Ariane 5
Cancelled plans for future developments
Cancelled plans for future developments
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[thumb\|upright\=1\.0\|right\|Belgian components produced for the Ariane 5 European heavy\-lift launch vehicle explained](/wiki/File:Belgian_components_for_the_Ariane_5_rocket.jpg "Belgian components for the Ariane 5 rocket.jpg")

### Ariane 5 ME

The Ariane 5 **ME** (Mid\-life Evolution) was in development into early 2015, and was seen as a stopgap between Ariane 5ECA/Ariane 5ES and the new [Ariane 6](/wiki/Ariane_6 "Ariane 6"). With first flight planned for 2018, it would have become ESA's principal launcher until the arrival of the new Ariane 6 version. ESA halted funding for the development of Ariane 5ME in late 2014 to prioritize development of Ariane 6\.

The Ariane 5ME was to use a new upper stage, with increased propellant volume, powered by the new [Vinci engine](/wiki/Vinci_%28rocket_engine%29 "Vinci (rocket engine)"). Unlike the HM\-7B engine, it was to be able to restart several times, allowing for complex orbital maneuvers such as insertion of two satellites into different orbits, direct insertion into geosynchronous orbit, planetary exploration missions, and guaranteed upper stage deorbiting or insertion into [graveyard orbit](/wiki/Graveyard_orbit "Graveyard orbit"). The launcher was also to include a lengthened fairing up to  and a new dual launch system to accommodate larger satellites. Compared to an Ariane 5ECA model, the payload to GTO was to increase by 15% to  and the cost\-per\-kilogram of each launch was projected to decline by 20%.

#### Development

Originally known as the Ariane 5**ECB**, Ariane 5ME was to have its first flight in 2006\. However, the failure of the first ECA flight in 2002, combined with a deteriorating satellite industry, caused ESA to cancel development in 2003\. Development of the Vinci engine continued, though at a lower pace. The ESA Council of Ministers agreed to fund development of the new upper stage in November 2008\.

In 2009, [EADS Astrium](/wiki/EADS_Astrium "EADS Astrium") was awarded a €200 million contract, and on 10 April 2012 received another €112 million contract to continue development of the Ariane 5ME  with total development effort expected to cost €1 billion.

On 21 November 2012, ESA agreed to continue with the Ariane 5ME to meet the challenge of lower priced competitors. It was agreed the Vinci upper stage would also be used as the second stage of a new Ariane 6, and further commonality would be sought. Ariane 5ME qualification flight was scheduled for mid\-2018, followed by gradual introduction into service.

On 2 December 2014, ESA decided to stop funding the development of Ariane 5ME and instead focus on Ariane 6, which was expected to have a lower cost per launch and allow more flexibility in the payloads (using two or four P120C solid boosters depending on total payload mass).

### Solid propellant stage

Work on the Ariane 5 EAP motors was continued in the [Vega](/wiki/Vega_%28launcher%29 "Vega (launcher)") programme. The Vega 1st stage engine – the [P80](/wiki/P80_%28stage%29 "P80 (stage)") engine – was a shorter derivation of the EAP. The P80 booster casing was made of filament wound graphite epoxy, much lighter than the current stainless steel casing. A new composite steerable nozzle was developed while new thermal insulation material and a narrower throat improved the expansion ratio and subsequently the overall performance. Additionally, the nozzle had electromechanical actuators which replaced the heavier hydraulic ones used for thrust vector control.

These developments could maybe have made their way back into the Ariane programme, but this was most likely an inference based on early blueprints of the Ariane 6 having a central P80 booster and 2\-4 around the main one. The incorporation of the ESC\-B with the improvements to the solid motor casing and an uprated Vulcain engine would have delivered  to LEO. This would have been developed for any lunar missions but the performance of such a design might not have been possible if the higher [Max\-Q](/wiki/Max_Q "Max Q") for the launch of this launch vehicle would have posed a constraint on the mass delivered to orbit.


How did the development of the Ariane 5 ME impact the Vega program?