EP2418454A3 - Steerable missile - Google Patents

Steerable missile Download PDF

Info

Publication number
EP2418454A3
EP2418454A3 EP11006540.6A EP11006540A EP2418454A3 EP 2418454 A3 EP2418454 A3 EP 2418454A3 EP 11006540 A EP11006540 A EP 11006540A EP 2418454 A3 EP2418454 A3 EP 2418454A3
Authority
EP
European Patent Office
Prior art keywords
missile
steerable
actuator
steerable missile
launcher
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
EP11006540.6A
Other languages
German (de)
French (fr)
Other versions
EP2418454A2 (en
EP2418454B1 (en
Inventor
Peter Gleich
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.)
MBDA Deutschland GmbH
Original Assignee
MBDA Deutschland 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 MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH
Publication of EP2418454A2 publication Critical patent/EP2418454A2/en
Publication of EP2418454A3 publication Critical patent/EP2418454A3/en
Application granted granted Critical
Publication of EP2418454B1 publication Critical patent/EP2418454B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • 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
    • F42B10/02—Stabilising arrangements
    • F42B10/22—Projectiles of cannelured type
    • 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
    • F42B10/38—Range-increasing arrangements
    • F42B10/42—Streamlined projectiles
    • F42B10/46—Streamlined nose cones; Windshields; Radomes

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

Ein lenkbarer Flugkörper, insbesondere ein aus einem Werfer verschießbarer lenkbarer Raketenflugkörper, mit einem im Wesentlichen rohrförmigen Korpus (1; 101; 201; 301; 401) sowie einer kippbewegbar am Korpus (1; 101; 201; 301; 401) angebrachten Flugkörpernase (2; 102; 202; 302; 402), deren Neigungswinkel zur Flugkörperlängsachse (X) mittels zumindest eines Aktuators veränderbar ist, zeichnet sich dadurch aus, dass der Aktuator von einem Elektromagneten (30, 32, 34, 36; 130, 134; 230, 234; 330, 334; 430, 434) gebildet ist.

Figure imgaf001
A steerable missile, in particular a steerable missile missile which can be launched from a launcher, having a substantially tubular body (1, 101, 201, 301, 401) and a missile nose (2, 101, 201, 301, 401) attached to the body (1; 102, 202, 302, 402), whose inclination angle to the missile longitudinal axis (X) is variable by means of at least one actuator, is characterized in that the actuator by an electromagnet (30, 32, 34, 36, 130, 134; 234; 330, 334; 430, 434).
Figure imgaf001
EP11006540.6A 2010-08-13 2011-08-09 Steerable missile Active EP2418454B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE201010034310 DE102010034310B4 (en) 2010-08-13 2010-08-13 Steerable missile

Publications (3)

Publication Number Publication Date
EP2418454A2 EP2418454A2 (en) 2012-02-15
EP2418454A3 true EP2418454A3 (en) 2013-05-29
EP2418454B1 EP2418454B1 (en) 2015-07-22

Family

ID=44840501

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11006540.6A Active EP2418454B1 (en) 2010-08-13 2011-08-09 Steerable missile

Country Status (2)

Country Link
EP (1) EP2418454B1 (en)
DE (1) DE102010034310B4 (en)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1982003453A1 (en) * 1981-04-08 1982-10-14 Thomson Keith Donald Directional control device for airborne or seaborne missiles
DE3503041C1 (en) * 1985-01-30 1986-09-11 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn High-speed missile with aerodynamic control
DE3628152C1 (en) * 1986-08-19 1987-09-10 Messerschmitt Boelkow Blohm Missile with aerodynamic control
DE19839493C1 (en) * 1998-08-29 1999-12-30 Inst Franco Allemand De Rech D Controlling a supersonic flying body to increase efficiency to be achieved while ensuring that drag is not increased, especially during low flight

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3519892C2 (en) * 1985-06-04 1987-04-23 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Braking and release device for a rotary nozzle body for guiding a missile
US6467722B1 (en) * 2002-01-31 2002-10-22 The United States Of America As Represented By The Secretary Of The Army Magnetostrictive missile guidance system
DE102007007929B3 (en) * 2007-02-17 2008-11-20 Lfk-Lenkflugkörpersysteme Gmbh Infantry weapon system for fighting fixed targets by means of steerable grenades fired from launchers
US7791007B2 (en) * 2007-06-21 2010-09-07 Woodward Hrt, Inc. Techniques for providing surface control to a guidable projectile

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1982003453A1 (en) * 1981-04-08 1982-10-14 Thomson Keith Donald Directional control device for airborne or seaborne missiles
DE3503041C1 (en) * 1985-01-30 1986-09-11 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn High-speed missile with aerodynamic control
DE3628152C1 (en) * 1986-08-19 1987-09-10 Messerschmitt Boelkow Blohm Missile with aerodynamic control
DE19839493C1 (en) * 1998-08-29 1999-12-30 Inst Franco Allemand De Rech D Controlling a supersonic flying body to increase efficiency to be achieved while ensuring that drag is not increased, especially during low flight

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
LINMOT INC: "LinMot Databook", 15 October 2006 (2006-10-15), XP002695553, Retrieved from the Internet <URL:http://web.archive.org/web/20061015010718/http://www.linmot.com/lm_typo/fileadmin/doc/Datasheets/linmot_databook_e_recent.pdf> [retrieved on 20130415] *

Also Published As

Publication number Publication date
DE102010034310A1 (en) 2012-02-16
DE102010034310B4 (en) 2013-11-07
EP2418454A2 (en) 2012-02-15
EP2418454B1 (en) 2015-07-22

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