• Journal of the Korea Institute of Military Science and Technology
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• v.26 no.2
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• pp.171-178
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• 2023

PCM data is result of air-vehicle flight test, this data is distributed for each engineers to analyze its condition. Since line-of-sight between the air-vehicle and the ground receiver cannot always be secured, remote PCM data recording system was claimed to be required. In this paper multi-function PCM data recorder has been described. This PCM data recorder was intended to place on inside of flight object. It can record about two hours in 32 GB SD card with maximum 7 Mbps data rate. RS-422/485 and RJ-45 interface enhanced accessibility for users. 5 V and 1 A power consumption and 19.5 mm × 152.5 mm × 102.3 mm allow to connect with mobile PCM devices. It acquired more than 190-minutes data in 12-times flight test. Also, it achieved military standard environmental test MIL-STD-810G to prove its stability and solidness.

• Proceedings of the KSRS Conference
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• 2005.10a
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• pp.557-560
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• 2005

The Korea Multi-Purpose SATellite-2 (KOMPSAT -2) will be launched into a circular sun synchronous orbit in Dec. 2005. For the mission operation of the KOMPSAT-2 satellite, KARl Ground Station (KGS) consists of the Mission Control Elements (MCE), Image Reception & Processing Elements (IRPE) and the overseas stations. For the oversea stations, the Kongsberg Satellite Services (KSAT) is the prime supplier of support service. KSAT has the capability to provide Tracking Telemetry and Commanding (TT&C) nominal, contingency and anomaly support for every single orbit for most polar orbiting satellites. Also KSAT provides nodal service through the network management functionality for all oversea ground stations. This paper describes the oversea stations and the support for Launch and nominal TT&C services for KOMPSAT-2 and the operation plan for KOMPSAT-2.

• Journal of Institute of Control, Robotics and Systems
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• v.9 no.12
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• pp.1042-1047
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• 2003

The goal of this research is to implement a PC-based remote control system of ion implanter using Visual Basic programming. Presently, skilled process engineers are required to regularly setup and adjust implanter parameters. Any reduction in the number of production hours devoted to ion beam implanter setup or recalibration after a species change would represent substantial improvements in both manpower and equipment utilization. An optical communication system for the remote control and telemetry in the operation of the 50kev potential was designed and constructed. This system enables continuous and safe operation of the ion implanter and can be the basis for the automation. The isolation characteristics of optical fiber were 10kV/cm, and performance tests of the system under the intense noise environment during the implanter operations showed satisfactory results. This system is designed to completely replace the existing human-machine interface with many new functions. This paper describes the important components of the system including system architecture and software development. It is expected that this system can be used for the communication and control purpose in the high noise environments such as the operation of the MeV energy implanter or other high power, high noise systems.

• The Journal of the Korea institute of electronic communication sciences
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• v.13 no.3
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• pp.517-524
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• 2018

This Paper presents the real time things control method through Web browser that has no limited by time and place. To design and realize the system that not only makes it possible to communicate with other protocols but also reinforces the advantages of each protocol, the real time communication environment, based on the WebSocket technology of HTML5 whose international standardization has recently been completed, is realized. Also, the message communication environment in the low electricity and limited communication environment is realized using MQTT(Message Queue Telemetry Transport) protocol which is in the spotlight as the optimum protocol in the IoT environment. And by designing intuitive and simple hardware and realizing the responsive web interface which is not limited by the user's contact devices, the interactive system in which the user receives real time data from the hardware and reversely the user controls the things is designed and realized.

• Proceedings of the KSRS Conference
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• 2005.10a
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• pp.493-496
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• 2005

The PMU (Payload Management Unit) in MSC (Multi-Spectral Camera) is the main subsystem for the management, control and power supply of the MSC payload operation. The PMU shall handle the communication with the BUS (Spacecraft) OBC (On Board Computer) for the command, the telemetry and the communications with the various MSC units. The PMU will perform that distributes power to the various MSC units, collects the telemetry reports from MSC units, performs thermal control of the EOS (Electro-Optical Subsystem), performs the NUC (Non-Uniformity Correction) function of the raw imagery data, and rearranges the pixel data and output it to the DCSU (Data Compression and Storage Unit). The BUS provides high voltage to the MSC. The PMU is connected to primary and redundant BUS power and distributes the high unregulated primary voltages for all MSC sub-units. The PSM (Power Supply Module) is an assembly in the PMU implements the interface between several channels on the input. The bus switches are used to prevent a single point system failure. Such a failure could need the PSS (Power Supply System) requirement to combine the two PSM boards' bus outputs in a wired-OR configuration. In such a configuration if one of the boards' output gets shorted to ground then the entire bus could fail thereby causing the entire MSC to fail. To prevent such a short from pulling down the system, the switch could be opened and disconnect the short from the bus. This switch operation is controlled by the BUS.

