EP0777101B1 - Mechanical unlocking system together with aerodynamic breaking, for missile sectons - Google Patents

Mechanical unlocking system together with aerodynamic breaking, for missile sectons Download PDF

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Publication number
EP0777101B1
EP0777101B1 EP19960402543 EP96402543A EP0777101B1 EP 0777101 B1 EP0777101 B1 EP 0777101B1 EP 19960402543 EP19960402543 EP 19960402543 EP 96402543 A EP96402543 A EP 96402543A EP 0777101 B1 EP0777101 B1 EP 0777101B1
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EP
European Patent Office
Prior art keywords
sections
micro
actuators
separation
section
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
EP19960402543
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German (de)
French (fr)
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EP0777101A1 (en
Inventor
Jean-François Thomson-CSF SCPI Denis
Jean Thomson-CSF SCPI Fourniols
Pascal Thomson-CSF SCPI Laurend
Alban Thomson-Csf Scpi Lienard
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TDA Armements SAS
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TDA Armements SAS
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Publication date
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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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Definitions

  • the present invention relates to a system for separating sections of machine with mechanical unlocking allowing uncoupling two sections of a machine.
  • An object of the invention is therefore a separation system free of these disadvantages thanks to the use of micro-actuators actuated by a pyrotechnic gas generator.
  • an exhaust is provided aerodynamics during the separation of sections thanks to flaps aerodynamics releasable mounted on one of the sections.
  • Figure 1 a machine comprising at least two sections, 1 and 2, section 2 being for example the rear part.
  • the separation system according to the invention is inserted between the two sections 1 and 2. It comprises a part in the form of a hub 13 which is integral of section 1 and in which micro-jacks 3 are arranged radially.
  • the fingers 7 of the micro-cylinders are directed towards the outside and come to house in corresponding radial housings 15 of an envelope cylindrical 14 extending the other section 2. These fingers 7 therefore join the two sections when the micro-cylinders are not actuated.
  • annular chamber 4 intended to distribute uniformly between the micro-cylinders the pressure in the room.
  • the gas under generated pressure actuates the micro-jacks 3 whose fingers 7 are retract inside, thereby unlocking the two sections 1 and 2.
  • the system also includes aerodynamic flaps 5, here two in number, releasable when unlocked.
  • These shutters are mounted on section 2 by means of a hinge 10 about an axis transverse tangential 11. They are fixed in the retracted position to the finger 7 of a micro-jack 3 opposite by a breaking screw 9.
  • a peripheral segment 6 (Figs. 4 and 5) whose sides are inclined opposite of inclined sides complementary to the envelopes of sections 1 and 2. Au by means of pressure screws arranged in a known manner, the segment comes brace and wedge the two envelopes.
  • segment 6 ensures good mechanical transmission with game catch-up and that the system allows you to simultaneously unlock the link between the two sections and release the aerodynamic flaps with a single event.

Description

La présente invention se rapporte à un système de séparation de tronçons d'engin à déverrouillage mécanique permettant de désaccoupler deux tronçons d'un engin.The present invention relates to a system for separating sections of machine with mechanical unlocking allowing uncoupling two sections of a machine.

Une telle séparation de deux tronçons est par exemple nécessaire dans le cas d'un missile en plusieurs parties lorsque l'une de ces parties a fini de remplir son rôle.Such separation of two sections is for example necessary in the case of a multi-part missile when one of these parts has finished fulfilling its role.

De nombreux systèmes existent assurant la découpe ou le désaccouplement sur un engin en vol. Parmi ceux-ci, on peut citer les cordeaux découpeurs, les sacs d'éjection gonflables ou les chambres pyrotechniques à rupture d'enveloppe.Many systems exist ensuring the cutting or the uncoupling on a craft in flight. Among these are the cutting lines, air bags or chambers envelope pyrotechnics.

Un autre système, décrit dans le brevet US N° 5 318 255, consiste à prévoir sur chaque tronçon en vis à vis une bride circulaire et à les maintenir assemblées par un collier de serrage circonférentiel. Celui-ci est maintenu serré par un boulon explosif reliant ses deux extrémités. La rupture de ce boulon relâche le collier et libère les deux brides, ce qui permet la séparation des deux tronçons.Another system, described in US Patent No. 5,318,255, consists provide a circular flange for each section opposite hold together by a circumferential clamp. It is held tight by an explosive bolt connecting its two ends. Breaking of this bolt loosens the collar and releases the two flanges, which allows the separation of the two sections.

