• Title/Summary/Keyword: 위성 탑재체 (satellite payload)

Search Result 168, Processing Time 0.023 seconds

Preliminary Design of STSat-2 Secondary Payload: a Laser Reflector Array for Satellite Laser Ranging (과학기술위성2호 부탑재체 초기 설계: 위성레이저정밀거리측정용 반사경)

  • 이준호;김병창;김도형;이상현;임용조
    • Proceedings of the Optical Society of Korea Conference
    • /
    • 2003.02a
    • /
    • pp.98-99
    • /
    • 2003
  • 2005년 국산 소형위성 발사체에 탑재되어 발사 될 예정으로, 과학기술위성2호의 개발이 2002년 10월부터 시작되었다. 과학기술위성2호는 약 100kg의 소형위성으로, 경사각 60~80$^{\circ}$의 300km x 1500km 타원궤도에 발사될 것으로 예상되고 있으며, 라만-a태양촬영망원경(LIST, Larman-a Imaging Solar Telescope)과 레이저정밀거리측정용 반사경이 각각 주 및 부 탑재체로 탑재될 예정이다. 위성레이저정밀거리측정(SLR, Satellite Laser Ranging)이란 위성간의 거리를 가장 정확하게 측정할수 있는 축지학적 기술이다. (중략)

  • PDF

과학기술위성 2호 운영개념

  • Lee, Seung-Hun;Keum, Jung-Hoon;Park, Jong-Oh;Sim, Eun-Sup
    • Aerospace Engineering and Technology
    • /
    • v.3 no.1
    • /
    • pp.79-85
    • /
    • 2004
  • In this study, the operations concept of STSAT-2 which will be launched by KSLV-1, the first Korean Space Launch Vehicle, from Naro is explained. The major tasks of STSAT-2 is acquiring Lyman-alpha images of Sun by LIST(Lyman-alpha Imaging Solar Telescope) payload and the exact position of the satellite by calculating distance between STSAT-2 and SLR ground stations using SLR(Satellite Laser Ranging) payload. Also spacecraft technology verification is performed.

  • PDF

Operation Mode Design and Performance Analysis for Small Satellite SAR Payload (초소형위성 SAR 탑재체 운용모드 설계 및 성능분석)

  • Park, Jongmin;Kim, Dongsik;Kim, Wansik;Kim, Jongpil
    • The Journal of the Institute of Internet, Broadcasting and Communication
    • /
    • v.19 no.5
    • /
    • pp.169-173
    • /
    • 2019
  • In this paper, SAR payload operation mode design method, results and performance analysis results are suggested. To SAR payload design, pramary parameter should be identified and designed. It is designed considering the small satellite of less than 100kg operated in low earth orbit. Also, an antenna structure for small size and light weight is proposed. Performance analysis is performed by applying the design values.

해석해를 이용한 발사시 위성체 열해석

  • Choi, Joon-Min;Kim, Hui-Kyung;Hyun, Bum-Seok
    • Aerospace Engineering and Technology
    • /
    • v.2 no.2
    • /
    • pp.83-88
    • /
    • 2003
  • Satellite mounted on the launch vehicles experiences several environmental heating, such as direct solar flux, Earth IR, Albedo, and free molecular heating during faring jettison-separation launch stage. So, the most outer payload box of satellite is under the worst hot condition. The thermal governing equation is reduced into 1st order ordinary differential equation and analytic solution is acquired if payload box is assumed as a single lumped mass. Applying the analytic solution, we can predict the temperature increase of payload box experienced the worst hot condition, easily.

  • PDF

Development Trends of Thermal Control Design and Analysis of Robotic Arm Payload for Spacecraft (인공위성 로봇팔 탑재체의 열 제어 설계 및 해석 개발 동향 )

  • Han-Seop Shin;Hae-Dong Kim
    • Journal of Space Technology and Applications
    • /
    • v.4 no.1
    • /
    • pp.27-47
    • /
    • 2024
  • In the New space era, satellites are being developed to perform on-orbit service (OOS) missions. Various missions for orbital service include failure repair, refueling, towing, component replacement, and space construction, and in order to do so, a robot arm payload must be mounted. Unlike conventional satellite payloads, the robot arm payload is not move in a fixed state, but is a payload that must move continuously to perform the mission. It is also characterized by the need to perform the mission while being directly exposed to outer space, rather than existing inside the structure of the satellite. Due to the characteristics of these payloads, thermal design and interpretation that can be operated smoothly in an extreme space thermal environment is essential, but there are not many papers on thermal design and interpretation of the robot arm. This paper introduces and summarizes cases of thermal design and interpretation of robot arm payloads developed so far, and finally, it intends to suggest directions for thermal design and interpretation of robot arm payloads to be developed in the future.

