EP0275766A1 - Bremsmechanismus für entfaltbare Flügel und Fernlenkgeschoss mit diesem Mechanismus - Google Patents

Bremsmechanismus für entfaltbare Flügel und Fernlenkgeschoss mit diesem Mechanismus Download PDF

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Publication number
EP0275766A1
EP0275766A1 EP87402911A EP87402911A EP0275766A1 EP 0275766 A1 EP0275766 A1 EP 0275766A1 EP 87402911 A EP87402911 A EP 87402911A EP 87402911 A EP87402911 A EP 87402911A EP 0275766 A1 EP0275766 A1 EP 0275766A1
Authority
EP
European Patent Office
Prior art keywords
wing
pin
deformation part
deployment
rotation
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
EP87402911A
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English (en)
French (fr)
Other versions
EP0275766B1 (de
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
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Filing date
Publication date
Application filed by Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0275766A1 publication Critical patent/EP0275766A1/de
Application granted granted Critical
Publication of EP0275766B1 publication Critical patent/EP0275766B1/de
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Expired - Lifetime 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 invention relates to deployable wings, such as those used on missiles, self-propelled rockets and the like, which will hereinafter be called guided projectiles. It relates in particular to a braking system for the deployment of these wings.
  • Deployable fins are known, which are articulated on the body of the projectile around longitudinal axes, parallel to the longitudinal axis of the body. These fins are tangential to this body in the folded position, and located in radial axial planes, in the active position.
  • This kind of empennage has a major drawback due to the brutality of the deployment of the fins. Indeed, this movement is caused mechanically either by pistons or by pyrotechnic devices which tend to spread the wings of the body of the projectile. Once these wings are spread, the increase in the speed of the projectile at the time of deployment, and the increase in speed of the rotation of the fins, due to the increase in the surface of the wing deploying, cause the latter to arrive in the deployed position at a considerable speed, and therefore with sufficient energy to damage either the fin itself or the abutment elements which hold it in this deployed position.
  • the invention proposes to remedy this drawback by proposing a system for braking the deployment of the fin to avoid this sudden stop in the deployed position, and the deterioration of a fin set mounted on a guided projectile.
  • the French patent application published under No. 2448707 discloses a vane assembly for flying craft, where a vane is rotatable about an axis tangential to the body of the machine, on a turntable, as may - even turn around an axis transverse to the machine.
  • This rotation is carried out by endless screws which transmit the rotational movement to the turntable, during the rotation of the fin about the tangential axis.
  • the fin is first applied against the surface of the flying object, its axis being directed tangentially and transversely to the longitudinal axis of the object. During the straightening, the fin rotates so that its axis is parallel to the longitudinal axis of the flying object.
  • a braking mechanism acting on the turntable to delay the rotational movement of the latter, and therefore, the deployment of the fin.
  • This device involves too many moving mechanical parts (turntable, worm, ).
  • the object of the invention is to provide another simpler braking device which acts directly on the fin, and a guided projectile equipped with such a device.
  • the invention consists in involving a thread and a deformation piece which by their combined effects allow regulation of the speed of deployment of the wing and the absorption of a maximum part of the kinetic energy due to this deployment, the remaining energy being calibrated so as not to alter the geometry of the airfoil or the supporting structure.
  • FIG. 1A a cross-sectional view along the axis A, A ⁇
  • the fin 20 is shown in the folded position against the body of the projectile 21. It is pivotally mounted relative to the body, about an axis A, A ⁇ which is oblique to the longitudinal axis of the body, and this as well with respect to the plane of the fin, that is to say along the plane in FIG. 1A, than with respect to the plane perpendicular to the plane of the fin, that is to say the plane of FIG. 1A, than with respect to the plane perpendicular to the plane of the fin, that is to say with respect to in the plane of FIG. 1B.
  • the rotation of the fin 20 around this axis brings the latter into its deployed position, that is to say that it is always pressed against the body of the missile 21, but its plane is perpendicular to the plane it occupied in the folded position.
  • the wing 6 is shown in the case of an oblique joint, such as that described in the previous paragraph, but provided with a braking device according to the invention.
  • This consists mainly of means for transforming the kinetic energy of rotation into translation energy which, by the effect of the thread and the deformation part, absorb a maximum part of the speed and give the wing a regular deployment.
  • the wing 6 is integral with a pin 1 which allows the rotation of this wing, relative to the body of the projectile.
