• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• v.2
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• pp.443-446
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• 2006

INS를 사용하는 지상항법시스템은 GPS 등의 보조 센서와 관계없이 다양한 환경에서 장시간 운용시 항법 성능을 보장하기 위하여 재교정 과정을 거쳐야 한다. 본 논문에서는 이러한 재교정 절차 없이 장시간의 반복적인 사용에도 신뢰할 수 있는 항법해를 제공하기 위한 동작간 교정 기법에 대한 기초 연구를 수행한다. 이를 위하여 지상항법시스템에 나타나는 다양한 운동 특성을 묘사할 수 있는 시뮬레이터를 개발하고, 각 운동 특성에서의 가관측성 해석과 INS와 GPS의 항법 출력 특성을 분석한다.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2022.11a
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• pp.195-197
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• 2022

위성항법시스템(GPS)은 편리성, 활용도 등으로 인해 항법, 이동통신, 금융, 전력 등 여러 분야(측위·항법·시각)에서 사용하고 있다. 위성이 지구로부터 약 2만키로미터 떨어져 있어 위성신호 수신 세기가 약해 외부로부터 전파간섭이나 교란 등 보안에 취약한 단점이 있다. 주요국(미국, 유럽, 중국, 인도 등)은 보안을 강화하여 독자적인 위성항법 시스템을 구축하여 운영하고 있다. 우리나라도 지상기반(eLoran)과, 위성기반(KPS)의 항법시스템을 구축중이다. 시스템 구축이 완료되면 한층 강화된 국가 PNT 체계 구축으로 만일의 사태에 발생할 수 있는 상황에 대비할 수 있을 것으로 기대하고 있다. 본 연구에서는 지상기반, 위성기반의 항법시스템에 대한 핵심 기능과 추진계획을 기술하였으며, 관련 연구개발을 통해 더욱 정밀한 서비스 제공으로 해양뿐만 아니라 자율주행 이동체, 무인기 등 여러 산업 분야에 서비스를 확대해 나갈 계획이다.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.60-60
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• 2003

과학위성 1호에는 원자외선 분광기를 포함한 다섯 개의 탑재체가 있다. MMS(Mass Memory System)는 이들 탑재체가 수집한 데이터를 대용량 메모리에 저장한 후 지상국으로 보내는 역할을 하며 우주방사선에 의한 메모리 데이터의 오류와 무선 채널을 통한 Downlink 상에서 발생하는 오류를 최소화하기 위해서 소프트웨어적으로 에러를 정정할 수 있는 Reed-Solomon Code를 사용 하였다. 탑재체의 데이터를 저장하기 위한 대용량 메모리는 총 2Gbits로써 8M SRAM, 64M SDRAM, 256M SDRAM의 세 가지로 구성되어 있으며 메모리 여러 개를 하나의 모듈로 만들고 이 모듈이 층으로 쌓여서 MMS에 탑재되어 있다. SRAM에 비해서 집적도가 매우 높은 SDRAM은 공간을 적게 차지하는 장점은 있지만 우주용이 아니므로 그 안정성을 보장할 수 없으므로 우리별 3호에서 성능이 입증된 SRAM과 같이 탑재되었다. 본 연구에서는 MMS의 구조, 동작모드, Spec 및 연구 개발 내용을 소개한다.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.58-58
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• 2003

과학위성 1호의 컴퓨터 시스템은 지상국 명령 및 데이터 처리, 위성 자세 제어, 위성체 운용, 상태 감시, 탑재체 운용, 배터리의 충방전 제어 등을 담당하며, 우리별 3호 위성을 통하여 검증된 컴퓨터 시스템을 기반으로 개발되었다 과학위성 1호의 컴퓨터 시스템은 탑재 컴퓨터(On-board Computer)와 비행 소프트웨어(Flight Software)로 구성된다. 과학위성 1호의 탑재 컴퓨터는 우리별 3호의 탑재 컴퓨터에 비하여 FPGA를 사용함으로써 크기 및 무게의 소형화를 추구하였고, 네트워크 제어기를 내장함으로써 통신 성능의 개선을 이루었다. 그리고 EEPROM을 장착하여 위성 운용 기간 도중에 발생할 수 있는 소프트웨어의 변경에도 대응하였다 과학위성 1호의 비행 소프트웨어는 우리별 3호의 비행 소프트웨어를 기반으로 하여 과학위성 1호의 명령 및 데이터 처리 시스템과 임무에 적합하도록 개발되었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.8
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• pp.671-680
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• 2021

This paper deals with the contents of designing and producing reconnaissance hardware and software, and verifying the functions after being installed on the CanSat platform and ground stations. The main reconnaissance mission is largely composed of two things: terrain search that renders the surrounding terrain in 3D using radar, GPS, and IMU sensors, and real-time detection of major objects through optical camera image analysis. In addition, data analysis efficiency was improved through GUI software to enhance the completeness of the CanSat system. Specifically, software that can check terrain information and object detection information in real time at the ground station was produced, and mission failure was prevented through abnormal packet exception processing and system initialization functions. Communication through LTE and AWS server was used as the main channel, and ZigBee was used as the auxiliary channel. The completed CanSat was tested for air fall using a rocket launch method and a drone mount method. In experimental results, the terrain search and object detection performance was excellent, and all the results were processed in real-time and then successfully displayed on the ground station software.

