EP0389358B1 - Leitwerkausspreizungssystem für ein Geschoss - Google Patents

Leitwerkausspreizungssystem für ein Geschoss Download PDF

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Publication number
EP0389358B1
EP0389358B1 EP90400758A EP90400758A EP0389358B1 EP 0389358 B1 EP0389358 B1 EP 0389358B1 EP 90400758 A EP90400758 A EP 90400758A EP 90400758 A EP90400758 A EP 90400758A EP 0389358 B1 EP0389358 B1 EP 0389358B1
Authority
EP
European Patent Office
Prior art keywords
component
chamber
bore
winglets
opening system
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
EP90400758A
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English (en)
French (fr)
Other versions
EP0389358A1 (de
Inventor
Bernard Baubry
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
Priority to AT90400758T priority Critical patent/ATE97483T1/de
Publication of EP0389358A1 publication Critical patent/EP0389358A1/de
Application granted granted Critical
Publication of EP0389358B1 publication Critical patent/EP0389358B1/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
    • F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces

Definitions

  • the present invention relates to a system for the combined opening of the fins of a tail unit deploying for projectiles, in particular mortar ammunition, provided with a propellant.
  • tail span larger than the caliber at the rear of a munition there are many reasons that may make it necessary, or at least preferable, to have a tail span larger than the caliber at the rear of a munition: long length of the ammunition, optimization of precision, presence of a propellant to increase range, etc.
  • a tail unit will advantageously be provided capable of assuming a folded position at rest, to make it fit into the caliber in order to reduce the size of the ammunition and to facilitate handling and storage.
  • this ability to be folded becomes a necessity, to allow the introduction of the ammunition into the barrel.
  • This type of empennage commonly called deploying empennage, is formed by a plurality of fins arranged around the munition. Their opening must meet three essential requirements: first, it must be triggered after the ammunition leaves, to protect the fins against shocks. On the other hand, the deployment must be complete and irreversible due to the radial influence of such a tail on the trajectory of the munition. Finally, the triggering of the propellant, positioned inside the projectile, must occur only after total and irreversible opening of the tail; this thus constituting a safety device for a projectile provided with a propellant.
  • Document US-A-3,304,030 describes a system for opening a deploying tail for a projectile, formed from a plurality of fins articulated on axes and distributed around the projectile, the system comprising a part capable of slide in leaktight manner, under the action of the pressure of a gas, from a first position to a second position so as to drive means for pivoting the fins, the fins being fully deployed when this part reaches the second position.
  • the projectile described in this document does not have a propellant, and the opening system is therefore not designed for the type of projectiles which interests us.
  • the object of the present invention is to provide a system for the combined opening of the fins of a deploying tail unit which is simple and which reliably meets these three requirements.
  • the subject of the invention is a system for opening a deploying tail for a projectile, as defined by claims 1 to 12.
  • a pressure sensitive delay igniter will advantageously be used, which will be triggered by the pressure inside the barrel at the time of the firing, the time delay being greater than the ejection time of ammunition.
  • the projectile is a self-propelled munition, of the type which is launched with mortars.
  • the body 1 of the ammunition in one or more sections, contains active elements such as an explosive charge 2.
  • the rear end of the body 1 has a tapped axial bore 3, into which a block 4 formed of a part is screwed cylindrical threaded 4a and a rear part consisting of radial plates 4b integral with part 4a and regularly distributed around the longitudinal axis XX.
  • Each plate 4b carries a perpendicular axis 5 on which is articulated the base 6a of a fin 6.
  • a tail fin with four fins has been shown in the drawings for reasons of clarity, these are more generally the number of six or eight, this number being determined by or for aerodynamic reasons.
  • the part 4a of the block 4 has a first axial bore 7 opening between the plates 4b, and in which a part of revolution 8 is slidably mounted.
  • a seal 9 surrounds the base of the part 8, to seal between it -ci and the wall of the bore 7.
  • the part 8 has a general bell shape, the top of which has a threaded orifice in which is fixed in leaktight manner, by means of a seal 11, a pyrotechnic assembly 10 provided with a pressure-sensitive delay igniter.
  • the function of the assembly 10 is to generate a gas under pressure in a sealed chamber 12 delimited by the interior of the part 8 and the bottom of the bore 7.
  • the external wall of the part 8 forms a first cylindrical part 8a closely matching the wall of the bore 7, a second cylindrical part 8b of smaller diameter, separated from the part 8a by a frustoconical shoulder 8c, and a groove 13 whose front edge is a frustoconical shoulder 8d, the bottom a cylindrical part 8e and the rear edge a shoulder 8f normal to the axis XX, followed by a cylindrical end portion 8g.
