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• 1999

The turbulent fluctuations of temperature and two components of velocity have been measured with hot- and cold-wires in the Thermally Stratified Wind Tunnel(TSWT). Using the fin-tube heat exchanger type heaters and the neural network control algorithm, both stable ($dT/dz=109.4^{\circ}C$) and unstable ($dT/dz=-49.1^{\circ}C$) stratifications were realized. An ambient air jet was issued normally into the cross flow($U_{\infty}=1.0 m/s$) from a round nozzle(d = 6 mm) flushed at the bottom waII of the wind tunnel with the velocity ratio of $5.8(U_{jet}/U_{\infty})$. The characteristics of turbulent dispersion in the cross flow jet are found to change drastically depending on the thermal stratification. Especially, in the unstable condition, the vertical velocity fluctuation increases very rapidly at downstream of jet. The fluctuation velocity spectra and velocity-temperature cospectra along the jet centerline were obtained and compared. In the case of stable stratification, the heat flux cospectra changes Its sign from a certain point at the far field because of the restratification phenomenon. It is inferred that the main reason in the difference between the vertical heat fluxes is caused by the different length scales of the large eddy motions. The turbulent kinetic energy and scalar dissipation rates were estimated using partially non-isotropic and isotropic turbulent approximation. In the unstable case, the turbulent energy dissipation decreases more rapidly with the downstream distance than in the stable case.