US1485305A - Aeroplane flying machine - Google Patents

Description

Feb. 26 1924.

H. 0. SHORT AEROPLANE FLYING MACHINE Filed Sent. 11 1922 2 Sheets-Sheet 1 Feb. 26, 1924. 1,485,305

H. 0. SHORT AEROPLANE FLYING MACHINE Filed Sent. 11, 1.922 2 Sheets-Sheet 2.

Patented F eb. 26, 1924. I

HUGH OSWALD SHORT, OF ROCHESTER, ENGLAND.

AEROPLANE FLYING MACHINE Application filed September 11, 1922. Serial No. 587,562.

To all whom it may concern:

Be it known that I, HUGH OswALn SHORT, a subject of the King of Great Britain, residing at Norfolk Lodge. Borstal Road. Rochester, Kent. England, have invented certain new and useful Improvements in Aeroplane Flying Machines, of which the following is a specification.

The present invention relates to the construction of fuselages and flying boat hulls (hereafter in this specification termed fuselages) for aeroplane flying machines, in which it is desired to provide an all-metal construction, and further a construction in which, while being light in weight, the outer shell, or body as hereafter termed. forms the main strength factor of the structure and a structure in which thin sheet metal, as for instance a light and strong metallic alloy such asduralumin can be advantageously and safely employed to form the said body.

According to this invention the body of the fuselage is composed of a plurality of annular sleeves of sheet metal, the end of one sleeve entering and fitting in contact for a requisite distance within the adjacent end of the next sleeve, and so on, and rings or annular transverse frame members of angle section are made to coincide with the overlapping ends of said annular sleeves said annular members being secured to said sleeves by the same rivets employed for securing the joints of said sleeves.

The fuselage body may obviously be of circular, oval or elliptical form in cross section.

The structure may be further strengthened by fixing to the interior surfaces of the sleeves themselves a plurality of longitudinal stiffening girders of relatively short lengths extending from one angle section ring to the next ring.

In carrying out the invention, each sleeve is composed of a stri (or a plurality of strips connected toget 'er) of' sheet metal cut to a requisite shape to conform with the contour of the fuselage body which is to be produced, and such a strip of sheet metal is bent upon itself into annular form, such as circular, oval or elliptical as required, so that its ends overlap and are connected together by rivets. The next sleeve is similarly constructed and is made of such dimensions that-.a short distance of one end enters and fits within the adjacent edge of the first-named sleeve so that the contacting annular edges of the two sleeves can then be riveted together, and similarly with succeeding sleeves.

The invention will be further described with reference to the accompanying drawlngs.

Fig. 1 shows in elevation the body of a' fuselage according to this invention, prior to apertures being cut to receive the engine and to form cockpits for the aviator and others. I

Fig. 2 is a part transverse section of such a fuselage as shown at Fig. 1, but drawn to a larger scale, and Fig. 3 is a longitudinal section of a portion of the fuselage corresponding tothe transverse section shown at Fig. 2.

Fig. 4 is a vertical section, and Fig. 5 an interior plan view (drawn to a larger scale than the previous figures), showing a joint between the edges of two sheet metal strips forming strakes and other members hereafter described. I

Fig. 6 is a vertical section, and Fig. 7 is an external plan view, showing a joint at the junction of two sleevesl At Fig. 1 of the drawings is shown the body composing the main portion of the fuselage, and which is adapted to take the main stresses to which the body may be subjected, and as will be observed the body is built up of a plurality of annular sleeves of sheet metal, of such relative diameters that the forward end of one sleeve 1 enters for a short distance within the rear end of the next forward sleeve 2, and the forward end of the sleeve 2 enters for a short distance within the rearward end of the next forward sleeve 3, so that the sleeves overlap each other generally in planes at right angles to the longitudinal axis of the fuselage, and atsuch overlapping portions the sleeves can be secured together by riveting or by any other known or equivalent means. In such a structure having been so built up, openings such as 4, 5 and 6 (indicated by dotted lines) may be cut to respectively accom-.

modate the engine, the pilot and the observer or passen ers. The dotted lines 7 indicate the position of the tail planes, and the dotted lines 8 merel indicate the position of the lower wing re atively to this particular fuselage. Such a structure as has been described and which forms the main portion of the fusela e, is adapted to take the main stresses to w ich it will be subjected.

