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©Arianespace - Ariane 6 - September 2019 TECHNICAL OVERVIEW ARIANE 6 ARIANE 6

The Ariane 6 launcher will provide Arianespace with new levels Payload Adaptator Fitting (PAF) of efficiency and flexibility to meet customers’ launch services needs across a full range of commercial and institutional missions. Payload Fairing

This next generation launcher comprises two versions, Dual Launch Structure (DLS) Ariane 64 and Ariane 62, for reduced production costs and design-to-build lead times, all while maintaining the quality and reliability that have made Ariane 5 an industry leader.

Thanks to its two versions and associated performances, Single Launch Dual Launch Multiple Launch LEO Heavy Big Scientific LEO Microsat Payload Adaptator Fitting (PAF) Ariane 6 will cover a wide range of missions: GEO, through Long Fairing Mission ATV Spacecraft Constellations intermediate orbits (in particular GTO and GTO+), Polar/SSO, Launch Vehicle Adapter (LVA) MEO and others. Upper Liquid Propulsion Module (UPLM) The new launcher features a modular configuration based on core stages powered by lower and upper liquid propellant modules, which are supplemented by either Tailored to any missions Vinci engine at the service of new ambitions two or four strap-on solid rocket motors, depending on the Vinci Engine configuration of the Launch Vehicle: Ariane 62 or Ariane 64. The Ariane 6 fairing at 20-m high and with an external The Vinci engine was conceived to enhance the Arianespace diameter of 5.4 m is particularly well-adapted to market heritage of reliability, earned by its predecessor HM7B. The first flight is scheduled for 2020. developments. This enables Ariane 6 to launch all types The new engine has the capability of restarting up of satellites now in service as well as new platforms. to five times, allowing Ariane 6 to reach a range of Arianespace continually develops solutions that meet the orbits on a single mission to deliver more payloads. evolving customer demand. Priority is given to provide

access to space for all applications under the best conditions. Lower Liquid Propulsion Module (LLPM) A cost-effective access to space A direct track to GTO for small-sized satellites

Unprecedented flexibility, modularity and This new launcher is modular and will be available in two Ariane 6 will introduce an innovative service providing competitiveness versions: Ariane 62 (with two P120C solid fuel boosters, fast-track access to Geosynchronous Equatorial Orbit, for common with Vega C) and Ariane 64 (with four P120C the new generation of small satellites, offering a first flight The capabilities of this next-generation launcher, the flexibility P120C solid fuel boosters). By making extensive use of shared opportunity with more than 4,500 kg of such payloads on its “GO- of its configuration, alongside Arianespace’s proven multiple components, Ariane 6 aims to cut down launch costs, 1” mission. Configured with the Multi-Launch Service carrying mission management ability, enables Ariane 6 to carry any by leveraging economies of scale in a very novel way. system (MLS), the new launcher will accommodate a full range type of spacecraft, from the smallest (1,000 kg or less) to the of small-sized satellites, from cubesats to microsats or larger. largest (>20,000 kg), in either dedicated or shared launch. Modernized Vulcain Engine

Moreover, a specific set of accommodation solutions Standard Ariane 6 mission profile for small satellites, from cubesats to minisatellites up for geostationary transfer orbit to more than 400 kg, will be available. These smallsats launch solutions, in piggyback (with one or several main passengers) or rideshare (no main passenger) configurations, Industrial Prime Contractor will be commercialized as “Multi-Launch Service” or MLS. & Design Authority : ArianeGroup

Lunar Earth Escape Performance GTO SSO LEO MEO Transfer Orbit mission

Payloads, kg (including adapters/ structures) Ariane 62 4,500 to 5,000 6,500 10,300 1,700 2,800 to 3,000 - Ariane 64 >11,500 15,000 21,600 TBD 8,200 to 8,500 7,400 to 7,600

Inclination (i), deg 6 97.4 5 56 - -

Altitude of perigee (Zp), km 250 500 300 23,200 - -

Altitude of apogee (Za), km 35,786 500 300 23,200 - -