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Publication numberUS2399839 A
Publication typeGrant
Publication dateMay 7, 1946
Filing dateSep 29, 1943
Priority dateSep 29, 1943
Publication numberUS 2399839 A, US 2399839A, US-A-2399839, US2399839 A, US2399839A
InventorsVorse Harry L
Original AssigneeVorse Harry L
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Flying machine
US 2399839 A
Images(1)
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Description  (OCR text may contain errors)

H. L. VORSE FLYING MACHINE May, 7, 1946.

Filed Sept. 29, 1945 INVENTOR fll. VO/FSE ATTORNEY Patented May 7, 1946 UNITED" STATES PATENT OFFICE FLYING mourns Barry L. vane, Portland, o Application September 29, 1943, Serial No. tomes 2 Claims. (01. 244-2a) This invention relates generally to aerial trans portation and particularly to a flying machine of the heavier-than-air type.

The main object of this invention is the development of a flying machine which will be efficient in operation, inexpensive to manufacture and maintain and easily maneuverable.

The second object is to utilize to the maximum extent the expansive action of the burning sases as a means of propulsion and steering,

The third object is to providev a unique formof skin surface for the streamlined fuselage element.

The fourth object is to achieve vertical takeoif and landing, and forward and rearward motion without the use of the conventional wing, rudder, or propeller, as well as to economize fuel, increase flying speed and safety and gain flexibility of operation.

The fifth object is to reduce the amount of head end resistance.

These and other objects are accomplished in the manner set forth in the following specification and as illustrated in the accompanying drawing, in which:

Fig. 1 is a side elevation of the machine with the major portion thereof broken away in vertical longitudinal section.

Fig. 2 is a plan of Fig. 1 with the foremost and rearmost portions thereof broken away in longitudinal horizontal section.

Fig. 3 is a fragmentary perspective view showing the relationship of the power generator to the special airfoil construction.

Fig. 4 is a section taken along line 4-4 in Fig. 3.

Fig. 5 is a front elevation of the machine.

Fig. 6 is a longitudinal section through one of the injectors.

Similar numerals refer, throughout the several views.

Referring in detail to the drawing, there is shown a streamlined shell I. having a pointed rearward end II and a somewhat blunt forward end I! around which is mounted a cylindrical shell l3, Disposed within the shell II is the transverse floor ll terminating in the inclined ramp I! at the lower end of which is formed a head It which extends to the upper side I! of the shell Ill forming a pressure compartment l8.

to similar parts A portion of the upper side l1 over the compartment ll ls stepped as shown in Figs. 3 and 4 so that the riser I! of each step shall form the discharge of the Venturi tube 2|. Directly behind the Venturi tube It is formed a depressed chanagainst a valve 38 when tube I2 with the intermediate point of the Venturi tube 20. Each channel 2| has on its rearward side an inclined surface 23 which merges with the top or tread 24 of the next step.

In the forward end of the shell III is disposed a cylindrical power generator II to which fuel may be drawn from the tank 20 through a pipe 2! by any convenient means, preferably a pump II. The purpose of this arrangementis to permit the fuel to be burneddirectly within the power generator II, means being provided for selectively energizing the various pumps 20 to vary the rate of burning.

The power generator is connected by various pipes 20 which are diagrammatically shown in solid lines in Fig. 3 and communicate through the head II with the compartment l8. Communicating with the power generator 25 is a pipe II which extends rearwardly to the three-way valve "-A having a right hand discharge outlet Ii and a left hand discharge outlet 32 and a rearward discharge outlet 33. The valve 3il--A may be operated manually or in any other convenient manner without departing from the spirit of this invention.

In Fig. 6 is shown the amplifiers M which are simply injectors drawing air from the open end Ii through the intake openings ll which are normally held in an open position but are immediately closed by the action of-the spring 31 the pressure within the amplifier ll drops for any reason. Obviously, the quantity of gas and air delivered by each ampliher male greatly exceeds the amount of gas supplied by the power generator 25., the ratio of volume being approximately thirty times the original amount of hot gas delivered thereto.

A suitable grille 40 is provided for the opening end 3! and similar closable grilles ll for the lateral openings II.

