• 품질경영학회지
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• 제32권3호
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• pp.166-181
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• 2004

The aircraft production quality management system in Korea has been implemented to support the developmental phase of Korean aircraft industries, from overhaul of the aircraft and engines to development of military trainer aircraft. After the deletion of the Mil-Q-9858A standard in 1996, Korean aerospace companies established ISO 9001 and AS 9100 as their basic aerospace quality management system specifications. These quality standards were adopted in the same period of time by other leading international aircraft manufacturing companies. This paper presents a future direction on the improvement of quality management systems for Korean aircraft production company by considering (1) Korean governments strategy for the development of Korean aircraft Production industries, (2) short and long term business plan of Korean aerospace industries, and (3) benchmarking leading international company's quality management systems.

• 시스템엔지니어링학술지
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• 제6권1호
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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.

• 한국군사과학기술학회지
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• 제27권4호
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• pp.495-506
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• 2024

In this study, we propose the terrain following algorithm using model predictive control and nonlinear disturbance observer-based backstepping sliding mode controller for an aircraft system. Terrain following is important for military missions because it helps the aircraft avoid detection by the enemy radar. The model predictive control is used to replace the generating trajectory and guidance with the flight path angle constraint. In addition, the aircraft is affected to the parameter uncertainty and unknown disturbance such as wind near the mountainous terrain. Therefore, we suggest the nonlinear disturbance-based backstepping sliding mode control method for the aircraft that has highly nonlinearity to enhance flight path angle tracking performance. Through the numerical simulation, the proposed method showed the better tracking performance than the traditional backstepping method. Furthermore, the proposed method presented the terrain following maneuver maintaining the desired altitude.

• 비파괴검사학회지
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• 제35권6호
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• pp.421-428
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• 2015

An important trend in the sustainment of military aircraft is the transition from preventative maintenance to condition based maintenance (CBM). For CBM, it is essential that the actual system condition can be measured and the measured condition can be reliably extrapolated to a convenient moment in the future in order to facilitate the planning process while maintaining flight safety. Much research effort is currently being made for the development of technologies that enable CBM, including structural health monitoring (SHM) systems. Great progress has already been made in sensors, sensor networks, data acquisition, models and algorithms, data fusion/mining techniques, etc. However, the transition of these technologies into service is very slow. This is because business cases are difficult to define and the certification of the SHM systems is very challenging. This paper describes a possibility for fielding a SHM system on legacy military aircraft with a minimum amount of certification issues and with a good prospect of a positive return on investment. For appropriate areas in the airframe the application of SHM will reconcile the fail-safety and slow crack growth damage tolerance approaches that can be used for safeguarding the continuing airworthiness of these areas, combining the benefits of both approaches and eliminating the drawbacks.

• 한국군사과학기술학회지
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• 제24권3호
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• pp.302-308
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• 2021

Developers generally use test standards suggested by military standards such as MIL-STD-810G when performing vibration tests in the materiel development. However, according to MIL-STD-810G, it is recommended to test by tailoring the test standard suitable for the developed materiel, and it is specified to apply the suggested test standard only when there is difficulty in tailoring. In addition, the test standards presented by MIL-STD-810G are standards created under operating conditions different from the actual operating environment of each developed materiel, so the test according to this standard may be excessive or understated. Therefore, the developer must create an appropriate vibration test standard for the developed materiel as similar to the operating conditions as possible. In this paper, the procedure for creating the functional test standard and durability test standard suitable for the operating environment of the equipment to be mounted on the propeller aircraft under development is described, and the created standard is introduced.

• Advances in aircraft and spacecraft science
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• 제8권4호
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• pp.289-302
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• 2021

Ensuring flight safety for passengers as well as crew is the most important aspect of modern aviation, and in order to achieve this, it is necessary to be able to forecast the durability of individual components. The present contribution illustrates the results of a computational analysis to determine the possibility of analysing the prediction of bearing durability in on-board rotating equipment from the point of view of thermal fatigue.In this study, a method developed at the Air Force Institute of Technology was used for analysis, which allowed to determine the bearing durability from the flight altitude profile. Two aircraft have been chosen for analysis - a military M-28 and a civilian Embraer. As a result of the analysis were obtained: the bearing durability in on-board rotating devices, average operation time between failures, as well as failure rate. In conclusion, the practical applicability of this approach is demonstrated by the fact that even with a limited number of flight parameters, it is possible to estimate bearing durability and increase flight safety by regular inspections.

• 한국군사과학기술학회지
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• 제16권2호
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• pp.146-153
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• 2013

Visual information and aural warning of independent aircraft survivability equipment increase the pilot workload and limit the effective countermeasures. For increase the aircraft survivability, Integrated design of survivability display and aural warning need to consider pilot intuitions. If pilot aware the threat by intuition, evade or escape from the threat using the countermeasures equipment, it will increase the survivability. This paper describe the design and verification of for Utility Helicopter survivability equipment.

• 한국군사과학기술학회지
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• 제16권2호
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• pp.191-198
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• 2013

Geo-pointing is a function that maintains LOS(Line of Sight) to a stationary ground target by controlling azimuth and elevation angles of a EOS(Electro-Optical System) which are calculated from aircraft navigation data and target coordinates. In design and implementation of the geo-pointing, a transmission time delay between GPS/INS and EOS is a major degradation factor of the geo-pointing performance when the aircraft is rapidly maneuvered especially. In this paper, a kalman filter is designed to compensate the transmission time delay of aircraft navigation data. Simulation and test results show that the geo-pointing performance is enhanced by the proposed compensation technique.

• 한국국방경영분석학회지
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• 제15권2호
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• pp.147-159
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• 1989

This paper presents a formalized methodology for conducting cost-effectiveness analysis on the ROK Navy's maritime patrol aircraft. The methodology involves a Delphi method application for determining the group of appraisal variables as well as their weight values in the area of aircraft effectiveness analysis, Life-cycle costing was employed to produce cost in terms of present worth values of all costs that occur over the common 20-year life cycle. A wide range of experts was selected so that their opinions could be effectively collected and synthesized to form the framework of the effectiveness model. Such a model development strategy provides easy acceptance of the analysis result and assure fairness of the analysis.

• 한국국방경영분석학회지
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• 제13권1호
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• pp.19-27
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• 1987

This paper deals with the development of an expert system modeling by constructing a knowledge-based system of the dive recovery for anticrash on the ground or sea during the task of fighter aircraft. In an IBM PC / XT computer, a prototype dive recovery expert system is constructed using mu LISP-86 programming language, and is interconnected to the SAM SUNG RM-501 robot arm to test and simulate this model. The knowledge base of this model is composed of the dive recovery charts and the V-N envelope charts of F-4 D Phantom fighter aircraft. It is shown that the prototype expert system woks well and the feasibility of practical realization is valid.