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Aigle
Test vehicle. Country: France. Status: Retired 1965.

Series of Experimental Vehicles (VE's), each named after precious stones, leading to the MSBS/SSBS solid propellant missiles that made up the French nuclear deterrent.

In 1959 French President de Gaulle approved development of a national deterrent force that included silo-based and submarine-based solid propellant ballistic missiles. A series of test rockets, based on available French solid propellant motors, would be necessary to prove thrust vectoring, solid propellant chemistry, control, guidance, and re-entry vehicles for the operational missiles. In September 1959 SEREB (Societe pour l'Etude et la Realisation d'Engins Balistiques) was created as a private company for development of these test vehicles and ballistic missiles. A basic ballistic research (EBB) program was carried using a series of Experimental Vehicles (VE's), each named after precious stones. These were flown in the 1960's, with a short-term result being the Diamant, France's interim satellite launch vehicle.

Manufacturer: SEREB. Launches: 32. Failures: 1. Success Rate: 96.88%. First Launch Date: 1960-12-17. Last Launch Date: 1965-05-21. Launch data is: complete. Version:

VE9.

First test rocket in the series leading to French IRBM's. The VE 9 instrumented warhead was boosted twice in 1960 and 1961 by a SEPR 732, motor, 55 cm in diameter. his had been developed as the booster for the SE.4400 Surface-to-Air Missile and was the most powerful French solid propellant motor available at that time.

Payload: 360 kg (790 lb). Apogee: 6.00 km (3.70 mi). Version:

VE10 Aigle. Manufacturer's Designation: VE 10.

The Aigle's simple mission was to allow test of the telemetry equipment that would be used on later instrumented warheads. The first version of the Aigle was a simple fin-stabilised solid rocket propelled by a Stromboli SEPR 737 loaded with 984 kg of 'Plastolite' propellant.

Launches: 4. First Launch Date: 1960-12-17. Last Launch Date: 1961-03-21. Payload: 360 kg (790 lb). Apogee: 20 km (12 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 2,300 kg (5,000 lb). Core Diameter: 0.55 m (1.80 ft). Total Length: 8.00 m (26.20 ft).

  • Stage1: 1 x VE10A Aigle-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 246 kg (542 lb). Motor: 1 x SEPR 737. Thrust (vac): 75.000 kN (16,860 lbf). Burn time: 16 sec. Length: 3.00 m (9.80 ft). Diameter: 0.56 m (1.83 ft). Propellants: Solid.
Version:

VE10A Aigle. Manufacturer's Designation: VE10A.

The VE10A used an improved, lightened version of the Stromboli booster.

Launches: 2. First Launch Date: 1963-03-05. Last Launch Date: 1964-11-02. Apogee: 20 km (12 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 2,300 kg (5,000 lb). Core Diameter: 0.55 m (1.80 ft). Total Length: 8.00 m (26.20 ft).

  • Stage1: 1 x VE10A Aigle-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 246 kg (542 lb). Motor: 1 x SEPR 737. Thrust (vac): 75.000 kN (16,860 lbf). Burn time: 16 sec. Length: 3.00 m (9.80 ft). Diameter: 0.56 m (1.83 ft). Propellants: Solid.
Version:

Agate. Other Designations: VE110.

The Agate was the first of the 'precious stone' series of French rockets leading to the Diamant satellite launcher. The single-stage vehicle used the NA801 Mammouth solid propellant rocket developed originally for the SSBT program. The purpose of the fin-stabilised unguided rocket was to test the recoverable instrument pod planned for later missile tests. The Agate R / VE110RR version was used to develop recovery procedures at sea.

Launches: 12. Failures: 1. First Launch Date: 1961-06-03. Last Launch Date: 1964-04-20. Apogee: 20 km (12 mi). Liftoff Thrust: 186.000 kN (41,814 lbf). Total Mass: 3,200 kg (7,000 lb). Core Diameter: 0.80 m (2.62 ft). Total Length: 8.50 m (27.80 ft).

  • Stage1: 1 x Rubis. Gross Mass: 2,000 kg (4,400 lb). Empty Mass: 100 kg (220 lb). Motor: 1 x Agate. Thrust (vac): 190.000 kN (42,710 lbf). Burn time: 18 sec. Length: 4.50 m (14.70 ft). Diameter: 0.80 m (2.62 ft). Propellants: Solid.
Version:

Topaze VE111.

Topaze was the first guided rocket in the French 'precious stones' series. As such it was the first launched from a pad rather than a ramp. The initial model was the VE111C (short) with the NA802 motor.

Six successful VE111C flights successfully demonstrated the concept. The remaining four VE111C's were flown in the VE111CI version to demonstrate recovery from purposely-induced unstable conditions for the MSBS SLBM.

Launches: 10. First Launch Date: 1962-12-19. Last Launch Date: 1964-12-15. Payload: 410 kg (900 lb). Apogee: 80 km (49 mi). Liftoff Thrust: 120.000 kN (26,970 lbf). Total Mass: 2,900 kg (6,300 lb). Core Diameter: 0.80 m (2.62 ft). Total Length: 7.07 m (23.19 ft).

