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GLONASS (satellite)
GLONASS (), also known as Uragan () (GRAU Index 11F654) are the first generation of Uragan satellite used as part of the Russian GLONASS radio-based satellite navigation system. Developed by Reshetnev Information Satellite Systems, it had its debut launch in 1983, with the last launched unit on 2005 and the retirement of the last unit Kosmos 2403 on April 30, 2009. I has been superseded by the GLONASS-M (GRAU Index 11F654M), the second-generation satellites.
== Design ==
It used a 3-axis stabilized pressurized bus with two solar panels, a propulsion module and a payload module.〔 It weights generates 1000W of power and had a limited design life of 3 years, but it was extended to 5 years in later models. It had a strict requirement of keeping the internal temperature at ±1°C. The previous design used an embedded liquid cooling system that weighted . The Uragan implemented a gaseous cooling system that put most of the heat generating parts on the outside of the pressure vessel, simplifying the system and weighting just .〔
The Uragan-M are usually launched in trios, and due to the close distance, the radios of the thee would interfere with each other, meaning that the ground segment can only command one satellite at a time. Setting sun pointing attitude for power and then Earth pointing attitude for communications for a single unit takes about 5 hours. Since the radio contact window with ground control is between 4 to 6 hours, ground control can not control all spacercafts in a single pass. The on board computer in the Uragan-M can put the spacecraft in sun pointing mode autonomously, and does many of the start up processes so the ground segment can take control and process the Earth pointing mode.〔
The payload consisted of 3 L-Band navigation signals in 25 channels separated by 0.5625 MHz intervals in 2 frequency bands: 1602.5625 - 1615.5 MHz and 1240 - 1260 MHz. EIRP 25 to 27 dBW. Right hand circular polarized.〔 It transmits the FDMA signals L1OF, L1SF and L2SF. It uses 2 Cs clocks with a clock stability of 5x10-13. And includes retroreflector for accurate orbit assessment by laser ranging.〔
抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』
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