• Journal of the Korean Society of Systems Engineering
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• v.6 no.1
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• pp.25-32
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• 2010

The Test and Evaluation (T&E) process is an integral part of the Systems Engineering Process. The purpose of Test and Evaluation (T&E) in a system development is to identify the areas of risk to be reduced or eliminated. In this study, when develop aircraft of Civil Aviation with development experience of Military Aircraft, it is that establish Test and Evaluation process. Test and Evaluation for KC-100 small aircraft development can divide to certification test and development test. Certification test is proved compliance about Korea Airworthiness standard (KAS Part 23), through Development Test verify required performance of aircraft. These Test and Evaluation Process is more efficient and optimized.

• Journal of the Korean Society of Systems Engineering
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• v.5 no.2
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• pp.49-56
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• 2009

KC-100(KAI Civil Aircraft, Small Series) aircraft is 4 seats general aviation aircraft with single piston engine which is developing under FAA part 23 category by Korea Aerospace Industries(KAI) and will be a shadow program for civil aircraft safety infrastructure improvement. This aircraft will be the first civil aircraft developed in Korea meeting the Korean regulatory KAS Part 23 requirements. Type certification for KC-100 aircraft was applied at the second half of this year. The type certificate is expected to be issued after 3 years of design, prototype manufacturing, ground and flight tests. In this paper the system engineering process for civil aircraft was first reviewed. Next, the differences and similarities in the system development between military and civil aircraft were systematically examined using experiences for KAI military aircraft development program.

• 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.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.16 no.5 s.110
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• pp.503-513
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• 2006

The duration time of aircraft noise event is also an important factor for the evaluation of civil aircraft noise, which is considered as a notable characteristic of military aircraft noise. SEL is proved as a suitable noise metric for the measuring military aircraft noise of various flight pattern considering the duration time of noise event. This study reviews whether SEL is a suitable for measuring civil aircraft noise and study shows SEL is fairly compensating the duration time of civil aircraft noise event for the evaluation of aircraft noise. Noise metric for the evaluation aircraft noise based on SEL is more appropriate than based on $L_{MAX}$ for compensating duration time of noise event either military aircraft or civil aircraft. In this reason, current formula of WECPNL based on energy average of measured $L_{MAX}$ for the evaluation of aircraft noise impact in 'Test Method of Noise and Vibration of Korea' is recommended to be amended to formula of WECPNL based on energy average of measured SEL considering compensation of noise event duration time, if WECPNL is not based on measured EPNL, a metric compensating duration time.

• The Korean Journal of Air & Space Law and Policy
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• v.19 no.1
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• pp.141-163
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• 2004

The limits in the use of force against a civil aircraft which intrudes into sovereign airspace have not been defined in the aspect of international law. Therefore, this paper intends to analyze international laws and practices about sovereign airspace intrusions by the civil aircraft, and to examine the legality in the use of force against the civil aircraft hijacked by means of political terrorism, in particular. In this paper, the sphere of study is restricted within the problems of interception against the civil aircraft which intrudes into sovereign airspace in times of peace, excluding the problems against a state aircraft, and the responsibilities for the civil or criminal affairs due to interceptions. Herein this paper analyzes the existing international laws and the cases of each nation's use of force against the civil aircraft which intrudes into sovereign airspace, and organizes the conditions in the use of force which have been accepted in international laws and practices, and then applies them to the special case of civil aircraft hijacked by political terrorism. Consequently, this paper suggests that the basic principles of necessity, ultimateness, and proportionality be taken into consideration in the use of force against civil aircraft which intrudes into sovereign airspace. This study finally suggests that the possibility in the use of force against civil aircraft hijacked by political terrorism might be higher than any type of civil aircraft intrusions into sovereign airspace due to the factor of necessity of national security concerned.

• The Korean Journal of Air & Space Law and Policy
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• v.24 no.1
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• pp.3-35
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• 2009

A concept of Aircraft crime includes an Air range, unlawful seizure of aircraft and unlawful acts against the safety of civil aviation. There are international treaties and conventions which have mainly been enacted by ICAO. The following treaties and conventions are categorical and unconditional norms that any States are clearly condemned. Convention on Offences and Certain other Acts Committed on Board Aircraft, Convention for the Suppression of Unlawful Seizure of Aircraft, Convention for the suppression of unlawful acts against the safety of civil aviation, Protocol for the Suppression of Unlawful Acts of Violence at Airports Serving International Civil Aviation, Convention on the Marking of Plastic Explosives for the Purpose of Detection In this essay, I present the meaning of the aircraft crime mentioned on the treaties above and jurisdiction of the crime. Moreover, I explain how to demand reparation for damages onboard or on the surface when an aircraft crime is occurred. Lastly, I indicate legal bases of how to protect the victims of the aircraft crime by mentioning specific cases relating to the crime.

