US1420509A - Ixsosog - Google Patents

Description

r 1. B. ANDERSON.-

- Patented June 20,1922. I 2 SHEETS-SHEET I.

rum

ATTORNEYS 1. B. ANDERSON. AEROPLANE BRAKING DEVICE.

APPLICATION FILED AUG.4, I920.

Patented June 20, 1922.

2 SHEETS-SHEET 2- W aw m N0 M 4 b S w 5 S. M d

A TTORNEVS .1 View through ing drawings forming pellers. I 40 om ts s TA'r JA-ians 'nnusn Annmson, on PORTLAND, onneon.

AERGPLAITE-B 11m G'r nEV'IGE.

Application-filed A ugust 4, 1920. Serial No. 401,132.

To all whom it may concern:

Be it known that 1, JAMES BRUSH Avenuson, a citizen "of the United States, and a resident of lortland, pounty of Multnomah, and State of Oregon, have invented a new and Improved Aeroplane-Braking Device, of which the following is a full, clear, and exact description.

invention relates to means for slowing the speed of an aeroplane, and has reference more particularly to an aeroplane having auxiliary propellers which are adapted to be rotated in a direction reverse to the direction of the main propeller so that the speed of the aeroplane will be decreased. An object of this invention'is to provide auxiliary propellers on an aeroplane which may be 'used to decrease the speed of the aeroplane when landing, and may also be used to obtain a quick get-a-wayf when rising fromthe ground.

Reference is to be had to the accompanya part of this specification, in which it is understood that the drawings illustrate one form of the invention with certain modifications, and in which- Figure 1 is a front view of an aeroplane with my improved device in position.

Figure 2 is a front. view of an aeroplane having a modified form of my devloe 1n position.

Figure 3 is a central sectional View through a second modified form of pinyinvention. 7

Figure 4 is a horizontal central sectional the aeroplane showing the operating mechanism for-my auxiliary pro- 5 a sectional view through the Figure being taken on the line 5-5 of mechanism Figure 4.

Figure 6 is a sectional view througlr the 'mechanism being-taken on the line of Figure 4. 7

Referrin to the accompanying drawing by numera 10 indicates the engine of an aeroplane having a main propeller 11, wings -12, wheels 13, and fuselage 14:. i'he main propeller 11 is usually located midway between the ends of the wings l2, and when landing, the engine 10 isrun at low speed but is not actually turned ofi -sincethemachine would then be out of the control of the operator. It is desirable to slow down the speed of the aeroplane immediately before landing sothat the landing be accomplished with less risk to the aeroplane and to the pilot. I For-this purpose 1 provlde a pair of aum'liarypropellers 15, one

positioned on each side of the main pro peller 11 and between the upper and lower wings 12. A tube 16 loosely fits around each of the aum'liary propellers-15, the forward and lower end of said tube being cut so as to slope downwardly and rearwardly as shown in Figure 3, and said tubes are curved to conform to the shape of the wings thus nicreasing the lifting power of the aeroane.

Each of the propellers 15 may be driven froman independent engine located in the Specificati n of Lette Paten Patented line 20, 1922.

fuselage or from the engine operating the main propeller 11 as shown in Figures 4: to 6' inclusive. If the auxiliary propellers 15 are operated fi'om the main engine 10, the

shaft 17 of said main engine will extend rearwardly and will be provided with a clutch 18 which may be operated by any suitable means so that the auxiliary propellers can .be disconnected. A clutch (not shown) may be also provided on the shaft 17 adjacent the main propeller 11 so that said propeller may be disconnected whenthe .UXllial'Y propellers 15 are in operation.

The shaft 17 extends rearwardly into a housing 19 and is provided on its end inside said housing with a bevel gear 20 meshing with ahevel gear 21 secured to a vertical shaft 22. The upper end of the shaft 22 extends into a housing23 and is provided with a bevel gear 24 meshing with a bevel gear 25 secured toa 'shaft 26.

The'shaft '26 extends laterally through the fuselage 14 and each end extends into one of the tubes 16. Each end of the shaft 26 is provided with a disc 2'2 which is mounted on said shaft so as to'be capable of axial movement along said shaft but being constrained to rotate continuously with said shaft 26. A shaft 28 is rotatably and concentrically mounted in each of the tubes 16 so that the axes of the shafts 28 areat right angles to the axes of the shaft26. I

A friction wheel 29 preferably of fibrous material, is mounted on each of theshafts 28adjacent the discs 27, saidjwheels being .capable of axial movement along the shafts

Images