• Journal of Korea Society of Industrial Information Systems
• /
• v.20 no.5
• /
• pp.1-11
• /
• 2015

This paper is focused on how the trajectory of launch vehicle could be optimally estimated by the quadratic regression of trajectory data mining for the operation of telemetry ground system in NARO space center during real-time. To receive the telemetry data, the telemetry ground system has to track the space launch vehicle without tracking loss, and it is possible by the well-designed algorithm to estimate a flight position in real-time. For this reason, the quadratic regression model instead of interpolation was considered to estimate the exact position data of launch vehicle and the improvement of antenna performance. For analysis, the real trajectory data which had been logged during NARO 1st launch mission were used, the estimation result of launcher current position was analyzed by the mathematical modeling. In conclusion, the algorithm using quadratic regression based on trajectory data mining showed the better performance than previous interpolation algorithm to estimate the next flight position and the antenna driving performance.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.228.2-228.2
• /
• 2012

본 논문에서는 탑재체자료전송장치의 시험검증을 위한 장비 개발에 관하여 소개 한다. 원격탐사위성에 탑재되는 고성능원격측정센서는 대용량 데이터를 생성하며 탑재체자료전송장치를 통하여 고주파통신에 의해 지상으로 전송된다. 따라서 탑재체자료전송장치의 검증은 전체 인공위성 개발에 있어서 매우 중요하다. 시험검증장비는 송신되는 수신자료를 수신하여 여러 장비로 분배해주는 고주파신호분배모듈, 계측기 및 복조기 등 다양한 장비로 구성된다. 시험검증장비는 고성능 고주파신호 부품, 다양한 전자장비와 이를 통합, 제어 운영하는 다양한 복잡한 소프트웨어가 필요하여 개발이 어렵다. 본 논문에서는 초기 제작 시험검증장비와 최종 제작 시험검증장비 사이의 차이와 성능, 기능의 향상을 위한 설계변경 등을 통하여 이에 대한 어려움을 극복한 과정과 설계 근거와 장비 선택 등 제반사항에 대하여 기술하여 이후 관련 유사장비의 개발에 있어 도움이 되고자 한다.

• Aerospace Engineering and Technology
• /
• v.2 no.2
• /
• pp.167-178
• /
• 2003

The design on the Telemetry Ground System for launch of KSLV(Korea Space Launch Vehicle) in the korean Space center has been conducted in this study. For the optimized system design, first of all, the system deployment plan reflecting the topographic and geographic environments of the space center and launch vehicle characteristics has been developed. The RF link budget analysis for the maximum tracking range, requirement for receiving subsystem including antenna subsystem, requirement for data processing subsystem are also analyzed based on the On-Board Telemetry characteristics and launch vehicle parameters. Based on those analysis, telemetry ground system containing tracking/receiving subsystem, recording subsystem and data processing subsystem, timing subsystem, calibration subsystem and monitoring and control subsystem are designed. Futhermore, the analysis for the maximum permissible data latency and communication protocol between each telemetry station and control center are conducted and the entire system is designed so that the major telemetry parameters selected to the best quality are provided in real time to the control center(RCC, RSC) for the launch mission operation.

• Current Industrial and Technological Trends in Aerospace
• /
• v.2 no.2
• /
• pp.109-119
• /
• 2004

• Atmosphere
• /
• v.12 no.4
• /
• pp.43-55
• /
• 2002

기상청의 위성기상업무는 위성자료를 취득하여 위성영상 및 기상분석정보를 생산하고, 예보관을 비롯한 자료 사용자들에게 자료를 신속하게 제공함으로써 체계적인 위성자료 활용서비스를 수행하는 것이다. 최근 외국의 우주개발 동향과 관련하여 활용 가능한 위성자료가 증가함에 따라 위성자료 활용시스템 개선을 추진해 왔으며, 2002년 현재 종래의 GMS, NOAA 이외에 Meteosat-5, FY-2B, FY-1C, Terra, QuickScat, DMSP, TRMM, SeaWiFS 등의 다양한 위성자료를 활용하고 있다. 예보현업에 대한 원격탐사자료 지원업무는 24시간 근무체계로 위성수신분석장비를 안정적으로 운영하면서 각종 위성정보를 종합적으로 활용하여 기상실황의 변화를 감시하고, 특히 전선, 저기압, 태풍에 동반된 구름의 변화상황, 황사의 발생 및 이동 등에 대한 상황을 파악하고 있다. 또한 위성자료의 보존관리 및 외부기관으로부터의 위성자료 요청에 대한 지원업무도 중요한 업무의 하나로 수행하고 있다. 위성정보 활용체계를 강화하기 위해, GMS-5호 위성의 관측임무를 대체하게 될 GOES-9, MTSAT-1R 위성의 자료수신 및 활용체계 구축을 준비하고 있으며, Terra, Aqua와 같은 첨단 지구관측위성자료를 이용한 기상정보 산출기술의 개발을 단계적으로 추진할 것이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.50 no.8
• /
• pp.591-597
• /
• 2022

