This paper deals with manufacturing process design of a simplified gun tube applying CE principle. A concept and characteristics of CE, mathematical model for understanding interaction between design and manufacturing, basic elements and related equations for process planning and cost estimating are introduced. A Knowledge-based Computer-Aided Process Planning System(KCAPPS) is constructed, yielding optimal production cost/time for the shape input and selection of appropriate machines and tools.

The purpose of this study is to develop a method of applying response surface analysis to trade-off techniques for the conceptual design of armored vehicle. The problem areas of concern are the use of this method in the selection of optimum design points when user requirements are in conflict. The application of this method to trade-offs of performance parameters in terms of weight are presented.

In this paper, we have proposed a novel method which can compose a reflected signal of the underwater target. The synthesis of the reflected signal in the target, the synthesized signal being similar to the characteristics of the reflected signal in the real target, is used the highlight model at the specific points of the target. We suggest the synthesis method of the reflected signal of the target using the pulsewidth variation and each other doppler effect at the highlight point, and compare the composed signal by the proposed method with that by conventional one. Simulation results show that the composed signal using the proposed method and the reflected signal of the real target is similar to the spectral characteristics.

This paper reviews the combat survivability and supermaneuverbility which are principal factors in current and future high performance combat aircraft design. First of all, the fighter agility evaluation factors were presented. And then, emphasis was put on technologies associated with supermaneuverbility, such as vortex lift, high angle of attack aerodynamics, thrust vectoring and control system technologies that integrate each technology. The advanced nations' supermaneuverbility R/D programs were introduced as well.

By implementing the Systems Engineering process for the aircraft preliminary design, functional analysis study is performed, hence Functional Interface Data Flow(FIDF) and Functional Flow Block Diagram(FFBD) are generated. Based on FIDF and FFBD, allocable and non-allocable design/performance/RM＆S requirements are allocated to the appropriate levels. Weight and cost tracking and design margin management methodologies are studied and implemented for the balanced aircraft design.

A dynamic stability test was performed to determine dynamic stability derivatives for the pure pitching motion of air-to-ground missile model in the low speed wind tunnel. The free vibration technique was employed to acquire oscillation characteristics of the model for damping coefficients. Damping coefficients are obtained by the method of logarithmic decrement. Results show good damping effects and stability capability at Mach numbers 0.1 and 0.2, with the angle of attack ranging from -15 to +20 degrees.

During the aircraft conceptual design stage, rapid aerodynamic analyses over various configurations are required. Hence, empirical and analytical methods play important roles in predicting the aero-dynamic characteristics. In this study, total drag estimation method based on empirical and analytical approaches is developed. By comparing with the results of the wind tunnel experiment and existing prediction methods, it is demonstrated that the developed method is accurate and useful in predicting total drag for the whole Mach number range.

Dynamic characteristic of manufacturing stage is understood and the utilization of each machine is maximized by developing on-line dynamic CAPP system to consider the overloads in the aircraft part manufacturing line. In this paper, a scheme of production planning and scheduling system was proposed through inspection about some predeveloped CAPP system. Developed production planning and scheduling system included process planning module. After precise inspection of some FMS line schema at domestic heavy industry, optimized FMS line was applied to aircraft part manufacturing and repairing factory. By virtue of considering overloads of factory and machine through on-line dynamic CAPP system, the utilization of resources is maximized and manufacturing lead time is minimized.

Dynamic behavior of missile which is fired in canister is analyzed by flexible multibody dynamics. The bending elasticity of missile is very important in case that missile is fired in the inclined launcher. In this paper, the force element model for the missile launching stage and the finite element model of missile are developed. The FEA model of missile is condensed into five lumped mass element model and the consistence between FE model and lumped mass model of missile is verified by modal analysis. As a result of analysis, sabot reaction force and pitch rate of missile for the variation of gap size and force element are obtained.

자동차, 항공기 혹은 로켓엔진 유동장의 불안정 파동은 음향모드와 와류모드 및 엔트로피 모드에 의해 복합적으로 발생한다. 본 연구에서는 이들 모드를 모두 포함하는 불안정 해석이론을 바탕으로 고체추진 로켓엔진 연소실의 내부유동을 대상으로 불안정 파동 증폭요인에 의한 영향을 고찰하였다. 연구결과 불안정 에너지 증폭계수의 증가에 따라 에너지 증폭율 관련변수들이 증가하며 에너지 증폭율 관련변수들은 층류보다 난류에서 더 크게 나타났다. 또한 고온의 측면-연소 로켓의 불안정 파동은 엔트로피 모드에 의해 지배되며 와류모드에 다소간 영향을 받고 음향모드에는 거의 영향을 받지 않았다.

