EP0821215A2 - Gegenmassnahmenvorrichtung zum Entfalten von Unterbrechungselementen von drallstabilisierten Raketen - Google Patents

Gegenmassnahmenvorrichtung zum Entfalten von Unterbrechungselementen von drallstabilisierten Raketen Download PDF

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Publication number
EP0821215A2
EP0821215A2 EP97112868A EP97112868A EP0821215A2 EP 0821215 A2 EP0821215 A2 EP 0821215A2 EP 97112868 A EP97112868 A EP 97112868A EP 97112868 A EP97112868 A EP 97112868A EP 0821215 A2 EP0821215 A2 EP 0821215A2
Authority
EP
European Patent Office
Prior art keywords
elements
nei
rocket
payload section
drive
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP97112868A
Other languages
English (en)
French (fr)
Other versions
EP0821215A3 (de
Inventor
David P. Smith
Jane M. Lin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Northrop Grumman Space and Mission Systems Corp
Original Assignee
TRW Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by TRW Inc filed Critical TRW Inc
Publication of EP0821215A2 publication Critical patent/EP0821215A2/de
Publication of EP0821215A3 publication Critical patent/EP0821215A3/de
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially

Definitions

  • This invention relates to countermeasures for killing a hostile missile and more particularly to the deployment of non-explosive intercepter elements ("NEI") deployed in the direct path of an incoming hostile missile from a spin stabilized rocket.
  • NAI non-explosive intercepter elements
  • Battlefield engagements involving such weaponry as tanks, mobile artillery vehicles and other artillery pieces are vulnerable to attack by enemy armor-destroying guided missiles.
  • Defensive countermeasures to neutralize or kill such incoming hostile attacks generally utilize explosive means for destroying the hostile missile and as a result pose a threat to friendly military personnel in the battle zone.
  • Currently available countermeasure systems which involve guided missiles are costly and complicated to construct and, above all, the use of explosives as a countermeasure offer the potential of harming friendly military personnel.
  • the use of countermeasures activated by proximity fuses are particularly hazardous to friendly military personnel. What is needed is an active defense system that itself is not explosive and yet will effectively intercept and kill an incoming guided missile using NEI which will at least lessen or decrease the hazard to friendly military personnel in the vicinity.
  • the subprojectiles and shrapnel-like particles pose a hazard to friendly military personnel.
  • Other known countermeasure techniques involve the use of guided missiles that are triggered by a contact fuse or otherwise guided by optical sensors to engage the incoming hostile missile. It has been found that the high probability of successfully defending against such hostile guided missiles is the creation of a cloud of NEI which are deployed directly in the trajectory path at a precise time and in a controlled pattern to assure collision and destruction.
  • an airborne apparatus is provided that is directed along an interception path for dispensing a plurality of non-explosive intercepter (“NEI") elements in a predetermined configuration to generate a continuous cloud which is directly in the path of the oncoming hostile missile.
  • the apparatus is in the form of a spin stabilized rocket having a longitudinal axis, a rearward end, a lead end, a nose cone body, and a payload section intermediate said nose cone and the rearward end, said payload being disposed circumferentially about the longitudinal axis of the rocket.
  • the payload is comprised of a supply of NEI elements which are propelled from the payload section at a constant tangential velocity in response to the centrifugal force produced by the spin rate of the spin stabilized rocket in flight.
  • Release means is provided in the form of a slidably driven sleeve assembly that covers the payload section during flight and releasing the NEI elements when the sleeve assembly is retracted from the rearward end to the lead end exposing the payload section free of containment. Dispersing the NEI elements forms an intercepter cloud. The cloud is precisely deployed directly in the trajectory path to stop the hostile missile.
  • the intercepters may be contained in a series of tube structures arranged radially about the longitudinal axis propelling the NEI elements in a particular formation by the centrifugal force of the spin stabilized rocket which generates a particularly shaped intercepter cloud.
