• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.74-81
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• 2004

In this study preliminary structural design has been performed to develop an all composite wing box for experimental aircraft(classified in FAR Part 21). Considerations on composite materials and their manufacturing process were taken into account throughout the design phase. Aerodynamic loads were estimated by using Shrenk method(NACA TM No 948) and FAR Part 23 Appendix A. The structural layout has been determined to carry effectively the critical loads and to maximize the benefit of composite structure. Maximum strain failure allowable and first ply failure criteria were applied for the sizing of major structural members. Finally, the designed composite wing box structure is presented in the form of drawings, which include material specifications, stacking sequences and joint design.

• Journal of Aerospace System Engineering
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• v.6 no.3
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• pp.7-12
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• 2012

The contents of aircraft system safety assessment vary depending on factors such as the complexity of the system, how critical the system is to flight safety, what volume of experience is available on the type of system and the novelty and complexity of the technologies being used. If the system safety assessment is to substantiate that the developed products are 'safe enough' to be taken into use, then the system safety assessment should be planned and managed to provide the necessary assurance that all relevant hazards and failure conditions have been identified and that all significant combinations of hazards and failures which could cause those conditions have been considered. The assessment must assist the designer and management in making decisions. It must make clear what the critical features of each system are and upon which special manufacturing techniques, inspection, testing, crew drills and maintenance practice they are critically dependent. This paper has prepared to study on promoting the efficiency of aircraft system safety assessment and to present how to compile system safety assessment strategy.

• Composites Research
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• v.28 no.6
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• pp.402-407
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• 2015

It is well known that the polymer matrix composite materials have good specific strength, making them appropriate for use in transport vehicle. Since the property of composite materials can be obtained only after manufacturing parts, the property depends on greatly on the fabrication process, which is different from metallic system. Therefore, in order to use composite materials for aircraft, the certifying agency requires a robust database with extensive tests and proof of the process unlike metals. Recently developed material qualification methodology by NCAMP (National Center for Advanced Materials Performance) has been accepted by FAA and EASA and can be applied to type certificate reducing time and cost of developing a composite materials database for aircraft application. This paper summarizes a study to establish the composite materials database to apply the NCAMP methodology to composite materials characterization for composite aircraft and to provide the effective materials database through Aerospace Composite Materials Data Center to be approved by Korea Civil Aviation Certification Agency.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2000.11a
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• pp.245-248
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• 2000

Modern aircraft composite structures are designed using a damage tolerance philosophy. This design philosophy envisions sufficient strength and structural integrity of the aircraft to sustain major damage and to avoid catastrophic failure. The only reasonable way to treat on the same basis all the conditions and uncertainties participating in the design of damage tolerant composite aircraft structures is to use the probability-based approach. Therefore, the model has been developed to assess the probability of structural failure (POSF) and associated risk taking into account the random mechanical loads, random temperature-humidity conditions, conditions causing damages, as well as structural strength variations due to intrinsic strength scatter, manufacturing defects, operational damages, temperature-humidity conditions. The model enables engineers to establish the relationship between static/residual strength safety margins, production quality control requirements, in-service inspection resolution and criteria, and POSF. This make possible to estimate the cost associated with the mentioned factors and to use this cost as overall criterion. The methodology has been programmed into software.

• The Journal of Industrial Distribution & Business
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• v.10 no.4
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• pp.13-24
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• 2019

Purpose - This research explores the impacts of third-party logistics (3PLs) within the aircraft Maintenance, Repair and Overhaul (MRO) industry in the United Arab Emirates (UAE) to explore the role of collaborative relationships for improving outsourcing. Globalization and time based competition have changed business environments and challenged the conventional management strategies that are related to core competencies and operational models. Organizations are forced to devise innovative practices in which logistics outsourcing to 3PLs offers significant advantages. Research design, data, and methodology - This case study was conducted within a leading global aircraft MRO organization whose reach spans across Europe, the Middle East, Asia and the Americas. The methods used face to face semi-structured interviews, validated through further focus group discussions. Results - These findings highlight the effectiveness of collaborative relationships on their role to improve outsourcing and also demonstrated that MROs gain several advantages from 3PL arrangements. However, any gaps in outsourcing management elevates potential risks to organizations as well, which could result in reputational, operational and financial losses. Conclusions - Although generalizability is not possible due to the case study approach, generality suggests that in order to reduce reputational, operational and financial risks, enhanced collaboration with 3PLs is recommended to optimize outsourcing arrangements.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.1 no.1
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• pp.79-88
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• 2002