Supersonic flows over an EFP(explosively formed projectile) have been calculated by a high-order conservation law scheme and two-layer $$textsc{k}$-{\varepsilon}$ model on hybrid viscous unstructured mesh. To verify the accuracy and robustness of the developed code, two basic flows about airfoils are computed and results are compared with existing experimental data and computational results. The comparisons confirm the validity of the code and justify our use for such a highly supersonic and viscous flow over a blunt body. Complex flow features of supersonic flows over an EFP are clearly captured and show agreements with the flow visualization. From the interaction of oblique shocks near the surface of flare, flow structures, that were not identified by previous experimental results, are discovered as a result of present computation.

In this paper, the performance of data communication function of military radio equipment P-999K is analyzed based on the standard CSMA/CA protocol which is DFWMAC standard protocol done by IEEE802.11 work group. Basic three standard protocols, i.e. Basic CSMA/CA, Stop & Wait ARQ and 4-Way Handshake CSMA/CA protocols are analyzed and compared with each other under the hidden terminal environment. The computer simulation is also done by using SIMSCRIPT II.5 which is popular software tool for an independent processing. The results show that p-persistent(with p=0.3) CSMA scheme is superior to non-persistent CSMA scheme with non-hidden terminal condition, but the performances of both schemes are almost same with hidden terminal situation. And the results of computer simulations are also showed that Basic CSMA/CA protocol is superior to the other protocols when the ratio of hidden terminals is below 10 % of total user population, however, with the above 20% hidden terminals environment and the higher offered traffic conditions the 4-Way Handshake CSMA/CA protocol shows the most superior performance.

An easy and efficient method is proposed for a computation of reliability of preprocessing filters in the fire control system when the sensor data are frequently unreliable depending on the operation environment. It computes state transition probability matrix after modeling filter states as a Markov process, and computing false alarm and detection probability of each filter state under the given sensor failure probability. It shows that two important indices such as distributed state probability and error variance can be derived easily for a reliability assessment of the given sensor fusion system.

A gene expressing organophosphorus acid (OPA) anhydrolases have been cloned from Alteromonas haloplanktis strain and expressed in bacterial strain BL21. Crude extract was prepared from the transformed bacterial strain BL2l and used in testing its degrading capability of real nerve gas, soman and sarin. Within 1 minute after the start of the reaction, nearly 65% of the soman added to the reactant(3mM) was degraded by adding 1 mg of the crude extract enzyme(20.0 Unit $mg^-{1}$ crude protein). In 6 minutes, the reaction reached at its steady state, which indicates that soman was completely degraded by that time. In the case of sarin, the degradation efficiency was observed to be about 0.7 times of that of soman. If the specific activity of OPAA is enhanced by both increased expression efficiency and purification, OPAA seems to be applied for the development of decontaminant of skin, especially of eye.

유한요소기법을 적용하여 열하중을 받는 원통형 복합적층 패널의 좌굴후 거동해석 및 진동 특성을 연구하였다. 열적 대변형을 고려하기 위해 층별변위장이론을 바탕으로 한 von-Karman 비선형 변위-변형률 관계식을 적용하였다. 원통형 패널의 스냅핑 현상을 해석하기 위해서 원통형 호길이법이 사용되었다. 원통형 패널의 두께비, shallowness angle 그리고 경계조건 등 여러 가지 구조 파라미터에 따라 열적 스냅핑과 진동 특성을 고찰하였다. 열적 스냅핑 특성이 정적인 변형뿐만 아니라 진동 모드 형상 및 순서를 변화시키고 있음을 보여준다.

Production and measurement of a super-polished few-ppm-scattering mirror substrate are investigated. In order to improve the surface roughness directly determining scattering, the super-polishing process using Bowl-Feed technique is tried. The surface quality of the super-polished substrate is estimated by the phase-measuring interferometer. For the reliable roughness measurement using the interferometer, data averaging method is applied so that the optimal data averaging condition, 30 phase-data averaging and 20 intensity-data averaging, minimizing the measurement error is experimently searched. Based on the optimal data averaging condition, surface roughness of home-made mirror substrate is measured to be less than $0.5{\AA}$ rms corresponding to 2-ppm total-integrated-scattering.

Weapon system is defined as a combination of primary system and logistics support system which are evaluated by capability and operational availability respectively. Weapon system developer thought that primary system was weapon system and also only primary system was important. Recent comparison of total life cycle cost showed that logistics support system was proved to be more important than primary system. However, until now no systematic approach to logistics support system development have applied in the area of developing support system and much money was exhausted by wrong logistics support system. We need to construct a universal metric for effectiveness of logistics support system and to cut out whatever activities or support elements which do not contribute to the metrics. This study describes a new approach under the name function approach to logistics support system development and also classifies five factors of failure frequency, stock out of frequency, administrative delay time, active repair time and logistic delay time that have influence on operational availability of logistics support system.

