US1503887A - Fuselage fitting - Google Patents

Description

that? IVAN H. DRIGGS, 0F DAYTON, OHIO, ASSIGNOR T0 DAYTON-WRIGHT COMPANY, OF

l DAYTON, 01H10, A CORPORATION OF DELAWARE.

FUSELAGE FITTING.

Application led. February 4, 1922. Serial No. 534,225.

To all whom it may concern.'

Be it known that I, IVAN H. Dulces, a citizen of the United States of America, residing at Dayton, county of Montgomery, and State of Ohio, have invented certain new and useful Improvements in Fuselage Fittings (Docket #49), of which the following is a full, clear, and exact description.

This invention relates to the construction of fuselage frames and is especially adapted for use in fuselages having metallic longerons and struts.

An object of this invention is to provide simple and effective means for securel attaching the metal stress members o the fuselage, such as the longrons, struts and brace members without welding or brazing the stress members.

Further objects and advantages of the present invention will be apparent 'from the following description, reference being had to the Iaccompanying, drawing, wherein a preferred form of embodiment of the present invention is clearly shown.

In the drawing:

Fig. 1 is a top View showing the attachment of the longron and horizontal strut, and wire pulls for the diagonal brace wires.

Fig. 2 is a view taken on line 2 2 of Fig. 1 showin the horizontal strut in section and showing all five Wire pulls for the ve brace wires attached at the fitting.

Fig. 3 isa section on line 3--3 of Fig. 2.

Fig. 4c is a perspective view of the fitting.

In the drawing, similar reference characters refer to similar parts throughout the several views.

Numeral 10 indicates a tubular metal longeron, 11 a vertical strut, and 12 a horizontal strut, these struts being illustrated as also made of metallic tubes.

A metal strap 15, constructed of malleable metal so that it can be bent around the longron, has its ends riveted together by rivets 16, as shown. One end of the strap 15 projects beyond the rivets and serves as a wire pull 17 for the diagonal brace wire 18 across the fuselage. In order to suitably attach the -abutting struts 11 and 12 to the strap 15 there are provided the parts 20, preferably aluminum die castings which may be cast accurately enough so as not to require machining, which have a contour conforming to the surface of the strap 15 where they abut same (see Fig. 3). The castings 20 lit snugly in the open ends of struts 11 and 12 and have shoulders 21 against which the struts abut. These castings 20 may be attached to the strap 15 in various ways, but I prefer to provide the bolts 22 and 23 which extend entirely through the longron 10 and thus firmly hold the castings 20 and the strap 15 in place. The bolts 22 and 23 of course must be set slightly off the center line of strap 15 to permit their crossing within the longron, and the strap 15 may be sli htly widened at the bolt heads as clearly i lustrated in the drawmg.

The malleable strap 15 is further provided with projecting lugs or ears along its sides, these ears being bent out at an an le with the longron 10 to form Wire pu s for the diagonal brace wires. The two ears 25 and 26 extend at the sides and lie in the plane of the vertical strut 11 and are bent vertically downward to the angle at which the vert1cal diagonal wires come in. The two ears 27 and 28 extend at the sides and lie in the plane of the horizontal strut 12 and are bent horizontally to the angle at which the horizontal diagonal Wires come in. The strap fitting 15 may be economically made by stamping from a plate of malleable metal and then bending to the described shape.

This invention provides a fitting, very simple and cheap to manufacture, for use in metal fuselage construction wherein the stress members are not Welded or brazed together but are pinned (the term pinned including the use of rivets, bolts, etc.) and hence heat treated stress members may be used and the higher strength of such metals taken advantage of.

While the form of mechanism herein shown and described, constitutes a preferred form of embodiment of the present invention, it is to be understood that other` forms might be adopted, all coming Within the scope of the claim which follows.

What I claim is as follows:

5 A composite metal ttng adapted for fuselage construction, including, a metal strap bent around a tubular longron and heving its ends'seeured together to form a Wire pull, a small metal casting adapted to 10 be secured to the end of an abutting strut and to said strap, the surface of said casting News? abutting the strap being substantially arcuate, whereby the same com site fitting may be used for different angu ar arrangements of said abuttn strut; and said wire 211. 1&5

En testimony Cuez'eoi I hereto a. my signature.

IVAN H. DRIGGS Witnesses:

Gmo. E. PASCO, WM. P. Pnsoo.

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