EP0137910A1 - Tête décrochable d'un obus vecteur ou missile - Google Patents

Tête décrochable d'un obus vecteur ou missile Download PDF

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Publication number
EP0137910A1
EP0137910A1 EP84106683A EP84106683A EP0137910A1 EP 0137910 A1 EP0137910 A1 EP 0137910A1 EP 84106683 A EP84106683 A EP 84106683A EP 84106683 A EP84106683 A EP 84106683A EP 0137910 A1 EP0137910 A1 EP 0137910A1
Authority
EP
European Patent Office
Prior art keywords
antenna
projectile
projectile head
target
head according
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.)
Granted
Application number
EP84106683A
Other languages
German (de)
English (en)
Other versions
EP0137910B1 (fr
Inventor
Wolfram Dr. Witt
Hendrik Lips
Herbert Dr. Scholles
Raimund Schweiger
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall GmbH
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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0137910A1 publication Critical patent/EP0137910A1/fr
Application granted granted Critical
Publication of EP0137910B1 publication Critical patent/EP0137910B1/fr
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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G9/00—Systems for controlling missiles or projectiles, not provided for elsewhere
    • F41G9/02—Systems for controlling missiles or projectiles, not provided for elsewhere for bombing control
    • 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
    • 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
    • F42B30/006—Mounting of sensors, antennas or target trackers on projectiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/006—Proximity fuzes; Fuzes for remote detonation for non-guided, spinning, braked or gravity-driven weapons, e.g. parachute-braked sub-munitions

Definitions

  • the invention relates to a projectile head that can be ejected from a cargo projectile or missile.
  • the projectile heads of the generic type are ejected from a cargo floor or missile and then sink over a target area, braked by a parachute, whereby they independently a target, for. B. an armored vehicle, capture and combat it after reaching the combat range.
  • a detachable projectile head which has an ignitable charge to combat the target, which hurls a secondary projectile onto the recognized target.
  • the secondary storey is formed from a flat charge that is deformed in the direction of flight before ignition to the secondary storey.
  • the detachable projectile head has a target recognition device with a transmitter, a receiver and an antenna for target acquisition.
  • the target location device including the antenna and additional guide surfaces are arranged in the direction of flight in front of the flat charge.
  • the invention has for its object to provide a projectile from a cargo floor or missile projectile head that is able to a secondary floor with max. Generate reach and penetration.
  • a charge 15, a flat coating 16 ′ arranged thereon to form a secondary projectile 16, a target recognition device 14 and a detonator 13 for activating the charge 15 are arranged within the casing 9 of the projectile head 10 according to FIG. 1.
  • the connecting lines between the projectile head 10 and the case screen 12 are designated by reference number 11.
  • FIG. 2 shows a partial section of the projectile head 10 with the flat occupancy 16 ′ arranged in the front in the flight direction, which is converted by a charge 15 activated by an igniter 13 after detection of a target and reaching the control range to a secondary projectile 16 destroying the target.
  • the igniter 13 in turn is connected via an ignition line 13 'to the target recognition device 14, which is arranged in the direction of flight behind the flat occupancy 16' and the charge 15.
  • the target recognition device 14 comprises a transmitter, a receiver and an antenna for transmitting and receiving electrical radiation, preferably in the microwave range, which is used for detecting and recognizing the target.
  • the space in front of the flat occupancy 16 is completely free, so that after activation of the charge 15, a powerful secondary floor 16 can develop undisturbed under optimal symmetry conditions.
  • the antenna 17 of the target recognition device which is arranged in the rest position within the envelope 9 of the projectile head 10, is to be put into operation at the earliest after the projectile head has been thrown off the load projectile.
  • it is expediently designed to be extendable or foldable.
  • the antenna 17 of the projectile head consists of a dome part 18 which is fixedly arranged in the projectile head and opens in the direction of flight of the projectile head 10 and on which segments 19 which can be folded out in the manner of a screen are articulated.
  • these segments 19 are folded in the rest position and are therefore within the diameter of the envelope 9 of the projectile head 10th
  • Fig. 3 illustrates on the basis of a partial representation of the projectile head 9 the unfolding of the segments 19 and shows the segments 19 in the extended state, whereby together with the fixed cap 18 they form the operational antenna 17.
  • the geometric shape of the antenna 17 is predetermined by the type of radiation characteristic of the antenna desired.
  • the antenna 17 extended in the operating position can have the shape of a paraboloid, in the focal point of which the actual radiator for the electromagnetic energy is arranged, which leads to the transmitter / receiver of the target recognition device 14.
  • This radiator is indicated schematically in FIG. 3 and is designated by reference number 31.
  • the segments 19 of the antenna 17 can be extended in a particularly simple manner by means of articulated rods 30, which are connected on the one hand to each of the segments 19 and on the other hand to a piston 41 (FIG. 4), which in turn is arranged displaceably in a cylinder 40.
  • the displacement of the piston 41 necessary for the unfolding of the segments 19 is expediently effected by an ejection charge 42 which is expediently activated in the target recognition device 14 by a timing element (not shown in more detail).
  • the hinged segments 19 of the antenna 17 lie on the in the idle state Envelope of a folded balloon 50.
  • the balloon 50 is acted upon with gas pressure by a gas generator 51, for example, the gas generator 51 being started by the central target recognition device 14.
  • the balloon 50 can still be used to separate the parts of the envelope 9 of the projectile head 10 which cover the projectile head at the level of the antenna 17 until the antenna 17 is extended.
  • a balloon 50 is provided for detaching the outer wall cladding, which is provided at most on a part of its inner or outer surface with a conductive, preferably metallic coating, which - in the form of a spherical cap - which Represents antenna reflector.
  • an antenna carrier 60 is mounted on an eccentrically arranged axis 61 in the projectile head 10 so that it can be swiveled out in the radial direction, in such a way that it is located within the casing 9 of the projectile head 10 in the idle state.
  • the antenna carrier 60 After the antenna carrier 60 has been swiveled out, which can be caused by ejection charges and / or spring means, the antenna 62 is outside the diameter of the projectile head 10 and can emit electromagnetic energy to the target area or take it from there.
  • this part 61 can also be designed as an antenna carrier for a further antenna, so that the transmitter and receiver of the target recognition device 14 can each be connected to their own antenna.
  • the effective area of the antenna 17 is shaded by the projectile body part in front of it, so that essentially only the antenna area is effective which, viewed in the radial direction, projects beyond the diameter of the warhead.
  • a second reflector 17 ' (FIG. 3a) can be provided in an advantageous further exemplary embodiment of the invention, which reflects the electromagnetic energy generated by the radiator 31 onto the main mirror 18, 19 of the antenna 17 judges. In the case of reception, this second mirror 17 'concentrates the energy absorbed by the antenna 17 onto the radiator 31 which is now acting as a receiver.
  • FIG. 3a A schematic arrangement of this antenna configuration with an indication of the beam path is shown in FIG. 3a.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Details Of Aerials (AREA)
EP84106683A 1983-06-25 1984-06-12 Tête décrochable d'un obus vecteur ou missile Expired EP0137910B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19833322927 DE3322927A1 (de) 1983-06-25 1983-06-25 Von einem lastengeschoss oder flugkoerper abwerfbarer geschosskopf
DE3322927 1983-06-25

