• Structural Engineering and Mechanics
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• 제56권6호
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• pp.959-982
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• 2015

In this study, a non-stationary random earthquake Clough-Penzien model is used to describe earthquake ground motion. Using stochastic direct integration in combination with an equivalent linear method, a solution is established to describe the non-stationary response of lead-rubber bearing (LRB) system to a stochastic earthquake. Two parameters are used to develop an optimization method for bearing design: the post-yielding stiffness and the normalized yield strength of the isolation bearing. Using the minimization of the maximum energy response level of the upper structure subjected to an earthquake as an objective function, and with the constraints that the bearing failure probability is no more than 5% and the second shape factor of the bearing is less than 5, a calculation method for the two optimal design parameters is presented. In this optimization process, the radial basis function (RBF) response surface was applied, instead of the implicit objective function and constraints, and a sequential quadratic programming (SQP) algorithm was used to solve the optimization problems. By considering the uncertainties of the structural parameters and seismic ground motion input parameters for the optimization of the bearing design, convex set models (such as the interval model and ellipsoidal model) are used to describe the uncertainty parameters. Subsequently, the optimal bearing design parameters were expanded at their median values into first-order Taylor series expansions, and then, the Lagrange multipliers method was used to determine the upper and lower boundaries of the parameters. Moreover, using a calculation example, the impacts of site soil parameters, such as input peak ground acceleration, bearing diameter and rubber shore hardness on the optimization parameters, are investigated.

• 한국정밀공학회지
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• 제28권12호
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• pp.1388-1396
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• 2011

This paper is focused on the procedure of the development of a micro air vehicle which has vertical take-off and landing capability for indoor reconnaissance mission. Trade studies on mission feasibility led to the proposal of a coaxial rotorcraft configuration as the platform. The survey to provide a guide for preliminary design were conducted based on commercial off-the-shelf platform, and the rotor performance was estimated by the simple momentum theory. To determine the initial size of the micro air vehicle, the modified conventional fuel balance method was applied to adopt for electric powered vehicle, and the sizing problem was optimized with the sequential quadratic programming method using MATLAB. The designed rotor blades were fabricated with high strength carbon composite material and integrated with the platform. The developed coaxial rotorcraft micro air vehicle shows stable handling quality with manual flight test in indoor situation.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.330-339
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• 2008

Ground-based interceptors(GBI) comprise a major element of the strategic defense against hostile targets like Intercontinental Ballistic Missiles(ICBM) and reentry vehicles(RV) dispersed from them. An optimum design of the subsystems is required to increase the performance and reliability of these GBI. Propulsion subsystem design and optimization is the motivation for this effort. This paper describes an effort in which an entire GBI missile system, including a multi-stage solid rocket booster, is considered simultaneously in a Genetic Algorithm(GA) performance optimization process. Single goal, constrained optimization is performed. For specified payload and miss distance, time of flight, the most important component in the optimization process is the booster, for its takeoff weight, time of flight, or a combination of the two. The GBI is assumed to be a multistage missile that uses target location data provided by two ground based RF radar sensors and two low earth orbit(LEO) IR sensors. 3Dimensional model is developed for a multistage target with a boost phase acceleration profile that depends on total mass, propellant mass and the specific impulse in the gravity field. The monostatic radar cross section (RCS) data of a three stage ICBM is used. For preliminary design, GBI is assumed to have a fixed initial position from the target launch point and zero launch delay. GBI carries the Kill Vehicle(KV) to an optimal position in space to allow it to complete the intercept. The objective is to design and optimize the propulsion system for the GBI that will fulfill mission requirements and objectives. The KV weight and volume requirements are specified in the problem definition before the optimization is computed. We have considered only continuous design variables, while considering discrete variables as input. Though the number of stages should also be one of the design variables, however, in this paper it is fixed as three. The elite solution from GA is passed on to(Sequential Quadratic Programming) SQP as near optimal guess. The SQP then performs local convergence to identify the minimum mass of the GBI. The performance of the three staged GBI is validated using a ballistic missile intercept scenario modeled in Matlab/SIMULINK.

• 대한조선학회논문집
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• 제47권5호
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• pp.733-742
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• 2010

In this study, optimization was performed to improve the conventional liquefaction process of offshore plants, such as a LNG-FPSO(Liquefied Natural Gas-Floating, Production, Storage, and Offloading unit) by maximizing the energy efficiency of the process. The major equipments of the liquefaction process are compressors, expanders, and heat exchangers. These are connected by stream which has some thermodynamic properties, such as the temperature, pressure, enthalpy or specific volume, and entropy. For this, a process design problem for the liquefaction process of offshore plants was mathematically formulated as an optimization problem. The minimization of the total energy requirement of the liquefaction process was used as an objective function. Governing equations and other equations derived from thermodynamic laws acted as constraints. To solve this problem, the sequential quadratic programming(SQP) method was used. To evaluate the proposed method in this study, it was applied to the natural gas liquefaction process of the LNG-FPSO. The result showed that the proposed method could present the improved liquefaction process minimizing the total energy requirement as compared to conventional process.

