Encyclopedia Astronautica
Sanger II-1

Mach 6.6 rocket launch aircraft. Winged scramjet using LH2 propellant. Loaded/empty mass 254,000/156,000 kg. Thrust 1,500.00 kN. Specific impulse 1200 seconds. Releases Horus @M 6.6 @ 37 km altitude @ 3100 km range

Cost $ : 10.000 million. No Engines: 6.

Status: Study 1985.
Gross mass: 254,000 kg (559,000 lb).
Unfuelled mass: 156,000 kg (343,000 lb).
Height: 84.50 m (277.20 ft).
Diameter: 14.00 m (45.00 ft).
Span: 41.40 m (135.80 ft).
Thrust: 1,500.00 kN (337,212 lbf).
Specific impulse: 1,200 s.
Specific impulse sea level: 3,600 s.
Burn time: 6,565 s.

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Associated Countries
Associated Engines
Associated Launch Vehicles
  • Saenger II Proposed two stage to orbit vehicle. Air-breathing hypersonic first stage and delta wing second stage. The German Hypersonics Programme and its Saenger II reference vehicle received most of the domestic funding for spaceplane development in the late 1980s and early 1990s. More...

Associated Propellants
  • Air/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. Liquid hydrogen has not been used as a fuel for aircraft to date due to its big drawbacks - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. It is mainly proposed in air-breathing engines for high-speed scramjet aircraft, and mixed propulsion single-stage-to-orbit designs, where use of hydrocarbon propellants creates coking and other issues. More...

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