EP0201433B1 - Armour-perforating projectile - Google Patents

Armour-perforating projectile Download PDF

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Publication number
EP0201433B1
EP0201433B1 EP19860400993 EP86400993A EP0201433B1 EP 0201433 B1 EP0201433 B1 EP 0201433B1 EP 19860400993 EP19860400993 EP 19860400993 EP 86400993 A EP86400993 A EP 86400993A EP 0201433 B1 EP0201433 B1 EP 0201433B1
Authority
EP
European Patent Office
Prior art keywords
charge
projectile
unit
leading
shaped
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
Application number
EP19860400993
Other languages
German (de)
French (fr)
Other versions
EP0201433A1 (en
Inventor
Alain Kerdraon
Gérard Solve
Hervé Rodriguez
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.)
Cessione giat Industries
Original Assignee
Direction General pour lArmement DGA
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Filing date
Publication date
Application filed by Direction General pour lArmement DGA filed Critical Direction General pour lArmement DGA
Publication of EP0201433A1 publication Critical patent/EP0201433A1/en
Application granted granted Critical
Publication of EP0201433B1 publication Critical patent/EP0201433B1/en
Expired 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
    • F42B12/10—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 shaped or hollow charge
    • F42B12/16—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 shaped or hollow charge in combination with an additional projectile or charge, acting successively on the target
    • F42B12/18—Hollow charges in tandem arrangement

Definitions

  • the present invention relates to a projectile intended for the aggression of armored and in particular active targets.
  • the patent FR-A-1 455 403 describes a self-propelled projectile, with a single hollow charge, the propellant of which is located in front of the charge. This patent is silent on the possible interposition of a propellant between two charges mounted in tandem and operating in sequence.
  • Patent FR-A-2 519 752 describes a self-propelled projectile with a single charge, operating over the objective. Means are provided on the one hand for separating the propellant from the military load, the propellant being imperatively at the rear of this load, and on the other hand for causing the subsequent tilting of the load. This patent therefore has nothing to do with projectiles comprising two charges mounted in tandem.
  • the present invention relates to a projectile and more particularly to a military head organization which makes it possible to reconcile favorably the gain in efficiency brought by the mounting of the shaped charges mounted in tandem with the functional requirements of a military head of anti-tank projectile such as a rocket or missile.
  • the subject of the invention is therefore a projectile intended for the aggression of armored and in particular active targets, consisting on the one hand of a military head comprising a front formed charge and a rear formed charge mounted in tandem and operating in sequence and d on the other hand of a propellant, characterized in that it comprises a protective screen constituted by the propellant itself, placed between the two charges, which is provided with an axial recess allowing the jet of the charge formed to pass back.
  • a deformable structure can be interposed between the propellant and the rear shaped charge.
  • the charge formed before and the propellant can be integrated into a rigid structure.
  • the connecting structure 12 between the propellant and the rear load is designed so that the effects of the shock induced by the detonation of the front load on the rear load remain negligible. To do this, this structure is deformable so as to absorb the energy developed by the front load.
  • the assembly constituted by the front load and the propellant is designed so as to form a rigid assembly transmitting almost entirely the detonation forces of the front load towards the connection structure 12.
  • the electronic processing unit 8 by virtue of its location, participates in the intercharge protection.

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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)

Description

La présente invention concerne un projectile destiné à l'agression de cibles blindées et notamment actives.The present invention relates to a projectile intended for the aggression of armored and in particular active targets.

L'évolution de la protection des véhicules blindés a conduit à une évolution parallèle des projectiles militaires antichar. Une des solutions retenue est le concept de charges creuses montées en tandem. Parmi les premières associations envisagées, on peut noter celle décrite dans le brevet FR-A-2 310 547.The evolution of the protection of armored vehicles has led to a parallel evolution of military anti-tank projectiles. One of the solutions chosen is the concept of tandem-mounted hollow loads. Among the first associations envisaged, one can note that described in patent FR-A-2,310,547.

