US3464356A - Self-stabilizing rod penetrators - Google Patents

Self-stabilizing rod penetrators Download PDF

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Publication number
US3464356A
US3464356A US694188A US3464356DA US3464356A US 3464356 A US3464356 A US 3464356A US 694188 A US694188 A US 694188A US 3464356D A US3464356D A US 3464356DA US 3464356 A US3464356 A US 3464356A
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Prior art keywords
rod
spring
penetrator
self
penetrators
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Expired - Lifetime
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US694188A
Inventor
Saul Wasserman
Robert Salzman
Walter C O'keefe
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United States Department of the Army
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United States Department of the Army
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/50—Brake flaps, e.g. inflatable
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/12—Stabilising arrangements using fins longitudinally-slidable with respect to the projectile or missile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/06—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with hard or heavy core; Kinetic energy penetrators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles

Definitions

  • the invention relates to a rod penetrator and more particularly to a rod penetrator having a collapsible flared section on its rearward end.
  • Rods of high length/diameter ratios have been found to be excellent penetrators. To eflect penetration, the rods must contact their targets headon, which requires precise stability in flight.
  • Stability in flight may be achieved gyroscopically or aerodynamically the latter presenting fewer problems due to the elimination of any elaborate mechanisms needed for spin-up.
  • Aerodynamic stabilization of rods by means of a noncollapsible flared section on the rearward end thereof poses two major disadvantages, namely, (1) high drag and (2) low packing density.
  • the flared section offers high drag resistance and quickly acts to reduce the velocity of the rod. This is not a serious problem, however, where distances of intercept are short or air densities are relatively low. In these two instances, the velocity of the rod will not decay substantially below that required to effect a kill.
  • the second disadvantage that of low packing density, is of major importance since the number of lethal mechanisms capable of being carried by a warhead is directly related to hit prob ability.
  • One method of packing rods having flared sections would be to place the rods in a nose-to tail fashion, thus, while desirably increasing the density of packing, would suffer the disadvantage of having one-half the rods launched backwards with obvious stability or aerodynamic drawbacks.
  • Another object is the provision of a rod penetrator having a collapsible flared section on its rearward end permitting denser packing than heretofore achieved.
  • FIG. 1 is a perspective view with parts broken away, of the invention in its open position.
  • FIG. 2 is a perspective view with parts broken away, of the invention in its closed position.
  • FIG. 3 shows a pluralty of inventive devices as placed in a warhead.
  • FIG. 4 shows an enlarged view of a plurality of inventive devices.
  • a rod penetrator 10 has a volute spring 12 secured to one end thereof.
  • the spring is secured at its closed end 12' to the rear of the rod penetrator 10 by the use of an epoxy resin.
  • the spring 12 is covered by an elastic membrane 14 also secured by epoxy to the rod 10.
  • the rod 10 has the configuration as illustrated in FIG. 2. In this closed position the flared section 16 is contracted to the diameter of the solid cylindrical rod body portion 18 of rod penetrator 10 thereby enabling easy packing of the rod penetrators 10 into a dense matrix 20 (FIGS. 3 and 4).
  • the spring 12 of each rod 10 When the rods are packed in a matrix bundle 20, the spring 12 of each rod 10 is held in compressive restraint by the adjacent rods, however when this restraining force is released by the breaking up of the matrix bundle 20, the spring 12 expands, as shown in FIG. 1.
  • the volute spring 12 has the unique property of expanding in width as well as length upon release. This expansion provides a supporting skeleton framework for the membrane 14 which is attached to the ends of the spring and which, upon the springs expansion, stretches to its full length and width.
  • the smooth surface of the membrane produces the outer assemblance of the frusto-conical configuration of aerodynamic contour, as shown in FIG. 1.
  • the turn of the volute spring in expansion could be tight enough to provide a continuous aerodynamic surface without the need of a membrane.
  • each rod penetrator In packing the matrix bundle 20 (FIG. 4) into a warhead 22 the fiared section 16 of each rod penetrator would have to be held in such as way as to prevent the spring 12 from unwinding. Once the particular rod penetrator has been inserted into the matrix bundle 20 then each adjacent rod penetrator would prevent of its spring unwinding.
  • a rod penetrator comprising:
  • volute spring having an open end and a closed end and secured at its closed end to a rearward portion of said rod
  • volute spring being expandable from a constrained position in which it is cylindrical and of substantially the same diameter as said rod to an unconstrained position in which it expands axially and radially thereby to assume a frusto-conical configuration in which the forward base of the spring is contiguous with the rearward end of said rod and is smaller in diameter than said rod and the rearward base of the spring is larger in diameter than said rod, to maintain aerodynamic stability in flight of said rod penetrator.
  • a rod penetrator of the type described in claim 1 having an elastic membrane covering said volute spring.
  • each rod penetrator including:
  • volute spring having an open end and a closed end
  • References Cited an elastic membrane covering said volute spring UNITED STATES PATENTS said volute spring secured at its closed end to a rear- 1 305 967 6/1919 Hawks 102 67 ward portion of said rod and held in a constrained 2368258 1/1945 g position in which it is cylindrical and of substantially 5 2671398 3/1954 Peck the same diameter as said rod by the adjacent rod 3:081:703 3/1963 Kamp et a1 penetrators in said matrix whereby upon release of 3,114,315 12/1963 Trump 102 4 said matrix said rod penetrator will separate from said matrix and said volute spring will expand axially FOREIGN PATENTS and radially thereby to assume a frusto-conical con- 10 550,001 12/1942 Great Britainfiguration in which the forward base of the spring is contiguous with the rearward end of said rod and BENJAMIN BORCHELT Primary Exammer is smaller in diameter than

