Encyclopedia Astronautica
Diamant BP-2


Solid propellant rocket stage. Loaded/empty mass 4,500/1,000 kg. Thrust 176.00 kN. Vacuum specific impulse 273 seconds.

Cost $ : 1.000 million.

AKA: P-4.
Status: Retired 1975.
Gross mass: 4,500 kg (9,900 lb).
Unfuelled mass: 1,000 kg (2,200 lb).
Height: 2.60 m (8.50 ft).
Diameter: 1.50 m (4.90 ft).
Span: 1.50 m (4.90 ft).
Thrust: 176.00 kN (39,566 lbf).
Specific impulse: 273 s.
Specific impulse sea level: 240 s.
Burn time: 55 s.
Number: 45 .

More... - Chronology...


Associated Countries
Associated Engines
  • P4 SNPE solid rocket engine. 176.5 kN. Out of Production. Isp=273s. Used on Diamant B launch vehicle. First flight 1970. 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...
  • MSBS M1 French intermediate range ballistic missile. Two stage vehicle consisting of 1 x SEP 901 + 1 x Rita I 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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