L'organisation des têtes militaires existantes se prête mal au montage de deux charges explosives détonant en séquence car:

  • - le propulseur est généralement placé derrière la charge principale et la présence d'une charge avant auxiliaire ainsi que l'espace intercharge associé détruisent l'équilibre aérodynamique de la munition,
  • - la charge avant nécessite une protection ou bouclier intercharge, masse inerte qui pénalise le' devis masse de l'ensemble,
  • - le montage d'une charge avant s'accommode mal de la présence de moyens de détection et de mise a feu généralement placés dans l'axe de la charge.
The organization of existing military warheads does not lend itself to mounting two detonating explosive charges in sequence because:
  • - the thruster is generally placed behind the main load and the presence of an auxiliary front load as well as the associated intercharge space destroy the aerodynamic balance of the ammunition,
  • - the front load requires an intercharge protection or shield, inert mass which penalizes the 'mass estimate of the assembly,
  • - The mounting of a front load is ill suited to the presence of detection and ignition means generally placed in the axis of the load.

Les brevets US-A-2 804 823 et DE-A-2 829 002 décrivent un projectile autopropulsé selon le préambule de la revendication 1 et comportant deux charges montées en tandem. Toutefois, le propulseur est toujours placé à l'arrière de la charge arrière et on provoque au voisinage de la cible un éloigenement de ces deux charges afin de protéger la charge arrière.The patents US-A-2 804 823 and DE-A-2 829 002 describe a self-propelled projectile according to the preamble of claim 1 and comprising two charges mounted in tandem. However, the propellant is still placed at the rear of the rear load and in the vicinity of the target is caused a separation of these two loads in order to protect the rear load.

Le brevet FR-A-1 455 403 décrit un projectile autopropulsé, a charge creuse unique, dont le propulseur est situé en avant de la charge. Ce brevet est muet sur l'éventuelle interposition d'un propulseur entre deux charges montées en tandem et fonctionnant en séquence.The patent FR-A-1 455 403 describes a self-propelled projectile, with a single hollow charge, the propellant of which is located in front of the charge. This patent is silent on the possible interposition of a propellant between two charges mounted in tandem and operating in sequence.

Le brevet FR-A-2 519 752 décrit un projectile autopropulsé a charge unique, fonctionnement en survol de l'objectif. Des moyens sont prévus d'une part pour séparer le propulseur de la charge militaire, le propulseur étant impérativement à l'arrière de cette charge, et d'autre part pour provoquer le basculement ultérieur de la charge. Ce brevet n'a donc rien à voir avec les projectiles comprenant deux charges montées en tandem.Patent FR-A-2 519 752 describes a self-propelled projectile with a single charge, operating over the objective. Means are provided on the one hand for separating the propellant from the military load, the propellant being imperatively at the rear of this load, and on the other hand for causing the subsequent tilting of the load. This patent therefore has nothing to do with projectiles comprising two charges mounted in tandem.

La présente invention concerne un projectile et plus particulièrement une organisation de tête militaire qui permet de concilier favorablement le gain d'efficacité apporté par le montage des charges formées montées en tandem avec les exigences fonctionnelles d'une tête militaire de projectile antichar tel qu'une roquette ou un missile.The present invention relates to a projectile and more particularly to a military head organization which makes it possible to reconcile favorably the gain in efficiency brought by the mounting of the shaped charges mounted in tandem with the functional requirements of a military head of anti-tank projectile such as a rocket or missile.

L'invention a donc pour objet un projectile destiné à l'agression de cibles blindées et notamment actives, constitué d'une part d'une tête militaire comprenant une charge formée avant et une charge formée arrière montées en tandem et fonctionnant en séquence et d'autre part d'un propulseur, caractérisé en ce qu'il comporte un écran de protection constitué par le propulseur lui-même, placé entre les deux charges, lequel est muni d'un évidement axial permettant le passage du jet de la charge formée arrière.The subject of the invention is therefore a projectile intended for the aggression of armored and in particular active targets, consisting on the one hand of a military head comprising a front formed charge and a rear formed charge mounted in tandem and operating in sequence and d on the other hand of a propellant, characterized in that it comprises a protective screen constituted by the propellant itself, placed between the two charges, which is provided with an axial recess allowing the jet of the charge formed to pass back.

