A detachable leading edge skin panel 2, forms part of a leading edge of an aerodynamic structure, such as an aircraft wing. The panel has a primary attachment component (fig.1,12) configured to prevent spanwise movement between the panel and the structure, and one or more secondary attachment components (fig.1,13) configured to permit a predetermined amount of spanwise movement between the panel and the structure. Each component may have a lug 221 and a pin 222, attaching, and transmitting load, to corresponding ribs 28 in the aircraft wing. The primary component may have a locking mechanism to prevent movement of the pin relative to the rib. The secondary components may have a sliding bearing to permit axial movement of the pin, and may also prevent movement in directions orthogonal to the spanwise direction. The primary and secondary components may be attached to an additional rib, i.e. a rib clevis, which they may move relative to in a spanwise direction. The panel and attachment components may be metallic with the attachment components bonded to an inner panel surface. Alternatively, they may be formed from a composite material with the attachment components formed integrally with the panel or attached by a hyperjoint.
Leading edge skin structure
2019-01-02
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |