• 한국군사과학기술학회지
• /
• 제20권2호
• /
• pp.255-263
• /
• 2017

An infrared-guided missile has been emerging as a major threat against combat aircraft due to its passive guidance characteristics and with recent advances in stealth technology. Hence, the infrared stealth technology and its effectiveness-evaluation technique become more significant than ever before. In this study, we applied missile aerodynamics to lethal range calculation which allowed more precise prediction. CFD analyses were newly involved in estimating drag force characteristics of an infrared-guided missile. Velocity profiles during flight period of the missile were constructed utilizing these drag characteristics and then incorporated into our in-house code to predict corresponding lethal ranges. The results showed that the present method can predict lethal range more appropriately than the previous one with constant velocity profile. As one of the results, if a fighter gains altitude more which reduces less drag of the attacking missile, then the lethal envelope increases significantly more compared to the lock-on envelope.

• 한국항공우주학회지
• /
• 제33권8호
• /
• pp.50-55
• /
• 2005

현대의 고성능 전투기는 공력성능 및 조종성능의 향상을 위하여 대부분 세로축 방향으로 항공기를 불안정하게 설계하는 정안정성 완화(Relaxed Static Stability) 개념을 채택하고 있다. 비행제어법칙의 설계 작업은 이러한 불안정하게 설계된 항공기가 주어진 비행임무에 대하여 만족스런 안정성과 조종성능을 발휘할 수 있도록 비행성능을 조작하는 일련의 과정이다. 전투기의 조종성능은 공대공 전투(Air-to-Air Fighting)와 공대지 전투(Air-to-Ground Fighting)로 분류할 수 있다. 공대공 전투 시에는 전체포착(Gross Acquisition) 및 정밀추적(Fine Tracking)성능을 동시에 만족해야 한다. T-50 비행시험 결과, 공대공 추적에서 전체포착성능은 만족하지만, 정밀추적성능은 만족하지 못하였다. 본 논문에서는 정밀추적성능의 향상을 위해 새로운 개념의 세로축 제어법칙 적용에 관한 연구 방향을 제시하였다. HQS 조종사 시뮬레이션 및 비행시험 결과, 본 제어법칙을 적용하였을 때 전체포착성능의 저하 없이 정밀추적성능을 개선시킬 수 있었다.

• 한국항공우주학회지
• /
• 제34권11호
• /
• pp.35-41
• /
• 2006

이 논문에서는 항공기의 비행제어에 적용하기 위해 각각의 비행영역에서 설계된 LQ(Linear Quadratic)제어기를 비행영역이 바뀜에도 충돌 없이 교체할 수 있는 알고리즘을 제안한다. 이 알고리즘은 기존의 구현 알고리즘에 비해 LQ제어기에 적용하기 편리하게 유도되었고, 비선형 모델에도 적용할 수 있도록 트림점을 포함한 식으로 제시된다. 제안된 알고리즘의 성능을 확인하기 위해 시험표준 문제로 초음속 시험 항공기의 LQ제어문제에 적용하는 모의실험을 수행하고 제어성능이 우수함을 예시한다.

• International Journal of Aeronautical and Space Sciences
• /
• 제11권4호
• /
• pp.247-265
• /
• 2010

Multi-objective design exploration (MODE) and its applications are reviewed as an attempt to utilize numerical simulation in aerospace engineering design. MODE reveals the structure of the design space based on trade-off information. A self-organizing map (SOM) is incorporated into MODE as a visual data mining tool for the design space. SOM divides the design space into clusters with specific design features. This article reviews existing visual data mining techniques applied to engineering problems. Then, we discuss three applications of MODE: multidisciplinary design optimization for a regional-jet wing, silent supersonic technology demonstrator and centrifugal diffusers.

• 항공우주정책ㆍ법학회지
• /
• 제19권1호
• /
• pp.109-139
• /
• 2004

라이트형제에 의한 비행기(飛行機)의 개발(開發)은 동세기(同世紀) 항공공학(航空工學)의 급속(急速))한 발전(發展)을 이루어 항공기를 이용하여 태평양을 횡단하고, 소리의 속도보다 빠르게 비행하게 되었으며, 수백명이 우주(宇宙) 비행(飛行)을 하였고, 10여명이 달에 다녀왔다. 그러나 이 경이로운 인간의 기술이면에는 항공기의 개발과 더불어 항공사고라는 난점이 자리하고 있다. 항공의 발달은 운송수단으로서 타 교통수단의 경쟁을 유도하였고, 항공산업의 획기적인 발달을 이룩하여 모든 여행객들과 물류수송에 선도적인 역할을 담당하고 있다. 그러나, 항공활동의 증가는 대조적으로 항공사고를 수반하게 되고, 사고시는 막대한 인명과 재산피해를 동반하게 된다. 따라서 향후 개발되는 항공기 의 초대형화와 신기술 개발 및 항공 교통량의 증가에 비례하여 항공사고건수 또한 증가할 것이며 항공사고는 인명 및 재산피해의 초대형화를 동반할 것이다. 이러한 항공사고 방지를 위해 사고조사의 전문화, 체계화 및 과학화가 필수적이다. 이를 달성하기 위한 항공사고 조사기구의 효율적인 역할을 수행하기 위하여는 사고조사위원회 위원의 상근화, 통합적사고 조사기구의 신설, 사고조사관의 제도적 신분보장, 인적요소분야 사고조사관의 확보(確保), 사고조사관의 법적 책임 한계, 사고(accident)와 중대한 준사고(serious incident)에 대한 정의와 조사범위, 그리고 민간항공기와 국가항공기가 연관된 사고 발생시 조사의 주체가 관련규정에 명시될 필요성이 개선방안(改善方案)으로 연구되었다.