Cependant tous ces systèmes présentent un inconvénient important qui est la création d'une onde de choc sur l'engin pouvant perturber ou endommager celui-ci et ses capteurs. D'autre part, ces systèmes causent la projection d'éclats vers l'extérieur. Ceci est un inconvénient du point de vue de la sécurité de stockage en cas de déclenchement intempestif.However, all these systems have a drawback important which is the creation of a shock wave on the machine which can disturb or damage it and its sensors. On the other hand, these systems cause the projection of shards outwards. This is a disadvantage of the point of view of storage security in the event of inadvertent tripping.

Un objet de l'invention est donc un système de séparation exempt de ces inconvénients grâce à l'utilisation de micro-vérins actionnés par un générateur de gaz pyrotechnique.An object of the invention is therefore a separation system free of these disadvantages thanks to the use of micro-actuators actuated by a pyrotechnic gas generator.

Selon l'invention, il est donc prévu un système de séparation de tronçons d'engin à déverrouillage mécanique permettant de désaccoupler deux tronçons d'un engin, caractérisé en ce qu'il comprend :

  • un moyeu comportant une pluralité de micro-vérins disposés radialement, ledit moyeu étant solidaire d'un desdits tronçons ;
  • une enveloppe cylindrique prolongeant l'extrémité de l'autre tronçon et percée de logements radiaux pour recevoir les doigts, dirigés vers l'extérieur, desdits micro-vérins, en position assemblée ;
  • une chambre annulaire disposée autour desdits micro-vérins pour répartir uniformément la pression qui y règne vers lesdits micro-vérins ; et
  • des moyens pyrotechniques pour générer dans ladite chambre une pression actionnant lesdits micro-vérins pour retracter lesdits doigts vers l'intérieur et désaccoupler ainsi les deux tronçons.
According to the invention, there is therefore provided a system for separating sections of machine with mechanical unlocking enabling two sections of a machine to be uncoupled, characterized in that it comprises:
  • a hub comprising a plurality of micro-cylinders arranged radially, said hub being integral with one of said sections;
  • a cylindrical envelope extending the end of the other section and pierced with radial housings to receive the fingers, directed outwards, of said micro-jacks, in the assembled position;
  • an annular chamber arranged around said micro-cylinders to uniformly distribute the pressure therein towards said micro-cylinders; and
  • pyrotechnic means for generating in said chamber a pressure actuating said micro-cylinders to retract said fingers inward and thus uncoupling the two sections.

Ainsi, on élimine tous les risques pour l'engin du fait de l'absence d'onde de choc ainsi que les risques dus à la projection d'éclats vers l'extérieur en cas de déclenchement lors du stockage de l'engin.Thus, we eliminate all risks for the machine due to the absence shock wave as well as the risks due to the projection of shards towards the outside in the event of tripping during the storage of the machine.

Selon un autre aspect de l'invention, on assure un échappement aérodynamique lors de la séparation des tronçons grâce à des volets aérodynamiques libérables montés sur un des tronçons.According to another aspect of the invention, an exhaust is provided aerodynamics during the separation of sections thanks to flaps aerodynamics releasable mounted on one of the sections.

L'invention sera mieux comprise et d'autres caractéristiques et avantages apparaítront à l'aide de la description ci-après et des dessins joints où :

  • la figure 1 est une vue en plan d'un engin équipé du système selon l'invention ;
  • les figures 2 et 3 sont des vues en coupe détaillant le système selon l'invention ;
  • la figure 4 est une vue en perspective schématique d'un engin avec le système selon l'invention ; et
  • la figure 5 représente en coupe partielle un détail du système selon l'invention.
The invention will be better understood and other characteristics and advantages will appear from the following description and the accompanying drawings, in which:
  • Figure 1 is a plan view of a machine equipped with the system according to the invention;
  • Figures 2 and 3 are sectional views detailing the system according to the invention;
  • Figure 4 is a schematic perspective view of a machine with the system according to the invention; and
  • Figure 5 shows in partial section a detail of the system according to the invention.

