US1326535A - Aeroplane. - Google Patents

Description

M. SEYMOUR.

AEROPLANE.

APPLICATION FILED JAN. 2. 1911.

1,326,535. Patented Dec. 30,1919.

3 SHEETS-SHEET I.

M. SEYMOUR.

AEROPLANE.

, APPLICATION FILED JAN.2. 1917.

1,326,535. Patented Dec. 30,1919.

3 SHEETSSHEET 2- M. SEYMOUR.

AEROPLANE.

APPLICATION FILED 1AN. 2. 1917.

Patented Dec. 30, 1919.

3 SHEETS-SHEET 3.

UNTTED STATES PATENT OFFICE.

MALCOLM SEYMOUR, F BOSTGN, MASSACHUSETTS.

AEROPLANE.

Application filed January 2, 1317.

To all whom it may concern:

Be it known that I, lviimcomi SnYnoUR, a citizen of the United States, residing at Boston, county of Suffolk, Commonwealth of lvLlassachusetts, have invented certain new and useful Improvements in Aeroplanes, of

. fully described in the specification which follows, and particularly pointed out in the appended claim. Throughout the specification and drawings like reference characters are correspondingly applied, and in the drawings Figure 1 is a plan view of an aeroplane in accordance with my invention,

Fig. 2 is an elevation, partly in longitudinal section thereof.

Fig. 3 is a bow view, and

Fig. 1 is a stern view.

I have indicated at 1 a frame member or keel to which is braced a stern piece 2 and propeller frame 8. The frame member 1 which I term the keel on account of its relation to the body of the machine is inclined fore and aft, and forms the lower edge of an elongated pyramidal frame of triangular cross section. The longitudinal edge frames l le are suitably braced to each other and to the keel member 1 as at 21 to provide centrally of the plane spread proper a light braced structure or body of great strength and rigidity.

The body thus defined by the longitudinal frames 1, l--i and the braces 21, is covered on its two lower faces with a suitable surfacing S which is continued as at S to form the wing planes. The wing planes are defined by the edge frames l-it, the rear cross frame 5 which with the rear braces 21 constitute a triangular stern frame for the body and stringers drawn from the ends of the cross frame 5 to the apex or bow 6 of the body. These wings or laterals are substantially elongated triangles and are set in the plane of the top frames of the body.

The ascent and descent of the machme 1S controlled through a pair of horizontal steering rudders 7 hinged to the cross frame Specification of Letters Patent.

Patented Dec. 30, 1919.

Serial No. 140,668.

5 and thus disposed at the rear ends of the wings or laterals formed by the surfaces S The horizontal rudders 7 are moved upwardly and downwardly by a control 8 within convenient reach of the pilot. I

The horizontal rudder connections 9 extend over suitable sheaves in a braced frame 11 mounted in the cross frame 5 to a drum 8 on the shaft of the wheel 8 being guided along the frame in suitable sheaves 11 The control 8 as here shown is a simple hand wheel mounted on a transverse drum shaft provided with the drum. 8 over which the control lines are turned and run as described to the opposite sides of the rudder 7 giving an opposed control. These connec tions enable the pilot to tilt either horizontal rudders 7 upwardly or downwardly as indicated in dotted lines, Fig. 2.

ll ithin the body framework of the machine is set the motor 12 for driving a propeller 13. The fuel tank 145 may be mounted in any convenient part of the pyramidal frame and the drivers seat 15 may be conveniently located in the waist of the body, all being preferably disposed to secure the desired balance.

The engine control, not indicated, n'ia-ybe suitably connected according to engine type and installation.

The lateral movements of the machine are guided by vertical fins or rudders 16 hinged to a second cross frame 5 which crosses the central body of the machine at the second angular body frame 21, thus forming a complete triangular body frame at this point. Second cross frame 5 is extended as is the frame 5 to the full width of the lateral planes at that point. The vertical rudders 16 are operated by control lines 1'? passing over sheaves 18 to a control wheel 19. The control wheel 19 is on a shaft having a drum 20 about which the line 17 is turned.

Corresponding with the cross frames 5 and 5 at the next forward frame of the body is disposed a cross member 5 similarly mounted and similarly bracing the body. Connecting the ends of these members 5, 5 and 5 is preferably a rigid stringer 22. This is not essential, but is preferred construction, it braces the area of the wing in which the rudder controls are located, and strengthens the broader areas of the laterals. The base of the laterals are also traced by wire braces 28 which are drawn taut to the rear end of the keel member 1.

The laterals are preferably strung forward of the cross frame 5 at least with fore and aft bracing wires 2a drawn from the cross frames at suitable distances from the body of the car to the apex or bow 6 of the body. This not only aifords a light form of body bracing, but strengthens the wing planes and gives reinforced bearing surface.

Referring to Figs. 1 and 3 I preferably provide a wheel base as follows: I provide a rear wheel frame 25 attached directly to the keel member 1 having a wheel 26 and a forward wheel support 27 constituting a plurality of braces running from the keel member 1 and the adjacent lateral ribs 21 which form the V-shaped frame of the body portion. These supports carry preferably a pair of wheels 28.

In constructing my machine I dispose my engine tank, fuel tank, pilots location, controls and gear so as to bring the center of gravity of the machine when flown slightly in advance of the transverse center of the plane spread so as to bring a preponderance of plane surface to the rear of the center of gravity. z

This phase of my invention, while in part combining with the particular plane disposition of my machine is in itself believed to be an element of novelty and to involve important principles. Without committing myself to theories, I may point out certain features and results in the action of such a machine in the air which are elements of great advantage.

The combination of gravity center with slightly predominating effective plane spread gives to the machine an unusual stability both on the lateral wing and in flight. By proportioning the fore and aft plane spread relative to the center of gravity, I am able to produce a machine which will carry its rear with least strain, which will glide, even from a moment of substantial arrest in its flight, and which is very responsive to its controls.

Various modifications may be made in the shapes and proportion of parts and details of structures, all without departing from the spirit of my invention if within the limits of the appended claim.

lVhat I therefore claim and desire to secure by Letters Patent is:

In flying apparatus, a triangular pyramidal central frame, spaced angular body braces therefor, a pair of forwardly tapering triangular wings arranged in co-planar relation to and in common apex with said central frame, transverse frames crossing the central frame at said angular body braces therefor, and extended to the full width of the lateral wings and forming with said angular braces complete triangular body bracing frames, directive elements mounted on said transverse frames at either side of the central frame, and propulsive and control equipment mounted upon said central frame.

In testimony whereof I aiiix my signature in presence of two witnesses.

MALCOLM SEYMOUR. Witnesses:

VICTORIA LOWDEN,

MARY P. Wo'rHERsrooN.

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