• Advances in aircraft and spacecraft science
• /
• 제8권4호
• /
• pp.345-372
• /
• 2021

The analysis of nonlinear vibrations, buckling, post-buckling, flutter boundary determination and post-flutter behavior of a homogeneous curved plate assuming cylindrical bending is conducted in this article. Other assumptions include simply-supported boundary conditions, supersonic aerodynamic flow at the top of the plate, constant pressure conditions below the plate, non-viscous flow model (using first- and third-order piston theory), nonlinear structural model with large deformations, and application of mechanical and thermal loads on the curved plate. The analysis is performed with constant environmental indicators (flow density, heat, Reynolds number and Mach number). The material properties (i.e., coefficient of thermal expansion and modulus of elasticity) are temperature-dependent. The equations are derived using the principle of virtual displacement. Furthermore, based on the definitions of virtual work, the potential and kinetic energy of the final relations in the integral form, and the governing nonlinear differential equations are obtained after fractional integration. This problem is solved using two approaches. The frequency analysis and flutter are studied in the first approach by transferring the handle of ordinary differential equations to the state space, calculating the system Jacobin matrix and analyzing the eigenvalue to determine the instability conditions. The second approach discusses the nonlinear frequency analysis and nonlinear flutter using the semi-analytical solution of governing differential equations based on the weighted residual method. The partial differential equations are converted to ordinary differential equations, after which they are solved based on the Runge-Kutta fourth- and fifth-order methods. The comparison between the results of frequency and flutter analysis of curved plate is linearly and nonlinearly performed for the first time. The results show that the plate curvature has a profound impact on the instability boundary of the plate under supersonic aerodynamic loading. The flutter boundary decreases with growing thermal load and increases with growing curvature.

• 한국유체기계학회 논문집
• /
• 제16권3호
• /
• pp.10-17
• /
• 2013

The organic Rankine cycle has been widely used to convert the renewable energy such as the solar energy, the geothermal energy, or the waste energy etc., to the electric power. Some previous studies focused to find what kind of refrigerant would be a best working fluid for the organic Rankine cycle. In this study, R245fa was chosen to the working fluid, and the cycle analysis was conducted for the output power of 30kW or less. In addition, properties (temperature, pressure, entropy, and enthalpy etc.) of the working fluid on the cycle were predicted when the turbine output power was controlled by adjusting the mass flowrate. The configuration of the turbine was a radial-type and the supersonic nozzles were applied as the stator. So, the turbine was operated in partial admission. The turbine efficiency and the optimum velocity ratio were considered in the cycle analysis for the low partial admission rate. The computed results show that the system efficiency is affected by the partial admission rate more than the temperature of the evaporator.

• 한국군사과학기술학회지
• /
• 제10권4호
• /
• pp.81-87
• /
• 2007

In this study, analysis of structural design criteria for the canopy actuating device has been conducted considering the aerodynamic breakaway capabilities of jettisonable canopy system. Unsteady aerodynamic loads for the opened canopy configuration at passively controlled jettision mode were computed using CFD method. The general purpose multi-body finite element code, SAMCEF Mecano, is used in the implemented analyses for the passive jettision condition. The recommended altitude and speed of aircraft was suggested as design criteria of aerodynamic breakaway capability of jettisonable canopy system as a bakup egress method when normal canopy jettison sequence malfunctioned. Aerodynamic breakaway condition of jettisonable canopy was also simulated and the fracture load conditions of canopy actuator were investigated.

• 대한기계학회논문집B
• /
• 제21권9호
• /
• pp.1095-1104
• /
• 1997

When a high-speed railway train enters a tunnel, a compression wave is generated ahead of the train and propagates along the tunnel, compressing and accelerating the rest air in front of the wave. At the exit of the tunnel, an impulsive wave is emitted outward toward the surrounding, which causes a positive impulsive noise like a kind of sonic boom produced by a supersonic aircraft. With the advent of high-speed train, such an impulsive noise can be large enough to cause the noise problem, unless some attempts are made to alleviate its pressure levels. For the purpose of the impulsive noise reduction, the present study investigated the effect of a vertical bleed duct on the compression wave propagating into a model tunnel. Numerical results were obtained using a Piecewise Linear Method and testified by experiment of shock tube with an open end. The results showed that the vertical bleed duct reduces the maximum pressure gradient of compression wave front by about 30 percent, compared with the straight tunnel without the bleed duct. As the width of the vertical bleed duct becomes larger, reduction of the impulsive noise is expected to be greater. However the impulsive noise is independent of the height of the vertical bleed duct.

• 대한기계학회논문집B
• /
• 제21권11호
• /
• pp.1403-1412
• /
• 1997

When a high-speed railway train enters a tunnel, a compression wave is generated ahead of the train and propagates through the tunnel, compressing and accelerating the rest air in front of the wave. At the exit of the tunnel, an impulsive wave is emitted outward toward the surrounding, which causes a positive impulsive noise like a kind of sonic boom produced by a supersonic aircraft. With the advent of high-speed train, such an impulsive noise can be large enough to cause the noise problem, unless some attempts are made to alleviate its pressure levels. In the purpose of the impulsive noise reduction, the present study calculated the effect of porous walls on the compression wave propagating into a model tunnel. Two-dimensional unsteady compressible equations were differenced by using a Piecewise Linear Method. Calculation results show that the cavity/porous wall system is very effective for a compression wave with a large nonlinear effect. The porosity of 30% is most effective for the reduction of the maximum pressure gradient of the compression wave front. The present calculation results are in a good agreement with experimental ones obtained previously.