• 산업경영시스템학회지
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• 제44권4호
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• pp.106-112
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• 2021

In the early 1960s, US Air Force lost missile launch bases during ICBM development by a defect in the missile design and operation plan. U.S. DoD realized the limitation of the existing accident prevention method. Therefore, the weapon development required system safety activity, and procurement projects of U.S. DoD applied MIL-STD-882(System Safety). Development projects of U.S. DoD more emphasized the importance of system safety after the space shuttle Challenger exploded in 1986. Currently, Airworthiness certification for military aircraft uses system safety to minimize accidents. The domestic defense aviation R&D projects also use the system safety for the airworthiness certification. However, non-aviation weapon R&D projects rarely applied system safety. This paper presents a system safety application method for domestic weapon R&D projects by studying the U.S. military standards/organizations and domestic defense aviation projects.

• 한국군사과학기술학회지
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• 제22권2호
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• pp.224-232
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• 2019

This paper presents guidelines for the verification test on electromagnetic environmental effects of a commercial derivative military aircraft. To prove the safety-of-flight of a renovated aircraft and appropriate working of electronic system/device, E3 test and analysis at the system level should be performed prior to its operations on real warfare. For the aircraft modified with Falcon 2000S, we concentrate on intra-system EMC, EMRADHAZ (Electromagnetic Radiation Hazards), electrical bonding, P-Static as test and lightning as analysis from a airworthiness certification point of view based on MIL-STD-464, MIL-HDBK-516. As a result, it is verified that the modified aircraft has enough electromagnetic compatibility capabilities under EME(Electromagnetic Environment). In the process, test and analysis methods considering shielding effectiveness(SE) are applied.

• 한국군사과학기술학회지
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• 제16권6호
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• pp.771-778
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• 2013

Transmission is a core component of helicopter to transmit power from engine to rotor and must have a endurance to be able to show satisfactorily its performance required during its life time. When developing a new helicopter, both military and civil airworthiness authorities require a tie-down test to verify its endurance. Procedure for transmission endurance test is described in FAR part 29 or US military specification but its details are more or less ambiguous. In this paper, we have proposed a proper procedure for transmission endurance test by giving KUH transmission endurance test example including determination of applicable torque, load and test profile.

• 한국항공운항학회지
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• 제28권1호
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• pp.115-121
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• 2020

Recently avionics equipment and its integration are most important part for implementing high performance aircraft system. This trends are emphasized in the military or special purpose aircraft development program. Flight Test Bed Aircraft (hereafter FTB A/C) - by modified commercial aircraft - was key solution to verify function and performance of avionics system for complex aircraft development program for a while, but there are no experience to use it in domestic airspace of ROK. This paper would like to address what act and regulation is necessary to perform flight operation of FTB A/C with keeping a airworthiness and airspace control policy. and then willing to propose what do we do for improving aviation industry.

• 품질경영학회지
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• 제41권3호
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• pp.433-441
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• 2013

Purpose: This study investigates software qualification procedures based on the FA-50 flight control software to satisfy high reliability and flight safety. Methods: We studied software qualification categories, standard/specification and developed country case. We proposed procedure to satisfy not only flight safety but also international standard. Results: The proposed software qualification procedure satisfied flight safety and airworthiness based on the testing result of the FA-50 flight control software. Conclusion: This paper showed an appropriate qualification procedures of the flight control software in domestic circumstance through the FA-50 flight control software qualification.

• 항공우주시스템공학회지
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• 제17권6호
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• pp.108-117
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• 2023

지금까지 해외 수출용 KT-1 군용 고정익 항공기에 통합된 임무 소프트웨어는 해외업체와 국제 공동개발을 통하여 개발이 되었으며, 감항인증을 위해 DO-178B를 기반으로 하는 해외업체의 개발 환경과 절차를 준수함으로써 소프트웨어의 신뢰성을 인정받을 수 있었다. 하지만, 최근에는 해외 수출 시 DO-178C 인증을 요구하고 있으며, 국내 소요군에 납품 시 방사청 무기체계 소프트웨어 개발 및 관리 매뉴얼 준수를 위해 신뢰성 시험을 필수적으로 요구하고 있다. 본 논문은 기 개발된 KT-1 수출형 항공기 체계통합 사업의 국제 공동개발에 있어 국내 감항인증을 받기 위한 문제점을 기술하고 DO-178C와 무기체계 소프트웨어 개발 및 관리 매뉴얼을 모두 준수하기 위한 해결방안을 찾아서 최적의 소프트웨어 신뢰성 시험 방안을 제시한다.

