Hypergolic Propellant


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The following article is from The Great Soviet Encyclopedia (1979). It might be outdated or ideologically biased.

Hypergolic Propellant

 

a two-component liquid rocket propellant that ignites when the two components (oxidizer and fuel) come into contact. For example, the oxidizer may be nitrogen tetroxide or a nitric acid oxidizer, and the fuel may be kerosine, hydrazine, or unsymmetrical dimethylhydra-zine. The use of hypergolic propellants simplifies the design of liquid-propellant rocket engines and improves engine reliability, since an ignition system is no longer necessary. Launching of the rocket is also facilitated by the more stable burning characteristics of the propellant.

The Great Soviet Encyclopedia, 3rd Edition (1970-1979). © 2010 The Gale Group, Inc. All rights reserved.
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