• 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 Nondestructive Testing
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• v.30 no.1
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• pp.54-59
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• 2010

After the advent of B787(Boeing Co.), a civil aircraft using composite materials more than 50% of it total structural weight for weight savings，best performances and efficiencies, various endeavors to develop and apply the state of art of structural health monitoring(SHM) technologies for composite aircraft have been made for many years. Despite their plentiful advantages composite aircraft structures are susceptible to the hidden or barely visible impact damages(BVID) and excessive loads that if unchecked may lead to lower structural integrity, loss of operational performance and finally a sudden catastrophic failure of the aircraft structure. In this paper background of SHM technology and relevant technologies for application of SHM technology to the composite aircraft in the near future and requirements for certification of SHM system are shortly presented.

• Journal of Aerospace System Engineering
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• v.6 no.2
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• pp.28-34
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• 2012

Structural integrity evaluation is important item in the aircraft certification. Recently, it is designed for limit load, material weakness about fatigue and corrosion, damage by bird strike in flight to evaluate structural integrity of aircraft. And static/fatigue analysis are performed to secure structural integrity, it was verified by static and fatigue tests. To evaluate the structural integrity of small aircraft tail, structural integrity was calculated by the finite element analysis. In the present study, finite element analysis are performed to pick out load cases in flight occurrence, and secure margin of safety to evaluate structural integrity of KC-100 tail unit. The proprieties of finite element analysis results are compared with the static structure test results. The estimation process of structural integrity for small aircraft tail may help the design.

• Journal of Aerospace System Engineering
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• v.14 no.spc
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• pp.31-38
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• 2020

The aircraft system safety assessment, which is emphasized in the development and certification of aircraft, is a systematic and comprehensive evaluation process to determine that all relevant failure conditions have been identified and that all significant combinations of failures cannot result in unacceptable hazards. As the aircraft systems become more complex and require integrated function and performance, proper safety objectives must be established and appropriate assessments are need to be accompanied. This paper has prepared to propose the efficient probabilistic analysis of failure data to evaluate the risk level over the entire aircraft lifecycle through the safety assessment and to review the considerations for aircraft certification and safety improvement.

• Journal of Aerospace System Engineering
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• v.2 no.4
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• pp.31-37
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• 2008

To operate UAV in the civil airspace, the airworthiness of UAV system have to be proven by the civil certification system. However, it is difficult for UAV to be certified by the existing certification system because the existing certification system has been developed for the manned aircraft. So, many civil aviation authorities and research institutes are studying developing airworthiness standards for UAV certification. To develop an airworthiness standards for UAV, the airworthiness level of safety have to be established based on UAV categorization. I would like to introduce an quantitative methods for establishing airworthiness level of safety of UAV based on UAV categorization and example of Smart UAV.

• Journal of Aerospace System Engineering
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• v.8 no.3
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• pp.20-26
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• 2014

This paper presents the procedures and the results of the pitch control force via flight test for a light airplane in order to make out the stability of the aircraft and the compliance with concerned regulation. The flight test procedures were determined in order to obtain the aircraft type certification. The instrumentation equipments including airspeed indicator, accelerometer, and pitch control force measurement tools are used to perform the flight test. For the flight test, the airspeed and the pitch control force with related normal acceleration are measured sustaining turn flight with bank angle derived from trim speed. The flight test results showed that the handling qualities of the airplane are complied with the KAS-23, the regulation of the Korean government for the light airplane type certification.

• Journal of Aerospace System Engineering
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• v.1 no.4
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• pp.7-12
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• 2007

From the beginning of aviation history, in-flight smoke/fire events have been a serious issue. As aircraft are getting larger and are becoming more auto-piloted and aircraft systems are getting more complex, it is an increasing risk of in-flight smoke/fire accidents accompanied with fire events. Therefore, we review the statistics of fire/smoke accidents in order to enhance an understanding for risk of in-flight smoke events, and present the certification requirements for smoke per KAS Part 25. In addition, we provide acceptable methods of complying with related requirements, such as smoke detection test, smoke penetration test and smoke evacuation test.

• Journal of Environmental Science International
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• v.23 no.3
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• pp.387-397
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• 2014

This study is carried out to propose an empirical equation which can promptly predict the aircraft noise level at a specific point (a receptor) near Jeju international airport by using the information of the flight path data. For this purpose, Analyses of multiple linear regression with the slant distances (SD) calculated from the gate analyses of the flight path data, aircraft noise certification levels with unit of EPNL(effective perceived noise level) and noise levels measured at receptors are performed by SPSS package. From these regression analyses for approach and departure of aircraft, we can propose empirical equations which is statistically significant. The noise levels predicted by these empirical equations are highly correlated the measured data.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1997.04a
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• pp.643-648
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• 1997

Concern for noise problems of a commercial aircraft in community and cabin is increasing due to the more restrictive regulation and customer requirements. This paper introduces to the work packages of the aircraft noise engineer for the development of a commercial aircraft. First of all, the noise engineer establish the design requirement and objectives(DR&O). Then the design and analysis are performed to satisfy with the DR&O during the conceptual and preliminary design phase. And the test and evaluation(T&E) are carried out to verify the analysis results and to acquire the type 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.