EP0690284A1 - Aufspreizvorrichtung für den Flügel eines Geschosses - Google Patents

Aufspreizvorrichtung für den Flügel eines Geschosses Download PDF

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Publication number
EP0690284A1
EP0690284A1 EP95401557A EP95401557A EP0690284A1 EP 0690284 A1 EP0690284 A1 EP 0690284A1 EP 95401557 A EP95401557 A EP 95401557A EP 95401557 A EP95401557 A EP 95401557A EP 0690284 A1 EP0690284 A1 EP 0690284A1
Authority
EP
European Patent Office
Prior art keywords
fin
projectile
drive
lateral
fins
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
EP95401557A
Other languages
English (en)
French (fr)
Other versions
EP0690284B1 (de
Inventor
Bruno Lang
Michel Schillin
Jean-Gabriel Misse
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.)
Luchaire Defense SA
Original Assignee
Luchaire Defense SA
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Filing date
Publication date
Application filed by Luchaire Defense SA filed Critical Luchaire Defense SA
Publication of EP0690284A1 publication Critical patent/EP0690284A1/de
Application granted granted Critical
Publication of EP0690284B1 publication Critical patent/EP0690284B1/de
Anticipated expiration legal-status Critical
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 present invention relates to a device for deploying a stabilizing wing of a projectile, in particular a projectile fired by a recoilless weapon.
  • Certain projectiles in particular those fired by a smooth tube such as that of a recoilless weapon, have stabilization fins at their rear part. These fins are folded back when the projectile is in the launch tube and they deploy at the exit of this one.
  • Known deployment devices most often use springs which are kept in a tension state when the fins are folded along the body of the projectile and which relax by deploying the fin at the outlet of the launch tube.
  • Patent FR7803397 describes such a deployment device.
  • the subject of the invention is a device for deploying a stabilization fin for a projectile which is characterized in that it comprises at least one pallet, made integral with a fin by means drive, and oriented so as to receive an aerodynamic flow during the firing of the projectile and thus to transmit a resultant force to the fin in order to deploy it.
  • Another advantage of this arrangement is that it allows maximum force to be exerted at the start of the opening, when the resistant forces are also the greatest.
  • the drive means of the fin are unlockable so as to separate the deployment device and the fin from a certain opening angle of the latter.
  • the device comprises at least two pallets separated by a groove in which the fin is positioned, the groove having a bottom on which the fin comes to bear when it is in the folded position along the projectile body and which constitutes the drive means.
  • the device comprises a front wall closing the groove at a front part of the device and which constitutes an axial stop for the end of the fin.
  • the device comprises at least two lateral support feet which are in contact with an external surface of the projectile and which are held by abutment profiles carried by the projectile and arranged so as to prevent any displacement of the device in a direction perpendicular to a lateral surface of the fin.
  • the device comprises at least one pallet integral with at least two lateral drive surfaces, each of these surfaces drive being intended to receive the support of a fin different from the projectile when the latter are in the folded position along the projectile body.
  • the device comprises a tongue intended to come into abutment against a flange secured to the projectile and which constitutes an axial stop for the device.
  • the device comprises at least one wall substantially perpendicular to each drive surface and constituting an axial stop for the end of the fin considered.
  • each lateral drive surface includes a zone for holding a first lateral surface of the fin.
  • the device comprises an external guide surface with a circular profile and whose diameter is equal to that of a projectile launching tube.
  • FIG. 1 schematically represents the rear part of a projectile 1 intended to be fired by a recoilless launcher of known type (not shown).
  • This rear part comprises a flange 2 on which are fitted screeds 3 regularly angularly distributed.
  • Each yoke receives a fin 4, pivotally mounted around an axis 5.
  • the projectile thus represented therefore carries six fins 4 regularly distributed (see FIG. 2).
  • the fins 4 are shown here in their folded position along the body of the projectile 1, which is their position inside the launch tube.
  • Each fin 4 carries at a front end 4a a deployment device 6 according to the invention (here a single device is shown for clarity of the figure).
