| H0 |
Engine ignition |
| Four first stage Snecma Viking 5 engines are started and undergo checkout prior to launch. |
|
| H0+00:04.2 |
Solid motor ignition |
| The four solid-fueled rocket boosters strapped to the first stage of the Ariane 4 rocket are lit. |
|
| H0+00:04.4 |
Launch |
| The Ariane 44P rocket lifts off from ELA-2 complex at Guiana Space Center in Kourou, French Guiana, South America. |
|
| H0+00:11 |
Start Pitch Maneuver |
| Following a vertical ascent phase, the rocket begins a 10-second pitch motion for positioning on the proper launch trajectory. |
|
| H0+01:11 |
Booster Separation |
| Having burned all their solid propellant, the Fiat Avio-built strap-on boosters are jettisoned from the Ariane rocket's first stage to fall into the Atlantic Ocean. |
|
| H0+03:31 |
First Stage Separation |
| The EADS Launch Vehicles-produced first stage of the Ariane 44P rocket is separated to fall into the Atlantic Ocean. |
|
| H0+03:33 |
Second Stage Ignition |
| The single Snecma Viking 4 engine aboard the Ariane's second stage is started, continuing the climb to orbit. |
|
| H0+04:26 |
Jettison Nose Cone |
| The 4-meter diameter payload fairing, built by Contraves, that protected Eurasiasat 1 spacecraft during atmospheric ascent is separated. |
|
| H0+05:43 |
Second Stage Separation |
| The Astrium-built second stage of the Ariane 44P rocket is jettisoned to fall into the Atlantic Ocean. |
|
| H0+05:48 |
Third Stage Ignition |
| Following the release of the second stage, the single Snecma HM 7B third stage engine is started to complete the powered phase of flight to deliver Eurasiasat 1 into orbit. |
|
| H0+18:54 |
Third Stage Shutdown |
| After consuming its supply of liquid hydrogen and liquid oyxgen, the third stage engine shuts down. Injection into the required orbit follows two seconds later. The EADS Launch Vehicles-built stage will now provide the necessary pointing and alignment for payload separation. |
|
| H0+20:20 |
Spacecraft Separation |
| The Eurasiasat 1 satellite is released into the desired geosynchronous transfer orbit. The predicted injection orbit features a perigee altitude of 180 km, apogee altitude of 35,786 km and inclination of 6.5 degrees. |
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