Une structure déformable peut être interposée entre le propulseur et la charge formée arrière.A deformable structure can be interposed between the propellant and the rear shaped charge.

La charge formée avant et le propulseur peuvent être intégrés dans une structure rigide.The charge formed before and the propellant can be integrated into a rigid structure.

- les moyens fonctionnels tels que le gyroscope de guidage, le détecteur de cible, l'alimentation électrique, le dispositif de sécurité de la charge avant sont disposés en couronne autour de la charge avant

  • - le bloc électronique de traitement est disposé
  • entre la charge avant 5 et le propulseur.
  • - le retard de fonctionnement entre les deux charges est compris entre 1000 et 3000 µs et plus particulièrement peut être de 2000 p.s.
- the functional means such as the guiding gyroscope, the target detector, the power supply, the safety device for the front load are arranged in a ring around the front load
  • - the electronic processing unit is arranged
  • between the front load 5 and the propellant.
  • - the operating delay between the two loads is between 1000 and 3000 µs and more particularly can be 2000 ps

D'autres caractéristiques et avantages de l'invention apparaîtront à la lecture de la description détaillée d'un mode de réalisation particulier de l'invention faite en regard du dessin annexé sur lequel:

  • - la figure 1 représente une coupe longitudinale du projectile selon l'invention.
  • - la figure 2 représente une coupe selon AA de la figure 1.
Other characteristics and advantages of the invention will appear on reading the detailed description of a particular embodiment of the invention made with reference to the appended drawing in which:
  • - Figure 1 shows a longitudinal section of the projectile according to the invention.
  • - Figure 2 shows a section along AA of Figure 1.

Le projectile représenté à la figure 1 est constitué:

  • - d'une charge creuse principale 1 située en arrière de la tête militaire et dite charge arrière.
  • - d'une charge creuse secondaire 2 de calibre réduit située en avant de la tête militaire et dite charge avant.
  • - d'un ensemble de moyens fonctionnels constitué par temple par des dispositifs: de guidage gyroscopique 3, de détection optique de cible 4, d'alimentation électrique 5, de sécurité d'amorçage de la charge avant 6, les dits moyens étant disposés en couronne autour de la charge avant 2.
  • - d'un bloc électronique de traitement de l'information 7 fournie par le détecteur optique 4 et délivrant les impulsions de mise à feu de la charge avant et d'initiation du retard de mise à feu de la charge arrière, le bloc électronique est logé dans un coffret métallique 8.
  • - d'un propulseur à poudre 9 permettant soit d'acquérir la vitesse de croisière (propulseur d'accélération) soit de maintenir la vitesse de croisière (propulseur de croisière). Ce propulseur comporte un évidement axial 10 permettant le passage, sans altération du jet de la charge arrière.
  • - d'un retard 11 qui réalise, soit par pyrotechnie, soit par un dispositif électronique, l'initiation de la détonation de la charge arrière environ 2000 µs après l'initiation de la charge avant.
The projectile shown in Figure 1 consists of:
  • - a main hollow charge 1 located behind the military head and called rear charge.
  • - a secondary hollow charge 2 of reduced caliber located in front of the military head and called front load.
  • - a set of functional means constituted by temple by devices: gyroscopic guidance 3, optical target detection 4, electrical supply 5, safety of priming of the front load 6, said means being arranged in crown around the front load 2.
  • an electronic block for processing information 7 supplied by the optical detector 4 and delivering the firing pulses of the front load and initiating the firing delay of the rear load, the electronic block is housed in a metal case 8.
  • - A powder propellant 9 allowing either to acquire cruising speed (acceleration propellant) or to maintain cruising speed (cruising propellant). This propellant has an axial recess 10 allowing passage, without altering the jet of the rear load.
  • - A delay 11 which performs, either by pyrotechnics, or by an electronic device, the initiation of the detonation of the rear charge approximately 2000 μs after the initiation of the front charge.

