• Journal of Astronomy and Space Sciences
• /
• v.19 no.3
• /
• pp.215-224
• /
• 2002

This paper describes EGSE design for the small satellite such like KOMPSAT-2 satellite. Recent design trend of small satellite and EGSE is to take short development time and less cost. For this purpose, the design for KOMPSAT-2 satellite and EGSE are not much modified from KOMPSAT-1 heritage. It means that it is able to be accommodated the verified hardware and software modules used in KOMPSAT-1 satellite program if possible. The objective of EGSE is to provide hardware and software for efficient electrical testing of integrated KOMPSAT-2 satellite in three general categories. (1) Simulators for ground testing (e.g. solar-simulation power, earth scenes, horizons and sun sensor). (2) Ground station type satellite data acquisition and processing test sets. (3) Overall control of satellite using hardline datum. In KOMPSAT (KOrea Multi-Purpose SATellite) program, KOMPSAT-2 EGSE was developed to support satellite integration and test activities. The KOMPSAT-2 EGSE was designed in parallel with satellite design. Consequently, the KOMPSAT-2 EGSE was based on the KOMPSAT-1 heritage since the spacecraft design followed the heritage. The KOMPSAT-2 baseline was elaborated by taking advantage of experience from KOMPSAT-1 program. The EGSE of KOMPSAT-2 design concept is generic modular design with preference in part selection with commercial off-the-shelf which were proven from KOMPSAT-1 programs, flexible/user friendly operational environment (graphical interface preferred), minimized new design and self test capability.

• Journal of Satellite, Information and Communications
• /
• v.2 no.2
• /
• pp.36-40
• /
• 2007

EGSE is used to check out satellite payload during the development prior to launch. The EGSE represented in this paper is a test system for Ka band communication transponder of COMS. The EGSE consist of two subsystems as CTS subsystem and PCTS subsystem. Communication Test subsystem (CTS) performs satellite transponder RF performance testing, data analysis and trending. Most of transponder RF performances are automatically tested by the CTS subsystem. Power, Command & Telemetry subsystem (PCTS) monitor telemetry messages from the transponder and send tele-commands to satellite transponder for the configuration change. PCTS also provide simulated S/C power to the transponder during the ground validation testing. The EGSE test functions are verified by the transponder simulator testing and will be used for the flight model transponders testing.

• Proceedings of the KIEE Conference
• /
• 2007.10a
• /
• pp.269-270
• /
• 2007

The COMS(Communication, Ocean & Meteorological Satellite) is the geostationary satellite which will be performing three main objectives such as meteorological service, ocean monitoring and Ka-band satellite communications. This paper reports on the hardware architecture of the system electrical ground support equipment(EGSE) for the COMS satellite. EGSE is used to check out satellite during the development prior to lunch. The EGSE represented in this paper consist of two parts. First, I will deal with the OCOE(Overall Check Out Equipment) system which controls and operates the all EGSE system. In second part, we will introduce the SCOE(Specific Check Out Equipment) systems which can test the specific subsystems of the COMS satellite.

• The Journal of the Korea institute of electronic communication sciences
• /
• v.13 no.3
• /
• pp.503-508
• /
• 2018

This study describes the design and implementation of EGSE for Digital Satellite Communication. The EGSE is a equipment that evaluates digital satellite communication and requires precise and accurate measurement. EGSE consists of a PLDIU and IIU(Instrument Interface Unit), Up/Down converter for SHF band, Modems to verify the Digital Satellite Communication. The EGSE was used for performance verification and space environment test such as thermal vacuum after developing digital satellite communication.

• The Journal of the Korea institute of electronic communication sciences
• /
• v.17 no.1
• /
• pp.147-152
• /
• 2022

This study describes the design and implementation of EGSE for Dehop/Rehop Transponder. The EGSE is a equipment that evaluates Dehop/Rehop Transponder and requires precise and accurate measurement. EGSE consists of a PLDIU and IIU(Instrument Interface Unit), Up/Down converter for L band, Modems to verify the Dehop/Rehop Transponder. The EGSE was used for performance verification and space environment test such as thermal vacuum after developing Dehop/Rehop Transponder.

• Proceedings of the IEEK Conference
• /
• 2002.06a
• /
• pp.235-238
• /
• 2002

In this paper we describe the design and implementation of Electrical Ground Support Equipment(EGSE) for the CBS transponder testing. The main task of EGSE is to check out satellite systems, at system or subsystem level, during integration and validation phases of their life-cycle. Through a combination of hardware and software elements, EGSE supports manual, semi-automatic and fully automated testing. Automation is achieved by offering users simple, yet powerful means to write their own test application programs (test sequences) in high-level, test-oriented language and to run them in a strict real-time environment. The core of this environment is a user-configurable real-time database, containing all the information needed to calibrate acquired data, check them against predefined thresholds, automatically react to out-of-range conditions, display data using animated graphics or synoptic windows, and so on.

