| 摘要 |
The invention relates to an aircraft propulsion assembly (1) including a turbojet pod (3) wherein said pod includes a stationary structure and a movable structure (7), including: a thrust reversal device (9) including at least one cover (15) translatable along a substantially longitudinal axis (17) of the pod between a retracted position, corresponding to a direct jet operation of the pod, and a deployed position, corresponding to a reverse jet position of the pod; and a secondary air flow exhaust nozzle (11) including a device (33) for electrically controlling and actuating said nozzle. The propulsion assembly according to the invention is characterized in that the device for controlling and actuating the nozzle includes at least one electrical switch (37) suitable for being closed during a direct jet operation of the pod and moreover suitable for being open during a reverse jet operation of the pod. Said switch includes at least one stationary connector (39) and at least one movable connector (41). |