  • a tooth 14 is engaged formed at the periphery of the base 6a of each fin 6.
  • each tooth 14 has a shape which substantially matches the profile of the groove 13 to register there.
  • the tooth 14 forms a projection on the internal side of the base part 6a, its front side 14a being in the extension of the front side of the part 6a.
  • Figure 2 shows the fins 6 fully deployed: the outer side of their base part 6a is applied against the bottom of the cylindrical part 4a of the block 4, while the front side is applied to the cylindrical surface 8b of the part 8 which has left the bottom of the bore 7 under the effect of a gas pressure generated in the chamber 12 by the pyrotechnic assembly 10. Note that in this position, the part 8 is blocked towards the rear because the shoulder 8c abuts against the base part 6a of the fins. On the other hand, the seal 9 at the periphery of the part 8 is always in contact on the internal wall of the bore 7, so that the pressure is maintained in the chamber 12 and prevents the return towards the bottom of the bore of the part 8.
  • the fins 6 are therefore perfectly locked between the two perpendicular bearings formed by the bottom of the part 4a and the surface 8b. It will be noted, by means of the drawings, that the complete deployment is carried out irreversibly as soon as the external edge of the shoulder 8d arrives at the level of the axis 5, that is to say before the part 8 has reaches its extreme rear position.
  • an additional security may consist of one or more flexible blades 15, fixed on the bottom of the block 4 , and ensuring a mechanical blocking of the part 8 by coming to brace in the groove 13, FIG. 2.
  • the projectile is introduced into a weapon, preferably provided with a device for protecting the fins as mentioned previously, the fins 6 being in the position of FIG. 1, that is to say inside of caliber.
  • the pressure in the barrel of the weapon triggers the delay igniter of the pyrotechnic assembly 10, the timing of which is chosen such that the pressurization in the chamber 12 takes place only after the ammunition has left the muzzle of the barrel.
  • the part 8 is then driven irreversibly to the position of Figure 2 described above.
  • seals 9 and 11 ensuring the tightness of the chamber 12 must be chosen to be strong enough to withstand the temperature and pressure conditions inside the barrel. In practice, butadiene-acrylic seals are found to be satisfactory.
  • the opening system according to the invention of Figures 3 and 4 provided for a projectile provided with a propellant, comprises the same elements operating in the same way as those of the system of FIGS. 1 and 2 and, for this reason, they will not be re-described here in detail and they will be designated by the same numerical references, accompanied by the sign '.
  • an ignition device consists, for example of several igniters 17 'regularly distributed at the base of a fuel 2' contained inside the propellant and of a pyrotechnic relay 18 'ensuring the ignition of 17 'igniters.
  • the relay 18 ' is located at the end of a second chamber, for example a bore 19' the other end of which opens into the bore 7 '.
  • the bore 19 ' is coaxial with the bore 7', and it extends somewhat inside the latter, in an annular part 20 '.
  • the part 8 'engaged in the bore 7' and ensuring the pivoting of the fins 6 ' is provided internally with a cylindrical axial rod 21', fixed to the bottom of the part 8 ', and the end of which free is substantially in the same plane as its base edge inside the bore 7 '.
  • the rod 21 ' has the same diameter as the bore 19', so as to be capable of being engaged therein intimately and sealingly by means of a seal 22 '.
  • the rod 21 'and the seal 22' thus constituting a means for closing the second chamber 19 '.
  • the end of the rod 21 leaves the bore 19' after the fins have been fully deployed in an irreversible manner, that is to say, as can be seen by observing the drawings, after the 'external edge of the shoulder 8d' has reached the level of the axis 5 '. Consequently, the pressure in the chamber 12 ′ is not transmitted to the relay 18 ′ to trigger it only after the fins 6 ′ have been locked in the deployed position.
  • one or more flexible blades 15 ′ can be fixed to the bottom of the block 4 ′ to provide additional mechanical locking of the part 8 ′ in the rear position.
  • the device of the invention has the advantage of being mechanically simple, and, therefore, reliable and easy to implement. Although particularly suitable for the type of ammunition for mortar, it can be applied to all kinds of projectiles, only the delay igniter used to establish the deployment pressure of the fins having to be changed or modified according to the triggering mode usable, for example electronic. In addition, if desired, one can easily provide the system of the invention with additional security intended to keep the ammunition in the inert state until the complete deployment of the fins, in the form of a contactor in an electrical circuit for activating the ammunition, the contactor being closed by the part 8 or 8 ′ when it reaches its extreme rear position.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Curing Cements, Concrete, And Artificial Stone (AREA)
  • Buildings Adapted To Withstand Abnormal External Influences (AREA)
  • Body Structure For Vehicles (AREA)
  • Air Bags (AREA)
  • Toys (AREA)
  • Fishing Rods (AREA)
  • Professional, Industrial, Or Sporting Protective Garments (AREA)

Claims (12)

  1. System zum Öffnen eines entfaltbaren Leitwerks für ein Geschoß, wobei das System aus einer Mehrzahl von auf Achsen (5') angelenkten und um das Geschoß gleichmäßig verteilten Flügeln (6') und einem Bauteil (8') besteht, das dicht in einer erste Bohrung (7') zwischen einer ersten Stellung und einer zweiten Stellung gleiten kann und dabei Mittel zum Schwenken der Flügel (6') mitnimmt, wobei das Bauteil (8') mit der ersten Bohrung (7') eine erste Kammer (12') bildet und durch einen von einem Gasgenerator in der ersten Kammer (12) erzeugten Gasdruck verschiebbar ist, wobei die Flügel (6') vollständig entfaltet sind, wenn das Bauteil (8') seine zweite Stellung erreicht, dadurch gekennzeichnet, daß, wenn das Projektil außerdem einen Brennstoff (2') für seinen Antrieb besitzt und die Antriebszündung durch eine Zündvorrichtung (17', 18') erfolgt, die unter der Wirkung eines Drucks ausgelöst wird, das System eine zweite Kammer (19') und ein Verschlußmittel (21', 22') aufweist, das auf dem Bauteil (8') befestigt ist und dicht in die zweite Kammer eindringt, um diese zweite Kammer von der ersten Kammer zu isolieren, solange das Bauteil (8') seine zweite Stellung nicht erreicht hat, aber das in der ersten Kammer (12') enthaltene Gas in die zweite Kammer (19') eindringen läßt, wenn die zweite Stellung erreicht ist, um die Zündvorrichtung auszulösen.
  2. Öffnungssystem nach Anspruch 1, dadurch gekennzeichnet, daß die zweite Kammer (19') in einer zweiten Axialbohrung am Boden der ersten Bohrung (7') ausgebildet ist und daß die Verschlußmittel eine am Boden des Bauteils (8') befestigte axiale Stange (21') gleichen Durchmessers wie die zweite Bohrung sowie eine Dichtung (22') aufweisen, die um die Stange (21') herumliegt, so daß die Stange (21') dicht in der zweiten Bohrung (19') sitzt.
  3. Öffnungssystem nach einem beliebigen der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß das Druckgas in der Kammer (12') von einer pyrotechnischen Einheit (10') erzeugt wird, die einen verzögert auf Druck ansprechenden Zünder besitzt, um für ein entfaltbares Leitwerk einer Munition verwendet zu werden, die mit einer Waffe abgeschossen werden soll, wobei der Verzögerungszünder von dem Druck in der Kanone beim Abschuß ausgelöst wird.
  4. Öffnungssystem nach einem beliebigen der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Zündvorrichtung aus mehreren Zündern (17') besteht, die gleichmäßig um die Basis der im Inneren des Antriebs befindlichen Brennstoffkammer (2') herum angeordnet sind, und aus einem pyrotechnischen Relais (18'), das das Zünden der Zünder (17') sichert.
  5. Öffnungssystem nach einem beliebigen der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die erste Bohrung (7') sich in einem hinter dem Geschoß befindlichen Block (4') befindet.
  6. Öffnungssystem nach einem beliebigen der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß sich die zweite Stellung des Bauteils (8') hinter der ersten Stellung dieses Bauteils (8') befindet.
  7. Öffnungssystem nach einem beliebigen der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die vollständig entfalteten Flügel (6') in dieser Stellung durch Blockiermittel festgehalten werden.
  8. Öffnungssystem nach Anspruch 7, dadurch gekennzeichnet, daß die Blockiermittel für die völlig entfalteten Flügel (6') aus einer zylindrischen Auflagefläche (8b) des Bauteils (8') und dem Boden des Blocks (4') bestehen, der die Flügel trägt, wobei diese Flächen beim Zurückweichen des Bauteils (8') in seine zweite Stellung zusammenwirken, um zwei senkrechte Anschlagflächen zu bilden, gegen die zwei benachbarte Seiten des Basisbereichs (6a') der entfalteten Flügel anliegen.
  9. Öffnungssystem nach einem beliebigen der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Mittel zum Schwenken der Flügel (6') aus einem Zahn (14') des Basisteils (6a') der Flügel bestehen, der in eine periphere Nut (13') des Bauteils (8') eindringt, wenn dieses Bauteil sich in der ersten Stellung befindet.
  10. Öffnungssystem nach einem beliebigen der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die zweite Stellung des Bauteils (8') durch Anschlag einer kegelstumpfförmigen Schulter (8c') dieses Bauteils gegen den Basisbereich (6a') der Flügel bestimmt ist, nachdem diese in der entfalteten Stellung blockiert worden sind.
  11. Öffnungssystem nach einem beliebigen der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß es außerdem ein mechanisches Blockiermittel für das Bauteil (8') in seiner zweiten Stellung besitzt, das aus mindestens einer flexiblen Lamelle (15) besteht, die auf dem Boden des Blocks (4') befestigt ist und sich gegen eine Schulter (8f') an der Peripherie des Bauteils (8') einspreizt.
  12. Öffnungssystem nach einem beliebigen der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Schwenkmittel und die Mittel zum Blockieren der Flügel (6') in der entfalteten Stellung so ausgebildet sind, daß sie bei der Verschiebung des Bauteils (8') wirksam werden, ehe dieses seine zweite Stellung erreicht hat, und daß das Bauteil (8') außerdem ein Mittel besitzt, um die Kammer (12') gegenüber einer zweiten in Richtung auf eine empfindliche Zündvorrichtung offenen Kammer zu isolieren.
EP90400758A 1989-03-24 1990-03-20 Leitwerkausspreizungssystem für ein Geschoss Expired - Lifetime EP0389358B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT90400758T ATE97483T1 (de) 1989-03-24 1990-03-20 Leitwerkausspreizungssystem fuer ein geschoss.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8903924 1989-03-24
FR8903924A FR2644880B1 (fr) 1989-03-24 1989-03-24 Systeme d'ouverture d'un empennage deployant pour projectile

Publications (2)

Publication Number Publication Date
EP0389358A1 EP0389358A1 (de) 1990-09-26
EP0389358B1 true EP0389358B1 (de) 1993-11-18

Family

ID=9380048

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90400758A Expired - Lifetime EP0389358B1 (de) 1989-03-24 1990-03-20 Leitwerkausspreizungssystem für ein Geschoss

Country Status (6)

