Adhesive bonding and miscellaneous chemical manufacture – Methods – Surface bonding and/or assembly therefor
Patent
1982-09-15
1984-06-05
Massie, Jerome W.
Adhesive bonding and miscellaneous chemical manufacture
Methods
Surface bonding and/or assembly therefor
5230916, 52630, 156213, 156215, 156227, 156265, 156297, 1563077, 156330, 244119, 428120, B29C 1704
Patent
active
044526571
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND OF THE INVENTION
This invention relates to stiffening a composite material web structure with transverse stiffeners. In the conventional, aluminum-metal design approach, a standard angle stiffener is utilized which is riveted against the web. However, fastening methods utilizing rivets cannot be used in graphite epoxy parts because the expansion of the head may crack the resin. Furthermore, fasteners should be electro-chemically compatible to prevent corrosion. The solution of utilizing screw type fasteners becomes highly uneconomical and utilizing so-called stiffeners becomes complicated in design, tooling and manufacture. By the teachings of this invention, transverse web stiffeners are utilized in the form of tubular elements having flattened ends which are inserted between the composite laminations of the web material.
The following references were found to be of interest: U.S. Pat. Nos. 3,831,333; 3,995,080; 4,047,354; 4,113,910; 4,129,974; 4,198,018; 4,219,980; and 4,219,980; Italian Pat. No. 682,106 and British Pat. No. 640,341.
A close approach to the present inventive method and proposed construction was not observed and accordingly, the patents should be considered as being of general interest and illustrating the scope of the available art. Several of these patents disclose various types of transverse stiffeners or reinforcements for beam structures of the general type under consideration, however, none appear to be close structurally to the proposed concept.
SUMMARY OF THE INVENTION
In general, stiffening of web construction or structures is often demanded in aircraft manufacture, such as rear spar assemblies, on horizontal and/or vertical stabilizers and in vertical wing or rib structures due to requirements for system attachments, access holes, etc.
The present invention proposes a web stiffening method wherein a tube with flattened ends is inserted between the composite epoxy laminates or between two graphite epoxy sheets. The tube, which may be of any metal or composite material, is cured into place by the curing of the web about the inserted tube. As a result, the tube and cured webs become an integral part of the stiffener.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 illustrates a typical conventional aircraft web structure.
FIG. 2 is a cross section taken along line 2--2 of FIG. 1.
FIG. 3 illustrates a graphite epoxy web structure stiffened by the present inventive method.
FIG. 4 is a section taken along line 4--4 of FIG. 3.
FIG. 5 is a cross section taken along line 5--5 of FIG. 3.
FIG. 6 is a cross section taken along line 6--6 of FIG. 3.
FIG. 7 is a thin wall tube in forward view.
FIG. 8 is a thin wall tube in side view.
FIGS. 9A-9E are cross sections of various possible tube configurations.
DETAILED DESCRIPTION OF THE INVENTION
In the conventional aluminum aircraft structure 10, illustrated in FIGS. 1 and 2, there are spars or ribs 12 and 14 interconnected by a web 16 which together form a typical structural assembly. In the event the web portion has to be strengthened, stiffeners 18 or doublers 20 are riveted against the web and are normally attached to the spars 12 and 14 as well. Now, as mentioned herein, when utilizing composite materials, it becomes difficult to attach stiffeners by the conventional method and also uneconomical and inefficient. Accordingly, the present invention utilizes a stiffener 22 which, in the preferred embodiment, has the shape of a tube made of thin wall tubing of corrosion resisting steel or titanium or other suitable material. The tube stiffener 22 is cut long enough to carry a load from spar to spar. Referring to FIGS. 7 and 8, the tube or stiffener 22 has been flattened at both ends 24 so as to accomplish easy insertion between laminations or webs and to accomplish a strong junction or interconnection at the upper and lower spar assembly 26. The complete assembly of a stiffened composite web structure 30 is illustrated in FIGS. 3-6 and cross sections 4--4, 5--5 and 6--6. In this preferred embodiment, a double or laminated web 32 and
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DeVogel Nicolaas
Donahue Bernard A.
Massie Jerome W.
The Boeing Company
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