US1887676A - Aeroplane construction - Google Patents

Description

NOV. 15, 1932. J 5 BRYLKA 1,887,676

AEROPLANE CONSTRUCTION Filed Nov. 4. 1930 2 Sheets-Sheet l gwuzhtoz wa Uh 0. 3 2%,

Saarmwoom- NOV. 15, 1932. BRYLKA 1,887,676

AERQPLANE CONSTRUCTION FilBd NOV. 4, 1950 2 Sheets-Sheet 2 Patented Nov. 15, 1932 PTET QFFICE JOSEPH S. BRYLKA, F DU BOIS, PENNSYLVANIA.

AEROPLANE CONSTRUCTION Application filed November 4, 1930. Serial No. 493,406.

This invention relates to certain new and useful improvements in aeroplane construction.

The primary object of the invention is to provide an aeroplane wherein the plane or Wing element thereof is designed to permit foldlng action of parts thereof for reducing the breadth of the aeroplane or length of the wing for occupying a minimum of space when out of use and to permit the same to be housed in a smaller aeroplane shed.

A further object of the invention is to provide an aeroplane construction wherein the plane or wing adjacent each end thereof is formed with hinged sections permitting the outer ends of the Wing to be folded inwardly above the intermediate portion of the wing for reducing the breadth of the aeroplane whereby the same may be housed in a smaller aeroplane shed and to occupy a minimum of space with latch devices associated with the outer end hinged sections to maintain them rigidly positioned relative to the intermediate section of the wing during flight.

With the above and other objects in View that will become apparent as the nature of the invention is better understood, the same consist-s in the novelform, combination and arrangement of parts hereinafter more fully described, shown in the accompanying drawings and claimed.

In the drawings Figure 1 is a top plan view of an aeroplane constructed in accordance with the present invention showing the outer end hinged sections of the plane or Wing with the ailerons carried by the hinged sections;

i gure 2 is a bottom plan view of the aeroplane showing the latch devices for holding the outer end sections of the wing in alinement with the intermediate section thereof;

Figure 3 is a top plan view showing the outer end sections of the wing folded inwardly over the intermediate section;

Figure 4: is a bottom plan view of the aeroplane with the wing in folded position;

Figure 5 is a longitudinal sectional view through the wing showing the end sections of the wing hinged at their upper sides to the intermediate portion and the latch devices associated with the lower sides of the hinged sections for retaining them in alinement with the intermediate portion of the wing;

Figure 6 is a sectional View of the wing in folded position; and

Figure 7 is a detail sectional View showing the keeper or latch for retaining the sections of the wing in alinement.

Referring more in detail to the accompanying drawings, there is illustrated an aeroplane comprising a fuselage 1 carrying a landing gear 2, an empennage 3 and equipped at its forward end with a pair of propellers 4 and 5 having the blades thereof spaced through an arc of 90 with the forwardly positioned propeller 5 being smaller than the rear propeller 4.

The aeroplane also includes a plane or wing 6 comprising a central or intermediate rigid section 7 and outer end sections 8 which carry rear edge ailerons 9. The wings 6 is of double wall construction as shown in Figures 5 to 7 with enclosed brace bars 10 and is constructed of the usual materials. H

The outer end sections 8 of the wing are hingedly connected as at 11 to the outer edges of the rigid intermediate section 7 the hinged connection 10 extending completely across the wing at the upper side thereof as shown in Figure 1 and from an inspection of Figs. 5 and 6 it will be observed that brace bars 10a are provided at the meeting edges of the intermediate and end sections 7 and 8 for abutting relation to provide a rigid Wing structure when the several sections of the wing are alined.

Latch devices are associated with the undersides of the intermediate and end sections of the wing for retaining the wing sections in alinement and include keepers carried by the end sections, one adjacent each end of the hinge connection, the keeper having one end 12 thereof extending into the end section and suitably anchored to an adjacent brace bar 10 while the other end of the keeper disposed exteriorly of the end section is in the form of a spring or resilient arm 13 as will be clearly evident from an inspection of Figure 7. A latch arm 14 is associated With each resilient keeper arm 13 and is pivotally mounted as at 15 upon the outer end of the underside of the intermediate section of the wing and is provided with a handle 16 to facilitate operation thereof, the latch arm being moved upon its pivotal mounting 15 to be engaged with the resilient keeper arm 13 as shown in Figures 2 and 7 for retaining the several sections of the wing 6 in alinement. From the above detailed description of the m invention, it is believed that the construction and operation thereof will at once be apparent, it being noted that when the latch arms 14 are released from the keepers 13, the end sections 8 of the wing 6 may be moved from their alined positions shown in Figures 1 and 2 to positions overlying the intermediate section of the wing 6 as shown in Figures 3, 4: and 6 for the reduction of the wing expanse and to permit more convenient storage of (/70 the aeroplane. The engaged brace bars 10a of the wing sections provide a rigid c011- struction when the sections of the wing are in alinement as shown in Fig. 5 and the a strength and efiiciency of the wing is not reduced in any manner by the sectional construction thereof.

While there is herein shown and described the preferred embodiment of the invention, it is nevertheless to be understood that minor changes may be made therein without departing from the spirit of the invention or the scope of the sub-joined claim.

I claim In an aeroplane, a fuselage and a wing having outer end transversely hinged sections foldable inwardly to overlie an intermediate section, the hinges being located so that the outer ends of the wings substantially abut m each other centrally of the fuselage, internalbrace bars for the wings, and means for re taining the wing sections in extended alignment including a latch keeper eXteriorly of the wing and having one end extending into an adjacent wing section to be anchored to an internal brace bar and a latch arm to be engaged by the latch keeper.

In testimony whereof I affix my signature.

JOSEPH S. BRYLKA.

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