고품질의 소프트웨어를 개발하는 사업의 중요성이 나날이 증대되고 있는 시점에서 소프트웨어를 종합군수지원 관점에서 해석하려고 하는 연구가 최근에 진행되고 있다. 즉, 소프트웨어 설계자의 입장은 소프트웨어 개발도 중요한 문제이지만 소프트웨어를 얼마나 가용성 있게 유지하는가에 더 많은 관심을 갖게 된다. 하드웨어는 개발 시부터 종합군수지원이라는 기법을 적용하여 체계 배치 시 체계 장비가 최상의 가용도를 가질 수 있도록 하는 노력이 이루어지고 있으며, 그 결과도 현실화되고 있다. 본 논문에서는 하드웨어에서만 적용하고 있는 종합군수지원 개발 기법을 소프트웨어에 적용하여 소프트웨어에 대한 종합군수지원 적용방안을 제시하고, 향후 소프트웨어 개발/배치 시에 경제적이고 가용도가 높은 소프트웨어의 개발/활용이 가능하도록 군수지원 분석을 통한 종합군수지원 활용 방안을 제안한다.

The CPS provides data with long-term stability independent of passed time and the INS provides high-rate data with short-term stability. By integrating these complementary systems, a highly accurate navigation system can be achieved. In this paper, a loosely-coupled GPS/INS integration system is designed. It is a simple structure and is easy to implement and preserves independent navigation capability of GPS and INS. The integration system consists of a NCU, an IMU, a GPS receiver, and a monitoring system. The navigation algorithm in the NCU is designed under the multi-tasking environment based on a real-time kernel system and the monitoring system is designed using the Visual C++. The integrated Kalman filter is designed as a feedback formed 15-state filter, in which the states are position errors, velocity errors, attitude errors and sensor bias errors. The van test result shows that the integrated system provides more accurate navigation solution then the inertial or the GPS-alone navigation system.

위험관리는 최근 다양한 분야의 산업에 적용 가능한 매우 중요한 토픽이다. 본 연구에서는 기본적인 위험관리의 일반적인 방법론과 새로운 위험관리 평가의 방법론을 제시한다. 위험관리의 실제 적용에 있어서 재정, 보험산업 등의 분야에서는 이미 많은 현실적 방법론들이 개발되었다. 다양한 산업현장에서 발전된 많은 적용사례들이 있으나 여전히 위험관리는 어려운 부분이며, 두 가지 주요한 위험평가 방법론이 시스템 엔지니어링 분야에서 개선되고 발전되어왔다. 그중 하나는 본래의 위험평가의 기본개념을 바탕으로 하여 발전한 것이며 다른 하나는 소프트웨어 엔지니어링분야의 위험평가에서 비롯된 것이다. 규모가 크고 복잡한 시스템에서 효과적인 위험관리는 프로젝트의 최종 목적을 달성하는데 있어서 불확실성에 적절히 대처하여 총 개발비용을 줄이고 목표일정과 성능을 달성하는 효과를 가져온다.

In this paper, an integrated S/W system from CAD to optimal design has been suggested and an application to a precision machine tool structure shown. The integrated system is so designed to reduce manual interfacing effort. An object-oriented programming language is used for combining 3-D CAD program, FEM and optimal design tools. In this system parametric modelling technique is applied and users can get the optimum design iteratively without much user intervention. The CAD model is automatically updated when the design parameters are transferred back to the CAD program. Not only design time can be dramatically reduced but unnecessary operation errors avoided by the integration.

This paper contains the computational simulation of a free rocket with a parachute and the development of a firing table for each range. To obtain the trajectory of the rocket, 6 DOF model of rocket with parachute was generated and the wind tunnel test was done for the input parameters. Good agreement was obtained between the analysis of trajectory and the flight test result. Also the trajectory error analysis was performed by the Monte Carlo simulation. As a result of simulation, the CEP(Circular Error Probability) of the firing table was calculated.

A transmitting antenna mounted on the naval vessels can be easily exited by exogenous disturbances such as wave and impact. Gimbal system need for the controller to maintain the robust performance against various modeling uncertainties and disturbances. PI controller, however, cannot supply good robust performance under situation. Thus a robust $H_{\infty}$ control scheme is used to ensure a specified dynamic response under above conditions. Gimbal system controlled simplified as 2 DOF system that ignored coordinate co-relations of each direction and hydraulic system is linearly modelled. In this paper, we compared those of simulation to the results of experiment and H$_{\infty}$ controller, proposed, showed the good response and stability than PI controller.

