Encyclopedia Astronautica

Air/Lox/LH2 propellant rocket stage. Loaded/empty mass 263,000/42,319 kg. Thrust 1,300.00 kN. Specific impulse 425 seconds. Engine thrust, burn time estimated.

No Engines: 2.

Status: Development ended 1995.
Gross mass: 263,000 kg (579,000 lb).
Unfuelled mass: 42,319 kg (93,297 lb).
Height: 82.00 m (269.00 ft).
Diameter: 6.25 m (20.50 ft).
Span: 25.00 m (82.00 ft).
Thrust: 1,300.00 kN (292,200 lbf).
Specific impulse: 425 s.
Specific impulse sea level: 2,000 s.
Burn time: 1,200 s.

More... - Chronology...

Associated Countries
Associated Engines
  • Sabre Rolls Royce air augmented rocket engine. Used Air/Lox/LH2. Developed -1995. Isp=700s. In development for Skylon launch vehicl; descendent of RB545 developed for abandoned HOTOL space launcher. More...

Associated Propellants
  • Air/Lox/LH2 Ambient air (78 % nitrogen, 21% oxygen, etc.) is scooped up by air intakes and used in turbojet, turbofan, ramjet, scramjet, or other airbreathing engines as an oxidiser. In this variant the motor converts to pure rocket propulsion, using on-board liquid oxygen for the final push to orbit. More...

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