USRE18143E - Aeroplane - Google Patents

Description

E. l CROZIER AEROPLANE 7 Aug. 4, 1931.

Original Filed July 30, 1923 zsheetvs-sneet 1 f. 1. Crane]:

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Au 4 1931 E- -CRQZIER AEROPLANB ginal Filed July 30. 1923 2 Sheets-Shee t Ori A Rem-ea Aug. 4, 1931 v UNITED STATES mm L. 03021153., BIRMINGHAM, ALABAMA AEBOPLANE Original I0. 1,471,327, dated October 23, 1923, Serial H0; 654,580, filed July 30, 1923. Application for reissue filed Kay 29, 1931. Serial No. 541,056.

This invention relates to certain new and useful improvements in aeroplanes, and has particular reference to devices of this kllld embodying two planes and commonly known as bi-planes. 0

The rimary object of the invention is to general y simplify and improve devices of the above kind whereby the same may be made more durable in construction and com- 1. pact in arrangement of parts. 7

Another object of the invention is to provide eflicient form and arrangement of planes arranged longitudinally of the fuselage instead of the commonly employed lateral planesor win now in use, the construction and form 0 which necessarily involves frailty of construction.

Other objects will appear as the nature of the invention is better understood, and the same consists in the novel form, combination and arrangement of parts hereinafter more fully described, shown in the accompanying drawings and claimed.

In the drawings, wherein like reference charadzers indicate corresponding parts throughout the several views,

Figure 1 is a view in side elevation of an aeroplane constructed in accordance with the present invention. v

so Figure 2 is a top plan view of the device shown in Figure 1.

Figure 3 is a. transverse sectional view taken on line 3-3 of Figure 1.

Figure 4 is a transverse sectional view taken on line 44 of Figure 1, and

Figure 5 is a view similar to Figure 4 taken on line 5-5 of Figure 1.

Referring more in detail to the drawings, the device embodies a main or passenger ca ing fuselage 5 provided with a suitable lan gear 6 and resilient ground engaging tail member 7 for retarding the forward movement of the aeroplane upon making a landing.

In accordance with the present invention, a pair of superimposed longitudinal planes 8 and 8 are provided, the plane 8 being somewhat wider than the fuselage 5 and rigidly constructed on the top of the latter as shown in Figure 1, and the upper plane 8 being somewhat wider than the lower plane 8'. The planes are rigidly connected and supported in spaced relation by means of suitable struts 9, the intermediate one-s of which may be extended through the lower plane 8' and built into the sides of the body of the fuselage 5.

Suitably supported by the intermediate struts 9 and between the latter is an engine fuselage 10 which is of considerably less length than the planes, and which is adapted to carry any suitable or preferred formof driving mechanism for the propeller 11 which is disposed vertically. between the planes at the forward end of the engine fuselage 10 and adjacent the forward end of the planes. The struts 9 may be suitably braced as at 12, and a tapered rearwardly widening vertical tail rudder'is'fixed between the rear ends of the planes 8 and 8' as clearly shown in Figure 1,

a movable tailrudder being provided as at 14 at the rear end of the stationary rudder 13 and adapted to be suitably controlled for determining the lateral courseof the aeroplane. Horizontal rudders 15 are also provided at the rear ends of each of the planes 8'- and 8 as clearly shown in Figures 1 and 2.

The form of each of the. planes 8 and 8 is substantially thesame, and will be readily'apparent from the drawings, particularly Figures 3 to 5 inclusive.

As shown, these planes are transversely curved so as to provide concavities at the undersides thereof, which concavities are of maximum depth at the forward ends of the planes and gradually taper narrower and shallower toward the rear of the aeroplane where they assume a flat form as shown in Figure 5, and the forward ends of these planes are preferably formed with lips as at 16 to give the desired streamline effect. This streamline effect will of course be embodied in the construction of the fuselage 5, also.

Particular attention is called to the wing or plane curvature. These wings or planes are formed at their forward ends with across section as shown in Figure 3 conforming to one half of an elongated ellipse, and the points of greatest curvature at the sides of the planes converge rearwardly toward the center as shown in Figures 2 and and assume a fiat form as shown in Figure at their rear ends.

Itis believed that the construction and operation as well as the advantages of the inv vention will be readily apparent to those 5 skilled in the art from the foregoing description.

What I claim and desire to secure by Letters Patent is 1. An aeroplane comprising a fuselage havin at least one plane of elongated form exten longitudinally thereof, an engine operativefiy ca 'ng a pro eller, said plane being of upwa y curved orm in cross section to provide a longitudinal recess at the under side thereof, said recess being of major depth at the forward end of the plane and gradually tapering shallower toward the rear end of the plane.

2. An aeroplane comprising a fuselage $0 havin .at least one plane of elongated form exten in longitudinally thereof an engine operative y carrying a propeller, said plane being shaped at its forward end to conform in cross section, to substantiall the upper half of an elongated ellipse, wit the points of greatest curvature thereof at the sides of the plane and converging rearwardly toward the center, assuming substantially a flat form at the rear end thereof. '3. An aeroplane comprising a main fuselage having rigid upper and lower planes of elongated forms extending longitudinally thereof in spaced relation, an engine fuselage mounted between said planes and supporting a vertical propeller at its forward end between the forward end portion of said lanes, 1 said planes being of upwardly curved orm in cross section to rovide longitudinal recesses at the under si es threof,-said recesses being 40 of major depth at the forward ends of the planes and gradually tapering shallower toward the rear ends of the plane, said planes being formed at their forward ends with a cross sectional form conforming to one-half of an elongated ellipse and with the points of greatest curvature thereof at the sides of the planes and converging rearwardly toward the center and assuming a flat form at the rear ends thereof. In testimony whereof I aflix in Si ature.

ELMER L. C O IER. 4

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