US1911041A

US1911041A - Aircraft

Info

Publication number: US1911041A
Application number: US542025A
Authority: US
Inventors: James S Smyser
Original assignee: Individual
Current assignee: Individual
Priority date: 1931-06-04
Filing date: 1931-06-04
Publication date: 1933-05-23
Anticipated expiration: 1950-05-23

Description

3, 1933. J. 5. sMYsER 1,911,041

AIRCRAFT Filed June 4, 1931 //V) f/V702 Jam; 5440:;

Patented May 23, 3933 JAMES S. SMYSER, OF BOSTON, MASSACHUSETTS AIRCRAFT Application filed June 4,

The object of this invention is to provide a novel lifting unit of simple design and effioient operation which will enable an aircraft to rise vertically from the ground without the necessity of horizontal speed.

In accordance with my invention I provide a lifting unit comprising one or more an nular aerofoils designed so that a continuous current of air discharged substantially radially thereof impinges upon their upper and lower surfaces to create a diminished pres: sure above and an increased pressure below each of the aerofoils, thereby producing a resultant force exerting a direct lifting ef- 17 fect thereon, the driving mechanism being so designed to overcome gyroscopic and torsional reaction. In conjunction with this unit means may be provided for changing the direction of the resulting force, relative 9 to the vertical, thereby to cause a lateral or horizontal movement of the craft.

One embodiment of my invention, chosen for the purpose of illustration, is shown in the accompanying drawing in which: Fig. 1 is a topplan view;

Fig. 2 is an enlarged elevation, partly in section; and

Fig. 3 is a section on the line 33 of Fig. 2. Referring to the drawing, particularly to Fig. 2, the numeral designates a platform which is provided with a landing gear comprising wheels 11 journaled in brackets 12 which are secured to the under side of the platform. The frame members Mare firmly secured to the platform and provide a rigid support for the lifting unit which preferably comprises a base 15 on which the motor 16 is mounted. The

struts

17 and 18, mount- .ed on the base 15, rigidly support the concentrically disposed

annular aerofoils

19 and 20. In order to increase the rigidity of the structure, suitable reinforcements such, for example, as tie-rods 21 may be provided.

A pair of brackets 22, mounted on the housing of the motor, support the transmis- 1931. Serial No. 542,025.

sion mechanism, designated generally by the numeral 25, which preferably comprises an eplcyclic bevel gear train having

driving gears

26 and 27 of'the same' size, the gear 26 being direct-connected to the driving shaft of the motor 16 and the idlergears being 1ournaled in the brackets'22. The

driving gears

26 and 27 are keyed or otherwise secured to the

telescoping shafts

28 and 29, respectlvely, which are concentrically disposed relative to the

aerofoils

19 and 20. Preferably the

shafts

28 and 29 arejournaled in cross bars 30. and 31 carried by struts The centrifugal fan 35 mounted on the shaft 28 is disposed, relative to the aerofoil 19, to discharge substantially radially thereof a continuous current of air which'implnges upon the opposite faces of the aerofoil. The fan 36, mounted on shaft 29, is of the same design as fan 35, having the same weight and moment of inertia, and is similarly disposed relative to the aerofoil 20. Preferably the fan 35 is-provided with a plate 37 secured to its under side to confine v the air intake to its opposite side, and like wise the fan 36 carries plate 38 on its upper side to confine the intake to the lower side, thereby preventing the intake currents, shown by the curved arrows in Fig. 2, from interfering with the high velocity currents discharged by the fans. It will be noted that as the

driving gears

26 and 27 are of the same size and rotate in opposite directions, the fans-35 and 36 are driven synchronously in opposite directions and thus, their velocities and moments of inertia produce substantially equal and opposite torques which overcome the gyroscopic and torsional reaction which would otherwise develop.

Suitable means may be provided for causing a relative horizontal movement of the craft, and although this may be accomplished in various ways a preferred method comprises changing the direction of the resultant thrust on the aerofoils, relative tothe vertical, by varying the center 'of gravity of the craft. To this end, I provide the weight 40 which is adjustably mounted on a bar 41, pivotally secured to the platform, the bar being provided with a set screw 42 by means of which the same may be locked in any angular position. Various" means such as a rack and pinion, screw shaft, or the like, may be employed for adjusting the longitudinal position of the weight relative to the bar and/or swinging the bar about its pivot.

