2010-F04
36 C-band transponders to replace Insat 2E at 55E. Also known as GSAT 5 prime. Possibly same as Insat 4D. Mass 2310 kg full 975 kg dry, 1.6 x 1.5 x 3.09m box + 2 panels.
Launch by GSLV-F06 with C15 stage - a lengthened version of the KVD-1A based C12 used on earlier flights, with engine uprated to 126% of rated thrust. This moved the stage 2 impact point to the Andaman Sea.
At 47s the strapon boosters failed to steer, losing communication with the flight computer. A set of connectors on the stage 2/3 interface were broken due to structural failure of their support fairing, causing the steering failure. This failure was a generic issue and could have happened on any of the previous GSLV flights. At 61s altitude was 13 km and relative velocity was 0.42 km/s. The vehicle was destroyed by aerodynamic stresses. Impact prior to 292s (T+4:52) at 2.7 km downrange.
The control failure occurred at 47 seconds and around 10 km altitude? And breakup a few seconds later at 51 s (estimated from video) at a similar altitude? Destruct signal at 63s but by then the rocket had already broken up. The screenshot at 61s shows altitude 12 km and velocity 0.453 km/s but whether that is true realtime data or the planned trajectory is unclear. It looks like it might be real data as the altitude reaches a max of 15.0 km at 80 s, vrel 0.05km/s and 6 km range and then starts to fall.
|
| GSAT-5P (plan) |
| |
|
| Date | Time | Event | Orbit |
|---|
|
| 2010 Dec 25 | | Launch by GSLV-F06 | SHAR SLP |
| | | T+2:28 GS1 burnout 68 km |
| | | T+3:46 Fairing 115 km |
| | | T+4:49 GS2 burnout 137 km |
| | | T+18:51 GS3 burnout 250 km 10.2 km/s |
| | | T+19:06 GS3 sep |
|
| GSAT-5P (actual) |
| |
|
| Date | Time | Event | Orbit |
|---|
|
| 2010 Dec 25 | 1034 | Launch by GSLV-F06 | SHAR SLP |
| | | T+47s SOB steering failed |
| | | T+51s Breakup 14 km, 0.2km/s |
| | | T+1:03 Destruct command sent |
| | | T+1:20 Apogee 21 km |
| | | T+4:52? impact |