  • the device 6 comprises two paddles 7a and 7b for receiving the aerodynamic flow which appears during firing along the body la of the projectile between the front part (mark AV) and the rear part (mark AR).
  • These pallets have substantially the shape of two planes inclined with respect to the axis 8 of the projectile and perpendicular to the lateral surfaces 4b and 4c of the fin 4.
  • the inclination of the pallets relative to the axis 8 of the projectile is chosen such that the aerodynamic flow has the effect of moving the device 6 away from the body la of the projectile.
  • the device according to the invention can only be used to deploy fins which in the rest position are folded along the body of the projectile, the free ends of the fins being oriented towards the front part. of the projectile and the screeds being arranged at the rear thereof.
  • FIGS. 3a, 3b and 3c show in detail the deployment device 6.
  • This device is made for example from molded plastic (such as high density polyethylene or polyamide). The material thickness is substantially constant for the entire device.
  • Pallets 7a and 7b are connected to side walls 8a and 8b which end with lateral support legs 9a and 9b.
  • the side walls 8a, 8b are planar and substantially parallel to the side surfaces 4b, 4c of the fin 4.
  • the device after its installation on the projectile, is shaped so as to present opposite the aerodynamic flow two channels 6a, 6b whose inlet openings (arranged towards the front part AV of the projectile) have a surface greater than the outlet openings (oriented towards the rear rear part), this due to the inclination of the pallet.
  • the support feet 9a, 9b are intended to come into contact with the external surface of the body la of the projectile, they therefore have a cylindrical profile with a diameter equal to that of the body la of the projectile.
  • the two pallets 7a and 7b are separated by a groove 10 in which the fin 4 is positioned.
  • the groove 10 has a bottom 10a on which the fin comes to bear when it is in the folded position along the body 1a of the projectile.
  • the groove 10 is closed by a front wall 11 at the level of a front part of the device 6.
  • the end 4a of the fin is in axial abutment on the wall 11.
  • the fin balances the inertia forces to which the pallet is subjected when fired.
  • the width of the groove 10 will be chosen such that there is no play when the device 6 is placed on the fin.
  • the feet 9a and 9b of the device are held laterally by abutment profiles 12 carried by the projectile. These profiles 12 are arranged so as to prevent any movement of the device in a direction perpendicular to the lateral surfaces 4b, 4c of the fin 4.
  • the abutment profiles 12 could also play the role of axial abutment for the device, it would then suffice to provide a recess on each foot preventing any recoil of the device.
  • the deflection of the fin is avoided during its journey inside the launching tube, which avoids vibrations from the end of the fin at the exit of the tube and improves the deployment process and the stabilization of the projectile.
  • FIG. 2 represents in section along the plane AA of FIG. 1 the projectile 1 placed in a launching tube 13.
  • the device 6 has an external guide surface 14 whose diameter is equal to that of the launch tube 13. The device thus improves the guiding of the projectile in the launch tube.
  • the operation of the device is as follows.
  • the fins are firmly held by the device all along the path inside the launch tube.
  • the aerodynamic flow enters the openings 6a and 6b and exerts a force on the pallets 7a and 7b. This effort separates the devices 6 from the body 1a of the projectile, which has the effect of driving the fins 4 via the bottom 10a of the grooves 10 and of the partition 11.
  • All the fins are symmetrically open, mainly because, thanks to the device according to the invention, the force applied to the fin is of aerodynamic origin and it is maximum at the start of the opening. Symmetry is also favored by the absence of vibrations of the fin obtained thanks to the transverse setting provided by the stop profiles 12.
  • the device according to the invention therefore makes it possible to avoid the problems encountered with known deployment springs whose mechanical characteristics are liable to deteriorate during storage of the projectile.
  • the result of the aerodynamic forces as well as the centrifugal force which are exerted on the device 6 manage to overcome the friction between the fin and the groove 10 and cause the separation of the device and the 'fin.
  • the devices are automatically ejected and do not disturb the flight of the projectile by causing aerodynamic braking.
