EP0298844A1 - Gerät zum Ausfahren von Steuerschwänzen und dessen Anwendung an einem Projektil - Google Patents

Gerät zum Ausfahren von Steuerschwänzen und dessen Anwendung an einem Projektil Download PDF

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Publication number
EP0298844A1
EP0298844A1 EP88401708A EP88401708A EP0298844A1 EP 0298844 A1 EP0298844 A1 EP 0298844A1 EP 88401708 A EP88401708 A EP 88401708A EP 88401708 A EP88401708 A EP 88401708A EP 0298844 A1 EP0298844 A1 EP 0298844A1
Authority
EP
European Patent Office
Prior art keywords
wing
ring
projectile
wings
axis
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Withdrawn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
EP88401708A
Other languages
English (en)
French (fr)
Inventor
Etienne Lamarque
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.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements SA
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 Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0298844A1 publication Critical patent/EP0298844A1/de
Withdrawn legal-status Critical Current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
    • 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

Definitions

  • the present invention converges the deployment, multiple or not, of wings preferably fitted to a projectile or a missile such as a missile.
  • missile all these projectiles or flying devices such as missiles.
  • Devices such as military missiles are often equipped with folding wings to allow optimized containment of several devices inside a carrier container, before these devices are dropped or expelled from the container.
  • the wings are deployed to ensure their stabilization function.
  • the main difficulty in deploying wings of this type is to deploy them in a combined manner, that is to say at exactly the same time.
  • the object of the invention is, while designing deployable wings of a different design, to provide a device for deploying said wings.
  • the object of the invention is a device for deploying one or more unfoldable wings, positioned in the same direction, by rotation relative to a body, the wing being able to occupy a folded position and a deployed position, characterized in that that the wing has, at its lower end, a projecting part penetrating into a notch formed in an annular ring so that, during the rotation of the ring around the axis of revolution of the body, the wing pivots around the pivot axis.
  • each of them is fixed thereto by means of an articulation 7.
  • This figure represents them in the folded position, that is to say say a storage position.
  • This representation is only an example, both of from the point of view of the number of wings, only in the direction in which they are folded back towards the projectile 1.
  • a dashed line shows one of these wings in its deployed position, that is to say that this wing is perpendicular to the outer surface of the projectile, where it is attached to the latter.
  • Figure 2 shows a second example of storage of the wings 2 against the projectile 1.
  • two wings have been shown, but this is in no way limiting. The same is true with regard to the fact that they have been shown folded in an opposite direction.
  • an annular ring 4 is inserted inside the body 3, and can rotate inside and relative to it.
  • the wing 2 can pivot about an axis 6 tangential to the body 3 thanks to a mechanical articulation, which can consist for example of a boss 8 projecting from the body 3, and in which the articulation is fixed.
  • invention provides means for transmitting the rotational movement of the ring 4 relative to the body 3, in a pivoting movement of the wing 2, which are constituted by a projecting part 5 of the wing which deviates from the axis of rotation 6, in order to penetrate a notch 10 in the ring 4.
  • a rotation along arrow F1 of ring 4 causes pivoting along arrow F2 of wing 2 around axis 6.
  • a stop is provided, materialized in FIG. 3 by a surface 9 of the boss 8, which blocks the wing 2 in an unfolded position, corresponding to that shown in FIG. 4.
  • the ring 4 has rotated enough so that the wing is fully unfolded, and pressing against the surface 9. It should be noted that for the wing to be maintained in this position, it is necessary that the surface 9 representing the stop and the external surface 11 of the ring 4 make an angle corresponding to that made by the projection 5 relative to the orientation of the wing 2.
  • This mechanism is the same for all the wings, and at least for the two wings of the same pair. It can be noted that during deployment, if a wing is stressed externally by a force which tends to close it, using this mechanism, the position of the two wings of the same pair will remain symmetrical.
  • the ring 4 can be an externally toothed wheel, meshing on the base of the wing 2 situated around the axis 6 in which corresponding teeth have been machined, so as to produce a mechanism identical to that of a rack.
  • FIGS. 5A and 5B show an example of means for rotating the ring 4.
  • a cylinder 13, integral with the structure of the body contains a piston 15 which can translate.
  • a piston 12 is attached to the piston 15 by means of a joint 14, which is preferably floating, that is to say mounted with play, or may be a ball joint.
  • the other end of the link is fixed to the ring by means of a joint 18.
  • the rotation of the ring 4 is effected by the translation of the piston 15. This is carried out, preferably, by means of a pyrotechnic generator 16 placed inside the cylinder 13, and initiated by an igniter 17 The piston, under the effect of the pressure, translates, pushes the link 12 which rotates the ring 4.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aerials With Secondary Devices (AREA)
  • Transmission Devices (AREA)
EP88401708A 1987-07-03 1988-07-01 Gerät zum Ausfahren von Steuerschwänzen und dessen Anwendung an einem Projektil Withdrawn EP0298844A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8709454A FR2617587B1 (fr) 1987-07-03 1987-07-03 Dispositif de deploiement conjugue d'ailes, et application a un engin volant
FR8709454 1987-07-03

Publications (1)

Publication Number Publication Date
EP0298844A1 true EP0298844A1 (de) 1989-01-11

Family

ID=9352843

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88401708A Withdrawn EP0298844A1 (de) 1987-07-03 1988-07-01 Gerät zum Ausfahren von Steuerschwänzen und dessen Anwendung an einem Projektil

Country Status (2)

Country Link
EP (1) EP0298844A1 (de)
FR (1) FR2617587B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3111157A4 (de) * 2014-02-26 2017-09-27 Israel Aerospace Industries Ltd. Rippeneinsatzsystem

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3188958A (en) * 1963-03-11 1965-06-15 James D Burke Range control for a ballistic missile
US3563495A (en) * 1969-02-03 1971-02-16 Us Air Force Power operated folding wing for rockets and missiles
GB1352118A (en) * 1964-09-28 1974-05-08 Dynamit Nobel Ag Rockets
GB2121147A (en) * 1982-06-02 1983-12-14 British Aerospace Missile fin assemblies
GB2155157A (en) * 1984-02-17 1985-09-18 Hunting Eng Ltd Helix ring devices and assemblies including them

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3188958A (en) * 1963-03-11 1965-06-15 James D Burke Range control for a ballistic missile
GB1352118A (en) * 1964-09-28 1974-05-08 Dynamit Nobel Ag Rockets
US3563495A (en) * 1969-02-03 1971-02-16 Us Air Force Power operated folding wing for rockets and missiles
GB2121147A (en) * 1982-06-02 1983-12-14 British Aerospace Missile fin assemblies
GB2155157A (en) * 1984-02-17 1985-09-18 Hunting Eng Ltd Helix ring devices and assemblies including them

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3111157A4 (de) * 2014-02-26 2017-09-27 Israel Aerospace Industries Ltd. Rippeneinsatzsystem
US9989338B2 (en) 2014-02-26 2018-06-05 Israel Aerospace Industries Ltd. Fin deployment system

Also Published As

Publication number Publication date
FR2617587B1 (fr) 1993-04-16
FR2617587A1 (fr) 1989-01-06

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