US1491581A - Flying machine - Google Patents

Description

Aprifl z z; 1924, 1,491,581

J. F. BRADY FLYING MACHINE Filed Abril 24. 1920 L H mn patented Apr. 22, 124.

- JOHN F. BRADY, OF COLORADO SPRINGS, COLORADO;

FLYING MACHINE.

Application filed April 24, 1920. Serial No. 376,250.

To all whom it may concern Be it known that I, JOHN F. BRADY, a citizen of the United States, and a resident of Colorado Springs, in'the county of El Paso and State of Colorado, have invented certain new and useful Improvements in Flying Machines; and I do hereby declare that the following is a full, clear, and exact description thereof. reference being had to the accompanying drawings, and to the letters of reference marked thereon, which form a part of this specification.

This invention relates to improvements in flying machines, and consists of the matters hereinafter described and more particularly pointed out in the appended claims.

The object of the invention is to provide a simple and efficient means, applicable to any type of flying machine, by which the buoyancy thereof may be readily increased and maintained, after the same has reached a predetermined altitude in its flight. The invention is herein illustrated and described as applied to and used in connection with a heavier-than-air type of a. flying machine, but may as readily be applied to and used in connection with a ,lighter-tha-n-air type of flying machine.

The advantages of the invention will be pointed out as I proceed with my specification.

In the drawings:

Figure 1 illustrates, in side elevation, a modern type of aeroplane to which my invention has been applied.

Referring now in detail to that embodiment of the invention illustrated in the accompanying drawings :-5 indicates the fuselage of the aeroplane, 6 indicates the supporting planes, and 7 indicates the propeller at the front or how end 8 of the fuselage. Said propeller is driven in the usual manner by an engine or motor 9, located in the bow end ofthe aeroplane. 10 indicates the aviators cockpit and 11 the observers cockpit. 12 indicates the landing gear, and 13 the skid associated with the landing gear which skid is of the usual kind arranged near the vertical and horizontal rudders 14.

15 indicates a longitudinal header pipe. closed at both ends and preferably secured by means of brackets 16 to the top surface of the fuselage 5, along its longitudinal median line, back of the observers cock pit 11. Throughout the length of said pipe are disposed, longitudinally-spaced valve casings 17 from which rise perpendicular branch pipes 18. Each of said pipes terminates in a bracket plate 19, by means of which is provided a plurality of stepped platforms or bases 20, one for each pipe 18, said platforms being defined fore and aft by upright, longitudinally spaced flanges 21.

Secured in suitable manner to each stepped platform, is the open bottom end of a vertically, elongated balloonette, or bag 22, made of a soft. flexible, air-tight textile material. Each bag in cross-sectional area approximates the horizontal axes of its associated platform 20. Each bag is collapsible in accordion pleated folds upon its associated platform as shown in the drawings,

the fore and aft vertical flanges 21 of the platform 20, providing a support for'the balloonette or bag, when in this position.

Each valve casing 17, has associated with it an arm 23 for actuating the contained valve mechanism. The several arms are connected by links 24 to associated actuating levers 25, pivoted on the side of the fuselage adjacent to the cock-pit 10, Within convenient reach of the aviator.

Connected to the pipe 15, between two of the valve casings 17, is a short pipe 26, which forms a continuation of a long pipe 27, extending along the side of the fuselage 5. The forward end of this pipe enters into the how 8 where it is connected to an air pump 28 within said how.

The pump 28 (shown in dotted lines) has an air inlet 29, and is adapted to be driven by the engine 9 in any convenient manner,- suitable means (not shown) being provided to connect or disconnect'the pump to and from the engine 9. In the pipe 27. adjacent the levers and Within convenient reach of the aviator is a hand valve 30, 'which' may be actuated to control the escape of air from the pipe 27 when itis desired to deflate the balloonettes 22.

The operation and use of my invention as applied to the aeroplane described is as follows :Assume that the aeroplane is in flight and that the balloonettes are deflated and are collapsed upon their associated platforms. IVhen the proper high altitude (say 30,000 feet) is reached, where the rarefied air approximates about four pounds per square inchof surface, one or more of the levers 25 may be actuated to open one or more of the valves 17, in the pipe 15 for the associated balloonette 22. The pump 28 is then connected with the engine 9 and the rarefied air is drawn or sucked in through the inlet 29 and is discharged through the pipes 27 and 26 into the header pipe 15, and thence through the open valve or valves 17, into the associated balloonettes,thus expanding and filling them with said rare air. When the desired number of balloonet-tes have thus been inflated with the rarefied buoyant air, the levers 25 are operated to close the valves 17 and the pump 28 is disconnected from the engine 9.

The advantage of using air of high altitude to fill the balloons is apparent. Ifhe air of the higher altitude will manifestly give buoyancy to the aeroplane in the denser atmosphere of the lower altitude, the containers or balloons inflated with the air of the high altitude floating on the denser air nearer the earth, as a cork or any lighter than water body will float on the water. The buoyancy is inversely in proportion to the pressure of the air at the higher altitude, as compared to the pressure of the denser air at the lower altitude. This proportion is readily calculable.

In addition, the air of the higher altitude has its different elements reduced in proportion and when brought to earth, besides being used as a lifting agent, it may be used for many urposes, owing tothe natural reduction o the several elements.

Any number of balloonettes or containers may be used, and they may be applied to flying machines of any construction or de-' sign,-that shown in the drawings being merely for urposes of illustration.

'While in escribing my invention, I have referred to many details of construction and arrangement, it will be understood that the invention is in no way intended to be limited thereto, except in so far as may be pointed out in the appended claims.

I claim as my invention 1. In combination with a flying machine including a fuselage having a cock pit and an engine in said fuselage forward of said cockpit, a header pipe secured to the median line of said fuselage back of the cockpit, upright branch pipes, valve'devices connecting said upright branch pi es with said header pipe, an air pump in t e fuselage adjacent the engine and adapted to be driven thereby, a conduit connecting the Ipump with the header pipe, a plurality o collapsible air tight bags, oneconnected to each upright branch pipe, and means carried by the fuselage adjacent the cockpit for actuating said valve devices.

2. In combination with a flying machine including a fuselage having a cockpit and an engine in said fuselage forward of said cockpit, a header pipe secured to the median line of said fuselage back of the cockpit, up-

.right branch pipes, valve devices connecting said upright branch pipes with said header pipe, an air pump in the fuselage adjacent the engine and adapted to be driven thereby, a conduit connecting the pump with the header pipe, a plurality of collapsible air tight bags one connected to each upright branch pipe, stepped supports carried at the ends of said-branch pipes for holding said bags when in collapsed condition, and means carried by the fuselage adjacent the cockpit for actuating said valve device.

3. In combination with a flying machine including a fuselage having a cockpit, a

header pipe mounted on the fuselage to the rear of the cockpit and extending in the longitudinal median plane of said fusela a plurality of platforms mounted on. t e header pi e, air tight ba s one on each platform, an a conduit lea ing to said header pipe, from a suitable source of air supply.

In testimony that I claim the foregoing as my invention, I aflix my signature in the presence of two witnesses, the 19th day of April, A. D., 1920.

HAZEL V. ORR, H. T. MCGABRY.

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