Solid propellant rocket stage. Loaded/empty mass 890/155 kg. Thrust 67.60 kN. Vacuum specific impulse 300 seconds.
Status: Development ended 1966.
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Gross mass: 890 kg (1,960 lb).
Unfuelled mass: 155 kg (341 lb).
Height: 4.00 m (13.10 ft).
Diameter: 0.42 m (1.37 ft).
Span: 2.20 m (7.20 ft).
Thrust: 67.60 kN (15,197 lbf).
Specific impulse: 300 s.
Specific impulse sea level: 210 s.
Burn time: 30 s.
Number: 2 .
Martlet 4-1 Bull solid rocket engine. 67.7 kN. Development ended 1966. Isp=300s. Used on Martlet 4 launch vehicle. More...
Associated Launch Vehicles
Martlet 4 Canadian gun-launched orbital launch vehicle. The Martlet 4 was ultimate goal of the HARP program - a gun-launched orbital launch vehicle. Two versions were considered: a preliminary version with two solid propellant upper stages, and a later model with two liquid propellant upper stages. Payload of the liquid propellant version would have reached 90 kg. The initial version was in an advanced stage of suborbital flight test when the HARP program was cancelled in 1967. More...
Martlet 3D Canadian sounding rocket. The Martlet 3D concept was intended to serve as a sub-orbital vehicle capable of lifting heavy payloads to satellite altitudes. The Martlet 3D was simply the first stage of the Martlet 4 vehicle ( Martlet 4A) with the two upper stages and the satellite payload being replaced with a single large payload. 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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