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Berenice
Sounding rocket. Country: France. Status: Retired 1972.

Berenice was Onera's successor to the Antares re-entry vehicle test booster. It was nearly double the mass of Antares.

The first two stages lofted the vehicle to a 270 km altitude. The expended second stage, stabilized by an aerodynamic fins remained attached to the upper stages until an altitude of 55 km was reached. Then the second stage was jettisoned, the third stage fired, and the test RV was accelerated to a speed of Mach 12 at 20 km altitude. The 4 stage vehicle consisting of 4 x SEPR P167(4 X 34 kN) stabilisation rockets around + 1 x Stromboli SEPR 739 + 1 x SEPR 740 + 1 x Tramontane + 1 x Melanie

Manufacturer: ONERA. Launches: 20. Failures: 1. Success Rate: 95.00%. First Launch Date: 1962-06-27. Last Launch Date: 1972-03-18. Launch data is: complete. Payload: 40 kg (88 lb). Apogee: 1,000 km (600 mi). Liftoff Thrust: 170.000 kN (38,210 lbf). Total Mass: 3,340 kg (7,360 lb). Core Diameter: 0.56 m (1.83 ft). Total Length: 13.25 m (43.47 ft).

  • Stage1: 1 x Berenice-1. Gross Mass: 1,900 kg (4,100 lb). Empty Mass: 700 kg (1,540 lb). Motor: 1 x Stromboli. Thrust (vac): 170.000 kN (38,210 lbf). Burn time: 20 sec. Length: 4.70 m (15.40 ft). Diameter: 0.56 m (1.83 ft). Propellants: Solid.
  • Stage2: 1 x Berenice-2. Gross Mass: 1,050 kg (2,310 lb). Empty Mass: 310 kg (680 lb). Motor: 1 x SEPR 740. Thrust (vac): 91.700 kN (20,615 lbf). Burn time: 18 sec. Length: 3.80 m (12.40 ft). Diameter: 0.56 m (1.83 ft). Propellants: Solid.
  • Stage3: 1 x Berenice-3. Gross Mass: 280 kg (610 lb). Empty Mass: 124 kg (273 lb). Motor: 1 x Tramontane. Thrust (vac): 50.000 kN (11,240 lbf). Burn time: 6.70 sec. Length: 2.40 m (7.80 ft). Diameter: 0.33 m (1.08 ft). Propellants: Solid.
  • Stage4: 1 x Melanie. Gross Mass: 100 kg (220 lb). Empty Mass: 40 kg (88 lb). Motor: 1 x Melanie. Thrust (vac): 38.000 kN (8,542 lbf). Burn time: 4.40 sec. Length: 3.00 m (9.80 ft). Diameter: 0.22 m (0.72 ft). Propellants: Solid.
Version:

Berenice Satmos. Orbital launch vehicle. Status: Study 1963.

In April 1963, ONERA proposed using a modified Berenice suborbtial test vehicle to place a small 3.5 kg satellite ('Satmos') into a 250 x 1800 km orbit. They claimed this booster could be ready in 1964, one year before Diamant. However the given the marginal growth potential of such a design, the government decided to stick with Diamant.

Version:

Tacite.

Single stage sounding rocket using a single Stromboli SEPR 739-2 stage with 'Plastoline' propellant. Stabilisation was by four fins and a nitrogen cold-gas spin thrusters.

Launches: 4. Failures: 1. First Launch Date: 1965-06-15. Last Launch Date: 1968-10-15. Payload: 285 kg (628 lb). Apogee: 160 km (90 mi). Liftoff Thrust: 170.000 kN (38,210 lbf). Total Mass: 2,000 kg (4,400 lb). Core Diameter: 0.56 m (1.83 ft). Total Length: 7.80 m (25.50 ft).

  • Stage1: 1 x Tibere-2. Gross Mass: 1,700 kg (3,700 lb). Empty Mass: 455 kg (1,003 lb). Motor: 1 x SEPR 739-2. Thrust (vac): 170.000 kN (38,210 lbf). Burn time: 20 sec. Length: 4.70 m (15.40 ft). Diameter: 0.56 m (1.83 ft). Propellants: Solid.
Version:

Titus.
Titus

Sounding rocket derived from the first two stages of the Berenice test vehicle. The two stage vehicle consisted of 4 x SEPR P167 stabilisation rockets around a Stromboli 739 first stage, topped by a stretched Stromboli SEPR 740-3 second stage with four fins. The launches were made from Chaco in collaboration with the Argentinian agency CNIE.

Launches: 2. First Launch Date: 1966-11-12. Last Launch Date: 1966-11-12. Payload: 400 kg (880 lb). Apogee: 250 km (150 mi). Liftoff Thrust: 170.000 kN (38,210 lbf). Total Mass: 3,400 kg (7,400 lb). Core Diameter: 0.56 m (1.83 ft). Total Length: 11.60 m (38.00 ft).

  • Stage1: 1 x Tibere-2. Gross Mass: 1,700 kg (3,700 lb). Empty Mass: 455 kg (1,003 lb). Motor: 1 x SEPR 739-2. Thrust (vac): 170.000 kN (38,210 lbf). Burn time: 20 sec. Length: 4.70 m (15.40 ft). Diameter: 0.56 m (1.83 ft). Propellants: Solid.
  • Stage2: 1 x Titus-2. Gross Mass: 1,100 kg (2,400 lb). Empty Mass: 372 kg (820 lb). Motor: 1 x SEPR 740-3. Thrust (vac): 170.000 kN (38,210 lbf). Burn time: 20 sec. Length: 3.80 m (12.40 ft). Diameter: 0.56 m (1.83 ft). Propellants: Solid.
Version:

Tibere. Test vehicle.