  • the NEI elements are randomly placed in the payload section so that deployment at the precise time forms a controlled cloud of air borne elements in the intercepting path of hostile missile.
  • This invention is directed to a defensive countermeasure apparatus identified generally with the numeral 10 that can be used to protect weaponry such as tanks and other mobile vehicles such as artillery pieces to be defended against guided missiles.
  • Such countermeasure apparatus desirably should intercept the incoming missile in a manner that presents a minimal hazard to friendly military personnel in the battle zone.
  • the use of explosive countermeasures against hostile missiles that depend on a contact fuse or proximity fuse to explode the defending apparatus in the vicinity of the incoming missile poses a recognized hazard to friendly military personnel operating in the targeted battle zone.
  • the defense system of this invention employs NEI elements which at least will reduce that hazard.
  • the construction and operation of the countermeasure apparatus is much less costly to produce because of the unique mechanical arrangement employed to deploy the NEI at the predetermined instant it encounters the incoming hostile missile.
  • the tracking system is rather uncomplicated for the reason it avoids the heat tracking sensors, proximity fuses or other sophisticated techniques. It relies on a radar tracking system.
  • the defense system of this invention is a spin stabilized rocket 10 spinning at 11,000 RPM having a rearward end 11 and a lead end 12 which is adapted to carry a deployable supply of NEI elements 14 .
  • Analogous elements in the various figures are denoted by the same reference numerals.
  • the apparatus 10 is a 102 mm diameter rocket equipped with a solid propellent motor (not shown) having a slidable sleeve assembly 16 , a payload section 17 , a nose cone body 18 and a drive mechanism identified generally with the numeral 20 .
  • the payload section 17 is defined by a movable wall 19 and rear fixed wall 22 .
  • the NEI elements 14 are loaded in the payload section 17 and are contained therein until the slidable sleeve assembly 16 is retracted uncovering the NEI elements 14 which are then propelled out from the payload section at a constant angular velocity in response to the centrifugal force generated by the spin rate of the rocket.
  • the manner of placement of the NEI elements within the payload section 17 provides advantages to the effectiveness of the apparatus.
  • the NEI elements are charged randomly into the payload section 17 . This is a less costly approach and upon deployment provides a randomly dispersed intercepter cloud.
  • the NEI elements are of a particular shape such as spheres or elongated rods and loaded into a series of rows of tubular structures extending radially about the longitudinal axis of the rocket.
  • the advantage of the second preferred embodiment is the special configuration of the intercepter cloud generated by the controlled rate at which the NEI elements are propelled as well as the uniform weight distribution of the load in the rocket assuring more accurate control of its flight pattern. Both embodiments provide good kill success by the respective intercepter clouds.
  • the NEI elements 14 are loaded into a series of rows of radially extending tubes 23 or cylinders forming an array of columns of NEI elements about the longitudinal axis 25 of the rocket.
  • the NEI elements are randomly charged into the payload section 17 .
  • portions of the loaded NEI elements are freed from containment forming an intercepter cloud of either a randomly deployed elements and in the other embodiment in particular configuration.
  • a drive mechanism 20 which at the appropriate time is actuated causing the slidable sleeve assembly 16 to move in a direction from the rearward end 11 to the lead end 12 of the spin stabilized rocket 10.
  • the slidable sleeve assembly 16 comprises a sleeve member 21 which is integrally affixed to and moves with the nose cone body 18 .
  • the support wall 19 has an annular opening 30 which is closed with a cup-shaped bracket 28 .
  • the drive mechanism 20 includes a drive cylinder 24 centrally mounted within the payload section 17 , generally along the center longitudinal axis 25 , and containing a drive rod 26 .
  • the drive rod 26 extends along the longitudinal axis 25 having one end 31 releasably supported in the rearward end 11 of the rocket and its forward end 32 affixed to the bracket 28 .
