EP0740124B1 - Markierungsanordnung für von Flagkörper zerstörte Ziele - Google Patents

Markierungsanordnung für von Flagkörper zerstörte Ziele Download PDF

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Publication number
EP0740124B1
EP0740124B1 EP19950201049 EP95201049A EP0740124B1 EP 0740124 B1 EP0740124 B1 EP 0740124B1 EP 19950201049 EP19950201049 EP 19950201049 EP 95201049 A EP95201049 A EP 95201049A EP 0740124 B1 EP0740124 B1 EP 0740124B1
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EP
European Patent Office
Prior art keywords
missile
target
housing
warhead
impact
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
EP19950201049
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English (en)
French (fr)
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EP0740124A1 (de
Inventor
Lynn Boyer
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Individual
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Individual
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Priority to DE1995619282 priority Critical patent/DE69519282T2/de
Priority to EP19950201049 priority patent/EP0740124B1/de
Priority to ES95201049T priority patent/ES2153452T3/es
Publication of EP0740124A1 publication Critical patent/EP0740124A1/de
Application granted granted Critical
Publication of EP0740124B1 publication Critical patent/EP0740124B1/de
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    • 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
    • F42B12/40—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 of target-marking, i.e. impact-indicating type

Definitions

  • This invention generally relates to marker devices incorporated in a missile having a warhead for impacting a target.
  • the marker is released on the target responsive to impact of the warhead with a target. More particularly the invention relates to such a missile which is used in the destruction of armored vehicles or the like.
  • the invention relates to a semi-permanent identification medium and a dispensing mechanism being placed in/on or made an integral part of precision, guided, integrally propelled or freefall and direct fire anti-armor munitions, such that upon the munitions impacting and thus "killing/destroying" an enemy vehicle, the semi-permanent, identification medium is applied to the vehicle. Because of the applied identification material, the "killed/destroyed" threat armored vehicle is able to be quickly and easily recognized by engaged and succeeding combat crews as being “killed/destroyed” and thus no longer a threat and that no further munitions need be expended at the "destroyed target”.
  • Anti-armor warfare has evolved from the practice of defeating enemy armor by massed fire or bombing, to one, while not excluding massed fire and bombing, of using precision munitions to destroy individual vehicles, frequently at distances previously not practical.
  • Wide ranging attack helicopters, fixed wing aircraft carrying smart anti-armor munitions, artillery firing smart munitions and friendly armored thrusts have combined to give modern battlefields breadth and depth, unimaginable but a few years ago.
  • PK The high probability of kill (PK) combined with the continuing evolution of anti-armor munitions into smaller and smaller weapons has made light forces (attack helicopters, wheeled vehicles - such as anti-armor missile carrying jeeps and light trucks) and even individual infantry men so armed, into potent anti-armor forces.
  • the invention will provide gunner's, including the original, both during an immediate engagement and in succeeding encounters, with specific means of identifying which enemy vehicles have been "hit” as opposed to those which are still active threats. This ability will improve friendly gunner situational awareness, active threat identification (i.e. those not displaying identification material and more probably still capable of hostile actions), combat efficiency/effectiveness and reduce friendly casualties.
  • U.S. Patent Number 5,009,164 issued April 23, 1991 is directed to a non-penetrating projectile which stains a target upon impact.
  • the projectile is provided with means for changing its shape on impact to reduce the danger of penetration into a target such as a human.
  • the device is used to disperse a crowd and to mark the individuals of the crowd as an aid in subsequent identification of involved persons.
  • None of the above patents disclose a missile having the combination of an active warhead and target identification means carried by the missile to a target so that upon impact of the warhead with the target, the target is "killed” (although it may not be totally visibly destroyed) and marked by the identification means to instantaneously and thereafter provide a means of identifying the "killed" target.
  • an object of the present invention to provide a means for identification of a target responsive to impact therewith by a warhead of a missile.
