| 摘要 |
The subject of the invention is a device for launching a drone from a carrier in flight, said drone comprising a fuselage (10) with a longitudinal axis XX', a main wing (12) with a longitudinal axis YY' and a rear empennage (14), characterized in that it comprises: a main wing (12) mounted with the ability to rotate from a retracted position in which said main wing (12) has its longitudinal axis YY' parallel to the longitudinal axis XX' of the fuselage into a deployed position in which the said main wing (12) has its longitudinal axis YY' parallel to the longitudinal axis XX' of the fuselage, motorized means of pivoting said main wing (12), means of locking the main wing (12) in the deployed second position, and launch means (16) able to adopt two positions, a retaining position (16-1), the other being a release position. |
