초록 ▼

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, soli

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.

대표청구항 ▼

[ What I claim as my invention is:] [1.]1. A reinforcement system for an aircraft comprising a fuselage frame aluminum skin, and fuselage frame aluminum skin being attached to a fuselage frame of said aircraft, wherein the system provides additional reinforcement to said aircraft without replacing a

[ What I claim as my invention is:] [1.]1. A reinforcement system for an aircraft comprising a fuselage frame aluminum skin, and fuselage frame aluminum skin being attached to a fuselage frame of said aircraft, wherein the system provides additional reinforcement to said aircraft without replacing any of its elements, the improvement comprising:(a) one or more fuselage section fabric jackets constructed of a lightweight, high performance solid fabric, with physical properties including: reduced air permeability, high tensile strength, high modulus and stiffness, and resistance to impact, punctures, cuts, tears, wear, fatigue, creep, repeated flexing, stretching, chemicals and corrosion, and thermal resistance to shrinking and cracking at high and low temperature extremes, fire, smoke and toxic gases; and(b) one or more said fuselage section fabric jackets installed between said fuselage frame aluminum skin and fuselage frame metal external paneling, covering one or more fuselage sections of entire said fuselage frame of said aircraft; and(c) said fuselage frame metal external paneling installed between said fuselage section fabric jackets and outside surface of entire said fuselage frame of said aircraft; and(d) an adhesive, bonding said fuselage section fabric to said fuselage frame aluminum skin and to said fuselage metal external paneling, preventing premature crimping, abrasion and tearing of said fuselage section fabric jackets, and rivet failure; and(e) an installation completed by riveting through in sequence: said fuselage frame aluminum skin, said adhesive, said fuselage section fabric jackets, said adhesive, said fuselage frame metal external paneling, into entire said fuselage frame of said aircraft.