| 摘要 |
An aircraft mechanical structural system which provides an improvement to the existing aircraft structure by reinforcing the fuselage frame aluminum skin (3) and fuselage frame (5), without replacement of any of the existing structural elements. The improvement is comprised of high performance, solid fabric (1) fuselage section jackets (13), fuselage frame metal external paneling (4), and a thermal and cryogenic resistant adhesive (23). The jackets (13) are installed between the aluminum skin (3) and fuselage frame metal external paneling (4). The external paneling (4) is installed between the jackets (13) and entire outside surface of the fuselage frame (5). The external paneling (4) provides a solid foundation for the jackets (13) by preventing sagging into openings in the fuselage frame (5). The adhesive (23) bonds the jackets (13) to the aluminum skin (3) and to the external paneling (4). The adhesive (23) prevents premature crimping, abrasion and tearing of the jackets (13), and rivet (22) failure. The adhesive (23) absorbs and dissipates the generated heat, distributing temperatures more evenly across the fuselage structure. The improvement provides physical properties to increase the stiffness and capacity of the airframe to resist high-tension loads generated in high-speed impact accidents and crashes by reducing the probability and extent of fuselage punctures, cuts, tears, breakup, rapid cabin decompression, and subsequent incidence of fire, smoke, toxic gases and explosion. The improvement further includes the potential reduction of pressurization and depressurization cycle stresses during takeoffs and landings which cause metal fatigue and fractures. |
