EP0690284B1 - Aufspreizvorrichtung für den Flügel eines Geschosses - Google Patents

Aufspreizvorrichtung für den Flügel eines Geschosses Download PDF

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Publication number
EP0690284B1
EP0690284B1 EP95401557A EP95401557A EP0690284B1 EP 0690284 B1 EP0690284 B1 EP 0690284B1 EP 95401557 A EP95401557 A EP 95401557A EP 95401557 A EP95401557 A EP 95401557A EP 0690284 B1 EP0690284 B1 EP 0690284B1
Authority
EP
European Patent Office
Prior art keywords
projectile
fin
lateral
deployment
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.)
Expired - Lifetime
Application number
EP95401557A
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English (en)
French (fr)
Other versions
EP0690284A1 (de
Inventor
Christian Trouillot
Alain Verstraete
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
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 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 deployment of a projectile stabilization wing, including a projectile fired by a recoilless weapon.
  • Certain projectiles notably those fired by a tube smooth like that of a recoilless weapon, have stabilization fins at their rear. These fins are folded back when the projectile is in the tube launch and they deploy at the exit of this one.
  • the known deployment devices put the most often using springs which are kept in good condition tension when the fins are folded along the body of the projectile and which relax by deploying the fin at the exit from the launch tube.
  • Patent FR7803397 describes such a device for deployment.
  • the patent GB2136930 which represents the preambles of claims 1 and 4, describes a sub-calibrated projectile in which the deployment of the fin is ensured by the aerodynamic flow exerted on the front end fin. The efficiency of such a system is reduced and the deployment symmetry is not guaranteed.
  • a fin deployment device stabilization for a projectile comprising at least one pallet, made integral with a fin by means drive, and oriented to receive a flow aerodynamics when firing the projectile and transmitting thus an effort resulting in the fin in order to deploy it, device characterized in that it comprises at least two pallets separated by a groove in which is positioned the fin, the groove having a bottom on which the fin comes into support when it is in the folded position on along the projectile body, bottom which constitutes the means which is unlockable so as to separate the deployment device and the fin from a certain opening angle of the latter.
  • the device will advantageously include a wall front closing the groove at a front part of the device and constituting an axial stop for the end fin.
  • It may include at least two lateral support feet which are in contact with an external surface of the projectile and which are held by stop profiles carried by the projectile and arranged to prevent displacement of the device in a direction perpendicular to a lateral surface of the fin.
  • the stabilizer fin deployment device is characterized in that it comprises at least one pallet secured to at least two lateral drive surfaces, each of these drive surfaces being intended for receive support from a different wing of the projectile when the latter are in the folded position along of the projectile body, lateral drive surfaces which constitute the means of training which is unlockable so as to separate the deployment device and the fin from a certain opening angle of the latter.
  • This device may include a tab intended to come into abutment against a flange secured to the projectile and which constitutes an axial stop for the device.
  • It may include at least one substantially wall perpendicular to each drive surface and constituting an axial stop for the end of the fin considered.
  • Each lateral drive surface may include a zone for holding a first lateral surface of the fin.
  • the device according to the invention may include a external guide surface with circular profile and the diameter is equal to that of a launch tube of the projectile.
  • An advantage of the invention is that it makes it possible to avoid, to open a fin, the use of potential energy elastic stored in springs.
  • Another advantage of the invention is that it allows exert maximum force at the start of the opening, when the resistant efforts are also the greatest.
  • the invention also makes it possible to avoid any drag residual aerodynamics caused by the device. In releasing the fin early enough we also limit rebounds of the latter.
  • Figure 1 shows schematically the rear part a projectile 1 intended to be fired by a launcher without known type of recoil (not shown).
  • This rear part includes a flange 2 on which are arranged screeds 3 regularly distributed angularly. Each yoke receives a fin 4, mounted pivoting around an axis 5.
  • the projectile thus represented therefore carries six fins 4 regularly distributed (see figure 2).
  • the fins 4 are represented here in their position folded along the body of projectile 1, position which is theirs inside the launch tube.
  • Each fin 4 carries at a front end 4a a deployment device 6 according to the invention (here a only device is shown for clarity of the figure).
  • the device 6 comprises two pallets 7a and 7b for receiving the aerodynamic flow that appears when firing along of the body of the projectile between the front part (AV mark) and the rear part (AR mark).
  • These pallets have substantially the shape of two planes inclined 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 axis 8 of the projectile is chosen such that aerodynamic flow has the effect of removing the device 6 from the body 1a 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 in material molded plastic (such as high density polyethylene or polyamide). The material thickness is substantially constant for the whole device.
  • Pallets 7a and 7b are connected to side walls 8a and 8b which are end with lateral support feet 9a and 9b.
  • the side walls 8a, 8b are flat and substantially parallel to the lateral surfaces 4b, 4c of the fin 4.
  • the device after being placed on the projectile, is shaped so as to present opposite aerodynamic flow two channels 6a, 6b whose inlet openings (arranged towards the front part of the projectile) have a surface greater than the openings of outlet (oriented towards the rear part AR), this due the tilt of the pallet.
  • the support feet 9a, 9b are intended to come into contact with the external surface of the projectile body 1a, they have therefore a cylindrical profile with a diameter equal to that of the body 1a 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 into support when it is in the folded position on along the projectile body 1a.
  • 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 subject the pallet when firing.
  • the width of the groove 10 will be chosen such that it there is no play when installing the device 6 on the fin.
  • the feet 9a and 9b of the device are maintained laterally by stop profiles 12 carried by the projectile. These profiles 12 are arranged so as to prevent any movement of the device in a perpendicular direction to the lateral surfaces 4b, 4c of the fin 4.
  • stop profiles 12 could also play the role of axial stop for the device, it would then suffice to provide a setback on each foot preventing any retreat of the device.
  • Figure 2 shows in section along the plane AA of the figure 1 the projectile 1 placed in a tube of launch 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 guidance of the projectile in the tube launch.
  • the operation of the device is as follows.
  • the fins are firmly held by the device throughout the course inside the launch tube.
  • All fins are symmetrically open this mainly because, thanks to the device according to the invention, the force applied to the fin is of origin aerodynamic and it is maximum at the start of the opening.
  • the 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 problems with known deployment springs whose mechanical characteristics are likely to deteriorate during storage of the projectile.
  • the resulting aerodynamic forces as well as the centrifugal force which are exercised on the device 6 manage to overcome the friction between the fin and the groove 10 and entrain the separation of the device and the fin.
  • the devices are automatically ejected and do not interfere with 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 channels 6a, 6b.
  • Figure 5 shows schematically the rear part a projectile 1 equipped with a deployment device 15 according to a second embodiment of the invention which is for projectiles equipped with an even number of fins.
  • This device includes a pallet 7 intended to receive the aerodynamic flow that appears when firing along of the body of the projectile between the front part (AV mark) and the rear part (AR mark).
  • the inclination of the pallet relative to axis 8 of the projectile is still chosen such that the flow aerodynamics has the effect of removing the device 15 from the body of the projectile.
  • FIGS 7a, 7b and 7c show in detail what deployment device.
  • Pallet 7 is connected to side walls 8a and 8b which end with lateral support feet 9a and 9b.
  • the walls side 8a, 8b are planar and substantially parallel to lateral surfaces 4b, 4c of the fin 4.
  • the device after its installation on the projectile, is shaped so as to present, in view of the aerodynamic flow, a channel 15a whose the entry opening (arranged towards the front part of the projectile) has a surface larger than that of the opening outlet (oriented towards the rear rear part).
  • the support feet 9a, 9b come into contact with the external surface of the projectile body 1a, they have a profile cylindrical 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 on along the body 1a of the projectile.
  • the feet 9a, 9b also carry holding zones 17a, 17b which are each in contact with a surface lateral of the fin considered.
  • 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 secured to the projectile body, for example by bonding.
  • the flanges are axially offset from the device, so that the flanges do not prevent the opening of the fin.
  • the dimensions of the devices 15 and the flanges 19 will be chosen so that there is no play during the placement on the fin.
  • Each device 15 finally comprises a rear tab 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 tab also makes it possible to locate, at the level of the rear flange and at equal distance from each fin, the pivot point of the device. Such a provision 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 guidance of the projectile in the tube launch.
  • the deployment device is still ejected at from a certain opening angle of the fins.
  • An advantage of this embodiment is that it allows to eject the device very quickly which reduces its action to a simple initial impulse on the fins which end then their opening by inertia and by the effect of their clean trail.
  • the rapid ejection of the device also presents the advantage of limiting the angular speed of the fin in limit switch 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 surfaces 16a, 16b and it is possible to determine precisely the instant of ejection of the device by playing on the dimensions of the drive surfaces 16a, 16b and especially on the length L (see Figures 6 and 7a).
  • Another advantage of this embodiment is that it reduces the number of devices used for a projectile, therefore the cost of production.
  • Such a device would include for example one or more fixed pallets 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)

