Eine Trägerrakete mit einem eine Längsachse (Z, Z') aufweisenden Raketenkörper (2; 102), der zumindest eine von einem vorwiegend parallel zur Längsachse (Z, Z') wirksamen Rückstoßantrieb (36; 136) antreibbare Antriebsstufe (3; 103) aufweist zeichnet sich dadurch aus, dass eine mit dem Raketenkörper (2; 102) und / oder der Antriebsstufe (3; 103) gekoppelte oder koppelbare und davon entkoppelbare Startstufe (5; 105) vorgesehen ist, die eine Mehrzahl von mittels jeweils eines Rotorantriebs (33; 133) antreibbaren äußeren Rotoren (34; 134) aufweist, deren jeweilige Rotorachse (ZRI, Z'RI) im Wesentlichen parallel zur Längsachse (Z, Z') des Raketenkörpers (2; 102) ausgerichtet ist und die nach Art eines Multikopters radial außerhalb des Raketenkörpers (2; 102) diesen umgebend angeordnet sind.

    The invention relates to a launch vehicle comprising a rocket body (2; 102) that has a longitudinal axis (Z, Z'), which rocket body has at least one propulsion stage (3; 103) that can be propelled by a jet propulsion means (36; 136) that acts predominantly in parallel with the longitudinal axis (Z, Z'), the launch vehicle being provided with a plurality of rotors that can be driven in each case by a rotor drive, the rotor axis of each rotor being oriented substantially in parallel with the longitudinal axis of the rocket body. The launch vehicle is characterised in that: a separate take-off stage (5; 105) is provided which is or can be coupled to the rocket body (2; 102) and/or the propulsion stage (3; 103), and uncoupled therefrom, which take-off stage comprises a plurality of external rotors (52); the external rotors (52) are situated radially outside and so as to surround the rocket body (2; 102) in the manner of a multicopter; the particular rotor drive (53) comprises at least one electric motor as a drive machine; the take-off stage (5; 105) is provided with at least one power storage means (58; 158) for storing electrical energy and for supplying electrical energy to the external rotor drives (53); and during autorotation of the external rotors (52) at least some of the rotor drives (53) can be operated in a generator mode in which electrical energy can be generated; and the relevant rotor drives (53) are designed to return the generated electrical energy into the particular associated power storage means (58; 158).


    Access

    Download


    Export, share and cite



    Title :

    Trägerrakete und Verfahren zum Betreiben einer Trägerrakete


    Contributors:

    Publication date :

    2022-09-01


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    German


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS