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Publication numberUS2044819 A
Publication typeGrant
Publication dateJun 23, 1936
Filing dateOct 27, 1933
Priority dateOct 27, 1933
Publication numberUS 2044819 A, US 2044819A, US-A-2044819, US2044819 A, US2044819A
InventorsTaylor James G
Original AssigneeTaylor James G
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
US 2044819 A
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Description  (OCR text may contain errors)

June 23, 1936. J G, TAYLOR 2,044,819

PROJECTILE Filed oct. 27, 1933 f Iventnr damaa E- Taylnr 2 ay MMM Patented Juney 23, 1936v UNITED STATES PATENT OFFICE rnoJEc'rnn James G. Taylor, Dayton, Ohio Application October 27, 1933, Serial No. 695,495

3 Claims. (Cl. 10g-2) (Granted under the act of March 3, 1883, as

' amended April 30, 1928; 370 0. G. '157) The invention described herein may be manufactured and used by or for the Government for governmental purposes, without the payment to me of any royalty thereon.

This invention relates generally to projectiles and more particularly it has reference to a, projectile such as a bomb or other missile adapted to be launched from aircraft. y The purpose of the invention is to provide a i vane wheel on a bomb for checking or retarding its descent. The vane wheel is intended to replace. the conventional parachute which is composed oi a material such as silk that is diiiicult to procure in wartime. While this substitution i has previously been proposed in Patent No. 1,003,- 082 of September l2, i911, and Patent No. 1,077,- 999 of November ll, l9l3, the present invention deals with a diierent problem, namely, that of vlaunching the bomb from a low-dying aircraft m and retarding its night and delaying its impact for such an interval of time as will permit the aircraft to travel outoithe danger zone.

If the ordinary small vane wheel is employed it will not aiiord suicient retardation and delay or impact and if a large vane wheel is associated with the bomb it is not only bulky and diicult to house but produces asoaring or glider action which is a variable factor and cannot be calculated and compensated for in aiming at a definite target. In addition such soaring action may result in the bomb following the general course of the aircraft in a trajectory that is closer to the horizontal than the vertical and in this event the aircraft will not clear the danger zone.

In order then to meet the requirements of size and compactnesslow rate of descent, accuracy, and a nearly vertical trajectory, the improved .vane wheel comprises curved blades conforming to the curvature of the bomb body and having `a vnovel manner of providing a large a le of ineing and an ear I8 of the hub is effected by means of dence.

With the foregoing and otherobjects in view, the invention resides in the novel arrangement l5 and combination of parts and in .the details of construction hereinafter described and claimed,-

it being Aunderstood that changes in the precise embodiment of the invention herein Vdisclosed may be made within the scope of what is claimed 50 without departing from the spirit of the invention. i A

A practical embodiment of the invention is illustrated in the accompanying drawing, wherein: 55 Fig. 1 isa view in side elevation of the improved bomb showing the vanes in open or extended position.

Fig. 2 is a view in side elevation, and partly in sectionshowing the vanes in the folded position.

Fig. 3 is a. plan view of Fig. 2.

Fig. ,4 is a view in end elevation of one of the blades. v f

Referring to the drawing by characters of reference there is shown a bomb body 5 having an annular ange' on its nose end and threadedly 1a carrying a spindle 'l in its tail.

The spindle is provided with a collar 8 'for engaging the body 5 and limiting its threaded engagement. The outer extremity of the spindle is reduced to form an annular seat 9 for the 15 inner race i6 of an anti-friction bearing unit il. The inner race is retained by a collar i2 on a bolt I3 that is threadedly connected to the spindle and terminates in an eye I4 which provides a means for suspension of the bomb.

A hub i 5 having an annular seat i6 on its lower end to seat the outer race il of the bearing unit and to be retained thereby is provided with a plurality of radially projecting supports or ears I8, three being shown.

A Wing or blade I9 isassociated with each ear i8 and has ya curvature in cross-section preferably conforming to the curvature of the body so that when in folded position as seen in Figs. 2 and 3 it will lend itself to the formation of a 30 compact unit requiring a of storage space. In the preferred embodiment of the invention a pair oi spaced ears 2li-20 is secured as by welding 2i to onevend ofthe blade. The center line of the spaced ears is oiset relative to the center line or longitudinal axis of the blade (Fig. 4) in order to provide the blade with an angle of incidence when open and increase its eiiciency. o

The connection between the ears 20 of the blade a. pin 22 passing through the ears. The-bomb is stored and also carried in the launching tube of an aircraft with its wings or blades folded alongside the body as seen in Fig. 2. The flange 6 on the nose' end of the bomb extends outside the trace of the blades and provides a clearance between the blades and the launching tube. 50 When the bomb is launched the air pressure causes the blades to be rotated about their pivots until they assume a generally horizontal position,

' with the inner 'end of' each blade brought up againstthe hub to limit the opening movement.

Because of the pitch or angle oi' incidence oi' the blades th described in connection with a bomb its adapt! 1. A projectile including a cylindrical body, spindle in one end of the body. an anti-friction being onset relative to the plane passing through of the bomb and the longitudinal axis tially perpendicular to the of the blade, and a. pivot pin passing through the ears of the blade and hub. f

3. A projectile including a cylindrical body, a

normal to its axis at its midpoint onset relative to the plane passing through the axis of the bomb and the longit dinal axis of the blade.

3.'A projectile inc uding a, body, a support rotatably mounted on the tail end of the body, a 15 plurality of blades curved in cross-section land pivotally mounted on the support i'or movement from a folded to an extended position, substanbody said pivotal mounting having the plane normal to its axis 20 at its mid-point onset relative to the plane passing through the axis of the bomb and the longitudinal axis oi the blade.


Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2432421 *Jan 8, 1942Dec 9, 1947Homrighous John HDirectional control for bombs
US2440291 *May 5, 1944Apr 27, 1948Autogiro Co Of AmericaRotor equipped aerial device
US2440292 *May 5, 1944Apr 27, 1948Autogiro Co Of AmericaRotor equipped aerial device
US2440295 *May 5, 1944Apr 27, 1948Autogiro Co Of AmericaRotor equipped aerial device
US2450992 *Nov 16, 1945Oct 12, 1948 Free-fall aerial contained
US2495486 *Apr 18, 1945Jan 24, 1950Stevenson Philip HAerial delivery container
US2509481 *May 18, 1945May 30, 1950Crise George WRotating vane parachute
US2606495 *Sep 30, 1947Aug 12, 1952Kilgore IncPyrotechnic device
US2667352 *Jul 1, 1949Jan 26, 1954Sepersky Joseph MAirflight whirling device
US2678785 *Apr 17, 1952May 18, 1954Northrop Aircraft IncRotating blade speed brake
US3115831 *Sep 26, 1961Dec 31, 1963Henry SuterFlexible rotochute
US3158336 *Sep 5, 1962Nov 24, 1964Lawson Billy DAssembly for recovering a capsule
US3175489 *Nov 27, 1962Mar 30, 1965Reed Jr Edwin GAir-delivered anti-personnel mine
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US7681504 *Aug 26, 2003Mar 23, 2010Bae Systems Information And Electronic Systems Integration Inc.Method and apparatus for displacing material and projectile thereof
EP0176046A1 *Sep 20, 1985Apr 2, 1986Rheinmetall GmbHWarhead
U.S. Classification102/388, 244/138.00A, 446/36
International ClassificationF42B10/58, F42B10/00
Cooperative ClassificationF42B10/58
European ClassificationF42B10/58