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Rollers For Roller Conveyors For Transfer (AREA)
  • Footwear And Its Accessory, Manufacturing Method And Apparatuses (AREA)

Description

P 1959 s. WASSERMAN ET AL 3,464,356
SELF-STABILIZING ROD BENETRATORS Filed D96. 28, 1967 INVENTORS SAUL WASSERMAN ROBERT SALZMAN WALTER O'KEEFE United States Patent 3,464,356 SELF-STABILIZING ROD PENETRATORS Saul Wasser'rnan, Rockaway, N.J., Robert Salzman,
Arlington, Va., and Walter C. OKeefe, Landing, N.J., assignors to the United States of America as represented by the Secretary of the Army Filed Dec. 28, 1967, Ser. N 0. 694,188 Int. Cl. F42b 25/08 US. Cl. 102-67 3 Claims ABSTRACT OF THE DISCLOSURE A rod for penetrating enemy target which includes a collapsible flared section on its rearward end, for permitting denser packing and aerodynamic stabilizatlon.
The invention described herein may be manufactured, used, and licensed by or for the government for governmental purposes without the payment to use of any royalty thereon.
The invention relates to a rod penetrator and more particularly to a rod penetrator having a collapsible flared section on its rearward end.
Rods of high length/diameter ratios have been found to be excellent penetrators. To eflect penetration, the rods must contact their targets headon, which requires precise stability in flight.
Stability in flight may be achieved gyroscopically or aerodynamically the latter presenting fewer problems due to the elimination of any elaborate mechanisms needed for spin-up.
Aerodynamic stabilization of rods by means of a noncollapsible flared section on the rearward end thereof poses two major disadvantages, namely, (1) high drag and (2) low packing density. The flared section offers high drag resistance and quickly acts to reduce the velocity of the rod. This is not a serious problem, however, where distances of intercept are short or air densities are relatively low. In these two instances, the velocity of the rod will not decay substantially below that required to effect a kill.
The second disadvantage, that of low packing density, is of major importance since the number of lethal mechanisms capable of being carried by a warhead is directly related to hit prob ability.
One method of packing rods having flared sections would be to place the rods in a nose-to tail fashion, thus, while desirably increasing the density of packing, would suffer the disadvantage of having one-half the rods launched backwards with obvious stability or aerodynamic drawbacks.
It is therefore an object of the present invention to provide a rod penetrator having a flared section on its rearward end for aerodynamic stabilization.
Another object is the provision of a rod penetrator having a collapsible flared section on its rearward end permitting denser packing than heretofore achieved.
The above objects as well as others together with benefits and advantages of the invention will be apparent upon reference to the detailed description set forth hereto wherein:
FIG. 1 is a perspective view with parts broken away, of the invention in its open position.
3,464,356 Patented Sept. 2, 1969 FIG. 2 is a perspective view with parts broken away, of the invention in its closed position.
FIG. 3 shows a pluralty of inventive devices as placed in a warhead.
FIG. 4 shows an enlarged view of a plurality of inventive devices.
