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Publication numberUS2848945 A
Publication typeGrant
Publication dateAug 26, 1958
Filing dateOct 15, 1954
Priority dateOct 15, 1954
Publication numberUS 2848945 A, US 2848945A, US-A-2848945, US2848945 A, US2848945A
InventorsBrumbaugh Donald Q
Original AssigneeBrumbaugh Donald Q
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Rocket decelerated mine
US 2848945 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)

Allg 26, 1958 D. Q. BRUMBAUGH ROCKET DECELERATED MINE Filed OCl'.. 15, 1954 NN N ml nl 1mi NQ .Nd-m

INVENTOR D. Q. BRUMBAUGH ATTORNEYS mm hm g @234g 91mg 2,848,945 Patented Aug. 26, 1958 ROCKET DECELERATED MINE Donald Q. Brumbangh, Hyattsville, Md., assignor to the United States of America as represented by the Secretary of the Navy Application October 15, 1954, Serial No. 462,635

3 Claims. (Cl. 102-7) (Granted under Title 3S, U. S. Code (1952), sec. 266) The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

'I'he present invention relates to a device for decelerating a mine and more particularly to a device for reducing the forward velocity of a mine whereby the mine may enter the water without damage thereto or to the delicate mechanism contained therein when launched at high or low altitudes from a fast moving aircraft.

More specifically, the invention relates to a decelerating device for use in an aerial launched mine in which the decelerating force is produced by a rocket motor mounted in the nose of the mine and which includes fuze means operated as the mine is dropped from the aircraft in ight for initiating the rocket motor when the mine is a predetermined distance from the surface of a body of Water thereby to reduce the velocity of the mine prior to entrance of the mine into the water.

The parachute method heretofore used for decelerating a mine during a mine planting operation has not proven entirely satisfactory particularly when the mine was released from high altitudes and a direct opening chute was employed for the reasons that the chute caused the mine to drift of course due to the various aerodynamic forces acting thereon and thus preventing accurate planting of the mine in the desired area and the delayed opening type parachute method required complicated control devices and equipment which at times proved unreliable.

The present invention overcomes the disadvantages heretofore encountered by providing a new and improved rocket decelerating device which is devoid of cumbersome parachute packs and fragile control devices whereby the mine may be accurately planted in the desired area and the forward motion of the mine is invariably retarded as lthe mine approaches the surface of the body of water.

An object of the invention is to provide a new and improved rocket decelerating device for an aerial launched mine.

Another object of the invention is the provision of a rocket decelerating device which may be readily installed in a conventional marine mine for reducing the forward velocity of the mine .after the mine is launched from a fast moving aircraft.

A further object of the invention is to provide a mine deceleration device in which the decelerating force is produced by a rocket motor actuated as the mine approaches the surface of a body of water after the mine is dropped from an aircraft in ight.

A further object of the invention is to provide a mine deceleration device constructed and arranged to reduce the velocity of the mine in predetermined time delayed relation with respect to impact of the mine with the surface of la body of water thereby to prevent damage to the mine and the mine control mechanism contained therein as the mine enters the water.

A still further object of the invention is the provision of a rocket deceleration device for au aerial launched marine mine wherein a discharge jet of a rocket motor operated in time delayed relation with respect to the release of the mine from an aircraft in flight thereby to reduce the forward velocity of the rnine prior to entrance of the mine into a body of water.'

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawing wherein:

Fig. 1 is an elevational view of a mine partially broken away and partially in section illustrating a preferred embodiment of the present invention attached to a marine mine;

Fig. 2 is a view similar to Fig. 1 illustrating an alternate arrangement of the device of Fig. l; and

Fig. 3 is a fragmentary sectional view of a mine illustrating another alternate arrangement of the device of Fig. l.

vReferring now to the drawing wherein like characters of reference are used to designate like parts throughout the several views and more particularly to Fig. 1 thereof, the numeral 10 generally indicates the mine. The mine comprises a casing 11 having a stabilizing assembly 12 secured to one end and a centrally disposed tubular member 13 formed on the other end thereof enclosed by the mine casing 11 and providing a well 14 within the leading end or nose of the mine casing.

The deceleration device consists essentially of a rocket motor 15 and a fuze 16, as illustrated, the aforesaid elements are disposed within the well or recess 14 and arranged along the longitudinal axis of the mine casing.

The motor 15 comprises a tube 17 secured to the mine casing 11 as at 18 by threaded engagement therewith and having propellant charge 19 therein. A nozzle 20 is disposed within the tube 17 at the nose end of the mine and a squib 21 and igniter 22 is disposed within the tube and arranged at one end of the propellant charge 19. It will be noted that the fuze 16 is releasably mounted in the forward end of the tube 17 by a pair of resilient elements 23 disposed about the fuze casing and in frictional engagement with the tube 17, the fuze being electrically connected to the squib 21 by a pair of conductors 24.

