WO2021251930A2 - Missile miniature guidé doté d'un système d'actionnement de commande - Google Patents

Missile miniature guidé doté d'un système d'actionnement de commande Download PDF

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Publication number
WO2021251930A2
WO2021251930A2 PCT/TR2021/050543 TR2021050543W WO2021251930A2 WO 2021251930 A2 WO2021251930 A2 WO 2021251930A2 TR 2021050543 W TR2021050543 W TR 2021050543W WO 2021251930 A2 WO2021251930 A2 WO 2021251930A2
Authority
WO
WIPO (PCT)
Prior art keywords
wing
extends
control
shaft
control actuation
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.)
Ceased
Application number
PCT/TR2021/050543
Other languages
English (en)
Other versions
WO2021251930A3 (fr
Inventor
Mahmut Emre GÜNGÖR
Semih TANIKER
Yusuf SİLİK
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.)
Roketsan Roket Sanayi ve Ticaret AS
Original Assignee
Roketsan Roket Sanayi ve Ticaret AS
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 Roketsan Roket Sanayi ve Ticaret AS filed Critical Roketsan Roket Sanayi ve Ticaret AS
Publication of WO2021251930A2 publication Critical patent/WO2021251930A2/fr
Publication of WO2021251930A3 publication Critical patent/WO2021251930A3/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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

Definitions

  • a preferred embodiment of the present invention comprises a bridging piece that is mounted on the opposite ends of the first and the second control member such that said bridging piece extends therebetween in order to ensure that they rotate together.
  • Said bridging piece connects aerodynamic first and second control members and ensures that they move together once it is driven by the movement of the pendulum arm following the deployment position of the wing pair.
  • the motor and the shaft extend coaxially such that they are parallel to a central axis. In that case, it is ensured that the shaft efficiently transfers torque to the pendulum arm, while a compact structure is maintained within the inner chamber.
  • FIGURE 1 illustrates a perspective view of a representational embodiment of the inventive control actuation system for a guided missile system.
  • Threaded rod member (65) and the pendulum arm (82) form a Scotch-Yoke mechanism.
  • the threaded rod member (65) when rotated, the protrusion (66) transfers the rotational motion to the fork section and rotates the pendulum arm (82) together with the bridging piece (86) attached therewith on the pin (44) axis.
  • the motor (60) is connected to the main body (10) by means of a retaining body (50).
  • the retaining body (50) is a thick, circular plate.
  • a hole (54) having an appropriate diameter is created so as to accommodate the corresponding motor (60) that extends cylindrically over the retaining body (50).
  • Said hole (54), from one end to the other, is in the form of a circular bore.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Transmission Devices (AREA)
  • Toys (AREA)

Abstract

La présente invention concerne un ensemble d'actionnement de commande d'un missile miniature guidé, comprenant un siège (20) comportant une plaque de support (22) qui est montée transversalement à une chambre interne limitée par un corps principal allongé creux (10) ; et au moins deux ailes (40) comportant des premier et second éléments de commande aérodynamiques (41, 43) qui sont adjacents l'un à l'autre de sorte que leur extrémité distale (47) soit logée dans la chambre interne lorsqu'elles sont dans une position pliée, et qui sont opposés l'un à l'autre, qui sont supportés par le siège (20) au moyen de broches respectives (44) les fixant sur un axe de prolongement à partir de leur extrémité proximale (46) de sorte qu'elles s'étendent vers l'extérieur du corps principal (10) lorsqu'elles sont dans une position de déploiement. Le système d'actionnement de commande comprend un élément de tige filetée (65) qui est disposé à proximité immédiate des deux ailes (40) et qui convertit le mouvement linéaire de l'arbre (64) du moteur (60), qui comprend un arbre (64) qui s'étend vers les deux ailes (40) à l'intérieur de la chambre interne, en un mouvement de rotation de l'axe de l'arbre (64) ; et un bras pendulaire (82) qui est adapté sur les deux ailes (40) pour, d'une part, tourner sur l'axe de la broche (44) et pour, d'autre part, se loger en son sein de manière à faire tourner une saillie (66) de l'élément tige filetée (65), qui s'étend radialement vers l'extérieur.
PCT/TR2021/050543 2020-06-08 2021-06-07 Missile miniature guidé doté d'un système d'actionnement de commande Ceased WO2021251930A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2020/08781 2020-06-08
TR2020/08781A TR202008781A2 (tr) 2020-06-08 2020-06-08 Bi̇r mi̇nyatür güdümlü füze i̇çi̇n bi̇r kontrol tahri̇k terti̇bati

Publications (2)

Publication Number Publication Date
WO2021251930A2 true WO2021251930A2 (fr) 2021-12-16
WO2021251930A3 WO2021251930A3 (fr) 2022-03-03

Family

ID=78846332

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/TR2021/050543 Ceased WO2021251930A2 (fr) 2020-06-08 2021-06-07 Missile miniature guidé doté d'un système d'actionnement de commande

Country Status (2)

Country Link
TR (1) TR202008781A2 (fr)
WO (1) WO2021251930A2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12391366B1 (en) 2024-06-12 2025-08-19 Bae Systems Information And Electronic Systems Integration Inc. Lead screw control actuation system

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6761331B2 (en) * 2002-03-19 2004-07-13 Raytheon Company Missile having deployment mechanism for stowable fins
US6880780B1 (en) * 2003-03-17 2005-04-19 General Dynamics Ordnance And Tactical Systems, Inc. Cover ejection and fin deployment system for a gun-launched projectile
US6726147B1 (en) * 2003-05-15 2004-04-27 Moog Inc. Multi-function actuator, and method of operating same
US20070018033A1 (en) * 2005-03-22 2007-01-25 Fanucci Jerome P Precision aerial delivery of payloads
US8754352B2 (en) * 2010-04-07 2014-06-17 Bae Systems Information And Electronic Systems Integration Inc. Compression spring wing deployment initiator
CN103837045B (zh) * 2014-02-24 2015-05-13 中国航天时代电子公司 一种可折叠菱形弹翼展开系统

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12391366B1 (en) 2024-06-12 2025-08-19 Bae Systems Information And Electronic Systems Integration Inc. Lead screw control actuation system

Also Published As

Publication number Publication date
TR202008781A2 (tr) 2021-12-21
WO2021251930A3 (fr) 2022-03-03

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