As seen in the drawings, a rod penetrator 10 has a volute spring 12 secured to one end thereof. The spring is secured at its closed end 12' to the rear of the rod penetrator 10 by the use of an epoxy resin. The spring 12 is covered by an elastic membrane 14 also secured by epoxy to the rod 10. When the spring 12 is contracted, the rod 10 has the configuration as illustrated in FIG. 2. In this closed position the flared section 16 is contracted to the diameter of the solid cylindrical rod body portion 18 of rod penetrator 10 thereby enabling easy packing of the rod penetrators 10 into a dense matrix 20 (FIGS. 3 and 4). When the rods are packed in a matrix bundle 20, the spring 12 of each rod 10 is held in compressive restraint by the adjacent rods, however when this restraining force is released by the breaking up of the matrix bundle 20, the spring 12 expands, as shown in FIG. 1. The volute spring 12 has the unique property of expanding in width as well as length upon release. This expansion provides a supporting skeleton framework for the membrane 14 which is attached to the ends of the spring and which, upon the springs expansion, stretches to its full length and width. The smooth surface of the membrane produces the outer assemblance of the frusto-conical configuration of aerodynamic contour, as shown in FIG. 1.
As an alternate method of construction the turn of the volute spring in expansion could be tight enough to provide a continuous aerodynamic surface without the need of a membrane.
In packing the matrix bundle 20 (FIG. 4) into a warhead 22 the fiared section 16 of each rod penetrator would have to be held in such as way as to prevent the spring 12 from unwinding. Once the particular rod penetrator has been inserted into the matrix bundle 20 then each adjacent rod penetrator would prevent of its spring unwinding.
We claim:
1. A rod penetrator comprising:
a solid cylindrical rod,
a volute spring having an open end and a closed end and secured at its closed end to a rearward portion of said rod,
said volute spring being expandable from a constrained position in which it is cylindrical and of substantially the same diameter as said rod to an unconstrained position in which it expands axially and radially thereby to assume a frusto-conical configuration in which the forward base of the spring is contiguous with the rearward end of said rod and is smaller in diameter than said rod and the rearward base of the spring is larger in diameter than said rod, to maintain aerodynamic stability in flight of said rod penetrator.
2. A rod penetrator of the type described in claim 1 having an elastic membrane covering said volute spring.
3. In combination with a warhead having a matrix of rod penetrators, each rod penetrator including:
a solid cylindrical rod,
a volute spring having an open end and a closed end, References Cited an elastic membrane covering said volute spring, UNITED STATES PATENTS said volute spring secured at its closed end to a rear- 1 305 967 6/1919 Hawks 102 67 ward portion of said rod and held in a constrained 2368258 1/1945 g position in which it is cylindrical and of substantially 5 2671398 3/1954 Peck the same diameter as said rod by the adjacent rod 3:081:703 3/1963 Kamp et a1 penetrators in said matrix whereby upon release of 3,114,315 12/1963 Trump 102 4 said matrix said rod penetrator will separate from said matrix and said volute spring will expand axially FOREIGN PATENTS and radially thereby to assume a frusto-conical con- 10 550,001 12/1942 Great Britainfiguration in which the forward base of the spring is contiguous with the rearward end of said rod and BENJAMIN BORCHELT Primary Exammer is smaller in diameter than said rod and the rearward 1. FOX, Assistant Examiner base of the spring is larger in diameter than said rod, 15
to maintain aerodynamic stability in flight of said rod CL penetrator. 4 1024
US694188A 1967-12-28 1967-12-28 Self-stabilizing rod penetrators Expired - Lifetime US3464356A (en)