  • warhead refers to that portion of the missile which impacts with the target to "kill” the target.
  • the "warhead” may be an armor piercing warhead which penetrates the target to damage internal components of the target and thus effectively “kill” the target.
  • the warhead may contain an explosive which, upon impact, effectively “kills” the target.
  • Figures 1, 4 and 5 illustrate a typical wire guided anti-armor missile 4 utilizing the target marking principles of the present invention
  • Figures 2, 6 and 7 illustrate a typical radar/millimeter wave/laser/optically guided anti-armor missile 6 utilizing the target marking principles of the present invention
  • Figure 10 illustrates a missile 8 as being a shot projectile
  • Figure 11 illustrates the shot projectile 8 of Figure 10 as having a trailing body in the form of a free flying shell or ballute attached to the missile.
  • Figure 12 illustrates a missile 10 as being a flechette or dart
  • Figure 13 illustrates the flechette 10 of Figure 12 as having a trailing body in the form of a free flying shell or ballute attached thereto.
  • Each of the missiles respectively illustrated in Figures 4, 7, 10 and 17 are provided with a reservoir 12 mounted in the missile body 14 and having a powdered, jelled, solid or liquid marking (identification) material 16 carried therein ( Figures 14-19).
  • Each of the missiles shown in Figures 1, 2, 5, and 6 has the marker material carried in containers which are secured to the shell of the missile body.
  • Figures 18 and 19 illustrate the marker material as being carried in a trailing body which is carried with the missile to the target.
  • the target marking material "marks" the target subsequent to rupturing of the skin of the reservoir or container responsive to impact of the missile with the target.
  • reservoir 12 includes a housing 18 comprised of forward and aft bulkheads 20 and 22 respectively, which are connected by an annular side body member 24. Housing 18 encloses the identification material 16. Annular side member 24 is shown to include an ejection port 26 adjacent the aft end 22 thereof which is closed off by a soft sealing member 28 which forms an ejection soft plug. Member 28 may be a single annular member which extends around the periphery of body member 24, or if desired, may be plurality of peripherally spaced soft plug members.
  • An initiator 30 may be provided in or adjacent the forward end 20 of the reservoir to rupture the reservoir and release the identification material. The initiator may be electrically, mechanically or explosively actuated. Such initiators are well known in the art.
  • FIG 15 illustrates another embodiment of the reservoir which is identified by the numeral 35.
  • Reservoir 35 contains the identification material 16 and is provided with ejection ports 36 similar to those of Figure 14.
  • the ejection ports are positioned adjacent the forward end 32 and the initiator 30 is shown positioned on the aft end 27 of the reservoir but may be a separate member mounted adjacent the reservoir, if desired. It is to be understood that reservoir 35 may be used in place of reservoir 12, if desired.
  • wire guided missile 4 is shown to include serially arranged sections or compartments identified as seeker 40, electronics 42, warhead 44, computer 46, guidance 48, motor 50 and motor nozzle 52.
  • First and second identification material reservoirs 12 are respectively shown mounted between the warhead section 44 and computer section 46 and between the computer section 46 and guidance section 48.
  • a third reservoir 12 is shown mounted between guidance section 48 and motor section 50.
  • a plurality of reservoirs 12 are serially positioned along the length of the body 14 of the missile in similar manner as discussed, supra, relating to Figure 4.
  • the radar/millimeter wave/laser/optically guided anti-armor missile 6 is shown to include a seeker and electronics section 45, a warhead section 47, a computer section 49, a guidance section 51, a motor section 53 and a motor nozzle 55.
  • a first reservoir 12 is shown to be positioned between the warhead and computer sections 47 and 49.
  • a second reservoir 12 is shown to be positioned between the computer and guidance sections 49 and 51.
  • a third reservoir 12 is shown to be positioned in the missile body between guidance section 51 and motor section 53.
  • a fourth reservoir 12 is shown to be positioned at the motor nozzle section 55 adjacent the motor nozzle.
  • Figures 8a and 8b are pictorial and side elevational views, respectively, of the reservoirs used in Figures 4 and 7.
  • Figures 8a and 8b further illustrate an embodiment of the invention wherein an annular frangible member 15 is disposed around the periphery of the reservoirs 12.
  • the frangible member is disposed for rupturing responsive to impact to eject the marker material onto the destroyed target.