Tibere was an atmospheric re-entry test vehicle derived from the earlier Berenice. Development was authorized in 1965 to support the Electre re-entry experiment program. The first two stages were Stromboli motors of identical length. The third stage was the P.064 motor developed for the Diamant orbital launcher. As with Berenice and Titus, four SEPR P167 stabilization rockets surrounded the first stage. The first two stages boosted the third stage and RV model to 150 km altitude. A Cassiopee attitude control system oriented the RV precisely before the P.064 accelerated the RV to high speed while descending from 130 to 60 km altitude. Although four Tibere were procured, only two were launched before the program was closed.

Launches: 2. First Launch Date: 1971-02-23. Last Launch Date: 1972-03-18. Apogee: 1,000 km (600 mi). Liftoff Thrust: 170.000 kN (38,210 lbf). Total Mass: 4,500 kg (9,900 lb). Core Diameter: 0.56 m (1.83 ft). Total Length: 14.50 m (47.50 ft).

  • Stage1: 1 x Tibere-2. Gross Mass: 1,700 kg (3,700 lb). Empty Mass: 455 kg (1,003 lb). Motor: 1 x SEPR 739-2. Thrust (vac): 170.000 kN (38,210 lbf). Burn time: 20 sec. Length: 4.70 m (15.40 ft). Diameter: 0.56 m (1.83 ft). Propellants: Solid.
  • Stage2: 1 x Tibere-2. Gross Mass: 1,700 kg (3,700 lb). Empty Mass: 455 kg (1,003 lb). Motor: 1 x SEPR 739-2. Thrust (vac): 170.000 kN (38,210 lbf). Burn time: 20 sec. Length: 4.70 m (15.40 ft). Diameter: 0.56 m (1.83 ft). Propellants: Solid.
  • Stage3: 1 x Diamant-3. Gross Mass: 703 kg (1,549 lb). Empty Mass: 68 kg (149 lb). Motor: 1 x P6. Thrust (vac): 29.400 kN (6,609 lbf). Isp: 211 sec. Burn time: 39 sec. Length: 1.98 m (6.49 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.
Berenice Chronology

1962 June 27 - Ile du Levant -. Berenice 001 Re-entry Vehicle test Agency: ONERA. Apogee: 270 km (160 mi).

1962 Q3 - Ile du Levant -. Berenice 003 Re-entry Vehicle test Agency: ONERA. Apogee: 270 km (160 mi).

1962 July 6 - Ile du Levant -. Berenice 002 Re-entry Vehicle test Agency: ONERA. Apogee: 270 km (160 mi).

1962 November 1 - Ile du Levant -. Berenice 004 Re-entry Vehicle test Agency: ONERA. Apogee: 270 km (160 mi).

1963 June 27 - Ile du Levant -. Berenice 005 Re-entry Vehicle test Agency: ONERA. Apogee: 270 km (160 mi).

1963 July 3 - Ile du Levant -. Berenice 006 Re-entry Vehicle test Agency: ONERA. Apogee: 270 km (160 mi).

1964 - Ile du Levant -. Berenice 008 Re-entry Vehicle test Agency: ONERA. Apogee: 270 km (160 mi).

1964 - Ile du Levant -. Berenice 007 Re-entry Vehicle test Agency: ONERA. Apogee: 270 km (160 mi).

1964 October 1 - Ile du Levant -. Berenice 009 Re-entry Vehicle test Agency: ONERA. Apogee: 250 km (150 mi).

1964 October 1 - Ile du Levant -. Berenice 010 Re-entry Vehicle test Agency: ONERA. Apogee: 250 km (150 mi).

1965 - Ile du Levant -. Berenice 011 Re-entry Vehicle test Agency: ONERA. Apogee: 270 km (160 mi).

1965 June 15 - 00:00 GMT - Biscarosse -. Tacite TACITE 01 Infrared Horizon Study Aeronomy mission Agency: ONERA. Apogee: 182 km (113 mi).

1966 - Ile du Levant -. Berenice 012 Titus test / solar mission Agency: ONERA. Apogee: 270 km (160 mi).

1966 November 12 - Las Palmas -. Titus 001 FU-150 A Solar Eclipse mission Agency: CNES. Apogee: 274 km (170 mi).

1966 November 12 - 13:42 GMT - Las Palmas -. Titus 002 FU-150 B Solar Eclipse mission Agency: CNES. Apogee: 270 km (160 mi).

1967 November 23 - Ile du Levant -. Tacite 002 FAILURE: Failure. FU-169 X-ray astronomy mission Agency: CNES. Apogee: 0 km ( mi).

1968 May 15 - 00:38 GMT - Ile du Levant -. Tacite TACITE 02 Earth infrared Aeronomy mission Agency: CNES. Apogee: 175 km (108 mi).

1968 October 15 - Ile du Levant -. Tacite 004 Sun pointing test / solar mission Agency: CNES. Apogee: 140 km (80 mi).

1971 February 23 - Biscarosse -. ELECTRE Re-entry Vehicle test Agency: ONERA. Apogee: 130 km (80 mi).

1972 March 18 - Biscarosse -. ELECTRE Re-entry Vehicle test Agency: ONERA. Apogee: 159 km (98 mi).

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