EP1688702A1 - Dispositif pour l'augmentation de la précision des munitions avec appendage arrière de stabilisation - Google Patents

Dispositif pour l'augmentation de la précision des munitions avec appendage arrière de stabilisation Download PDF

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Publication number
EP1688702A1
EP1688702A1 EP05028015A EP05028015A EP1688702A1 EP 1688702 A1 EP1688702 A1 EP 1688702A1 EP 05028015 A EP05028015 A EP 05028015A EP 05028015 A EP05028015 A EP 05028015A EP 1688702 A1 EP1688702 A1 EP 1688702A1
Authority
EP
European Patent Office
Prior art keywords
ammunition
kit
tail
steering
accuracy
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Withdrawn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
EP05028015A
Other languages
German (de)
English (en)
Inventor
Wolfgang Dr. Seidel
Frank Guischard
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 Waffe Munition GmbH
Original Assignee
Rheinmetall Waffe Munition 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 Waffe Munition GmbH filed Critical Rheinmetall Waffe Munition GmbH
Publication of EP1688702A1 publication Critical patent/EP1688702A1/fr
Withdrawn legal-status Critical Current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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control

Definitions

  • the invention relates to a device for increasing the precision of rear wing stabilized, unguided ammunition or artillery projectiles.
  • the invention has as its object to provide a simple means by which the unguided ammunition can be made intelligent.
  • the invention is based on the idea of using a so-called Guidance Kit (set) from a conventional rear wing stabilized ammunition cost to make a guided ammunition, ie, by integrating the kit, the precision of the ammunition in the target of the steering ammunition approximate.
  • a so-called Guidance Kit set
  • it is envisaged to replace the conventional igniter in the projectile by the kit with integrated detonator.
  • This is one in already finished Ammunition of existing detonator, for example, unscrewed and screwed the Guidance Kit with the same thread and the same ignition on the remaining rear part of the ammunition. If the detonator is part of the kit, you already have a new ammo. If the detonator is not included, it will be turned on to the kit.
  • An aerodynamic steering can also be part of the kit.
  • Canards wings
  • micro reaction engines etc.
  • a bullet steering takes place precisely to the target.
  • a laser aiming head can be integrated in the kit or in the ammunition tip. Also combinations of the systems are possible.
  • a projectile is shown, which is tail wing stabilized.
  • a guidance kit marked 2 is integrated in the front area 3 of the projectile and in this case contains a projectile fuze 4 or a sighting head 5 with a projectile fuze 6 ( Figure 2).
  • Preferably part of the guidance kits 2 is an aerodynamic steering 7, for example an annular, aerodynamic actuator 7.1 or fold-out spoilers (not shown) or, as shown in FIG. 2, microreaction engines 12, which are preferably evenly distributed around the circumference, as well the wings 7.2.
  • the wings 7.2 of the actuator 7.1 are brought, for example by adjusting motors 7.3 in position.
  • the Guidance kit 2 also includes a battery 10 that can be activated with the launch, which, among other things, controls the servo motors 7.3.
  • the aerodynamic steering 7 is preferably retracted during the projectile passage in a gun barrel, not shown, and should preferably be unfolded only after a ballistically definable flight phase, then to steer the projectile 1 into the target E (FIG. 4).
  • the rear area 8 are only sketchily indicated rear wing 9.
  • With 11 is a navigation sensor characterized.
  • FIG. 4 shows the individual phases of flight on the basis of the ballistic flight of the projectile 1.
  • the rear wings 9 shown in sketchy form are directly extended in position B.
  • the unfolding of the aerodynamic steering 7 is preferably carried out at point C.
  • the sliding phase and the associated increase in range is initiated.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP05028015A 2005-02-04 2005-12-21 Dispositif pour l'augmentation de la précision des munitions avec appendage arrière de stabilisation Withdrawn EP1688702A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005005502 2005-02-04
DE102005039902A DE102005039902A1 (de) 2005-02-04 2005-08-24 Einrichtung zur Steigerung der Präzision heckflügelstabilisierter Munition

Publications (1)

Publication Number Publication Date
EP1688702A1 true EP1688702A1 (fr) 2006-08-09

Family

ID=36293275

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05028015A Withdrawn EP1688702A1 (fr) 2005-02-04 2005-12-21 Dispositif pour l'augmentation de la précision des munitions avec appendage arrière de stabilisation

Country Status (3)

