• Aerospace Engineering and Technology
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• v.11 no.1
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• pp.111-117
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• 2012

Agile is a software development methodology which was established for four objectives; people, collaboration, responsiveness, and working software. Thus the Agile methodologies have been applied not only software development fields but also various special areas of technology. ESA (European Space Agency) adopt several Agile methodologies, including Scrum as the key technique, for the software development of ground segment. This article analyzes trends of Agile methodologies and introduction cases of the methodologies for ESA's ground segment software development.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.51-56
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• 2010

There are two main software in COMS ground station at the normal mode operation - stationkeeping and wheel off-loading. In this paper, ground software validation test for wheel off-loading is summarized and described. The wheel off-loading was performed the design change from E3000 heritage and analyzed. The wheel off-loading of ground software has two part; one is wheel off-loading management for parameters change at the thruster set switching time and the other is wheel off-loading set-point being sent to satellite for the reference momentum.

• Aerospace Engineering and Technology
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• v.13 no.2
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• pp.73-79
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• 2014

During developing cubesat flight software, Communication test between cubesat and ground station is needed. For this, we have constructed indoor ground station without outdoor antenna for decreasing total cost and time. In this time, if output power of ground station is high, it will affect for cubesat transceiver to be fail. For solving this problem, ground station must be designed for output power of it to be lower than input power of cubesat satellite, and it must be verified. In this paper, first, we describe cubesat indoor ground station using UHF and VHF. Second, we describe output power decreasing test for indoor operation of ground station by attaching attenuators in the end of the output connector.

• Aerospace Engineering and Technology
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• v.11 no.2
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• pp.49-56
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• 2012

LEO Satellite performs the operations and missions by FSW(Flight Software) after separation from a launch vehicle. Many of the operations by FSW are automatically conducted by the algorithms of FSW. In the case of the IAC(Initial Activation and Checkout) operations, a mission scheduling, an orbit transition, etc, however, a decision and a control of the satellite operators or manufacturers are required in order to operate the satellite safely. For this, the wireless communication channel between a satellite and a ground station should be prepared to receive telemetries and to transmit tele-commands for controlling FSW properly. Therefore, the verification of the interface between KOMPSAT-3 and a ground station is essential. This verification test is named the satellite end-to-end test. In this paper, we show the design process of the satellite end-to-end test and test results.

• Journal of Aerospace System Engineering
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• v.15 no.5
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• pp.113-128
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• 2021

In this paper, we present a simple ground receiving station as an educational method for a satellite system. Our system is produced similarly to the existing fixed ground station in terms of function by using satellite communication technology and related software commonly used in the amateur radio field. In addition, we conducted operation test to receive signals from operating satellites and confirmed the possibility of using them as a way to educate satellite systems, such as understanding ground station systems through satellite reception experience and satellite state information acquisition, and further designing satellite systems.

• Proceedings of the Korean Information Science Society Conference
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• 2004.10c
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• pp.508-510
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• 2004

저궤도 위성은 고도가 낮아 하루에도 지구주위를 여러 번 회전해야 하고 주로 극궤도로 운영되므로 지상국과 접촉할 수 있는 시간에 상당한 제약을 가진다. 따라서 저궤도 위성의 경우 대부분의 시간을 지상의 모니터링이나 제어 없이 스스로 임무수행에 필요한 기능을 유지하면서 위성에서 생성되는 각종 데이터를 저장해 두었다가 다음 번 지상과의 접촉에서 위성의 실시간 상태정보 및 저장된 데이터들을 지상으로 송신하고 수행해야 할 임무를 지상명령으로 수신하는 과정을 통해서 운명된다. 본 논문은 국내 대표적인 저궤도 위성인 다목적실용위성 2호의 비행소프트웨어에서 위성의 실시간 상태정보 및 대용량 메모리에 저장된 데이터를 지상으로 전송하기 위한 전송제어 소프트웨어 및 전송 제어절차에 대해서 서술하였다.

