• Journal of Aerospace System Engineering
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• v.6 no.3
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• pp.13-18
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• 2012

Every 3000 hour an aircraft is stricken by a lightning. Also the lightning damage to the aircraft during flight are continually occurred due to extreme weather phenomena such as global warming. Under the airworthiness standards, the aircraft must be designed to protect lightning. To show compliance for lightning, the test should be conducted by the actual lightning current and voltage waveform for the actual aircraft or parts. After test, structure damage is detected via visual inspection or NDI. Structure substantiation for damage is to show retaining limit or near limit load capability. This is conducted by test or analysis based on test. Thus, the aircraft should retain structural strength to land safely, even though the damage of aircraft fuselage from Lightning strike are occurred.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.1
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• pp.49-61
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• 2015

Ground Based Augmentation System(GBAS) is a system that offers an aircraft within 23 NM radius from the airport precision positioning service and precision approach service using the concept of Differential Global Positioning System(DGPS). After GBAS ground equipment installing at the airport, functionalities and performances of GBAS should be verified through the GBAS ground and flight testing. This paper describes the methods and results for GBAS flight test using the flight inspection aircraft at Gimpo International Airport. From the test results, we confirmed that the VDB data was received without misleading within the VDB coverage of Gimpo International Airport, and VDB field strength, protection level, and course alignment accuracy met the evaluation's criteria.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.20 no.4
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• pp.126-131
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• 2012

In South Korea, there is no consideration for increasing labor costs and price fluctuation regarding the commission for a flight inspection. Because this causes a deficit in the flight inspection related operation, the cost system should be improved. Therefore, this research considers the first cost analysis in order to calculate a proper flight inspection commission through three different types of cost making methods. Moreover, as flight inspections are held by flights and human labors, labor costs are included as the main operation cost. According to the research, it is analyzed that the total cost to process flight inspection operations is decided by the scope of aircraft operation.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.13 no.6
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• pp.104-110
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• 2014

This paper presents a non-contact inspection system for automatically measuring the thickness of an aircraft wing rip product. In order to conduct the inspection of the wing rib thickness automatically, a non-contact laser displacement sensor, end-effector, and a robot were selected for use. The non-contact type inspection system was evaluated by measuring the measurement deviation of the rotation direction of a C-type yoke end-effector and the transfer direction of a V-slim end-effector. In addition, the non-contact inspection system for wing rib thickness measurements was validated through thickness measurements of a web, flange, and stiffener.

• Proceedings of the Korean Institute of Building Construction Conference
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• 2022.04a
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• pp.85-86
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• 2022

Traditionally, the facility inspection was visually conducted by the managers, and consequently the result can be subjective because of different perspective and experience of them. To solve this problem, the studies on this topic has tried to integrate the UAS. However, it is still concerned to use in practice due to the lack of analysis of the performance factors affecting the UAS-based facility condition inspection. Hence, the purpose of this study is to identify the critical factors as well as their correlations by modeling causal loop diagram (CLD). A total of 20 variables were derived in four categorized groups, and the relationships were analyzed. Further study will develop a system dynamics (SD) model to simulate various scenarios based on stock-flow diagram through the defined relationships in this study.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.21 no.7
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• pp.638-644
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• 2020

This study examines cracks that occur under the load of an aircraft. The life of aircraft vulnerability structures was analyzed and structural fitting improvements were made. Structural integrity and safety have been achieved through preemptive life expectancy and life management of aircraft structures. The crack size inspection capability of the aircraft under analysis is 0.03inch, compared with 0.032inch, which is the lowest of the three vulnerable parts. In addition, the fatigue life analysis results in approximately 1450 operating hours, the lowest of the three vulnerable parts relative to the aircraft's required life of more than 15000 operating hours, which increased the repeat count of the aircraft's initial and re-inspection times, and hence raised the resulting costs and manpower consumption. Finally, the features were improved through structural fitting of the identified three weak parts. The lowest critical crack size was secured at 0.13 through increased structural resistance to generated cracks and increased aircraft safety. The lowest structural fatigue life for cracks occurring during aircraft operation is 25000 operating hours, which are analyzed above the required structural life, resulting in more optimized improvements than the repair costs and excessive fitting range caused by cracks and fractures.

• The Magazine of the IEIE
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• v.21 no.11
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• pp.75-85
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• 1994

Safety and Reliability assessments of Avionics Parts must be conducted essentially in the step of disign and manufacture as it constitutes a major field of aircraft critical operation. Recently Avionics parts fabrication techniques are continuously developing by applying digital techniques. Airborne computer is being adopted on an aircraft for flight is being adopted on an aircraft for flight safety augmentation and simplification of controls including reduction of human error. Therefore inspection and evaluation procedures should be developed in order to accomodate such trends. The number of avionics parts is approximitely 72% of total TSO parts, so it is expected high added-values through manufactures of TSO parts in aircraft industries. Particuarly avionics parts must be manufacturered with our own technology to be used in Mid-class aircraft which will be developed soon. Along with this, preparation of Certification Procedures is essential for Avionics Parts.

• Journal of Mechanical Science and Technology
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• v.14 no.10
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• pp.1072-1080
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• 2000

Leakage magnetic flux (LMF) is widely used for non-contact detection of cracks. The combination of optics and LMF offers advantages such as real time inspection, elimination of electrical noise, high spatial resolution, etc. This paper describes a new nondestructive evaluation method based on an original magneto-optical inspection system, which uses a magneto-optical sensor, LMF, and an improved magnetization method. The improved magnetization method has the following characteristics: high observation sensitivity, independence of the crack orientation, and precise transcription of the geometry of a complex crack. The use of vertical magnetization enables the visualization of the length and width of a crack. The inspection system provides the images of the crack, and shows a possibility for the computation of its depth.

• Advances in aircraft and spacecraft science
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• v.7 no.3
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• pp.271-290
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• 2020

The paper describes the analysis of deployment strategies and trajectories design suitable for executing the inspection of an operative spacecraft in orbit through re-usable CubeSats. Similar missions have been though indeed, and one mission recently flew from the International Space Station. However, it is important to underline that the inspection of an operative spacecraft in orbit features some peculiar characteristics which have not been demonstrated by any mission flown to date. The most critical aspects of the CubeSat inspection mission stem from safety issues and technology availability in the following areas: trajectory design and motion control of the inspector relative to the target, communications architecture, deployment and retrieval of the inspector, and observation needs. The objectives of the present study are 1) the identification of requirements applicable to the deployment of a nanosatellite from the mother-craft, which is also the subject of the inspection, and 2) the identification of solutions for the trajectories to be flown along the mission phases. The mission for the in-situ observation of Space Rider is proposed as reference case, but the conclusions are applicable to other targets such as the ISS, and they might also be useful for missions targeted at debris inspection.

• Journal of Aerospace System Engineering
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• v.3 no.3
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• pp.1-6
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• 2009

The first Type Certificate project for small airplane is in progress in the Republic of Korea. Therefore, it is necessary to prepare the circumstances that the airplane developed and certificated by this country will exported to foreign countries and operated in the world. One of the main items to be prepared is the systems related with continuing airworthiness of aircraft during the operation. From this point of view, the systems and corresponding capabilities to maintain the aircraft to continue the flight and safe landing will be the immediate work. This study is to review the continuing airworthiness system established by foreign countries such as USA FAA and European EASA and to propose how we will setup our continuing airworthiness system for the airplane developed and certificated by the Republic of Korea.