An aircraft comprising a wing having a wing tip device (1, figure 1) configurable between a flight configuration and a ground configuration in which the wing span is reduced. The aircraft comprises a lock (13) for locking the wing tip device in the flight configuration, and an actuator (3) for unlocking the lock (13) and subsequently actuating the wing tip device to the ground configuration. The actuator is a two-stage hydraulic actuator, comprising a first hydraulic actuator stage (21) for unlocking the lock and a second hydraulic actuator stage (23) for sequentially actuating the wingtip device. The first and second actuator stages are arranged in series and the second stage is unable to receive hydraulic input feed until the first stage has been actuated to unlock the lock. During the reverse operation, the first stage is not able to receive hydraulic feed to lock the lock until the second stage has been actuated to move the wing tip device to the flight configuration. Preferably the wing tip device rotates upwards about a hinge (9).
A dual-purpose locking and folding arrangement for an aircraft wing tip device
2017-05-31
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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