technically simple and inexpensive, the resources are inexhaustible. However, emission of molecular and/or dissociated hydrogen is problematic. conceivable reactions: The amount of hydrogen emitted is 3 to 4 times higher than for a conventional launch system. Due to the reaction of hydrogen and oxygen/ozone, the amount of water in the atmosphere would be 3 to 4 times higher. Thus, a chemical propulsion system (LH2 / LOX) would be preferable. Helium (He) Helium is quite suitable from technical viewpoint; the required power of about 4 GW is more realistic than for oxygen, nitrogen and argon. The temperature of the combustion chamber of approximately 11000 K might be handled, but magnetic confinement of the jet seems to be necessaiy. The impact on the atmosphere seems to be non-critical: inert gases only react at very high pressure, at atmospheric pressure they are absolutely inert. The production of liquid helium is certainly very expensive. Especially the cost for liquefaction is very high, because the boiling point of helium is
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