  • Stage1: 1 x Topaze VE111-1. Gross Mass: 1,500 kg (3,300 lb). Motor: 1 x NA 802 Soleil C. Thrust (vac): 120.000 kN (26,970 lbf). Length: 4.50 m (14.70 ft). Diameter: 0.80 m (2.62 ft). Propellants: N2O4/UDMH.
Version:

Topaze VE111L.

The VE111L (long) used the stretched NA803 motor. The VE111L was successfully demonstrated the thrust vectoring concept over a longer burn period. The last two flights were VE111LG configuration, equipped with all-up inertial navigation systems.

Launches: 4. First Launch Date: 1963-12-21. Last Launch Date: 1965-05-21. Payload: 360 kg (790 lb). Apogee: 110 km (60 mi). Liftoff Thrust: 147.000 kN (33,046 lbf). Total Mass: 3,434 kg (7,570 lb). Core Diameter: 0.80 m (2.62 ft). Total Length: 7.90 m (25.90 ft).

  • Stage1: 1 x Topaze VE111L-1. Gross Mass: 2,200 kg (4,800 lb). Motor: 1 x NA 803 Soleil. Thrust (vac): 156.000 kN (35,070 lbf). Burn time: 44 sec. Length: 4.60 m (15.00 ft). Diameter: 0.80 m (2.62 ft). Propellants: N2O4/UDMH.
VE Chronology

1960 December 17 - Hammaguira Bacchus. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1960 December 19 - Hammaguira Bacchus. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1961 March 16 - Hammaguira Bacchus. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1961 March 21 - Hammaguira Bacchus. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1961 June 3 - Hammaguira Bacchus. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1961 June 7 - Hammaguira Bacchus. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1961 November 13 - Hammaguira Bacchus. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1961 November 17 - Hammaguira Bacchus. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1962 March 19 - Hammaguira Bacchus. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1962 March 23 - Hammaguira Bacchus. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1962 December 19 - Hammaguira Bacchus. Topaze VE111 C3 Test mission Agency: ONERA. Apogee: 80 km (49 mi).

1963 March 5 - Hammaguira Brigitte. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1963 March 22 - Hammaguira Bacchus. Topaze VE111 C4 Test mission Agency: ONERA. Apogee: 80 km (49 mi).

1963 March 28 - Hammaguira Bacchus. Topaze VE111 C7 Test mission Agency: ONERA. Apogee: 80 km (49 mi).

1963 May 18 - Hammaguira Brigitte. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1963 May 21 - Hammaguira Brigitte. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1963 June 21 - Hammaguira Bacchus. Topaze VE111 C9 Test mission Agency: ONERA. Apogee: 80 km (49 mi).

1963 June 27 - Hammaguira Bacchus. Topaze VE111 C8 Test mission Agency: ONERA. Apogee: 80 km (49 mi).

1963 October 24 - Hammaguira Bacchus. Topaze VE111 C10 Test mission Agency: ONERA. Apogee: 80 km (49 mi).

1963 November 19 - Ile du Levant -. Agate R FAILURE: Failure. Test mission Agency: ONERA. Apogee: 0 km ( mi).

1963 November 28 - Ile du Levant -. Agate R Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1963 December 21 - Hammaguira Bacchus. Topaze VE111L L1 Test mission Agency: ONERA. Apogee: 110 km (60 mi).

1964 February 28 - Ile du Levant -. Agate R Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1964 March 11 - Hammaguira Bacchus. Topaze VE111L L2 Test mission Agency: ONERA. Apogee: 110 km (60 mi).

1964 April 20 - Ile du Levant -. Agate R Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1964 June 4 - Hammaguira Bacchus. Topaze VE111 Ci1 MSBS test Agency: ONERA. Apogee: 80 km (49 mi). MSBS stability recovery test

1964 October 21 - Hammaguira Bacchus. Topaze VE111 Ci2 MSBS test Agency: ONERA. Apogee: 80 km (49 mi). MSBS stability recovery test

1964 November 2 - Hammaguira Brigitte. Test mission Agency: ONERA. Apogee: 20 km (12 mi).

1964 December 11 - Hammaguira Bacchus. Topaze VE111 Ci3 MSBS test Agency: ONERA. Apogee: 80 km (49 mi). MSBS stability recovery test

1964 December 15 - Hammaguira Bacchus. Topaze VE111 Ci4 MSBS test Agency: ONERA. Apogee: 80 km (49 mi). MSBS stability recovery test

1965 May 18 - Hammaguira Bacchus. Topaze VE111L LG1 Test mission Agency: ONERA. Apogee: 100 km (60 mi).

1965 May 21 - Hammaguira Bacchus. Topaze VE111L LG2 Test mission Agency: ONERA. Apogee: 100 km (60 mi).

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Topaze