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Publication numberUS3276377 A
Publication typeGrant
Publication dateOct 4, 1966
Filing dateNov 3, 1964
Priority dateNov 3, 1964
Publication numberUS 3276377 A, US 3276377A, US-A-3276377, US3276377 A, US3276377A
InventorsBell Jack B
Original AssigneeBell Jack B
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Fin locking device
US 3276377 A
Images(1)
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Description  (OCR text may contain errors)

d 1966 J. B. BELL FIN LOCKING DEVICE Filed Nov. 5, 1964 INVENTOR. JACK B. BELL V. C. MU L L ER ATTOR N EY.

United States Patent This invention relates to rocket motors and more particularly to improvements in detachably securing stabilizing fins to same.

An exemplary environment for the present invention is in the ASROC missile disclosed in patent application Serial No. 15,769, filed March 17, 1960, for Rocket Thrown Weapon by Miles H. Hamilton. As disclosed in such patent application the rear end of the missile is provided with four equiangularly spaced fins 27 which stabilize it during flight.

The ASROC missile has also been adapted for launching from the TERRIER launcher which was not originally designed for launching the ASROC missile. In this adaptation each ASROC missile is provided with an adapter rail which receives the ASROC launching lugs, the adapter rail and missile being bodily received, in turn, by the TERRIER launching rail. Prior to attaching or ramming the adapter rail onto the TERRIER launching rail the adapter rail and missile are disposed in a ready room where it is necessary to attach the fins. This operation is performed by two operators, one on each side of the missile. As illustrated in FIG. 5, the spaces available for securing the fins are illustrated as R & L (right and left), the spaces shown by broken lines indicating obs-tructions which prevent the operators from manually operating any fin locking actuator which might be disposed within these spaces.

Again with reference to FIG. 5, it will be apparent that if actuators are provided which are accessible in spaces R and L, fins must be provided with right and left hand actuators. As will be apparent, to provide two different types of fins complicates production and is undesirable from a logistic standpoint. It becomes desirable, accordingly, that all fins be identical, yet be provided with locking actuators which are accessible from available spaces regardless of which of the four positions on the missile to which a fin would be attached.

One of the objects of the invention is to provide a missile fin which may be attached to any of the four orthogonal positions on a missile and locked to it by actuators which are accessible in only two opposite quadrants.

Another object is to provide dual actuators, one on each side of a fin, and either of which may be independently operated for locking a fin to a missile.

Another object is to connect the dual actuators to novel locking mechanism.

Still further objects, advantages and salient features will become more apparent from the description to follow, the appended claim, and the accompanying drawing in which:

FIG. 1 is a fragmentary side elevation of a rocket missile with one of its four orthogonally arranged stabilizing fins;

FIG. 2 is an enlarged section taken on line 22, FIG. 1;

FIG. 3 is a like section taken on line 3-3, FIG. 1;

FIG. 4 is an exploded detail as viewed in the direction of arrow 4, FIG. 2, and;

FIG. 5 is an end elevation as viewed in the direction of arrow 5, FIG. 1 illustrating obstructions, previously referred to.

Referring now to the drawing, fin 10, of which there are four, as shown in FIG. 5, comprises a plate 12, the inner "ice edge of which is riveted between parallel outwardly extending flanges 14 of an extruded H-shaped fin base 16, the inner flanges 18 of which are formed as longitudinally extending male dovetail members 20. A securing base 22, welded to the missile M, is provided with a like female dovetail slot 24 which slideably receives the male dovetail. Portions of the dovetails in each member are milled away at spaced intervals, best shown in FIG. 2, so that the fin may be moved laterally into the base member and thence moved longitudinally to effect engagement of the dovetail members. The connection is thus what might be termed a dovetail bayonet joint or connection in which the longitudinal engaging movement is only the movement of the length of one cut-away in the dovetails. This is necessary since certain obstructions prevent longitudinal movement the full length of the dovetails as is the practice in applying the fins when the missile is being readied for the ASROC launcher. Also, as will be apparent this affords more rapid attachment of a fin to the missile. After a fin is so applied and moved to final position, which may be controlled by any sort of stop pin 26, legs 18 must be expanded laterally so that the male dovetails tightly engage the female dovetail slot.