  • Figure 10 illustrates the missile 8 as a solid shot having a forward portion 54 and an aft portion 56.
  • a reservoir 34 is shown to be mounted at the aft portion 56 of the missile 8.
  • Figure 11 is an elevational view of the missile 8 of Figure 10 with a trailing body 58 connected thereto.
  • the trailing body 58 is in the form of a free flying shell or ballute and contains the marker material 16 as shown in Figure 18.
  • Figure 18 illustrates in cross-section, the trailing of free flying shell or ballute 58 of Figure 11.
  • the trailing body 58 (free flying shell or ballute) includes a housing 59 having the forward portion 60 thereof disposed for attachment to the solid shot 8.
  • Shell or ballute 58 further includes a central section 62 and an aft section 64. The identification material is completely enclosed by forward, central and aft sections of the housing 59.
  • FIG 17 illustrates the flechette or dart of Figures 12 and 13 in cross-section.
  • An elongated reservoir 66 is shown to be carried in the aft end 68 of the flechette.
  • the reservoir 66 includes a forward portion having blow-out plugs 70 (as discussed in conjunction with the discussion of Figures 14 and 15) mounted therein.
  • the blowout plugs form a part of the outer shell of the flechette.
  • Figure 19 illustrates the trailing or free flying dart or ballute of Figure 13 in cross-section.
  • the body 71 of the device completely encloses the identification material and is shown to include a forward portion 72 for attachment to the dart missile 10.
  • Body 71 includes an aft portion 74 having stabilizing fins 76 thereon.
  • FIG 16 is a cross-sectional view of a container in the form of a strake 78 as used in the missile of Figures 1 and 2.
  • the strake is shown to be comprised of a body 79 having forward, intermediate and end portions 80, 82 and 84, respectively.
  • the strake is shown to have a reservoir 86 enclosed by upper, lower, forward and rear end enclosures 88, 90, 92 and 94.
  • Lower enclosure 90 may be the outer surface of the skin of the missile or may be a separate member which is attached to the missile body.
  • the forward section 80 of the strake is provided with an ejection port 96 therein. Port 96 is enclosed by a skin or plug 98 which is softer than the material of which the strake is comprised.
  • An initiator 100 may be provided, if desired, at the aft end 84 nestled between the juncture of lower and upper surfaces 88 and 90, respectively.
  • the initiator may be electrically, mechanically, or explosively actuated. Such initiators are well known in the art.
  • the strakes are better illustrated in Figures 3a, 3b and 3c.
  • a plurality of strakes 78 may be positioned on the missile as shown in Figures 1 and 2 which illustrate the strakes 78 as being mounted on the body of the missile and positioned between adjacent pair of the four stabilizing fins of the missiles.
  • FIGs 5 and 6 illustrate the use of packet/conformal containers 102 for carrying the marker material on the missiles 4 and 6.
  • the packet/conformal containers are arranged in two serially arranged pairs with the pairs being positioned 180° apart on the missile body.
  • the containers are aerodynamically configured so as to provide minimum drag on the missile.
  • each container 102 includes a substantially flat upper surface 104 and curved sides 106 and 108. Sides 106 and 108 curve outwardly and downwardly to mate with a base portion 110.
  • a forward portion 112 is provided which slopes outwardly and downwardly to mate with base portion 110.
  • a rear portion 114 is provided which slopes outwardly and rearwardly to mate with base portion 116.
  • the marker material 16 is carried in the interior of the containers.
  • the packet/conformal container is a container which is provided with a configuration which conforms to the general shape of the missile body but may or may not have outside aerodynamic surfaces.
  • the strakes, as used in the present invention, however, are aerodynamically configured elongated members.
  • the invention consists of the application of an identification medium as part of the destruction process due to precision, guided, self-propelled or free fall and direct fire, anti-armor munitions.
  • the specific identification medium will be weapons systems dependent, i.e. it must be compatible with the particular system it is part of. Considerations for the identification medium will include type of medium to be dispensed, aerodynamics of the weapon, center of gravity considerations, weapon speed, impact angle and velocity, location of placement in or on the round, size of reservoir, number and type of reservoirs or containers, physical properties of the identification material, quantity of the identification material, and environment due to weapons impact.
  • the identification medium will provide immediate and obvious indication that the armored vehicle has been "killed/destroyed" by any of several means or combinations thereof.