La structure de liaison 12 entre le propulseur et la charge arrière est conçue de façon à ce que les effets du choc induit par la détonation de la charge avant sur la charge arrière restent négligeables. Pour ce faire cette structure est déformable de manière à absorber l'énergie développée par la charge avant. Par contre, l'ensemble constitué par la charge avant et le propulseur est conçu de façon à former un ensemble rigide transmettant quasi intégralement les efforts de détonation de la charge avant vers la structure de liaison 12.The connecting structure 12 between the propellant and the rear load is designed so that the effects of the shock induced by the detonation of the front load on the rear load remain negligible. To do this, this structure is deformable so as to absorb the energy developed by the front load. On the other hand, the assembly constituted by the front load and the propellant is designed so as to form a rigid assembly transmitting almost entirely the detonation forces of the front load towards the connection structure 12.

D'autre part, le bloc électronique de traitement 8, de par son emplacement, participe à la protection intercharge.On the other hand, the electronic processing unit 8, by virtue of its location, participates in the intercharge protection.

Le projectile ainsi réalisé offre les avantages provenant du fait;

  • - que le propulseur et le bloc électronique sont disposés entre les deux charges et jouent ainsi le rôle d'écran de protection de la charge arrière, donc permettent un allègement du projectile, d'où un accroissement de portée.
  • - que la masse de tous les dispositifs années est reportée vers l'avant du projectile, ce qui permet d'atteindre un niveau de stabilité important sur trajectoire.
  • - que la disposition de tous les éléments permet une réduction de l'encombrement du projectile.
The projectile thus produced offers the advantages arising from the fact;
  • - That the propellant and the electronic unit are arranged between the two charges and thus play the role of protective screen for the rear charge, thus allowing the projectile to be lightened, hence an increased range.
  • - that the mass of all the device years is transferred towards the front of the projectile, which makes it possible to reach a significant level of stability on trajectory.
  • - that the arrangement of all the elements allows a reduction in the size of the projectile.

Claims (7)

1. A projectile intended to attack armored and especially active targets, composed of a warhead including a leading shaped-charge unit (2) and a trailing shaped charge unit (1) arranged in tandem and detonating in sequence, on the one hand, and of a propel lent charge, on the other hand, characterized in that it incorporates a protective screen constituted by the propellent charge (9) itself, placed between the two units (1, 2), which is fitted with an axial recess making way for the jet of the trailing shaped-charge unit (1 ).
2. A projectile as claimed in claim 1, characterized in that a deformable structure (12) is interposed between the propellent charge (9) and the trailing shaped-charge unit (1).
3. A projectile as claimed in claim 2, characterized in that the leading shaped-charge unit (2) and the propellent charge (9) are integrated into a rigid structure.
4. A projectile as claimed in any one of claims 1 to 3, characterized in that the functional means such as the guidance gyro (3), the target seeker (4), the electrical power supply (5), the safety device (6) of the leading unit are arranged in the annular space around the leading unit (2).
5. A projectile as claimed in any one of claims 1 to 4, characterized in that it comprises an electronic data processing unit (7) located between the leading unit (2) and the propellent charge (9).
6. A projectile as claimed in any one of claims 1 to 5, characterized in that the ignition time delay interval between the two units (1, 2) ranges from 1000 to 3000 µs.
7. A projectile as claimed in any one of claims 1 to 6, characterized in that the ignition time delay interval between the two units (1, 2) is 2000 µs.
EP19860400993 1985-05-10 1986-05-09 Armour-perforating projectile Expired EP0201433B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8507080 1985-05-10
FR8507080A FR2581749B1 (en) 1985-05-10 1985-05-10 ANTICHAR PROJECTILE

Publications (2)

Publication Number Publication Date
EP0201433A1 EP0201433A1 (en) 1986-12-17
EP0201433B1 true EP0201433B1 (en) 1988-08-31

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Family Applications (1)

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EP19860400993 Expired EP0201433B1 (en) 1985-05-10 1986-05-09 Armour-perforating projectile