• 한국항공우주학회지
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• 제50권11호
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• pp.763-770
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• 2022

다수의 드론이 운용되는 환경에서 경로점이 겹칠 때 충돌이 발생할 수 있으며 이를 대비한 충돌 회피는 필수적이다. 다수의 드론이 여러 임무를 수행하는 경우 드론의 경로가 복잡하고 충돌 예상점이 너무 많아 경로계획 단계에서 충돌을 회피하는 경로를 생성하는 방법을 사용하는 것은 적합하지 않다. 본 논문에서는 일반적으로 사용하는 경로 생성 알고리즘을 통해 경로를 생성하고, 그 경로에서 속도 프로파일 최적화를 이용한 충돌 회피 방법을 제안한다. 드론의 경로 간 충돌 예상점에서 드론 사이의 안전거리를 고려하였고, 경로 구간에 속도 프로파일을 할당하도록 설계하였다. 최적화 문제는 드론 간 거리에 대한 식을 비행시간을 변수로 두어 정의하였다. 선형화와 컨벡스화를 통해 구속 조건을 구성하고, 다수 드론 운용 환경에서 SQP(Sequential Quadratic Programming)알고리즘과 컨벡스 최적화 기법의 연산시간을 비교하였다. 마지막으로 20대 드론 운용 환경에서 컨벡스 최적화를 수행한 결과가 본 연구에서 제시한 다수 드론 운용에 적합한지 확인하였다.

• 한국강구조학회 논문집
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• 제10권3호통권36호
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• pp.553-564
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• 1998

최근도심지의 극심한 교통체증의 해소를 위한 방안으로 2층도로 강구조 덱 시스템의 채택이 증가하고 있다. 그 주된 이유는 신속한 시공과 콘크리트덱에 비하여 자중의 감소효과가 크고 보다 큰 강도와 효율적인 가설이 가능하기 때문이다. 본 연구의 목적은 강구조 덱 시스템의 최적설계프로그램을 이용한 2층도로용 강구조 덱 시스템의 가장 합리적인 형식 결정에 관한 연구이다. 최적화의 목적함수는 최소 초기비용으로 정식화하였다. 설계 제약조건은 도로교시방서의 ASD설계기준에 맞추어 정식화하였으며 최적설계과정은 두 단계로 이루어져 있다. 첫 번째 단계는 박스 또는 플레이트주형에 대한 강구조 덱 시스템의 최적설계가 수행된다. 그리고 두 번째 단계에서 개단면 또는 폐단면리브를 갖는 강상판에 대하여 최적설계를 한다. 최적설계 프로그램의 구조해석은 주형에 대하여 격자해석 모델링을 이용하였고 강상판에 대해서는 Pelican-Esslinger법을 사용하였다. 최적화 기법은 SQP를 이용하였다. 적용 예의 각 형식별 강구조 덱 시스템의 최적설계 결과의 비교를 통하여 비용의 효율성을 검토하였고 폐단면리브를 가지는 직선 형상의 박스거더 형식이 가장 효율적이고 경제적으로 판단된다.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2005년도 춘계학술대회 논문집
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• pp.1883-1886
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• 2005

In this paper, a decoupled dual servo (DDS) stage for ultra-precision scanning system with large working range is introduced. In general, dual servo systems consist of a fine stage for short range and a coarse stage for long range. The proposed DDS also consists of a $XY\theta$ fine stage for handling and carrying workpieces and one axis coarse stage. Its coarse stage consists of air bearing guide system and a coreless linear motor with force ripple. The fine has four voice coil motors(VCM) as its actuator. According to a VCM's nature, there are no mechanical connections between coils and magnetic circuits. Moreover, VCM doesn't have force ripples due to imperfections of commutation components of linear motor systems - currents and flux densities. However, due to the VCM's mechanical constraints the working range of the fine is about $25mm^2$. To break that hurdle, the coarse stage with linear motors is used to move the fine about 500mm. Because of the above reasons, the proposed DDS can achieve higher precision scanning than other stages with only one servo. With MATLAB's Sequential Quadratic Programming (SQP), the VCMs are optimally designed for the highest force under conditions and constraints such as thermal dissipations due to its coil, its size, and so on. And for their movements without any frictions, guide systems of the DDS are composed of air bearings. To get precisely their positions, a linear scale with 5nm resolution are used for the coarse stage's motion and three plane mirror laser interferometers with 5nm for the fine's $XY\theta$ motions. With them, on scanning the two stages have same trajectories. The control algorithm is named Parallel method. The embodied ultra-precision scanning system has sub 100nm following error and in-positioning stability.