The principal components, i.e., the combustion chamber and the nozzle, of the thrust chamber of a rocket engine are presented and discussed together with their performance parameters. Injectors, engine cycles, and igniters are discussed. Methods are given for their quantitative design. Cooling systems and combustion stabilising devices are also presented.


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    Title :

    The Thrust Chamber Assembly


    Additional title:

    Springer Aerospace Techn.


    Contributors:


    Publication date :

    2020-09-27


    Size :

    140 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English





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