"First orbit raising operation of GSAT-14 is successfully completed by firing the Apogee Motor for 3,134 seconds on Jan 06, 2014. Realised orbit is 8,966 km (Perigee) by 35,744 km (Apogee). "
http://isro.gov.in/gslv-d5/d5-post-updates.aspx
Confirming this, USSTRATCOM has tracked the satellite, after the first orbit raising maneuver, in the following orbit:
2014-001A/39498 in 8943 x 35767 km x 7.60° (epoch Jan 6, 1401UTC)
ISRO @ISROOFFICIAL 7 Jan The MEASURED orbital parameters after the second Orbit raising maneuver is 32,544 km (Perigee) by 35,742 km (Apogee); 0.6 degree inclination
Confirming this, USSTRATCOM has tracked the satellite, after the second orbit raising maneuver, in the following orbit:
2014-001A/39498 in
32544 x 35741 km x 0.67° (epoch Jan 7, 0609UTC)
ISRO chief reflects on the success of GSLV, says that the payload injection was so precise that satellite could save some fuel for orbit correction, thereby gaining extra 1.5 yr life.
ISRO chief reflects on the success of GSLV, says that the payload injection was so precise that satellite could save some fuel for orbit correction, thereby gaining extra 1.5 yr life.
The politician says something about Kulasekarapattinam at the end. I've heard ISRO is considering this location seriously for the 2nd spaceport.
The politician says something about Kulasekarapattinam at the end. I've heard ISRO is considering this location seriously for the 2nd spaceport.
Here's a snippet from that interview. It seems it's still under "review" and not confirmed yet:
Meanwhile, minister of state in Prime Minister's Office V Narayanasamy said on Friday that the third rocket launching pad is being considered in Kulasekaranpattinam of Tuticorin district by the central government. Talking to reporters at Mahendragiri, the minister said that there has been a demand for setting up the launching pad in Kulasekaranpattinam, as it is found to be a vantage point.
http://articles.timesofindia.indiatimes.com/2014-02-01/science/46897203_1_mahendragiri-vikram-sarabhai-space-centre-gslv
Attaching GSLV Mk2 D5 brochure by VSSC. This is more detailed than that of ISRO.
(Thanks to Ohsin, /r/isro)
The Cryogenic Engine develops a nominal thrust of 73.6 kN (vacuum) with a specific impulse of 452 seconds. The engine works on Stage Combustion Cycle in the pump-fed mode with an integrated turbopump running at around 40,000 rpm. The steering engine with the thrust of 2.2 kN provides three-axis control of the vehicle during thrusting phase. During coast phase, the OSS provides the required control to the vehicle. The unique feature of this engine is the closed loop control of both thrust and mixture rati os, which ensures optimum propellant management during the mission. The overall stage length is 8469 mm and the stage dry mass is 2548 kg.