  • the bracket 28 also receives the forward end 29 of the drive cylinder 24 .
  • the support wall 19 extends transversely across the inside diameter of the rocket meeting the sleeve member 21 at the juncture 27 where it comes with the nose cone body 18 .
  • the sleeve member 21 , the shell of the nose cone body 18 and the wall 19 are welded at the juncture 27 or otherwise integrated so that the assembly 16 moves as a unitary assembly.
  • a slide support casing 34 concentrically surrounds the drive cylinder 24 .
  • the casing 34 is diametrically larger than the drive cylinder 24 forming an annular space 36 therebetween.
  • the slide support casing extends rearwardly through the payload section, its front end 37 fixed to the support wall 19 , and the back end being unattached. With the slide support casing 34 affixed to the front support wall 19 it will slide toward the lead end 12 as the support wall is moved forward.
  • a spring unit 40 disposed between the bracket 28 and the rear fixed support wall 22 of the payload section.
  • the driving mechanism may be equipped with an initiator type squib.
  • the drive rod 26 running through center of the rocket 10 along the longitudinal axis 25 is the drive rod 26 releasably secured at the rearward end 11 and extending into and through the drive cylinder 24 through the opening 41 and terminating at the other end of the drive cylinder 24 through opening 42 and secured to the bracket 28 within a notch 44 .
  • the back end of the drive rod 26 is releasably supported in the rearward end 11 of the rocket 10 and is locked in position by a trigger assembly 46 that releases the drive rod 26 in response to a predetermined signal generated by a time delay mechanism built into the trigger assembly.
  • the NEI elements 14 are randomly loaded in the payload section 17 .
  • the randomly loaded elements 14 in Fig. 5 will form a continuous cloud of randomly dispersed elements 14 .
  • Deployment occurs in the same manner as described in connection with Fig. 4 except that the NEI elements are propelled out from the payload section in random fashion thereby forming a continuous intercepter cloud.
  • the dimensions of the cloud are similar to that described in connection with Fig. 4.
  • the incoming hostile missile is detected.
  • the radar sensor provides the incoming velocity and range of the hostile missile which enables the calculation of the aiming and time point of actuating the time delay of the defense rocket of the instant invention.
  • the drive mechanism 20 is set to force the nose cone 18 and the sleeve member 21 to advance in the direction of the lead end 12 of the rocket by the biasing force of the coiled spring unit 40 biased against the ends of the cup-shaped bracket 28 which covers the annular opening 30 of the movable front payload wall 19 .
  • a dash pot 48 which serves to control the rate of movement of the drive rod 26 within the cylinder 24 that uncovers the payload section 17 .
  • the size and geometry of the continuous intercepter cloud of NEI can be controlled by the rate at which the sleeve member 21 unsheathes the payload section 17 centrifugally forcing out the NEI elements 14 in controlled cloud patterns. Rapid release in a short period of time of all of the NEI elements would create a rather condensed intercepter cloud and the slower the rate at which they are propelled out of the payload section 17 the more dispersed would be the continuous intercepter cloud.
  • Fig. 4 there is shown the condition of the rocket 10 with the trigger assembly 46 having been actuated releasing the drive rod 26 thereby setting the sleeve assembly 16 in motion towards the lead end 12 of the rocket 10 exposing the initial arrays of NEI elements.
  • the elements 14 are deployed by the centrifugal force of the spin stabilized rocket. Laboratory tests have demonstrated that the system will create a continuous cloud 50 of spherical intercepters.
  • the NEI elements may be spherically shaped such as, for example, ball bearings of 5/16 inches in diameter or steel rods 1/4 to 3/4 inches long and 5/16 inches in diameter, dispersed in the trajectory path of the incoming hostile missile.
  • the trigger assembly 46 is a time delay fuse that can be preset at launch or controlled by a radio link.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP97112868A 1996-07-25 1997-07-25 Gegenmassnahmenvorrichtung zum Entfalten von Unterbrechungselementen von drallstabilisierten Raketen Withdrawn EP0821215A3 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US68787796A 1996-07-25 1996-07-25
US687877 1996-07-25

