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Publication numberUS1264152 A
Publication typeGrant
Publication dateApr 30, 1918
Filing dateAug 1, 1916
Priority dateAug 1, 1916
Publication numberUS 1264152 A, US 1264152A, US-A-1264152, US1264152 A, US1264152A
InventorsErnest G Briggs
Original AssigneeErnest G Briggs
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
US 1264152 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)



, 1 Q6Q 1 5%., Patentad Apr. 30, 1918.



1 Q6$J5 Pafented Apr. 30,1918.



' Specification of Letters Patent.

Patented Apr. 311 191.

Application filed August 1, 1916. Serial No. 112,586.

To all whom it may concern:

Be it known that I, ERNEST G. BRIGGS, a citizen of the United States, residing at Brookville, in the county of Jefi'erson and State of Pennsylvania, have invented certain new and useful Improvements in Aeroplanes, of which the following is a specification.

This invention relates to aeroplanes, and more particularly to means for stabilizing aeroplanes and for preventing too rapid descent of the same in case of accident.

()ne of the main objects of the invention is to provide an aeroplane of simple con struction and operation which will remain steady in swirls or high winds. A further object is to provide an aeroplane with means for exerting a parachute efi'eot in case of accidentto the motor, so as to prevent a too rapid descent of the plane.

1n the drawings: A Figure 1 is a plan view of the invention. Fig. 2 is a side view partly broken away with the main plane omltted, and

Fig. 3 is a front view partly in section. 1 designates the boat or body of the plane in the forward part of which is mounted the engine 2 of suitable construction. The

propeller 3 projects forward of the body and is operatively connected to the engine so as to be rotated thereby.

The main plane A is mounted near the front of boat 1 and extends a considerable distance from each side of the same. This plane is of usual construction and carries at each side of boat 1, a base 5. A vertical shaft 6 is rotatably mounted in each of-the bases and is braced by suitable collars 7 mounted about the same and supported by stay rods 8 secured to the plane A and the sides of body 1. A circular lane 9 1s firmly secured on the up er end 0 each shaft 6 so as to be rotated t ereby.

A horizontal steering plane 10 is mounted.

at the back of boat 1 and is adapted to be tilted so as to vary the angle of the machine so as to ascend or descend as desired,- in the usual manner. In back of plane 10 the vertical rudder 11 is mounted for movement laterally so as to steer the machine to either side in the manner now well known in this art.

The body 1 is mounted on light pneumatic wheels 12 and 13 so as to support it for raisin the machine fromthe ground by ring rward until ulliit speed has been attained to lift the machine 0d the ground in the usual manner.

A beveled gear 1 1 is keyed to each shaft 6, near the lower end thereof. This gear meshes with a similar gear 15 keyed on the outer end of a shaft 16 rotatable in standards 17. A beveled gear 18 is keyed on the mner end of shaft 16 and meshes with a beveled driving gear 19 keyed on the engine shaft 20. a

When the shaft is rotated the planes 9.

, are revolved at a comparatively high speed in opposite directions. As these planes are rotating they have a constant tendency to remain in a horizontal plane and resist any force tending to move them out of this plane. As they rotate in opposite directions, any force which tends to move one of them out of the horizontal would not only be resisted by the plane upon which this force is directly exerted, but would also be equally resisted by the other plane. These two planes really constitute, so far as their stabilizing efiect is concerned, two oppositely revolving gyroscopes, and act in the same manner in resisting forces which tend to move them out of a horizontal plane, and to overcome such forces and return to a horizontal plane if they be moved out of it.

Tn addition to acting as stabilizing elements, the planes 9 are of material assistance in steadying the plane in high winds or swirls. Due to the fact that they rotate outwardly and forwardly from the body 1 they act to turn unusually large bodies of air to each side of the machine, thus opening a path for the machine which in this manner escapes the direct effect of the air body encountered. As the amount of air which is thus turned aside by one plane will be equal to the amount which is turned aside by the other plane, the machine will be mainperipheral edges formed very thin so as to readily cut through the air and thus reduce the resistance to the forward travel of the machine to a minmum.

. I have shown the planes 9 as revoluble by the same engine as is used for rotating the propeller 3, but I desire it to be understood that I do not limit myself to this particular form of drive. These planes may be operated in numerous other ways, as by an independent motor, or may even be adapted to be driveneither by an independent motor or by the propeller motor, optionally. My invention resides more particularly in the provision of supplemental planes in spaced relation to the main plane and adapted to be optionally revolved, and not in the particular means for revolving. these planes.

Although I have shown the planes 9. as located above the main plane 4, very good results may be obtained by placing them below the main plane. Also, the two planes 9 may be replaced by a single revoluble plane positioned at the center of the main plane without departing from the principle of my invention.

While I have shown the planes 9 as being perfectly flat, it will be evident that they can be made in numerous shapes, either concave or convex, or other shape, as may be deemed expedient. There may .also be numerous changes made in the other parts of my invention without departing from the field and scope of the same, and I intend to include all such variations in this application, in which the preferred form only of my invention is disclosed.

What I claim is:

In an aeroplane, a body, a main plane projecting from each side of and beneath the body, supporting bases secured on the upper surface of said plane at each side of, and equi-distant from, the body, vertical shafts rotatably supported by said bases, flat circular planes secured on the upper ends of said shafts, a motor carried by the body, and driving connections between said motor and shafts for causing simultaneous rotation of the shafts in opposite direction whereby the planes mounted at the upper ends of said shafts will be rotated oppositely simultaneously and in a plane above the said main plane so as to resist forces tending to cause rocking of the aeroplaine about the longitudinal axis of said b0 III; testimony whereof I aifix my signature in presence of a witness.


Witness J. A. MCGRATH.

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3288396 *Dec 2, 1964Nov 29, 1966Gouin Robert Leon AugusteAircraft having disc-shaped rotating wings
US4120468 *Feb 10, 1978Oct 17, 1978Rhein-Flugzeugbau GmbhRemotely piloted vehicle
US5918832 *Mar 14, 1997Jul 6, 1999General Atomics Aeronautical Systems, Inc.Wing design using a high-lift center section, augmented by all-moving wing tips and tails
US6932296Oct 21, 2003Aug 23, 2005Information Systems Laboratories, Inc.Cycloidal VTOL UAV
US7219854Mar 4, 2005May 22, 2007Information Systems Laboratories, Inc.Cycloidal hybrid advanced surface effects vehicle
US7264202Nov 1, 2005Sep 4, 2007Information Systems Laboratories, Inc.Tri-cycloidal airship
US20050082422 *Oct 21, 2003Apr 21, 2005Tierney Glenn M.Cycloidal VTOL UAV
US20060196992 *Mar 4, 2005Sep 7, 2006Boschma James H JrCycloidal hybrid advanced surface effects vehicle
US20070034737 *Aug 9, 2005Feb 15, 2007Tierney Glenn MDual axis control for cycloidal propeller
US20070095983 *Nov 1, 2005May 3, 2007Sullivan Callum RTri-cycloidal airship
US20070200029 *Feb 27, 2006Aug 30, 2007Sullivan Callum RHydraulic cycloidal control system
WO2007021361A2 *Jun 16, 2006Feb 22, 2007Information Systems Laboratories, Inc.Dual axis control for cycloidal propeller
WO2007021361A3 *Jun 16, 2006Apr 16, 2009Information Systems Lab IncDual axis control for cycloidal propeller
U.S. Classification244/39
Cooperative ClassificationB64C39/005