  • FIG. 4 thus shows by way of example a device in which the bottom 11 is set back relative to the inlet openings of the channels 6a, 6b.
  • FIG. 5 schematically represents the rear part of a projectile 1 equipped with a deployment device 15 according to a second embodiment of the invention which is intended for projectiles equipped with an even number of fins.
  • This device comprises a pallet 7 intended to receive the aerodynamic flow which appears during the firing along the body of the projectile between the front part (mark AV) and the rear part (mark AR).
  • the inclination of the pallet relative to the axis 8 of the projectile is also chosen such that the aerodynamic flow has the effect of separating the device 15 from the body 1a of the projectile.
  • FIGS 7a, 7b and 7c show in detail this deployment device.
  • the pallet 7 is connected to side walls 8a and 8b which terminate in lateral support legs 9a and 9b.
  • the side walls 8a, 8b are planar and substantially parallel to the side surfaces 4b, 4c of the fin 4.
  • the device after its installation on the projectile, is shaped so as to present, facing the aerodynamic flow, a channel 15a whose inlet opening (disposed towards the front part AV of the projectile) has a surface greater than that of the outlet opening (oriented towards the rear part AR).
  • the support feet 9a, 9b come into contact with the external surface of the body la of the projectile, they have a cylindrical profile with a diameter equal to that of this body.
  • Each surface 16a, 16b therefore receives a different fin when the latter are in the folded position along the body la of the projectile.
  • the feet 9a, 9b also carry holding zones 17a, 17b which are each in contact with a lateral surface of the fin considered.
  • three devices 15 according to the invention make it possible to deploy six fins.
  • Each fin is held laterally on one side by a holding zone 17 carried by one of the devices 15 and on the other by a stop profile 18 secured to a flange 19 also made of plastic and made integral with the body of projectile, for example by bonding.
  • the flanges are offset axially relative to the device, this so that the flanges do not prevent the opening of the fin.
  • the dimensions of the devices 15 and of the flanges 19 will be chosen so that there is no play when it is placed on the fin.
  • Such an arrangement makes it possible to immobilize the ends of the fins, which prevents vibrations during shooting and improves the deployment process and the stabilization of the projectile.
  • Each device 15 finally comprises a rear tongue 20 which is intended to come into abutment against a flange 21 of the projectile and which constitutes an axial stop for the device.
  • the tongue also makes it possible to locate, at the rear flange and at an equal distance from each fin, the pivot point of the device. Such an arrangement ensures symmetrical opening of the two fins by the device.
  • the device 15 has an external guide surface 14 whose diameter is equal to that of the launch tube 13. The device thus improves the guiding of the projectile in the launch tube.
  • the deployment device is still ejected from a certain angle of opening of the fins.
  • An advantage of this embodiment is that it makes it possible to eject the device very quickly, which reduces its action to a simple initial impulse on the fins which then terminate their opening by inertia and by the effect of their own drag.
  • the rapid ejection of the device also has the advantage of limiting the angular speed of the fin at the end of the stroke, which limits the rebounds of the fin and improves the stabilization of the projectile.
  • the distance between the ends of two neighboring fins increases during opening.
  • the fins are therefore quickly released from the drive surfaces 16a, 16b and it is possible to precisely determine the instant of ejection of the device by adjusting the dimensions of the drive surfaces 16a, 16b and in particular over the length L ( see Figures 6 and 7a).
  • Another advantage of this embodiment is that it makes it possible to reduce the number of devices used for a projectile, and therefore the cost of production.
  • a deployment device which would remain integral with the fin even after deployment.
  • Such a device would for example include one or more pallets fixed to the side walls of each fin.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Pallets (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Iron Core Of Rotating Electric Machines (AREA)
EP95401557A 1994-06-28 1995-06-28 Aufspreizvorrichtung für den Flügel eines Geschosses Expired - Lifetime EP0690284B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9407953A FR2721702B1 (fr) 1994-06-28 1994-06-28 Dispositif de déploiement d'une ailette de projectile.
FR9407953 1994-06-28

