The various missions
In November 1987, the European ministers in charge of Space matters decided to develop the Ariane 5 launcher.
This decision was mainly in response to the predictable evolution of user needs for launch systems (increased mass and volumes of satellites for geostationary orbits (GEO), launching of components for manned flights into low orbit). Ariane 5 was also designed to be able to serve as a launcher for the European Hermes shuttle which was then being developed (the Hermes programme was later abandoned).
Unlike the gradual evolution of the Ariane 1 to Ariane 4 launchers, the Ariane 5 benefited from a completely new design. The initial specifications required that the new launcher be able to carry bigger and heavier satellites, that it be able to reach low orbits, that its cost remain reasonable and that it be sufficiently reliable for manned flights. The great versatility of Ariane 5 enables it to carry out a wide range of different missions, such as the placing of a payload in low orbit or the launching of a probe onto a sun-synchronous orbit.
The principal mission of the Ariane 5 launcher is to carry one or more satellites into a geostationary transfer orbit (GTO) but it may also be assigned other missions such as transporting Earth observation satellites onto required orbits, or transporting elements of the International Space Station (ISS), probes and even manned flights.
The Ariane 5 launcher is notably different to previous launchers in terms of the high level of performance required as well as its capability for manned flight launches. It has an identical lower part for all missions, and an upper part whose configuration varies according to the mission. The launcher also has a different propulsion system.
A main cryogenic stage (EPC) was developed using a new Vulcain engine. Lift-off takes place with two boosters (EAP), which are only ignited once the Vulcain engine is operating satisfactorily.
The net throwweight of Ariane 5 is 6,800 kg for a single launch and 5,900 kg for a dual launch onto a geostationary transfer orbit (GTO). The launcher is capable of launching a 10,000 kg payload onto a sun-synchronous orbit (SSO) and also has to be able to carry elements for the infrastructure of the International Space Station into low orbit (with a mass of 18 to 18.5 tonnes).
In order to meet the changing needs of the launch market (for greater masses for communication satellites for instance), ESA undertook the ‘Ariane 5 plus’ programme in 1998; this was intended in particular to develop the new upper stages (by integrating a cryogenic stage making it possible to increase the throwweight capability for a GTO to 10-12 tonnes by 2005).
Source : cnes.fr
This decision was mainly in response to the predictable evolution of user needs for launch systems (increased mass and volumes of satellites for geostationary orbits (GEO), launching of components for manned flights into low orbit). Ariane 5 was also designed to be able to serve as a launcher for the European Hermes shuttle which was then being developed (the Hermes programme was later abandoned).
Unlike the gradual evolution of the Ariane 1 to Ariane 4 launchers, the Ariane 5 benefited from a completely new design. The initial specifications required that the new launcher be able to carry bigger and heavier satellites, that it be able to reach low orbits, that its cost remain reasonable and that it be sufficiently reliable for manned flights. The great versatility of Ariane 5 enables it to carry out a wide range of different missions, such as the placing of a payload in low orbit or the launching of a probe onto a sun-synchronous orbit.
The principal mission of the Ariane 5 launcher is to carry one or more satellites into a geostationary transfer orbit (GTO) but it may also be assigned other missions such as transporting Earth observation satellites onto required orbits, or transporting elements of the International Space Station (ISS), probes and even manned flights.
The Ariane 5 launcher is notably different to previous launchers in terms of the high level of performance required as well as its capability for manned flight launches. It has an identical lower part for all missions, and an upper part whose configuration varies according to the mission. The launcher also has a different propulsion system.
A main cryogenic stage (EPC) was developed using a new Vulcain engine. Lift-off takes place with two boosters (EAP), which are only ignited once the Vulcain engine is operating satisfactorily.
The net throwweight of Ariane 5 is 6,800 kg for a single launch and 5,900 kg for a dual launch onto a geostationary transfer orbit (GTO). The launcher is capable of launching a 10,000 kg payload onto a sun-synchronous orbit (SSO) and also has to be able to carry elements for the infrastructure of the International Space Station into low orbit (with a mass of 18 to 18.5 tonnes).
In order to meet the changing needs of the launch market (for greater masses for communication satellites for instance), ESA undertook the ‘Ariane 5 plus’ programme in 1998; this was intended in particular to develop the new upper stages (by integrating a cryogenic stage making it possible to increase the throwweight capability for a GTO to 10-12 tonnes by 2005).
Source : cnes.fr