In this paper, we analyzed linkbudget with comparing actual received level of telemetry system at Palau Tracking Station. Because Palau Tracking Station participated in the launch mission for the first time and lack of verification tests for antenna tracking and signal reception performance, we analyzed the linkbudget more accurately by predicting transmit antenna polarization gain according to the trajectory and attitude of launch vehicle. The analysis results were used to analyze signal reception range, antenna operation angle and LHCP/RHCP received level. The actual received level of the antenna was similar to the linkbudget result as a result of the launch mission operation.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.50 no.9
• /
• pp.657-662
• /
• 2022

In this paper, the calculation using simulation and two measurement methods for G/T of the telemetry are analyzed. Antenna gain and noise temperature are calculated by using ICARA and Antenna Noise Temperature Calculator. System G/T were calculated by using Antenna gain/noise temperature, LNA gain/noise temperature, cable loss. The first G/T measurement method is Y-factor measurement method, which is to calculate G/T by comparing LNA noise temperature and a signal level difference when an antenna and a 50ohm termination are respectively connected to an LNA input terminal Second method is Solar calibration measurement method that is to calculate G/T by comparing noise level difference when looking at the sun and lowest level point. Finally, the accuracy was reviewed by comparing the G/T calculation results with the two measurement methods, and the optimal measurement method according to antenna performance and operating environment was presented.

• Journal of the Korea Institute of Information and Communication Engineering
• /
• v.25 no.6
• /
• pp.825-833
• /
• 2021

In flight tests, aircraft moves in real time, so it is important that data from instrumentation/measurement equipment used to determine aircraft status are processed in necessary form and transmitted to flight control systems in real time. Therefore, through telemetry data processing time reduction and processing cycle improvement in flight test control computer data processing system, in order to provide faster slave-data and safety judgment information to radar/telemetry slave-data processing, flight safety analysis system, emergency destruction transmission system, etc., we developed a PCM processing system that can be operated independently by installing data processing software that can receive and process PCM data in current telemetry data processing system and radar information at the same time. In this paper, we explain classified software functions in detail, starting with overall structure of PCM data processing systems developed by supplementing existing systems. Additionally, PCM data processing system will be supplemented through system stabilization and test operation.

• Proceedings of the Korea Water Resources Association Conference
• /
• 2004.05b
• /
• pp.251-255
• /
• 2004

본 연구에서는 현장에서의 유량측정 전 과정과 내업에서의 자료 검토 및 관리 등 일련의 유량측정 과정을 일관성 있고 편리하게 수행할 수 있도록 하는 유량측정 보조 장비인 PDA 시스템을 개발하였다. PDA는 방수가 가능하고, 휴대 가능한 소형이며, 계산, 자료 관리 및 전송 기능을 가지고 있으므로 이를 이용하여 유량측정 전 과정을 수행할 수 있으며, 이의 현장 활용을 통해 현장의 유량측정 정확도를 크게 개선시킬 수 있다. 더불어, 무선 전송된 현장 유량측정 결과를 원격지에서 수신하여 그 정확도를 재검토할 수 있도록 일반 PC용 유량 산정 및 검토용 시스템을 볕도 구축하였다. 개발된 PDA 시스템은 각종 유량측정 용역사업을 수행하는 용역업체 및 대학 등에서 유량측정 및 현장 평가, 보고 및 자료 관리 등에 직접 활용될 수 있을 것으로 기대되려, 유랑측정용 PDA 시스템의 사용을 통해 일관성 있고 충실한 유량측정자료를 지속적으로 확보한 다면, 이후 신뢰성 있는 유량자료를 확보하는데 기여할 수 있을 것으로 판단된다.

• Journal of Korea Society of Industrial Information Systems
• /
• v.19 no.6
• /
• pp.53-61
• /
• 2014

For monitoring the flight trajectory and the status of a launch vehicle, the mission control system in NARO space center process data acquired from the ground tracking system, which consists of two tracking radars, four telemetry stations, and one electro-optical tracking system. Each tracking unit exhibits its own tracking error mainly due to multi-path, clutter and radio refraction, and by utilizing only one among transmitted informations, it is not possible to determine the actual vehicle trajectory. This paper presents a way of generating flight trajectory via post-processing the data received from the ground tracking system. The post-processing algorithm is divided into two parts: compensation for atmosphere radio refraction and multi-sensor fusion, for which a decentralized Kalman filter was adopted and implemented based on constant acceleration model. Applications of the present scheme to real data resulted in the flight trajectory where the tracking errors were minimized than done by any one sensor.