US1407505A - Aeroplane - Google Patents

Description

' S,. A. WILLIAMSON.

AEROPLANE. APPLICATION FILED FEB. I2. I92].

Patented Feb. 21, 1922.

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AEROPLANE.

APPLICATION FILED FEB. 12, I92].

1 07,505 Patented Feb. 21, 1922.

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Be it known'that I, SEAMAN A. WILLIAM- soN, a citizen of the United States, residing at Point Richmond, in the county of Contra .Costa and State of California, have invented new and useful Improvements 1n Aeroplanes, of. which the following is a specification. s

This invention'relates to aeroplanes and similar aerial vessels and hasprimarily for its object to devise .aneflicient means whereby the ascent, or the too rapid descent of the vessel is controlled according to the adjustment of the regulating means provided therefor.

, Another object of this invention is to pro-- vide means disposed adjacent the center of gravity for balancingv the aeroplane, which means is adapted to be used for ascending and likewise descending, and which reeludes possibility of the usual dipping w en passing through varying atmospheric zones, and also in no way interfering with the operation of theaeroplane or retarding its movement.

.A further object bf this invention is a r provide an improved mechanism positioned in close proximity to the body of the aeroplane,.which is manually controlled'by the operator and easily adjusted to various pos1- tions. 1 3

A still further object of this invention is to provide asupport for the stabilizing meansfor the aeroplane which can be readily applied thereto without materiallyaltering the construction of the same; '1

Other objects and advantages of the invention will be apparent'du'ring the course of the following description In the accompanying drawings-forming numerals are employed to designate 'like section of the parts throughout thesame,

Figure l-is a view of the machine in side elevation,

trolling the Specification of Letters Patent. Patented )Fgb, 21, 1922, Application filed February 12, 1921 1 Serial No. 444,408. I v

plane which is provided with upper and lower sustaining planes 7 and 8, the upper plane being slotted as shown at 8.

" numeral 6. designates the body of the aero- In the body of the aeroplane there is mounted the usual motor 9 which controls the propeller shaft 10 carrying the usual 1 propeller 11 disposed at the front end of the body 6. This construction is of the con-c ventional type and forms nopart of my invention.

The numeral 12 designates a pair of su porting guides detachably fastened at their free extremities to the body of the aeroplane 6.

Disposed between and connecting the guides is a cross piece 13 provided with a centrally located upper bearing '14.- As

'shown to advantage in Figure 3, the cross piece is likewise provided with apertured extremities 14 adapted to. encircle the guides 12 Suitably mounted within the body 6 is a base support 15 provided with vertical standards 15 adjusted to receive therein a shaft 16.. They numeral 17 designates a frame as a whole, which includes a yoke member 18 and anupper portion 19 formed integral with the cross piece. 13. Formed 1n the lower extremity of the yoke member 18 is a gear segment 20 adapt'edto inesh with a'worm 21 provided on a control shaft 22 'journaled in extensions '23 formed intefgral with the base support 15. Then'umeral 23' designates a control column and .23" indicates a universal] coupling adapted to actuate the shaft 22 upon movement of the control column 23".

- This construction is set forth in Figures 3 and 4, while in dotted line position in Figure 1 there is shown the means for conaction of the worm on the gearsegment.

From this construction it will be apparentlthat movement of the worm will cause the frame to assume'various-angular posi I tions; v V

Formed integral with the upper portion of-the yoke 18 is a lower bearing 24, which together with the upper bearing 14 .en- "-circle a normally vertical propeller shaft 25, I

which has on its lower extremity a beveled gear 26' and likewise-carries onits. upper extremity an auxiliary or'horizontally .posed propeller 27 adapted to rotate on a vertical axis and designed for use in. ascend ing or descending, which use will be hereinafter more fully described.

In order that the weight of the propeller shaft may be supported on the bearing 24, I have provided a collar 28 which rests on the bearing and rotates with the shaft. The collar 28 is provided with a flat face 29, whereby the rotating action of the shaft may be gradually checked when apivoted" arm 30 1s swung from its normal vertical position to its retarding position, as shown in dotted lines in Figure 3, and in detail in Figure 5.

It will thus be evident that means are provided for checking. the rotation of the vertical propeller shaft and thus overcoming the air resistance offered by the horizontal or auxiliary propeller when its pose has been accomplished.

Meshing with the gear wheel 26 is a master gear 31, which in turn has meshing therewith for the purpose of driving the same, a second bevel gear 32 mounted on a sectional engine shaft 33 which has associated therewith a friction clutch 34 of the conventional type. For the purpose of supporting the en 'ne shaft and its associated clutch, a stan ard 34' has been provided which is integrally formed with the base member 15.

It will thus be evident that means are provided for throwing the vertical propeller shaft out or for drivin the same when so desired, according to t exmanipulation of readily have the stabilizing means assume either of the dotted line positions shown to advantage in Fi ure 1.

In operation t erefore, assuming that the operator wishes to employ the auxiliary propeller to assist in the ascent, the driving propeller is started, then the vclutch 1s throwrr, in and through the action of the bevel gear 32 on the master gear 31, the auxiliary propeller is rotated. .When this action occurs, the operator by a manipulation of the control column causes the worm be made, the same 0 eration as above described for causing t e auxiliary propeller to operate, is repeated, but only w1th a .reverse movement of the control wheel. The

auxiliary propeller will then assume an aft position and the speed of the aeroplane canto a great degree be checked so that a landing can be made on a comparatively small area.

' It is to be understood that the form of my invention, herein shown and described, is.

to be taken as a preferred example of the same, and that various changes in the shape, size and arrangement of parts may be resorted to without departing from the spirit of the invention, or the scope of the subjoined claims.

Having thus claim 1. In an aeroplane, a body portion, a pair of sustaining planes mounted thereon, one of said planes being slotted, a main drivin propeller, an auxiliary propeller, a sectiona described my invention, I

engine shaft for driving said main propeller and said auxiliary propeller, a clutch mounted on said sectional shaft for alternately throwing said auxiliary propeller into and out of engagement with said engine shaft, a frame positioned within the body portion of said aeroplane for supporting said auxiliary propeller, and means under the control of an occupant for rocking said frame to cause said auxiliary propeller to assume different an 1131' positions.

2. In an aeroplane, t e combination with a body portion,of sustaining planes mounted on said bod a driving propeller, an auxiliarv propelfer, a frame positioned in the body of said aeroplane and adapted to hold said auxiliary propeller, mechanism, for

rocking said frame, and a universal coupling connected to said mechanism and adapted to SEAMAN A. WILLIAMSON.

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