• Aerospace Engineering and Technology
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• v.12 no.2
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• pp.1-6
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• 2013

A LEO satellite transmits recorded images to a ground station using an X-band antenna during contact. The X-band antenna points to the ground station according to a TPF (tracking parameter file) during communication time. A TPF generation software generates azimuth and elevation profile which make the antenna point to the ground station using satellite orbit and attitude information and mission information including recording and downlink operation. When the satellite passes above the ground station, azimuth velocity increases rapidly so that jitter may occur if the azimuth velocity is in specific range. In case of realtime mission in which the satellite perform recording and downlink simultaneously, azimuth velocity must be lower than specific value to prevent image blur due to jitter effect. The method to point one virtual ground station has limitation of azimuth velocity reduction. In this paper, we propose the azimuth fixing method to reduce azimuth velocity of X-band antenna. The experimental results show that azimuth velocity of the X-band antenna is remarkably reduced using proposed method.

• Proceedings of the Korea Information Processing Society Conference
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• 2010.11a
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• pp.1555-1557
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• 2010

위성 탑재 소프트웨어는 기본적인 위성의 상태 데이터 획득에서부터 지상국과의 송수신 및 위성 고유의 임무 수행의 전 과정을 담당하고 있다. 이러한 위성 탑재 소프트웨어에 있어 무엇보다 강조되는 점이 신뢰성이며, 이를 위한 많은 연구가 진행되어 왔다. 위성 탑재 소프트웨어의 개발 과정에서 여러 단계의 검증 및 테스트가 수반되게 되며, 이러한 위성 탑재 소프트웨어의 개발에는 많은 시간과 노력이 요구된다. 또한, 위성의 소프트웨어는 그 특성상 위성 발사 후 탑재 소프트웨어에 대한 수정 및 개선에 많은 어려움이 따르게 된다. 본 연구에서는 위성 탑재 소프트웨어 개발 과정에서 재사용성을 높이고 소프트웨어 및 위성 임무 변경에 보다 용이하게 대응할 수 있는 Reconfigurable Software Architecture 를 제안한다.

• Proceedings of the Korea Information Processing Society Conference
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• 2010.11a
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• pp.921-924
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• 2010

정지궤도 위성을 제외한 대부분의 저궤도 위성 및 심우주 관측용 위성은 임무를 수행하면서 하루동안에도 제한된 시간동안만 지상국과의 통신이 가능하다. 따라서 위성 운영에 고수준의 자율적 제어기능이 요구된다. OBCP(On-Board Control Procedures)는 별도로 개발된 언어로 작성한 작은 용량의 스크립트 프로그램을 통해 위성을 제어하는 기능을 제공한다. 이러한 방법을 통해 지상관제 시에 위성의 임무수행동안 수행되어야 하는 다양하고 복잡한 운영 시퀀스를 용이하게 준비하고 업로드할 수 있다. OBCP는 위성비행소프트웨어와는 분리된 별도의 서브시스템으로 수행되기 때문에 새로운 위성운영 프로시져의 생성을 위해 위성비행소프트웨어의 수정, 재검증, 코드업로드 등의 절차가 요구되지 않으며 지상에서 개발 및 검증시험을 완벽하게 수행할 수 있다. 본 논문에서는 기존의 저궤도 관측위성에서 사용되었던 위성의 자율적 제어 시퀀스 기능과 OBCP의 기능을 비교하여 설명하고, 실제 Herschel and Plank 위성에 활용된 예를 통해 OBCP의 개념 및 설계 방안에 대하여 소개한다.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2016.05a
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• pp.297-300
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• 2016

The typical Differential Global Navigation Satellite System service of South Korea is the Ground Based Differential GNSS service. South Korea building the Satellite-Based Augmentation System for GNSS to expand the Differential GNSS service. The satellite-based differential GNSS serive is called the SBAS(Satellite Based Augmentation System). The SBAS reference station on ground should be installed to operate the SBAS service alike the ground based augmentation system. That SBAS reference station can be installed with ground based DGNSS reference station. To make the SBAS reference station combined with the ground based DGNSS reference station, DGNSS system should be connected to NovAtel's G-III receiver. In this paper, the DGNSS software reference station's software module architecture was changed and G-III interface module was designed to use the G-III receiver.