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Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050109233A1 (en) * 2003-10-03 2005-05-26 Giat Industries Perforating ammunition
US20050109234A1 (en) * 2001-08-23 2005-05-26 Lloyd Richard M. Kinetic energy rod warhead with lower deployment angles
US20060021538A1 (en) * 2002-08-29 2006-02-02 Lloyd Richard M Kinetic energy rod warhead deployment system
US20060086279A1 (en) * 2001-08-23 2006-04-27 Lloyd Richard M Kinetic energy rod warhead with lower deployment angles
US20060283347A1 (en) * 2001-08-23 2006-12-21 Lloyd Richard M Kinetic energy rod warhead with projectile spacing
US20060283348A1 (en) * 2001-08-23 2006-12-21 Lloyd Richard M Kinetic energy rod warhead with self-aligning penetrators
WO2006116589A3 (en) * 2005-04-26 2007-03-29 Lockheed Corp Dunnage for penetrators
US20070084376A1 (en) * 2001-08-23 2007-04-19 Lloyd Richard M Kinetic energy rod warhead with aiming mechanism
WO2007117993A3 (en) * 2006-04-07 2008-10-16 Us Army Artillery rocket kinetic energy rod warhead
US20080307994A1 (en) * 2004-01-15 2008-12-18 Bae System Bofors Ab Warhead
US20090205529A1 (en) * 2001-08-23 2009-08-20 Lloyd Richard M Kinetic energy rod warhead with lower deployment angles
US20100084505A1 (en) * 2008-10-02 2010-04-08 Raytheon Company Multi-stage hyper-velocity kinetic energy missile
US7717042B2 (en) 2004-11-29 2010-05-18 Raytheon Company Wide area dispersal warhead
US7726244B1 (en) 2003-10-14 2010-06-01 Raytheon Company Mine counter measure system
US7762196B1 (en) * 2007-04-12 2010-07-27 Lockheed Martin Corporation Munition containing sub-munitions that disperse in a circular delta grid impact pattern and method therefor
US20100212531A1 (en) * 2007-07-20 2010-08-26 Dindl Firearms Manufacturing, Inc. Flechette cartridge
US20120068000A1 (en) * 2008-10-12 2012-03-22 Israel Aerospace Industries Ltd. Interception system that employs miniature kill vehicles
US8418623B2 (en) 2010-04-02 2013-04-16 Raytheon Company Multi-point time spacing kinetic energy rod warhead and system
US8575526B1 (en) * 2010-10-05 2013-11-05 Lockheed Martin Corporation System and method for dispensing of multiple kill vehicles using an integrated multiple kill vehicle payload

Families Citing this family (4)

* Cited by examiner, † Cited by third party
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DE2845431C1 (en) * 1978-10-19 1991-10-24 Rheinmetall Gmbh Balancing bullet
GB2205798B (en) * 1983-08-11 1989-06-01 Secr Defence Improvements in or relating to unmanned aircraft.
DE3403573A1 (en) * 1983-11-09 1985-08-08 Diehl GmbH & Co, 8500 Nürnberg BULLET WITH FOLD-OUT WINGS
GB8524813D0 (en) * 1985-10-08 1986-12-17 British Aerospace Projectiles

Citations (6)

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Publication number Priority date Publication date Assignee Title
US1305967A (en) * 1918-05-22 1919-06-03 Edward A Hawks Explosive shell.
GB550001A (en) * 1941-07-16 1942-12-17 Lewis Motley Improvements in or relating to ordnance projectiles
US2368258A (en) * 1942-02-04 1945-01-30 Frank G Manson Stabilizing retarder for bombs
US2671398A (en) * 1951-05-11 1954-03-09 Allen S Peck Metal pop-out stabilizing tail for small bombs
US3081703A (en) * 1958-07-29 1963-03-19 Ewald A Kamp Spin-cone stabilized projectile
US3114315A (en) * 1961-09-26 1963-12-17 William E Trump Dive brake