• 한국항공우주학회지
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• 제43권6호
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• pp.526-532
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• 2015

국내개발 헬기인 수리온의 악기상 시 운용능력을 입증하고 결빙하 운용 제한 사항을 해제하기 위하여 결빙 감항인증이 요구되고 있다. 군용헬기인 수리온의 결빙 감항인증 절차는 유사 무기체계인 UH-60과 AH-64의 사례와 S/W 기술의 성숙도를 보았을 때, 전산해석${\rightarrow}$모의결빙형상 비행시험${\rightarrow}$인공 결빙 비행시험${\rightarrow}$자연 결빙 비행시험의 4가지 방법에 의한 단계화된 추진이 고려되고 있다. 수리온의 최적 비행시험 소티와 비행시간은 인공 결빙 비행시험 20~30소티 및 20~23시간과 자연 결빙 비행시험 20~30소티 및 20~22시간이 요구되며, 효율적인 결빙 감항인증 비행시험을 위해서는 LWC $0.5{\sim}1.0g/m^3$범위의 대기온도 조건은 인공 결빙 비행시험을 추진하고, LWC $0.5g/m^3$이하의 대기온도 조건에서는 자연 결빙 비행시험이 필요하다.

• 비파괴검사학회지
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• 제35권6호
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• pp.421-428
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• 2015

An important trend in the sustainment of military aircraft is the transition from preventative maintenance to condition based maintenance (CBM). For CBM, it is essential that the actual system condition can be measured and the measured condition can be reliably extrapolated to a convenient moment in the future in order to facilitate the planning process while maintaining flight safety. Much research effort is currently being made for the development of technologies that enable CBM, including structural health monitoring (SHM) systems. Great progress has already been made in sensors, sensor networks, data acquisition, models and algorithms, data fusion/mining techniques, etc. However, the transition of these technologies into service is very slow. This is because business cases are difficult to define and the certification of the SHM systems is very challenging. This paper describes a possibility for fielding a SHM system on legacy military aircraft with a minimum amount of certification issues and with a good prospect of a positive return on investment. For appropriate areas in the airframe the application of SHM will reconcile the fail-safety and slow crack growth damage tolerance approaches that can be used for safeguarding the continuing airworthiness of these areas, combining the benefits of both approaches and eliminating the drawbacks.

• 항공우주시스템공학회지
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• 제15권3호
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• pp.71-78
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• 2021

현대 항공기에서 대부분의 기능은 소프트웨어에 의해 통제되고 있으므로 소프트웨어 오류는 항공기 안전과 직결된다. MIL-HDBK-516C 15장은 군용항공기 탑재 소프트웨어의 안전한 개발과 검증을 위해서 적용되는 기준이다. 미 공군은 이 기준이 반복적인 미충족을 경험함에 따라 기준 충족을 위한 지침으로 감항성 회람(AC-17-01)을 발간하였다. 본 논문에서는 MIL-HDBK-516C 15장, AC-17-01, 그리고 미 연방 항공청에서 적용하고 있는 SW 인증 지침(DO-178C)을 비교 분석하였다. 먼저 AC-17-01 단계와 각 단계에서 명시된 MIL-HDBK-516C 15장 기준 그리고 MIL-HDBK-516C 기준에서 DO-178C를 명시한 기준간 정합 비율 식을 정의하였다. 그리고 비율 분석을 통하여 AC-17-01과 DO-178C를 달성하는 경우 MIL-HDBK-516C 충족 가능한 기준을 도출하였다. 분석결과를 바탕으로 항공 소프트웨어 개발 프로세스를 수립하고 MIL-HDBK-516C 15장 적용 사례를 제시하였다.

• 한국군사과학기술학회지
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• 제26권1호
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• pp.83-90
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• 2023

The external store fitted to the aircraft may affect the flight characteristics and flight safety of the aircraft, which requires the analyses and testing on it. The purpose of this study is to identify and analyze types of failures that can affect the flight safety of aircraft due to the installation of external stores, and to check the flight safety of aircraft through dropping tests of the external stores. After identifying the types of failures that could affect the flight safety of the aircraft, the criticality was calculated to analyze the effect on the flight safety of the aircraft. Four types of failures were selected: unintentional dropping, failure of dropping, unintentional main wing deployment, and release of tail wing restraint of the external store, which are considered to affect the flight safety of the aircraft due to the operation of the external store. As a result of the aircraft's flight safety analysis on the failure types, the criticality requirements were met. Based on this, after obtaining the airworthiness certification, the drop test was successfully performed to confirm the flight safety of the aircraft by mounting an external store on the aircraft. However, in addition to the four hazards carried out in this study, the real external stores of the military aircraft may have various factors affecting the flight safety of the aircraft, so further research will be needed.