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).
TRÄGERRAKETE UND VERFAHREN ZUM BETREIBEN EINER TRÄGERRAKETE
LAUNCH VEHICLE AND METHOD FOR OPERATING A LAUNCH VEHICLE
VÉHICULE DE LANCEMENT ET PROCÉDÉ DE FONCTIONNEMENT D'UN VÉHICULE DE LANCEMENT
2023-12-13
Patent
Electronic Resource
German
IPC: | B64G Raumfahrt , COSMONAUTICS |
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