- Historical Background
- CNES began studying designs for an Ariane 5 vehicle in 1977 as a derivative of the proposed Ariane 4 vehicle with a cryogenic second stage. This concept was abandonned in 1984 in favor of a completely new vehicle with a cryogenic core stage and large solid strap on boosters. The vehicle was to be man-rated in order to loft the Hermes space plane to low Earth orbit. This design was upgraded several times in the following years as the launch mass of Hermes grew to up to 22 t.
- ESA took over the program for preliminary study in January 1985 and full development in November 1987.
- The cancellation of the Hermes space plane in 1992 did not affect the program which is intended to provide autonomous access to space for Europe beyond the phasing out of the Ariane 4 in 2000.
- First qualification flight failed on June 4, 1996.
- Second and third qualification flights are planned for fall 1997 and early 1998. Arianespace is to take over operations by mid 1998.
- Improvements are planned to be introduced progressively to increase launch performances from 1998 to 2000.
- An upgraded Ariane 5E is scheduled for 2003.
- Launch Sites
- Kourou, French Guiana (13° 41′ N / 80° 14′ E)
- Launch Log
- Major References
- The Orbital Launcher Report
- Volume 1
- N°4, N°6, N°7, N°8, N°9, N°10
- Volume 2
- N°1, N°2, N°3, N°4, N°5, N°6, N°7, N°8, N°9, N°10
- Volume 3
- N°1, N°3, N°4, N°6, N°7, N°8, N°9
| Number of Stages | 2 + 2 boosters | |
| Total Length | 45.71 to 51.37 m | depending on upper composite |
| Gross Lift Off Mass | 746,000 kg |
| Designation | EAP (P230) | two units |
| Diameter | 3.05 m | |
| Length | 31.162 m | |
| Total Mass | 277,100 kg | each |
| Propellant | HTPB | |
| Propellant Mass | 237,800 kg | |
| Engine | MPS | one each |
| Burning Time | 130 sec. | |
| Specific Impulse | 271 sec. | vacuum |
| Average Thrust | 4,827 kN | vacuum |
| Maximum Thrust | 6,254 kN | vacuum |
| Designation | EPC (H155) | |
| Diameter | 5.458 m | |
| Length | 30.525 m | |
| Total Mass | 170,300 kg | at H0 |
| Propellant | LH2 + LOx | |
| Propellant Mass | 158,100 kg | at H0 |
| Engine | Vulcain 1 | |
| Burning Time | 589 sec. | after liftoff (7 sec. before) |
| Specific Impulse | 431.2 sec. | vacuum |
| Average Thrust | 1,114 kN | vacuum |
| Designation | EPS (L9) | |
| Diameter | 5.460 m | with Vehicle Equipment Bay |
| Length | 3.356 m | |
| Total Mass | 12,500 kg | with Vehicle Equipment Bay |
| Propellant | MMH + N2O4 | |
| Propellant Mass | 9,700 kg | |
| Engine | Aestus | |
| Burning Time | 1,100 sec. | |
| Specific Impulse | 324 sec. | vacuum |
| Average Thrust | 29 kN | vacuum |
| Diameter | 4.5 m / 4.561 m | internal / external |
| Length | 3.244 m |
| Diameter | 5.375 m / 5.435 m | internal / external |
| Length | 4.16 m / 5.66 m | short / long versions |
| Diameter | 4.57 m / 5.425 m | internal / external |
| Length | 12.728 m / 17 m | short / long versions |
| 18,000 kg |
500 km, 28.5° |
| > 10,000 kg |
800 km, 98.6° |
| 6,800 kg / 5,970 kg |
580 x 35,786 km, 7° | single launch / dual launch |
| European Space Agency (ESA) |
| Centre National d’Etudes Spatiales (CNES) |
| Arianespace |
| Aerospatiale Espace & Defense |
| Aerospatiale Espace & Defense | EPC, EAP, Flight Programs |
| Matra Marconi Space (MMS) | Vehicle Equipment Bay |
| Daimler-Benz Aerospace (DASA) | EPS, Aestus, Vulcain 1 Combustion Chamber |
| Societe Europeenne de Propulsion (SEP) | Vulcain 1 |
| Europropulsion | MPS |
| Oerlikon-Contraves | Payload Fairings |
| Dornier Satellitensysteme | Speltra, Sylda 5 |
| CASA | Payload Adaptors |
| Saab Ericsson Space | Payload Adaptors |
| MAN Technologie | EAP Structures |
| Cryospace | EPC Cryogenic Tanks |
| Volvo Aero | Vulcain 1 Exhaust Nozzle and Turbines |
| Dassault Aviation | Pyrotechnics |
Homepage | Top of the Page | Launch Vehicles | Operational Systems
© Takyon International 1997.