The expanding apparatus comprises a pair of right and left hand threaded screws 28, 30 which threadedly engage flanges 18. As best shown in FIG. 4, the inner end of screw 28 is provided with a transverse slot 32 and screw 30 is provided with a mating key or tongue 34. Each screw 28, 30 is provided with a lever 36 which is secured to it by a pin 38.

Since the manner of assembly of the right and left hand screws may not be readily apparent, a description of this invention may be in order. Screws 28, 30 are screwed into their respective threads from opposite side of the base member until their inner abutting ends 40 are spaced sub stantially equi-distant from the central plane of flanges 18 and with tongue 34 about to enter slot 32. Further rotation of the screws in the same direction will next engage tongue 34 in slot 32 after which further rotation will effect abutment of ends 40 of the screws. Any further rotation in the same direction will now expand or spread flanges 18 laterally and effect tight engagement of the dovetail members.

It is desirable that all fins be locked to their bases with the same frictional force and with the levers 36 pointed toward the rear of the missile, as shown in FIG. 1. To achieve this end, each base member 18 is disposed, during production, in a suitable master dovetail fixture and the screws 28, 30 are adjusted to attain the desired force. Levers 36 are then secured to the screws by pins 38 in the locked position. As will be apparent, when the levers are swung counterclockwise from that shown in FIG. 1 to the unlocked position the dovetail will be free to permit assembly.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claim the invention may be practiced otherwise than as specifically described.

What is claimed is:

In a missile fin of the type having a base member disposed along a longitudinal edge of the same, said base member having a pair of spaced walls terminating in opposed outwardly directed male dovetails adapted to slideably engage between mating female dovetails disposed on a missile and be locked to the same when said male dovetails are spread apart, the improvements comprising:

(a) a first screw extending through one of said walls and threadedly engaging the same with a right hand thread,

(b) a second screw extending through the other wall and threadedly engaging the same with a left hand thread,

(c) said screws being axially aligned with their inner ends abutting Within the space between the Walls, (d) one of said screws having a transverse slot adjacent its inner end,

(e) the other of said screws having a transverse tongue adjacent its inner end engaging within the slot, Whereby both of said screws may be simultaneously ro- 1 tated by the outer end of either screw, and

(f) a lever secured to the outer end of each screw,

either of which levers may be operated for rotating both screws.

References Cited by the Examiner UNITED STATES PATENTS 3,048,109 8/1962 Feernster 10250 BENJAMIN A. BORCHELT, Primary Examiner. V. R. PENDEGRASS, Assistant Examiner.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US3048109 *Nov 12, 1958Aug 7, 1962Feemster John RWing assembly
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3648953 *Dec 30, 1969Mar 14, 1972Univ Johns HopkinsFin mount latch
US4722496 *Nov 4, 1985Feb 2, 1988Hughes Aircraft CompanyCoupling mechanism for quick attach/disconnect of a missile control
US4845871 *Apr 19, 1988Jul 11, 1989Swan Richard EAttachment device
US5064142 *Aug 27, 1990Nov 12, 1991Raytheon CompanyApparatus for wing attachment
US5106034 *Feb 28, 1991Apr 21, 1992The United States Of America As Represented By The Secretary Of The NavyDevice and process for attachment of parts to rocket motors
US6315240 *Mar 2, 2000Nov 13, 2001Raytheon CompanyTactical missile control surface attachment
US7059076Jun 25, 2004Jun 13, 2006Abrahms Airborne ManufacturingFirearm rail system
US7562485Nov 9, 2005Jul 21, 2009Gg & G, Inc.Apparatus and method for coupling an auxiliary device with a male dovetail rail
US7739824Apr 4, 2008Jun 22, 2010Swan Richard EQuick detach mount with latching assembly
US7793452Jan 22, 2009Sep 14, 2010Samson Manufacturing CorporationModular fore-end rail assembly with locking mechanism
US8429845Nov 16, 2012Apr 30, 2013Richard E. SwanModular integrated rail system including a dampening device
US20110168842 *Apr 20, 2009Jul 14, 2011Jose Antonio Estancano ErcillaJoining system between linings and the structural elements that support them
USRE40216Mar 29, 2004Apr 8, 2008Swan Richard EModular sleeve
EP0540789A1 *Nov 5, 1991May 12, 1993Raytheon CompanyApparatus for wing attachment
Classifications
U.S. Classification244/3.24
International ClassificationF42B10/06, F42B10/00
Cooperative ClassificationF42B10/06
European ClassificationF42B10/06