EP0767356A1 - Spin braking system for a cargo ammunition submissile - Google Patents

Spin braking system for a cargo ammunition submissile Download PDF

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Publication number
EP0767356A1
EP0767356A1 EP96401987A EP96401987A EP0767356A1 EP 0767356 A1 EP0767356 A1 EP 0767356A1 EP 96401987 A EP96401987 A EP 96401987A EP 96401987 A EP96401987 A EP 96401987A EP 0767356 A1 EP0767356 A1 EP 0767356A1
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EP
European Patent Office
Prior art keywords
submunition
shell
base
braking system
airbrakes
Prior art date
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Granted
Application number
EP96401987A
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German (de)
French (fr)
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EP0767356B1 (en
Inventor
Pierre Thomas
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Giat Industries SA
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Giat Industries SA
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Publication date
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Publication of EP0767356A1 publication Critical patent/EP0767356A1/en
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Publication of EP0767356B1 publication Critical patent/EP0767356B1/en
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    • 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
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/54—Spin braking means

Definitions

  • the present invention relates to an improvement made to an aerodynamic braking system of a submunition ejected from a cargo shell while being driven in a rotational movement, the braking system comprising several articulated air brakes which are attached around the body of the submunition and intended to deploy after the ejection of the submunition.
  • a cargo munition which is fired by the cannon of a field artillery, consists of a large caliber shell containing a payload which is released at a point in the trajectory of the shell.
  • the payload can be an illuminating load or consist of one or more submunitions.
  • a cargo ammunition of this type is notably described in document FR-A-2 363 077, this ammunition comprising a shell formed by a casing closed at its front end by a warhead and at its rear end by a base, this base being connected to the envelope by means of a mechanical connection intended to break when the shell was unloaded.
  • the cargo shell is generally fired from a barrel with a rifled tube to impart to the shell a very rapid rotational movement intended to stabilize it on its trajectory. Under these conditions, when the shell is unloaded, the payload is ejected while also being driven by a rapid rotational movement.
  • new generation submunitions carry target detectors and / or navigation systems, the operation of which is based on a low rotational speed of the submunitions after their ejection.
  • the submunitions are equipped with a braking system constituted by articulated airbrakes which are attached around the body of the submunition and intended to deploy after the ejection of the submunition to slow down its movement of rotation.
  • these submunitions are more and more bulky because of the large number of components they contain, which requires a reduction in the thickness of the shell of the shell, thus resulting in a reduction in its resistance.
  • the stripping system used is necessarily at low pressure so as not to damage the shell of the shell and the systems on board in the submunitions.
  • the submunition or munitions which are placed inside the shell are in particular subjected to centrifugal forces which tend to spread the airbrakes by pressing them against the wall of the envelope or of the base. This results in an adhesion or friction force which will then oppose the ejection force produced by the stripping system to eject the base and the submunitions. This can cause malfunctions, especially when the unloading system is at low pressure.
  • the object of the invention is to overcome these drawbacks by providing an improvement to an aerodynamic braking system of the aforementioned type, an improvement which is characterized in that the braking system also comprises a device for holding the airbrakes in their folded position at l inside the shell, holding device which is released following the ejection of the submunition to allow the opening of the air brakes outside the shell of the shell, the holding device consisting of bars or legs interposed between the airbrakes and the shell or the shell of the shell, these legs being integral with a support attached against an end face of the submunition.
  • the support of the holding device is constituted by a cup, and the tabs are connected, by one end, to the periphery of the cup, extending on the same side thereof as follows. a direction substantially perpendicular to the plane of the cup.
  • the legs are for example angularly regularly spaced around the cup, and their number is such that at least one leg is associated with an airbrake.
  • the legs have come from the same piece as the cup or are fixed to the latter by a welding or gluing operation.
  • the legs may advantageously be cylindrical pins.
  • the effects of centrifugal force are significantly reduced due to a significant reduction in the contact surface between the braking system and the shell, this contact surface being limited to the legs of the holding device, and, once the submunition is ejected from the shell, the centrifugal force can then be exerted on the legs holding device to move them away from the submunition and allow the airbrakes to open.
  • the shell of the shell is arranged to receive in part the body of a submunition and the airbrakes of the submunition come to be located opposite the side wall of the shell, the shell assembly and submunition is ejected from the shell of the shell as a result of the actuation of the stripping system, known per se.
  • a connecting element is fixed to the device for holding the airbrakes of the submunition on the one hand and to the shell of the shell on the other hand, this connecting device being constituted by a drop-down means, such as a cable or a chain for example, to release the tabs from the notches or holes in the submunition, once the base itself has been released from the submunition, and allow the opening of the airbrakes under the action of centrifugal force.
  • the effects of the centrifugal force are notably reduced as a result of a significant reduction in the contact surface between the braking system and the shell base, this contact surface being limited to the legs of the maintenance, which facilitates the separation of the base from the submunition.
  • the holding device makes it possible to retain the airbrakes of a submunition in their folded position during the interior and exterior ballistic phases of the shell and this, as long as the submunition n is not ejected from the shell of the shell.
  • the friction forces between the braking system and the shell or the shell of the shell, which result from the centrifugal force, are considerably reduced as a result of a significant reduction in the surfaces of contact.
  • a device for maintaining the airbrakes of a submunition can be envisaged independently of the number of submunitions on board the cargo shell.
  • the holding device is of a simple structure and easy to implement for a reduced manufacturing cost.
  • the cargo shell 1 illustrated in FIG. 1 comprises an envelope 2, the front part of which is closed by a warhead 4 and the rear part of which is closed by a base 5.
  • the base 5 is connected to the envelope 2 by means of a mechanical link (not shown) intended to break when the shell 1 was unloaded.
  • connection is for example obtained by freely engaging the base 5 in the casing 2 and retaining it axially by fixing means having a break point such as screws or pins.
  • the shell 2 of shell 1 contains one or more submunitions 7 which are ejected when the shell 1 is unloaded, that is to say after the separation between shell 2 and base 5 which is caused by a stripping system known per se.
