Ariane 3
| Function | Medium launch vehicle |
|---|---|
| Manufacturer |
Aérospatiale for ESA and Arianespace |
| Size | |
| Height | 49.13 m (161.2 ft) |
| Diameter | 3.8 m (12 ft) |
| Mass | 234,000 kg (516,000 lb)[1]:518 |
| Stages | 3 |
| Capacity | |
| Payload to GTO | 2,700 kg (6,000 lb) |
| Associated rockets | |
| Family | Ariane |
| Launch history | |
| Status | Active |
| Launch sites | Guiana Space Centre ELA-1 |
| Total launches | 11[2] |
| Successes | 10 |
| Failures | 1 |
| First flight | 4 August 1984 |
| Last flight | 12 June 1989 |
| Boosters - SEP P7.35[3] | |
| No. boosters | 2 |
| Length | 8.32 m (27.3 ft) |
| Diameter | 1.07 m (3 ft 6 in) |
| Gross mass | 19.32 tonnes (21.30 tons) |
| Engines | P7 |
| Thrust | 1,260 kN (280,000 lbf) |
| Specific impulse | 2314 N·s/kg |
| Burn time | 27s |
| Fuel | CTPB |
| First stage - L-140[3] | |
| Length | 19.09 m (62.6 ft) |
| Diameter | 3.80 m (12.5 ft) |
| Gross mass | 165.89 tonnes (182.86 tons) |
| Engines | Viking 2B |
| Thrust | 2,580 kN (580,000 lbf) |
| Specific impulse | 2376 N·s/kg |
| Burn time | 138s |
| Fuel | UH 25 / N2O4 |
| Second stage - L-33[3] | |
| Length | 11.47 m (37.6 ft) |
| Diameter | 2.60 m (8 ft 6 in) |
| Gross mass | 39.41 tonnes (43.44 tons) |
| Engines | Viking 4B |
| Thrust | 784.8 kN (176,400 lbf) (vacuum) |
| Specific impulse | 2851 N·s/kg |
| Burn time | 128.9s |
| Fuel | UH 25 / N2O4 |
| Third stage - H-10[3] | |
| Length | 9.89 m (32.4 ft) |
| Diameter | 2.60 m (8 ft 6 in) |
| Gross mass | 12.74 tonnes (14.04 tons) |
| Engines | HM7B |
| Thrust | 64.2 kN (14,400 lbf) |
| Specific impulse | 4336 N·s/kg |
| Burn time | 729s |
| Fuel | LOX / LH2 |
Ariane 3 was a European expendable carrier rocket, which was used for eleven launches between 1984 and 1989. It was a member of the Ariane family of rockets, derived from the Ariane 2, although it flew before this. It was designed by the Centre National d'Etudes Spatiales, and produced by Aérospatiale in France.[1]:214
The Ariane 3 followed the same basic design as the earlier Ariane 1, but incorporated modifications made for the Ariane 2. Unlike the Ariane 2, two solid-fuelled PAP strap-on booster rockets were used to augment the first stage at liftoff.[3][1]:216-217
The core of the Ariane 3 was essentially an Ariane 2. The first stage was powered by four Viking 2B bipropellant engines, burning UH 25 (25% straight hydrazine, 75% UDMH) in a dinitrogen tetroxide oxidiser. The second stage was powered by a Viking 4B, which used the same fuel-oxidiser combination. The third stage used a cryogenically fuelled HM7B engine, burning liquid hydrogen in liquid oxygen. On some flights, a Mage 2 kick motor was flown as a fourth stage.
Launch history
The Ariane 3 made its maiden flight on 4 August 1984, almost two years before Ariane 2 from which it had been derived, placing the ECS-2 and Télécom 1A satellites into geosynchronous transfer orbit. Eleven were launched with ten successes and one failure. The failure occurred on the fifth flight, launched on 12 September 1985, when the third stage failed to ignite resulting in the rocket failing to achieve orbit. The ECS-3 and Spacenet-3 satellites were lost in the failure.[4][5]
The Ariane 3 was quickly replaced by the more capable Ariane 4, resulting in a comparatively small number of launches. It made its final flight on 12 July 1989, carrying the Olympus F1 satellite.[2][4]
References
- 1 2 3 Harvey, Brian (2003). Europe's Space Programme: To Ariane and Beyond. Berlin: Springer-Verlag. ISBN 1852337222.
- 1 2 Krebs, Gunter. "Ariane-3". Gunter's Space Page. Retrieved 14 June 2015.
- 1 2 3 4 5 "Ariane, Design(1)". b14643.de. Retrieved 13 June 2015.
- 1 2 "Ariane 1-3". Ariane Heritage. Arianespace. Retrieved 13 June 2015.
- ↑ Wade, Mark. "Ariane". Encyclopedia Astronautica. Archived from the original on 13 June 2015. Retrieved 2009-04-27.
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