• Journal of Aerospace System Engineering
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• v.4 no.2
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• pp.16-20
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• 2010

In General, the hydraulic system of T-50 Advanced Trainer is applied to flight control system, wheel & Brake system and fuel system for aircraft operation. The hydraulic system is operation with pressure of 3000psi. and many mechanical parts which is operated by hydraulic system has been stressed in incomplete environment same as heat and friction. for example, Oil leakage had occurred in the shutoff valve of FFP used in a certain period of time. After study, The crack progressed by fatigue due to the irregular hydraulic pressure and vibration has been identified as the reason of oil leakage. This paper presents life cycle extension plans of FFP shutoff valve by configuration improvements of shutoff valve and FFP hydraulic motor.

• International Journal of Aeronautical and Space Sciences
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• v.3 no.2
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• pp.31-39
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• 2002

In this paper, KOMPSAT-2 on-board fault and ground recovery management design is addressesed in terms of hardware and software components which provide failure detection and spacecraft safing for anomalies which threaten spacecraft survival. It also includes ground real time up-commanding operation to recover the system safely. KOMPSAT-2 spacecraft fault and recovery management is designed such that the subsequent system configuration due to system initialization is initiated and controlled by processors. This paper will show that KOMPSAT-2 has a new design feature of CPU SEU mitigation for the possible upsets in the processor CPUs as a part of on-board fault management design. Recovery management of processor switching has two different ways: gang switching and individual switching. This paper will show that the difficulties of using multiple-processor system can be managed by proper design implementation and flight operation.

• Journal of the Korean Institute of Intelligent Systems
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• v.21 no.3
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• pp.323-328
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• 2011

In real system application, the 3-D obstacle avoidance system for the autonomous control of the underwater flight vehicle (UFV) operates with the following problems: the sonar offers the range/bearing information of obstacles in a local detection area, it requires the system that has reduced acoustic noise and power consumption in terms of the autonomous underwater vehicle (AUV), it has the UFV operation constraints such as maximum pitch and depth, and it requires an easy design procedure in terms of its structures and parameters. To solve these problems, an intelligent 3-D obstacle avoidance algorithm using the evolution strategy (ES) and the fuzzy logic controller (FLC), is proposed. To verify the performance of the proposed algorithm, the 3-D obstacle avoidance of UFV is performed. Simulation results show that the proposed algorithm effectively solves the problems in the real system application.

• Journal of Advanced Navigation Technology
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• v.27 no.5
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• pp.534-539
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• 2023

Currently, in Korea, to obtain a jet type rating, you must receive training on a small business jet model. The reason is because of the law in the Aviation Safety Act Enforcement Rules 『Appendix 4』 that states, "You must receive at least 2 hours of flight training." In the end, it is acquiring type rating as a small business jet aircraft with relatively low operating costs. The qualifications acquired in this way are different from those for aircraft operated by airlines. However, if you have an initial jet type rating, you can acquire an airline aircraft qualification just by training on a simulator, so airlines want you to have at least a small-jet type rating. However, in the United States and Australia, there is a system in place to acquire initial jet type rating through simulator training without actual flight training.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.6
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• pp.16-27
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• 2020

For the operation of the scramjet engine in the wide flight range, the design of the inlet must show stable performance in various flight conditions. In this study, the design methods of a 2D fixed inlet for stable performance in wide flight ranges of Mach number 4 to 6 and angle -6° to 6°, is performed. After proposing the design method and design focus, performance prediction and analysis were performed by various initial compression angles and design Mach numbers, which are essential design factors in total pressure recovery and inlet capture area ratio in the wide flight range. Based on the analysis results, we present the selection criteria for the two main design elements to represent stable performance in the wide flight range.

• The Journal of Korea Institute of Information, Electronics, and Communication Technology
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• v.12 no.6
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• pp.666-671
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• 2019

The flight controller(FC) used in small-sized drone was developed as simple structure does not perform complex operations because it uses different MCU with large-sized drone. Also, the balance control of small-sized drone should be simpler than Kalman filter using complex filter and the method using Complementary filter has relatively more operations. So, the method to realize the balance control on small-sized drone effectively using two-track control operating as proper method for above is suggested in this research. This method is a system maintaining effective balance with simple structure and less operations by operating adaptively for the unbalance of the drone with the acceleration sensor with the advantage which performing accurate correction by data processing for long term change and gyroscope sensor maintaining the balance of the drone by data processing for short term change. It is confirmed that stable operation was performed mostly based on the test result for repeatable test more than 100 times using two-track control and it maintained normal state operation more than 98% excluding the difficulty of maintaining normal operation when meets sudden and rapid wind yet.

• Journal of Advanced Navigation Technology
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• v.27 no.5
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• pp.528-533
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• 2023

Airlines tried to introduce training programs in connection with practical work in order to provide more effective education and training. To this end, airlines have been conducting evidence-based training(EBT) to strengthen the practical capabilities of aviation personnel and enhance safety culture. Airlines can systematically evaluate the capabilities and practical capabilities of aviation personnel by analyzing operational data and case studies for effective EBT model development. In addition, EBT models can be constructed by applying technical methods such as crew resource management (CRM) and a holistic approach that includes human factors. Due to the introduction of EBT, airlines will establish diagnostic and feedback systems for pilots' practical work, provide personalized education, and establish an education and training system that verifies the effectiveness of education through educational outcomes.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.25 no.3
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• pp.61-67
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• 2017

The Nose Landing Gear(NLG) of Rotary Wing Aircraft is an essential equipment in Landing System for pilot to perform a flight mission. It supports the fuselage at ground and absorbs the impact from the ground when landing, thereby, these functions sustain operational capability for pilot and crew. However, the A aircraft caused stick-slip behavior when it was stationed on the ground. Therefore, this paper summarizes pilot comment in operation which are classified by cause of occurrence and the troubleshooting process about each comment. It also describes design improvements which was derived from troubleshooting and suggests verification results of flight test.

• Journal of Aerospace System Engineering
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• v.13 no.6
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• pp.36-42
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• 2019

This research illustrates how the simulation environment for operating the simultaneous man/unmanned aerial vehicle teaming is constructed. X-Plane program, HILS for the ducted fan aircraft (unmanned) and CTLS (manned aircraft) with communication devices are interfaced to simulate the basic co-operational flight. The X-plane and HILS can allow operators to experience the maned and unmanned aircraft operation in the airspace on the ground in turn they can perform various simulated missions in advance before the actual flight. For the test purpose, the data link between man/unmanned aircraft and ground control station is examined using C Band and UHF radio channels by the manned aircraft.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.3
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• pp.86-92
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• 2005

Synthetic Aperture Radar is an active sensor utilizing the microwaves in order to get the requested high resolution imageries day or night regardless of the weather conditions. In this paper, the architecture of a real-time system controller for the airborne small SAR system, KOrea Miniature SAR which was developed by Agency for Defense Development is proposed considering the embedded real-time environment. The main purpose of the system controller is to control the internal and the rest of subsystem within SAR system in real-time. The main characteristics of the proposed system controller were implemented using the real-time operating system and the distributed hardware architecture for the small, low weight and real-time operation. The system controller performance and real-time operation were verified and confirmed by the demo flight with the KT-1 airplane.