US1457871A

US1457871A - Aeroplane construction

Info

Publication number: US1457871A
Application number: US481292A
Authority: US
Inventors: Bonsiakos Michael
Original assignee: Individual
Current assignee: Individual
Priority date: 1921-06-29
Filing date: 1921-06-29
Publication date: 1923-06-05
Anticipated expiration: 1940-06-05

Description

June 5, 11923.

M. BONSIAKOS AEROPLANE CONS TRUCT ION Filed June 29, 1921 chine may Patented dame 5, 1223..

MICHAEL nensrnnos, OF SAN FRANCISCO, CALIFQRNIA.

AEROPLANE CONSTRUCTIUN.

Application tiled June 29, N21.

State of California, have invented new and.

useful Improvements in Aeroplane Constructions, of which the following i a specification.

This invention relates to air craft and particularly pertains to the propulsion of heavier-than-air machines.

It is a principal object of the present in vention to provide an air craft, as, for example, an aeroplane, equipped with'fiuid propulsion means, operating without the use of the usual, .propeller, and which will insure that the craft may be rapidly propelled and easily controlled while taking flight, landing, or during the course of its flight.

The present invention contemplates the use of an aeroplane equipped with impulse nozzles through which a fluid under pressure is exhausted into the air to produce an impulse reaction sufficient to move the aeroplane in a counter-direction to that of the exhaust; said craft being further e nipped with nozzles by which the body of t e mabe swung in any desired direction.

The invention is illustrated byway of example in the accompanying drawings, in.

which V Fig. 1 is a view in longitudinal section in elevation showing the general arrangement of the parts of the present invention; Fig. 2 is a view in front elevation show in the craft disclosed in Fig. 1.

i' ferring more particularly to the drawing, 10 indicates the body of an aeroplane formed with the usual fuselage 11, cock-pit 12 and en 'ne cowl 13. Suitable wings 14 are provi ed for the support of the machine. At the rear of the body portion of the craft a horizontal stabilizer 17 is mounted. Thisstabilizer may be equipped with elevator members 18, if desired, although it is not believed that the present invention will require such. a structure.

5Tt is-tobe understood that the particular type of machine is immaterial to the present invention; and that the invention is more particularly concerned with means for propelling and controlling the direction of Serial Etc. 481,292.

flight of the craft. For this purpose a suit able engine 19 is mounted within the cowl portion of the body and is connected with an air compressor 20. The air compressor is in communication with a storage tank 21 within which the surplus air may be stored for use as desired. This communication is established through a pipe .22. The induction port of the compressor is connected with an inlet pipe 23 which extends forwardly through the nose of the engine cowl and receives the incoming air. rotary motor 24 is placed in the path of this air and may be suitably connected with means on the machine for generating electric current. The propulsion means of the present invention comprises a plurality of nozzles 25. These nozzles are arranged in sets around the body of the aeroplane and are directed, with their eduction ports, rearwardly. The nozzles of each set are in communication with an annular distributing member 26. This member is connected with a front air reservoir 27 by means of a pipe 28. A control valve 29 is provided to permit air from this valve entering the distributing chambers 26. I

By reference to Fig. 1 it will be noted that there are two sets of nozzles 25, and it is to be understood that any number of sets may be provided, as re uired. The distributing chambers 26 o the two sets of nozzles are connected by a pipe 30 so that air may be simultaneously delivered to the two sets of nozzles. The basic principle of this invention is concerned with the fact that the re-action roduced by the violent exhaustion of air rom the nozzles 25 in a direction toward the rear of the machine will cause the machine to be moved forwardly.

The direction of flight of the machine is controlled by levers 31 which maybe selectively operated to open valve members 32 controlling ports 33. The ports 33 are formed in the top, bottom and sides of. a-

steering box 34. This box is secured at the rear of the aeroplane body, and it will be evident that when air is exhausted from any box 34 from the tank 27 through the pipe 34. Air pressure is therefore maintained in the box at all times.

In addition to the advantages obtained by pro elling the aeroplane in the manner descri d and determining its course of flight, the landin of the machine may be readily brought a out in case of accident to the driving mechanism, due'to the fact that a considerable quantity of compressed air'will be stored in the rear tank 21 and forward tank 27, thus making it possible to propel the machine some distance after the engine is stopped.

In the operation of the present invention, the machine is assembled, as shown in the drawings, and after this the engine may be set in operation to accumulate a desired store of air in the tanks 21 and 27. This air will be drawn in through the pipe 23 to the come pressor 20 and delivered'from the compressor to the forward storage tank 27 through a pipe 27. Additional air will be conveyed through the pipe 22' to the rear tank 21. When it is desired to start the machine the valve member 29 is manipulated to establish communication between the forward distributing chamber 26 and the air pipe 28. Air will instantly flow through all of the distributing chambers 26 and will be violently exhausted from the nozzles 25, four of which are shown in each set. This will cause the aeroplane to move forwardly and, by suitable mani ulation of the control members 31- the aerop ane ma take flight. The course of flight may be etermined by opening the various 'orts 33 in the steering box 34.

It wil thus be seen that by constructing an aeroplane as shown in the drawings and providing a flow of-air travelling at a suflicientliv 111 h velocity, the craft may be propelle an its direction of travel readily determined.

While I have shown the preferred form of my invention, it is to be understood that va rious changes may be made b those skilled in the art without departing om the spirit of my invention.

Having thus described my invention, what I claim and desire to secure by Letters Patent is:

1. An aeroplane propulsion means comprising a plurality of rearwardly extending nozzles arranged in groups around the body of the-aeroplane; a powerplant; air compression means driven by said power plant; and controlling means between sor and the nozzles. k

2. An aeroplane propulsion means comprising a plurality of rearwardly extendmg nozzles arranged in groups around the body of the aeroplane; a power plant; air

compression means driven by said power plant; controlling means between the communication with said com ressor; and means operated by the flow 0 air to the compressor for generating power.

4. An apparatus'ofthe haracter described including an airplane body having win air compressing means mounted in the a plurality of air manifolds circumscribing the bod rearwardly directed nozzles on the manifo ds, a fluid connection between the air the compres compressing means and the manifolds, an

air storage tank means for directing the air into the manifolds'and the storage tank, an air controlled steering apparatus comprising the machine and having outlets in its top and bottom walls and its opposite side walls, a closure for each of said outlets, means for admitting air to said compartment, and means for controlling said closures from the drivers seat.

MICHAEL BONSIAKOS.

an air compartment arranged at the rear of