• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.599-602
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• 2011

A propulsion controller for one-time flight vehicles should be designed robustly so that it can complete its missions even in case sensor failures. These vehicles improve their fault tolerance by back-up sensors prepared for the failure of major sensors, which raises the total cost. This paper presents the NARX model which substitutes vehicles' velocity sensors, and detects failure of sensor signals by using model based fault detection. The designed NARX model and fault detection algorithm were optimized and installed in TI's TMS320F2812 so that they were linked to HILS instruments in real-time. The designed propulsion controller made the vehicle to have better fault tolerance with fewer sensors and to complete its missions under a lot of complicated failure situations. The controller's applicability was finally confirmed by tests under the HILS environment.

• Journal of Astronomy and Space Sciences
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• v.15 no.2
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• pp.449-458
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• 1998

The Korea Muliti-Purpose Satellite(KOMPSAT) uses a sun-synchronous orbit with an altitude 685km as mission orbit and undergoes earth eclipses and infrequently lunar eclipses. Lunar eclipses occur when the moon is located between the sun and the satellite and blocks partially or fully the sunlight. The eclipse causes the satellite to increase battery discharge times and affects satellite lifetime and mission operation. The KOMPSAT lunar eclipses can cause additional effects to energy balance and battery disc of the KOMPSAT lunar eclipse for 3 year mission lifetime. Also mission planning scenario is presented for lunar eclipses at the KOMPSAT Grouns Station(KGS).

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.24 no.2
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• pp.198-206
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• 2013

This paper presents the improvement of tracking performance using fuzzy inference system based task prioritizations for multi-function radars. The presented technique calculates elemental priorities using track information of a target and obtain the total priority from fuzzy inference system of each fuzzy set's membership function. In this paper, we proposed the task prioritization algorithms based on fuzzy inference system, and evaluated the tracking performance on multi-function radar scenario using it. As a result, we confirmed that excellent performance could be achieved when using the proposed algorithm.

• Journal of Satellite, Information and Communications
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• v.1 no.2
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• pp.16-24
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• 2006

As a multi-mission GEO satellite, COMS system is being developed jointly by KARI, ETRI, KORDI, KMA, and industries from both abroad and domestic. EADS ASRTIUM is the prime contractor for manufacturing the COMS. ETRI is developing the COMS Ka-band payload and SGCS with the fund from MIC. COMS Satellite Ground Control System (SGCS) will be the only system for monitor and control of the satellite in orbit. In order to fulfill the mission operations of the three payloads and spacecraft bus, COMS SGCS performs telemetry reception and processing, satellite tracking and ranging, command generation and transmission, satellite mission planning, flight dynamics operations, and satellite simulation, By the proper functional allocations, COMS SGCS is divided into five subsystems such as TTC, ROS, MPS, FDS, and CSS. In this paper, functional design of the COMS SGCS is described as five subsystems and the interfaces among the subsystems.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.4
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• pp.344-350
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• 2014

Multi Function Display(MFD) of Korean Utility Helicopter(KUH) is the component of mission management/display control system and displays image information(navigation, flight, survivability, digital map, maintenance) acquired from Mission Computer(MC) while the aircraft is operated. It is an essential equipment for pilots to perform flight mission and it has functions of display scene control, data display, built in test(BIT) and brightness control. In this paper, it is analyzed the cause of abnormal display(flickering) on MFD and summarized the design changes to solve the defect. It is also described system safety analysis and suggested verification results of flight/ground test.

• The Journal of the Korea institute of electronic communication sciences
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• v.17 no.3
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• pp.433-440
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• 2022

High Altitude Long Endurance(HALE) solar powered UAV is the vehicle that flies for a long time as solar power energy sources. It can be used to replace satellites or provide continuous service because it can perform long-term missions at high altitudes. Due to the property of the mission, it is very important for HALE solar powered UAV to have maximum flight time. It is required for mission performance to fly at high altitudes continuously except a return for temporary maintenance. Therefore mission availability time analysis is a critical factor in the commercialization of HALE solar powered UAV. In this paper, we presented an analytic model and logic for available time analysis based on the design parameters of HALE solar powered UAV. This model can be used to analyze the possibility of applying UAV according to the UAV's mission in concept design before the UAV detail design stage.

