• Journal of the Korea Institute of Military Science and Technology
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• v.10 no.1
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• pp.22-32
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• 2007

This paper describes a study of a helicopter database for the sizing stage of a preliminary design process. The database includes specifications and performance parameters for more than 150 conventional single rotor helicopters currently in market. Design parameters, including configuration and weight parameters, have been analyzed and trend curve equations(regression equations) are derived using the regression analysis method. Finally, the applicability of this research result was verified whether the method is reliable for being adopted as a useful design tool in the early stage of a helicopter design process.

• Journal of the Korea Institute of Military Science and Technology
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• v.17 no.4
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• pp.448-455
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• 2014

Virtual Fire Control System(VFCS) in attack helicopter is developed. VFCS is comprised of multifunction display, store management computer, mission computer, target acquisition and designation system, mission planning system, weapon simulator and flight simulator. Weapon engagement process under the operational environment of helicopter was considered by using the VFCS. We considered hellfire missile, tow missile, unguided rocket and turret gun. The results of this study will be utilized efficiently on integrated fire control system SIL(System Integration Lab.) in attack helicopter.

• Journal of Korean Society of Industrial and Systems Engineering
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• v.43 no.4
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• pp.150-160
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• 2020

In this paper, we introduce a pilot's scheduling model which is able to maintain and balance their capabilities for each relevant skill level in military helicopter squadron. Flight scheduler has to consider many factors related pilot's flight information and spends a lot of times and efforts for flight planning without scientific process depending on his/her own capability and experience. This model reflected overall characteristics that include pilot's progression by basis monthly and cumulative flight hours, operational recent flight data and quickly find out a pinpoint areas of concern with respect to their mission subjects etc. There also include essential several constraints, such as personnel qualifications, and Army helicopter training policy's constraints such as regulations and guidelines. We presented binary Integer Programming (IP) mathematical formulation for optimization and demonstrated its effectiveness by comparisons of real schedule versus model's solution to several cases experimental scenarios and greedy random simulation model. The model made the schedule in less than 30 minutes, including the data preprocessing process, and the results of the allocation were more equal than the actual one. This makes it possible to reduce the workload of the scheduler and effectively manages the pilot's skills. We expect to set up and improve better flight planning and combat readiness in Korea Army aviation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.9
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• pp.734-739
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• 2013

Representative crashworthiness requirement documents for military helicopter are MIL-STD-1290 and the Aircraft Crash Survival Design Guide(ACSDG) which were lastly revised in the 1980's. Taking analysis results of diverse U.S. Army helicopter mishaps into account, we can say that adequate guidelines do not exist to ensure crashworthiness of new generation aircraft. In this paper, U.S. Army helicopter mishap analysis conducted by U.S. Army Research, Development and Engineering Command(RDECOM) is readjusted to review the basis of new crashworthiness design criteria for military helicopter, in other words, Full Spectrum Crashworthiness Criteria(FSCC). This analysis effort is a part of FSC development. This effort was to research and quantify the dynamics of military aircraft crashes to be used as the quantitative basis for new design criteria.

• Journal of the Korea Institute of Military Science and Technology
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• v.12 no.6
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• pp.750-759
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• 2009

FLIR(Forward Looking Infrared) geo-pointing is a function that helps pilots to see a target within the field of view under all coordinates and attitudes of helicopter. Geo-pointing controls FLIR LOS(line of sight) toward known target coordinates by using azimuth and elevation angles calculated from several information such as helicopter coordinates and attitudes, a FLIR position from a GPS antenna, and target coordinates. Geo-pointing performance has been tested and evaluated on the ground to save flight test costs and ensure flight safety. In this paper, design and implementation of a geo-pointing system is described with the results of performance test conducted on the ground test system.

• Journal of the Korea Institute of Military Science and Technology
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• v.16 no.3
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• pp.268-276
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• 2013

The objective of this paper is to give a general understanding for the development flight test of Korean Utility Helicopter(KUH). This paper contains the contents of detailed flight test plan, the type of flight test, an introduction to main flight test area, and the overview of flight test results. At the beginning, more than 8,500 test points were identified for airworthiness certification to show the compliance for the KUH development requirements. However, the number of flight test points were optimized to 7,800 at the end. To accomplish the test objectives, about 860 flight test sorties had been performed, and more than 1,000 test sorties were consumed for trouble shooting. This paper also describes some major issues faced during development flight test phase.

• Journal of the Korea Institute of Military Science and Technology
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• v.8 no.3 s.22
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• pp.33-41
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• 2005

This paper describes the conceptual design of medium size helicopter rotor system. Based on assumed design requirements, trade-off study for rotor configuration has been conducted in terms of rotor tip speed, disk loading, blade area, solidity, etc for estimated primary mission gross weight. For the main rotor, four-blade and five-blade rotors are studied with the conventional tail rotor. The performance analysis for baseline configuration is conducted using a helicopter performance analysis program. The analysis shows design results satisfy the design requirements.

• Journal of the Korea Institute of Military Science and Technology
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• v.15 no.6
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• pp.746-753
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• 2012

ROK military helicopters are frequently exposed to the hazard situations due to the characteristic of operation. Especially, helicopter accident may lead to critical damage of human and structure. Accordingly, pilots have to train the autorotation procedures and learn the skill to prevent hard landing. In this paper, the behavior of skid gear subject to the helicopter autorotation was conducted by using numerical method. The computer simulation approach by using finite element method was employed to accomplish this goal. Additionally, the behavior of skid gear was evaluated for the different landing conditions. In conclusion, the maximum stress concentration was occurred at the attached area of skid cross-tube to the fuselage. Also, it was revealed that the most proper attitude was level landing to prevent hard landing.

• Journal of the Korea Institute of Military Science and Technology
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• v.7 no.4 s.19
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• pp.53-60
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• 2004

In this paper, the radar antenna of navigation radar on helicopter was suggested to Ka-band lens antenna. It is type of the streamlined convex lens to reduce the air resistivity when helicopter was navigated. Although aperture area is smaller than the standard antenna just like horns, the gain is higher and beamwidth is smaller than standard horns. We made the lens by using maximum flare angle of the horn and dielectric constant of the lens. As a result, when aperture diameter was 280mm and focal length was 145mm, the return loss -21.25dB, the gain was 32.2dBi, E and H beamwidth was $1.8^{\circ}$(E-plane), $1.4^{\circ}$(H-plane), nearly $1.5^{\circ}$, and side-lobe level was -18.4 dB(E-plane), -19.5dB(H-plane) lower were presented. So this suggested type can be used for the radar antenna of navigation radar on helicopter, and it will possible just a little some sidelobe suppression by using the choked horn as a feeder horn.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2003.05a
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• pp.325-329
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• 2003

Nowadays many peoples are using helicopter in various fields, not only military use but also common people applications such as air-measurement, photography, transportation of goods and persons, saving life and fire fighting etc. And it will be expected more popular than now. Most important part of helicopter to increasing performance and to reducing noise is rotor hub-system. Hub system consists of rotor-blade and rotor-hub. We participate to develop next-generation rotor hub system with elastomeric bearing, part of rotor hub. In this paper we introduce about the role and shape of elastomeric bearing in next-generation helicopter hub system. Then we study about bearing-material requirements and measuring methods. Finally we represent some experimental results.