7 As. shown in Fig. 3 the bar 41 is provided with a dovetail flange 42 which interfits with the dovetail recess of the weight 40 and secures the same to the bar. The weight is provided with a set screw 43 engageable with the flange 42 to lock the weight to the bar.

Obviously the weight may be located in any desired position, and may not only serve to vary the relative direction of the resultant thrust on the aerofoils but also to provide a mechanical stabilizer.

An aircraft embodying the features herein shown and described may be built on a small scale as a model or toy as well as on a larger scale for commercial uses.

I claim:

1. An aircraft comprisin a pair of annular aerofoils in superpose spaced relation to each other, centrifugal fans disposed concentrically with said aerofoils for discharging a current of air against the opposite faces of each of said aerofoils to produce a resulta direct lifting effect on said aircraft, an means for rotating said fans in opposite directions at a constant speed ratio.

2. An aircraft comprising a pair of annular aerofoils, frame members supporting said annular aerofoils in superposed spaced relation, telescoping shafts arranged concentrically with said aerofoils, centrifugal fans having substantially the same moment of inertia mounted on said shafts, said fans being arranged to discharge continuous currents of air against the opposite faces of said aerofoils, and means for rotating said fans synchronously in opposite directions.

3. An aircraft comprising annular aerofoils, centrifugal fans dlsposed concentrically with said aerofoils for discharging a current of air against the opposite faces of each of the aerofoils, said fans having substantially the same moments of inertia, and driving means for rotating said fans synchronously in opposite directions.

4. An aircraft com rising two annular aerofoils, centrifugal ans disposed concentrically-with said aerofoils and arranged to discharge currents of air substantially radially against said aerofoils, said fans havsubstantially the same moment of inermeans for rotating said fans synchrodlrections, and means ming tia, nously 1n opposite air against the opposite faces of said aerofoil to produce a resultant force exerting a direct lifting effect on said aircraft, a rotary mass concentrically arranged relative to said shaft, said mass andcentrifugal fan having substantially the same moment of inertia, a d means for rotating said mass and fan synchronously in opposite directions.

6. An aircraft comprising an annular aerofoil, a driving shaft concentric with said aerofoil, a fan mounted on said shaft and arranged to discharge a current of air against the opposite faces of said aerofoil to produce a resultant force exerting a direct lifting effect on said aircraft, a rotary mass concentrically arranged relative to said shaft including transmission mechanism, -and a motor and transmission mechanism for driving said shaft and mass in opposite directions at a constant speed ratio, the respective moments of inertia of said mass and fan being such as to produce substantially equal and opposite torques on said aircraft.

7. An aircraft comprising two annular aerofoils, driving shafts concentric with said aerofoils, centrifugal fans mounted on said shafts, said fans being arranged to discharge currents of air substantially radially againstthe opposite faces of said aerofoils, and means including a transmission mechanism for driving said shafts in opposite directions at a constant speed ratio, the respective'moments of inertia of said fans being such as to produce substantially equal and opposite torques on said aircra v 8. An aircraft comprising an annular aerofoil, a driving shaft concentric with said aerofoiha fan mounted on said shaft and arranged to discharge a current of air against the opposite faces of said aerofoil to produce a resultant force having a direct lifting effect on said aircraft, a rotary mass having substantially the same moment of inertia as said fan concentrically arranged relative to said shaft, means for rotating said mass and fan synchronously in op osite directions, and means independent 0 said fan and aerofoil for changing the direction of said resultant force to cause a relative hori. 'zontal movement of said aircraft.

- 9. 'An aircraft comprising two annular aerofoils, driving shafts concentric with said aerofoils, centrifugal fans mounted on I foils, means including a transmission mechanism for driving said shafts in opposite directionsat a constant speed ratio, the respective moments of inertia of said fans being such.as to produce substantially equal and opposite torques on said aircraft, and means independent of said fans and aerofoils for changing the direction of the resultant force to cause a relative horizontal movement of said aircraft.

Signed by me at Boston, Massachusetts, this 2d day of June, 1931.

JAMES S. SMYSER.