• Aerospace Engineering and Technology
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• v.11 no.1
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• pp.49-56
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• 2012

The flight software monitors the status of the satellite and performs attitude control and its own mission. Due to the operating environments and its uniqueness, the high level of reliability is required for the flight software. To this end, a variety of activities to meet the given requirements and improve the safety and reliability are made during the development of flight software. A variety of development environments should be provided to support execution of flight software on hardware or satellite simulator and dynamic verification of flight software through command/telemetry interface. The satellite flight software team has been developing the IVF to be applied to various satellite projects more effectively and to improve the reliability of flight software. In this paper, the design and configuration method of IVF for the effective verification of flight software is introduced.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.81-81
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• 2004

위성체와 발사체 사이에는 임무설계접속, 기계접속, 전기접속, 환경접속 등 다양한 접속이 존재한다. 본 논문은 2004년 1월 수행된 발사체 전기접속 시험을 통하여 검증한 다목적 실용위성 2호와 ROCKOT 발사체간 전기접속과 발사장에서의 위성체, 발사체, 지상지원 장비 및 임무통제센터를 포함한 주변 지원시설간 접속을 기술하였다. 본 시험의 목적은 KIA(KOMPSAT-2 Interface Assembly)를 포함한 발사체 TMS(Telemetry Measure ment System)와 다목적실용위성 2호 사이의 호환성을 검증하고 LV TMS와 위성체 LSTS (Launch Support ＆ Test Set)의 하드웨어 및 소프트웨어의 정확한 동작을 검증하는 것이다. (중략)

• ETRI Journal
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• v.27 no.2
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• pp.140-152
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• 2005

In this paper, we present design features, implementation, and validation of a satellite simulator subsystem for the Korea Multi-Purpose Satellite-2 (KOMPSAT-2). The satellite simulator subsystem is implemented on a personal computer to minimize costs and trouble on embedding onboard flight software into the simulator. An object-oriented design methodology is employed to maximize software reusability. Also, instead of a high-cost commercial database, XML is used for the manipulation of spacecraft characteristics data, telecommand, telemetry, and simulation data. The KOMPSAT-2 satellite simulator subsystem is validated by various simulations for autonomous onboard launch and early orbit phase operations, anomaly operation, and science fine mode operation. It is also officially verified by successfully passing various tests such as the satellite simulator subsystem test, mission control element system integration test, interface test, site installation test, and acceptance test.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2003.11a
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• pp.170-176
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• 2003

The pantograph for Korean High Speed Train was developed and had been evaluating by through "G7- R＆D for home grown high speed train technology". In this study, a relation in mechanical aspect between the train running speed and the current collecting performance of the pantograph is conducted.'for this study, a measuring system for current collecting performance and mechanical characteristics is developed and installed on the prototype Korean High Speed Train, and measurement is conducted while the train runs on the test track. The measuring system is composed of video monitoring system and telemetry & data processing unit. It monitors whether the hazard behavior in the pantograph is occurs or not, and measures acceleration and vertical contact force between the pan head and catenary. Through this study, evaluation of a mechanical vibration characteristics and trend of the pantograph and a interface performance of pantograph - catenary up to 200㎞/h train speed are facilitated.

• Proceedings of the KSR Conference
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• 2003.05a
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• pp.574-579
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• 2003

In this study, a measuring system for performance of pantograph was developed. The measuring system was installed on the prototype high speed train and measurement has been conducted during running on the test track. The measuring system is composed of video monitoring system and telemetry & data processing system. It can monitor the hazard behavior of pantograph and measure acceleration and vertical force of the pan head. Owing to the measuring system, performance of pantograph and safety of interface system of pantograph and catenary is evaluated.