Baseline Configuration of Ariane 6 Selected

Artist’s view of Ariane 6. Credit: ESA–D. Ducros, 2013

The baseline configuration for Europe’s Ariane 6 launch vehicle has been selected.

In November 2012, European Ministers responsible for space, meeting in Naples, Italy, approved the start of preparatory activities for Europe’s next-generation Ariane 6 launch vehicle.

The objective of Ariane 6 is to maintain guaranteed autonomous access to space for Europe, while minimizing exploitation costs and suppressing any support to exploitation.

The performance requested for the new launch vehicle was 3–6.5 tonnes in equivalent geostationary transfer orbit (GTO), to cover both governmental and commercial needs. The general configuration retained was ‘PPH’ – indicating the sequence of stages using solid propulsion, solid propulsion, and cryogenic propulsion.

Ministers also requested that the new launch vehicle exploits maximum commonalities with the cryogenic reignitable upper stage of Ariane 5 ME.

Process
Seven months after ESA’s Ministerial Council decision, the project team of ESA, supported by CNES, has endorsed the final concept proposed by industry for the vehicle that will become Europe’s workhorse for reaching space in the 2020s and beyond.

This concept was selected after six months of trade-off studies done by a ‘plateau project’ integrating industrial teams (Astrium, Avio, Herakles, and the participation of Safran, MT Aerospace, and others) working under ESA contract, consistent with Ministerial decisions mentioned above.

The choice of configuration was made by consensus and based on the following main criteria: exploitation costs, time to market, and development costs.

Ariane 6 will benefit from the advances by European industry in solid and cryogenic propulsion, structures, systems, avionics, ground segment, and operations through the Ariane and Vega programs.

‘Multi P linear’ concept. Credit: ESA–D. Ducros, 2013

Baseline Configuration Selected
The selected ‘Multi P linear’ concept is based on a lower ‘composite’ of four motors, each loaded with around 135 tonnes of solid propellant, providing also synergies with the Vega evolution perspectives. An “in-line” arrangement of three will serve as the first stage, while the fourth will be mounted above as the second stage.

The third stage will be an adapted version of the Ariane 5 ME upper stage, equipped with the Vinci engine and specific propellant tanks.

The 5.4 m-diameter (17.7 ft) payload fairing will be able to accommodate the same volume of satellites as Ariane 5.

Steps to October 2013
The next step will be for ESA to consult with the industry to gather competing ideas on key work packages of the new launch system. The industry will have maximum flexibility for meeting the requirements.

Consolidation of the current Phase A will take place at the Preliminary Requirements Review (PRR) in October 2013.

Decisions taken by the ESA Council at Ministerial level in November 2012 are being implemented strictly and timely.