US1405667A - Aeroplane - Google Patents

Description

I. CARLSO N.

AEROPLANE.

APPLICATION FILED NOV. 6. i920.

2 SHEETS-SHEET I- Iaoented Feb. 7, 1922.

INSLE'NTDFE.

ATTDHNEY I I. CARLSON.

AEROPLANE.

APPLICATION FILED NOV. 6., 1920.

Patented Feb. 7, 1922.

2 SHEETS-SHEET 2.

I iMYENTUE.

UNITED STATES.

PATENT OFFICE.

rvm OABLSON, or momms'rna, MASSACHUSETTS, ASSIGNOB, or ONE-Tm m exam ommo, or LOWELL, mssaonusnr'rs, AND one-m To 301m may LYNCH, or raw'rucxn'r, nnonn 15mm).

AEBOPLANE.

Specification of Letters Patent.

Patented Feb. '7, 1922.

Application filed November 6, 1920. Serial No. 422,271.

. To all whom it may concern:

in my application for a United States patent filed October 27, 1919, Serial No. 333,559, allowed August 3, 1920.

The object of my invention is to improve the construction and operation of such an aeroplane whereby the actions of rising and descending vertically and of flying are greatly facilitated.

My invention consists in the peculiar and novel construction and improvements in such I anaeroplane, said new construction and improvements being principally in the planes, top, front and rear rudders and in the means for operating the same, as will be more fully set forth hereinafter and claimed.

Figure 1 is a top plan view of my improved aeroplane showing the movable side planes in the raised position for flying.

Fi re 2- is a vertical longitudinal sectiona view through the aeroplane taken on line 2, 2 of Figure 1, and

Figure 3 is a front view of the aeroplane showm the movable side planes in the lowere position, in broken lines, for rising or descending vertically and in the raised position in full lines for flight.

In the drawings 4 indicates the fuselage, 5 the central plane, 6, 6 the side planes, 7 the top rudder, 8 the front rudder, 9 the twin rear rudder, 10 the engine, 11 the tractor shaft on which is a tractor helix 12, 13 the propeller shaft on which is a propeller helix 14; and 15 the transmission of my improved aeroplane.

The fuselage 4 consists of a suitable frame 16 as' shown, supporting the engine 10, wheels 17, 17, tractor bearinglS, propeller bearing 19, central plane 5, side planes 6, 6, transmission 15 and operators seat 20 and the frame terminates in a front overhanging end 21 and a rear overhangin end 22.

The central plane 5 is tent s. aped in cross section. It extends the length of the fuselogo 4 and the slopes 23, 23 of the plane form on the underside of the plane an inverted flattened V shape trough '24 which extends the length of the plane. This central plane 5 is rigidly secured to the frame 16.

The side planes 6, 6 are each in the form of a flat rectan lar shaped plane. They extend the length of the central plane 5 on each side and are hinged at their inner edges at 25,25, to the frame 16, as shown in Figure 3 and form a continuation of the central plane 5. The width of these side planes is such that when in the lowered position for rising or descending the outer edges of the planes come at approximately the center of the wheels 17, 17. The side planes are operated by a hand lever 26 to raise or lower the side planes. This hand lever 26 1s p lvotly secured to the frame 16 in a convenient position to the operators seat 20, as shown in Figure 2. From this hand lever 26 rods 27, 27 extend to pivot connections 28, 28, on the side planes 6, 6, as shown in Fi re 3. i

he top vertical rudder 7 is flat and elon- .gated in form, it is pivotally secured adjacent its forward end to the frame 16, at 29 on top of the central plane 5 and extends centrally lengthwise of the central plane. It is operated to steer the aeroplane sidewise by wires 30, 30 which are secured at one end to each side of the top rudder 7. Each wire 30, 30 extends down over pulleys 31, 31 and then to a foot treadle 32 on the frame 16 in a convenient position for the foot of the operator, as shown in F i res 2 and 3.

The front rudder 8 is at and semi-circular in form. It'is pivotally secured at 33in a horizontal position, to the end of the front overhan 'ng end 21 of the frame 16. It is operate to steer the aeroplane up or down by wires 34, 34, which are secured at one end to the rudder and at their other ends to a hand lever 35 pivotally secured to the frame 16 in a-convenient position to the operators seat 20, as shown in Figure 2.

The twin rear rudder 9 consists of a horizontal rudder 36 and a'vertical rudder 37. The horizontal rudder 36 is the same as the front rudder 8, it is pivotally secured at 38 to the end of the overhanging end 22 of the frame 16. It is o erated to steer the aeroplane up or down y wires 39, 39 which are secured at one end to the horizontal rudder 36 and at their other ends to a hand lever 40, pivotally secured tothe frame 16 in a convenient position to the operators seat 20. The vertical rudder 37 is pivotally secured at 41 to the horizontal rudder 36 and it has a slot 42 through which the horizontal rudder 36 extends, whereby the horizontal and vertical rudders have independent move-- ments. The vertical rudder 37 is operated to steer the aeroplane sidewise by wires 43, 43 which are secured at one end to the vertical rudder 37. These wires 43, 43 extend over pulleys 44, 44 and then downwards to a foot treadle 45 to which they are secured, the foot treadle 45 being in a convenient position to the operators seat 20, as shown in Figure 2.

The engine 10 is secured to the frame 16, it may be of any well known form of a gas engine supplied with fuel by a ipe 46 from an overhead fuel tank 47. Tile engine is operated in the usual way not shown from the operators seat 20.