  • the pin 1 is mounted to rotate about its axis X X ⁇ which is fixed relative to a body 2.
  • the means for transforming the kinetic energy of rotation into translation energy further comprise means for locking in translation relative to the body 2 of the journal 1.
  • These energy transformation means also comprise a ring 4 which is called the compression ring and which is screwed onto a thread 10, formed on the outside diameter of the journal 1.
  • the means of transformation of the energy also include means for locking in rotation relative to the body 2 of this compression tank 4.
  • the energy transformation means comprise a stop in translation around the pin 1.
  • the deformation part 5 is placed between this translation stop and the compression ring 4.
  • the length of this ring is less than the distance separating the stop from a shoulder 14 of the compression ring 4, so that there remains a clearance E in length when the wing is in the folded position.
  • Trunnion 1 is mounted rotating around its axis X X ⁇ by means of a bearing 3, integral with body 2.
  • the inside diameter of this trunnion actually has a recess corresponding to a shoulder 11 of the trunnion 1, so that the latter either blocked in translation relative to the body 2, so as not to move in the direction indicated by the arrow F.
  • a second bearing is produced using the compression ring 4 which is fixed in rotation relative to the body 2.
  • the rotation ring of this compression ring is made by two flats, not shown, and made on the outside diameter 12 of the compression ring 4.
  • This ring has a lateral face 14 against which the deformation piece comes to bear. 5.
  • this deformation part is shown in the form of a flattened U, but this form is not limiting.
  • the system works as follows.
  • the wing 6 is caused to pivot about the axis X, X ⁇ it drives the pin 1 which is integral with it. Due to this rotation, and the fact that the compression ring 4 is mounted screwed around this axis and locked in translation relative to the body 2, the latter moves in translation inside the hole 13.
  • the direction of thread screw 10 of the journal 1 and the internal thread of the compression ring 4 are chosen so that the compression ring moves towards the first bearing 3 so as to compress the deformation piece 5 between a surface radial 15 of the first bearing 3 and the radial surface 14 of the compression ring 4.
  • a minimum clearance be provided between the thread 10 and the internal thread of the compression housing, a minimum clearance be provided.
  • the internal thread and the thread may be with several threads, which allows better mechanical resistance of the system, and greater displacement in translation of the compression part.
  • Deployment of the wing at substantially constant speed is only possible, if an additional device gives it a sufficient incidence at the start, for the air current to make it deploy. To do this, it is necessary that the wing has a free rotation at the start of its deployment before the braking phase. Depending on the case, this rotation can vary from 20 to 60 degrees.
  • the deformation piece 5 must therefore have a length such that, in the folded position of the wing, there remains the clearance E between the end 7 opposite the compression ring 4 and the radial face 15 of the bearing 3. This clearance E corresponds to the translation of the compression ring 4 during this free rotation phase.
  • the additional incidence setting device can be produced by means of a piston actuated by the action of gases generated by a charge placed on board the projectile, and ignited by an electric igniter or a mechanical striker.
  • the deformation part 5 can absorb energy in several ways.
  • this compression part has a tubular shape reinforced at these ends, so as to represent a flattened U.
  • this part When this part is compressed, there is a buckling of its central part, the material of this central part partially filling the interior of the U.
  • the materials used can be copper, aluminum, or any relatively malleable alloy and ductile.
  • the compression ring 34 and the deformation part 35 have shapes different from those of the previous embodiment.
  • the compression ring 34 is always free in translation and fixed in rotation, so as to translate towards the deformation part 35.
  • the actual deformation does not occur in the same way, because the deformation part, although being always tubular, has a more compact shape, and its internal diameter is adjusted to that of the axis 31. It is always in abutment on the radial surface 15 of the first bearing 33.
  • the opposite end receives the action of the compression ring 34 which is directed towards the part deformation 35. Longitudinal compression by buckling of the latter is no longer possible, due to the compactness of this part.
  • the deformation piece 35 may be made of a more or less viscous material, depending on whether an elastomer or a grease is used.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Vibration Dampers (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP87402911A 1986-12-23 1987-12-18 Bremsmechanismus für entfaltbare Flügel und Fernlenkgeschoss mit diesem Mechanismus Expired - Lifetime EP0275766B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8618084 1986-12-23
FR8618084A FR2608750A1 (fr) 1986-12-23 1986-12-23 Dispositif de freinage du deploiement d'une aile et projectile guide equipe d'un tel dispositif

