EP0760458B1 - Asymmetrisches Penetratorgeschoss - Google Patents

Asymmetrisches Penetratorgeschoss Download PDF

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Publication number
EP0760458B1
EP0760458B1 EP96630047A EP96630047A EP0760458B1 EP 0760458 B1 EP0760458 B1 EP 0760458B1 EP 96630047 A EP96630047 A EP 96630047A EP 96630047 A EP96630047 A EP 96630047A EP 0760458 B1 EP0760458 B1 EP 0760458B1
Authority
EP
European Patent Office
Prior art keywords
warhead
target
missile
nose
nose section
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.)
Expired - Lifetime
Application number
EP96630047A
Other languages
English (en)
French (fr)
Other versions
EP0760458A1 (de
Inventor
Zeev Tal
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.)
Rafael Armament Development Authority Ltd
Rafael Advanced Defense Systems Ltd
State of Israel
Original Assignee
Rafael Armament Development Authority Ltd
Rafael Advanced Defense Systems Ltd
State of Israel
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 Rafael Armament Development Authority Ltd, Rafael Advanced Defense Systems Ltd, State of Israel filed Critical Rafael Armament Development Authority Ltd
Publication of EP0760458A1 publication Critical patent/EP0760458A1/de
Application granted granted Critical
Publication of EP0760458B1 publication Critical patent/EP0760458B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F42B12/04—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
    • F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
    • F42B30/08—Ordnance projectiles or missiles, e.g. shells