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1305967A (en) * 1918-05-22 1919-06-03 Edward A Hawks Explosive shell.
GB550001A (en) * 1941-07-16 1942-12-17 Lewis Motley Improvements in or relating to ordnance projectiles
US2368258A (en) * 1942-02-04 1945-01-30 Frank G Manson Stabilizing retarder for bombs
US2671398A (en) * 1951-05-11 1954-03-09 Allen S Peck Metal pop-out stabilizing tail for small bombs
US3081703A (en) * 1958-07-29 1963-03-19 Ewald A Kamp Spin-cone stabilized projectile
US3114315A (en) * 1961-09-26 1963-12-17 William E Trump Dive brake

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7621222B2 (en) 2001-08-23 2009-11-24 Raytheon Company Kinetic energy rod warhead with lower deployment angles
US7624683B2 (en) * 2001-08-23 2009-12-01 Raytheon Company Kinetic energy rod warhead with projectile spacing
US8127686B2 (en) 2001-08-23 2012-03-06 Raytheon Company Kinetic energy rod warhead with aiming mechanism
US20060086279A1 (en) * 2001-08-23 2006-04-27 Lloyd Richard M Kinetic energy rod warhead with lower deployment angles
US7624682B2 (en) 2001-08-23 2009-12-01 Raytheon Company Kinetic energy rod warhead with lower deployment angles
US20060283347A1 (en) * 2001-08-23 2006-12-21 Lloyd Richard M Kinetic energy rod warhead with projectile spacing
US20060283348A1 (en) * 2001-08-23 2006-12-21 Lloyd Richard M Kinetic energy rod warhead with self-aligning penetrators
US20090205529A1 (en) * 2001-08-23 2009-08-20 Lloyd Richard M Kinetic energy rod warhead with lower deployment angles
US20050109234A1 (en) * 2001-08-23 2005-05-26 Lloyd Richard M. Kinetic energy rod warhead with lower deployment angles
US20070084376A1 (en) * 2001-08-23 2007-04-19 Lloyd Richard M Kinetic energy rod warhead with aiming mechanism
US20060021538A1 (en) * 2002-08-29 2006-02-02 Lloyd Richard M Kinetic energy rod warhead deployment system
US20050109233A1 (en) * 2003-10-03 2005-05-26 Giat Industries Perforating ammunition
US7063020B2 (en) * 2003-10-03 2006-06-20 Giat Industries Perforating ammunition
US7726244B1 (en) 2003-10-14 2010-06-01 Raytheon Company Mine counter measure system
US8196514B2 (en) * 2004-01-15 2012-06-12 Bae Systems Bofors Ab Warhead
US20080307994A1 (en) * 2004-01-15 2008-12-18 Bae System Bofors Ab Warhead
US7717042B2 (en) 2004-11-29 2010-05-18 Raytheon Company Wide area dispersal warhead
WO2006116589A3 (en) * 2005-04-26 2007-03-29 Lockheed Corp Dunnage for penetrators
WO2007117993A3 (en) * 2006-04-07 2008-10-16 Us Army Artillery rocket kinetic energy rod warhead
US7762196B1 (en) * 2007-04-12 2010-07-27 Lockheed Martin Corporation Munition containing sub-munitions that disperse in a circular delta grid impact pattern and method therefor
US20100192796A1 (en) * 2007-04-12 2010-08-05 Lockheed Martin Corporation Munition containing sub-munitions that disperse in a circular delta grid impact pattern and method therefor
US20100212531A1 (en) * 2007-07-20 2010-08-26 Dindl Firearms Manufacturing, Inc. Flechette cartridge
US7823509B2 (en) * 2007-07-20 2010-11-02 Frank J Dindl Flechette cartridge
US8119956B2 (en) * 2008-10-02 2012-02-21 Raytheon Company Multi-stage hyper-velocity kinetic energy missile
US20100084505A1 (en) * 2008-10-02 2010-04-08 Raytheon Company Multi-stage hyper-velocity kinetic energy missile
US20120068000A1 (en) * 2008-10-12 2012-03-22 Israel Aerospace Industries Ltd. Interception system that employs miniature kill vehicles
US8418623B2 (en) 2010-04-02 2013-04-16 Raytheon Company Multi-point time spacing kinetic energy rod warhead and system
US8575526B1 (en) * 2010-10-05 2013-11-05 Lockheed Martin Corporation System and method for dispensing of multiple kill vehicles using an integrated multiple kill vehicle payload

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