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Reference Terms
from Wikipedia, the free encyclopedia

Hybrid rocket

A hybrid rocket propulsion system comprises propellants of two different states of matter, the most common configuration being a rocket engine composed of a solid propellant lining a combustion chamber into which a liquid or gaseous propellant is injected so as to undergo a strong exothermic reaction to produce hot gas that is emitted through a De Laval nozzle for propulsive purposes.

Note:   The above text is excerpted from the Wikipedia article "Hybrid rocket", which has been released under the GNU Free Documentation License.
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