Encyclopedia Astronautica
Rook IIIA


Solid rocket stage. 300.00 kN (67,443 lbf) thrust. Mass 1,057 kg (2,330 lb).

AKA: Rook.
Status: Retired 1974.
Gross mass: 1,057 kg (2,330 lb).
Unfuelled mass: 186 kg (410 lb).
Height: 5.40 m (17.70 ft).
Diameter: 0.44 m (1.44 ft).
Thrust: 300.00 kN (67,440 lbf).
Burn time: 5.50 s.
Number: 28 .

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Associated Countries
Associated Engines
  • Rook Royal Ordnance solid rocket engine. 300 kN. Out of production. Fast-burning version of Raven. Rook was fired 70 times altogether, in 65 flights and 16 different vehicle designs. More...

Associated Launch Vehicles
  • Jaguar 2 Three stage version consisting of 1 x Rook IIIA + 1 x Goldfinch II + 1 x Gosling IV More...
  • Jabiru 2 The Rook motor was 0.43 m in diameter and 5.28 m long. It contained a case-bonded charge of 846 kg of non-aluminized plastic propellant giving a total impulse of 1760 kN-seconds in 5.6 seconds; with a maximum thrust of 323 kN and a specific impulse of 213 seconds. The motor was capable of withstanding the 40g acceleration it provided during firing. It was employed as the first propulsion stage of the Leopard and Jaguar (Jabiru) supersonic test vehicles, and by itself in single-stage test applications. More...
  • Jabiru 3 Two stage version consisting of 1 x Rook IIIA + 1 x Rook IIIB More...

Associated Manufacturers and Agencies
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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