Auto-compatibility Analysis for Ka-band payload of COMS

  • Park, Jae-Woo;Lee, Seong-Pal;Baek, Myung-Jin
    • Journal of Satellite, Information and Communications
    • /
    • v.2 no.2
    • /
    • pp.41-47
    • /
    • 2007
  • The first geostationary satellite made by Korea, COMS, has the three different payload ; Meteorological sensor, Oceanographic sensor and Ka-band communication payload. There are Meteorological & Ocean Data Communication Subsystem(MODCS) and Telemetry, Command and Ranging Subsystem(TC&R) as other RF radiation sources. MODCS transmits and receives Meteo and Ocean measurement data from/to earth using L-band and TC&R using S-band. The Ka-band communication payload will provide high-speed multimedia services and communication services for natural disaster such as prediction, prevention, and recovery services in the government communications network.Ka-band beacon is for the earth antenna pointing and the experiment of rain fading. This paper gives the analysis results about the mutual radiation effect on Ka-band communication payload, Ka-band beacon, MODCS and TC&R. Up/Down link power and coupling factor including the geometrical position and distance of antenna, filter rejection and degradation factor due to the different polarization are considered. The results show MODCS and TC&R are compatible for Ka-band communication payload and Ka-band beacon does not interfere with MODCS and TC&R normal operation.

  • PDF

MEASUREMENTS OF ALBEDO AND SPECTRAL PATTERNS OF MAN-MADE SATELLITE MATERIALS (인공위성 재질별 반사율 및 분광유형 측정)

  • 이동규;김상준;이준호;한원용;민상웅
    • Journal of Astronomy and Space Sciences
    • /
    • v.19 no.4
    • /
    • pp.319-326
    • /
    • 2002
  • Laboratory tests have been carried out for investigation of the spectroscopic characteristics at visible wavelength of 12 common satellite materials used in satellite bus and payload. The obtained spectral data show that the materials can be classified and identified since their spectral features and albedos distinctly differ among them. It is suggested that the result of the laboratory tests for the satellite materials can be used for the predictions of material types, material composition ratios, sizes, and masses in comparison with the spectral data obtained from observations of new satellites or space debris.

Design of the COMS Satellite Ground Control System (통신해양기상위성 관제시스템 설계)

  • Lee, Byeong-Seon;Jeong, Won-Chan;Lee, Sang-Uk;Lee, Jeom-Hun;Kim, Jae-Hun
    • Journal of Satellite, Information and Communications
    • /
    • v.1 no.2
    • /
    • pp.16-24
    • /
    • 2006
  • As a multi-mission GEO satellite, COMS system is being developed jointly by KARI, ETRI, KORDI, KMA, and industries from both abroad and domestic. EADS ASRTIUM is the prime contractor for manufacturing the COMS. ETRI is developing the COMS Ka-band payload and SGCS with the fund from MIC. COMS Satellite Ground Control System (SGCS) will be the only system for monitor and control of the satellite in orbit. In order to fulfill the mission operations of the three payloads and spacecraft bus, COMS SGCS performs telemetry reception and processing, satellite tracking and ranging, command generation and transmission, satellite mission planning, flight dynamics operations, and satellite simulation, By the proper functional allocations, COMS SGCS is divided into five subsystems such as TTC, ROS, MPS, FDS, and CSS. In this paper, functional design of the COMS SGCS is described as five subsystems and the interfaces among the subsystems.

  • PDF

Prospect and Direction on Korean Ground System Development (우리나라 지상시스템의 발전 전망 및 방향)

  • Chung, Daewon
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.44 no.8
    • /
    • pp.718-727
    • /
    • 2016
  • Korean ground systems have started to be developed for mission control and payload data processing since 1990s. International technology cooperations were needed in the early development phase of ground system for science experiment satellite, LEO satellite and GEO satellite and then they have been developed as domestic own technology since acquiring early technology. Our country has developed total 14 ground systems until now, this paper suggests prospect and direction on ground system development in the base of such development experiences. Mission control system is needed to develop multi-satellite mission control system in the base of technology of re-configure, re-use and automation. Processing system is needed to acquire processing technology for kinds of payload sensor data and study inter-operation to integrate and use outputs which are processed between users. Finally, national ground system infrastructure is needed to operate kinds of lots of satellites at worldwide area.