Claims (8)

  1. Auffaltvorrichtung für Stabilisierungsflügel (4) für ein Geschoß (1) mit mindestens einem Anker, der fest mit einem Flügel (4) durch Mitnahmemittel verbunden ist und so ausgerichtet wird, daß er eine aerodynamische Strömung beim Abschießen des Geschosses erhält und eine resultierende Kraft auf den Flügel (4) überträgt, um diesen aufzufalten, gekennzeichnet dadurch, daß sie mindestens zwei Anker (7a, 7b) umfaßt, die durch eine Rille (10) getrennt sind, in der sich der Flügel (4) positioniert, wobei die Rille (10) einen Grund (10a) umfaßt, auf dem der Flügel (4) zum Aufliegen kommt, wenn er sich in seiner entlang des Körpers des Geschosses (1) zurückgefalteten Position befindet, wobei dieser Grund (10a) das Mitnahmemittel bildet, das so entriegelbar ist, daß die Auffaltvorrichtung und der Flügel (4) ab einem gewissen Öffnungswinkel des Flügels getrennt werden.
  2. Vorrichtung gemäß dem Anspruch 1, gekennzeichnet dadurch, daß sie eine Stirnwand (11) besitzt, die die Rille (10) auf der Ebene eines vorderen Teils der Vorrichtung schließt und einen axialen Anschlag für das Ende des Flügels (4) bildet.
  3. Vorrichtung gemäß einem der Ansprüche 1 oder 2, gekennzeichnet dadurch, daß sie mindestens zwei seitliche Stützfüße (9a, 9b) umfaßt, die mit einer externen Oberfläche des Geschosses (1) in Berührung sind und von Anschlagprofilen (12) gehalten werden, die das Geschoß trägt, und die so angeordnet sind, daß sie jegliche Verschiebung der Vorrichtung in eine Richtung verhindern, die zu einer Seitenfläche (4b, 4c) des Flügels (4) im rechten Winkel liegt.
  4. Auffaltvorrichtung für Stabilisierungsflügel (4) für ein Geschoß (1) mit mindestens einem Anker, der fest mit einem Flügel (4) durch Mitnahmemittel verbunden und so ausgerichtet ist, daß er beim Abschuß des Geschosses eine aerodynamische Strömung erhält und eine resultierende Kraft auf den Flügel (4) überträgt, um diesen aufzufalten, gekennzeichnet dadurch, daß sie mindestens einen Anker (7) umfaßt, der mit mindestens zwei seitlichen Mitnahmeoberflächen (16a, 16b) fest verbunden ist, wobei jede dieser Mitnahmeoberflächen dazu bestimmt ist, einen anderen Flügel (4) des Geschosses (1) in Auflage zu erhalten, wenn sich diese Flügel (4) in ihrer entlang des Körpers des Geschosses zurückgefalteten Position befinden, wobei die seitlichen Mitnahmeoberflächen das Mitnahmemittel bilden, das so entriegelbar ist, daß es die Auffaltvorrichtung und den Flügel ab einem gewissen Öffnungswinkel des Flügels trennt.
  5. Vorrichtung gemäß dem Anspruch 4, gekennzeichnet dadurch, daß sie eine Zunge (20) umfaßt, die gegen einen Kragen (21) zum Aufliegen kommt, der mit dem Geschoß (1) fest verbunden ist und einen axialen Anschlag für die Vorrichtung bildet.
  6. Vorrichtung gemäß dem Anspruch 4, gekennzeichnet dadurch, daß sie mindestens eine in etwa im rechten Winkel zu jeder Mitnahmeoberfläche (16a, 16b) stehende Wand umfaßt, die einen axialen Anschlag für das betroffene Ende des Flügels (4) bildet.
  7. Vorrichtung gemäß einem der Ansprüche 4 bis 6, gekennzeichnet dadurch, daß jede seitliche Mitnahmeoberfläche (16a, 16b) eine Haltezone (17a, 17b) einer ersten Seitenoberfläche des Flügels (4) umfaßt.
  8. Vorrichtung gemäß einem der Ansprüche 1 bis 7, gekennzeichnet dadurch, daß sie eine externe Führungsoberfläche (14) mit kreisförmigem Profil umfaßt, deren Durchmesser gleich ist wie der eines Abschußrohres des Geschosses (1).
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
FR9407953 1994-06-28
FR9407953A FR2721702B1 (fr) 1994-06-28 1994-06-28 Dispositif de déploiement d'une ailette de projectile.

Publications (2)

Publication Number Publication Date
EP0690284A1 EP0690284A1 (de) 1996-01-03
EP0690284B1 true 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
EP1947415A1 (de) * 2007-01-19 2008-07-23 Diehl BGT Defence GmbH & Co.KG Vorrichtung zur Tragflächenentfaltung

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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
US7856929B2 (en) 2007-06-29 2010-12-28 Taser International, Inc. Systems and methods for deploying an electrode using torsion
WO2009005540A1 (en) * 2007-06-29 2009-01-08 Taser International, Inc. Systems and methods for a projectile having a stabilizer for spin stabilization
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

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1947415A1 (de) * 2007-01-19 2008-07-23 Diehl BGT Defence GmbH & Co.KG Vorrichtung zur Tragflächenentfaltung

Also Published As

Publication number Publication date
EP0690284A1 (de) 1996-01-03
DE69512146T2 (de) 2000-01-27
IL114383A0 (en) 1995-10-31
ES2138165T3 (es) 2000-01-01
IL114383A (en) 1998-12-06
FR2721702B1 (fr) 1996-08-14
DE69512146D1 (de) 1999-10-21
ZA955302B (en) 1996-12-23
FR2721702A1 (fr) 1995-12-29
US5685503A (en) 1997-11-11

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