EP0251890A1 - Mehrfache Entfaltung eines Flügels und seine Anwendung an einem Flugkörper - Google Patents

Mehrfache Entfaltung eines Flügels und seine Anwendung an einem Flugkörper Download PDF

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Publication number
EP0251890A1
EP0251890A1 EP87401434A EP87401434A EP0251890A1 EP 0251890 A1 EP0251890 A1 EP 0251890A1 EP 87401434 A EP87401434 A EP 87401434A EP 87401434 A EP87401434 A EP 87401434A EP 0251890 A1 EP0251890 A1 EP 0251890A1
Authority
EP
European Patent Office
Prior art keywords
wing
primary
wings
axis
deployment
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Withdrawn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
EP87401434A
Other languages
English (en)
French (fr)
Inventor
Robert Baldovi
Jean-Baptiste Koppel
Jean-Pierre Roux
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 EP0251890A1 publication Critical patent/EP0251890A1/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Withdrawn legal-status Critical Current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

Definitions

  • the present invention relates to a multi-deployment wing, fitted to a projectile or a missile such as a missile. Provision is made to equip said missile with two or four wings, the latter each having a folded position in which they are not operational, and at least one deployed position in which they are operational.
  • Projectiles or missiles such as military missiles are often fitted with folding fins to allow optimized containment of several missiles inside a carrier container, before these missiles are dropped or exploded from the container. When the missile or projectile is operational, the fins are deployed to assume their stabilization function.
  • the object of the invention is to remedy this drawback by designing a deployable wing of a different design which does not give rise to the drawback mentioned in the preceding paragraph.
  • we several different shapes of the wing are required in the deployed position, according to the different navigation conditions, and in particular according to the speed of the projectile.
  • a first object of the invention is a multiple deployment wing intended to equip a flying machine with a longitudinal axis relative to the body of which it takes a folded position, and several operational positions by successive deployment, characterized in that it comprises a primary wing and at least one secondary wing which can be housed inside said primary wing, and in that said primary wing is fixed to said body by a first articulation around a first axis parallel to the body so that the wing can be folded down so that said primary wing can be applied against the body tangentially.
  • a second object of the invention is a flying machine equipped with a wing as defined in the paragraph above.
  • the cylindrical body 2 of the machine with a longitudinal axis OX is equipped with four wings according to the invention.
  • This number is not limitative.
  • Each wing consists of a primary wing 1 articulated on the body according to a rotation about an axis OY parallel to the longitudinal axis OX of the body. The rotation movement of this primary wing around its axis OY, as well as the deployment position thereof, has been shown in broken lines.
  • a secondary wing 3 is housed in a retaining chamber 4.
  • This secondary wing is articulated on the primary wing along an axis OZ perpendicular to the longitudinal axis OX of the projectile and perpendicular to the primary wing 1.
  • the wings have been folded towards each other in pairs, the joints being arranged at the periphery of the body every 90 °.
  • the wings have the same shape as those shown in Figure 1, but their position relative to the body is different.
  • one of the two pairs has been inverted in its first position, called storage, which means that, to arrive at the second position called operation or deployment, the rotation of all the wings is done in the Same direction.
  • the space occupied by this storage position does not have the same shape as the space defined by the position drawn in FIG. 1.
  • This arrangement according to FIG. 2 can be envisaged for a larger number of wings. by machine.
  • the machine is equipped with wings shown in the deployed position.
  • the primary wings 1 have made a rotation of approximately 90 ° around their axis of rotation OY.
  • the secondary wing 3 housed entirely in the primary wing.
