Proton-M – AsiaSat 9 – Flight Profile

Time Event
T-0:00:02.50 Ignition Sequence Start
T-0:00:01.75 Ignition – 40% Thrust
T-0:00:00.90 Stage 1 at 100% Thrust
T-0 LIFTOFF
T+0:01:02 Maximum Dynamic Pressure
T+0:01:59 Stage 2 Ignition Command
T+0:01:59.7 Stage 1 Shutdown
T+0:01:59.7 Stage 1/2 Separation
T+0:05:24 Stage 3 Vernier Ignition Command
T+0:05:27 Stage 2 Shutdown & Separation
T+0:05:30 Stage 3 Main Ignition Command
T+0:05:45 Payload Fairing Separation
T+0:09:31 Third Stage Main Engine Cutoff
T+0:09:41 Third Stage Vernier Cutoff
T+0:09:42 3rd Stage / Briz-M Separation
T+0:11:16.0 Briz-M First Ignition
Burn Duration: 4 min & 20 sec
T+0:15:36.0 Briz-M Shutdown
T+1:07:24.0 Briz-M Second Ignition
Burn Duration: 17 min & 52 sec
T+1:25:16.0 Briz-M Shutdown
T+3:27:59.0 Briz-M Third Ignition
Burn Duration: 11 min & 33 sec
T+3:39:32.0 Briz-M Shutdown
T+3:40:22.0 APT Separation
T+3:41:49.0 Briz-M Fourth Ignition
Burn Duration: 6 min & 3 sec
T+3:47:52.0 Briz-M Shutdown
T+8:52:58.0 Briz-M Fifth Ignition
Burn Duration: 6 min & 14 sec
T+8:59:12.0 Briz-M Shutdown
T+9:13:00.0 Spacecraft Separation

To deliver the AsiaSat 9 Spacecraft to an optimized Geostationary Transfer Orbit, the three-stage Proton-M Rocket will perform a nominal ascent mission and deliver the Orbital Unit consisting of a Briz-M Upper Stage and the Payload to a sub-orbital trajectory.

Separating after 9 Minutes and 42 Seconds, the Orbital Unit will start powered flight by igniting the Briz-M Main Engine to place itself in a Low-Earth Parking Orbit. In total, the Briz-M Upper Stage will make five Main Engine Burns separated by coast phases to increase its orbital altitude in a methodical fashion. After all burns are complete, the satellite will be separated 9 Hours and 13 Minutes after Liftoff and start its own mission lasting for 15 years.

Launch Data

Launch Vehicle: Proton-M/Briz-MLaunch Site: Site 200/39, BaikonurLaunch Date: September 28, 2017
Launch Time:  18:52:16 UTC
Payload: AsiaSat 9 (6,140kg)Flight Azimuth: 61.3° 

Flight Design
Parking Orbit: 
168 by 179 Kilometers
Inclination: 51.6°
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Intermediate Orbit:
270 by 5,000 Kilometers
Inclination: 50.4°
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Transfer Orbit:
434 by 35,805 Kilometers
Inclination: 49.2°
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Injection Orbit - GTO:
4,045 by 35,786 Kilometers
Inclination: 23.4°


Map: International Launch Services

Image: International Launch Services
Image: Khrunichev
Image: Khrunichev
Image: Khrunichev
Image: Khrunichev