• 품질경영학회지
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• 제34권3호
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• pp.1-18
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• 2006

CMMI(Capability Maturity Model Integration) has been recognized as a critical method to validate the competitiveness of software development organization since its introduction. CMMI imposes additional requirements on the software development organization which has been established and certified to the ISO 9001 quality management system. This paper reviews the similarities and differences between CMMI and ISO 9001. This paper also examines what ate required to deploy the CMMI on the aircraft software development organization which has been certified to ISO 9001. The results of this study will help software development organization to provide the direction for implementing CMMI. Some suggestions are presented to identify and strengthen the weak portion of the software process quality management system.

• 한국기술혁신학회:학술대회논문집
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• 한국기술혁신학회 2000년도 추계 학술대회(The 2000 Autumn Conference of korea Technology Inovation Society)(한국기술혁신학회)
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• pp.227-245
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• 2000

Korean firms have attempted to catch up in the aircraft industry during last quarter century. Korean firms have built up their capabilities by moving from parts manufacturing through subassembly to system integration. The number of projects carried out and the intensity of technological effort undertaken by firms strongly influences market position and firm performance. However, successful catching up is not simply dependent on capability building within the firm. The national environment (Porter, 1990) in which firms are located plays a pivotal role. The Korean government has been effective in creating a favorable environ-ment in many areas, but has not been able to replicate this success in the aircraft industry. Opportunities for learning in the aircraft industry have been hampered by the small size of the Korean civilian aircraft market and the sophisticated requirements of military systems. A policy of domestic rivalry in airframe manufacture has created too many firms for such a small market. The ability of Korean firms to catch up in the aircraft industry depends on both the internal capabilities of firms as well as appropriate government policies and the involve- ment of government research institutions and universities over an extended period of time. There have been many studies about the catching up of developing countries in mass production (such as automobile, consumer electronics, and recently DRAM), but few in complex systems, such as aircraft.

• 제어로봇시스템학회논문지
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• 제14권10호
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• pp.1081-1087
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• 2008

This paper describes limitations and solutions of the existing processor-monitoring concept for a military supersonics aircraft Flight Control Computer (FLCC) equipped with modern architecture processor to perform the system integration test. Safecritical FLCC integration test, which requires automatic test for thousands of test cases and real-time input/output test condition generation, depends on the processor-monitoring device called Processor Interface (PI). The PI, which relies upon on the FLCC processor's external address and data-bus data, has some limitations due to multi-fetching capability of the modern sophisticated military processors, like C6000's VLIW (Very-Long Instruction Word) architecture and PowerPC's Superscalar architecture. Several techniques for limitations were developed and proper monitoring approach was presented for modem processor-adopted FLCC system integration test.

• 항공우주시스템공학회지
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• 제8권2호
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• pp.27-32
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• 2014

From the flight safety and the performance point of views, a new engine installation impacts an helicopter development or upgrade program significantly. More than a close relationship between an aircraft manufacturer and an engine manufacturer is necessary for the best integration work from the program initiation phase. In this paper, technical cooperation between aircraft and engine companies, and technical supports by the engine manufacturer for the T700/701K engine during the Surion development program are summarized. The applications of official technical program documents, US Mil-spec, France airworthiness regulations as the standard of the engine installation work, and engineering activities at each phase such as contract, design and manufacturing, flight clearance, ground and flight tests are described. This paper would be a cornerstone for the future domestic helicopter development program.

• 한국항공우주학회지
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• 제42권11호
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• pp.968-973
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• 2014

유무인 겸용 비행체인 OPV는 무인기 개발방법 중의 하나로 기존 유인기 운용을 통해 검증된 유인 비행체와 엔진 및 각 계통을 유지하며, 무인기 운용을 위해 필요한 부가 시스템을 장착하고, 필요에 따라 기존시스템을 수정하여 개발비용과 시간을 줄일 수 있는 장점을 가지고 있다. 또한 임무 및 비행조건에 따라 유인기와 무인기로 겸용하여 운용할 수 있는 장점을 가지고 있으며, 퇴역하는 유인기를 재활용하는 측면에서도 국가의 중요재원을 효율적으로 활용할 수 있는 시스템이다. 본 논문에서는 국내 최초로 개발한 고정익 OPV 비행체의 자동비행조종시스템을 중심으로 초기 중요 개발개념과 기술적 고려사항 들을 정리하였다.