• The Journal of the Convergence on Culture Technology
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• v.10 no.4
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• pp.589-594
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• 2024

In this paper, we introduce the results of the Sounding Rocket LTE communication test using the LTE-Cat.M1 module. The developed LTE data transmission/reception system consists of Mission-Mounted Equipment(Payload) and Ground Observation Equipment(GOE), and the delay rate was secured based on the time between data measured when received from the GOE by constantly transmitting data from the Payload at a speed of 10 Hz. In order to increase the accuracy of the actual flight test, ground network delay rate tests, hardware internal delay rate tests, and ground tests were performed. As a result of the flight test, it was confirmed that the handover failed in the upward phase and the communication was lost for 13 seconds, and then the parachute was deployed and the communication was reconnected in a situation with a constant positional displacement. LTE-Cat.M1 technology is expected to be utilized for descent phase observation missions or data backup during Sounding Rocket missions.

• Proceedings of the Korean Information Science Society Conference
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• 1998.10a
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• pp.42-44
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• 1998

위성 시스템은 전력 분배, 자세 제어, 열 제어 및 임무 수행에 필요한 탑재체 지원과지상과의 명령 수신 및 측정데이터의 수집을 위해서 프로세서를 내장하고 있다. 임무 수행 및 시스템의 복잡성 여부에 따라서 하나의 프로세서만을 탑재하기도 하지만 여러 개의 프로세서를 탑재하여 기능에 적합하게 분배하여 운용하기도 한다. 아리랑위성은 3개의 프로세서사 탑재되며, 크게 나누어 원격 측정 명령계, 자세 제어계 그리고 전력계에 기능을 담당하게 된다. 하나 이상의 프로세서를 탑재하게 되면 프로세서간의 동기화가 요구되며 프로세서간의 정보 전달을 위해서 통신 채널이 필요하게 된다. 실제로 프로세서간의 동기화는 상호 통신에 있어서 기준 점을 제공하므로 매우 중요한 의미를 가진다. 본 논문에서는 아리랑위성의 동기화는 어떤 방식으로 설계되었으며, 어떻게 운영되는지에 대해 설명한다.

• Proceedings of the Korean Society of Machine Tool Engineers Conference
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• 1998.10a
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• pp.102-114
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• 1998

항공기 개발단계에서의 RAM(Reliability, Availability, Maintainability) 예측은 진행중인 설계개념이 RAM 개발 목표값을 달성할 수 있는지를 판단하여 이를 설계에 반영하기 위한 것이다. 본 연구에서 신뢰도 예측 모델은 항공기의 임무에 초점을 둔 임무신뢰도와 시스템신뢰도를 산출하고, 정비도 예측 모델은 군수지원분석자료(LSAR)와의 호환성을 유지할 수 있도록 하였으며, 가용도 예측 모델은 신뢰도와 정비도 자료를 활용한 운용가용도를 예측하는 데에 기준을 두었다. 본 연구는 기존의 RAM 예측이 각각 독립적으로 수행된 점을 보완하여 서로간의 상호관계를 반영한 통합 예측 모델을 개발하는 데에 초점을 두었으며, 실제적인 운용개념을 반영한 모델링으로서 항공기 개발단계에서 뿐만 아니라 실제 운용단계에서의 RAM 분석에 효과적이라 판단된다.

• Journal of the Korean Society of Systems Engineering
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• v.1 no.1
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• pp.67-72
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• 2005

Design and optimization study has been performed to obtain a supersonic air.launching mission for the nanosat launcher. Given mission is to launch 10kg payload to target orbit of $700km{\times}700km$. Additional design constraints are imposed by the mother plane. After the required velocity is obtained, the stag ing optimization is carried out. Serial analyses for the propulsion system and aerodynamics are performed then, the rocket trajectory optimization has been carried out. After several mission design and optimization iterations, the optimized mission which satisfies the mission target is obtained. Total weight of the three-staged air-launching rocket is 1231.4kg and the payload weight is 10 kg.