• Journal of the Korean Society for Aviation and Aeronautics
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• v.16 no.4
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• pp.1-11
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• 2008

This research presents a study for the knowledge-based configuration design development of a RC (remote control) helicopter. Parametric design and knowledge based design concepts are introduced for rapid design changes and analyses using commercial CAD software, CATIA(R) Knowledgeware module. It is crucial for RC helicopter design because it enables rapid conceptual design through instant configuration changes. Positions and dimensions of RC helicopter parts were used as design parameters. As an example, positions of CG(center of gravity) points were traced and plotted as the configuration changes. Further research should be performed in areas of user interfaces and web-based multi-user environments instead of using Excel data sheets.

• Journal of Korean Society of Steel Construction
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• v.16 no.6 s.73
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• pp.819-832
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• 2004

This study describes an efficient and facile method for configuration optimum design of structures. One of the ways to achieve numerical shape representation and the selection of design variables is using the design element concept. Using this technique, the number of design variables could be drastically reduced. Isoparametric mapping was utilized to automatically generate the finite element mesh during the optimization process, and this made it possible to easily calculate the derivatives of the coordinates of generated finite element nodes w.r.t. the design variables. For the structural analysis, finite element analysis was adopted in the optimization procedure, and two different techniques(the deterministic method, a modified method of feasible direction; and the stochastic method, a genetic algorithms) were applied to obtain the minimum volumes and section areas for an efficient configuration optimization procedure. Futhermore, spline interpolation was introduced to present a realistic optimum configuration that meet the manufacturing requirements. According to the results of several numerical examples(steel structures), the two techniques suggested in this study simplified the process of configuration optimum design of structures, and yielded improved objective function values with a robust convergence rate. This study's applicability and capability have therefore been demonstrated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.38-42
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• 2007

In this study, cruise missile configuration is optimal designed by using multidisciplinary analysis. Aerodynamic, weight, performance and mission analysis modules are developed by FORTRAN and integrated with framework. Darwin algorithm, a global optimization tool, is used for optimization. In the result of optimal design, gross weight of designed configuration is reduced about 17% than baseline configuration while satisfying design constraint conditions.

• Journal of the Korean Society for Precision Engineering
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• v.17 no.10
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• pp.192-199
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• 2000

The design of multi-stage gear drives is a time-consuming process because it includes more complicated problems, which are not considered in the design of single-stage gear drives. The designer has no determine the number of reduction stages and the gear ratios of each reduction stage. In addition, the design problems include not only dimensional design but also configuration design of gear drive elements. There is no definite rule or principle for these types of design problems. Thus the design practices largely depend on the sense and the experiences of the designer, and consequently result in undesirable design solution. A new and generalized design algorithm has been proposed to support the designer at the preliminary phase of the design of multi-stage gear drives. The proposed design algorithm automates the design process by integrating the dimensional design and the configuration design process. The algorithm consists of four steps. In the first step, the user determines the number of reduction stages. In the second step, gear ratios of every stage are chosen using the random search method. The values of the basic design parameters of a gear are chose in the third step by using the generate and test method. Then the values of the dimensions, such as pitch diameter, outer diameter and face width, are calculated for the configuration design in the next step. The strength and durability of each gear is guaranteed by the bending strength and the pitting resistance rating practices by using AGMA rating formulas. In the final step, the configuration design is carried out using simulated annealing algorithm. The positions of gears and shafts are determined to minimize the geometrical volume (size) of a gearbox while avoiding interferences between them. These steps are carried out iteratively until a desirable solution is acquired. The proposed design algorithm is applied to the preliminary design of four-stage gear drives in order to validate the availability. The design solution has considerably good results in both aspects of the dimensional and the configuration design.

• Proceedings of the KSR Conference
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• 2005.11a
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• pp.362-369
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• 2005

In this paper, a research for the knowledge based configuration design software development of a train vehicle has been presented. Parametric design and knowledge based design concepts have been introduced for rapid design changes and analyses using a commercial CAD software, $CATIA^{/circledR}$ Knowledgeware module. Positions and dimensions of door, small window, large window, and number of seats were used as design parameters. It is crucial for train vehicle design because it enables rapid conceptual design by instant configuration changes. The results of this research can be used as one sub module of the multidisciplinary train vehicle design software and provide a basic data for rolling stock behavior and driver cab ergonomics of a train vehicle.

• Korean Journal of Computational Design and Engineering
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• v.5 no.3
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• pp.224-231
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• 2000

In order to satisfy customers'various needs in the market, manufacturing companies tend to add similar variants to an existing product model. This variety causes immense growth of product configuration and makes data management uncontrollable. In order to resolve this problem, we propose a method to efficiently represent the variants in a single schema of product structure and configuration and manage the product configuration. First of all, the product structure which adopts the concept of features and options is suggested. Second, the method to represent option specifications which restricts option configurations is proposed. Finally, the prototype module, which inspects if a product configuration violates the option specifications, is introduced.

• Proceedings of the KSME Conference
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• 2000.04a
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• pp.890-893
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• 2000

It is known that about 15 to 40 percent of total design time is spent on retrieving information such as standard parts handbook data, engineering equations, previous designs. This paper describes a knowledge management system for machine tool design. Product structuring, change management, and complex design knowledge management are possible through the developed system. The system can speed up the design process by making necessary data instantly available as it is needed and keeping track of all the relevant design information and knowledge including individual decisions, design intentions, documents, and drawings.

• Current Industrial and Technological Trends in Aerospace
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• v.8 no.1
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• pp.45-54
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• 2010

The goal of the paper is to discuss the recent trend of the configuration of high resolution LEO(Low Earth Orbit) EO(Earth Observation) satellites. The satellite configuration is decided by considering several factors such as mission, payloads, launch vehicle, propulsion and attitude control module. The advent of commercial companies selling satellite's images in 2000's requires additional changes of the satellite system to be capable of obtaining many high resolution images quickly. In order to meet customer's needs, the overall configuration of satellites is designed to be compact and stable without the loss of structural integrity and reliability. Among design changes, the configuration change of satellites is treated intensively in the paper.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.20 no.12
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• pp.3804-3821
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• 1996

The configuration optimization is a structural optimization method which includes the coordinates of a structure as well as the sectional properties in the design variable set. Effective reduction of the weight of discrete structures can be obrained by changing the geometry while satisfying stress, Ei;er bickling, displacement, and frequency constraints, etc. However, the nonlinearity due to the configuration variables may cause the difficulties of the convergence and expensive computational cost. An efficient approximation method for the configuration optimization has been developed to overcome the difficulties. The method approximates the constraint functions based onthe second-order Taylor series expansion with reciprocal design variables. The Hessian matrix is approzimated from the information on previous design points. The developed algotithms are coded and the examples are solved.

• International Journal of Aeronautical and Space Sciences
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• v.15 no.2
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• pp.138-145
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• 2014

The initial configuration for 95-seat passenger regional turboprop aircraft, the so called KC950, was designed to meet the market requirements. This paper prescribes the initial design based upon aircraft design guidelines and compared the competitive aircraft configurations after considering the related FAR 25 regulations. More specifically, results of design describe how to select the fuselage cross-sectional area, how to layout the cabin, and how to determine the overall shape and physical dimension of the fuselage. Sizing of wing and empennage areas is estimated using empirical equations and tail volume coefficients in this design. Some design guidelines to determine wing sweep angle, taper ratio, incidence angle and location are also introduced.