Publications (2)

Publication Number Publication Date
EP0821215A2 true EP0821215A2 (de) 1998-01-28
EP0821215A3 EP0821215A3 (de) 2001-11-07

Family

ID=24762240

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97112868A Withdrawn EP0821215A3 (de) 1996-07-25 1997-07-25 Gegenmassnahmenvorrichtung zum Entfalten von Unterbrechungselementen von drallstabilisierten Raketen

Country Status (2)

Country Link
EP (1) EP0821215A3 (de)
IL (1) IL121220A0 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003006915A1 (en) * 2001-07-11 2003-01-23 Metal Storm Limited Projectile for radially deploying sub-projectiles
WO2004017014A1 (en) * 2002-08-16 2004-02-26 Metal Storm Limited Target interception
WO2013020911A1 (de) 2011-08-08 2013-02-14 Rheinmetall Air Defence Ag Vorrichtung und verfahren zum schutz von objekten
US8525977B2 (en) 2009-12-29 2013-09-03 Baiwen Qiao Phase measurement calibrating method and calibrating device based on liquid crystal light valve principle

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3799094A (en) * 1971-06-17 1974-03-26 Us Navy Underwater acoustical jamming apparatus
US3899975A (en) * 1972-07-11 1975-08-19 Bender Limited F Dispensing apparatus
US4388869A (en) * 1967-03-22 1983-06-21 The United States Of America As Represented By The Secretary Of The Navy Rotating rod warhead
EP0346214A1 (de) * 1988-06-10 1989-12-13 Thomson-Brandt Armements Verfahren und Vorrichtung zum Auswerfen von Submunition
US4947754A (en) * 1987-12-10 1990-08-14 General Dynamics Corporation, Pomona Division System and method for penetrating orbiting targets
US4975888A (en) * 1967-03-22 1990-12-04 The United States Of America As Represented By The Secretary Of The Navy Mine neutralization system

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4388869A (en) * 1967-03-22 1983-06-21 The United States Of America As Represented By The Secretary Of The Navy Rotating rod warhead
US4975888A (en) * 1967-03-22 1990-12-04 The United States Of America As Represented By The Secretary Of The Navy Mine neutralization system
US3799094A (en) * 1971-06-17 1974-03-26 Us Navy Underwater acoustical jamming apparatus
US3899975A (en) * 1972-07-11 1975-08-19 Bender Limited F Dispensing apparatus
US4947754A (en) * 1987-12-10 1990-08-14 General Dynamics Corporation, Pomona Division System and method for penetrating orbiting targets
EP0346214A1 (de) * 1988-06-10 1989-12-13 Thomson-Brandt Armements Verfahren und Vorrichtung zum Auswerfen von Submunition

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003006915A1 (en) * 2001-07-11 2003-01-23 Metal Storm Limited Projectile for radially deploying sub-projectiles
WO2004017014A1 (en) * 2002-08-16 2004-02-26 Metal Storm Limited Target interception
US7631600B2 (en) 2002-08-16 2009-12-15 Metal Storm Limited Target interception
US8525977B2 (en) 2009-12-29 2013-09-03 Baiwen Qiao Phase measurement calibrating method and calibrating device based on liquid crystal light valve principle
WO2013020911A1 (de) 2011-08-08 2013-02-14 Rheinmetall Air Defence Ag Vorrichtung und verfahren zum schutz von objekten
DE102011109658A1 (de) 2011-08-08 2013-02-14 Rheinmetall Air Defence Ag Vorrichtung und Verfahren zum Schutz von Objekten

Also Published As

Publication number Publication date
IL121220A0 (en) 1998-01-04
EP0821215A3 (de) 2001-11-07

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