US1765972A - Aeroplane safety device - Google Patents

Description

June 9 K. FECHTER AEROPLANE SAFETY DEVICE Filed June 14, 1928 LOW J/ w07r% I Patented June 24, 1930 4 KURT rnon'rnn, or JoLIn'r, ILLINOIS AEROPLANE SAFETY DEVICE Application filed June 14,

This invention relates to heavier-than-air crafts and more particularly to safety devices therefor, although certain features thereof may be employed with equal advanatage for other purposes.

It contemplates more especially the provision of means for creating an emergency increased buoyant effect which materially relieves the propelling device and enables such unnecessary to retain the craft in the air to materially impede its descent incident to the forced or otherwise inoperation of the motor or any component element of-the propelling mechanism. I

Aeroplanes and other heavier-than-air crafts have proven to be very successful for commercial and sport purposes. Of late, these vehicles have acquired a prominent position in the art of transportation, and although comparatively dependable considering their present erformance, yet these are not sufliciently sa e to render flying heavierthan-air crafts an indispensable means of transportation.

Numerous expedients have been proposed for increasing operation of such crafts with much safety but nothing has heretofore been proposed which precludes mishaps coincident with the failure of the motor or other component elements of the propelling mechanism. The parachute serves the purpose to a substantial degree, yet such' is not'entirely dependable and in every instance re ults in complete destruction to the air vehicle or 5 craft.

One objectof the present invention is to provide a safety device which materially increases the buoyancy of heavier-than-air crafts to an extent of insuring the landing thereof with safety.

Another object is the provision of means operative responsive to an emergency to maintain a heaVier-than-air craft aloft at any desired elevation.

Still another object is the provision of a normally collapsible container which is capable of inflation foremergency purposes to impart sufficient buoyancy to a heavier-thanair craft so as to enable a safe landing without destruction to life or limb.

i928. Serial No. 285,293.

v A further object is the provision of means for normally confining a lighter-than-air medium under pressure so as to effect the inflation of a container associated with the craft for the purpose of controlling or at least retardin the descent during the inoperation of the propelling mechanism.

A still further object is the provision of a v collapsible container which is associable with a heavier-than-air craft in a manner to enable the immediate inflation thereof by means independent of the propelling mechanism.

Still a further object is the provision of means for enabling the use of a lighter-thanair medium to maintain a heaVier-than-air craft aloft or retard the descent thereof responsive to the inoperation of the propelling mechanism. 7

Other objects and advantages will appear from the following description of an illustrative .embodiment of the present invention.

In the drawing:

Figure 1 is a side View in elevation of an aeroplane with parts thereof shown in seotion to clarify features of the present invention.

Figure 2 is a plan-view of the vehicle disclosed in Figure 1.

Figure 3 is a diagrammatic sketch ofcoor- 8 dinating instrumentalities capable of increasin the buoyancy of heavier-than-air. crafts or the purpose set forth.

The heavier-than-air craft selected for illustration comprises an aeroplane having the 5 usual fuselage 1O communicating with a hood 11 which conceals the engine constituting the motive power for a propeller 12 secured to the crank shaft 13 of the motor (not shown).

Wheels 14 constituting the landing gear are associated with the body of the aeroplane by means of divergent brackets 15 of standard construction to enable the landing thereof without impact, injury or destruction. Horizontal wings 16 and 17 project laterally of the fuselage 10 to assist the ascension of the craft responsive to the rotation of the propeller 12, the wings 16 and.17 being maintained in superposed position by a plurality of rods 18 disposed therebetween. The fuselage 1.0 terminates in a rudder 19 of standard construction which is connected to the controls within the cabin 20 for guiding the maneuvers of the craft.

In order to increase the buoyant effect of the craft either during the improper functioning of the pro 'ielling mechanism or responsive to the total failure thereof, a safety expedient is provided. This comprises a suitable tank for confining a lighterthanair confining medium within the craft in a manner which will not impede the progress thereof during normal traverse occasioned by the propelling mechanism 12. Another gas confining medium, in this instance, a collapsible container 21 is provided for inflation by the gas under pressure within the tank. The container 21 is preferably T-shaped to enable the association of a substantial portion thereof with the wing 17 which may, as in this instance, be hollow and so shaped as to define a maximum interior space to receive the head portion of the container 21 therein.

The remainder of the collapsible container 21 terminates in a tail 22 which projects through a suitable slit 23 provided in the edge 24 of the wing 17, it being noted that the lower wall 25 thereof may be hinged or otherwise supported at 26 to enable the recisiou thereof to admit the introduction of the container 21 therein. It is possible, however, to render the slit 23 of sufficient magnitude as to enable extrusion of the container 21 therethrough so that the tail 22 projects therefrom on the fuselage 10 for the entire length thereof. To this end, the fuselage 10 is provided with bow rods 27 which are spaced at suitable distances for secural to the craft, these being maintained in position by a longitudinally disposed cross rod 28 secured to the wing 17 and the terminal bow rod 27 situated adjacent the rudder 19. A suitable cover 29 composed of fabric or other suitable material envelopes the rods 27 and 28 to completely conceal the tail 22 of the container 21 from the effects of the wind or the elements.