Definitions

  • the present invention relates to projectiles and missiles and, more particularly, to roll-stabilized guided missiles or "smart bombs" designed to reach and penetrate specific hardened targets.
  • a projectile is described in US-A-4 085 678. This document is considered to be the closest prior art.
  • a typical guided missile is commonly made up of a number of sections, which are housed in, or connected to a generally cylindrical housing of varying radius in the longitudinal direction.
  • the guidance section which typically includes one or more sensors, such as a Forward Looking Infrared (FLIR) or video camera, and the various electronic systems which control the sensors, analyze and interpret the signals received by the sensors, and control the flight control system which determines the trajectory and the roll position of the missile.
  • the guidance section may also include means for receiving signals from outside of the missile and may also includes means for transmitting signals from the missile.
  • the warhead which is typically a hollow cylindrically shaped casing, typically made of a high strength steel.
  • the function of a penetration warhead is to penetrate a hardened target and place the explosive charge in the appropriate position, i.e., inside the target, at the moment of explosion, thereby maximizing the effect of the explosion on the target.
  • Inside the hollow casing is placed the explosive and the rear end of the warhead lies the ignition fuse which is designed to be set off at the proper moment, typically, at some pre-determined time after the warhead encounters the target.
  • the warhead is typically made of three sections: (1) a front section, or nose, which is usually in the shape of an ogive or cone; (2) the main section which includes the explosive charge and is usually cylindrical; and (3) the aft section which seals the explosive charge within the casing and holds the fuse.
  • the flight control section housed in and connected to the housing at the rear of the missile, and in some cases also in other locations along the missile housing, is the flight control section, including fins and foils, which are used to adjust and stabilize the trajectory of the missile during its flight to the target and to prevent the missile from rolling during flight.
  • the missile impact the target directly i.e., at a 90° to the target surface.
  • the angle of impact is different, sometimes significantly, from the optimal 90°.
  • a significant fraction of hardened targets such as command bunkers, and the like, are built into the ground and have an outer wall which is substantially horizontal.
  • a typical guided missile would typically impact the outer wall at an angle which, in many cases, may be in the range of from about 45° to about 65°, substantially different from the optimal angle of 90°.
  • the deviation of the impact from the perpendicular greatly reduces the penetration depth of the warhead into the target and significantly decreases the effectiveness of the explosion.
  • DE-A-1 428 690 discloses a projectile featuring an asymmetric tip, such that when the projectile hits a target it creates forces which hasten the deviation of the projectile.
  • the asymmetric tip of the projectile disclosed in DE-A-1 428 690 accelerates the inclination of the projectile upon impacting a target.
  • US-A-4,085,678 to Heincker teaches a projectile equipped with a warhead having a forward section and an aft section.
  • the forward section has an asymmetric rear end, whereas the aft section has an asymmetric front end, such that these rear and front ends match one another.
  • the forward section is used to penetrate a target, whereas the aft section include the explosive and is intended to follow the forward section into the target.
  • US-A-4,554,871 to Nixon discloses a missile carrying at least two submunitions each having one asymmetric end. When the missile reaches a predetermined point in its trajectory, the submunitions are dispensed in a manner which causes the submunitions to acquire different flight paths.
  • a penetration warhead in combination with a missile having defined up and down portions, said missile being position-controlled to ensure that the missile flies with the top portion oriented up and the down portion facing down and said missile being roll-stabilized to keep the angular position of the missile about its axis roughly constant, said warhead having a main axis and comprising a nose section which is asymmetric with respect to said main axis of the warhead, said asymmetry is being selected so that upon impacting a target, at an angle which deviates from a perpendicular to a surface of said target (22), the forces acting on said nose section by said target create a moment about a warhead's center of gravity which directs the penetration warhead in a direction which is substantially toward the perpendicular to the surface of the target, thereby increasing the warhead's penetration depth into the target.
  • the present invention successfully addresses the shortcomings of the presently known configurations by providing a penetration warhead or projectile which is shaped to include a nose section which is asymmetric with respect to its longitudinal axis.
  • the warhead is in combination with a roll-stabilized, position-controlled, guided missile which is designed to penetrate a hardened concrete target or other highly resistant targets.
  • Roll-stabilization relates to the keeping of the angular position of the missile about its axis roughly constant.
  • Position control relates to ensuring that the missile is oriented so that the top portion is pointing up while the bottom portion is pointing down, i.e. to prevent the missile from flying with the wrong roll angle.
  • the present invention is of a penetration warhead assembled in a roll-stabilized or non-rolling guided missile or smart bomb (herein referred to collectively or singularly as "missile") body having a construction which significantly improves the penetration of the warhead into a target which is impacted at an angle which differs from the perpendicular.
  • missile roll-stabilized or non-rolling guided missile or smart bomb
  • FIG. 1 Shown in Figure 1, is a schematic side cross-sectional view of a missile 10 which includes a guidance section 12 , a warhead 14 (which is described in greater detail below), with an explosive charge 15 , an engine section 16 and a flight control section 18 and tail fins 20 .
  • Missile 10 is shown just prior to impact with a target 22 , at a certain angle, ⁇ , between the plane of the target and the main (longitudinal) axis of missile 10 .
  • various warheads, bombs and projectiles are used for penetrating armored vehicles, such as tanks and thick concrete or similar other hard or hardened targets, typically made of concrete and further protected by layers of rock, soil and/or steel.
  • warheads are symmetrical so that the performance of the missile is independent of its roll angle at the moment of impact between the missile and the target.
  • the symmetry of the warhead is critical in missiles, bombs, and the like, which roll during flight so that it is not possible to predict the roll angle of the missile at the instant of impact.
  • the nose of a conventional warhead has either an ogival or a conical front section ( Figures 2 and 3, respectively), both configurations being completely symmetrical with respect to the main axis of the warhead.
  • a penetration warhead is to penetrate as deeply as possible into the target in order to place the explosives in the targeted space, or as close to it as possible.
  • the extent of penetration of the warhead is greatly affected by the angle of impact, i.e., the angle between the main axis of the missile or warhead and the plane of the target.
  • the warhead penetrates the target but tends to form a J-shaped path ( Figures 5).
  • the diversion of the warhead from a straight line path is causes by an imbalance of forces on the nose of the warhead, as shown schematically in Figure 8 which induces a moment tending to rotate the warhead about its center of gravity in a direction away from the target.
  • the warhead comes to a stop with its nose pointing somewhat away from the target ( Figure 2).
  • the J-shaped path implies a decreased penetration of the warhead into the target.
  • the present invention relates to a kinetic energy penetrating warhead which is designed to at least partly mitigate the negative effects of an angled impact of a hardened target.
  • a warhead according to the present invention includes, in sharp contrast with known warheads, a front section, or nose, which is asymmetric with respect to the main axis of the warhead.
  • a warhead according to the present invention is intended for use with guided missiles, projectile or smart bombs which do not roll, or are roll-stabilized, position-controlled and which are designed to penetrate hard and high value targets. In such systems, the missile or bomb has defined up and down portions and impact takes place substantially with the lower portion of the system ( Figure 9).
  • the asymmetric configuration of the warhead makes it possible for the warhead to dig into the target by allowing the target counter forces to act on the warhead so as to counter and correct the tendency of the warhead to take a J-shaped path, as shown in Figures 8, 5 and 6.
  • the forces acting on the nose of the warhead thus tend to create a moment about the warhead's center of gravity which tends to direct the penetrating warhead in a direction which is substantially toward the perpendicular, thereby increasing the warhead's penetration depth.
  • FIGS 11 and 12 Shown in Figures 11 and 12 are a side and a front view of a nose design which includes a planar surface.
  • the planar surface takes on the shape of an ellipse.
  • the nose section is in the shape of an oblique cone, i.e., a cone which is asymmetric with respect to its base or, more importantly with respect to the main axis of the warhead whereas the cone tip can be at any designed distance from the warhead main axis.
  • FIG. 15 and 16 Shown in Figures 15 and 16 is a nose section which is asymmetrically concave while the nose section in the embodiments of Figures 17 and 18 are asymmetrically convex.
  • Figures 19 and 20 and in Figures 21 and 22 are two more configurations which are asymmetrically concave and convex.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Inorganic Compounds Of Heavy Metals (AREA)
  • Inorganic Insulating Materials (AREA)
  • Ceramic Products (AREA)
  • Fluid-Damping Devices (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (5)

