Solid propellant rocket stage. Loaded/empty mass 300/25 kg. Thrust 25.00 kN. Vacuum specific impulse 287 seconds.
Cost $ : 0.750 million.
Status: Retired 1972.
Gross mass: 300 kg (660 lb).
Unfuelled mass: 25 kg (55 lb).
Height: 1.48 m (4.85 ft).
Diameter: 0.50 m (1.64 ft).
Span: 0.50 m (1.64 ft).
Thrust: 25.00 kN (5,620 lbf).
Specific impulse: 287 s.
Specific impulse sea level: 250 s.
Burn time: 31 s.
Number: 3 .
More... - Chronology...
Associated Countries
Associated Engines
-
FW-4D Thiokol solid rocket engine. 25 kN. Isp=287s. Kick stage motor for Delta E, Delta L. First flight 1965. More...
Associated Launch Vehicles
-
Delta E1 American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E + 1 x FW4D More...
-
Delta L American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor 2 + 1 x LT Thor DSV-2L-1B + 1 x Delta E + 1 x FW4D 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...
Home - Browse - Contact
© / Conditions for Use
