• 한국전산유체공학회:학술대회논문집
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• 2010.05a
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• pp.464-467
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• 2010

Ice accretion on aircraft surface in icing condition induces external shape changes that may result in a hazard factor for aircraft safety. In case of aircraft main wing with high lift equipment, ice accretion is observed around leading edge and flap. During the design phase, location of ice accretion and associated aerodynamic characteristics must be investigated. In this study, icing effects on aerodynamic characteristics of the main wing section of KC-100 aircraft are investigated using an Eulerian-based FENSAP-ICE code in various icing conditions.

• International Journal of Aerospace System Engineering
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• v.2 no.2
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• pp.87-91
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• 2015

KT-1P for the Peru Air Force will be used as a utility aircraft with upgraded avionics equipment and arming capability based on KT-1 and KA-1. KT-1P should be shown for compatibility of new store loading configurations loaded with dispenser, bomb, and rocket based on aircraft-store compatibility test and evaluation procedures before KT-1P is operated as a light attack aircraft. The weapon system ground test for installation and flight test for envelope expansion including store separation are described in this paper, which was performed referring 'seek eagle program' under MIL-HDBK-1763 and MIL-HDBK-244A.

• Journal of Ocean Engineering and Technology
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• v.23 no.2
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• pp.92-97
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• 2009

In order to export aircraft components or substructures, it is necessary to get a certification from the main company for the components or an airworthiness certification from the FAA. In Korea, those processes are performed by a small number of private companies for aircraft components. However, airworthiness certification has never been done in the company. To export an assembled aircraft, whether small or large, it is obligatory to get a certification for the aircraft being exported. Currently, the Korean government is trying to get BASA agreement in a few years. For a mid-size company, it is easier to get the NADCAP audit process for the supply of aircraft components to the main company. In this paper, the overall process of aircraft certification is discussed and airworthiness certification is treated for export aircraft. Moreover, the NADCAP audit process is described in detail by introducing example parts made of composite material. This detailed process would be very helpful to a small or mid-size company that wants to develop and deliver aircraft components to foreign companies.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.16 no.2
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• pp.288-295
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• 2012

Recently personal income level is rising. So, many people use the leisure lightweight aircraft and the population which enjoys a leisure is increasing. But as the leisure lightweight aircraft compares in the civil aircraft and the military aircraft, and it has a low price. So the equipment which it is loaded in the lightweight aircraft is not equipped. In this paper, we develop the air navigation for lightweight aircraft using the smart phone(iPhone, Android phone, Window mobile, BADA phone etc.) and the smart pad(iPad, Galaxy Tab etc.).

• Journal of the Korea Institute of Information and Communication Engineering
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• v.22 no.9
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• pp.1220-1227
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• 2018

Avionics electronic equipment refers to the electronic equipment installed on an aircraft. Failure of avionics equipment can have a significant impact on aircraft operations as well as threaten the safety of pilots and passengers. Therefore, avionics electronic equipment is required to have higher reliability and safety than electronic equipment used for other purposes. Avionics equipment must consider various component selection and system design to meet reliability and safety-related requirements from the initial design stage. In this paper, we describe safety, reliability performance analysis method of avionics equipment, and introduce various design improvement methods that can be performed to meet safety requirement performance. Finally, the safety performance of the improved avionics equipment was reanalyzed and compared with the value before the improvement, the validity of the proposed design change was verified.

• Journal of Aerospace System Engineering
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• v.17 no.1
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• pp.97-105
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• 2023

For aviation sensor pod, structural integrity should be verified through static structural tests for flight loads induced in various maneuvering conditions of the aircraft. For this, it is necessary to develop a test system for full-scale static load test of sensor pod. Based on test requirements, this paper introduced a test system configuration of the static test and the development of test structure frame, restraints equipment, loading equipment, control, and measurement equipment. In addition, methods and procedures for verifying the developed test system were explained. In conclusion, the static load test and data acquisition were successfully performed. Reliability of the test equipment was also verified in the process.

• Journal of Advanced Navigation Technology
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• v.21 no.5
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• pp.459-465
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• 2017

In this paper, we introduce the design consideration of the lightning induced transient protection circuit for the indirect lightning strike on the avionics equipment. The lightning induced surge voltage, which is so-called as indirect effects of lightning, may cause a functional failure or physical damage to the electrical and electronic equipment of aircraft. In order to protect the electrical and electronic equipment of aircraft from the indirect effects of lightning, we should analyze the effect of lightning strike on aircraft and consider applying protection design for each avionics device. However, lightning induced transient protection circuits can have unintended consequences because parasitic inductance elements are exist in PCB and TVS diodes. In this paper, we introduce the design method of the protection circuit considering the parasitic inductance of the protection circuit. In addition, we show the result of verification test performed to validate the protection circuits for indirect effects of lightning.

• The Journal of the Institute of Internet, Broadcasting and Communication
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• v.23 no.2
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• pp.139-147
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• 2023

The compact tracking radar system is a pulsed radar tracking system that searches, detects, and tracks targets in real time against aircraft targets with a small RCS(Radar Cross Section) maneuvering at high speed. This paper describes the development of comprehensive performance test equipment to verify the performance of the radar system in a anechoic chamber environment. Describes the design and manufacture of comprehensive performance test equipment to meet requirements, including the generation of simulated target signals to simulate aircraft target signals to verify performance in the laboratory environment of radar systems. It also describes a GUI(Graphic User Interface) program to check performance through a test in conjunction with the tracking radar system. Verify the comprehensive performance test equipment implemented through the performance test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.8
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• pp.639-646
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• 2017

In this paper, a new load monitoring system for military aircraft is introduced. This system consists of sensors, an onboard device and an ground analysis equipment. The sensors and onboard device are mounted on the aircraft and the ground analysis equipment is operated on the ground. Through this system, structural static load can be estimated with flight parameters and structural responses can be measured by sensors due to static load, dynamic load and unexpected events. Especially, optical fiber sensors with mutiplexing capability are utilized. The onboard device was specially designed for complying the requirements of relevant military specifications and was verified through a series of the environment tests. This system was used and evaluated through ground structural tests before flight tests. In the near future, this system will be applied to military aircraft as a structural load monitoring system after flight test evaluation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.9
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• pp.801-811
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• 2021

Lightning can deliver large amounts of energy to the aircraft in a short period of time, resulting in catastrophic consequence. In particular, lightning strikes accompanied by high temperature heat and current can damage aircraft surface and internal electronic equipment, seriously affecting flight safety. Lightning experiments to analyze this effect use a Component A waveform with a maximum current of 200 kA as specified in SAE ARP 5412B. However, the actual lightning occurs mostly below 35kA and lightning indirect tests are conducted by reducing waveforms to prevent damage to internal electronic equipment. In this study, we examine previous methods to plot the Component A reduced waveform and identify their limitations. We then propose a new method to plot the reduced waveform based on adjusting the correction factor of the aircraft lightning Component A waveform. Finally, the electromagnetic analysis software EMA3D was used to compare the internal induced current size reduction ratio of the internal cable harness of the EC-155B helicopter.