Publications (2)

Publication Number Publication Date
EP0690284A1 true EP0690284A1 (de) 1996-01-03
EP0690284B1 EP0690284B1 (de) 1999-09-15

Family

ID=9464743

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95401557A Expired - Lifetime EP0690284B1 (de) 1994-06-28 1995-06-28 Aufspreizvorrichtung für den Flügel eines Geschosses

Country Status (7)

Country Link
US (1) US5685503A (de)
EP (1) EP0690284B1 (de)
DE (1) DE69512146T2 (de)
ES (1) ES2138165T3 (de)
FR (1) FR2721702B1 (de)
IL (1) IL114383A (de)
ZA (1) ZA955302B (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7919740B2 (en) 2007-01-19 2011-04-05 Diehl Bgt Defence Gmbh & Co. Kg Wing-unfolding apparatus, folding wing assembly, and vehicle with folding wing assemblies

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19827278A1 (de) * 1998-06-19 1999-12-23 Diehl Stiftung & Co Lenkbarer Flugkörper
DE10118216A1 (de) * 2001-04-12 2002-10-17 Diehl Munitionssysteme Gmbh Ruderblatt-Lagereinrichtung für ein Geschoß
US6691948B1 (en) 2003-04-10 2004-02-17 The United States Of America As Represented By The Secretary Of The Navy High torque rocket nozzle
FR2864612B1 (fr) 2003-12-24 2007-11-23 Giat Ind Sa Dispositif de deploiement des ailettes d'un projectile
US7262394B2 (en) * 2004-03-05 2007-08-28 The Boeing Company Mortar shell ring tail and associated method
US7984676B1 (en) 2007-06-29 2011-07-26 Taser International, Inc. Systems and methods for a rear anchored projectile
WO2009005540A1 (en) * 2007-06-29 2009-01-08 Taser International, Inc. Systems and methods for a projectile having a stabilizer for spin stabilization
US7856929B2 (en) 2007-06-29 2010-12-28 Taser International, Inc. Systems and methods for deploying an electrode using torsion
FI120709B (fi) * 2008-01-31 2010-01-29 Patria Weapon Systems Oy Tukielin kranaatin tukemiseksi ja menetelmä
RU2462685C1 (ru) * 2011-02-15 2012-09-27 Николай Евгеньевич Староверов Многоэлементный патрон староверова (варианты)
US9212877B2 (en) * 2012-07-05 2015-12-15 The United States Of America As Represented By The Secretary Of The Army Retention system for a deployable projectile fin
RU2512041C1 (ru) * 2012-11-13 2014-04-10 Открытое акционерное общество "Конструкторское бюро приборостроения" Стабилизатор снаряда
RU2551299C1 (ru) * 2014-06-26 2015-05-20 Открытое акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Способ испытаний артиллерийского снаряда
FR3041744B1 (fr) * 2015-09-29 2018-08-17 Nexter Munitions Projectile d'artillerie ayant une phase pilotee.
RU2651671C1 (ru) * 2017-01-17 2018-04-23 Акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Выстреливаемая из пусковой трубы ракета
FR3071917B1 (fr) * 2017-10-04 2021-11-19 Nexter Munitions Dispositif de blocage d'ailette et projectile comportant un tel dispositif
US20230072799A1 (en) * 2021-09-03 2023-03-09 Raytheon Company Control surface restraining system for tactical flight vehicles

Citations (4)

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Publication number Priority date Publication date Assignee Title
US2666387A (en) * 1949-12-07 1954-01-19 United Aircraft Corp Stabilizing fins for missiles
FR2070389A5 (de) * 1969-12-03 1971-09-10 Serat
GB2115117A (en) * 1982-02-10 1983-09-01 Gen Dynamics Corp Wing housing and cover release assembly for self-erecting wing
GB2136930A (en) * 1983-03-17 1984-09-26 Diehl Gmbh & Co A fin-stabilised projectile with propelling cage

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US2427217A (en) * 1943-09-23 1947-09-09 Harry J Lebherz Rocket fin assembly
NL106348C (de) * 1959-03-09
US3188957A (en) * 1962-04-03 1965-06-15 Aerojet General Co Ring stabilizer
CH552189A (de) * 1972-05-10 1974-07-31 Oerlikon Buehrle Ag Treibspiegelgeschoss.
DE2264338A1 (de) * 1972-12-30 1974-07-04 Dynamit Nobel Ag Ausklappbares leitwerk, insbesondere fuer raketen
FR2221707B1 (de) * 1973-03-14 1976-04-30 France Etat
DE2721536A1 (de) * 1977-05-13 1978-11-16 Brunsch Kurt Projektil mit leitflaechen
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
US4158447A (en) * 1977-11-29 1979-06-19 The United States Of America As Represented By The Secretary Of The Navy Expanding stabilizing fin cup
US4332360A (en) * 1980-07-21 1982-06-01 The United States Of America As Represented By The Secretary Of The Army Automatically deployed shell fins
IL72000A (en) * 1984-06-04 1989-09-10 Israel State Projectile stabilization system
US4667899A (en) * 1984-11-28 1987-05-26 General Dynamics, Pomona Division Double swing wing self-erecting missile wing structure
SE444612B (sv) * 1984-12-13 1986-04-21 Ffv Affersverket Styrverk for utfellning av fenor hos projektil
GB8815060D0 (en) * 1988-06-24 1988-11-16 British Aerospace Fin assembly for projectile

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2666387A (en) * 1949-12-07 1954-01-19 United Aircraft Corp Stabilizing fins for missiles
FR2070389A5 (de) * 1969-12-03 1971-09-10 Serat
GB2115117A (en) * 1982-02-10 1983-09-01 Gen Dynamics Corp Wing housing and cover release assembly for self-erecting wing
GB2136930A (en) * 1983-03-17 1984-09-26 Diehl Gmbh & Co A fin-stabilised projectile with propelling cage

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7919740B2 (en) 2007-01-19 2011-04-05 Diehl Bgt Defence Gmbh & Co. Kg Wing-unfolding apparatus, folding wing assembly, and vehicle with folding wing assemblies

Also Published As

Publication number Publication date
ES2138165T3 (es) 2000-01-01
FR2721702A1 (fr) 1995-12-29
IL114383A (en) 1998-12-06
FR2721702B1 (fr) 1996-08-14
ZA955302B (en) 1996-12-23
DE69512146D1 (de) 1999-10-21
IL114383A0 (en) 1995-10-31
DE69512146T2 (de) 2000-01-27
EP0690284B1 (de) 1999-09-15
US5685503A (en) 1997-11-11

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