A launch vehicle with a rocket body (2; 102) having a longitudinal axis (Z, Z'), which rocket body has at least one propulsion stage (3; 103) which can be driven by a reaction propulsion system (36; 136) acting predominantly parallel to the longitudinal axis (Z, Z'), wherein the launch vehicle is provided with a plurality of rotors each drivable by means of a rotor drive, the respective rotor axis of which is aligned substantially parallel to the longitudinal axis of the rocket body, wherein the launch vehicle comprises a separate takeoff stage (5; 105) coupled to or couplable to and decouplable from the rocket body (2; 102) and/or the propulsion stage (3; 103), said takeoff stage comprising the plurality of outer rotors, wherein the outer rotors are arranged in the manner of a multicopter radially outside the rocket body (2; 102) surrounding it and wherein the respective rotor drive has at least one electric drive motor as drive engine, wherein the propulsion stage forms a main propulsion stage (3; 103) which is coupled to or can be coupled to and decoupled from the rocket body (2; 102) and/or an upper stage (4; 104) of the launch vehicle (1; 101), which upper stage (4; 104) has at least one reaction propulsion system (43; 143), wherein the main propulsion stage (3; 103) has at least one reaction propulsion system (36; 136) and a plurality of inner rotors (34; 134) each of which can be driven by means of a rotor drive (33; 133) and whose respective rotor axis (Z RI, Z' RI) is aligned essentially parallel to the longitudinal axis (Z, Z') of the rocket body (2; 102), and which are arranged annularly around the longitudinal axis (Z, Z') in the manner of a multicopter, and wherein the takeoff stage (5; 105) is provided with at least one power storage device (58; 158) for storing electrical energy and for supplying electrical energy to the outer rotor drives, and wherein at least some of the rotor drives can be operated in a generator mode, in which electrical energy can be generated, during an autorotation of the outer rotors, and wherein the respective rotor drives are designed to feed the electrical energy generated back into the respectively associated power storage device (58; 158). wherein the launch vehicle is provided with a plurality of rotors each drivable by means of a rotor drive, the respective rotor axis of which is aligned substantially parallel to the longitudinal axis of the rocket body, wherein the launch vehicle comprises a separate takeoff stage (5; 105) coupled to or couplable to and decouplable from the rocket body (2; 102) and/or the propulsion stage (3; 103), said takeoff stage comprising the plurality of outer rotors, wherein the outer rotors are arranged in the manner of a multicopter radially outside the rocket body (2; 102) surrounding it and wherein the respective rotor drive has at least one electric drive motor as drive engine, wherein the propulsion stage forms a main propulsion stage (3; 103) which is coupled to or can be coupled to and decoupled from the rocket body (2; 102) and/or an upper stage (4; 104) of the launch vehicle (1; 101), which upper stage (4; 104) has at least one reaction propulsion system (43; 143), wherein the main propulsion stage (3; 103) has at least one reaction propulsion system (36; 136) and a plurality of inner rotors (34; 134) each of which can be driven by means of a rotor drive (33; 133) and whose respective rotor axis (Z RI, Z' RI) is aligned essentially parallel to the longitudinal axis (Z, Z') of the rocket body (2; 102), and which are arranged annularly around the longitudinal axis (Z, Z') in the manner of a multicopter, and wherein the takeoff stage (5; 105) is provided with at least one power storage device (58; 158) for storing electrical energy and for supplying electrical energy to the outer rotor drives, and wherein at least some of the rotor drives can be operated in a generator mode, in which electrical energy can be generated, during an autorotation of the outer rotors, and wherein the respective rotor drives are designed to feed the electrical energy generated back into the respectively associated power storage device (58; 158).