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EP (1) EP0201433B1 (en)
DE (1) DE3660645D1 (en)
FR (1) FR2581749B1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3924810A1 (en) * 1989-07-27 1991-02-07 Bundesrep Deutschland Spin-stabilised rotating rocket with terminal war-heads - has lateral propulsion nozzles also active as steering fins
DE19617221A1 (en) * 1996-04-30 1997-11-06 Diehl Gmbh & Co Projectile, e.g. a mortar, for use against armoured vehicles or bunkers

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3601979A1 (en) * 1986-01-21 1987-07-23 Lfu Labor Fuer Umweltanalytik Process for the biotechnological recovery of environmentally damaged soil
DE3619791A1 (en) * 1986-06-18 1988-01-14 Rheinmetall Gmbh ACTIVITIES TO COMBAT, PARTICULARLY ACTIVE, ARMORED TARGETS
FR2603375B1 (en) * 1986-08-26 1990-07-27 Matra Manurhin Defense AMMUNITION WITH TANDEM LOADS
DE3740412C1 (en) * 1987-11-28 1996-04-25 Rheinmetall Ind Gmbh Warhead for use against targets with active armour
US5078069A (en) * 1990-03-27 1992-01-07 Hughes Aircraft Company Warhead
FR2729750B1 (en) * 1990-03-29 1997-03-21 France Etat MILITARY HEAD WITH HOLLOW LOADS IN SEQUENCE
DE4102772C1 (en) 1991-01-31 1998-10-01 Daimler Benz Aerospace Ag Two stage warhead combating reactively-armoured tanks
US5565647A (en) * 1991-05-24 1996-10-15 Giat Industries Warhead with sequential shape charges
FR2953009A1 (en) 2009-11-26 2011-05-27 Nexter Munitions MILITARY HEAD WITH TANDEM LOADS
GB201118903D0 (en) * 2011-10-27 2012-03-21 Mbda Uk Ltd An improved guided munition
RU2714274C2 (en) * 2018-06-15 2020-02-13 Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-Морского Флота "Военно-морская академия им. Адмирала Флота Советского Союза Н.Г. Кузнецова" Cruise missile with self-contained unmanned underwater vehicle-mine

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Publication number Priority date Publication date Assignee Title
FR1002092A (en) * 1946-07-25 1952-03-03 Soc Tech De Rech Ind Perforating projectiles improvements
US2804823A (en) * 1955-05-13 1957-09-03 Jablansky Louis Multiple unit projectile
FR1569559A (en) * 1964-11-26 1969-06-06
FR1455403A (en) * 1965-09-03 1966-04-01 Ring-nozzle warhead powder thruster
FR2310547A1 (en) * 1975-05-06 1976-12-03 Realisa Et Applic Tech Et Missile with secondary charge ahead of main charge - has small charge on nose cone positioned not to disturb main explosion
DE2629280C1 (en) * 1976-06-30 1985-07-25 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Warhead for fighting target objects, especially aircraft, which are housed in protective spaces
DE2829002C2 (en) * 1978-07-01 1985-04-04 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Warhead
FR2519752B1 (en) * 1982-01-07 1987-01-16 Serat IMPROVEMENTS ON TENSIONED GROUND-TO-GROUND WEAPONS WORKING OVER THE OBJECTIVE

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3924810A1 (en) * 1989-07-27 1991-02-07 Bundesrep Deutschland Spin-stabilised rotating rocket with terminal war-heads - has lateral propulsion nozzles also active as steering fins
DE19617221A1 (en) * 1996-04-30 1997-11-06 Diehl Gmbh & Co Projectile, e.g. a mortar, for use against armoured vehicles or bunkers
DE19617221C2 (en) * 1996-04-30 1999-07-01 Diehl Stiftung & Co Steerable projectile that can be used as a mortar

Also Published As

Publication number Publication date
FR2581749B1 (en) 1987-10-02
DE3660645D1 (en) 1988-10-06
FR2581749A1 (en) 1986-11-14
EP0201433A1 (en) 1986-12-17

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