  • a belt 9 fixed around the envelope 2 is intended to take the scratches from the barrel launching tube which pulls the shell 1 to impart to the latter a rapid rotational movement intended to stabilize it on its trajectory.
  • the submunitions 7 which are also driven in rotation by the shell or the shell of the shell, for example by keys, are consequently ejected while being animated by a rapid rotational movement and, for the reasons explained in preamble, this speed is reduced by means of a braking system constituted by airbrakes 10 which deploy automatically after the ejection of the submunitions.
  • an air brake 10 is for example constituted by a blade 12 mounted articulated on the body of the submunition 7.
  • the blade 12 is shaped with a radius of curvature such that it can match the shape of the body of the submunition 7.
  • Several airbrakes 10, four in number for example, are thus distributed around the body of the submunition 7.
  • the blades 12 conform to the shape of the body of the submunition 7 and the airbrakes 10 are in a folded position between the body of the submunition 7 and either inner wall of the envelope 2, or the inner wall of the base 5, as will be explained below.
  • a holding device 15 is used to retain the airbrakes 10 in their folded position inside the shell 1 to avoid the effects of centrifugal force resulting from the rotational movement imparted to the shell 1 from the cannon shot. In fact, the centrifugal force tends to spread the airbrakes 10 to press them against the casing 2 or the base 5 until the shell 1 is unloaded.
  • the holding system 15 consists of a set of lugs or bars 20 which are interposed between the airbrakes 10 and the internal wall of the casing 2 or of the base 5.
  • the lugs 20 are integral with a support 22 which is simply fitted against an end face or rear end face of the submunition 7.
  • the support 22 is constituted by a cup 23.
  • the tabs 20 are connected by one end to the periphery of the cup 23, so as to extend substantially perpendicular to the cup 23 and on the same side of it.
  • the tabs 20 delimit between them a cylinder and extend along the generatrices of this cylinder.
  • the tabs 20 may have come in one piece with the cup 23 or be fixed to the latter by a bonding or welding operation.
  • the base 5 of the shell 1 can be arranged, in particular as regards the axial length of its cylindrical side wall 5a, to receive the rear part of the submunition. Under these conditions, once the submunition has been placed in the shell 1, the airbrakes 10 will be located opposite the side wall 5a of the base 5.
  • a connecting means 25 is provided between the holding device 15 and the base 5.
  • this means is unrollable and consists of a cable or a chain 27 whose two free ends are respectively connected to the cup 23 and at the bottom of the base 5.
  • the cup 23 advantageously has a rounded shape to delimit a space intended to receive the cable 27.
  • Shell 1 is fired while being rotated at high speed.
  • the submunition 7 which is rotated by the shell 1 is therefore subjected to the action of centrifugal force which should have the effect of pressing the tabs 20 against the side wall 5a of the base 5 while eliminating the initial play e .
  • the centrifugal force can at most only cause bending of the legs 20, so that only the central part of the legs 20 is capable of coming into contact with the side wall 5a of the base 5.
  • This contact surface can moreover be limited to the minimum with cylindrical legs 20. The frictional forces which result from this contact are therefore considerably reduced because, without the presence of these lugs 20, the blades 12 of the airbrakes 10 would come directly into contact with the side wall 5a of the base 5 on a significantly larger surface.
  • the unloading of shell 1 will then take place at a point in its trajectory following the actuation of a unloading system known per se.
  • This system is for example constituted by a gas-generating pyrotechnic composition which is mounted in the warhead 4 and by a chronometric initiation rocket. After initiation of the pyrotechnic composition, the pressure of the gases resulting from the combustion is applied to the front end face of the submunition 7 by means of a piston until the breaking of the mechanical connection between the envelope 2 and base 5.
  • the assembly consisting of the base 5 and the submunition 7 ejects out of the casing 2 while also being driven by a rapid rotational movement.
  • the aerodynamic forces which are then applied to the base 5, in particular on the free end face of its side wall 5a which is no longer in abutment against an associated shoulder of the submunition 7, and the relaxation of the Belleville washer 29 cause the base 5 of the submunition to separate 7. This separation is carried out all the more easily when the friction forces of the tabs 20 on the side wall 5a of the base 5 are reduced.
  • the airbrakes although released from the envelope 2 are still retained in their folded position by the holding device 15.
  • the cable 27 is stretched and consequently pulls on the holding device 15, which has the effect of releasing the tabs 20 from the notches 24 of the submunition 7.
  • the device holding 15 is thus released from the submunition 7 with the legs 20 which, under the action of centrifugal force, move apart to allow the opening or deployment of the airbrakes 10 in order to slow down the rotational movement of the under -ammunition.
  • the airbrakes 10 of a submunition 7 can also be retained in their folded position until the ejection of the submunition 7 by means of a holding device 15 similar to that previously described.
  • the centrifugal force resulting from the rotation of the shell and the submunitions from the moment of the cannon shot will also have the effect of pressing the legs 20 against the envelope 2 but on a surface limited contact, which reduces the friction forces which will then oppose the action of the unloading system.
  • the rise in pressure of the gases generated by the combustion of the pyrotechnic composition causes the mechanical connection between the casing 2 and the base 5 to break.
  • the base 5 is released from the envelope 2 then is ejected, and the submunition 7 in turn comes out of envelope 2 under the thrust of the gases.
  • the centrifugal force acts first on the legs 20 by moving them away from the body of the submunition 7 in order to disengage them from the airbrakes 10, and then on the airbrakes 10 themselves who go then open or deploy to slow down the rotational movement of the submunition 7.
  • the cup 23 of the holding device 15 is pierced with a central opening 30.
  • Figures 8 and 9 show a holding device according to another embodiment of the invention.
  • the holding tabs 20 are formed by cylindrical pins, regularly distributed angularly and fixed by welding to the cup 23.
  • Each pin enters a hole 24 arranged on the body of the submunition 7.
  • This embodiment has the advantage of being simple to manufacture.
  • the support provided by the pins is more rigid than that allowed by thin legs and it also makes it possible to further reduce friction. Indeed, the contact between the pins and, on the one hand the airbrakes 10, and on the other hand the internal wall of the casing or of the base takes place along a reduced surface which is that of the generators of the pins.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Braking Arrangements (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Valves And Accessory Devices For Braking Systems (AREA)

Abstract

The braking system comprises a container (2) surrounded by a skirt (5). It is equipped with several air brakes (10) which are folded over the sub-munition and designed to deploy once it has been ejected from the carrier shell. The air brakes are held in their folded position inside the shell by a plate (23). The plate has series of radial arms (20) spaced evenly round the edge of the plate and attached to it by welding or adhesive, or made in one piece with it. The components of the sub-munition are joined together by a flexible element (25) such as a cable or chain, and the air brake retaining plate and arms are deployed by centrifugal force.

