Encyclopedia Astronautica
Martlet 4C


Solid propellant rocket stage. Loaded/empty mass 90/20 kg. Thrust 5.39 kN. Vacuum specific impulse 300 seconds.

Status: Development ended 1966.
Gross mass: 90 kg (198 lb).
Unfuelled mass: 20 kg (44 lb).
Height: 1.22 m (4.00 ft).
Diameter: 0.42 m (1.37 ft).
Span: 0.42 m (1.37 ft).
Thrust: 5.39 kN (1,212 lbf).
Specific impulse: 300 s.
Specific impulse sea level: 210 s.
Burn time: 19 s.
Number: 2 .

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Associated Countries
Associated Engines
  • Martlet 4-3 Bull solid rocket engine. 5.390 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...

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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