  • These secondary wings have approached approximately the same width as the primary wings. They are mounted so as to articulate around an axis OZ perpendicular to the primary wings situated approximately in the middle of the width of the primary wings and practically at the front end 13 thereof, so that each secondary wing can pivot relative to the primary wing to deploy.
  • FIG. 4 This deployment position is described in FIG. 4, in which these secondary wings identified 3 are practically perpendicular to the longitudinal axis of the machine, thus forming a wing with maximum wingspan used for subsonic speeds.
  • This pivoting of the secondary wing relative to the primary wing is therefore made perpendicular to the first pivoting of the primary wing relative to the machine.
  • the invention provides, to improve the lift performance, of adding a tertiary wing 5 housed inside the secondary wing in a slot 6 when it is not operational.
  • This tertiary wing 5 is articulated relative to the secondary wing 3 about an axis OZ ⁇ , parallel to the axis OZ of articulation of the secondary wing on the primary wing and located practically at the rear end 7 of the secondary wing 5.
  • this tertiary wing 5 is such that, when the secondary wing 3 is deployed, this tertiary wing can pivot around the axis OZ ⁇ so as to complete the bearing surface of the wing secondary.
  • the shapes of these secondary and tertiary wings, as well as the deployment position as shown in Figure 7, are not limited to this representation.
  • the angle of deployment of the secondary wing 3 relative to the longitudinal axis OX of the machine can vary, as well as the pivoting angle of the tertiary wing 5 relative to the secondary wing.
  • the secondary wing has an approximately constant width, and the deployment angle is slightly less than 90 °.
  • the tertiary wing 5 fills the uncovered surface between the rear end 7 of the secondary wing deployed and the body of the machine.
  • a guide groove is provided for this purpose. 11, made inside the slot 4 of the primary wing 1, and in which a tenon 12 can slide, integral with the tertiary wing 5.
  • the secondary wing 3 is deployed relative to the 'primary wing 1
  • the tenon 12 is forced to follow the groove and allows the tertiary wing 5 to pivot about its axis OZ ⁇ so as to cover the surface determined between the secondary wing and the primary wing.
  • the length, shape and orientation of the groove 11 are calculated according to the deployment angles and the shapes of the secondary and tertiary wings.
  • the length of the tertiary wing 5 is also provided sufficient so that, the secondary wing 3 once deployed, the tertiary wing 5 is still in contact with the primary wing 1. This embodiment is not limiting.
  • FIG. 5B shows in section the manner in which the primary, secondary and tertiary wings are housed one inside the other. It can be noted that the secondary 3 and tertiary 5 wings do not have a constant section. These are slightly rounded because they have a large deployment angle and their profile is calculated according to the optimal air flow along these wings. The largest section of the secondary wing 3 is in the middle, the ends being of minimum thickness.
  • the articulation of the primary wing relative to the body around the longitudinal axis OY allows the wings to be folded along the body in order to obtain a minimum bulk in a container.
  • the deployment of the primary wing makes it possible to stabilize the craft at supersonic speed, with low deployment constraints.
  • the deployment of the secondary wing makes it possible to obtain a relatively high fineness ratio.
  • this tertiary wing can come to bear on the primary wing 1 by its rear end 13. This makes it possible to relieve the secondary wing in the air resistance efforts, these efforts being partially transferred via the tertiary wing 5 to the primary wing 1.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
EP87401434A 1986-06-27 1987-06-23 Mehrfache Entfaltung eines Flügels und seine Anwendung an einem Flugkörper Withdrawn EP0251890A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8609357A FR2600618A1 (fr) 1986-06-27 1986-06-27 Aile a deploiement multiple, et son application a un engin volant
FR8609357 1986-06-27

Publications (1)

Publication Number Publication Date
EP0251890A1 true EP0251890A1 (de) 1988-01-07

Family

ID=9336802

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87401434A Withdrawn EP0251890A1 (de) 1986-06-27 1987-06-23 Mehrfache Entfaltung eines Flügels und seine Anwendung an einem Flugkörper

Country Status (2)

