Solid propellant rocket stage. Loaded/empty mass 703/68 kg. Thrust 29.40 kN. Vacuum specific impulse 211 seconds.
Cost $ : 3.000 million.
More... - Chronology...
Status: Out of production.
Gross mass: 703 kg (1,549 lb).
Unfuelled mass: 68 kg (149 lb).
Height: 1.98 m (6.49 ft).
Diameter: 0.66 m (2.16 ft).
Span: 0.66 m (2.16 ft).
Thrust: 29.40 kN (6,609 lbf).
Specific impulse: 211 s.
Specific impulse sea level: 211 s.
Burn time: 39 s.
Number: 16 .
P6 SNPE solid rocket engine for Diamant launcher. 29.4 kN. Out of production. Isp=211s. First flight 1965. More...
Associated Launch Vehicles
Rubis French orbital launch vehicle. Two-stage test vehicle consisting of 1 x Agate + 1 x P064. It was designed to test the upper stage and payload elements of the Diamant orbital launcher. These included fairing jettison, spin-up, release, and ignition of the P064 final stage. Six launches were used to validate the design and led to the success of the Diamant on its first flight. The last four launches were made on behalf of CNES to validate payloads for the D1 satellite and carry scientific instruments for the Paris Observatory and Max Planck Institute. More...
Diamant A French orbital launch vehicle. Diamant development could be done relatively quickly using stages and systems being developed for strategic missiles. In May 1962 CNES selected DMA as program manager, with SEREB as the prime contractor. The Diamant orbital launch vehicle was created by replacing the payload of the existing Saphir test vehicle with a new third stage. Prior to any all-up satellite launch attempt the P064 third stage was flight tested on the smaller suborbital Rubis test vehicle. This evolutionary approach paid off. More...
Tibere French 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. More...
Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...
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