The present invention relates to an actuating system for a wing arrangement (3) for an aircraft (1). The arrangement (3) includes a wing (9) comprising a base section (11) having a first end portion (11a) adapted to be secured to the fuselage (5) of an aircraft (1) and an opposite second end portion (11b), and a tip section (13) having a third end portion (13a) and an opposite fourth end portion (13b), wherein the third end portion (13a) is pivotably connected to the second end portion (11b) such that the tip section (13) is pivotable about a pivot axis (17) between a deployed position and a stowed position in which the spanwise length of the wing (9) is smaller than in the deployed position. The actuating system (21) comprises an actuating arrangement (23) which comprises an actuator (25), a first coupling part (29) and a second coupling part (31). The first coupling part (29) is adapted to be coupled to the base section (11), the second coupling part (31) is adapted to be coupled to the tip section (13) and the actuator (25) is operable to move the second coupling part (31) with respect to the first coupling part (29) between a first position and a second position, such that when the first coupling part (29) is coupled to the base section (11) and the second coupling part (31) is coupled to the tip section (13) the actuating arrangement (23) is operable to selectively move, by operating the actuator (25), the tip section (13) between the deployed position and the stowed position. In the first position of the second coupling part (31) the tip section (13) is in the deployed position, and in the second position of the second coupling part (31) the tip section (13) is in the stowed position. The actuating system (21) further comprises a heating arrangement (33) which is positioned and adapted to be operable to heat at least one portion of the actuating arrangement (23) such that at least for ambient temperatures below a predetermined temperature the required work to be effected by the actuator (25) when moving the second coupling part (31) between the first position and the second position is lower than without heating the at least one portion.
Приводная система для приведения в движение складываемой концевой части консоли крыла для летательного аппарата
2020-05-18
Patent
Electronic Resource
Russian
IPC: | B64C AEROPLANES , Flugzeuge |
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