Abstract In Sect.  1.3.1 , we found out that there are limits to the obtainable payload mass because of the finite structural mass. This limit is crucial for the construction of a rocket. If a rocket is to reach the low Earth orbit, a propulsion demand of about 9 km s−1 has to be taken into account (see end of Sect.  6.4.7 ), which is at the limit of feasibility for today’s chemical propulsions. If a higher payload ratio beyond 3% is required, or the S/C needs to leave the gravitational field of the Earth requiring a higher propulsion demand, one has to take measures to increase the rocket efficiency.


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    Title :

    Rocket Staging


    Contributors:

    Published in:

    Edition :

    3rd ed. 2018


    Publication date :

    2018-01-01


    Size :

    19 pages




    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English





    Optimum staging of solid-propellant rocket vehicles

    Thackwell, Jr., H.L. / Vandenkerckhove, J.A. | Engineering Index Backfile | 1961