• Journal of Advanced Navigation Technology
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• v.22 no.2
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• pp.84-89
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• 2018

Due to the development of domestic technology, a variety of aircraft launch weapons have been developed, and the importance of aircraft-store integration certification is increasing. The aircraft-Store integration certification is to certify compliance with the armaments/stores integration criteria set out in the Standard ACC and to prove that there is no problem with the safety flight. Therefore, it is necessary to reflect the requirements of the aircraft in the store development process to reduce the design change requirement in the compatibility verification stage. In this paper, the relationship between the Standards ACC, aircraft-store compatibility reference document MIL-HDBK-1763, and the development process of cruise guided weapons have been analyzed. As a result of the analysis, it was concluded that the design changes in the aircraft-store integration certification stage could be reduced if the aerodynamic and structural design requirements were reflected from the conceptual design stage.

• International Journal of Aerospace System Engineering
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• v.10 no.1
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• pp.14-24
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• 2023

The materials applied to the aircraft fuselage, parts, and components must be verified by relative authorities in accordance with the procedures set by the airworthiness authority to achieve the aircraft type certification. There are no examples of domestic composite materials which were verified in order to be applied to aircraft structure. In this study, the composite material certification system of NCAMP, an American composite material standard certification organization, was reviewed and used as the fundamentals of the first aerospace composite material certification system in ROK(Fig 2,8). Also updated material certification documents were developed and confirmed by material certification engineers and inspectors. This aerospace composite material qualification system is intended to modernize the material certification system for AAM(Advanced Air Mobility) as well as aircraft and to enhance the understanding of related technicians and inspectors.

• Advances in aircraft and spacecraft science
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• v.2 no.4
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• pp.391-401
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• 2015

Crashworthiness design and certification have been and will continue to be the main concern in aviation safety. The effects of roll angles on fuselage section crashworthiness for typical civil transport category aircrafts were investigated. A fuselage section with waved-plates under cargo floor is suggested, and the finite element model of fuselage section is developed to simulate drop test subjected to 7 m/s impact velocity under conditions of 0-deg, 5-deg, 10-deg and 15-deg roll angles, respectively. A comparative analysis of failure modes, acceleration responses, and energy absorption of fuselage section under various conditions are given. The results show that the change of roll angles will significantly affect fuselage deformation, seat peak overloads, and energy absorption. The crashworthiness capability of aircraft can be effectively improved by choosing appropriate landing way.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.3
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• pp.251-262
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• 2021

The airworthiness certification of lightning indirect effects becomes an important issue in personal air vehicles (PAVs), which are being actively developed around the world. PAVs are very vulnerable to lightning strikes, because of miniaturization, use of the electric engines, composite materials, and application of unmanned navigation systems. In this study, we first examined various steps of certifications for lightning indirect effects shown in AC 20 136B issued by the Federal Aviation Administration (FAA). We then applied certification guidelines for equipment transient design level listed in RTCA DO 160G Section 22 to PAVs and investigated lightning transient environments inside the PAVs. We also analyzed the aircraft level tests specified in SAE ARP 5416A by using electromagnetic computational analysis software EMA3D. Finally, we analyzed the actual transient level for PAVs and derived the data necessary for conformity certification.

• Journal of Aerospace System Engineering
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• v.17 no.1
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• pp.1-9
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• 2023

Recently, aerospace industries in South Korea are expected to continue to grow due to UAM. Accordingly, certification services for aircraft are expected to increase. As a way to cope with the increase of certification work, one could consider a delegation system that can limitedly delegate the unique role of airworthiness authorities. In this paper, we reviewed regulations of FAA's individual delegation (DER, DAR, DMIR, etc.), the organizational delegation system (ODA), and the EASA's organizational delegation system (DOA, POA). We also reviewed regulations and actual status of delegation system in South Korea. On the basis of these, considering circumstances of aerospace industries in South Korea, we presented a method to introduce certification delegation system gradually and to improve domestic certification regulation.

• Journal of Aerospace System Engineering
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• v.6 no.2
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• pp.1-6
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• 2012

On this study, as a Human Factor(HF)'s point of view, typical PVI(Pilot Vehicle Interface) evaluation for small airplane cockpit design, PVI evaluation items and procedures to show compliance to KAS Part 23 "Airworthiness Standards : Normal, Utility, Acrobatic, And Commuter Category Airplanes" are introduced and reviewed. This study is based on the experience of Korean small civil airplane development and certification program.

• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.196-204
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• 2008

Modem rotorcraft is required to have the capability to operate in all-weather conditions. Also icing condition is important issue to aircraft safety and certification. And rotorcraft icing research has come a long way during the past few decades. The aircraft icing is the most difficult to handle. So, icing-related accidents, incidents and operating problems still occur regularly in service, despite improvements in design and test techniques. By reviewing icing certification requirement of FAR(Federal Aviation Regulations) and KAS(Korean Airworthiness Standard), this paper describes methods how to demonstrate safety in the flight and consideration of icing when rotorcraft is required TC(Type Certification).

• Current Industrial and Technological Trends in Aerospace
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• v.8 no.2
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• pp.124-135
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• 2010

The Japanese and U.S. governments has signed a Bilateral Aviation Safety Agrement and associated implementation procedures for airworthiness on April 27, 2009 to mutually accept the airworthiness approvals for aircraft and parts that the other country issue. This bilateral agreements do not relieve the Civil Aviation Authority(CAA) of its statutory responsibilities for certification. However, they provide an alternative means for the CAA to make its findings, recognizing the competency of another authority to conduct certification functions in a manner comparable to, and on behalf of, the CAA. In this way, the bilateral agreements contribute to ensuring aviation safety as well as reducing the burden imposed on the aviation industries without compromising safety. This paper is to discuss recent status of Bilateral Aviation Safety Agreement and associated Japanese Aircraft Certification System.

• Journal of Aerospace System Engineering
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• v.14 no.1
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• pp.62-67
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• 2020

The European Aviation Safety Agency (EASA) legislates the CS-E (Certification Specification-Engine) for type certification of aircraft engines. According to the CS-E, engine manufacturers (type certificate holders) the need to show compliance of continued airworthiness of an engine during the overhaul, and the Accelerated Mission Test (AMT) is usually accepted as means of compliance. As a part of the Korean Civil Helicopter program, the engine has been developed with foreign manufacturers to achieve the EASA engine type certificate. In this study, the AMT procedure is planned for the engine to be certified by the EASA, and AMT cycles are also established to meet airworthiness requirements of the CS-E in consideration of the engine design and operation characteristics.

• Journal of Aerospace System Engineering
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• v.16 no.1
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• pp.17-27
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• 2022

A certain level of stability margin airworthiness criteria should be met to secure robustness against uncertainties between the real plant and the model in a flight control system design. The U.S. Department of Defense (DoD) specification of MIL-F-9490D and airworthiness certification standard of MIL-HDBK-516B uses gain and phase margin criteria of flight control system. However, the same stability margin criteria is applied at all development phases without considering the design maturity of each development phase of the aircraft. Ultimately, a problem arises when the aircraft operation envelope is excessively restricted. This paper proposes the relation of handling qualities and stability margin, and presents re-established stability margin criteria as a development phases and verification methods. The results of the research study are considered to contribute to the verification of the stability margin criteria more flexibly and effectively by applying the method to not only the currently manned developing aircrafts but also the unmanned vehicle to be developed in the future.