• 항공우주시스템공학회지
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• 제16권1호
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• pp.86-96
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• 2022

제트 전투기의 항공전자 시스템 아키텍처 개발 경향은 서브 시스템 구성요소 기능의 디지털화, RF 센서 공유의 증가, 광섬유 채널 네트워크, 그리고 모듈화된 통합 구조이다. 5세대 제트 전투기(F-22, F-35)의 항공전자 시스템 아키텍처는 컴퓨팅 기능 통합과 RF 통합 센서 시스템 기반인 통합 모듈형 항공전자 시스템으로 발전했다. 제트 전투기의 통합 항공전자 시스템은 전투기의 전투력 향상, 내결함성 및 제어 용이성을 제공해야한다. 이를 위해 본 논문에서는 5세대 제트 전투기의 항공전자 시스템 아키텍처 분석을 통해 차세대 제트 전투기의 항공전자 시스템 아키텍처의 방향과 요구사항을 제시한다. 차세대 통합 모듈화 항공전자 시스템 아키텍처 요구사항들의 핵심 과제는 주요 구성 장치와 센서들을 항공기에 통합하는 플랫폼을 구축하는 것이라 할 수 있다. 즉, 차세대 전투기의 아키텍처는 시스템의 표준화와 개방형 인터페이스를 통한 각 서브 시스템의 센서통합, 기능요소 통합, 네트워크 통합이며 조종사와 전투기의 일체화로 고자율적 대응 및 제어능력 향상에 있다.

• 한국군사과학기술학회지
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• 제14권3호
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• pp.474-481
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• 2011

The Electronic Warfare Computer for the Aircraft Survivability Equipment will improve the ability for countermeasures by analysis about threat information. This paper suggests method that threat data integration of multiple sensors(Radar Warning Receiver, Laser Warning Receiver, Missile Warning Receiver). The algorithm of threat data integration is based on detected threat sequence and azimuth information. The threat sequence information is analyzed in advance and the azimuth data is received from sensors. The suggested method is evaluated through simulation under the environment like real helicopter.

• 한국항공우주학회지
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• 제39권7호
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• pp.666-673
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• 2011

최신항공기 개발에서 증가추세에 있는 항공전자 장비들의 효율적인 통합시험 수행을 위 해 통합시험환경구축이 중요한 역할을 하고 있다. 특히 개발기간 최소화 및 신뢰성과 신속한 통합시험수행을 위해 통합시험장비 개발이 필수적이다. 본 논문에서는 수리온(KUH) 임무탑재장비(MEP)의 각 장비별 특성을 분석 후 최적의 통합시험 수행을 위한 장비별 모델개발을 다루었다. 모델은 동작특성에 따라 동적(Dynamic), 행동(Behavior), 연동(ICD) 모델로 구분하였으며 장비의 고장탐구 및 미장착된 장비의 동작특성 모사가 모델링의 주목적이다. 모델은 소프트웨어 단위시험 및 체계 통합시험 두 단계로 나누어 객관적 신뢰성을 검증하였다. 수리온 MEP 통합시험장비(SIL)를 이용하여 개발된 모델을 통합시험에 적용한 결과 설계 목적에 부합됨을 확인하였다.

• 항공우주시스템공학회지
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• 제10권1호
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• pp.1-7
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• 2016

During flight of the aircraft, the vortex merging phenomenon appears under the certain condition between co-rotating vortices which were generated at the wing tip and lifting-surface. And then these merged vortices at both sides show counter-rotating pattern to affect on the downstream of the aircraft. In this paper, the numerical simulations are conducted assuming this phenomenon in two-dimensional co-rotating or counter-rotating vortices pairs. Two-dimensional incompressible Navier-Stokes equations were converted into Vorticity-Streamfunction form and the Galerkin spectral method was adopted. The third order Runge-Kutta method was used for time integration. The effects on the vortex merger and degree of vortex merger were investigated according to time, Reynolds number, and changes in the distance between two vortices.

• 항공우주시스템공학회지
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• 제2권3호
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• pp.29-32
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• 2008

The overview of KUH design and development process is presented according to Buede's systems and development "vee" model. The system decomposition and integration activities exemplify KUH specification tree, design maturity and analysis according to design stage(conceptual, preliminary, and detail design), scheduled work breakdown structure, qualification test, ground test, and flight test. This process can be applied to the development of a new aircraft.