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.
These systems are superior to solid propulsion systems in the respects of safety, throttling, restartability, and environmental cleanliness.
Hybrid systems are slightly more complex than solids, but the reduction of safety, storage and transport issues may be an offsetting factor.
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