Astra 1KR

From Wikipedia, the free encyclopedia
Jump to: navigation, search
Astra 1KR
SATCAT no. 29055
Mission duration 15 years
Spacecraft properties
Bus A2100AX
Manufacturer Lockheed Martin
Launch mass 4,332 kilograms (9,550 lb)
Start of mission
Launch date April 20, 2006 (2006-04-20)
Rocket Atlas V 411
Launch site Cape Canaveral SLC-41
Contractor ILS
Orbital parameters
Reference system Geocentric
Regime Geostationary
Longitude 19.2°E Coordinates: 0°00′N 19°12′E / 0°N 19.2°E / 0; 19.2
Perigee 35,774 kilometres (22,229 mi)[1]
Apogee 35,811 kilometres (22,252 mi)[1]
Inclination 0.06 degrees[1]
Period 1436.10 minutes[1]
Epoch 24 January 2015, 05:02:48 UTC[1]
Band 32 Ku-band
Bandwidth 26 MHz
TWTA power 140 W

Astra 1KR is one of the Astra geostationary satellites owned by SES. It was launched in April 2006 as a replacement for Astra 1K, which failed to reach orbit on launch in 2002.[2] The launch of Astra 1KR was the first attempted by SES since the Astra 1K failure.

The craft launched to 3.4° east for testing, before moving to Astra 19.2°E, where it replaced Astra 1B, which was effectively decommissioned, and Astra 1C, which was then elderly and running beneath full capacity. It was expected to also replace Astra 2C, which was under-utilised, and to allow that satellite to return to Astra 28.2°E to join 2A/2B/2D to provide additional capacity. However, SES stated that Astra 1L would replace Astra 2C.[3]

The first signals from the craft at 19.2° east were direct replacements for four transponders on the failing Astra 1E.[citation needed]

See also[edit]


  1. ^ a b c d e "ASTRA 1KR Satellite details 2006-012A NORAD 29055". N2YO. 24 January 2015. Retrieved 25 January 2015. 
  2. ^ "ASTRA 1K satellite stabilised" (Press release). SES ASTRA. November 28, 2002. Retrieved January 26, 2012. 
  3. ^ "SES ASTRA PROCURES TWO SATELLITES WITH LOCKHEED MARTIN" (Press release). SES ASTRA. June 17, 2003. Retrieved January 26, 2012. 

External links[edit]