Entering into further details of construction and referring particularly to Fig. 2, in the example here" shown the sleeve illustrated is composedof two strips of sheet metal 9, 10, the strips 9, 10 being connected together at 11 by Overlapping and riveting, and then bent to the oval form shown and again overlapped and riveted at 12, and by forming the strips of the requisite shape, when so bent and connected into annular form, the sleeves 1, Fig. 3, so formed will fit at its forward end for a short distance within the next forward sleeve 2, while the forward end of the latter sleeve 2 will fit for a short distance within the rear end of the next forward sleeve 3.

To strengthen the structure against stresses which would tend to deform the body, considered in transverse section, I provide rings 13 of angle section metal located within the shell constructed as described, 0? such ring 13 within each joint of the a nular sleeves, so that where one annular sleeve overlaps. another the rivets connecting the two sleeves will pass through one flange of the angle metal ring 13, and this construction is shown very clearly upon an enlarged scale at Figs. 4 and v5, where the forward end of one sleeve 1 enters within the rearward end of the next sleeve 2- and rivets pass through the sleeves and through the angle metal ring 13. Strengthening rings such as 13 may, when required, be also fitted intermediate of the junction of the sleeves.

Figs. 6 and 7 are views showing the joint where the overlapping ends, such as 12 Fig. 2, of the sheet metal strip forming one of the sleeves overlaps the similar joint of the next sleeve, and it is believed it will be readily understood and appreciated without further description. I

As a further strengthening device, where such is found necessary, longitudinal stilfening girders 14, Figs. 2 and 3, are fixed to the interior surfaces of the sleeves composing the structure, suchgirders 14 being each composed of divided lengths extending from one internal angle section'ring 13 to the next internal ring 13, each longitudinal girder 14 being rivete to the sleeves, and said girders 14 are arranged at distances apart around the interior of the body.

Such members 14, which'I have termed girders, may conveniently be composed of sheet metal bent into .a channel section and having flanges, as will be clearly seen at Fig. 2, and the flanges are utilized for riveting to the structure as is shown at Figs. 4 and 5.

What I claim as my invention and desire to secure by Letters Patent is 1. In fuselages for aeroplane flying machines; a body composed of a plurality of annular sleeves of sheet metal the end of one of said sleeves entering and fitting in contact for a requisite distance within the adjacent end of the next sleeve and so on, rings of angle section metal located within the interior of the body,- one flange of each ring in contact with the interior surface thereof and located to coincide with the overlapping ends of said annular sleeves, and rivets passing through said flanges of said rings and said overlapping ends of said sleeves to permanently and rigidly fix together the overlapping and contacting edges of said annular sleeves and said interiorly located rings.

2; In fuselages for aeroplane flying machines; a body composed of a plurality of annular sleeves of sheet metal the end of one of said sleeves entering and fitting in contact for a requisite distance within the adjacent end of the next sleeve and so on, rings of angle section metal located within the interior of the body, one flange of each ring in contact with the interior surface thereof and located to coincide with the overlappin ends of said annular sleeves, rivets passing through said flanges of said rings and said overlapping ends of said sleeves to permanently and rigidly fix together the overlapping and contacting edges of said annular sleeves and said interiorly located rings, and a plurality of longitudinally extending stiffening girders of relatively short lengths in contact with the in terior surfaces of the sleeves composing the structure, said longitudinal girders extending from one internal angle section ring to the next internal ring, said girders being arranged at distances a art around the interior of the bod and rivets to connect said longitudinal gir ers to said sleeves.

In witness whereof I have hereunto set my hand in the presence of two witnesses.

HUGH. OSWALD' SHORT.

- Witnesses: JAMES HENRY Woon,

HENRY MILTON RELPH.

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