Country Link
EP (1) EP1688702A1 (fr)
DE (1) DE102005039902A1 (fr)
NO (1) NO20056230L (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2910613A1 (fr) * 2006-12-21 2008-06-27 Ateliers Mecaniques De Pont Su Projectile guide muni d'un manchon pour le montage d'un systeme de guidage
EP2046634A2 (fr) * 2006-10-24 2009-04-15 Rafael Advanced Defense Systems Ltd. Obus guidé aéroporté
WO2011037663A1 (fr) * 2009-09-28 2011-03-31 Raytheon Company Adaptateur de guidage de roquette

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103471474B (zh) * 2013-09-12 2015-12-30 贵州航天电子科技有限公司 一种小型化雷达引信结构
CN104236398B (zh) * 2014-09-25 2016-02-24 航宇救生装备有限公司 一种同时具有爆轰波和激光起爆的燃爆弹

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4899956A (en) * 1988-07-20 1990-02-13 Teleflex, Incorporated Self-contained supplemental guidance module for projectile weapons
DE4408085A1 (de) * 1994-03-10 1995-09-14 Rheinmetall Ind Gmbh Vorrichtung zur Lenkung eines Flugkörpers
WO1999030106A1 (fr) * 1997-12-11 1999-06-17 Lockheed-Martin Corporation Bombe aerienne munie d'une enveloppe
US6135387A (en) * 1997-09-17 2000-10-24 Rheinmetall W&M Gmbh Method for autonomous guidance of a spin-stabilized artillery projectile and autonomously guided artillery projectile for realizing this method
US6254031B1 (en) * 1994-08-24 2001-07-03 Lockhead Martin Corporation Precision guidance system for aircraft launched bombs
US20020117580A1 (en) * 2001-02-01 2002-08-29 United Defense, L.P. 2-D projectile trajectory corrector
US20020153448A1 (en) * 1993-11-18 2002-10-24 Mayersak Joseph R. Precision guidance system for aircraft launched bombs
FR2845763A1 (fr) * 2002-10-11 2004-04-16 Tda Armements Sas Systeme autonome de guidage pour munition d'artillerie et munition d'artillerie guidee

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4899956A (en) * 1988-07-20 1990-02-13 Teleflex, Incorporated Self-contained supplemental guidance module for projectile weapons
US20020153448A1 (en) * 1993-11-18 2002-10-24 Mayersak Joseph R. Precision guidance system for aircraft launched bombs
DE4408085A1 (de) * 1994-03-10 1995-09-14 Rheinmetall Ind Gmbh Vorrichtung zur Lenkung eines Flugkörpers
US6254031B1 (en) * 1994-08-24 2001-07-03 Lockhead Martin Corporation Precision guidance system for aircraft launched bombs
US6135387A (en) * 1997-09-17 2000-10-24 Rheinmetall W&M Gmbh Method for autonomous guidance of a spin-stabilized artillery projectile and autonomously guided artillery projectile for realizing this method
WO1999030106A1 (fr) * 1997-12-11 1999-06-17 Lockheed-Martin Corporation Bombe aerienne munie d'une enveloppe
US20020117580A1 (en) * 2001-02-01 2002-08-29 United Defense, L.P. 2-D projectile trajectory corrector
FR2845763A1 (fr) * 2002-10-11 2004-04-16 Tda Armements Sas Systeme autonome de guidage pour munition d'artillerie et munition d'artillerie guidee

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2046634A2 (fr) * 2006-10-24 2009-04-15 Rafael Advanced Defense Systems Ltd. Obus guidé aéroporté
EP2046634A4 (fr) * 2006-10-24 2012-10-17 Rafael Advanced Defense Sys Obus guidé aéroporté
FR2910613A1 (fr) * 2006-12-21 2008-06-27 Ateliers Mecaniques De Pont Su Projectile guide muni d'un manchon pour le montage d'un systeme de guidage
WO2008102069A2 (fr) * 2006-12-21 2008-08-28 Societe Des Ateliers Mecaniques De Pont Sur Sambre Projectile guide muni d' un manchon pour le montage d'un systeme de guidage
WO2008102069A3 (fr) * 2006-12-21 2008-10-30 Ateliers Mecaniques De Pont Su Projectile guide muni d' un manchon pour le montage d'un systeme de guidage
WO2011037663A1 (fr) * 2009-09-28 2011-03-31 Raytheon Company Adaptateur de guidage de roquette
US8291827B2 (en) 2009-09-28 2012-10-23 Raytheon Company Rocket guidance adapter

Also Published As

Publication number Publication date
NO20056230L (no) 2006-08-07
DE102005039902A1 (de) 2006-08-10

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