Operator CNSA / INPE SATCAT no. 32062 Bus Phoenix-Eye 1 | COSPAR ID 2007-042A Mission duration 2 years planned Launch date 19 September 2007 Last contact 10 May 2010 | |
Launch mass 1,450 kilograms (3,200 lb) Similar China–Brazil Earth Resource, CBERS‑2, CBERS‑1, CBERS‑4, Satélite de Coleta de Dados | ||
Cz 4b y17 cbers 2b launch 19 9 07
China–Brazil Earth Resources Satellite 2B (CBERS-2B), also known as Ziyuan I-02B or Ziyuan 1B2, was a remote sensing satellite operated as part of the China–Brazil Earth Resources Satellite programme between the China Centre for Resources Satellite Data and Application and Brazil's National Institute for Space Research. The third CBERS satellite to fly, it was launched by China in 2007 to replace CBERS-2.
CBERS-2B was a 1,450-kilogram (3,200 lb) spacecraft built by the China Academy of Space Technology and based on the Phoenix-Eye 1 satellite bus. The spacecraft was powered by a single solar array, which provided 1,100 watts of electricity for the satellite's systems. The instrument suite aboard the CBERS-2B spacecraft consisted of three systems: the Wide Field Imager (WFI) produced visible-light to near-infrared images with a resolution of 260 metres (850 ft) and a swath width of 890 kilometres (550 mi); a high-resolution CCD camera was used for multispectral imaging at a resolution of 20 metres (66 ft) with a swath width of 113 kilometres (70 mi); the third instrument, the High Resolution Camera (HRC) was a panchromatic imager with a resolution of 2.7 metres (8 ft 10 in) and a swath width of 27 kilometres (17 mi). HRC replaced the lower-resolution Infrared Multispectral Scanner instrument flown on earlier CBERS satellites.
A Chang Zheng 4B carrier rocket, operated by the China Academy of Launch Vehicle Technology, was used to launch CBERS-2B. The launch took place at 03:26:13 UTC on 19 September 2007, using Launch Complex 7 at the Taiyuan Satellite Launch Centre. The satellite was successfully placed into a sun-synchronous orbit.
CBERS-2B suffered a power system failure on 10 May 2010, leaving it unable to continue operations. As of 25 January 2015 it remains in orbit, with a perigee of 745 kilometres (463 mi), an apogee of 789 kilometres (490 mi), 98.26 degrees inclination and a period of 100.04 minutes. It has a semimajor axis of 7,138.59 kilometres (4,435.71 mi), and eccentricity of 0.0031332.