A supply of lighter-than-air gas such as helium is confined in a metallic tank 30 which is disposed within the fuselage 10, the gas being held therein under considerable pressure to enable the accommodation of a maximum supply for expansion purposes within the collapsible container 21. Conduits 31 and 31 communicates with the tank 30 and the collapsible container 21, there being spaced valves 32 and 33 provided in conduit 31 to provide when open a flow from the tank 30 to the container 21 to effect the inflation thereof. As shown, the conduit 31 communicates with a conduit 34 which connects at one end with the tank 30 and at the other with a pump 35 disposed adjacent thereto. A valve 32 is positioned at the juncture of the conduit 31 and34.- to effect the connection of the high side of the pump 35 with the tank 30. l/Vhen so connected,

conduit 31 is closed to bag 21.

Another conduit 36 communicates with the low sidcof the pump 35 for connection with valve 33 to enable the selective connec tion or disconnection of the pump 35 between the tank 30 and bag 21. It is to be noted that the valves 32 and 33 are of the two-way type of standard construction which are capable of manipulation to effect a direct flow from the tank 30 through the conduits 31 and 31 to the container 21, thereby automatically shutting off the pump completely from the gas line. To deflate the container 21, the valve 32 is so adjusted to effect communication between the pump 35 and the tank 30, and the valve 33 is manipulated to create communication between the low side of the pump and theconduit 31 so that the portion 31 of the conduit 31 between the valves and 33 will be entirely closed to the tank or pump.

Deflation of the container 21 is effected, as indicated by manipulating the valves 32 and 33 to connect the low side of the pump to communicate directly therewith and operating to pump 35 to force the gas therein into tank 30 for recontinement therein. With the inflation of the container 21, the buoyancy of the craft is materially increased to the extent that it may remain aloft or its descent retarded materially to enable the safe landing responsive to the inoperation of the propelling mechanism 12. The container 21 is of such size and capacity as to create the required buoyancy to effect the specified purpose, it being noted that such is capable of variation to meet the demands of particular crafts. The collapsible container 21 may be segregated into two portions so that the container confined Within the wing 17 will be separate and independent from the portion disposed above the fuselage 10. In such a case, the tank 30 communicates with both containers or if commercial practice dictates, the Wing 17 may be made gas tight to entirely dispense with the necessity of a collapsible container therein. The portion of the collapsible container 21 Within the wing 17 may be of substantial size, since the lower wall 25 of the wing 17 may be lowered to permit the total inflation thereof, thereby increasing the air displacement and buoyant effect thereof.

An electrical motor 37 is operatively connected to the pump 35, both being confined in a unitary casing to effect the rotation of the pump for inflating or deflating the container 21 as may be required from time to time. The motor 37 is preferably connected motor and pump in unison. This is highly desirable in that the safety device constituting a gas confining medium will necessarily be resorted to for emergency purposes at which time the propelling mechanism is rendered inoperative.

With the arrangement of arts above described it will be apparent t at a novel device has been provided to render an air craft sufficiently buoyant to retain an elevated position without forced descent where injury and destruction thereto would be inevitable.

Various changes may be made in the embodiment of the invention herein specifically described without departing from or sacrifici'ng any of the advantages thereof as defined in the appending claims.

I claim:

1. In an aeroplane safety device, the com -municating means to selectively inflate or deflate said container.

2. In an aeroplane safety device, the combination with a heavier-than-air craft having a hollow wing, of a collapsible container in said wing and projecting therefrom for disposition on the fuselage of said craft, a tank for confining lighter-than-air gases under pressure, valved means for establishing communication between said tank and container, a pump connected to said communieating means to selectively inflate or deflate said container, and a motor connected to said pump to effect the operation thereof.

3. In an aeroplane safety device, the combination with a heavier-than-air craft having a hollow wing, of a collapsible container in said wing and projecting therefrom for disposition on the fuselage of said craft, a

tank for confining lighter-than-air gases under pressure, valved means for establishing communication between said tank and container, a pump connected to said communicating means to selectively inflate or deflate said container, a motor connected to said pump to effect the operation thereof, and an energy supply harnessed to said motor to propel said pump independent of the craft propelling means.

4. In an aeroplane safety device, the combination with a heavier-than-air craft, of a container associated with said wing, a collapsible container constituting an extension of said wing container for disposition on the fuselage of said craft, a tank in the fuselage of said craft for confining a li hterthan-air gas under pressure, a valve passage connecting said tank and container, and

a pump for inflating or deflating said containers with the gas normally confined within said tank.

5. In an aeroplane safety device, the combination with a heavier-than-air craft, of a container associated with said wing, a collapsible container constituting an extension of said wing container for disposition on the fuselage of said craft, a tank in the fuselage of said craft for confining a lighter-than-air gas under pressure, a valved passage connecting said tank and container, a pump for inflating or deflating said containers with the gas normally confined within said tank, and means for confining said container extension against displacement on the fuselage.

6. In an aeroplane safety device, the combination with a heavier-than-air craft, of a container associated with said wing, a collapsible container constituting an extension of said wing container for disposition on the fuselage of said craft, a tank in the fuselage of said craft for confining a lighter-than-air gas under pressure, a valved passage connecting said tank and container, a pump for inflating or deflating said containers with the gas normally confined within said tank, and means for limiting the inflatable extent of said container extension to serve as a protector therefor.

KURT FECHTER.

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