• 한국항공우주학회지
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• 제39권1호
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• pp.50-55
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• 2011

본 연구에서는 고고도 장기 체공 항공기 날개의 스팬과 주날개보의 형상을 설계변수로 동시에 고려하는 공력-구조 동시 설계를 수행하였다. 이 때 공기역학적 성능 최대화와 중량 최소화를 한 번에 수행하기 위해 다목적 최적화를 이용하였다. 설계 대상이 된 날개는 구조적 대변형이 발생되므로 전산유체역학과 유한요소법을 이용하여 비선형 정적 공탄성 해석을 수행하였다. 설계를 위한 해석에 요구되는 계산 비용을 감소시키기 위해 반응면을 구성하였으며 이를 위해 실험계획법이 이용되었다. 또한 본 연구에서는 대변형이 발생되지 않은 형상과 대변형이 발생한 형상의 공력 성능을 비교하여 대변형이 발생하는 경우 설계를 위해 반드시 변형이 고려되어야 함을 검증하였다.

• International Journal of Aeronautical and Space Sciences
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• 제2권2호
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• pp.95-107
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• 2001

This paper is devoted to the parameter optimization of unmanned aerial vehicle's (UAV) flight control laws. Optimization procedure is based on the ideas of mixed $H_2/H_{\infty}$ control of multi-model plants. By using this approach, some partial $H_2$-terms defining the performance of nominal and parametrically perturbed Flight Control System (FCS) responses to deterministic command signals in stochastic atmosphere as well as $H_{\infty}$-terms defining robustness of the FCS can be incorporated in the composite cost function. Special penalty function imposed on the location of closed-loop system's poles keeps the speed of response and oscillatory properties for both nominal and perturbed FCS in reasonable limits. That is the reason why this procedure may provide reasonable trade-off between the performance and robustness of FCS that are very important especially for UAV. Its practical importance is illustrated by case studies of lateral and longitudinal control of small UAV.

• 한국자동차공학회논문집
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• 제14권1호
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• pp.1-7
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• 2006

This paper presents an ASF (Aluminum Space Frame) BIW optimal design, which minimizes the weight and satisfies multi-disciplinary constraints such as the static stiffness, vibration characteristics, low-speed crash, high-speed crash and occupant protection. As only one cycle CPU time for all the analyses is 12 hours, the ASF design having 11-design variable is a large scaled problem. In this study, ISCD-II and conservative least square fitting method is used for efficient RSM modeling. Then, ALM method is used to solve the approximate optimization problem. The approximate optimum is sequentially added to remodel the RSM. The proposed optimization method used only 20 analyses to solve the 11-design variable design problem. Also, the optimal design can reduce the] $15\%$ of total weight while satisfying all of the multi-disciplinary design constraints.

• 한국항공우주학회지
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• 제50권7호
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• pp.445-454
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• 2022

항공기가 빙점 이하의 습도가 높은 구름대를 지날 때 액적이 항공기와 충돌하면 날개, 동체 등 항공기 구성품에 결빙이 발생한다. 특히 항공기의 날개에 결빙이 증식되면 공력 성능의 저하와 비행 안정성의 감소 등의 치명적인 안전 문제를 초래할 수 있다. 본 연구에서는 항공기 날개에 적용되는 고양력 장치인 다중 익형의 결빙 증식량이 최소가 되도록 형상 최적설계를 수행하였다. 3차원 Reynolds-Averaged Navier-Stokes 지배 방정식을 이용하여 공력해석을 수행하였고, 다물리 전산해석을 통해 결빙의 형상 및 증식량을 예측하였다. 최적설계의 목적함수는 결빙 증식량 최소화로 설정하였고, 설계변수는 Slat과 Flap의 전개 각도와 위치를 정의하는 형상 변수 6개를 선정하였다. 설계 과정에서 목적함수의 평가는 크리깅 근사모델을 사용하여 대체하였고 유전자 알고리즘을 적용하여 최적 형상을 도출하였다. 최적화를 수행한 결과, Slat과 Flap에 최적의 전개 각도와 위치를 적용하였을 때 결빙 증식량이 약 8% 감소하였다.

• 한국생산제조학회지
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• 제21권6호
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• pp.954-960
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• 2012

Nowadays, rapidly changing and unstable global economic environments request a lot of roles to engineers. In this situation, product should be designed to make more profit by cost down and to satisfy distinguished performance comparing to other competitive ones. In this research, the optimization design of the industrial robot casting will be done. The weight and deflection have to be reduced as objective functions and stress has to be constrained under some constant value. To reduce time cost, CCD (Central Composite Design) will be used to make experimental design. And RSM (Response Surface Methodology) will be taken to make regression model for objective functions and constraint function. Finally, optimization will be done with Genetic Algorithm. In this problem, the objective functions are multiple, so NSGA-II which is brilliant and efficient for such a problem will be used. For the solution quality check, the diversity between Pareto solutions will be also checked.

