IRNSS-1F

Launch data:

Spacecraft data: Prime manufacturer  ISRO Platform   Operator  Indian Space Research Organization (ISRO) Mass at launch  1425 kg Dry Mass  598 kg Basic shape   Dimension (m)   Equipment   Solar array   Stabilization   Propulsion   DC power  1600 W Design lifetime  12 yrs

IRNSS-1F being readied for vibration test - Credit: ISRO

Location:

Description:

• IRNSS-1F is the sixth navigation satellite of the seven satellites constituting the Indian Regional Navigation Satellite System (IRNSS) space segment. All the five predecessors satellites are functioning satisfactorily from their designated orbital positions.
• The configuration of IRNSS-1F is similar to that of IRNSS-1A, 1B, 1C, 1D and 1E. The two solar arrays of IRNSS-1F consisting of Ultra Triple Junction solar cells generate about 1660 Watts of electrical power. Sun and Star sensors as well as gyroscopes provide orientation reference for the satellite. Special thermal control schemes have been designed and implemented for some of the critical elements such as atomic clocks. The Attitude and Orbit Control System (AOCS) of IRNSS-1F maintains the satellite´s orientation with the help of reaction wheels, magnetic torques and thrusters. Its propulsion system consists of a Liquid Apogee Motor (LAM) and thrusters.
• IRNSS -1F carries two types of payloads – navigation payload and ranging payload. The navigation payload of IRNSS-1F will transmit navigation service signals to the users. This payload will be operating in L5 band and S band. A highly accurate Rubidium atomic clock is part of the navigation payload of the satellite. The ranging payload of IRNSS-1F consists of a C-band transponder, which facilitates accurate determination of the range of the satellite. IRNSS-1F also carries Corner Cube Retro Reflectors for laser ranging.

Mission details:

• The Indian Regional Navigation Satellite System was augmented by launch of the 1F satellite on Mar 10, 2016. The initial insertion orbit was 270 x 20649 km x 17.9 deg; an initial perigee burn to raise apogee was followed by several apogee burns towards circular inclined synchronous orbit.
• The satellite is placed on a geostationary orbit at 32.5 degrees east longitude over Africa. IRNSS 1F is the second satellite to be launched into geostationary orbits closer to the equator. Once in service, its orbital inclination will be 5 degrees.

External links:

• Satellite tracking: Real time satellite tracking