The fuze 16 may be a well known conventional VT type fuze such, for example, as the type which is actuated by reections of a radio signal transmitted therefrom and from the water or land when the mine is a predetermined distance from the surface thereof. The fuze, however, is rendered operable as the arming wire 25 is withdrawn therefrom, withdrawal of the arming wire occurring as the mine is released from an aircraft and falls away therefrom. When this occurs, the fuze is in a condition to be operated in response to water reflections thereby to supply an electrical firing impulse to the squib 21 by way of conductors 24. Moreover, the fuze 16 is constructed and arranged to initiate the rocket motor when the mine is a predetermined distance from the surface of the body of water such, for example, as from 500 to 1000 feet.

Upon firing of the squib 21 in the aforesaid manner, the igniter 22 is ignited which, in turn, ignites the propellant charge 19. It will be understood that when the propellant 19 is ignited, the fuze 16 is forcibly ejected from the motor tube 17 by the force of the jet developed and discharged through nozzle 20. Thus as the rocket motor operates the resulting action creates a substantial backward thrust to slow the forward velocity of the mine sufliciently to permit the mine to enter the water without damage thereto.

If desired, a pair of slip connectors may be provided on the pair of conductors 24 respectively at the squib end of the motor to detachably secure the conductors thereto whereby the conductors may be carried along with the fuze as the fuze is forcibly ejected from the motor tube 17 1n the aforesaid manner. Furthermore, suitable insulating material 30 is disposed between the tube 17 and tubular elementlS thereby to `heatinsulatethe motor. s

from the main charge 26 whereupon iringrof the main charge by the heat developed as the propellant is ignited and burns is prevented.

Referring now to Fig. 2, the arrangement shown thereon is particularly adapted for use in mine planting operations at low altitudes such, for example, as at 20G feet and comprises a fuze generally indicated by the reference character 2'7; It will be noted that the mine, rocket motor and fuze retaining elements are identical to the structure shown in.Fig. l and thus like reference characters are employed to designate such like parts.

The fuze 27 illustrated on Fig; 2 is a percussion red and delayed type fuze and comprises a casing 28 releasably held in the nose end of the mine by the resilient elements 23. A delay element 29 and flash charge 31 is disposed within one end of the casing 28, the flash charge having one end of a quick burning pyrotechnic fuze 32 connected thereto, the other end of the fuze being connected to the squib 2l. A spring actuated tiring pin 33 is releasably held in an initial safe position by the arming wire 25, the wire being withdrawn to release the firing pin in the manner heretofore set forth. When this occurs, the firing pin is forcibly driven into firing engagement with the delay element 29 by the spring 33' whereupon the delay element is fired. After a predetermined period of time has elapsed the delay element fires the ash charge ,3l which ignites the quick burning fuze 32'thereby tiring the squib 2l. The squib ignites the igniter 22 which ignites the propellant 19 whereupon the fuze 27 is forcibly ejected from the motor tube 17 and thus the rocket motor will operate in the same man- Iner as heretofore set forth to retard the forward motion of the mine.

In the arrangement of Fig. 3, the fuze is generally indicated by the reference character 34 and comprises casing 35 releasably secured within the motor tube 17 in like manner to fuzes lo and 27. The fuze 34 is preferably a mechanical delay type fuze which is rendered operable as the arming wire Z is withdrawn therefrom and may include either a suitable clock mechanism of any well known type such, for example, as the type of clock mechanism employed in an automatic electric toaster or motor means having a reduction gear arrangement for actuating the Switch 35 from a normally open position to a closed position in predetermined time delayed relation withV respect t'o the release of the mine from the aircraft by movement of the switch actuating rod 39 as the arming wire 25 is withdrawn. The switch comprises a pair of contacts 36 and 37 normally engaging a sleeve 3S .mounted on the switch actuating rod 39 and composed of any insulating material suitable for the purpose. VBy this arrangement, the switch is normally openY and will remain open until the rod 39 is moved axially toward the trailing end of the mine by the aforesaid mechanisms. lt will be understood that as the rod 39 is moved, contacts 3io-37 are brought into engagement with the rod which is composed of conducting material. When this occurs, the ring `circuit 41 connected to the squib 21 and including contacts 36-37 and a battery B is rendered effective thereby to re the squib which ignites the igniter 22 and thus the rocket motor is set in operation whereupon the resulting action forcibly ejects the fuze 34 from tube 17 and creates a substantial `backward thrust to slow the forward velocity of the mine.

Brieiy stated in summary, the present. invention contemplates the provision of a new and improved deceleration device for an aerial planted marine mine for reducing Vthe forward velocity of the mine after the minehas been released from the aircraft and a predetermined period of time before the mine enters a body of water.

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 sco-pe of the appended claims the invention may be practiced otherwise-than as specifically described.