• Structural Engineering and Mechanics
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• 제88권6호
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• pp.521-533
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• 2023

In the present study, the finite volume method is applied for the thermal performance prediction of the natural ventilation system using vertical solar chimney whereas, design parameters are optimized through the response surface methodology (RSM). The computational simulations are performed for various parameters of the solar chimney such as absorber temperature (40≤T_abs≤70℃), inlet temperature (20≤T₀≤30℃), inlet height of (0.1≤h≤0.2 m) and chimney width (0.1≤d≤0.2 m). Analysis of variance (ANOVA) was carried out to identify the design parameters that influence the average Nusselt number (Nu) and mass flow rate (ṁ). Then, quadratic polynomial regression models were developed to predict of all the response parameters. Consequently, numerical and graphical optimizations were performed to achieve multi-objective optimization for the desired criteria. According to the desirability function approach, it can be seen that the optimum objective functions are Nu=25.67 and ṁ=24.68 kg/h·m, corresponding to design parameters h=0.18 m, d=0.2 m, T_abs=46.81℃ and T₀=20℃. The optimal ventilation flow rate is enhanced by about 96.65% compared to the minimum ventilation rate, while solar energy consumption is reduced by 49.54% compared to the maximum ventilation rate.

• Steel and Composite Structures
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• 제27권4호
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• pp.427-438
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• 2018

In this paper, the single and multi-objective optimization of thin-walled conical tubes with different types of indentations under axial impact has been investigated using surrogate models called metamodels. The geometry of tapered thin-walled tubes has been studied in order to achieve maximum specific energy absorption (SEA) and minimum peak crushing force (PCF). The height, radius, thickness, tapered angle of the tube, and the radius of indentation have been considered as design variables. Based on the design of experiments (DOE) method, the generated sample points are computed using the explicit finite element code. Different surrogate models including Kriging, Feed Forward Neural Network (FNN), Radial Basis Neural Network (RNN), and Response Surface Modelling (RSM) comprised to evaluate the appropriation of such models. The comparison study between surrogate models and the exploration of indentation shapes have been provided. The obtained results show that the RNN method has the minimum mean squared error (MSE) in training points compared to the other methods. Meanwhile, optimization based on surrogate models with lower values of MSE does not provide optimum results. The RNN method demonstrates a lower crashworthiness performance (with a lower value of 125.7% for SEA and a higher value of 56.8% for PCF) in comparison to RSM with an error order of $10^{-3}$. The SEA values can be increased by 17.6% and PCF values can be decreased by 24.63% by different types of indentation. In a specific geometry, higher SEA and lower PCF require triangular and circular shapes of indentation, respectively.

• 한국항공우주학회지
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• 제40권3호
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• pp.251-257
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• 2012

무인기 및 유인기의 자동비행제어기는 다양한 비행성 규정, 안정도 여유 및 시간응답 특성에 대한 요구조건을 만족할 수 있도록 설계되어야 한다. 기존의 제어기 설계과정은 많은 시간과 시행오차를 수반하기 때문에 최적화 알고리즘을 활용하면 다양한 요구조건들을 충족시키는 제어기를 효율적으로 설계할 수 있다. 본 논문에서는 통합 최적화 제어설계 프로그램인 CONDUIT을 소형 무인기의 횡운동 SCAS 설계에 적용하여 그 효용성을 제시하였다. 최적화를 통해 설계된 롤 자세각 및 방위각 제어기는 시간응답특성만을 고려하여 설계한 기본제어기와 성능을 비교하고 분석하여, 최적화 기법을 적용한 제어기의 성능이 우수하고 다양한 비행성 요구조건을 충족시킬 수 있음을 확인하였다.

• 한국산업융합학회 논문집
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• 제25권1호
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• pp.121-129
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• 2022

With the recent increase in international trade volume the trade volume through ships is also continuously increasing. The treatment of ballast water goes through the following five steps, samples are taken and analyzed at each step, and samples are obtained using a suction pump. These suction pumps have low efficiency and thus need to be improved. In this study, it is to optimize the form of the impeller which affects directly improvements of performance to determine the capacity of suction pump and to fulfill the purpose of this research. To do it, we have carried out parametric design as an input variable, geometric form for the impeller. By conducting the flow analysis for the optimum form, it has confirmed the value of improved results and achieved the purpose to study in this paper. It has selected the necessary parameter for optimizing the form of the pump impeller and analyzed the property using experiment design. And it can reduce the factor of parameter for local optimization from findings to analyze the property of form parameter. To perform MOGA(Multi-Objective Genetic Algorithm) it has generated response surface using parameters for local optimization and conducts the optimization using multi-objective genetic algorithm. with created experiment cases, it has performed the computational fluid dynamics with model applying the optimized impeller form and checked that the capacity of the pump was improved. It could verify the validity concerning the improvement of pump efficiency, via optimization of pump impeller form which is suggested in this study.

• 대한기계학회논문집A
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• 제32권10호
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• pp.882-889
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• 2008

A humanoid is a robot with its overall appearance based on that of the human body. When the humanoid moves or walks, dynamic forces act on the body structure. Although the humanoid keeps the balance by using a precise control, the dynamic forces generate unexpected deformation or vibration and cause difficulties on the control. Generally, the structure of the humanoid is designed by the designer's experience and intuition. Then the structure can be excessively heavy or fragile. A humanoid design scenario for a systematic design is proposed to reduce the weight of the structure while sufficient strength is kept. Lower parts of the humanoid are selected to apply the proposed design scenario. Multi-body dynamics is employed to calculate the external dynamic forces on the parts and structural optimization is carried out to design the lower parts. Because structural optimization using dynamic forces directly is fairly difficult, linear dynamic response structural optimization using equivalent static loads is utilized. Topology and shape optimizations are adopted for two steps of initial and detailed designs, respectively. Various commercial software systems are used for analysis and optimization. Improved designs are obtained and the design results are discussed.