|Publication number||US1355611 A|
|Publication date||Oct 12, 1920|
|Filing date||Sep 22, 1917|
|Priority date||Sep 22, 1917|
|Publication number||US 1355611 A, US 1355611A, US-A-1355611, US1355611 A, US1355611A|
|Original Assignee||Kawneer Mfg Company|
|Export Citation||BiBTeX, EndNote, RefMan|
|Referenced by (3), Classifications (5)|
|External Links: USPTO, USPTO Assignment, Espacenet|
H. MACLEOD. TRAILING EDGE FOR AIRPLANESI. APPLICATION FILED SEPT. 22, 1917.
Patented Ot. 12,1920.
,UNITED STATES' PATENT OFFC.
HECTOR MACLEOD, OF GUELPH, ONTARIO, CANADA, ASSIGNO FACTURING- COMPANY, OF NILES, MICHIGAN, A CORPOR TRAILING EDGE FOR AIRPLANES.
To all whom it may concem: e
Be it known that I, Hnc'ron MAcLEoD, a subject of the King of Great Britain, residing at Guelph, in the county of Wellington and Province of Ontario, Canada, have in vented certain new and useful Improvements in Trailing Edges for Airplanes, of which the following is a specification.
This invention relates to aircrafts and more particularly to edgings for the trailing edge ailerons, rudders, elevating planes, and the like.
In the Construction of airplanes as heretofore conducted, the securing of the cross ribs of the ailerons, wings, rudders, stabilizers, and the like, to the edgng member has been eifected in an inefiicient and impractical manner, as by butting the end of the rib against the tube edging member and securing the same in place by means of straps passing around the tube edging. members. This has proven very unsatis factory for many reasons, among which are the excessive cost, the insecurity of the connection, the additional weight necessary in the edging member, the Consumption of too much time in building, and the general lack of Simplicity, adaptability, neatness, elficiency, compactness, and economy. These difficulties have been entirely overcome by this invention.
Among the objects of my invention, therefore, is to provide a new and useful edging for aircraft wings, ailerons, rudders, and the like; further to provide a novel form of connection between the end of the ribs and the edging member; further to so edge the wings, ailerons, rudders, and the like, of aircrafts that the maximum; of lightness, efiiciency, neatness, strength, Simplicity, compactness, and economy is effected; and such further objects and advantages as will iereafter become more apparent.
My invention further resides in such combination, Construction, and arrangement of parts as disclosed in the accompanying drawing, and while I have illustrated therein a preferred embodiment, I desire the same to be understood as illustrative only and not as limiting the scope of my invention.
In the drawings:
Figure 1 is a plan View of an aileron embodying my invention.
Specification of Letters Patent.
of the wings, and also to edgings for.
p Patented Oct. Application filed September 22, 1917. Serial No.
R 'ro KAWNER ATION or MICHIGAN.
2 is a perspective View of a portion showing the ereto. line 3 3 of trps '8 and drawings, Fig. 1 shows an .aileron consisting of a framework indicated generally as edging member material 4'. The edging memb houses the ends of the ribs is l,and made up of a rear 2, cross rbs 3, and coverng er 2 which formed U.-
shape in cross section out of a suitable gage and width of metal, as clearly shown in F ig.
3, the free edges of which are slightly iliclined inwardly toward each other forming l ps 5 and 6. This inolined feature of the llps 5 and 6 provides additional strength and prevents the from frction at these which may be covering places. of lght,
wearing by The cross ribs 3, strong wood or metal, or other suitable material, are tapered so as to fit into the tralmg edging member,
as shown at between the lips 5 and 6.
By having the rib ends fit between the Lips 5 and 6 and within the edging member these parts will be eifectively held together not only by the tightness of the by the fastenings (any suitable fit but also kind being used) and covering material which is drawn tghtly around the edgng member and secured in place.
When metal ribs are used they may be welded, brazed, or otherwise suitably Secured in place within member.
the edgng It is to be noted that the particular shape of the edging member as shown i ngs is such as to n the draw'- gve not only the maximum of strength for the metal used, but
and at the at the rear in the drawings edgng member as apedge of an aleron, (which position it would also occupy in wing constructiom) it is to the same s used as be understood that when an edging for rudders,
stabilizers, or the like, it may be eXtended entirely therearound, or over the ends, instead of being conned only to the rear edge, if such be desired. Also -might be found desirable to at times it extend the same partially around the ends of wings and ailerons. The shape of the edging member 2 is such as to permit the covering material to be drswn around and over the same without damage to such covering. Also the use of the filling strip's 8 'and 9 brings the sides of the edgingv member 2 flush as shown in Fig. 3, which :further greatly facilitetesthe application of the covering material to its place.
Having now described my invention, I claim: p
1. In aircreft Construction, ribs, facing strips on oppositeedges of said ribs terminatng short of the ends of said ribs, an edging strip generally U-shaped in cross section withthe ends of the U inclined slightly toward each other, said edging strip embracing the ends of the ribs and abutting the ends of the facing strips. e
2. In aircraft construction, ribs, facing strips on opposite edges of said rbs terminating 'short of the ends of said ribs, an edg'ng strip, generally U-shaped in cross section with the ends of the U inclined slightly toward each other, said edging strip enbracing the ends of the ribs and abutting member, and filling strips on seid rib and substantially abuttng seid inclined portions whereby to hold the covering material without undue chafing.
In witness whereof I hereunto subscribe i my name to this specification in the presence of a wtness i HECTOR ACLE D.
H. M. CHRISTMAN.
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|Cooperative Classification||B64C3/00, B64C2700/6233|