• Proceedings of the KSME Conference
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• 2007.05a
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• pp.1595-1600
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• 2007

It is necessary a simple helicopter design and performance analysis program for a stage of helicopter conceptual design. To meet that needs, we have developed a program which is simply used to estimate helicopter configuration and performance. The program developed by this study is composed of Requirement, Mission profile Analysis, Size, Aerodynamic, Trim, Propulsion, Weight, and Performance modules, and each modules carry out operations for a given flight condition. In this study, we validate this analysis program in 9,500 1bs and 22,000 1bs helicopters and estimate design configuration and performance of 16,000 1b helicopter. And We can use this program to optimization process for Helicopter MDO framework.

• Journal of Astronomy and Space Sciences
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• v.23 no.4
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• pp.445-452
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• 2006

In this paper, the conceptual design of satellite digital base put which is based upon data interface between satellite on-board computer and remote devices like satellite sub-components is presented. This conceptual design shows the unification of the interface between on-board computer and satellite remote devices and the hierarchical results of the interface level. A comparison of different system and merits and demerits of digital base part coming from this conceptual design is performed.

• Proceedings of the KSME Conference
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• 2007.05a
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• pp.296-299
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• 2007

KAERI is in the process of carrying out the Nuclear Hydrogen Development and Demonstration (NHDD) Program. The indirect cycle gas cooled reactors that produce heat at temperatures in the order of $950^{\circ}C$ are being considered in the NHDD program. For the indirect gas cooled reactors, the intermediate hear exchanger (IHX) and hot gas duct (HGD) are the main components. For the NHDD program we are in the process of establishing a conceptual design of the IHX and HGD. The pre-conceptual design activities in this study dealt with a preliminary design of the IHX and the HGD including strength and thermal expansion evaluation of the main components.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.18 no.3
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• pp.1-8
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• 2010

A design study has been performed to obtain configuration and weight of a compound gyroplane. A study of research trends and characteristics was performed to develop the compound gyroplane sizing program. Based on these results, the sizing program has been developed and its suitability has been validated using existing compound gyroplane data. The subject air vehicles was a Challis Heliplane UAV, Carter Coptet, FB-1 Gyrodyne, and Jet Gyrodyne. As results, the program was suitable to size a compound gyroplane at conceptual design phase, because the greatest error rate was less than 10% and the conceptual design allowance error rate is less than 15%.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.10
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• pp.134-141
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• 2004

This paper addresses development of the conceptual design program of satellite communication system. A database for more than 200 small satellites of LEO which are between 10kg and 200kg was constructed to conduct a sequential process of conceptual design. General parameters based on the database were derived to be able to use for initial design of satellite communication system. The general conceptual design process developed and programed in this work is applicable to micro-class small satellites without regard to mission types. This conceptual design algorithm is consisted of five sequential steps, in which various parameters are defined every phase. These parameters are utilized for conceptual design through database analysis. The validity of an entire design algorithm has been demonstrated via program simulation.

• Journal of the Korea Institute of Military Science and Technology
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• v.17 no.2
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• pp.189-196
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• 2014

Automated design program using commercial process integration and optimization program was developed for conceptual design of fighter-class aircraft. Wind tunnel test data and performance analysis results were compared for the verification of analysis tool of this program, and the usefulness of the tool was found. After integration with radar cross section analysis tool, the correlation with configuration design variables of wing, tail and performance parameters was identified by design of experiment, and the optimized configuration for weight and RCS was derived from optimization of empty weight and average frontal RCS value. After parameter definition of fuselage, the program can be implemented for full aircraft configuration.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.21 no.2
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• pp.40-46
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• 2013

In this paper, it has implemented the design for the K-Line Operations Safety Audit(K-LOSA) designed to provide a proactive snapshot of system safety and flight crew performance before an incident and accident. It introduces the a LOSA and ten operating characteristics that have come to define LOSA methodology. According to the LOSA methodology, we explain the conceptual and detail design and implement the prototype for the data collected with LOSA collection tool.

• International Journal of Aeronautical and Space Sciences
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• v.18 no.4
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• pp.641-650
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• 2017

In order to include the design capability for a compound rotorcraft in a helicopter conceptual design and optimization framework, relevant further improvement was planned and conducted. Previously, a certain conceptual design optimization framework was developed by the present authors to design a modern rotorcraft with single main and tail rotor. The previously developed framework was further improved to expand its capability for a compound rotorcraft. Specifically, its power estimation algorithm was upgraded by using a comprehensive rotorcraft analysis program, CAMRAD II. The presently improved conceptual design and optimization framework was validated using data of the XH-59A aircraft.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.9
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• pp.805-815
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• 2007

In order to build a conceptual design program for a liquid rocket engine system, performance based sub-programs for each core component of the engine system were made. Parts included were the combustion chamber, supersonic nozzle, centrifugal pump, and impulsive turbine. Simple mathematical models based on classical thermodynamic and inviscid theories were adopted with proper tuning by empirical data. In Part I, aiming to validate each sub-program, we examined the results of each program qualitatively, and parametrically investigated the sensitivity due to the change in design parameters.

• 한국태양에너지학회:학술대회논문집
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• 2011.11a
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• pp.99-104
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• 2011

This paper describes a design strategy at conceptual design stage using RETScreen software tool for building application of renewable energy resources. Currently, government and public buildings are required to adopt renewable energy systems with a minimum requirement for the amount of renewable energy supply. Meanwhile, there is a certificate program for private office buildings to enhance propagation of renewable energy systems. When considering application of renewable energy systems to a building, it is worthwhile developing a method to determine optimal design sizes of renewable energy systems. In the paper, a design strategy is introduced with a couple of case studies to determine optimal capacities of each renewable energy system in a building and suggest to use the method to evaluate the system for the building certificate program and the mandatory renewable target program. Objective functions considered in the study are initial system cost and reduction of CO2 emissions from the system. In the optimization study, it is assumed that solar thermal collectors are installed to satisfy solar fraction of 60%. Other renewable energy systems such as ground-source heat pump, solar PV and non-renewable systems such as electric chiller and gas-fired boiler are sized using an optimal sizing method with RETScreen suggested the authors previously.