Description

La présente invention concerne un perfectionnement apporté à un système de freinage aérodynamique d'une sous-munition éjectée d'un obus cargo en étant animée d'un mouvement de rotation, le système de freinage comprenant plusieurs aérofreins articulés qui sont rapportés autour du corps de la sous-munition et destinés à se déployer après l'éjection de la sous-munition.The present invention relates to an improvement made to an aerodynamic braking system of a submunition ejected from a cargo shell while being driven in a rotational movement, the braking system comprising several articulated air brakes which are attached around the body of the submunition and intended to deploy after the ejection of the submunition.

D'une manière générale, une munition cargo qui est tirée par le canon d'une artillerie de campagne, est constituée d'un obus de gros calibre renfermant une charge utile qui est libérée en un point de la trajectoire de l'obus. La charge utile peut être une charge éclairante ou être constituée d'une ou plusieurs sous-munitions.In general, a cargo munition which is fired by the cannon of a field artillery, consists of a large caliber shell containing a payload which is released at a point in the trajectory of the shell. The payload can be an illuminating load or consist of one or more submunitions.

Une munition cargo de ce type est notamment décrite dans le document FR-A-2 363 077, cette munition comprenant un obus formé d'une enveloppe fermée à son extrémité avant par une ogive et à son extrémité arrière par un culot, ce culot étant relié à l'enveloppe au moyen d'une liaison mécanique destinée à se rompre au moment du dépotage de l'obus.A cargo ammunition of this type is notably described in document FR-A-2 363 077, this ammunition comprising a shell formed by a casing closed at its front end by a warhead and at its rear end by a base, this base being connected to the envelope by means of a mechanical connection intended to break when the shell was unloaded.

L'obus cargo est généralement tiré à partir d'un canon à tube rayé pour imprimer à l'obus un mouvement de rotation très rapide destiné à le stabiliser sur sa trajectoire. Dans ces conditions, au moment du dépotage de l'obus, la charge utile est éjectée en étant également animée d'un mouvement de rotation rapide.The cargo shell is generally fired from a barrel with a rifled tube to impart to the shell a very rapid rotational movement intended to stabilize it on its trajectory. Under these conditions, when the shell is unloaded, the payload is ejected while also being driven by a rapid rotational movement.

Cependant, les sous-munitions de la nouvelle génération emportent des détecteurs de cible et/ou des systèmes de navigation, dont le fonctionnement repose sur une vitesse de rotation faible des sous-munitions après leur éjection. A cet effet, on équipe les sous-munitions d'un système de freinage constitué par des aérofreins articulés qui sont rapportés autour du corps de la sous-munition et destinés à se déployer après l'éjection de la sous-munition pour ralentir son mouvement de rotation.However, new generation submunitions carry target detectors and / or navigation systems, the operation of which is based on a low rotational speed of the submunitions after their ejection. For this purpose, the submunitions are equipped with a braking system constituted by articulated airbrakes which are attached around the body of the submunition and intended to deploy after the ejection of the submunition to slow down its movement of rotation.

En outre, ces sous-munitions sont de plus en plus encombrantes de par le grand nombre de composants qu'elles renferment, ce qui nécessite une réduction de l'épaisseur de l'enveloppe de l'obus entraînant ainsi une diminution de sa résistance. Dans ce cas, le système de dépotage utilisé est nécessairement à faible pression pour ne pas endommager l'enveloppe de l'obus et les systèmes embarqués dans les sous-munitions.In addition, these submunitions are more and more bulky because of the large number of components they contain, which requires a reduction in the thickness of the shell of the shell, thus resulting in a reduction in its resistance. In this case, the stripping system used is necessarily at low pressure so as not to damage the shell of the shell and the systems on board in the submunitions.

L'obus étant gyrostabilisé, la ou les sous-munitions qui sont placées à l'intérieur de l'obus sont notamment soumises à des forces centrifuges qui tendent à écarter les aérofreins en les plaquant contre la paroi de l'enveloppe ou du culot. Il en résulte une force d'adhérence ou de frottement qui s'opposera ensuite à la force d'éjection produite par le système de dépotage pour éjecter le culot et les sous-munitions. Il peut en résulter des dysfonctionnements, notamment lorsque le système de dépotage est à faible pression.The shell being gyro-stabilized, the submunition or munitions which are placed inside the shell are in particular subjected to centrifugal forces which tend to spread the airbrakes by pressing them against the wall of the envelope or of the base. This results in an adhesion or friction force which will then oppose the ejection force produced by the stripping system to eject the base and the submunitions. This can cause malfunctions, especially when the unloading system is at low pressure.

Le but de l'invention est de pallier ces inconvénients en apportant un perfectionnement à un système de freinage aérodynamique du type précité, perfectionnement qui est caractérisé en ce que le système de freinage comprend également un dispositif de maintien des aérofreins dans leur position repliée à l'intérieur de l'obus, dispositif de maintien qui est libéré suite à l'éjection de la sous-munition pour permettre l'ouverture des aéro-freins hors de l'enveloppe de l'obus, le dispositif de maintien étant constitué par des barrettes ou pattes interposées entre les aérofreins et l'enveloppe ou le culot de l'obus, ces pattes étant solidaires d'un support rapporté contre une face d'extrémité de la sous-munition.The object of the invention is to overcome these drawbacks by providing an improvement to an aerodynamic braking system of the aforementioned type, an improvement which is characterized in that the braking system also comprises a device for holding the airbrakes in their folded position at l inside the shell, holding device which is released following the ejection of the submunition to allow the opening of the air brakes outside the shell of the shell, the holding device consisting of bars or legs interposed between the airbrakes and the shell or the shell of the shell, these legs being integral with a support attached against an end face of the submunition.

