• Journal of the Korea Institute of Military Science and Technology
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• v.8 no.1 s.20
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• pp.49-55
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• 2005

Due to small and light mission payloads, subsystems and propulsion system, small sized UAVs come to be available for reconnaissance that have been performed by aircraft and huge UAVs. The objective of this study is to develop an efficient propulsion system for small reconnaissance UAVs. A glow engine was modified for an efficient and robust 4-stroke gasoline engine with carburetor, new electronic control unit and lubrication system. Engine modification technique and small engine performance test stand are capable of economical method for military UAVs.

• International Journal of Control, Automation, and Systems
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• v.5 no.3
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• pp.223-233
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• 2007

Crane payloads frequently swing with large amplitude motion that degrades safety and throughput. Open-loop methods have addressed this problem, but are not effective for disturbances. Closed-loop methods have also been used, but generally require the speed of the driving motors to be precisely controlled. This paper develops a feedback control method for controlling motors to cancel the measured payload oscillations by intelligently timing the ensuing on and off motor commands. The effectiveness of the oscillation suppression scheme is experimentally verified on an industrial bridge crane.

• Journal of the Korean Institute of Telematics and Electronics
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• v.26 no.4
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• pp.45-52
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• 1989

The size of links and actuators of robots tends to be overdesigned compared with their performance. It is recently reported that the balancing of a robot links simplifies its dynamics and eliminates the gravity terms. As a way of avoiding overdesign problem, an auto-balancing mechanism is proposed, which enables to satisfy varying balancing condition according to payloads. The performance of this auto-balancing mechanism is illustrated by the computer simulation evidences.

• Aerospace Engineering and Technology
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• v.1 no.1
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• pp.128-134
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• 2002

Outer surfaces of KSR-III are insulated to protect outer structure and inner payloads from the aerodynamic heating. The characteristics of insulation material (BMS 10-102), selected through careful tests and thermal analyses, are low heat transfer rate and low density. It is applied in a wet and continuous spray pattern for outer surfaces of KSR-III. In the present study, the honeycomb sandwich structure of nose fairing, which is one of the typical multi-layer structures of KSR-III, is thermally analyzed with insulation.

• Proceedings of the Korea Information Processing Society Conference
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• 2002.04b
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• pp.1289-1292
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• 2002

The number of connected computers in the Internet, which has reached a state in which its address space is becoming insufficient is exponentially increased. Also nowadays modern Laptops and Mobile terminal are being used more and more. As hewn, the number of available IPv4 address is limited and many organizations have limited budget to use the global address. So the way to overcome such problems is using private addresses in their networks. In addition, the use of private address makes the system more secure. Moreover, we have considered about supporting of the scalability of data forwarding processes of nodes in their network especially Mobile IP data communication. Thus, we propose the integration of MPLS and Mobile IP network. Also we propose the security services of a constrained LSP for the MPLS payloads.

• Proceedings of the KSRS Conference
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• 2002.10a
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• pp.243-248
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• 2002

The International Space Station (ISS) offers research opportunities for researchers in the field of remote sensing to conduct world-class activities in Low Earth Orbit. ISS provides the facilities to place and operate research experiments in a variety of fields, providing investigators opportunities to perform research and Earth observation. This paper is intended to give the reader an introduction to the ISS utilization and the capabilities for remote sensing research that are being implemented through the development of research facilities. We hope that reader will consider what kind of payloads could be developed to take advantage of facilities, and will consider proposing remote sensing research on the ISS.

• Proceedings of the KSRS Conference
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• 2003.11a
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• pp.280-282
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• 2003

The downlink data rates of the space-born payloads such as high-resolution optical cameras, synthetic aperture radars (SAR) and hyper-spectral sensors are being rapidly increased. For example, the image transmission rates of KOMPSAT-2 MSC(Multi-Spectral Camera) is 320Mbps even if on-board image compression scheme is used.[1] In the near future, the data rates are expected to be a level 500${\sim}$600Mbps because the required resolution will be higher and the swath width will be increased. This paper describes many techniques they enable 500Mbps data receiving and archiving system.

• Proceedings of the KSRS Conference
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• 2003.11a
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• pp.811-813
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• 2003

The Satellite Technology Research Centre (SaTReC), Korea Advanced Institute of Science and Technology (KAIST) has developed and is to launch STSAT-1 (Science and Technology Satellite - 1) on 27$^{th}$ September 2003. The data collection system (DCS) is the one of its payloads. The DCS is a data relay system used for transmission from ground-based sensors through satellite to receiving station. This is one of the important methods collecting global data from the remote locations. In this paper, the DCS on the STSAT-1 will be introduced and the development of the mobile terminal (MT) will be reported.

• Proceedings of the Optical Society of Korea Conference
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• 2000.08a
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• pp.36-37
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• 2000

정밀 지상관측 위성인 다목적실용위성 1호기에는 해상도 6.6 m인 전자광학카메라(EOC)가 탑재되어 현재 우수한 영상을 보내오고 있으며 2003년 발사예정인 2호기를 위하여 해상도 1 m의 Multispectral Camera(MSC)가 개발중이다. 미 TRW 사가 제작한 EOC 개발에 항우연의 연구진은 그 설계 및 시험의 각 단계별 검토와, 탑재, 위성전체 시험과 보정을 포함한 궤도운용 등의 수행과 함께, 개발기간 동안 현지에서 수행된 별도의 현장교육을 통하여 동급의 위성카메라를 실제 개발할 수 있는 설계기술을 이전받았다. 수차례 대구경 비구면 광학계 제작 경험을 더한 항우연은 MSC 공동개발선인 이스라엘 ELOP 사와 현재 그 설계를 진행하고 있다. (중략)

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2000.11a
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• pp.581-586
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• 2000

Explosively activated pyro-technic device is used to release exhausted rocket booster or payloads at prescribed times in the rocket's flight. It creates pyro-shock environment that rocket or payload components must survive. With the shock spectra acquired from flight data, laboratory test should be performed before flight to check whether all of component can sustain the shock environment. The pyro-shock environment simulation was created by the resonance fixture response to a projectile impact. Desired shock spectra is realized by adjusting the natural frequency of resonance plate and the velocity of impact hammer. This paper describes the development process of Pyro-shock testing machine, which is designed and tested by Korean engineers, to verify components of Korean Sounding Rocket(KSR-3) and the other Korean space vehicle. Both analytical and experimental techniques are introduced in this paper.