allows the engine to burn for 945 seconds while providing 6.5 tonne of thrust. The ESC provides roll control during powered flight and full attitude control during payload separation using hydrogen gas thrusters. Oxygen gas thrusters allow longitudinal acceleration after engine cutoff. The flight assembly includes the Vehicle Equipment Bay, with flight electronics for the entire rocket, and the payload interface and structural support. Fairing The payload and all upper stages are covered at launch by a fairing for aerodynamic stability and protection from heating during supersonic flight and acoustic loads. It is jettisoned once sufficient altitude has been reached, typically above . It is made by Ruag Space and since flight VA-238 it is composed of 4 panels. Variants Launch system status: Launch pricing and market competition , the Ariane 5 commercial launch price for launching a "midsize satellite in the lower position" was approximately €50 million, competing for commercial launches in an increasingly competitive market. The heavier satellite is launched in the upper position on a typical dual-satellite Ariane 5 launch and is priced higher than the lower satellite, on the order of €90 million . Total launch price of an Ariane 5 – which can transport up to two satellites to space, one in the "upper" and one in the "lower" positions – was around €150 million . Cancelled plans for future developments 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. 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. 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. 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