Sur la figure 1 est représenté un engin comprenant au moins deux tronçons, 1 et 2, le tronçon 2 étant par exemple la partie arrière. Comme on le voit mieux en se reportant également aux figures 2 à 5, où la figure 2 est une coupe selon la ligne A-A de la figure 1 et la figure 3 une coupe selon la ligne B-B, le système de séparation selon l'invention s'intercale entre les deux tronçons 1 et 2. Il comporte une partie en forme de moyeu 13 solidaire du tronçon 1 et dans lequel sont disposés radialement des micro-vérins 3. Les doigts 7 des micro-vérins sont dirigés vers l'extérieur et viennent se loger dans des logements radiaux 15 correspondants d'une enveloppe cylindrique 14 prolongeant l'autre tronçon 2. Ces doigts 7 solidarisent donc les deux tronçons lorsque les micro-vérins ne sont pas actionnés.In Figure 1 is shown a machine comprising at least two sections, 1 and 2, section 2 being for example the rear part. As we see it better by also referring to Figures 2 to 5, where Figure 2 is a section along line A-A of Figure 1 and Figure 3 a section along the line B-B, the separation system according to the invention is inserted between the two sections 1 and 2. It comprises a part in the form of a hub 13 which is integral of section 1 and in which micro-jacks 3 are arranged radially. The fingers 7 of the micro-cylinders are directed towards the outside and come to house in corresponding radial housings 15 of an envelope cylindrical 14 extending the other section 2. These fingers 7 therefore join the two sections when the micro-cylinders are not actuated.

Autour du moyeu 13 et des micro-vérins 3 est prévue une chambre annulaire 4 destinée à répartir uniformément entre les micro-vérins la pression régnant dans la chambre. Around the hub 13 and the micro-jacks 3 is provided a annular chamber 4 intended to distribute uniformly between the micro-cylinders the pressure in the room.

Dans le moyeu 13 est prévu le logement 12 d'une cartouche pyrotechnique 8. Ce logement communique avec la chambre 4.In the hub 13 is provided the housing 12 of a cartridge pyrotechnic 8. This accommodation communicates with room 4.

Lorsque le fonctionnement de la cartouche 8 est déclenché, le gaz sous pression généré vient actionner les micro-vérins 3 dont les doigts 7 se rétractent à l'intérieur en déverrouillant ainsi les deux tronçons 1 et 2.When the operation of the cartridge 8 is triggered, the gas under generated pressure actuates the micro-jacks 3 whose fingers 7 are retract inside, thereby unlocking the two sections 1 and 2.

Pour assurer la séparation des deux tronçons lors du déverrouillage, le système comprend aussi des volets aérodynamiques 5, ici au nombre de deux, libérables lors du déverrouillage. Ces volets sont montés sur le tronçon 2 par l'intermédiaire d'une articulation 10 autour d'un axe tangentiel transversal 11. Ils sont fixés en position rétractée au doigt 7 d'un micro-vérin 3 en vis-à-vis par une vis de rupture 9.To ensure the separation of the two sections during the unlocking, the system also includes aerodynamic flaps 5, here two in number, releasable when unlocked. These shutters are mounted on section 2 by means of a hinge 10 about an axis transverse tangential 11. They are fixed in the retracted position to the finger 7 of a micro-jack 3 opposite by a breaking screw 9.

Ainsi, lors du déverrouillage, le mouvement de retrait des doigts 7 assure la rupture des vis 9 ce qui libère les volets 5. Ceux-ci prennent alors la position représentée en pointillés sur la figure 2. Le tronçon 1 poursuit son mouvement dû à la vitesse initiale de l'engin cependant que le tronçon 2 est freiné aérodynamiquement par les volets 5 ce qui assure la séparation effective des deux tronçons.Thus, upon unlocking, the movement of withdrawal of the fingers 7 ensures the rupture of the screws 9 which releases the flaps 5. These then take the position shown in dotted lines in FIG. 2. The section 1 continues its movement due to the initial speed of the machine, however, section 2 is aerodynamically braked by flaps 5 which ensures separation effective of the two sections.

Pour le montage des différents éléments du système, un jeu axial est nécessaire. Pour le compenser après montage, on peut prévoir un segment périphérique 6 (Figs. 4 et 5) dont les flancs sont inclinés en vis-à-vis de flancs inclinés complémentaires des enveloppes des tronçons 1 et 2. Au moyen de vis de pression disposées de manière connue, le segment vient s'arc-bouter et caler les deux enveloppes.For the assembly of the various elements of the system, an axial clearance is necessary. To compensate for it after assembly, a peripheral segment 6 (Figs. 4 and 5) whose sides are inclined opposite of inclined sides complementary to the envelopes of sections 1 and 2. Au by means of pressure screws arranged in a known manner, the segment comes brace and wedge the two envelopes.

