PLESETSK MOSCOW BAIKONUR The Plesetsk Cosmodrome Plesetsk Cosmodrome is a spaceport located in Mirny, Arkhangelsk Oblast, about 800 km north of Moscow. It has served as a launch site since 1957. Its high latitude makes it ideal for Angara 1.2 LEO and SSTO missions. The future launch site for Angara is the Vostochny Cosmodrome, located on the east coast of Russia. Quality • Unified Quality Management System throughout Khrunichev and its integrated key suppliers • Periodic reviews and recertification • Quarterly Customer Quality Reports • Insurance community annual briefings • Commitment to continuous quality and reliability improvement PHONE +1 571 633 7400 FAX +1 571 633 7500 1875 EXPLORER STREET, SUITE 700 RESTON, VA 20190 Our Mission Statement ILS creates value for our customers by providing dependable access to space through proven and innovative launch solutions. Angara 1.2 www.ilslaunch.com www.ilslaunch.com © February 2017 ILS International Launch Services, Inc. All rights reserved. Plesetsk Cosmodrome Launch Site Features Operational Angara 1.2 SSO ANGARA 1.2 Projected Performance from Plesetsk PAYLOAD FAIRING: SERVICE MODULE: 3 y Diameter: 2.9 m, 2.53 m usable volume The Service Module engine is designed to: (Geographic location: 62° 55’ 32” N, 40° 34’ 40” E) y Clamshell design y Generate velocity impulses to inject the payload into the target orbit COMMERCIAL 2000 y Structure is three-layered honeycomb compound y Support the required attitude during coast phase while on transfer orbit LAUNCH SERVICES and for payload separation 1900 Diagram of PLF and usable volume below y Generate velocity impulse for de-orbiting maneuver from the payload target orbit International Launch Services (ILS) 1800 PROPELLANTS: possesses the exclusive rights to market 1700 MON+MMH (600 kg) the Angara 1.2 vehicle to commercial Ø1434 Payload Envelope 1600 customers. Based on state of the art yload System Mass (kg) Payload Fairing Pa technology, the Angara 1.2 vehicle has a 1500 Ø2900 high performing payload mass to lift-off 1400 Spacecraft (SC) 400 500 600 700 800 00 92 10 mass ratio, when fully fueled. Altitude (km) 61 70 42 Ø2530 The Angara 1.2 launch vehicle can Adapter System (AS) launch a variety of satellites, weighing SC Separation Plane SERVICE MODULE AND ADAPTER SYSTEM AS / SM Joint Plane Ø1193 11 90 up to 3 metric tons, to Low Earth 90 300 12 Orbit (LEO) and was successfully flight PLF Separation Plane Typical Mission Service Module demonstrated on July 9, 2014 from the SM MES #3 SM Withdrawal Trajectory Plesetsk launch site. The Proton launch SM Disposal vehicle family, launching from Baikonur, will OU Separation Disposal Tr ajectory continue to meet heavy lift requirements, Sub-orbital Tr ajectory LV Lift-off with Angara 1.2 providing the low- and Hа = 250 km Нp = −350 km medium-lift requirements. i = 97.5° VT Ignition SM Withdrawal SM MES #1 OU Injection into Tr ansfer Orbit SC Separation Intermediate Orbit Нcirc = 505 km Hа = 505 km i = 97.5° Нp = 265 km i = 97.5° SC Target Orbit Hа = 505 km SM MES #2 Нp = 505 km OU Injection into i = 97.5° Target Orbit • Sun-Synchronous Orbit (SSO) and Low Earth Orbit (LEO) missions Angara Launch • Flight-proven launch vehicle: • Projected high performance launch capability Vehicle Family - Angara first stage major components were flight demonstrated on the Korean Space Launch • Effective cost per kilo for launch Vehicle (KSLV) for first three missions (2009, 2010, 2013) • Capability to launch to various orbits - First Angara 1.2 maiden launch was successful in 2014 • Ideal for highly inclined and polar orbit missions - First Angara 5 maiden launch was successful in 2014 • Two-Stage vehicle with restartable Service Module • Manufactured and tested by Khrunichev in Omsk and Moscow, Russia • First Angara 1.2 commercial mission announced in August 2016 RD-0124A RD-0191 for Korea Aerospace Research Insitute (KARI) ENGINE FIRST STAGE ENGINE www.ilslaunch.com.