What is claimed as new and desired to be secured by Letters VPatenteof the United States is:

l. A decelerating device for a mine adapted to be dropped from an aircraft in flight comprising, in combination, a mine casing having a centrally disposed well formed therein and opening in the nose portion thereof, a rocket motor disposed with-in said well, a fuze disposed within saidwell, means including a normally open tiring circuit connected to said motor and fuze for igniting said rocket motor as said ring circuit is closed, normally open switch; means 'carriedby said fuze andincluded in said tiring'circuit for closing said tiring circuit,

a movable rod having a contact element carried thereby' for closing said switch means as the rod is movedlongif tudinally from anY initial locked position to a moved yposition, an arming wire releasably connected to said rodfor locking the rod in said initial position until the arming wire is disconnected therefrom, and a time delay actuating mechanism connected to said rod for moving` the rod to said moved position when a predetermined` period of time has elapsed after the arming wire has been disconnected.

2. A device fordecelerating the forward velocity-,of an I aerial launched mine as the mine approaches the surface of a body of water comprising, in combination, a mine` casing having an axially disposed wall integral with said casing and forming a well within the casing, a container disposed within said well in threaded engagement withsaid casing and in uniform spaced relation with respect to said wall, a rocket motor having a propellant charge disposed within said container, an igniter arranged within said container for igniting said propellant charge as the igniter is ignited, a perCussive fuze disposed Within and releasably sealed in one end of the well and adapted to be forcibly ejected therefrom by the products of combustion of the propellant charge as the charge is ignited, a

pair of mutually spaced annular grooves formed in said f wall, a pair of complementary grooves formed in'said fuze, a pair of mutually spaced annular resilient elements disposed within said grooves in the wall and fuze respectively for releasably sealing said fuze within the well, a

firing pin carried by said fuze, means for actuating said 1 firing pin to a tiring position as the mine is released from an aircraft in flight, a pyrotechnic delay element carried'.

by sai-d fuze and ignited by said tiring pin, a pyrotechnic flash charge carried by said delay element and ignited thereby, a quick 'burning elongated pyrotechnic fuze having one end connected to said flash charge and the otherV end thereofconnected to said igniter and ignited by said ash charge for igniting saidv igniter when a predetermined period of time corresponding to said delay has elapsed thereby to ignite said propellant charge when the mine is a predetermined distance above the surface of the aerial launched mine asy the mine approaches the surface of 4a body of water comprising, in combinationa mine casing having-an axially disposed wall integral with said,V

casing and forming a well within the casingga container disposed within said wellA ,in threaded engagementwith saidwall and 4in uniform spaced relation, with respect to said wall, a 'rocket motor disposed within said container, an igniter arranged within the container for igniting said rocket motor, an electrical fuze disposed within and releasably sealed in one end of the well and adapted to be forcibly ejected therefrom by the products of combustion ofthe motor as the motor is ignited, means including a pair of mutually spaced resilient elements carried by said fuze in engagement with said wall for releasably sealing the fuze in saidrwell, a source of electrical energy arranged within the fuze, a normally open tiring circuit connected to said igniter and said source for gniting said igniter as said circuit is closed, a rod composed of electrical conducting. material arranged within said fuze and movable axially from an initial position to a moved position, a sleeve composed of insulating material mounted on said rod, a pair of contacts included in said firing circuit normally in engagement with said sleeve for closing the ring circuit as the sleeve is moved lby said rod an amount suieiently to move the contacts out of engagement with the sleeve and into engagement with said rod, and a clock time delay actuating mechanism arranged within said fuze, for moving said rod from said initial position to said moved position a predetermined period of time after the mine has been dropped from an aircraft in Hight.

References Cited in the file of this patent UNITED STATES PATENTS 1,311,740 Asbury July 29, 1919 1,483,864 Borden et al. Feb. 19, 1924 1,884,125 Murrow Oct. 25, 1932 2,101,082 Mathsen Dec. 7, 1937 2,693,327 Hild Nov. 2, 1954 FOREIGN PATENTS 554,733 Great Britain July 16, 1943

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US1311740 *Jun 15, 1917Jul 29, 1919 asbury
US1483864 *Jun 27, 1922Feb 19, 1924Borden William ABomb body
US1884125 *Jun 4, 1930Oct 25, 1932Mitchell & MurrowOil well torpedo
US2101082 *Jun 4, 1935Dec 7, 1937Mathsen Marvin LFuse
US2693327 *Apr 6, 1951Nov 2, 1954Mutual CorpAerial supply projectile brake mechanism
GB554733A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3137232 *Mar 4, 1959Jun 16, 1964Julius AndrasSpace exploration rocket
US6699091Nov 4, 1999Mar 2, 2004Jon A. WarnerHand-launchable underwater projectile toy
US8033890May 17, 2006Oct 11, 2011Warner Jon ASelf-propelled hydrodynamic underwater toy
US20040259463 *Feb 26, 2004Dec 23, 2004Warner Jon A.Hand-launchable underwater projectile toy
Classifications
U.S. Classification102/390, 102/411
International ClassificationF42B22/44, F42B10/48, F42B10/00, F42B22/00
Cooperative ClassificationF42B10/48, F42B22/44
European ClassificationF42B22/44, F42B10/48