| 摘要 |
The hole is equipped with a detachable cover plate (5) and filler plate (6). The filler plate provides compressive stress continuity through edge contact with the hole. Cover plate and filler plate have flanges (26, 27) pinching the panel. The filler plate has openings in the region of its peripheral reinforcement, resting against the edge of the hole. These openings are provided for attachment screws. The filler plate occupies the hole in the panel with minimal play (9). Any play is made good by deformation of the panel when subjected to compression, especially when the aircraft flies. The shape of the hole is oval. The compressive stress is orientated along the longer axis (13) of the oval. When used in an aircraft, the ratio of maximum radii is preferably 2. The filer plate itself includes a hole (18). It is slightly plastic, for example, it is made of composite materials, especially a layer of carbon fibers and/or laminated material. One flange includes a seal (22). One flange is connected to the panel or plate by a jointing groove. The panel has a thinner central zone for stress relief, offset closer to one face of the panel. Materials of construction are in aluminum, titanium or a composite. Connection is made by screwing or adhesion. The plate is chamfered or located using a cheek construction. |
