PAYLOAD FAIRINGS This mission will utilize the standard PLF-BR-15255 Satellite Mission Overview commercial payload fairing which is 4.1 meters SATELLITE OPERATOR in diameter and 15.255 meters in length. The PLF AsiaSat encapsulates the satellite along with the Breeze M www..com upper stage to provide protection from the dense SATELLITE MANUFACTURER atmosphere for the first 5 minutes and 47 seconds SSL after launch. www.sslmda.com

BREEZE M UPPER STAGE PLATFORM SSL 1300 The Breeze M is powered by one pump-fed gimbaled main engine that develops thrust of 20 kN (4,500 lbf). SEPARATED MASS It is composed of a central core and an auxiliary 6140 kg propellant tank which is jettisoned in flight following SATELLITE DESIGN LIFETIME depletion. The Breeze M control system includes 15+ Years an on-board computer, a three-axis gyro stabilized platform, and a navigation system. The quantity of propellant carried is dependent on specific mission requirements and is varied to maximize mission performance.

PROTON BOOSTER The Proton booster consists of three stages (described below). The overall height of the three stages of Proton Proton is 42.3 meters (138.8 ft). • 3rd ILS Proton Launch in 2017 TOTAL HEIGHT Third Stage 58.2 m (191 ft) Powered by one RD-0213 engine, this stage • 96th ILS Proton Launch Overall develops thrust of 583 kN (131,000 lbf), and a four- GROSS LIFT-OFF WEIGHT th 705,000 kg nozzle vernier engine that produces thrust of 31 kN • 5 AsiaSat Satellite Launched (1,554,000 lb) (7,000 lbf). Guidance, navigation, and control of the on ILS Proton PROPELLANT Proton M during operation of the first three stages is st UDMH and NTO carried out by a triple redundant closed-loop digital • 31 SSL Satellite Launched avionics system mounted in the Proton’s third stage. on ILS Proton INITIAL LAUNCH 16 July 1965 Second Stage Proton-1 Spacecraft Of conventional cylindrical design, this stage is powered by three RD-0210 engines plus one RD‑0211 engine and develops a vacuum thrust of 2.4 MN (540,000 lbf). SATELLITE MISSION First Stage AsiaSat 9 is AsiaSat’s most powerful satellite designed with The first stage consists of a central tank containing enhanced performance, higher efficiency and greater flexibility AsiaSat 9 the oxidizer surrounded by six outboard fuel tanks. for DTH, video distribution, VSAT broadband and mobility Each fuel tank also carries one of the six RD‑276 services. AsiaSat 9 is a replacement satellite for AsiaSat 4 at engines that provide first stage power. Total 122°E with 28 C-band and 32 Ku-band transponders, and a first stage vacuum-rated level thrust is 11.0 MN regional Ka-band payload. It carries the world’s first dedicated (2,500,000 lbf). Ku-band Myanmar beam, new Ku-band beams for Indonesia and Mongolia, in addition to two enhanced Ku-band beams The Proton and the Breeze M are built by Khrunichev serving Australasia and East Asia and a wider high-power State Research and Production Space Center. C-band coverage across the Asia-Pacific region. The five Ku‑band beams onboard AsiaSat 9 are equipped with cross- www.ilslaunch.com strap beam switching capability to provide flexible coverage. 3rd Stage/Breeze M 1st Burn = 00:04:20 2nd Burn = 00:17:52 3rd Burn = 00:11:33 4th Burn = 00:06:03 5th Burn = 00:06:14 Spacecraft Payload Fairing Separation Ignition Shutdown Ignition Shutdown Ignition Shutdown APT Jettison Ignition Shutdown Ignition Shutdown Separation (PLF) 00:09:42 00:11:16 00:15:36 01:07:24 01:25:16 03:27:59 03:39:32 03:40:22 03:41:49 03:47:52 08:52:58 08:59:12 09:13:00 Separation 00:05:47

AsiaSat 9

Mission Description 7UDQVIHU2UELW  The Proton M , utilizing a 5-burn 2nd/3rd Stage Breeze M mission design, will lift off from Pad 39 at /LIWRII Separation  00:05:27 the Baikonur Cosmodrome in Kazakhstan, with the AsiaSat 9 satellite on board. The first three stages

of the Proton will use a standard ascent profile to 3DUNLQJ2UELW  place the orbital unit (Breeze M upper stage and the AsiaSat 9 satellite) into a sub-orbital trajectory. From

this point in the mission, the Breeze M will perform  planned mission maneuvers to advance the orbital /DWLWXGH GHJUHHV unit first to a nearly circular parking orbit, then to an ,QWHUPHGLDWH2UELW intermediate orbit, followed by a transfer orbit, and  1st/2nd Stage finally to a geosynchronous transfer orbit. Separation Separation 00:02:00 of the AsiaSat 9 satellite is scheduled to occur approximately 9 hours, 13 minutes after lift-off.           /RQJLWXGH GHJUHHV Ground Track

Proton History Transfer Orbit  Maximum H = 434 km Dynamic p • Lead designer was Vladimir Chelomei, who designed it Ha = 35805 km Pressure i = 49.2° with the intention of creating both a powerful rocket 00:01:02 Launch Pad for military payloads and a high-performance ICBM. The  Command 39 program was changed, and the rocket was developed Geo-Transfer Orbit (GTO) Stage 1 H = 4045 km exclusively for launching spacecraft. p (100% Thrust) H = 35786 km -00:00:00.9 a • First named UR-500, but adopted the name “Proton”, i = 23.4°  Stage 1 which also was the name of the first three payloads Ignition Intermediate Orbit launched. /9/LIWRII (40% Thrust) Hp = 270 km H = 5000 km -00:00:01.75 • Proton launched Russian interplanetary missions to the a i = 50.4°  Ignition Start Moon, Venus, Mars, and Halley’s Comet. Sequence • Proton launched the Salyut space stations, the Mir core -00:00:02.5 *HRVWDWLRQDU\ Launch Pad segment and both the Zarya (Dawn) and Zvezda (Star) 2UELW *62 39 modules for today’s International Space Station. Parking Orbit

• First commercial Proton launch — 9 April 1996 Hp = 168 km H = 179 km • First commercial Proton M/Breeze M launch — Flight Design a Ascent Profile i = 51.6° 30 December 2002 • 400th Proton launch — 15 December 2014 • 50th year in service in 2015 • KhSC 100 year anniversary — 30 April 2016