• Nuclear Engineering and Technology
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• v.54 no.1
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• pp.326-342
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• 2022

Comparative analyses of a shield building subjected to a large commercial aircraft impact between decoupling method and coupling method are performed in this paper. The decoupling method is applying impact force time-history curves on impact area of the shield building to study impact damage effects on structure. The coupling method is using a model including aircraft and shield building to perform simulation of the entire impact process. Impact force time-history curves of the fuselage, wing and engine and their total impact force time-history curve are obtained by the entire aircraft normally impacting the rigid wall. Taking aircraft structure and impact progress into account some loading areas are determined to perform some comparative analyses between decoupling method and coupling method, the calculation results including displacement, plastic strain of concrete and stress of steel plate in impact area are given. If the loading area is determined unreasonably, it will be difficult to assess impact damage of impact area even though the accurate impact force of each part of aircraft obtained already. The coupling method presented at last in this paper can more reasonably evaluate the dynamic response of the shield building than the decoupling methods used in the current nuclear engineering design.

• The Korean Journal of Air & Space Law and Policy
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• v.35 no.2
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• pp.247-280
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• 2020

For customs-free and liberalization on the trade of aircraft parts, the WTO Agreement on Trade in Civil Aircraft was separately concluded as plurilateral trade agreement at the time of launching WTO in 1995, and currently 33 countries including the United States and the EU are acceded but Korea does not. Major details of the Agreement on Trade in Civil Aircraft include product coverage, the elimination of customs duties and other charges, the prohibition of government-directed procurement of civil aircraft, the application of the Agreement on Subsides and Countervailing Measures, and the consultation on issues related to this Agreement and dispute resolution. Article 89 paragraph 6 of the current Customs Act was newly established on December 31, 2018, and the tariff reduction rate for imports of aircraft parts will be reduced in stages from May 2019 and the tariff reduction system will be abolished in 2026. Accordingly, looking at the impact of the Agreement on Trade in Civil Aircraft on the aviation industry, first, as for the impact on the air transport industry, an tariff allotment of the domestic air transport industry is expected to reach about 160 billion won a year from 2026, and upon acceding to the Agreement on Trade in Civil Aircraft, the domestic air transport industry will be able to import aircraft parts at no tariff, so it will not have to pay 3 to 8 percent import duties. Second, as for the impact on the aviation MRO industry, if the tariff reduction system for aircraft parts is phased out or abolished in stages, overseas outsourcing costs in the engine maintenance and parts maintenance are expected to increase, and upon acceding to the Agreement on Trade in Civil Aircraft, the aviation MRO industry will be able to import aircraft parts at no tariff, so it will reduce overseas outsourcing costs. If the author proposes a policy direction for the trade liberalization of aircraft parts to ensure competitiveness of the aviation industry, first, as for the tariff reduction by the use of FTA, in order to be favored with the tariff reduction by the use of FTA, it is necessary to secure the certificate of origin from foreign traders in the United States and the EU, and to revise the provisions of Korea-Singapore and Korea-EU FTA. Second, as for the push of acceding to the Agreement on Trade in Civil Aircraft, it would be resonable to push the acceding to Agreement on Trade in Civil Aircraft for customs-free on the trade of aircraft parts, as the tariff reduction method by the use of FTA has limits. Third, as for the improvement of the tariff reduction system for aircraft parts under the Customs Act, it is expected that there will take a considerable amount of time until the acceding to the Agreement on Trade in Civil Aircraft, so separate improvement measures are needed to continue the tariff reduction system of aircraft parts under Article 89 paragraph 6 of the Customs Act. In conclusion, Korea should accede to the WTO Agreement on Trade in Civil Aircraft to create an environment in which our aviation industry can compete fairly with foreign aviation industries and ensure competitiveness by achieving customs-free and liberalization on the trade of aircraft parts.

• Current Industrial and Technological Trends in Aerospace
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• v.7 no.2
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• pp.85-94
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• 2009

The Fly-By-Wire system was first applied to the fighter and its inherent advantages lead to the advent of the Fly-By-Wire civil aircraft. Recently even the small jet aircraft shows the trend of adopting the Fly-By-Wire system. In the future, most of the aircraft are expected to be the Fly-By-Wire type. In this paper, the structure and the characteristics of the Fly-By-Wire system applied to the civil aircraft was described. The development trend of the redundant method of the flight control system, data communication system, control surface actuation system and the control laws implemented by the Fly-By-Wire system of the civil aircraft are discussed.

• Structural Engineering and Mechanics
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• v.44 no.1
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• pp.35-49
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• 2012

A series of fatigue test were carried out on scarfed lap joints (SLJ) using in airfoil siding to explore the effect of structural details, such as rows of rivets, lap angles, on its fatigue performance. Finite element (FE) analysis was employed to explore the effect of lap angle on load transfer and the stress evolution around the rivet hole. At last, the fatigue lives were predicted by nominal stress approach and critical plane approach. Both of the test results and predicted results showed that fatigue life of SLJ was remarkably increased after introducing lap angle into the faying surface. Specimen with the lap angle of $1.68^{\circ}$ exhibits the best fatigue performance in the present study.