Country Link
US (1) US5082203A (de)
EP (1) EP0389358B1 (de)
AT (1) ATE97483T1 (de)
CA (1) CA2012925A1 (de)
DE (1) DE69004604T2 (de)
FR (1) FR2644880B1 (de)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE9102702L (sv) * 1991-09-18 1993-03-19 Bofors Ab Stridsdel
US5464173A (en) * 1994-12-16 1995-11-07 The United States Of America As Represented By The Secretary Of The Navy Subassembly means
US6168111B1 (en) * 1997-03-03 2001-01-02 The United States Of America As Represented By The Secretary Of The Army Fold-out fin
US6224013B1 (en) * 1998-08-27 2001-05-01 Lockheed Martin Corporation Tail fin deployment device
DE10015514B4 (de) 2000-03-30 2007-10-04 Rheinmetall Waffe Munition Gmbh Flügelstabilisiertes Geschoß
DE10205043C5 (de) * 2002-02-07 2010-06-17 Diehl Bgt Defence Gmbh & Co. Kg Aus einem Rohr zu verschließender Flugkörper mit überkalibrigem Leitwerk
US6559370B1 (en) * 2002-08-06 2003-05-06 The United States Of America As Represented By The Secretary Of The Navy Submarine countermeasure vehicle with folding propeller
US8338769B1 (en) * 2008-02-07 2012-12-25 Simmonds Precision Products, Inc. Pyrotechnic fin deployment and retention mechanism
US8438977B2 (en) * 2008-12-25 2013-05-14 Lockheed Martin Corporation Projectile having deployable fin
US9068807B1 (en) * 2009-10-29 2015-06-30 Lockheed Martin Corporation Rocket-propelled grenade
US9140528B1 (en) 2010-11-16 2015-09-22 Lockheed Martin Corporation Covert taggant dispersing grenade
US8415598B1 (en) * 2010-12-20 2013-04-09 The United States Of America As Represented By The Secretary Of The Army Extendable fins for a tube-launched projectile
US8866057B2 (en) * 2011-10-17 2014-10-21 Raytheon Company Fin deployment method and apparatus
JP6212898B2 (ja) * 2012-03-29 2017-10-18 ダイキン工業株式会社 高速飛翔体
US9423222B1 (en) 2013-03-14 2016-08-23 Lockheed Martin Corporation Less-than-lethal cartridge
US9200876B1 (en) 2014-03-06 2015-12-01 Lockheed Martin Corporation Multiple-charge cartridge
CN104089547B (zh) * 2014-06-30 2016-01-27 中国航天时代电子公司 一种折叠舵面的展开与锁定装置
CN105292410A (zh) * 2015-10-30 2016-02-03 北京精密机电控制设备研究所 一种由火工品驱动带锁定功能的弹出式减速翼***
US10641590B2 (en) * 2016-10-26 2020-05-05 Simmonds Precision Products, Inc. Wing deployment and lock mechanism
US11300390B1 (en) 2018-03-05 2022-04-12 Dynamic Structures And Materials, Llc Control surface deployment apparatus and method of use

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE565999A (de) * 1953-02-06
BE552288A (de) * 1953-10-20
US2821924A (en) * 1954-07-09 1958-02-04 Lawrence J Hansen Fin stabilized projectile
US3196793A (en) * 1963-01-16 1965-07-27 Milenkovic Veljko Folded fin rocket
US3304030A (en) * 1965-09-24 1967-02-14 James E Weimholt Pyrotechnic-actuated folding fin assembly
FR2221707B1 (de) * 1973-03-14 1976-04-30 France Etat
DE7804927U1 (de) * 1978-02-18 1978-06-01 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Vorrichtung zum ausklappen von schwenkfluegeln
SE444612B (sv) * 1984-12-13 1986-04-21 Ffv Affersverket Styrverk for utfellning av fenor hos projektil

Also Published As

Publication number Publication date
CA2012925A1 (fr) 1990-09-24
DE69004604D1 (de) 1993-12-23
FR2644880A1 (fr) 1990-09-28
ATE97483T1 (de) 1993-12-15
FR2644880B1 (fr) 1994-03-11
US5082203A (en) 1992-01-21
DE69004604T2 (de) 1994-05-11
EP0389358A1 (de) 1990-09-26

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