  1. Penetratorgeschoß (14) in Kombination mit einer Rakete (10) mit definierten oberen und unteren Teilen, wobei die Rakete (10) positionsgesteuert ist, um sicherzustellen, daß die Rakete mit aufwärts gerichtetem oberen Teil und nach unten gerichtetem unteren Teil fliegt, und wobei die Rakete (10) rollstabilisiert ist, um die Winkelposition der Rakete um deren Achse im wesentlichen konstant zu halten, wobei das Geschoß (14) eine Hauptachse und einen Nasenabschnitt aufweist, der bezüglich der Hauptachse des Geschosses (14) asymmetrisch ist, wobei die Asymmetrie derart gewählt ist, daß beim Auftreffen auf ein Ziel (22) unter einem Winkel, der von einer Senkrechten auf eine Fläche des Ziels (22) abweicht, die auf den Nasenabschnitt von dem Ziel ausgeübten Kräfte ein Moment um den Schwerpunkt des Geschosses (14) erzeugen, welches das Penetratorgeschoß (14) in eine Richtung leitet, die im wesentlichen in Richtung der Senkrechten auf die Fläche des Ziels verläuft, wodurch die Eindringtiefe des Geschosses (14) in das Ziel (22) vergrößert wird.
  2. Kombination nach Anspruch 1, bei der der Nasenabschnitt an seinem vorderen Ende eine planare Ausbildung aufweist.
  3. Kombination nach Anspruch 1, bei der der Nasenabschnitt an seinem vorderen Ende eine schräge konische Ausbildung aufweist.
  4. Kombination nach Anspruch 1, bei der der Nasenabschnitt an seinem vorderen Ende eine konvexe Ausbildung aufweist.
  5. Kombination nach Anspruch 1, bei der der Nasenabschnitt an seinem vorderen Ende eine konkave Ausbildung aufweist.
EP96630047A 1995-08-17 1996-08-14 Asymmetrisches Penetratorgeschoss Expired - Lifetime EP0760458B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IL11497395A IL114973A (en) 1995-08-17 1995-08-17 Asymmetric penetration warhead
IL11497395 1995-08-17

Publications (2)

Publication Number Publication Date
EP0760458A1 EP0760458A1 (de) 1997-03-05
EP0760458B1 true EP0760458B1 (de) 2000-12-20

Family

ID=11067888

Family Applications (2)

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EP96630047A Expired - Lifetime EP0760458B1 (de) 1995-08-17 1996-08-14 Asymmetrisches Penetratorgeschoss
EP96927859A Expired - Lifetime EP0845098B1 (de) 1995-08-17 1996-08-16 Asymmetrisches penetratorgeschoss

