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2 — Description of the launcher Overeenkomst tussen bepaalde Europese Regeringen en de Europese Organisatie voor Ruimteonderzoek betreffende de uitvoering van het Ariane draagraketprogramma

Description of the launcher

The Ariane launcher is a 3-stage vehicle. It is 47.60 metres high and weighs 202 metric tons at lift-off.

The first stage, 'L140', with a diameter of 3.8 metres, contains 140 metric tons of propellants (N2O4 and UDMH) stored in two separate identical tanks, pressurised by hot gases drawn from the engines. They are of steel, whereas the connecting structure is of light alloy. The stage is powered by four 'Viking-2' engines, with turbo-pump and film-cooled single-wall nozzle. The total thrust at lift-off is 240 metric tons and the burn time 150 seconds.

The second stage, 'L33', with a diameter of 2.6 metres, carries 33 metric tons of the same propellants in two light-alloy tanks with a common bulkhead. The propellants are pressurised by helium stored at high pressure. The stage is equipped with a 'Viking-4' engine derived from the 'Viking-2' by adapting the nozzle for operation in vacuum.

The third stage, 'H 8', with the same diameter as the 'L 33', carries 8 metric tons of liquid hydrogen and liquid oxygen in two tanks with a common bulkhead, thermally protected by external insulation. These tanks are of a light alloy especially chosen for its behaviour at low temperatures. The same material was chosen for the 'L 33', whose tanks have a similar geometry.

These tanks are pressurised. The stage is powered by an 'H M 7' engine with a thrust of 6 metric tons.

Stage separation is achieved by explosive cords, and the stages are forced apart by retro-rockets (lower stage) and acceleration rockets (upper stage).

The instrumentation pack, located above the third stage, performs centrally, with the help of a computer, the autopilot, guidance and sequencing functions.

It also carries telemetry, telecommand, trajectography and breakup equipment, together with the inertial platform.

The fairing is bulb-shaped to house the foreseeable satellites. It allows for a payload of 3 metres effective diameter and 4 metres height.

Orbiting is achieved by direct injection, without an intermediate coasting phase, at 200 km altitude.

Regeling
Overeenkomst tussen bepaalde Europese Regeringen en de Europese Organisatie voor Ruimteonderzoek betreffende de uitvoering van het Ariane draagraketprogramma
Soort
Verdrag
Geldend vanaf
06-02-1979
BWB-id
BWBV0003413
Versie
1979-02-06_0

In de hele regeling · Officiële tekst op wetten.overheid.nl