Publications (2)

Publication Number Publication Date
EP0137910A1 true EP0137910A1 (fr) 1985-04-24
EP0137910B1 EP0137910B1 (fr) 1987-02-11

Family

ID=6202384

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84106683A Expired EP0137910B1 (fr) 1983-06-25 1984-06-12 Tête décrochable d'un obus vecteur ou missile

Country Status (5)

Country Link
US (2) US4622900A (fr)
EP (1) EP0137910B1 (fr)
DE (2) DE3322927A1 (fr)
ES (1) ES8503219A1 (fr)
NO (1) NO154811C (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0252036A2 (fr) * 1986-03-27 1988-01-07 Aktiebolaget Bofors Sous-munition autoguidée
EP0424336A2 (fr) * 1989-10-20 1991-04-24 Aktiebolaget Bofors Sous-tête militaire
EP0424337A2 (fr) * 1989-10-20 1991-04-24 Aktiebolaget Bofors Sous-tête militaire

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3428051A1 (de) * 1984-07-30 1986-03-06 Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt Wirkkoerpereinheit
DE3516673A1 (de) * 1985-05-09 1986-11-13 Diehl GmbH & Co, 8500 Nürnberg Endphasen-korrigierbare suchzuender-munition und verfahren zum bekaempfen gepanzerter zielobjekte
DE3527522A1 (de) * 1985-08-01 1987-02-12 Diehl Gmbh & Co Verfahren und verwendung von endphasenkorrigierter submunition zum bekaempfen von gepanzerten unterstaenden
DE3700342A1 (de) * 1987-01-08 1988-07-28 Rheinmetall Gmbh Submunitionskoerper mit einer zielerfassungsvorrichtung
FR2623773B1 (fr) * 1987-11-30 1990-04-27 Aerospatiale Corps largable muni de moyens de freinage aerodynamique
FR2639106B1 (fr) * 1988-11-15 1990-12-21 Thomson Brandt Armements Dispositif de verrouillage et de deverrouillage de deux elements d'un projectile, notamment d'un pot de parachute
DE3900269C2 (de) * 1989-01-07 1998-02-26 Rheinmetall Ind Ag Gefechtskopf
FR2642159B1 (fr) * 1989-01-20 1991-03-29 Thomson Brandt Armements Dispositif de mise en position inclinee d'une sous-munition sous parachute
US5070786A (en) * 1990-09-26 1991-12-10 Honeywell Inc. Standoff sensor antennae for munitions having explosively formed penetrators
SE468869B (sv) * 1991-09-18 1993-03-29 Bofors Ab Saett att bromsa upp en maalsoekares utfaellningsroerelse samt bromsanordning foer utfaellningsmekanism foer maalsoekare
SE9102702L (sv) * 1991-09-18 1993-03-19 Bofors Ab Stridsdel
DE4200727C2 (de) * 1992-01-14 1996-02-15 Rheinmetall Ind Gmbh Gefechtskopf
IL107830A (en) * 1993-12-01 1998-07-15 Israel State Controlled scanner head missile
US5537928A (en) * 1995-04-17 1996-07-23 Hughes Missile Systems Company Piggyback bomb damage assessment system
US8798450B2 (en) * 2004-10-01 2014-08-05 Flir Systems, Inc. Gimbal system
US7471451B2 (en) * 2005-10-14 2008-12-30 Flir Systems, Inc. Multiple field of view optical system
US7671311B2 (en) * 2006-02-17 2010-03-02 Flir Systems, Inc. Gimbal system with airflow
DE102007033831A1 (de) * 2007-07-18 2009-01-22 Rheinmetall Waffe Munition Gmbh Submunitionseinheit
US9448040B2 (en) * 2010-03-22 2016-09-20 Omnitek Partners Llc Remotely guided gun-fired and mortar rounds
DE102019105225B4 (de) * 2019-03-01 2023-10-19 Deutsches Zentrum für Luft- und Raumfahrt e.V. System und Verfahren zum Aufnehmen mindestens eines Bildes eines Beobachtungsbereiches

