Stock material or miscellaneous articles – Structurally defined web or sheet – Honeycomb-like
Patent
1981-09-30
1983-07-26
Van Balen, William J.
Stock material or miscellaneous articles
Structurally defined web or sheet
Honeycomb-like
156201, 1562755, 244123, 244131, 428119, B64C 318, B32B 500
Patent
active
043954502
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND OF THE INVENTION
The high strength to weight ratio of composite components make the composites attractive for use on airplanes. However, the joints betwen composite components involve one of the most difficult problems of adapting the composites to the manufacture of airplanes. These problems are severely multiplied when the joints are highly stressed in several directions. It was found that a composite skin-spar joint could be prepared that not only lends itself to providing a low weight high strength joint for any composite, but it is particularly attractive for use in aircraft wings. The joint when integrated makes spars that carry the loads without the need for ribs.
SUMMARY OF THE INVENTION
A composite skin-spar joint has a resin impregnated interwoven fabric with a pair of spaced apart spanwise extending panels, and a bisecting laterally extending interwoven panel that extends laterally to each side. Three cores are joined to one side of the laterally extending panel. The intermediate core extends between and is joined to the spaced apart panels, and has directional reinforcement to handle torsional loads. The other two cores have reinforcement to handle varying loads in a spanwise direction. A fourth core is located adjacent to the intermediate core and is joined to the three panels.
DESCRIPTION OF THE DRAWINGS
FIG. 1 shows a fragmented exploded perspective view of the composite skin-spar joint.
FIG. 2 shows a fragmented perspective view of the skin-spar joint being formed.
FIG. 3 shows a fragmented perspective view of the composite skin-spar joint of FIG. 1 joined to parts of a wing.
FIG. 4 shows a cross-sectional side elevational view of skin-spar joint joined in a wing of an airplane.
FIG. 5 shows a schematic plan view of a wing of an airplane using the composite skin-spar joint.
FIG. 6 is a graph showing the wing bending moment for the wing of FIG. 5.
FIG. 7 shows a side elevational view of one of the chords, without a cover, making up the composite skin-spar joint.
FIG. 8 is a cross-sectional view taken along line 8--8 of FIG. 7.
DETAILED DESCRIPTION
Composite skin-spar joint 10, is made up of resin impregnated interwoven fabric 12, cores 14, and 16, and chords 18a and 18b.
The interwoven fabric 12 is prepared from any of the known reinforcing fibers such as, but not limited to, fiberglass and graphite, and will be impregnated with any of the known resins, such as but not limited to, phenolic or epoxy resin. The impregnated fabric extends for the length of the desired span for the joint, is essentially H-shaped in cross section, and has fiber orientation that is predominately transverse. The fabric has a panel 20 that extends laterally and is bisected at 22a and 22b where it is interwoven with a pair of spaced apart panels 24a and 24b. The two spaced apart panels preferably have the spacing increase as the panels extend outward.
Core 14 is directly in contact with all three layers of the fabric, is located in the web area 26, and is preferably of a honeycomb material. A plastic potting compound 27 is preferably used between the core and panel 20.
On the opposite side of panel 20 and in contact with all the panels is an intermediate core 16; which is a fabricated core. It has a center 28 of honeycomb; which is aligned in a crisscrossing pattern to resist shear due to lateral bending, and a reinforced plastic top layer 30a and a bottom layer 30b. A covering 32 of a resin impregnated wound fiber may be used.
Chords 18a and 18b are located to the right and left of the intermediate core 16, and are fabricated chords. Those chords respectively have top layer 34a and 34b and bottom layer 36a and 36b; which are each made from reinforced plastics and are precured before assembly. There is honeycomb 38a and 38b between the layers and the cores have a wrapping 40a and 40b of resin impregnated reinforcing fibers. Various materials can be used to prepare the cores and the chords, however, the preferred material for the honeycomb is a glass fiber treated with a heat resistant phenolic re
REFERENCES:
patent: 3771748 (1973-11-01), Jones
patent: 3950115 (1976-04-01), Euler
patent: 4151031 (1979-04-01), Goad et al.
patent: 4253898 (1981-03-01), Rinker et al.
patent: 4284443 (1981-08-01), Hilton
Case Morris A.
Donahue B. A.
The Boeing Company
Van Balen William J.
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