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Publication numberUS1886289 A
Publication typeGrant
Publication dateNov 1, 1932
Filing dateFeb 16, 1931
Priority dateFeb 16, 1931
Publication numberUS 1886289 A, US 1886289A, US-A-1886289, US1886289 A, US1886289A
InventorsMiller Arthur E, Salisbury Hervey M
Original AssigneeMiller Arthur E, Salisbury Hervey M
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Variable camber propeller
US 1886289 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)

Nov. 1, 1932. A. E. MILLER ET AL VARIABLE CAMBER PROPELL ER Filed Feb. l6, 1931 '2 Sheets-Sheet 1 INVENTORS Ar tlzu/r EZMLLl/er and Harvey MSalisbury By E ATTORNEY Nov. 1, ,1932. A. E. MILLER ET AL 1,336,289

vAfiIABLE CAMBER PROPELLER Filed Feb. 16, 1931 2 Sheets-Sheet 2 INVENTORS Apzhuk EiMiLler mad Hruey By G g g ATTORNEQY Patented Nov. 1, 1932 ARTHUR E. MILLER, OF SACRAMENTO, AND


VARIABLE CAMBER PROPELLER Application filed February '16, 1931.

This invention relates to airplanes, and particularly to the construction of the propellers of the same. In effect a propeller is nothing more than a wing. or in other words the propellers action or lift is caused by driv-- mg an airfoil through the air. Since by changing the camber of a wing it is possible to change its lifting effect, the same holds true of a propeller. \Vc make use of this fact in the present invention, the principal object of which is to construct the blades of a propeller so that they have adjustable trailing edge portions in order that the camber or transverse form of the blades may be altered; and'to provide a means whereby these edge portions may be adjusted by the pilot and mechanically held in any position while the airplane is in flight.

The same principle may also be applied to lifting propellers or helicopters, or to supporting wing units.

A further object of the invention is to produce a simple and inexpensive device and yet one which will be exceedingly effective for the purpose for which it is designed.

These objects we accomplish by means of such structure and relative arrangement of parts as will fully appear by a perusal of the following specification and claim.

In the drawings similar characters of reference indicate corresponding parts in the several views:

Fig. l is a fragmentary side outline of an airplane, showing our adjustable camber propeller and the means for adjusting the same.

Fig. 2 is an enlarged fragmentary side view of the propeller and its control means.

ig. 3 is a top plan view of the structure, partly in section, showing the propeller blade elements in their normal position.

Fig. 4 is a similar view, showing the camber of the blades increased.

Referring now more particularly to the characters of reference on the drawings, 1 5 denotes the fuselage of an airplane, from the front end of which the drive shaft 2 projects from the motor as usual. This shaft projects forwardly a slightly greater distance than in ordinary practice, and on its forward end is fixed a standard hub 3, in the opposed Serial No. 5:5,ai5.

bosses 30: of which are fixed ends of the opposed blades 4. The blades may be of conventional form, except that their rearor trailing edge portions 5 are formed separate from the main blade portions, and are hinged thereto along their adjacent edges by shafts 6, which extend lengthwise of the blades as clearly shown.

These shafts extend beyond the portions-5 inwardly of the outer ends of the hub bosses 6o 1n overhanging clearance relation thereto. At these ends the shafts are rigidly connected to the adjacent ends of pylons 7, which extend thence rearwardly in overhanging relation to the hub on the opposite sides of the same. At their rear ends the pylons are pivoted on the forward ends of the longitudinally adjustable links 8, which at their rear ends are swivellyconnected to the outer ends of arms 9, which project oppositely and radially from a collar 10. This collar is slidably splined on the shaft 2 so as to be I always maintained in the same relation to the propeller. This collar is engaged by a yoke 11, there being anti-friction bearings 12 of 7 the annular and thrust type between the collar and yoke, so that the resistance to relative rotation is reduced to a minimum.

The shift fork 13, which is pivoted intermediate itsends on to the fuselage or motor, is connected to the yoke and has a control rod 14 leading thence to the pilots compartment of the airplane. At this end the rod is connected to a control lever 15, which is provided with a pawl and ratchet mechanism indicated at 16 so that it may be held immovable in any position.

It will, therefore, be seen that by shifting the lever in one direction or the other, the air entering surfaces of the propeller blades will be simultaneously changed from a normal camber as shown in Fig. 3, to a greater cambe! or one of convex form, as shown in Fig. 4; or the camber may be made relatively concave as indicated in Fig. 3, thereby tending to '0 negative the forward propelling action of the propeller and exert .a braking effect.

For taking off or for climbing, where the maximum en inc and propeller speed is desired, the cam er or section of the airfoil (the 1 is flattened out, while for speed and cruising the camber, is increased and the engine speed may be lessened. The camber adjusting action we feel will give better or more practical results than can be obtained by adjusting the pitch of the propeller blades as a whole, since such form of adjustment tends at times to stall the engine, if not handled very carefully. With the adjustment of the camber on the other hand, the propeller blades retain their normal, easy lead into the air at all times, any difference of the thrust being had only in the trailing edges of the blades. Also this arrangement enables the blades themselves to be rigidly mounted so that there is no tendency for any excessive vibration or misalignment to be had as is the propeller) case when the propellers are turnable in the hub.

From the foregoing description it will be readily seen-that we have produced such a device as substantially fulfills the objects of the invention as set forth herein.

While the specification sets forth in detail v the present and preferred construction of the device, still in practice such deviations from such detail may be resorted to as do not form a departure from the spirit of the invention, as defined by the appended claim.

Having thus described our invention what we claim as new and useful and desire to secure by Letters Patent is:

A propeller comprising main blade portions and trailing edge portions initially separate therefrom, hinge means between the blade portions including shafts secured to the trailing edge portions and projecting beyond the inner ends of the same, a hub having laterally extending portions from which the main blade portions project, the shafts over hanging said rigidly connected to the projecting ends of the shafts and extending rearwardly and laterally of the blades on opposite sides of the hub, a shaft projecting rearwardly from the hub, a collar splined on said shaft, opposed arms projecting outwardly from the collar, links parallel to the shaft flexibly connecting said arms and pylons, the latter being positioned so as to be concealed from in front by the lateral hub portions, and means to slide the collar along the shaft.

In testimony whereof we affix our signatures.


lateral hub portions, pylons 1

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2429665 *Mar 20, 1944Oct 28, 1947David BiermannVariable pitch propeller
US2648390 *Jul 30, 1947Aug 11, 1953Lagabbe Edmond DeVariable pitch screw propeller
US3181615 *Aug 7, 1963May 4, 1965Gen Motors CorpVariable camber propeller blade
US6327957Jan 8, 1999Dec 11, 2001Wind Eagle Joint VentureWind-driven electric generator apparatus of the downwind type with flexible changeable-pitch blades
U.S. Classification416/23, 416/168.00R, 416/237
International ClassificationB64C11/30, B64C11/00
Cooperative ClassificationB64C11/30
European ClassificationB64C11/30