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2353566A1 (de) * 1972-10-25 1974-05-09 Constr Navales Ind Abwerfbarer geschosskopf
FR2478297A1 (fr) * 1980-03-12 1981-09-18 Serat Perfectionnements apportes aux tetes militaires, notamment antichars, agissant en survol d'un objectif ou d'un groupe d'objectifs
GB2090950A (en) * 1979-11-09 1982-07-21 Avco Corp Overflying missile

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2432920A (en) * 1942-04-29 1947-12-16 Mckay Herbert Couchman Radiation-controlled release for aerial bombs or other loads
US4207841A (en) * 1945-05-19 1980-06-17 The United States Of America As Represented By The Secretary Of The Army Dipole antenna for proximity fuze
US3439610A (en) * 1964-04-20 1969-04-22 Us Navy Folding munition
US3527167A (en) * 1967-07-17 1970-09-08 Milton Morse Anti-ballistic missile system
BE795623A (fr) * 1972-02-18 1973-06-18 Dynamit Nobel Ag Mines a charge creuse pour usages multiples
US4050381A (en) * 1972-04-12 1977-09-27 The United States Of America As Represented By The Secretary Of The Army Low density indirect fire munition system (U)
US3818833A (en) * 1972-08-18 1974-06-25 Fmc Corp Independent multiple head forward firing system
US4160415A (en) * 1978-05-05 1979-07-10 The United States Of America As Represented By The Secretary Of The Army Target activated projectile
DE2838347A1 (de) * 1978-09-02 1980-03-20 Rheinmetall Gmbh Gefechtskopf mit in einem abschussrohr angeordneten tochtergeschossen
DE2856610A1 (de) * 1978-12-29 1983-01-27 Dynamit Nobel Ag, 5210 Troisdorf Hohlladungswirkkoerper

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2353566A1 (de) * 1972-10-25 1974-05-09 Constr Navales Ind Abwerfbarer geschosskopf
GB2090950A (en) * 1979-11-09 1982-07-21 Avco Corp Overflying missile
FR2478297A1 (fr) * 1980-03-12 1981-09-18 Serat Perfectionnements apportes aux tetes militaires, notamment antichars, agissant en survol d'un objectif ou d'un groupe d'objectifs

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0252036A2 (fr) * 1986-03-27 1988-01-07 Aktiebolaget Bofors Sous-munition autoguidée
EP0252036A3 (en) * 1986-03-27 1988-02-17 Aktiebolaget Bofors Homing submunition
US4858532A (en) * 1986-03-27 1989-08-22 Aktiebolaget Bofors Submunitions
EP0424336A2 (fr) * 1989-10-20 1991-04-24 Aktiebolaget Bofors Sous-tête militaire
EP0424337A2 (fr) * 1989-10-20 1991-04-24 Aktiebolaget Bofors Sous-tête militaire
EP0424337A3 (en) * 1989-10-20 1992-01-22 Aktiebolaget Bofors Subwarhead
EP0424336A3 (en) * 1989-10-20 1992-02-19 Aktiebolaget Bofors Subwarhead

Also Published As

Publication number Publication date
EP0137910B1 (fr) 1987-02-11
NO842401L (no) 1984-12-27
US4622900A (en) 1986-11-18
NO154811C (no) 1986-12-29
DE3462377D1 (en) 1987-03-19
ES533659A0 (es) 1985-03-01
ES8503219A1 (es) 1985-03-01
US4691636A (en) 1987-09-08
NO154811B (no) 1986-09-15
DE3322927A1 (de) 1985-01-03

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