A titre d'exemple, le support du dispositif de maintien est constitué par une coupelle, et les pattes sont raccordées, par une extrémité, à la périphérie de la coupelle en s'étendant d'un même côté de celle-ci suivant une direction sensiblement perpendiculaire au plan de la coupelle.By way of example, the support of the holding device is constituted by a cup, and the tabs are connected, by one end, to the periphery of the cup, extending on the same side thereof as follows. a direction substantially perpendicular to the plane of the cup.

Les pattes sont par exemple angulairement régulièrement espacées autour de la coupelle, et leur nombre est tel qu'au moins une patte est associée à un aérofrein.The legs are for example angularly regularly spaced around the cup, and their number is such that at least one leg is associated with an airbrake.

D'une manière générale, les pattes sont venues d'une même pièce que la coupelle ou sont fixées à celle-ci par une opération de soudage ou collage.In general, the legs have come from the same piece as the cup or are fixed to the latter by a welding or gluing operation.

Les pattes pourront avantageusement être des goupilles cylindriques.The legs may advantageously be cylindrical pins.

Lorsque les aérofreins d'une sous-munition sont situés en regard de l'enveloppe de l'obus, les effets de la force centrifuge sont notablement diminués par suite d'une réduction importante de la surface de contact entre le système de freinage et l'enveloppe de l'obus, cette surface de contact étant limitée aux pattes du dispositif de maintien, et, une fois la sous-munition éjectée hors de l'enveloppe de l'obus, la force centrifuge peut alors s'exercer sur les pattes du dispositif de maintien pour les écarter de la sous-munition et permettre l'ouverture des aérofreins.When the airbrakes of a submunition are located opposite the shell of the shell, the effects of centrifugal force are significantly reduced due to a significant reduction in the contact surface between the braking system and the shell, this contact surface being limited to the legs of the holding device, and, once the submunition is ejected from the shell, the centrifugal force can then be exerted on the legs holding device to move them away from the submunition and allow the airbrakes to open.

Par contre, lorsque le culot de l'obus est aménagé pour recevoir en partie le corps d'une sous-munition et que les aérofreins de la sous-munition viennent se situer en regard de la paroi latérale du culot, l'ensemble culot et sous-munition est éjecté hors de l'enveloppe de l'obus par suite de l'actionnement du système de dépotage, connu en soi.On the other hand, when the shell of the shell is arranged to receive in part the body of a submunition and the airbrakes of the submunition come to be located opposite the side wall of the shell, the shell assembly and submunition is ejected from the shell of the shell as a result of the actuation of the stripping system, known per se.

Dans ce cas et selon d'autres caractéristiques de l'invention :

  • les extrémités libres des pattes du dispositif de maintien sont initialement reçues dans des encoches ou des trous ménagés dans le corps de la sous-munition, et
  • un moyen élastique est monté à l'état comprimé entre le culot de l'obus et le corps de la sous-munition, la détente de ce moyen élastique, une fois l'ensemble culot et sous-munition éjecté hors de l'enveloppe de l'obus, permettant de séparer le culot de la sous-munition alors que les pattes du dispositif de maintien des aérofreins restent maintenues en place au moyen des encoches ou des trous de la sous-munition pour faciliter la séparation du culot d'une part et retenir en place le dispositif de maintien et empêcher l'ouverture des aérofreins d'autre part.
In this case and according to other characteristics of the invention:
  • the free ends of the legs of the holding device are initially received in notches or holes made in the body of the submunition, and
  • an elastic means is mounted in the compressed state between the shell of the shell and the body of the submunition, the relaxation of this elastic means, once the base and submunition assembly ejected from the shell of the shell, allowing the base to be separated from the submunition while the legs of the airbrake holding device remain maintained in place by means of the notches or holes in the submunition to facilitate the separation of the base on the one hand and retain in place the holding device and prevent the opening of the airbrakes on the other hand.

En outre et selon une autre caractéristique de l'invention, un élément de liaison est fixé au dispositif de maintien des aérofreins de la sous-munition d'une part et au culot de l'obus d'autre part, ce dispositif de liaison étant constitué par un moyen déroulable, tel qu'un câble ou une chaînette par exemple, pour dégager les pattes des encoches ou des trous de la sous-munition, une fois le culot lui-même dégagé de la sous-munition, et permettre l'ouverture des aérofreins sous l'action de la force centrifuge.In addition and according to another characteristic of the invention, a connecting element is fixed to the device for holding the airbrakes of the submunition on the one hand and to the shell of the shell on the other hand, this connecting device being constituted by a drop-down means, such as a cable or a chain for example, to release the tabs from the notches or holes in the submunition, once the base itself has been released from the submunition, and allow the opening of the airbrakes under the action of centrifugal force.

Dans ce cas également, les effets de la force centrifuge sont notablement diminués par suite d'une réduction importante de la surface de contact entre le système de freinage et le culot de l'obus, cette surface de contact étant limitée aux pattes du dispositif de maintien, ce qui facilite la séparation du culot de la sous-munition.In this case also, the effects of the centrifugal force are notably reduced as a result of a significant reduction in the contact surface between the braking system and the shell base, this contact surface being limited to the legs of the maintenance, which facilitates the separation of the base from the submunition.

Selon un avantage important de l'invention, le dispositif de maintien permet de retenir les aérofreins d'une sous-munition dans leur position repliée pendant les phases de balistique intérieure et extérieure de l'obus et ce, tant que la sous-munition n'est pas éjectée hors de l'enveloppe de l'obus.According to an important advantage of the invention, the holding device makes it possible to retain the airbrakes of a submunition in their folded position during the interior and exterior ballistic phases of the shell and this, as long as the submunition n is not ejected from the shell of the shell.

