NO20053824L - Winger device. - Google Patents

Winger device.

Info

Publication number
NO20053824L
NO20053824L NO20053824A NO20053824A NO20053824L NO 20053824 L NO20053824 L NO 20053824L NO 20053824 A NO20053824 A NO 20053824A NO 20053824 A NO20053824 A NO 20053824A NO 20053824 L NO20053824 L NO 20053824L
Authority
NO
Norway
Prior art keywords
wing
winger
projectile
longitudinal axis
wing element
Prior art date
Application number
NO20053824A
Other languages
Norwegian (no)
Other versions
NO20053824D0 (en
Inventor
Erich Locher
Michael Feuerstein
Original Assignee
Diehl Bgt Defence Gmbh & Co Kg
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 Diehl Bgt Defence Gmbh & Co Kg filed Critical Diehl Bgt Defence Gmbh & Co Kg
Publication of NO20053824D0 publication Critical patent/NO20053824D0/en
Publication of NO20053824L publication Critical patent/NO20053824L/en

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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/16—Wrap-around fins

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)
  • Specific Sealing Or Ventilating Devices For Doors And Windows (AREA)

Abstract

Oppfinnelsen vedrører en vingeanordning (10) for et prosjektil omfattende to vingeelementer (12, 14), med hvilken et første vingeelement (12) er utfoldbart festet langs dets lengdeakse via en forbindelsesinnretning (24) ved prosjektilet, og med hvilken det andre svingeelementet (14) er således forbundet med det første vingeelementet (12), at det er svingbart om en akse som står loddrett i forhold til lengdeaksen for det første vingeelementet (12).The invention relates to a wing arrangement (10) for a projectile comprising two wing elements (12, 14), with which a first wing element (12) is unfoldably attached along its longitudinal axis via a connecting device (24) to the projectile, and with which the second swing element (14) ) is so connected to the first wing element (12) that it is pivotable about an axis which is vertical to the longitudinal axis of the first wing element (12).

NO20053824A 2004-08-16 2005-08-15 Winger device. NO20053824L (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200410039770 DE102004039770A1 (en) 2004-08-16 2004-08-16 wing assembly

Publications (2)

Publication Number Publication Date
NO20053824D0 NO20053824D0 (en) 2005-08-15
NO20053824L true NO20053824L (en) 2006-02-17

Family

ID=35295672

Family Applications (1)

Application Number Title Priority Date Filing Date
NO20053824A NO20053824L (en) 2004-08-16 2005-08-15 Winger device.

Country Status (3)

Country Link
EP (1) EP1628112A1 (en)
DE (1) DE102004039770A1 (en)
NO (1) NO20053824L (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007002948B4 (en) 2007-01-19 2009-04-02 Diehl Bgt Defence Gmbh & Co. Kg Device for wing deployment
IL189785A (en) 2008-02-26 2013-07-31 Elbit Systems Ltd Foldable and deployable panel
US8847134B2 (en) 2012-02-16 2014-09-30 Lockheed Martin Corporation Deployable wing and fin control surface actuation
RU2549047C1 (en) * 2014-03-04 2015-04-20 Открытое акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Device to lock aircraft folded airfoils
EP3032213B1 (en) 2014-12-11 2018-06-20 MBDA Deutschland GmbH Folding fin system
DE102015004703B4 (en) * 2014-12-11 2019-12-12 Mbda Deutschland Gmbh Folding wing system
CN104677200B (en) * 2015-01-21 2016-05-18 浙江理工大学 One twice-folded aerofoil horizontal spreading mechanism
FR3035493B1 (en) * 2015-04-21 2018-09-14 Nexter Munitions BALLISTIC PROJECTILE COMPRISING A WING OPENING MECHANISM AND METHOD OF USING SUCH A BALLISTIC PROJECTILE
DE102015014794A1 (en) * 2015-08-25 2017-03-02 Diehl Bgt Defence Gmbh & Co. Kg Wing arrangement and missile with wing arrangement
SE544987C2 (en) * 2020-08-19 2023-02-21 Saab Ab A wing arrangement, a projectile, a use and a method for deploying a wing blade

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1199664B (en) * 1962-09-11 1965-08-26 Dynamit Nobel Ag Folding tail, especially for rocket projectiles
US3633846A (en) * 1970-05-28 1972-01-11 Us Navy Expandable aerodynamic fin
DE2635676A1 (en) * 1976-08-07 1978-02-09 Dynamit Nobel Ag Guide fin with extension for rocket - has sliding fin in cavity pushed out by spring force after launching
DE2649643A1 (en) * 1976-10-29 1978-06-15 Messerschmitt Boelkow Blohm Rocket missile extending stabilising fins - have sections extended progressively by springs and releasing charges
DE3010027C2 (en) * 1978-09-26 1985-07-11 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Pivoting arrangement of a tail unit, especially for missiles or projectiles
AU524255B2 (en) * 1978-12-29 1982-09-09 Commonwealth Of Australia, The Deployable wing
DE2926933A1 (en) * 1979-07-04 1981-01-22 Grs Ges Fuer Raketen Systeme M Missile stabilising mechanism with extensible rigid fins - which act both as braking and guide surfaces according to adjusted position
DE3417082A1 (en) * 1984-05-09 1985-11-14 Diehl GmbH & Co, 8500 Nürnberg FOLDING WING, IN PARTICULAR FOR ONE STOREY
US4667899A (en) * 1984-11-28 1987-05-26 General Dynamics, Pomona Division Double swing wing self-erecting missile wing structure
US4778127A (en) * 1986-09-02 1988-10-18 United Technologies Corporation Missile fin deployment device

Also Published As

Publication number Publication date
DE102004039770A1 (en) 2006-03-02
NO20053824D0 (en) 2005-08-15
EP1628112A1 (en) 2006-02-22

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Legal Events

Date Code Title Description
FC2A Withdrawal, rejection or dismissal of laid open patent application