The transmission 15 is operatively connected to a power shaft 48 which is operatively connected to the engine 10. On the forward end of the power shaft 48 is secured a bevel gear 49 meshing with a bevel gear 50 on an inclined shaft 51 rotatably supported in bearings 52, 52 on the frame 16. On the forward end of the shaft 51 is a bevel gear 53 meshing with a bevel gear 54 on the tractor shaft 11, thereby transmitting power from the engine 10' to the tractor shaft 11. 1

The tractor shaft 11 is rotatably supported in the tractor shaft bearing 18 and has fixed on its forward end' the tractor helix 12 and thehtractor shaft revolves preferably to the rig t.-

On the rear end of the ower shaft 48 is secured a bevel gear 55 mes ing with a bevel gear 56 on a vertical shaft 57 rotatably supp)orted in bearings 58, 58 on the frame 16.

n the upper end of the vertical shaft 57 is a bevel gear 59 meshing with a bevel gear 60 on the propeller shaft 13, rotatably supported in the propeller shaft bearing 19, thereby transmitting power from the engine 10 to the propeller shaft 13.

The transmission 15, on the power shaft 48, is operated to control the same by a hand lever 61 adjacent the operators seat 20 as shown in Figure 2. The construction of the transmission, not shown, is such that through the operation of the hand lever 61 the tractor helix 12 and the propeller helix 14 may be made to revolve simultaneously to the right to propel the aeroplane in a forward direction, or the tractor helix 12 may be made to revolve simultaneously to the right and the propeller helix 14 simultaneously to the left to raise the aeroplane vertically upwards. The operations of the tractor and propeller helixesare the same as in my previous patent application and any form of a I transmission may be used,.that will accomplish the same result. A

As hown in Figure 3 the central plane 5 is concaved in cross section and forms a flat tened V shaped trough 24 on its under side and which extends the le h of the central plane. The aeroplane w en moving forward in the air moves in the direction of the arrow62, as shown in Figure 2 and when moving vertically upwards in the direction of (phe arrows'63 63 as shown in Figures 2 an 3.

When in use and it is desired to arise vertically upwards, the operator seats himself in the operators. seat 20 and then operates the transmission 15 by the hand lever 61, so that the tractor helix 12 will revolve to the right to move the aeroplane forward, and the propeller helix 14 to the left, to move the aero lane backwards. He then operates the hall lever 26 to close the side planes 6, 6 into position, as shown in broken lines in Figure 3. The to rudder 7, front rudder 8 an rear twin ru der 9, being in a central or neutral position, as shown in full lines in the figures, the operator now starts the engine 10 in the usual way. The helixes revolving in the directions stated, cause blasts of air to meet in the center. portion of the trough'24 on the underside of the'central plane 5 and forces the central plane 5 and tral plane 5 and coming together, at the central portion of the plane are forced downatmosphere, also. 1n conjunction with the first blasts of air against the plane, forces the aeroplane upwards. With the' side planes 6, 6 closed as shown in broken lines 1n Figure 3, the blasts of air are more confined to a downward direction and a better ,wards and forming an air pack against the operated b the hand lever 61 so that the tractor an propeller helixes will both revolve to the right, both helixes now revolve in the same direction and at the same speed. As the helixes are now revolving on the same plane, or center line of the aeroplane, in the same direction and at the same speed, the speed of the engine ma now be increased to its maximum s eed. en it is desired to alight vertical poon the ground or other structures, the a ve operations are reversed.

My present invention lies more particularlpk in new construction and operation such as t e central tent shaped plane 5, the movable side planes 6, 6 the top rudder 7 the twin rear rudder 9 and the frame 16.

Having thus described my invention I claim as new 1. An aeroplane having a frame, a central plane extending lengthwise of the frame and formed to have a flattened V shaped trough on its underside and extending the length of the plane, said plane bein secured to the frame, rectangular shaped side planes hinged to the'frame and extending the length of the central plane, means for 0 erating the side planes, a top rudder pivota ly secured to the frame over the central plane,-means for operating the top rudder, a front horizontal rudder hinged to the frame, means for operating the front rudder, a twinrear rudder comprising a horizontal rudder hinged to the frame and a vertical rudder pivoted to the horizontal rudder, means for operating{ the twin rear rudder, an engine supporte by the frame, a tractor shaft rotatably supported in bearings in the frame and operatively connected with the engine, a tractor helix on the tractor shaft at the forward end of the central plane, a propeller shaft rotatably supported in bearings, a propeller he lix on the propeller shaft at the rear end of the central plane, a transmission operatively connected with the tractor and propeller shafts, and means for operating the trans.- mission, for the purpose as described.

2. An aeroplane having a frame with overhanging front and rear ends, a rectangular shaped central plane extending lengthwise of the frame and having a flattened V shaped trough on its underside and extending the length of the plane, being secured to the frame, rectangular shaped side planes hinged to the frame and extending the length of the central plane and forming a continuation of the central plane, means for operating the side planes, a rectangular shaped vertical top rudder over the central plane and pivotally secured to the frame, means for o crating the top rudder, a semi-circular ront horizontal rudder hinged to the front overhangin end of the frame, means for operating the front rudder, a twin rear rudder comprising a semi-circular horizontal rudder hinged to the rear overhanging end of the frame and a vertical rudder pivoted to the horizontal rudder, said vertical rudder havin a slot through which the horizontal ru der extends, means for operatin "the twin .rear rudder, an engine su porte by the frame, a tractor helix at the orwardend of the central plane and operativel connected with the engine, a propeller helix at the rear end of the frame, and operatively connected with the engine, a transmission operatively connecting the engine with the tractor and propeller helixes and means for operating the transmission, for the pur ose as described.

In testimony whereof, have signed my name to this specification.

IVAR CARLSON.

said plane

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