ANGARA 1.2 LAUNCH VEHICLE FACT SHEET

ANGARA 1.2 LAUNCH VEHICLE FACT SHEET
ANGARA 1.2: COMMERCIAL LAUNCH SERVICES FOR
A WIDE RANGE OF SATELLITES (UNDER 3000 KG)
FOR SUN-SYNCHRONOUS ORBIT (SSO) AND
LOW EARTH ORBIT (LEO) MISSIONS
High performance launch capability
Effective cost per kilo for launch
y Capability to launch to various orbits
y Restartable upper stage
y Ideal for highly inclined and polar orbit missions
y
y
International Launch Services (ILS) markets the
Angara 1.2 launch service to global commercial
and governmental marketplace for Low Earth
Orbit (LEO) and Sun-Synchronous (SSO) missions.
Commercial satellite operators, as well as Space
Agencies around the world can now utilize the
new capabilities of the latest launch vehicle
developed by Khrunichev State Research and
Space Production Center (Khrunichev).
Khrunichev is one of the cornerstones of the
Russian space industry, and since 2008, is the
majority shareholder of ILS. ILS also markets the
Proton launch vehicle to commercial customers
worldwide, also built by Khrunichev. The Proton
launch vehicle has a heritage of over 410 missions
since 1995 (with over 90 being commercial
missions) conducted under the auspices of ILS.
For more information about ILS
and Khrunichev, please go to
www.ilslaunch.com or
www.khrunichev.ru.
ANGARA LAUNCH VEHICLE
Newest launch vehicle developed by the Russian Federation
Future variants will include higher launch performance
y High performance payload to lift-off mass ratio
y Flight-proven launch vehicle:
y Angara variant was flight demonstrated as the first stage of the Korean Space
Launch Vehicle (KSLV) for first three missions (2009, 2010, 2013)
y First Angara 1.2 maiden launch was successful in 2014
y First Angara 5 maiden launch was successful in 2014
y Current Angara factory co-located with Proton and Breeze M factory in Moscow
y Future Angara factory in Omsk, Russia
y All components domestically supplied within KhSC companies
y
y
LAUNCH SITE: PLESETSK COSMODROME
(Geographic location: 62° 55’ 32” N, 40° 34’ 40” E)
3D\ORDG6\VWHP0DVVNJ
ABOUT US
$OWLWXGHNP
Angara 1.2 Sun-Synchronous Performance
from Plesetsk Cosmodrome
www.ilslaunch.com
Angara 1.2 Tranport via Train
Angara 1.2 on Pad Verticalization
Angara 1.2 First Flight, 9 July 2014
SERVICE MODULE
The Service Module engine is designed to:
y Generate velocity impulses to inject the payload into the target orbit
y Support the required attitude during coast phase while on transfer
orbit and for payload separation
y Generate velocity impulse for de-orbiting maneuver from the
payload target orbit
Propellants: MON+MMH (600 kg)
Service Module and
Adapter System
PAYLOAD FAIRING
Diameter: 2.9 m, 2.53 usable volume
Clamshell design
y Structure is three-layered honeycomb compound
y
y
ANGARA 1.2 LEO PERFORMANCE
Diagram of PLF and usable volume below:
Orbit Parameters
Ø1434
Payload Envelope
Payload Fairing
Inclination
200 km
63.2°
2960
835 km
98.7°
2270
1500 km
83°
1530
Spacecraft (SC)
6110
Stage 2 Separation
Service Module 1st Burn
PLF Separation
4270
9200
Ø2900
Hcirc
Payload System
Mass (kg)
Stage 1 Separation
Ø2530
Transfer Orbit
Adapter System (AS)
Ø1193
AS / SM Joint Plane
1190
1290
SC Separation Plane
300
PLF Separation Plane
Service Module
(Upper Stage)
Target Orbit
P HONE +1 571 633 7400
FA X +1 571 633 7550
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© 2016 ILS International Launch Services, Inc. All rights reserved.
www.ilslaunch.com
Service Module 2nd Burn