Selon un autre avantage de l'invention, les forces de frottement entre le système de freinage et l'enveloppe ou le culot de l'obus, qui résultent de la force centrifuge, sont considérablement réduites par suite d'une diminution importante des surfaces de contact.According to another advantage of the invention, the friction forces between the braking system and the shell or the shell of the shell, which result from the centrifugal force, are considerably reduced as a result of a significant reduction in the surfaces of contact.

Selon un autre avantage de l'invention, un dispositif de maintien des aérofreins d'une sous-munition peut être envisagé indépendamment du nombre de sous-munitions embarquées dans l'obus cargo.According to another advantage of the invention, a device for maintaining the airbrakes of a submunition can be envisaged independently of the number of submunitions on board the cargo shell.

Selon un autre avantage de l'invention, le dispositif de maintien est d'une structure simple et facile à mettre en oeuvre pour un coût de fabrication réduit.According to another advantage of the invention, the holding device is of a simple structure and easy to implement for a reduced manufacturing cost.

D'autres avantages, caractéristiques et détails de l'invention ressortiront de la description explicative qui va suivre, faite en référence aux dessins annexés donnés uniquement à titre d'exemple et dans lesquels :

  • la figure 1 est une vue en perspective d'un obus cargo équipé d'un système de freinage perfectionné selon l'invention,
  • la figure 2 est une demi-vue en coupe partielle de la partie arrière de l'obus pour illustrer les différents éléments constitutifs du système de freinage selon l'invention, en particulier un dispositif de maintien des aérofreins constituant le système de freinage d'une sous-munition lorsque les aérofreins viennent se loger dans le culot après montage de la sous-munition dans l'obus,
  • la figure 3 est une vue en perspective éclatée du dispositif de maintien des aérofreins selon un mode de réalisation de l'invention,
  • les figures 4 et 5 sont des vues en perspective partielle illustrant les deux étapes successives de fonctionnement du système de freinage perfectionné selon l'invention,
  • la figure 6 est une demi-vue en coupe semblable à celle de la figure 2 lorsque les aérofreins d'une sous-munition ne viennent pas se loger dans le culot après montage de la sous-munition dans l'obus, et
  • la figure 7 est une vue en perspective d'une variante de réalisation du système de maintien illustré à la figure 3.
  • la figure 8 est une demi vue en coupe partielle de la partie arrière d'un obus montrant un dispositif de maintien selon un autre mode de réalisation de l'invention,
  • la figure 9 est une vue en perspective du dispositif de maintien illustré à la figure 8.
Other advantages, characteristics and details of the invention will emerge from the explanatory description which follows, given with reference to the appended drawings given solely by way of example and in which:
  • FIG. 1 is a perspective view of a cargo shell equipped with an improved braking system according to the invention,
  • Figure 2 is a partial sectional half-view of the rear part of the shell to illustrate the various components of the braking system according to the invention, in particular a device for holding airbrakes constituting the braking system of a submunition when the airbrakes are housed in the base after mounting the submunition in the shell,
  • FIG. 3 is an exploded perspective view of the device for holding the airbrakes according to one embodiment of the invention,
  • FIGS. 4 and 5 are partial perspective views illustrating the two successive stages of operation of the improved braking system according to the invention,
  • FIG. 6 is a half-view in section similar to that of FIG. 2 when the airbrakes of a submunition do not come to be housed in the base after assembly of the submunition in the shell, and
  • FIG. 7 is a perspective view of an alternative embodiment of the holding system illustrated in FIG. 3.
  • Figure 8 is a partial sectional half view of the rear part of a shell showing a holding device according to another embodiment of the invention,
  • FIG. 9 is a perspective view of the holding device illustrated in FIG. 8.

L'obus cargo 1 illustré à la figure 1 comprend une enveloppe 2 dont la partie avant est fermée par une ogive 4 et dont la partie arrière est fermée par un culot 5. Le culot 5 est relié à l'enveloppe 2 au moyen d'une liaison mécanique (non représentée) destinée à se rompre au moment du dépotage de l'obus 1.The cargo shell 1 illustrated in FIG. 1 comprises an envelope 2, the front part of which is closed by a warhead 4 and the rear part of which is closed by a base 5. The base 5 is connected to the envelope 2 by means of a mechanical link (not shown) intended to break when the shell 1 was unloaded.

Cette liaison est par exemple obtenue en engageant librement le culot 5 dans l'enveloppe 2 et en le retenant axialement par des moyens de fixation présentant une amorce de rupture tels que des vis ou des goupilles.This connection is for example obtained by freely engaging the base 5 in the casing 2 and retaining it axially by fixing means having a break point such as screws or pins.

L'enveloppe 2 de l'obus 1 renferme une ou plusieurs sous-munitions 7 qui sont éjectées au moment du dépotage de l'obus 1, c'est-à-dire après la séparation entre l'enveloppe 2 et le culot 5 qui est provoquée par un système de dépotage connu en soi.The shell 2 of shell 1 contains one or more submunitions 7 which are ejected when the shell 1 is unloaded, that is to say after the separation between shell 2 and base 5 which is caused by a stripping system known per se.

Une ceinture 9 fixée autour de l'enveloppe 2 est destinée à prendre les rayures du tube de lancement du canon qui tire l'obus 1 pour imprimer à ce dernier un mouvement de rotation rapide destiné à le stabiliser sur sa trajectoire.A belt 9 fixed around the envelope 2 is intended to take the scratches from the barrel launching tube which pulls the shell 1 to impart to the latter a rapid rotational movement intended to stabilize it on its trajectory.

Les sous-munitions 7 qui sont également entraînées en rotation par l'enveloppe ou le culot de l'obus grâce par exemple à des clavettes, sont par conséquent éjectées en étant animées d'un mouvement de rotation rapide et, pour les raisons explicitées en préambule, cette vitesse de rotation est réduite au moyen d'un système de freinage constitué par des aérofreins 10 qui se déploient automatiquement après l'éjection des sous-munitions.The submunitions 7 which are also driven in rotation by the shell or the shell of the shell, for example by keys, are consequently ejected while being animated by a rapid rotational movement and, for the reasons explained in preamble, this speed is reduced by means of a braking system constituted by airbrakes 10 which deploy automatically after the ejection of the submunitions.