High speed machining system have been used in industrial because it is effective to a material manufacturing with various shape. Recently the end-milling processing is needed the high-precise technique with good surface roughness and rapid time in aircraft, automobile part and molding industry. Therefore this study proposed to decide best manufacturing cutting condition for surface roughness and rapid manufacturing tune by using computer Image processing system and 3D modelling. Until the 16,000 rpm, the surface roughness is decreased rapidly, but it is not over that. The 22,000 rpm is the spindle speed with the optimum surface in the high speed end-milling. In the case of the feed rate with 2,000 mm/mm and 8,000 mm/mm, the surface roughness is better than 4,000 mm/min and 6,000 mm/min. By using the 3D modelling, it is effectively represented shape characteristics of working surface m high speed end-milling.

• Transactions of the Korean Society of Machine Tool Engineers
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• v.11 no.1
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• pp.52-60
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• 2002

The purpose of this research is to study the vibration and acoustic pressure radiation from a thin isotropic flat plate stiffened by a rectangular array of beams, and excited by a time harmonic point force. These constructions on aircraft and ship structures are often subjected to fiequency dependent pressure fluctuations and forces. Forces from the these excitations induce structural vibrations in a wide range of fiequencies, which may cause such things as acoustic fatigue and internal cabin noise in the aircraft. It is thus important that the response characteristics and vibration modes of such periodic structures be horn. From this theoretical model, the sound pressure levels(SPL) in a semi-infinite fluid(water) bounded by the plate with the variation in the locations of an external time harmonic point farce on the plate can be calculated efficiently using three numerical tools such as the Gauss-jordan method the LU decomposition method md the IMSL numerical package.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2014.10a
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• pp.42-47
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• 2014

In this paper, fatigue life analysis of each structure was performed through theoretical analysis method at design stage in order to verify the success or failure of the store's acoustic noise durability according to the Method 515.5 standard of MIL-STD-810F. In addition, experimental analysis was carried out through the ground and flight test by manufacturing the measuring store, and verification of the sound durability was completed through the flight test after manufacture of the actual store. Furthermore, the commercial FEM code through the PSD calculation method applying measured SPL enables verify the durability of new store components development for the future.

• Journal of Aerospace System Engineering
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• v.8 no.2
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• pp.27-32
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• 2014

From the flight safety and the performance point of views, a new engine installation impacts an helicopter development or upgrade program significantly. More than a close relationship between an aircraft manufacturer and an engine manufacturer is necessary for the best integration work from the program initiation phase. In this paper, technical cooperation between aircraft and engine companies, and technical supports by the engine manufacturer for the T700/701K engine during the Surion development program are summarized. The applications of official technical program documents, US Mil-spec, France airworthiness regulations as the standard of the engine installation work, and engineering activities at each phase such as contract, design and manufacturing, flight clearance, ground and flight tests are described. This paper would be a cornerstone for the future domestic helicopter development program.

• Journal of the Korea Institute of Military Science and Technology
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• v.6 no.2
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• pp.35-44
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• 2003

A Decal Panel is developed for the Night Vision Imaging System of XKO-1 aircraft. The Decal Panel is a kind of lighting system kits and is installed on each system switch box in crewstation. The Decal Panel consists of upper panel made of polycarbonate and lower panel which is a printed circuit board. This paper includes the design, manufacture, test and evaluation of Decal Panel in addition to items and conditions of environmental test. Besides it is confirmed the Key for manufacturing a decal panel, is depth of paint, dry time period and frequency, and diffusion material for spreading of light.