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP96927859A Expired - Lifetime EP0845098B1 (de) 1995-08-17 1996-08-16 Asymmetrisches penetratorgeschoss

Country Status (8)

Country Link
EP (2) EP0760458B1 (de)
AT (1) ATE199978T1 (de)
AU (1) AU6753796A (de)
BR (1) BR9610411A (de)
DE (1) DE69611273T2 (de)
ES (1) ES2155196T3 (de)
IL (1) IL114973A (de)
WO (1) WO1997007379A2 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU2003212584A1 (en) * 2003-03-25 2004-10-18 Ruag Munition Projectile comprising a sub-caliber penetrator core
RU2503921C2 (ru) * 2012-03-15 2014-01-10 Шепеленко Виталий Борисович Реактивный снаряд
IL219010A (en) 2012-04-03 2016-11-30 Amon Jacob Warhead
CN103389014B (zh) * 2013-06-25 2015-04-08 西安电子科技大学 靶场钻地弹爆炸位置定位系统和方法
CN109029158A (zh) * 2018-08-30 2018-12-18 南京理工大学 一种基于弹头不对称性的可控防爆弹

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US603466A (en) * 1898-05-03 Projectile

Family Cites Families (17)

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Publication number Priority date Publication date Assignee Title
GB539699A (en) * 1939-12-08 1941-09-22 Christopher William Kent Improvements in and relating to aerial bombs
US2464834A (en) * 1945-03-16 1949-03-22 Lawrence H Taylor Method and apparatus for determining depth and current direction
US2612108A (en) * 1948-08-11 1952-09-30 Benjamin F Schmidt Projectile
DE1428690A1 (de) * 1964-08-04 1969-01-16 Inst Nac De Ind Gewehrgeschoss
US3282214A (en) * 1964-12-14 1966-11-01 Madison H Briscoe Projectile
US3401637A (en) * 1966-09-28 1968-09-17 Madison H. Briscoe Broadside bullet
DE2222785A1 (de) * 1972-05-10 1973-11-22 Messerschmitt Boelkow Blohm Infanteriegeschoss zur bekaempfung von erdzielen
ES199626Y (es) * 1974-01-19 1975-12-16 Centro De Est. Tec De Mate. Esp. - Inst. Nac. Ind. Proyectil de pequeno calibre con punta asimetrica.
DE2457503C2 (de) * 1974-12-05 1984-11-29 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Infanteriegeschoß
US4389028A (en) * 1976-01-14 1983-06-21 The United States Of America As Represented By The Secretary Of The Navy Flat trajectory projectile
US4085678A (en) * 1977-04-25 1978-04-25 The United States Of America As Represented By The Secretary Of The Air Force Kinetic energy, impact-separated, follow-through ungula penetrator
US4637313A (en) * 1981-01-05 1987-01-20 Avco Corporation Earth penetrator
DE3267517D1 (en) * 1981-04-08 1986-01-02 Commw Of Australia Directional control device for airborne or seaborne missiles
US4554871A (en) * 1983-11-21 1985-11-26 Allied Corporation Dispensed guided submunition
US4998994A (en) * 1989-09-20 1991-03-12 The United States Of America As Represented By The Secretary Of The Army Aerodynamically compliant projectile nose
FR2673277B1 (fr) * 1991-02-26 1995-01-13 Giat Ind Sa Structure de tete pour projectile a caractere perforant.
DE4142116A1 (de) * 1991-12-20 1993-06-24 Weber Adolf Dipl Ing Uebungspfeilgeschoss mit reduzierter reichweite

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US603466A (en) * 1898-05-03 Projectile

Also Published As

Publication number Publication date
AU6753796A (en) 1997-03-12
EP0845098A2 (de) 1998-06-03
DE69611273D1 (de) 2001-01-25
IL114973A0 (en) 1996-06-18
EP0845098B1 (de) 2001-03-21
IL114973A (en) 2000-07-26
EP0760458A1 (de) 1997-03-05
BR9610411A (pt) 1999-12-21
ES2155196T3 (es) 2001-05-01
DE69611273T2 (de) 2001-08-09
WO1997007379A3 (en) 1997-05-22
EP0845098A4 (de) 1999-04-07
WO1997007379A2 (en) 1997-02-27
ATE199978T1 (de) 2001-04-15

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