En se reportant notamment aux figures 4 et 5, un aérofrein 10 est par exemple constitué par une lame 12 montée articulée sur le corps de la sous-munition 7. La lame 12 est conformée avec un rayon de courbure tel qu'elle puisse venir épouser la forme du corps de la sous-munition 7. Plusieurs aérofreins 10, au nombre de quatre par exemple, sont ainsi répartis autour du corps de la sous-munition 7.With particular reference to FIGS. 4 and 5, an air brake 10 is for example constituted by a blade 12 mounted articulated on the body of the submunition 7. The blade 12 is shaped with a radius of curvature such that it can match the shape of the body of the submunition 7. Several airbrakes 10, four in number for example, are thus distributed around the body of the submunition 7.

Une fois la sous-munition 7 logée dans l'obus 1, les lames 12 épousent la forme du corps de la sous-munition 7 et les aérofreins 10 se retrouvent dans une position repliée entre le corps de la sous-munition 7 et soit la paroi interne de l'enveloppe 2, soit la paroi interne du culot 5, comme cela sera explicité plus loin.Once the submunition 7 is housed in the shell 1, the blades 12 conform to the shape of the body of the submunition 7 and the airbrakes 10 are in a folded position between the body of the submunition 7 and either inner wall of the envelope 2, or the inner wall of the base 5, as will be explained below.

Un dispositif de maintien 15 est utilisé pour retenir les aérofreins 10 dans leur position repliée à l'intérieur de l'obus 1 pour éviter les effets de la force centrifuge résultant du mouvement de rotation imprimé à l'obus 1 dès le coup de canon. En effet, la force centrifuge tend à écarter les aérofreins 10 pour venir les plaquer contre l'enveloppe 2 ou le culot 5 jusqu'au dépotage de l'obus 1.A holding device 15 is used to retain the airbrakes 10 in their folded position inside the shell 1 to avoid the effects of centrifugal force resulting from the rotational movement imparted to the shell 1 from the cannon shot. In fact, the centrifugal force tends to spread the airbrakes 10 to press them against the casing 2 or the base 5 until the shell 1 is unloaded.

D'une manière générale, le système de maintien 15 est constitué par un ensemble de pattes ou barrettes 20 qui sont interposées entre les aérofreins 10 et la paroi interne de l'enveloppe 2 ou du culot 5. Les pattes 20 sont solidaires d'un support 22 qui est simplement rapporté contre une face d'extrémité ou face d'extrémité arrière de la sous-munition 7.In general, the holding system 15 consists of a set of lugs or bars 20 which are interposed between the airbrakes 10 and the internal wall of the casing 2 or of the base 5. The lugs 20 are integral with a support 22 which is simply fitted against an end face or rear end face of the submunition 7.

Selon un exemple de réalisation, le support 22 est constitué par une coupelle 23. Les pattes 20 sont raccordées par une extrémité à la périphérie de la coupelle 23, de manière à s'étendre sensiblement perpendiculairement à la coupelle 23 et d'un même côté de celle-ci. Autrement dit, les pattes 20 délimitent entre elles un cylindre et s'étendent selon les génératrices de ce cylindre.According to an exemplary embodiment, the support 22 is constituted by a cup 23. The tabs 20 are connected by one end to the periphery of the cup 23, so as to extend substantially perpendicular to the cup 23 and on the same side of it. In other words, the tabs 20 delimit between them a cylinder and extend along the generatrices of this cylinder.

Les pattes 20 peuvent être venues d'une même pièce avec la coupelle 23 ou être fixées à celle-ci par une opération de collage ou de soudage.The tabs 20 may have come in one piece with the cup 23 or be fixed to the latter by a bonding or welding operation.

Selon un premier mode de réalisation illustré aux figures 1, 2, 4 et 5, on va considérer un obus cargo avec une charge utile constituée d'une seule sous-munition 7, dont les aérofreins 10 sont situés, ce qui est souvent le cas, vers une extrémité ou extrémité arrière de la sous-munition en considérant le sens d'introduction de la sous-munition dans l'obus 1. En outre, le culot 5 de l'obus 1 peut être aménagé, notamment en ce qui concerne la longueur axiale de sa paroi latérale cylindrique 5a, pour recevoir la partie arrière de la sous-munition. Dans ces conditions, une fois la sous-munition mise en place dans l'obus 1 les aérofreins 10 vont se situer en regard de la paroi latérale 5a du culot 5.According to a first embodiment illustrated in Figures 1, 2, 4 and 5, we will consider a cargo shell with a payload consisting of a single submunition 7, whose airbrakes 10 are located, which is often the case, towards a rear end or rear end of the submunition considering the direction of introduction of the submarine ammunition in the shell 1. In addition, the base 5 of the shell 1 can be arranged, in particular as regards the axial length of its cylindrical side wall 5a, to receive the rear part of the submunition. Under these conditions, once the submunition has been placed in the shell 1, the airbrakes 10 will be located opposite the side wall 5a of the base 5.

Le dispositif de maintien 15 vient se monter entre le culot 5 et la partie arrière de la sous-munition 7, si bien qu'après montage, comme cela est illustré à la figure 2 :

  • la coupelle 23 est coincée entre le fond du culot 5 et une face d'extrémité arrière de la sous-munition 7, et
  • les pattes 20 sont positionnées entre le corps de la sous-munition 7 et la paroi latérale 5a du culot 5 et les extrémités libres de ces pattes 20 viennent s'engager dans des encoches 24 ménagées dans la sous-munition 7, un léger jeu ou espace e séparant les pattes 20 et la paroi latérale 5a du culot 5.
The holding device 15 is mounted between the base 5 and the rear part of the submunition 7, so that after assembly, as illustrated in FIG. 2:
  • the cup 23 is wedged between the bottom of the base 5 and a rear end face of the submunition 7, and
  • the tabs 20 are positioned between the body of the submunition 7 and the side wall 5a of the base 5 and the free ends of these tabs 20 engage in notches 24 formed in the submunition 7, a slight play or space e separating the legs 20 and the side wall 5a of the base 5.