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  • 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)
  • Guiding Agricultural Machines (AREA)

Claims (9)

  1. Gerät, um ein Ziel im wesentlichen zu zerstören und um das Ziel im wesentlichen gleichzeitig mit dem Akt der Zerstörung zu markieren, um augenfällig zu machen, daß das Ziel nicht länger aktiv und eine Bedrohung ist, wobei das Gerät umfaßt:
    einen Flugkörper mit einem Gefechtskopf, um das Ziel im wesentlichen zu zerstören;
    zumindest ein vom Flugkörper (4, 6, 8, 10) mitgeführtes Gehäuse (18), wobei das Gehäuse separat und verschieden vom Gefechtskopf (44) ist;
    ein Zielmarkierungsmittel, das im Gehäuse (18) mitgeführt wird und eingerichtet ist, beim Zusammentreffen des Gefechtskopfes (44) mit dem Ziel an diesem anzuhaften, wobei das Zielmarkierungsmittel ein semi-permanentes Markierungsmaterial (16) umfaßt, das eine Anzeige dafür ergibt, daß das Ziel durch den Gefechtskopf (44) im wesentlichen zerstört wurde und daß kein weiterer Angriff auf das Ziel mit zusätzlichem Kampfmaterial nötig ist.
  2. Gerät nach Anspruch 1, wobei das Gehäuse (18) eine zylindrische Gestalt besitzt, die durch im wesentlichen parallele Vorder- und Rückseiten und eine dazwischenliegende, verbindende, ringförmige Wand definiert ist, und wobei ein zerbrechbares Verschlußmittel (28) in der ringförmigen Wand angeordnet ist, um bei Zusammentreffen des Gefechtskopfes (44) mit dem Ziel zu zerreißen, wobei das zerbrechbare Verschlußmittel (28) vorzugsweise ein ringförmiges Element umfaßt, das entlang der Außenfläche des ringförmigen Abschnitts des Gehäuses (18) angeordnet ist, und wobei vorzugsweise eine Mehrzahl solcher Gehäuse (18) entlang der Länge des Flugkörpers (4, 6, 8, 10) mit Abstand hintereinander angeordnet sind.
  3. Gerät nach Anspruch 2, ferner umfassend Zündmittel (30) zum Zerreißen des Gehäuses beim Zusammentreffen des Gefechtskopfes (44) mit dem Ziel.
  4. Gerät nach einem der vorherigen Ansprüche, wobei das Gehäuse (18) durch eine Mehrzahl von Planken (78) begrenzt wird, die außen auf einem Körper des Flugkörpers (4) angeordnet sind, wobei die Planken (78) aerodynamisch gestaltete Oberflächen aufweisen und jeweils mit Abstand zueinander entlang der Außenfläche des Flugkörpers (4) angeordnet sind und eine Kammer (86) in ihrem Inneren einschließen, und wobei das Markierungsmaterial (16) in der Kammer jeder Planke (78) mitgeführt wird.
  5. Gerät nach einem der vorherigen Ansprüche, wobei das Gehäuse durch zumindest einen Paket-/angepaßten Behälter (102) begrenzt wird, umfassend
    eine Unterseite, die mit dem Körper des Flugkörpers zusammenpaßt (abschließt),
    eine Oberseite mit einer im wesentlichen ebenen Mittelfläche (104), und
    ein Paar gekrümmter Seitenflächen (106, 108), die sich von der oberen ebenen Fläche (104) zum Abschließen mit der Unterseite (110) abwärts erstrecken, und
    ein Paar voneinander getrennter Kopfseiten (112, 114), die abwärts und nach außen geneigt sind zur Verbindung (zum Abschließen) mit der Unterseite (110),
    wobei die Oberseite (104), die Seitenflächen (106, 108), die Kopfseiten (112, 114) und die Unterseite (110) eine Kammer mit dem Zielmarkierungsmaterial (16) einschließen.
  6. Gerät nach einem der vorherigen Ansprüche, wobei das Gehäuse durch eine Mehrzahl von Paket-/angepaßten Behältern (102) begrenzt ist, wobei die Behälter paarweise hintereinander auf dem Flugkörper (4, 6, 8, 10) angebracht sind, wobei jedes Paar einen ersten, vorderen Behälter und einen zweiten, hinteren Behälter umfaßt, und wobei die Paare in im wesentlichen gleichen Abständen entlang der Außenfläche des Körpers des Flugkörpers angeordnet sind.
  7. Gerät nach Anspruch 1, umfassend einen Schleppkörper (58), der an einer Flechette (10) befestigt ist, wobei der Schleppkörper (58) das Markierungsmaterial in seinem Inneren besitzt.
  8. Gerät nach einem der vorherigen Ansprüche, wobei der Flugkörper ein freifliegendes Projektil ist.
  9. Gerät nach einem der vorherigen Ansprüche, wobei der Flugkörper ein drahtgelenkter panzerbrechender Flugkörper ist, oder wobei der Flugkörper ein radar-/millimeterwellen-/laser-/optisch gelenkter Flugkörper ist.
EP19950201049 1995-04-25 1995-04-25 Markierungsanordnung für von Flagkörper zerstörte Ziele Expired - Lifetime EP0740124B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE1995619282 DE69519282T2 (de) 1995-04-25 1995-04-25 Markierungsanordnung für von Flagkörper zerstörte Ziele
EP19950201049 EP0740124B1 (de) 1995-04-25 1995-04-25 Markierungsanordnung für von Flagkörper zerstörte Ziele
ES95201049T ES2153452T3 (es) 1995-04-25 1995-04-25 Formas de señalizacion de objetos destruidos por misiles.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19950201049 EP0740124B1 (de) 1995-04-25 1995-04-25 Markierungsanordnung für von Flagkörper zerstörte Ziele

