AbstractThe state-of-the-art liquid propellant cooled combustion chambers utilized in the space shuttle are third-generation designs which have evolved from a continuing demand for higher operating pressure and aircraft-type reusability. History has shown that major advances in cooling occur in approximately ten-year cycles, with each cycle providing a nominal 400% increase in operating pressure and/or a higher degree of reusability.The previous technologies include the first-generation double-wall steel jackets used in the 220 psi V-2 and Aerobee, and the second generation wire-wrapped double tapered tubular assemblies typical of the 800 psi Titan I, II, and III, and 1000 psi F-1 engines. The third-generation designs utilize milled slot, high thermal conductivity liners and electrodeposited nickel closures. The space shuttle main engine operating at 3200 psia is adequate for individual flights; however, the desired goal of 55 service-free missions has yet to be realized.Future single-stage-to-orbit propulsion concepts can benefit from a further increase in operating pressures to 6000 to 10,000 psi combined with engine reuse capabilities in excess of the 55 flight goals of the space shuttle. A fourth-generation approach will be required to attain these more ambitious goals. These new designs will require a combination of cooling processes, including regenerative and transpiration, combined with improved high-temperature materials and new fabrication techniques.The limitations of the third-generation designs, the impact of propellant/coolant selection, and the approaches for the coming fourth-generation cooling technologies are discussed.


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    Titel :

    High-pressure propulsion - advanced concepts for cooling


    Beteiligte:

    Erschienen in:

    Acta Astronautica ; 14 ; 423-438


    Erscheinungsdatum :

    1986-01-01


    Format / Umfang :

    16 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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