Un moyen de liaison 25 est prévu entre le dispositif de maintien 15 et le culot 5. A titre d'exemple, ce moyen est déroulable et constitué par un câble ou une chaînette 27 dont les deux extrémités libres sont respectivement reliées à la coupelle 23 et au fond du culot 5. La coupelle 23 présente avantageusement une forme bombée pour délimiter un espace destiné à recevoir le câble 27.A connecting means 25 is provided between the holding device 15 and the base 5. For example, this means is unrollable and consists of a cable or a chain 27 whose two free ends are respectively connected to the cup 23 and at the bottom of the base 5. The cup 23 advantageously has a rounded shape to delimit a space intended to receive the cable 27.

Enfin, un élément élastique, tel qu'une rondelle Belleville 29, est interposé entre le fond du culot 5 et la coupelle 23 du dispositif de maintien 15, cette rondelle 29 étant mise en compression une fois le culot 5 fixé à l'enveloppe 2.Finally, an elastic element, such as a Belleville washer 29, is interposed between the bottom of the base 5 and the cup 23 of the holding device 15, this washer 29 being compressed once the base 5 is fixed to the casing 2 .

Le fonctionnement du système de freinage va être explicité ci-après en référence aux figures 4 et 5.The operation of the braking system will be explained below with reference to FIGS. 4 and 5.

L'obus 1 est tiré en étant animé d'un mouvement de rotation à vitesse élevée. La sous-munition 7 qui est entraînée en rotation par l'obus 1, est donc soumise à l'action de la force centrifuge qui devrait avoir pour effet de plaquer les pattes 20 contre la paroi latérale 5a du culot 5 en supprimant le jeu initial e. Or, comme les pattes 20 sont radialement maintenues d'un côté par la coupelle 23 et de l'autre côté par les encoches 24 de la sous-munition 7, la force centrifuge ne peut tout au plus que provoquer un cintrage des pattes 20, de sorte que seule la partie centrale des pattes 20 est susceptible de venir en contact avec la paroi latérale 5a du culot 5. Cette surface de contact peut être d'ailleurs limitée au minimum avec des pattes 20 cylindriques. Les forces de frottement qui résultent de ce contact sont donc considérablement réduites car, sans la présence de ces pattes 20, les lames 12 des aérofreins 10 viendraient directement au contact de la paroi latérale 5a du culot 5 sur une surface notablement plus importante.Shell 1 is fired while being rotated at high speed. The submunition 7 which is rotated by the shell 1, is therefore subjected to the action of centrifugal force which should have the effect of pressing the tabs 20 against the side wall 5a of the base 5 while eliminating the initial play e . However, as the legs 20 are radially maintained on one side by the cup 23 and on the other side by the notches 24 of the submunition 7, the centrifugal force can at most only cause bending of the legs 20, so that only the central part of the legs 20 is capable of coming into contact with the side wall 5a of the base 5. This contact surface can moreover be limited to the minimum with cylindrical legs 20. The frictional forces which result from this contact are therefore considerably reduced because, without the presence of these lugs 20, the blades 12 of the airbrakes 10 would come directly into contact with the side wall 5a of the base 5 on a significantly larger surface.

Le dépotage de l'obus 1 va ensuite intervenir en un point de sa trajectoire suite à l'actionnement d'un système de dépotage connu en soi. Ce système est par exemple constitué par une composition pyrotechnique génératrice de gaz qui est montée dans l'ogive 4 et par une fusée chronométrique d'initiation. Après initiation de la composition pyrotechnique, la pression des gaz résultant de la combustion est appliquée sur la face d'extrémité avant de la sous-munition 7 par l'intermédiaire d'un piston jusqu'à provoquer la rupture de la liaison mécanique entre l'enveloppe 2 et le culot 5.The unloading of shell 1 will then take place at a point in its trajectory following the actuation of a unloading system known per se. This system is for example constituted by a gas-generating pyrotechnic composition which is mounted in the warhead 4 and by a chronometric initiation rocket. After initiation of the pyrotechnic composition, the pressure of the gases resulting from the combustion is applied to the front end face of the submunition 7 by means of a piston until the breaking of the mechanical connection between the envelope 2 and base 5.

Dans un premier temps illustré à la figure 4, l'ensemble constitué du culot 5 et de la sous-munition 7 s'éjecte hors de l'enveloppe 2 en étant également animé d'un mouvement de rotation rapide. Les forces aérodynamiques qui sont alors appliquées sur le culot 5, en particulier sur la face d'extrémité libre de sa paroi latérale 5a qui n'est plus en appui contre un épaulement associé de la sous-munition 7, et la détente de la rondelle Belleville 29 entraînent la séparation du culot 5 de la sous-munition 7. Cette séparation s'effectue d'autant plus facilement que les forces de frottement des pattes 20 sur la paroi latérale 5a du culot 5 sont réduites. Les aérofreins bien que dégagés de l'enveloppe 2 sont encore retenus dans leur position repliée par le dispositif de maintien 15. En effet, sous l'action des forces aérodynamiques, la coupelle 23 reste plaquée contre la sous-munition 7 et les pattes 20, qui sont retenues par les encoches 24 de la sous-munition 7, ne peuvent pas s'écarter ou s'ouvrir sous l'action de la force centrifuge. Enfin, le câble 27 en cours de déroulement ne produit aucune action sur le dispositif de maintien 15.Initially illustrated in Figure 4, the assembly consisting of the base 5 and the submunition 7 ejects out of the casing 2 while also being driven by a rapid rotational movement. The aerodynamic forces which are then applied to the base 5, in particular on the free end face of its side wall 5a which is no longer in abutment against an associated shoulder of the submunition 7, and the relaxation of the Belleville washer 29 cause the base 5 of the submunition to separate 7. This separation is carried out all the more easily when the friction forces of the tabs 20 on the side wall 5a of the base 5 are reduced. The airbrakes although released from the envelope 2 are still retained in their folded position by the holding device 15. In fact, under the action of aerodynamic forces, the cup 23 remains pressed against the submunition 7 and the legs 20 , which are retained by the notches 24 of the submunition 7, cannot move apart or open under the action of centrifugal force. Finally, the cable 27 during unwinding produces no action on the holding device 15.