• Bulletin of the Korean Space Science Society
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• 2006.04a
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• pp.125-128
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• 2006

Communication Subsystem of HAUSAT-2 which is 25kg class nanosatellite is designed, manufactured and tested for its performance verification at the Space System Research Laboratory (SSRL). HAUSAT-2 Communication Subsystem provides communication link for commands receiving, mission and state of health data transmission with high reliability. This paper describes design, manufacturing, test results of Engineering Model of HAUSAT-2.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2018.11a
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• pp.95-96
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• 2018

This paper deals with the development status of eLoran system which is the best backup position, navigation, and timing (P NT) system of Global Navigation Satellite System (GNSS) and its performance result. I t especially explains the status of eLoran testbed implementation for the eLoran test service, development of eLoran transmitting system, differential Loran (dLoran) system, integrated operation and control system (IOCS), and integrated eLoran/GNSS receiver. The paper discusses about the future plan for the build up test transmitting station and backup P NT service to succeed to the trial operation of eLoran testbed system.

• The Korean Journal of Air & Space Law and Policy
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• v.20 no.1
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• pp.87-107
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• 2005

Land Remote Sensing' is defined as the science (and to some extent, art) of acquiring information about the Earth's surface without actually being in contact with it. Narrowly speaking, this is done by sensing and recording reflected or emitted energy and processing, analyzing, and applying that information. Remote sensing technology was initially developed with certain purposes in mind ie. military and environmental observation. However, after 1970s, as these high-technologies were taught to private industries, remote sensing began to be more commercialized. Recently, we are witnessing a 0.61-meter high-resolution satellite image on a free market. While privatization of land remote sensing has enabled one to use this information for disaster prevention, map creation, resource exploration and more, it can also create serious threat to a sensed nation's national security, if such high resolution images fall into a hostile group ie. terrorists. The United States, a leading nation for land remote sensing technology, has been preparing and developing legislative control measures against the remote sensing industry, and has successfully created various policies to do so. Through the National Oceanic and Atmospheric Administration's authority under the Land Remote Sensing Policy Act, the US can restrict sensing and recording of resolution of 0.5 meter or better, and prohibit distributing/circulating any images for the first 24 hours. In 1994, Presidential Decision Directive 23 ordered a 'Shutter Control' policy that details heightened level of restriction from sensing to commercializing such sensitive data. The Directive 23 was even more strengthened in 2003 when the Congress passed US Commercial Remote Sensing Policy. These policies allow Secretary of Defense and Secretary of State to set up guidelines in authorizing land remote sensing, and to limit sensing and distributing satellite images in the name of the national security - US government can use the civilian remote sensing systems when needed for the national security purpose. The fact that the world's leading aerospace technology country acknowledged the magnitude of land remote sensing in the context of national security, and it has made and is making much effort to create necessary legislative measures to control the powerful technology gives much suggestions to our divided Korean peninsula. We, too, must continue working on the Korea National Space Development Act and laws to develop the necessary policies to ensure not only the development of space industry, but also to ensure the national security.

• Bulletin of the Korean Space Science Society
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• 2006.04a
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• pp.129-132
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• 2006

Animal Tracking System consists of Animal Tracking System Receiver on the Satellite segment, Animal Tracking Terminal and Ground Station for data analysis on the Ground segment. This paper describes operation concept and hardware design for Animal Tracking System which is the payload of HAUSAT-2 being developed by the Space System Research Laboratory (SSRL). Algorithms for determination of animal position and data processing are also referred to.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.2
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• pp.156-165
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• 2015

A survivability-analysis program has been developed to analyze the ground collision risk of atmospheric reentry objects, such the upper stages of a launch vehicle or satellites, which move at or near the orbital velocity. The aero-thermodynamic load during the free fall, the temperature variation due to thermal load, and the phase shift after reaching the melting point are integrated into the 3 degree-of-freedom trajectory simulation of the reentry objects to analyze the size and weight of its debris impacting the ground. The analysis results of the present method for simple-shaped objects are compared with the data predicted by similar codes developed by NASA and ESA. Also, the analysis for actual reentry orbital objects has been performed, of which results are compared with the measurement data.