본 논문에서는 얇은 직사각형 단면 형상을 가지는 세 가지 서로 다른 유동로 안에서 움직이는 공기버블의 변형 거동에 대한 실험을 수행하였다. 압력 차이로 유체는 유동되며, 유동장을 따라서 변형하는 버블의 정상상태 모양을 관찰하였다. 벽면효과를 알아보기 위해 세 종류의 얇은 사각단면을 사용하였으며, 두 가지 종류의 작동 유체, 버블의 초기 크기, 작동 유체의 유량 등을 변화시켰을 때 이에 대한 공기 버블의 변형을 체계적으로 관찰하고 이들의 관계를 고찰하였다. 실험데이타를 정량화하여 캐필러리 수에 대한 버블의 무차원 속도비와의 관계를 상세하게 고찰하였다. 글리세린의 경우는 항상 버블 선단부의 곡률이 후단의 곡률보다 더 작게 나타났으며 실리콘 오일의 경우와 반대 경향이 관찰되었다. 두 경우 모두 캐필러리 수에 대한 속도비와 세장비 값은 1 보다 큰 값을 가졌다. 실리콘 오일의 경우는 주어진 Ca 수에 대하여 속도비가 글리세린의 경우보다 더 크게 나왔으며 버블 크기에 따른 속도비 분산도가 더 조밀하게 나타났다. 사각 단면 폭이 감소할수록 벽면 효과는 증대되었으며 같은 폭에 대해서는 버블 변형이 축소관의 경우가 가장 크게 나타났다.

This paper presents an estimation scheme of the external torque applied on the motor by using measured motor input current when the IPM(Interior Permanent Magnet) rotor type BLDC motor operates with constant speed. In general, the BLDC motor is controlled by vector control method. If it could be operated at over critical speed, the control scheme must be modified to flux-weakening control method. The external torque applied on the motor using flux-weakening control method could not be calculated by conventional torque equation because the demagnetizing current Id exists in the motor input current. In this paper, the commonly used flux-weakening control method is studied and the modified torque estimation scheme is suggested. The estimation scheme has been verified by the simulations and experimental results.

The stiffness of joint parts in the finite element beam model are corrected by the direct comparison between the modal test and analysis model. The corrected stiffness are reviewed according to the boundary conditions of modal testing. For the improved modal test/analysis correction, more modes measured than acceleration sensors are used to make a minimal order system model. In addition, the initial F.E. model is reduced to the degrees of freedom of a minimal order system model, keeping the dynamics of the initial model. Finally, for the parametric correction of the reduced model, the submatrices are used to model the initially assumed stiffness.

본 논문은 측정시스템의 정확도와 불확도 설정, 측정기법 및 측정시스템에 대한 공인화 방안을 제시하고 있다. 측정오차는 크게 정적오차 및 동적오차로 구분되는데, 측정시 항상 존재할 수 있는 정적오차를 구할 수 있는 오차방정식과, 공인화 절차를 제안하였다.

An alternative panel flutter approach utilizing minimum angle is presented. The minimum angle is the lowest value among the angles between modes i and j at a certain pressure condition. This method utilizes eigenvectors rather than eigenvalues. Cross-ply composite plates are considered in this study. A remarkable result of this investigation is that the angle always dropped gradually to zero for all presented examples

Wall-bounded 유동과 달리 자유 전단 유동은 Hyperbolic Tangent Profile을 가지고 비점성 불안정에 의해 지배된다. 따라서 자유 전단 유동에서 난류로의 천이과정은 비점성 불안정성 이론에 의해 해석되어 진다. 본 연구는 분리판(Splitter plate)에 의해 분리된 속도가 다른 자유 유속의 혼합에 의해 형성되는 혼합층에서 와류병합과정에 대한 속도비의 영향에 대하여 연구한다. 속도비는, R, $ \frac{U_1-U_2}{U_1+U_2}$ 로 정의되며, 여기서 $U_1$은 분리판 위에서의 자유 유속을 그리고 $U_2$ 는 분리판 아래에서의 자유 유속을 나타낸다. 본 연구에서 와류구조의 병합작용을 분석하기 위하여 2차원 비정상 Large-Eddy Simulation 방법을 적용하였다. 속도비의 변화에 따라 혼합층에서 불안정 Wave가 성장하게 되고, 유체는 2차원 와류구조에서 Roll-up한다. 이러한 2차원 와류구조는 주위의 다른 와류구조와 상호작용을 하게 되고 하나의 커다란 와류구조를 형성하는 것을 볼 수 있다. 혼합층에서 와류병합과정은 반복적으로 일어나는 것을 알 수 있었고, 이 결과를 이용하여 혼합층의 성장을 제어할 수 있다.