Publications (2)

Publication Number Publication Date
EP0275766A1 true EP0275766A1 (de) 1988-07-27
EP0275766B1 EP0275766B1 (de) 1990-08-29

Family

ID=9342240

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87402911A Expired - Lifetime EP0275766B1 (de) 1986-12-23 1987-12-18 Bremsmechanismus für entfaltbare Flügel und Fernlenkgeschoss mit diesem Mechanismus

Country Status (4)

Country Link
US (1) US4852828A (de)
EP (1) EP0275766B1 (de)
DE (1) DE3764633D1 (de)
FR (1) FR2608750A1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2237362A (en) * 1989-10-24 1991-05-01 British Aerospace Projectile retardation system
GB2256622A (en) * 1991-06-14 1992-12-16 Diehl Gmbh & Co Flying body with mechanism for deploying control fins.

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2657703B1 (fr) * 1990-01-26 1992-04-10 Thomson Brandt Armements Dispositif pour la commande d'attitude en roulis d'un projectile stabilise par empennage.
SE544263C2 (en) 2020-07-03 2022-03-22 Saab Ab A wing arrangement, a projectile, a method for deploying a wing blade, a use and a method for assembly

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3785290A (en) * 1971-03-01 1974-01-15 Us Navy Bomb fin shock absorber assembly
US4143838A (en) * 1977-08-22 1979-03-13 The United States Of America As Represented By The Secretary Of The Navy Folding fin assembly detent
US4175720A (en) * 1978-04-05 1979-11-27 The United States Of America As Represented By The Secretary Of The Navy Retainer/release mechanism for use on fin stabilized gun fired projectiles

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3819132A (en) * 1973-02-21 1974-06-25 Sarmac Sa Self propelled projectile with fins
US4323208A (en) * 1980-02-01 1982-04-06 British Aerospace Folding fins

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3785290A (en) * 1971-03-01 1974-01-15 Us Navy Bomb fin shock absorber assembly
US4143838A (en) * 1977-08-22 1979-03-13 The United States Of America As Represented By The Secretary Of The Navy Folding fin assembly detent
US4175720A (en) * 1978-04-05 1979-11-27 The United States Of America As Represented By The Secretary Of The Navy Retainer/release mechanism for use on fin stabilized gun fired projectiles

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2237362A (en) * 1989-10-24 1991-05-01 British Aerospace Projectile retardation system
GB2237362B (en) * 1989-10-24 1994-01-19 British Aerospace Retardation and arming mechanism for a projectile
GB2256622A (en) * 1991-06-14 1992-12-16 Diehl Gmbh & Co Flying body with mechanism for deploying control fins.
GB2256622B (en) * 1991-06-14 1995-01-04 Diehl Gmbh & Co A flying body having rudder or control blades

Also Published As

Publication number Publication date
FR2608750B1 (de) 1993-02-26
DE3764633D1 (de) 1990-10-04
FR2608750A1 (fr) 1988-06-24
EP0275766B1 (de) 1990-08-29
US4852828A (en) 1989-08-01

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