US1871015A

US1871015A - Airplane

Info

Publication number: US1871015A
Application number: US345303A
Authority: US
Inventors: Squires John
Original assignee: Individual
Current assignee: Individual
Priority date: 1929-03-08
Filing date: 1929-03-08
Publication date: 1932-08-09
Anticipated expiration: 1949-08-09

Description

Aug. 9, 1932. ES 1,871,01'5

AIRPLANE Filed March 8, 1929 INVENTOR' (7072 735g Z6 7/7'65 A TTORNEYJ.

Patented Aug. 9, 1932 JOHII SQUIRES, OF DETROIT, MICHIGAN AIRPLANE Application filed March 8,

This invention relates to airplanes, and particularly to a construction therefor that will result in a more efficient operation theret Another object is to provide a novel construction for a power unit section of an airplane of the pushertype, designed to offer minimum air resistance and maximum efliciency, I

Another object is to provide an airplane of the pusher type provided. with an enclosed power plant, a propeller being mounted at the rear of the power plant enclosure and being formed to cooperate therewith whereby to offer a minimum amount of resistance to the passage of the enclosure through the air.

' Another object is to provide, in combination with an airplane of the pusher type, a power plant enclosure of substantially circular section at its rear end, a propeller driven by the power plant being positioned rearwardly of the enclosure and being provided with a central hood .of substantially the same diameter, in the neighborhood of the propeller blades, as the rear endof the enclosure and being reduced rearwardly therefrom in a manner to avoid the formation of undesirable air currents due to its passage through the air.

Another object is to provide, in combination with an airplane of the pusher type, an enclosure for a power plant including a generally cylindrical housing having a projectile-like shoulder at its forward end and provided with a propeller positioned rearwardly to the housing,'the propeller being provided with a central hoodof maximum diameter in the plane of the blades, which corresponds to the diameter of the housing, the hood terminating in a streamlined tail portion.

A further object is to provide certain novel features of construction that will be specifically pointed out, or will be obvious in the following specification. i

The above being among the objects of the present invention, the same consists in certain novel features of construction and combinations of parts to be hereinafter described 50 with reference to the accompanying draw- 1929, Serial No. 345,303.

ing, and then claimed, having the above and other objects in view.

In the accompanying drawing which shows a suitable embodiment of the present invention, and in which like numerals refer to like parts throughout the several different views;

Fig. 1 is a more-or-less diagrammatic perspective view of an airplane of the pusher I type.

Fig. 2 is a vertical sectional view taken through the axis of one of the power units shown suspended from the wings of the airplane shown in Fig. 1. a

Fig. 3 is a more-or-less diagrammatic partially'broken end view of one of the wings of the airplane shown in Fig. 1, showing the mounting of a power plant upon the same.

Fig. 4 is a sectional view taken on the line 33 of Fig. 2.

In the conventional, design of airplanes of the pusher type, the engines are generally mounted either on the wings or suspended from them. In some constructions no enclosure of any type is provided for the engines, and in other types the engines are enclosed and the propeller is positioned rearwardly of such enclosure. Where the engine is not enclosedthe resistance offered by the 'passage of the same through air is relatively great, and in the constructions heretofore employed where the engine is enclosed it has been attempted to so design the enclosure at its rear end as to ofi'er a minimum amount of resistance to its passage through the air, and so as to result in as small a disturbance to theair as is possible. propeller in the last described constructions is positioned rearwardly. of the housing, and

because of the impossibility of supporting.

the propeller at too great a distance from the power plant, limitations have been present preventing an eflicient housing construction. Furthermore, the propeller is so positioned relative to the housing that it works in the air disturbed by the housing and has therefore resulted in less efficient use of the propeller than is desired.

In accordance with theprcsent invention, I provide a, construction in which the same efiiciency' may be r lized from'the propeller Inasmuch as the in a pusher ty e of airplane having an enclosed power p iant, as can be realized from the tractor type of airplane.

Referring to the accompanying drawing, I show more-or-less diagrammatically in 1, anairplane of the pusher type having a uselage and oppositely extending Wings 11. A housing 12 1s formed upon the upper face of each win 11 adjacent the ends thereof and in each liousing 12 is positioned a power plant such as 13 shown in Fig. 3, which is adapted to drive a propeller such as 14. Suspended below each wing 11 closer to the fuselage 10 than the housings 12, b suitable 15 supports such as 15, is a housing oft e nacelle type 16.

' As indicated in Fig. 2, this last housing may be generally circular in section and of a cylindrical form fromits rear edge 17 to its forward edge 18, the forward edge blending into the nose 17 through a projectile-like shoulder 20. A power plant 21 is suitably supported within the housing 16 and is provided with ashaft 22 projecting rearwardly past the rear edge 17 of the housing 16. A propeller havinga hub 22-and blades 23 is carried by the shaft 21. Mounted concen.

trically with the hub 22 and turning therewith is a hood or shell 24 which may be supported from the hub 22 by rings such as 25 carried by the hub and spokes such as 26. The shell or hood 24 extends into relatively close relationship with respect to the rear edge 17 of the housing 16 and at that point is of substantially the same diameter as-the housing 16. From this point the hood 24 extends rearwardly, preferably at full diameter to a point rearwardly of the trailing edges of the blades 23 from which pointit is gradually reduced insection to form a tail portion 27 designed to offer a minimum resistance and to' set up a minimum amount of eddies during its passage through the air.

