Jae-Woo Lee

Development of Web services-based Multidisciplinary Design Optimization framework

The defining characteristic of a Multidisciplinary Design Optimization (MDO) strategy or method, compared to the more traditional, sequential approach to conducting design work, is that the contributions of all mutually influential disciplines are concurrently taken into account. Therefore, a framework that allows the implementation of MDO methods must be an environment for design synthesis. It is also desired that the user of an MDO framework be capable of efficiently integrating and managing the resources distributed over heterogeneous platforms. This paper proposes a Web services-based MDO framework that enables the synthesis of available disciplinary and cross-disciplinary resources for MDO via the Globus Toolkit. Examples of organic and autonomous execution of MDO methods are presented to highlight the effectiveness of modern automation techniques, such as workflow management system and agent technology. The salient features of a planned collaborative design environment, which will be built through Web-based user interfaces, are discussed last.

Comprehensive aircraft configuration design tool for Integrated Product and Process Development

This paper describes an efficient aircraft geometry design tool which is necessary for design and analysis applications through Integrated Product and Process Development (IPPD). The design process decomposes aircraft geometry into several components to represent it accurately and realistically with a reduced number of shape control parameters. For this purpose, several configuration representation algorithms are thoroughly investigated and discussed. The proposed configuration generation algorithm employs the super ellipse equation with simple analytic distribution functions, Class function/Shape function Transformation (CST) and can represent and manipulate complex shapes accurately with a small number of control parameters. A model of aircraft geometry, represented in this approach, can be applied to conceptual and preliminary stages of aircraft design and development with realistic and accurate configuration data. A Parameter-based Comprehensive Aircraft Design (PCAD) tool which implements a geometry generation process for aircraft design and optimization using customization of commercial computer-aided design software (CATIA V5) and the Product Data Management (Enovia Smarteam). The proposed configuration design tool could be especially efficient when automation, flexibility and rapid changes of geometry are required in a short time and with low computational resources.

New integrated model to estimate the manufacturing cost and production system performance at the conceptual design stage of helicopter blade assembly

This paper describes a new integrated model development to estimate the manufacturing cost and production system performance at the conceptual design stage. A fully automated conceptual framework for design for manufacturing (DFM) has been developed. An integrated product process design concept using activity based costing is applied in this paper. The new integrated model consists of four sub-modules: the geometric parameters generation module, processing time estimation module, activity based costing (ABC) module and production system performance module. All of the input-output data flows of developed modules are fully integrated for automated manufacturing cost analysis and production system performance. A developed integrated model is very useful for designers or integrated product development team to make a decision for evaluating the design alternatives and trade-offs between design and manufacturing phases at the conceptual design stage. A case study for a composite helicopter rotor blade is included.

Integrated approach for rotor blade manufacturing cost estimate

Purpose – The purpose of this research is to develop an integrated model for composite rotor blade manufacturing cost estimates at the conceptual design stage. The integrated model seeks to provide a rapid and dynamic feedback based on evaluating the manufacturing cost estimate for a new product design at the conceptual design stage. This paper describes the automated estimating process for design to manufacturing cost of composite rotor blade.Design/methodology/approach – An integrated approach is implemented for evaluating the manufacturing cost estimates. The paper develops each module of the computer‐aided parametric model generation, time estimation models for composite manufacturing processes and decision support system. Finally, process flow data integration is done for all the modules. An example for a complicated geometric rotor blade is shown in this research paper. The results are compared in different design parameters and discussed.Findings – The data integration for this approach was built b...

A distributed Web-based framework for helicopter rotor blade design

In Multidisciplinary Design Optimization (MDO) a wide variety of tools and techniques have been developed to assist in the analysis and optimization of highly complex systems. This paper focuses on a Web-based MDO framework that could be applied to MDO problems by combining rotorcraft blade analysis data and processing cost manufacturing data. The framework is based on a Web environment platform and is implemented in Java Programming Language. The system includes: an analysis code module, a graphical user interface (GUI), a CAD configuration module and a manufacturing process cost module. All modules are connected to the database and a centralized database management system (DBMS) that controls all input and output data. The analysis code module utilizes: initial sizing, airfoil configuration, airfoil coordinates, 2Kfoil, performance, and trim programs. The GUI module is developed from JSP and HTML code. By using a Java Database Connection component, data connection access between the GUI and database is possible. This framework aims to simultaneously support the integration of: legacy code, workflow management, parallel computing and fault tolerance. The application focuses on ease of use and access through Internet browser tools within a local intranet zone. Based on this framework, we can easily predict flight characteristics by using a flight simulation program, and pre-test real scenarios.

