| 摘要 |
A missile comprises a propulsion system, a passageway (1) for delivering air to the propulsion system and a ducting element (9) associated with the passageway (1). The ducting element (9) has a ducting surface for ducting air into the passageway (1), and the ducting element (9) is rotatable, about an axis (13) that is aligned, or more preferably co-axial, with the axis (19) of the passageway (1), from a stowed position in which the ducting surface is received in the passageway (1), to a deployed position in which the ducting surface protrudes from the passageway (1) to duct air into the passageway. |
