Encyclopedia Astronautica
Diamant B-3


Solid propellant rocket stage. Loaded/empty mass 800/120 kg. Thrust 50.00 kN. Vacuum specific impulse 211 seconds.

Cost $ : 4.000 million.

AKA: P-6.
Status: Out of production.
Gross mass: 800 kg (1,760 lb).
Unfuelled mass: 120 kg (260 lb).
Height: 1.67 m (5.47 ft).
Diameter: 0.80 m (2.62 ft).
Span: 0.80 m (2.62 ft).
Thrust: 50.00 kN (11,240 lbf).
Specific impulse: 211 s.
Specific impulse sea level: 211 s.
Burn time: 46 s.
Number: 12 .

More... - Chronology...


Associated Countries
Associated Engines
  • P6 SNPE solid rocket engine for Diamant launcher. 29.4 kN. Out of production. Isp=211s. First flight 1965. More...

Associated Launch Vehicles
  • Diamant B French orbital launch vehicle. As a follow-on to the Diamant-A, CNES decided to evolve a more capable launch vehicle. The Diamant-B used a new first stage with 50% more propellants and 33% more thrust; the same second stage; and a fatter third stage. Six Diamant-B boosters were ordered. Originally four of these were to be used to test the Europa 2 launch vehicle's Perigee-Apogee System. These tests were cancelled and instead CNES used five of the six boosters for orbital attempts. More...
  • Europa II European orbital launch vehicle. Four stage version of the Europa vehicle, adding a P068 fourth stage. More...
  • Diamant BP.4 French orbital launch vehicle. In January 1972 a further evolution, the Diamant BP.4, was authorized. The second stage was replaced with the P4 Rita motor developed for the MSBS SLBM. The larger 1.38 m diameter fairing developed for the British Black Arrow launcher allowed larger payloads to be accommodated. Three launches of the BP.4 in 1975 completed the Diamant saga. More...

Associated Propellants
  • 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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