Hybrid aircraft fuselage structural components and methods of making same
View Patent ↗An aircraft fuselage assembly of basic construction in composite materials employs metallic frames with reduced quantity of metallic shear ties attached to the composite stiffened skin, formed by two or more longitudinal panels, spliced with longitudinal metallic splice members. Typically, the latitudinal metallic frame members are fastened to the inward outstanding flange portion of the composite stringers which are in turn integrated to the skin. As such, the frame members are spaced from (floating over) the fuselage skin. An electrical path may thus be established so as to protect the fuselage structure against the impact of electrical discharges commonly encountered in the atmosphere by providing metallic shear ties interconnecting the frame and splice members so as to span the space therebetween.
1. An aircraft fuselage structural component comprising:
non-metallic skins;
longitudinally spaced-apart metallic frame members spaced from the skins and defining a latitudinal section of an aircraft fuselage section;
longitudinally oriented non-metallic stringers having a lower flange joined to the skins and an upper flange joined to an upper part of the frame members;
at least one metallic splice member connecting adjacent ones of the skins; and
metallic shear ties each being connected to respective frame and splice members.
2. The component of claim 1 , further comprising secondary shear ties which span the space between the frame members and the skins, the secondary shear ties being structurally united to the frame members and the skins.
3. The component of claim 2 , wherein the secondary shear ties are formed of a metallic or non-metallic material.
4. The component of claim 1 , wherein the stringers and the skins are each formed of a co-cured resin reinforced composite material.
5. An aircraft fuselage comprising aircraft fuselage structural components as in claim 1 , wherein a plurality of the longitudinal spice members are provided so as to connect the skins of adjacent ones of the fuselage structural components and thereby join the structural components to one another.
6. The aircraft fuselage of claim 5 , further comprising secondary shear ties which span the space between the frame members and the skin, the secondary shear ties being structurally united to the frame members and the skin.
7. The aircraft fuselage of claim 6 , wherein the secondary shear ties are formed of a metallic or non-metallic material.
8. The aircraft fuselage of claim 5 , wherein the stringers and the skins are each formed of a co-cured resin reinforced composite material.
9. The aircraft fuselage of claim 5 , wherein the metallic shear ties span the space between the frame members and the skin and are structurally united to the respective frame and splice members so as to establish an electrical path therebetween.
10. An aircraft which comprises an aircraft fuselage of claim 5 .
11. A method of making an aircraft fuselage structural component comprising:
(a) joining non-metallic skins to a lower flange of longitudinal non-metallic stringers; and thereafter
(b) joining latitudinal metallic frame members to an upper flange of the stringers so as to be in a spaced relationship with the skin.
12. The method of claim 11 , wherein step (a) includes providing the skin and stringers of a reinforced resin composite material, and co-curing the skin and stringers so as to bond one to another.
13. The method of claim 11 , wherein step (b) includes interconnecting the frame members and the skin with the metallic shear ties so as to span the space therebetween.
14. A method of assembling an aircraft fuselage section comprising:
(i) providing plural aircraft fuselage structural components as in claim 1 ; and
(ii) joining the skins of adjacent ones of the fuselage structural components to one another with the longitudinal splice members.
15. The method of claim 14 , wherein the skins and stringers are formed of a reinforced resin composite material, and wherein the method further comprises establishing an electrical path between the frame members and the splice members by interconnecting the frame and splice members with a respective metallic shear ties so as to span the space therebetween.
16. The method of claim 14 , wherein step (b) includes interconnecting the frame members and the skins with secondary shear ties so as to span the space therebetween.