Encyclopedia Astronautica
P6


SNPE solid rocket engine for Diamant launcher. 29.4 kN. Out of production. Isp=211s. First flight 1965.

Thrust (sl): 29.400 kN (6,609 lbf). Thrust (sl): 3,000 kgf.

Status: Out of production.
Gross mass: 800 kg (1,760 lb).
Unfuelled mass: 120 kg (260 lb).
Height: 2.07 m (6.79 ft).
Diameter: 1.50 m (4.90 ft).
Thrust: 29.40 kN (6,609 lbf).
Specific impulse: 211 s.
Specific impulse sea level: 211 s.
Burn time: 45 s.
Number: 9 .

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Associated Countries
See also
Associated Launch Vehicles
  • Diamant French orbital launch vehicle. In December 1961 France decided to demonstrate an indigenous satellite-launch capability, using stages in development for its ballistic missile program. Following careful evolutionary development, Diamant was successful on its first attempt in 1965. Improved versions were flown over the next ten years. More...
  • 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...

Associated Manufacturers and Agencies
  • SNPE French manufacturer of rocket engines. Societe Nationale des Poudres et Explosifs, France. 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...

Associated Stages
  • Diamant B-3 Solid propellant rocket stage. Loaded/empty mass 800/120 kg. Thrust 50.00 kN. Vacuum specific impulse 211 seconds. More...
  • Diamant-3 Solid propellant rocket stage. Loaded/empty mass 703/68 kg. Thrust 29.40 kN. Vacuum specific impulse 211 seconds. More...

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