Publications (2)

Publication Number Publication Date
EP0740124A1 EP0740124A1 (de) 1996-10-30
EP0740124B1 true EP0740124B1 (de) 2000-11-02

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EP19950201049 Expired - Lifetime EP0740124B1 (de) 1995-04-25 1995-04-25 Markierungsanordnung für von Flagkörper zerstörte Ziele

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DE (1) DE69519282T2 (de)
ES (1) ES2153452T3 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110695948A (zh) * 2019-08-30 2020-01-17 江西洪都航空工业集团有限责任公司 一种适应自动挂载的导弹标记方法
CN113551565B (zh) * 2021-09-18 2021-11-30 中国科学院力学研究所 一种级间段气动保形的固体火箭及分离方法

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3150875A (en) * 1962-11-08 1964-09-29 Searles Signals Co Self-locating arrow having breakable container means containing artificial smoke producing chemicals
US3712228A (en) * 1969-02-26 1973-01-23 Us Navy Target marker warhead
FR2057590A5 (en) * 1969-08-29 1971-05-21 France Etat Disintegratable tracer practice shell for - armoured vehicles
FR2473699A1 (fr) * 1980-01-15 1981-07-17 Alsetex Armement Etud Perfectionnements apportes aux bombes marqueuses et aux bombes d'exercice
US4326463A (en) * 1980-05-27 1982-04-27 The United States Of America As Represented By The Secretary Of The Army Dye marker assembly for rocket practice round

Also Published As

Publication number Publication date
ES2153452T3 (es) 2001-03-01
DE69519282T2 (de) 2001-06-07
DE69519282D1 (de) 2000-12-07
EP0740124A1 (de) 1996-10-30

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