With this construction the housing 16, because of its cylindrical formation and projectile-like shoulder 20, offers a minimum resistance in being thrust through the air, and because of its cylindrical formation, the air has a tendency to be maintained along. its 59 side surfaces without setting up eddies. In carrying the full diameter of the housing 16 to a point rearwardly of the propeller blades 23, the normally ineflicient center portion of the propeller is eliminated, as far as propulsion and air resistance is concerned, and the air that the effective portions'of the blades 23 work in is flowing in a true axial direction and is free of detrimental eddies. Inasmuch as the hood 24 does not transmit any driv- Go ing or other strains, its construction may be relatively light, and it may be extended to any reasonable distance rearwardly of the propeller that is desired to obtain the streamlined construction thouuht necessary for opi timum results.

The housings 12 on the wings 11 are carried out with the same end in view as the construction described in Fig. 2. In this case it may be found preferable to extend the housing 12 as far as the leading edge of the wing 11 and preferably form it to a generally circular section, as indicated in Fig. 4, the axis of the section being parallel to the direction of normal travel. The housing 12 will thus generally increase in size from the leading edge of the wing to the power plant .13, at which point it will be of maximum diameter. The power plant 13 drives the pro peller 14, which is provided with a hood 30 hearing the same relation with respect to the 24 previously described bears to the housing 16. Where the power plant is of that type having aligned cylinders it may be desirable, in some cases, to form a projecting portion such as 31 on the upper surface of the housing 12 in order to' accommodate the outer ends of the engine cylinders, as is con ventional practice in connectionwith some engine cowling constructions. Inasmuch as such projections 31 ."re of limited area as respects the entire area of the cowling or housing, I prefer to disregard them in designing an airplane in accordance with the present invention. In other words, in considering the section through the housing as indicated in Fig. 4, in designing the hood 30 the maximum diameter of the hood 30 may be constructed in ac cordance with the normal maximum diameter of the housing 12.

It will be noted that by this construction it is possible to mount the ropeller in closely adjacent relationship with respect to the power plant and still provide a streamlined construction which will offer a minimum resistance and set up a minimum disturbance in passing through the air.

Formal changes may be made in the specific embodiment of the invention described without departing from the spirit or substance of the broad invention, the scope of which is commensurate with the appended claims.

What I claimis 1. In an airplane, in combination, an engine, a propeller positioned rearwardly of said engine and driven therefrom, an enclosure for said engine, a central hood carried'by said propeller having parallel side walls extending from in advance of said propeller rearwardly thereof, the rear end of said enclosure being of generally circular shape and the forward end of said hood being of substantially the same size as the rear end of said enclosure and extending into closely adjacent relationship with respect thereto, said hood having a streamlined tail integrally formed therewith.

2. In an airplane, in combination, an engine, a propeller positioned rearwardly of housing 12 as the hood said engine and driven therefrom, an enclosurefor said engine, a central hood car v the forward end of said hood being of substantially the samesize as the rear end of said enclosure and extending into closely adjacent relationship with respect thereto, the forward end of said enclosure being provided with a projectile-like shoulder.

' 3. In an airplane, in combination, an engine, a propeller positioned rearwardly of said engine, an enclosure for said engine of substantially maximum cross sectional area at its rear end, and a central hood carried by said propeller, said hood being cylindrical in shape within the axiallimits of said propeller andacting to continue the stream-lining of said enclosure to a point rearwardly of said propeller.

4. In an aircraft, in combination, a nacelle of generally cylindrical formation supported upon converging outrigger braces, an engine carried thereby, a propeller positioned rearwardly of the rear edge of said nacelle, and a central hood rotatable with said propeller, said hood being of substantially the same diameter at its forward edge as said, nacelle at its rear edge and lying in closely adjacent relationship with respect thereto.

5. In an aircraft, in combination, a nacelle of generally cylindrical formation supported upon converging outrigger braces having a projectile-like shoulder at its forward end,

an engine carriedby said nacelle, a propeller positioned rearwardly'of said nacelle driven by said engine, and a hood rotatable with said propeller acting to continue the cylindrical formation of said nacelle to a point rearwardly of said propeller.

6. In an-aircraft, incombination, a nacelle of generally cylindrical formation supported upon converging outrigger braces having a projectile-like shoulder at its forward end, an

engine carried by said nacelle, a propeller positioned rearwardly of said nacelle driven by said engine, and a hood rotatable with said propeller acting to continue the cylindrical formation of said nacelle to a point rearwardl-y of said propeller and extending rearwardly therefrom in a streamlined tail;

7. In an aircraft, in combination, anacelle of generally cylindrical formation supported upon converging outrigger braces and of maximum diameter at its rear edge, an enginecarried thereby, a propeller positioned rearwardly of the rear edge of said nacelle,

and a central hood rotatable with said ,pro-

peller, said hood being cylindrical from its forward edge to a point rearwardly of sald propeller and being ofsubstantiallythe same diameter at its forward edge as said nacelle at its rear edge and lying in closely adjacent relationship with respect thereto.

I JOHN SQUIRES.