Country Link
EP (1) EP0251890A1 (de)
FR (1) FR2600618A1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4844381A (en) * 1987-09-08 1989-07-04 Diehl Gmbh & Co. Airborne submunition member
US4869442A (en) * 1988-09-02 1989-09-26 Aerojet-General Corporation Self-deploying airfoil
US5108051A (en) * 1987-11-26 1992-04-28 L'etat Francais Represente Par Le Delegue General Pour L'armement Deployment mechanism of a projectile fin
EP0811822A1 (de) * 1996-06-07 1997-12-10 Gec-Marconi Dynamics Inc. Ausfaltbares Flügelelement
US6220544B1 (en) * 1998-06-19 2001-04-24 Diehl Stiftung & Co. Guided missile
GB2388094A (en) * 1986-08-12 2003-11-05 Aerospatiale Missile with variable flying surface
CN106005413A (zh) * 2016-07-22 2016-10-12 珠海银通农业科技有限公司 多元化折叠式无人机
CN107161322A (zh) * 2017-05-05 2017-09-15 西北工业大学 一种变后掠短距起降固定翼飞行器

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103123292B (zh) * 2013-01-07 2015-07-08 西北工业大学 折叠翼气动加载展开实验装置
CN103879556B (zh) * 2014-03-31 2016-03-02 冯加伟 宽飞行包线变体飞行器
CN104457443A (zh) * 2014-11-24 2015-03-25 江西洪都航空工业集团有限责任公司 一种用于层叠式折叠翼上下加载装置

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1199664B (de) * 1962-09-11 1965-08-26 Dynamit Nobel Ag Klappleitwerk, insbesondere fuer Raketengeschosse
FR1436334A (fr) * 1965-05-22 1966-04-22 Contraves Ag Petites roquettes à quatre ailerons stabilisateurs
US3853288A (en) * 1967-07-17 1974-12-10 H Bode Encasement for the tail section of a rocket with a central nozzle and extendible control vanes
EP0013096A1 (de) * 1978-12-29 1980-07-09 The Commonwealth Of Australia Anordnung für ausklappbare Flügelflächen
FR2564189A1 (fr) * 1984-05-09 1985-11-15 Diehl Gmbh & Co Ailette rabattable, notamment pour projectile

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1199664B (de) * 1962-09-11 1965-08-26 Dynamit Nobel Ag Klappleitwerk, insbesondere fuer Raketengeschosse
FR1436334A (fr) * 1965-05-22 1966-04-22 Contraves Ag Petites roquettes à quatre ailerons stabilisateurs
US3853288A (en) * 1967-07-17 1974-12-10 H Bode Encasement for the tail section of a rocket with a central nozzle and extendible control vanes
EP0013096A1 (de) * 1978-12-29 1980-07-09 The Commonwealth Of Australia Anordnung für ausklappbare Flügelflächen
FR2564189A1 (fr) * 1984-05-09 1985-11-15 Diehl Gmbh & Co Ailette rabattable, notamment pour projectile

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2388094A (en) * 1986-08-12 2003-11-05 Aerospatiale Missile with variable flying surface
GB2388094B (en) * 1986-08-12 2004-04-07 Aerospatiale Missile with variable flying surface
US4844381A (en) * 1987-09-08 1989-07-04 Diehl Gmbh & Co. Airborne submunition member
US5108051A (en) * 1987-11-26 1992-04-28 L'etat Francais Represente Par Le Delegue General Pour L'armement Deployment mechanism of a projectile fin
US4869442A (en) * 1988-09-02 1989-09-26 Aerojet-General Corporation Self-deploying airfoil
EP0811822A1 (de) * 1996-06-07 1997-12-10 Gec-Marconi Dynamics Inc. Ausfaltbares Flügelelement
US6220544B1 (en) * 1998-06-19 2001-04-24 Diehl Stiftung & Co. Guided missile
CN106005413A (zh) * 2016-07-22 2016-10-12 珠海银通农业科技有限公司 多元化折叠式无人机
CN107161322A (zh) * 2017-05-05 2017-09-15 西北工业大学 一种变后掠短距起降固定翼飞行器

Also Published As

Publication number Publication date
FR2600618A1 (fr) 1987-12-31

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Inventor name: ROUX, JEAN-PIERRE

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Inventor name: BALDOVI, ROBERT

Inventor name: LAMARQUE, ETIENNE