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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    Titel :

    Rocket Staging


    Beteiligte:
    Walter, Ulrich (Autor:in)

    Erschienen in:

    Ausgabe :

    3rd ed. 2018


    Erscheinungsdatum :

    2018-01-01


    Format / Umfang :

    19 pages




    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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