• Korean Journal of Remote Sensing
• /
• v.33 no.5_1
• /
• pp.521-535
• /
• 2017

Since satellites, including payloads, are limited in how they can respond to problems after launch, the functionality of the satellite should be verified sufficiently by EGSE (Electrical Ground Support Equipment). In addition, considering the trend that the development period of the satellite is shortening and the development of the EGSE must precede the development of the engineering model of electronic equipment, early securing of EGSE is necessary to comply with the development schedule of the entire satellite. In this paper, we propose a method for early securing highly reliable EGSE by devising a scenario based operating payload packet analyzer, which is a part of the EGSE, through functional modularization and external parameterization, and show the result of applying the implemented payload packet analyzer to real satellite program.

• Current Industrial and Technological Trends in Aerospace
• /
• v.6 no.1
• /
• pp.56-64
• /
• 2008

Although the EGSE (Electrical Ground Support Equipment) and MCS (Mission Control System) have many similar or even identical functions, the EGSE used for assembly, integration and validation phase and the MCS for the mission operations phase are normally developed separately and used by different groups of engineers. However, the common ground system for EGSE and MCS has developed and many space missions such as PROBA (PRoject for On-Board Autonomy), ROSETTA, MARS EXPRESS, CRYOSAT (Cryosphere Satellite), GOCE (Gravity field and steady state Ocean Circulation Explorer), and GALILEO have used or will use it to minimize risk, reduce cost and improve overall product quality. It is based on ECSS (European Cooperation for Space Standards) E70 which is the international standard for ground systems and operations published by ECSS E70 Working Group. The ECSS E70 contains the basic rules, principles and requirements applied to the engineering of the ground systems and the execution of mission operations. This paper introduces standardization policy, organization and standard documentation in ECSS. The overview of ECSS E70 such as status, purpose and contents is also described in this paper.

• Current Industrial and Technological Trends in Aerospace
• /
• v.5 no.2
• /
• pp.33-42
• /
• 2007

위성체 총조립 및 시험(AIT ; Assembly, Integration & Test)을 위한 전기지상지원장비(EGSE ; Electrical Ground Support Equipment)와 위성 임무 준비 및 운용을 위한 관제시스템(MCS ; Mission Control System)의 공동 개발은 미국과 유럽의 위성사업 기관 및 업체에서 지금까지 많은 연구가 되어 왔다. 비록 두 시스템이 다른 목적으로 사용되고 있지만 기술적으로 유사한 기능을 갖는 시스템으로서 많은 공통점과 호환 가능성을 갖고 있다. 두 시스템의 공동 개발은 시스템 개발과 위성 운용 교육 및 준비에 필요한 비용 절감뿐만 아니라 AIT 단계에서 위성운용단계로의 자연스러운 전환이 가능하다. 이는 AIT 단계에서 공통지상시스템 하드웨어 및 운영시스템, 시험/운용 절차서, 위성 데이터베이스의 사전 검증이 이루어지기 때문이다. 또한 위성 운용 요원의 AIT 참여를 통해 공통지상시스템 운용 훈련과 위성 관제 지식 습득이 자연스럽게 이루어 질 수 있다. 이로서 사업 일정과 개발 위험도를 최소화 할 수 있다. 이러한 두 시스템의 공통성과 호환성 및 공통시스템 개발 장점이 있기에 EGSE와 MCS의 공통 기능에 대한 표준화 작업은 1986년 만들어진 COES(Committee for Operations and EGSE Standard)에서 공식적으로 논의되기 시작하여 1994년 CNES와 ESA의 발의로 제정된 ECSS(European Cooperation for Space Standards)를 통해 국제 표준(ISO, CCSDS 등)을 바탕으로 한 지상시스템에 대한 유럽 표준화 작업이 ECSS-E-70 Working Group에서 진행되고 있다. 또한 검증된 지상시스템의 핵심 운영시스템의 소프트웨어 모듈의 재사용을 통해 최근에서 다양한 공통지상시스템이 개발되어 운용되고 있다. 이러한 배경으로 국내에서도 저궤도 위성 개발에서 EGSE 핵심 모듈인 TM/TC 처리 및 Database 관리 모듈을 AIT 단계에서 개발 및 검증 후에 MCS에서의 재사용을 적극적으로 고려하고 있다. 앞으로 국제적인 추세에 따라 AIT 및 지상국간의 기술 및 인력 교류와 핵심모듈 개발을 통한 공통지상시스템 개발의 활발한 전개가 예상된다.

• Proceedings of the KSRS Conference
• /
• 2004.10a
• /
• pp.436-439
• /
• 2004

Output data streams of the MSC contain flags, Headers and image data according to the established protocols and data formats. Especially the Header added to each data lines contain information of a line sync, a line counter and, ancillary data which consist of ancillary identification bit and one ancillary data byte. This information is used by ground station to calculate the geographic coordinates of the image and get the on-board time and several EOS(Electro-Optical Subsystem) parameters used at the time of imaging. Therefore, the EGSE(Electrical Ground Supporting Equipment) that is used for testing MSC has to have functions of interpreting and displaying this Header information correctly following the protocols. This paper describes the design of the header data processing module which is in EOS­EGSE. This module provides users with various test functions such as header validation, ancillary block validation, line-counter and In-line counter validation checks which allow convenient and fast test on imagery data.