The operation of the device is as follows: When the pump 28 is operated and fuel is drawn from the tank 28 through the pipe 21 and burned within the power generator 25, there is naturally built up a pressure by of the hot gases and this gas is permitted to flow through thepipes 29 through the respective ampliflers 34 where cold air is entrained and the burned gas mixed with air at a corresponding- 1y increased volume is deliveredto the compartment I. from whence it escapes thru the airfoil by way of the aspirators 2|! which are flattened Venturi tubes extending transversely to the fuselage and with their flow axis extending longitunel II which communicates by means of the dinallyto the fuselage. The gases now flow from increase in temperature a the aspirators 20 over the various members 24 producing the desired lifting action.

Attention is drawn to the fact that two distinct; and yet importantly related results are obtained by this arrangement. First, the zone of reduced pressure is formed above each surface 23 due to the withdrawal of air from the depressed channel 2| through the tube 22 by the action of Venturi tube 20. This definitely increases the lifting eifect'over each surface 23 while the retarding action of the boundary layer over the surface 23 is greatly reduced by the flow of air from the tube 20. While this is taking place and due to the withdrawal-of air from the vestibule 43 within the forward end l2, there is produced an atmospheric unbalance between the front and rear end of the fuselage, thereby urging the aircraft in a forward direction.

It will be further noted that the very element, namely, air or a mixture of air and products of combustion, by means of which the aspirators afford lift to and hold the whole fuselage in aerial suspension, is the selfsame element that, by means of the injectors, indirectly imparts lateral motion to the fuselage.

Attention is drawn to the fact that the lateral openings 42 may be closed or opened by the respective grilles 4| by means of which air is supplied for take-off, landing, and pivoting while lateral motion of the aircraft is not desired and the forward air valve is closed.

In flight or otherwise, air jets are derived from the influx of air into the yestibule, and are used to eliminate air pockets at the tail of the fuselage, and to act as arudder, all ofwhich are actuated throughthe valves till-A at the will of the operator.

It can be seen from the foregoing that while the 7 drawing has been made somewhat diagrammatically for the purpose of giving a clear understanding of the invention without concealing the principle beneath the mass of details, that there has been provided a radially new and yet novel combination of old and tried elements and phenomena in order to produce a heavier-thanair flying machine having radically diflerent characteristics over any other machine in use at the present time.

While I have thus illustrated and described my invention it is not my intention to be limited to the precise form shown herein but I do intend to cover such form and modification thereof as fall fairly within the appended claims:

I claim:

1. In a device of the class described, a fuselage surface consisting of a plurality of stepped aspirators, each aspirator consisting of a transversely elongated Venturi tube having its outlet on the step riser, a space between successive steps consisting of a depression directly behind the riser terminating in a convex incline tangent to the following step, connections .between each depressed area and the suction side of the Venturi tube and means for supplying gas to said aspirators from the under side thereof.

2. A device of the class described including a streamlined fuselage having a top surface thereof formed of a plurality of steps, the risers of which face the rear of the fuselage, each of said risers having elongated Venturi tubes discharging there-through in'a manner that the discharge therefrom shall pass over the next lower riser and means for coupling the low pressure point in the Venturi tube to the low at the foot of the step riser.

HARRY L. VORSE.

pressure zone disposed

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2475786 *Dec 22, 1945Jul 12, 1949Jordan John LAirship
US2659202 *Jun 6, 1950Nov 17, 1953Fay E NullAugmented thrust pulse jet pump or motor and method of creating augmented thrust or suction
US2873931 *Aug 24, 1953Feb 17, 1959Fleischmann CarloBoundary layer control apparatus for improving the action of aircraft
US5480110 *Mar 25, 1994Jan 2, 1996Daimler-Benz Aerospace AgTransport plane with stub tail
US5505409 *May 20, 1994Apr 9, 1996Wells; Anthony R.Supercavitating airframe
Classifications
U.S. Classification244/23.00R, 244/207, 244/52, 60/264, 60/229
International ClassificationB64C29/00
Cooperative ClassificationB64C29/0041
European ClassificationB64C29/00B3