Uncertainty-based MDO for aircraft conceptual design

Purpose – The purpose of this paper is to study the consideration of uncertainty from analysis modules for aircraft conceptual design by implementing uncertainty-based design optimization methods. Reliability-Based Design Optimization (RBDO), Possibility-Based Design Optimization (PBDO) and Robust Design Optimization (RDO) methods were developed to handle uncertainties of design optimization. The RBDO method is found suitable for uncertain parameters when sufficient information is available. On the other hand, the PBDO method is proposed when uncertain parameters have insufficient information. The RDO method can apply to both cases. The RBDO, PBDO and RDO methods were considered with the Multidisciplinary Design Optimization (MDO) method to generate conservative design results when low fidelity analysis tools are used. Design/methodology/approach – Methods combining MDO with RBDO, PBDO and RDO were developed and have been applied to a numerical analysis and an aircraft conceptual design. This research eva...

Preliminary Design of the Hybrid Air-launching Rocket for Nanosat

Air-Launching is an effective method that can launch the Nanosat for low launching cost. In this study, the preliminary design of the air-launching micro rocket was performed. Mission and trajectory optimization was performed and the propulsion system was designed based on the mission design. A supersonic air launching rocket with total weight of 830.95 kg, the payload weight of 3.56 kg and the propulsion system length of 5.89 m has been designed.

Development of integrated rotorcraft design and virtual manufacturing framework

Purpose – The purpose of this paper is to develop an integrated rotorcraft design and virtual manufacturing framework. The framework consists of two major sub‐frameworks which are e‐design and virtual manufacturing frameworks. This paper aims to describe the process of generating a specific framework for helicopter design and manufacturing in general, and a method for main rotor blade design.Design/methodology/approach – The e‐design process integrates a pre‐conceptual, conceptual and preliminary design phases and includes many high accuracy physics‐based analysis tools and in‐house codes. The development of analysis programs and integration of flow data are discussed under the e‐design process. The virtual manufacturing process discusses physical three‐dimensional (3D) prototypes using rapid prototyping, virtual process simulation model development using Delmia Quest, virtual machine tool simulation and process‐based cost model. Vehicle geometry is modelled parametrically in computer‐aided 3D interactive...

Performance Prediction of Large Scale Vacuum Furnace Using Thermal Analysis

A method using thermal analysis has been recommeded to substitute the original method what was based on trial and error for manufacturing a high performance, low cost product. At first, a large scale vacuum furnace was modeled according to a real product, and it was simulated using the material properties in a previous study under the condition of having argon ambient gas. Finally, the performance of the large scale vacuum furnace was discussed using the obtained results of analysis. The method in this study will be used to produce an energy efficient, low cost product using optimization technique under the condition of fully satisfying users design requirements.

Integrated analysis of an air-launching rocket maneuvering at high angle of attack

The rocket design requires all aspects of aerodynamics, structure analysis, controllability and other technologies. More sophisticated design and analyses methods are required to enhance design results. Computational Fluid Dynamics (CFD) and the Finite Element Method (FEM) are used for the fluid-structure interaction analysis of air-launching rocket. In this study, the aerodynamics-structure coupled analysis procedure for the air-launching rocket is established and is applied to accurately predict the surface pressure and rocket deformation during the pull-up maneuver of the air-launching rocket. Euler equations and FEM are employed for the analyses. For the case considered in this study, convergent solutions are reached within 5 iterations. The rocket thickness case satisfies the structural constraint. The results of analysis presents drag coefficient decrease at convergence process.