• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.3
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• pp.44-52
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• 2004

In this study, a component map generation method using experimental data and the genetic algorithms are newly proposed. In order to generate the performance map for components of this engine, after obtaining engine performance data through many experimental tests, and then the third order equations which have relationships the mass flow function the pressure ratio and the isentropic efficiency as to the engine rotational speed were derived by using the genetic algorithms. A steady-state performance analysis was performed with the generated maps of the compressor by the commercial gas turbine performance analysis program GASTURB. In comparison, it was found that the component maps can be generated from the experimental test data by using the genetic algorithms, and it was confirmed that the analysis results using the generated maps were very similar to those using the scaled maps from the GASTURB.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.195-200
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• 2004

In this study, a component map generation method using experimental data and the genetic algorithms are newly proposed. In order to generate the performance map for components of this engine, after obtaining engine performance data through many experimental tests, and then the third order equations which have relationships the mass flow function the pressure ratio and the isentropic efficiency as to the engine rotational speed were derived by using the genetic algorithms. A steady-state performance analysis was peformed with the generated maps of the compressor by the commercial gas turbine performance analysis program GASTURB(1). In comparison, it was found that the component maps can be generated from the experimental test data by using the genetic algorithms, and it was confirmed that the analysis results using the generated maps were very similar to those using the scaled maps from the GASTURB.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.10-10
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• 1999

선형 및 비선형 GPA 기법을 이용한 가스터빈 엔진의 성능예측 및 진단을 연구하고 전형적 산업용 가스터빈 엔진인 TB5000에 적용하여 최적의 계측변수를 정의하였다. 선형 GPA는 가스가 지나가는 구성품의 계측가능한 온도, 압력, 연료유량, 로터 회전수 등과 같은 종속변수와 효율, 유량과 같은 측정불가능한 독립변수의 관계 방정식을 열역학 법칙, 연속방정식, 질량 및 에너지 보존법칙, 구성품 성능곡선 등으로부터 유도하는 것이며 비선형 GPA는 독립변수와 종속변수의 비선형 관계를 충분히 고려하기 위해 선형 GPA를 반복적으로 적용하는 방법이다. 본 연구에서 반복기법은 Newton-Raphson 반복기법을 사용하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2001.11a
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• pp.39-40
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• 2001

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.35-38
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• 2007

Aiming at time-dependent performance prediction of Liquid Rocket Engine(LRE) system, Modular Program for Conceptual Design of LRE is reviewed, and a modeling and dynamic analysis of rocket engine system with reference to Rocket Engine Dynamic Simulator(REDS) is outlined. Component modeling is based on classical thermodynamic and inviscid theories, and were formulated mathematically in terms of essential parameters. Essential design parameters are addressed. The rocket engine is modeled as a system of pipes with various hydraulic elements, and then the operate characteristic of that elements are simulated by solving conservation equation sequentially.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.232-241
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• 2004

KARI(Korea Aerospace Research Institute) is achieving the KSLV program according to National Space Technology Development Program. In this paper, the authors are intend to introduce the Integrated Power Plant(IPP) test facility which will be constructed for the variety of tests on KSLV program. IPP test facility refers to comprehensive testing equipment for liquid rocket launch vehicle. Using this facility, KARI can verify the adaptedness of parts and subsystems for launch vehicle and finally can qualify the system characteristics of launch vehicle doing kinds of test including hot firing test. IPP test facility will make it possible to simulate the vehicle launching circumstances and to predict the performance of launch vehicle during its flight test.

• Proceedings of the KAIS Fall Conference
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• 2011.12b
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• pp.499-502
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• 2011

중형급 회전익 항공기는 약 5,000여종의 주요기능 부품이 사용된다. 이들 주요 기능부품은 항공기에 장착되기 위해 최적화설계로 목표중량을 달성하고, 요구성능을 상회하여야 한다. 따라서 항공기 기능부품은 개발비를 제외하고도, 동종의 자동차 부품에 비해 약 100배 이상의 양산 단가 구조과 막대한 개발비가 소요된다. 이와 같은 구성품 개발에 있어 개발비를 절감하는 기술관리 수단중 하나가 형상관리이며, 형상관리 체계의 수립은 사업의 성패에 중요요인으로 작용하고, 군사규격에 의거 항공분야 개발사업의 형상관리체계 수립이 요구된다. 본 연구에서는 다양한 민군겸용 구성품 국산화 개발에 적합한 형상관리 체계를 제안하고, 제안된 형상관리 체제를 구축 운용하여, 성공적인 민군겸용 구성품 형상관리가 수행되었음을 확인하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.10
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• pp.717-727
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• 2022

An algorithm is realized for estimating the component fault and health diagnosis such as a deterioration. Based on the turbofan engine health diagnosis model, from the health parameters which are estimated by a real time tracking filter, the outliers are eliminated efficiently by an effective median filter to minimize an false alarm. The difference between the fault and deterioration trends is identified by the detection measure for abrupt change, thereby the clear diagnosis classifying the fault and the health condition is possible. The effectiveness of the algorithm for fault and health diagnosis is verified from the simulated results of engine component faults and deterioration.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.5
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• pp.18-25
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• 2008

A performance analysis program has been developed for the gas generator cycle liquid rocket engine. This program predicts the system performance with the performances of subsystems which are evaluated by the models based on another analyses or experiments. The analysis method has been validated by comparing the engine performance against the published conceptual design. The performance models of the subsystems have been verified to give reasonable results by comparing with the MC-1 engine design and the system analysis of 10 ton thrust engine. The system performance of the 30 ton thrust rocket engine using LOx/Jet-A1 has been presented as an application example.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.4
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• pp.328-336
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• 2008

The shock tunnel as a hypersonic ground test facility was designed, constructed and its performance test was conducted to reproduce the high speed flow which the hypersonic propulsion system is encountered. The design points were understood and the conceptual design was completed using the quasi one dimensional operation analysis code. After that, the specific performance and compartment design were completed using CFD simulation as the part analysis. The facility was then constructed according to those design results and the performance test was conducted for various operation conditions. In this paper, we suggested the compartment design method using CFD analysis, construction process and various performance test results in detail.