Test vehicle. Country: France. Status: Retired 1963. Two stage vehicle consisting of 1 x Emma Booster + 1 x Emma
Manufacturer: Matra. Launches: 8. Failures: 1. Success Rate: 87.50%. First Launch Date: 1963-02-19. Last Launch Date: 1963-10-10. Launch data is: complete. Apogee: 69 km (42 mi). Liftoff Thrust: 0 N ( lbf). Core Diameter: 0.14 m (0.45 ft). Total Length: 3.90 m (12.70 ft).
- Stage0: 1 x Emma-0. Gross Mass: 20 kg (44 lb). Empty Mass: 13 kg (28 lb). Motor: 1 x SEPR P191. Thrust (vac): 14.800 kN (3,327 lbf). Burn time: 1.00 sec. Length: 0.80 m (2.62 ft). Diameter: 0.13 m (0.42 ft). Propellants: Solid.
- Stage1: 1 x Emma-1. Gross Mass: 50 kg (110 lb). Empty Mass: 11 kg (24 lb). Motor: 1 x SEPR P163. Thrust (vac): 1.400 kN (315 lbf). Burn time: 37 sec. Length: 1.70 m (5.50 ft). Diameter: 0.13 m (0.42 ft). Propellants: Solid.
Emma Chronology
1963 February 19 - Hammaguira -. Emma 05 Aeronomy mission Agency: CNES. Apogee: 60 km (37 mi).
1963 February 20 - Hammaguira -. Emma 06 Aeronomy mission Agency: CNES. Apogee: 60 km (37 mi).
1963 February 26 - Hammaguira -. Emma 02 Aeronomy mission Agency: CNES. Apogee: 32 km (19 mi).
1963 February 28 - Hammaguira -. Emma 01 Aeronomy mission Agency: CNES. Apogee: 55 km (34 mi).
1963 May 10 - Hammaguira -. Aeronomy mission Agency: CNES. Apogee: 18 km (11 mi).
1963 May 10 - Hammaguira -. Aeronomy mission Agency: CNES. Apogee: 25 km (15 mi).
1963 October 8 - Hammaguira -. Emma 03 FAILURE: Failure. Aeronomy mission Agency: CNES. Apogee: 2.00 km (1.20 mi).
1963 October 10 - Hammaguira -. Emma 04 Aeronomy mission Agency: CNES. Apogee: 55 km (34 mi).
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