Les principaux avantages d'un tel système de séparation selon l'invention ont déjà été mentionnés plus haut. On peut y ajouter que l'utilisation du segment 6 assure une bonne transmission mécanique avec rattrapage du jeu et que le système permet de déverrouiller simultanément la liaison entre les deux tronçons et de libérer les volets aérodynamiques avec un seul événement.The main advantages of such a separation system according to the invention have already been mentioned above. We can add that the use of segment 6 ensures good mechanical transmission with game catch-up and that the system allows you to simultaneously unlock the link between the two sections and release the aerodynamic flaps with a single event.

Claims (4)

  1. System for separating missile sections with mechanical unlocking allowing two sections (1, 2) of a missile to be uncoupled, characterized in that it comprises:
    a hub (13) comprising a great many micro-actuators (3) arranged radially, the said hub being secured to one of the said sections (1);
    a cylindrical casing (14) extending the end of the other section (2) and pierced with radial housings (15) to accommodate the outwardly directed pins (7) of the said micro-actuators in the assembled position;
    an annular chamber (4) arranged around the said micro-actuators to uniformly distribute the pressure obtaining therein towards the said micro-actuators; and
    pyrotechnic means (8, 12) for generating within the said chamber a pressure actuating the said micro-actuators to retract the said pins (7) inwards and thus uncouple the two sections (1, 2).
  2. Separation system according to Claim 1, characterized in that, between the ends of the casings of the two sections (1, 2), there is a peripheral segment (6) which has inclined flanks that complement the facing flanks of the casings so that the said segment can exert an axial force component on the said casings to compensate for the axial clearances between the said assembled sections.
  3. Separation system according to either of Claims 1 and 2, characterized in that it further comprises aerodynamic flaps (5) which are releasable upon separation of the two sections and mounted on one of the sections (2) so as to exert an aerodynamic braking effect on the said section at the time of separation.
  4. Separation system according to Claim 3, characterized in that each of the said flaps (5) is mounted on the section (2) to which it is attached by an articulation (10, 11) about a tangential axis and in that it is fixed in the retracted position to the pin (7) of one of the micro-actuators (3) by a breaking screw (9), the breakage of which is brought about by the retracting movement of the micro-actuator.
EP19960402543 1995-11-28 1996-11-26 Mechanical unlocking system together with aerodynamic breaking, for missile sectons Expired - Lifetime EP0777101B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9514077A FR2741710B1 (en) 1995-11-28 1995-11-28 MECHANICAL UNLOCKING AND AERODYNAMIC EXHAUST SEPARATION SYSTEM
FR9514077 1995-11-28

Publications (2)

Publication Number Publication Date
EP0777101A1 EP0777101A1 (en) 1997-06-04
EP0777101B1 true EP0777101B1 (en) 2001-02-28

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EP19960402543 Expired - Lifetime EP0777101B1 (en) 1995-11-28 1996-11-26 Mechanical unlocking system together with aerodynamic breaking, for missile sectons

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DE (1) DE69611889T2 (en)
FR (1) FR2741710B1 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2963803B1 (en) * 2010-08-10 2017-02-10 Astrium Sas FIXING DEVICE WITH PYROTECHNIC LOCK
CN112124611B (en) * 2020-08-22 2023-11-28 西安科为实业发展有限责任公司 Shelling separation system and method for cylindrical jet type folding wing aircraft

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2154307B (en) * 1984-02-15 1987-06-17 Portsmouth Aviat Limited Improved store for carriage on aircraft
US5020436A (en) * 1989-07-24 1991-06-04 General Dynamics Corp., Air Defense Systems Div. Booster retarding apparatus
US5318255A (en) * 1992-06-22 1994-06-07 Hughes Aircraft Company Stage separation mechanism for space vehicles

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DE69611889T2 (en) 2001-08-30
DE69611889D1 (en) 2001-04-05
EP0777101A1 (en) 1997-06-04
FR2741710B1 (en) 1998-01-02
FR2741710A1 (en) 1997-05-30

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