Dans un deuxième temps illustré à la figure 5, le câble 27 est tendu et tire par conséquent sur le dispositif de maintien 15, ce qui a pour effet de dégager les pattes 20 hors des encoches 24 de la sous-munition 7. Le dispositif de maintien 15 se libère ainsi de la sous-munition 7 avec les pattes 20 qui, sous l'action de la force centrifuge, s'écartent pour permettre l'ouverture ou le déploiement des aérofreins 10 afin de ralentir le mouvement de rotation de la sous-munition.In a second step illustrated in FIG. 5, the cable 27 is stretched and consequently pulls on the holding device 15, which has the effect of releasing the tabs 20 from the notches 24 of the submunition 7. The device holding 15 is thus released from the submunition 7 with the legs 20 which, under the action of centrifugal force, move apart to allow the opening or deployment of the airbrakes 10 in order to slow down the rotational movement of the under -ammunition.

On va maintenant envisager des aérofreins d'une sous-munition ou de plusieurs sous-munitions embarquées dans un obus, qui sont cette fois-ci situés en regard de l'enveloppe de cet obus. Dans ce cas, la force centrifuge résultant de la mise en rotation de l'obus dès le coup de canon, tend à appliquer les aérofreins contre la paroi de l'enveloppe de l'obus. Les forces de frottement qui en résultent s'opposent alors à l'action du système de dépotage qui provoque l'éjection de la ou des sous-munitions après la séparation du culot de l'obus.We will now consider airbrakes of a submunition or of several submunitions on board a shell, which are this time located opposite the envelope of this shell. In this case, the centrifugal force resulting from the rotation of the shell from the shot, tends to apply the airbrakes against the wall of the shell of the shell. The friction forces which result therefrom then oppose the action of the stripping system which causes the ejection of the submunition or munitions after the separation of the base from the shell.

Dans ce cas, les aérofreins 10 d'une sous-munition 7 peuvent être également retenus dans leur position repliée jusqu'à l'éjection de la sous-munition 7 au moyen d'un dispositif de maintien 15 semblable à celui précédemment décrit.In this case, the airbrakes 10 of a submunition 7 can also be retained in their folded position until the ejection of the submunition 7 by means of a holding device 15 similar to that previously described.

En se reportant à la figure 6 qui illustre schématiquement deux sous-munitions 7 et 7' adjacentes logées dans l'obus 1, le dispositif de maintien 15 des aérofreins 10 de la sous-munition 7 est tel que :

  • la coupelle 23 est globalement coincée entre les deux faces d'extrémités adjacentes des corps des deux sous-munitions 7 et 7', et
  • les pattes 20 sont positionnées entre les aérofreins 10 et la paroi de l'enveloppe 2.
Referring to FIG. 6 which schematically illustrates two adjacent submunitions 7 and 7 ′ housed in the shell 1, the device 15 for holding the airbrakes 10 of the submunition 7 is such that:
  • the cup 23 is generally wedged between the two adjacent end faces of the bodies of the two submunitions 7 and 7 ′, and
  • the tabs 20 are positioned between the airbrakes 10 and the wall of the envelope 2.

Dans ce cas cependant, les extrémités libres des pattes 20 ne viennent pas se loger dans des encoches de la sous-munition 7. En effet, une telle disposition ne s'avère plus nécessaire car l'éjection de la sous-munition 7 n'interfère pas avec la séparation du culot 5 de l'obus 1. En outre, le câble 27 qui reliait précédemment le dispositif de maintien 15 et le culot 5 peut être supprimé.In this case, however, the free ends of the legs 20 do not come to be housed in the notches of the submunition 7. In fact, such an arrangement is no longer necessary since the ejection of the submunition 7 does not not interfere with the separation of the base 5 from the shell 1. In addition, the cable 27 which previously connected the holding device 15 and the base 5 can be removed.

Une fois l'obus tiré, la force centrifuge résultant de la mise en rotation de l'obus et des sous-munitions dès le coup de canon, va également avoir pour effet de plaquer les pattes 20 contre l'enveloppe 2 mais sur une surface de contact limitée, ce qui réduit d'autant les forces de frottement qui vont s'opposer ensuite à l'action du système de dépotage.Once the shell is fired, the centrifugal force resulting from the rotation of the shell and the submunitions from the moment of the cannon shot, will also have the effect of pressing the legs 20 against the envelope 2 but on a surface limited contact, which reduces the friction forces which will then oppose the action of the unloading system.

Suite à l'actionnement du système de dépotage, la montée en pression des gaz engendrés par la combustion de la composition pyrotechnique, entraîne la rupture de la liaison mécanique entre l'enveloppe 2 et le culot 5. Le culot 5 se dégage de l'enveloppe 2 puis est éjecté, et la sous-munition 7 sort à son tour de l'enveloppe 2 sous la poussée des gaz. Lorsque le dispositif de maintien 15 est totalement dégagé de l'enveloppe 2, la force centrifuge agit tout d'abord sur les pattes 20 en les écartant du corps de la sous-munition 7 pour les dégager des aérofreins 10, et ensuite sur les aérofreins 10 eux-mêmes qui vont alors s'ouvrir ou se déployer pour ralentir le mouvement de rotation de la sous-munition 7.Following actuation of the unloading system, the rise in pressure of the gases generated by the combustion of the pyrotechnic composition, causes the mechanical connection between the casing 2 and the base 5 to break. The base 5 is released from the envelope 2 then is ejected, and the submunition 7 in turn comes out of envelope 2 under the thrust of the gases. When the holding device 15 is completely disengaged from the casing 2, the centrifugal force acts first on the legs 20 by moving them away from the body of the submunition 7 in order to disengage them from the airbrakes 10, and then on the airbrakes 10 themselves who go then open or deploy to slow down the rotational movement of the submunition 7.

Si on maintenait la présence du câble 27, il serait alors fixé entre le dispositif de maintien 15 des aérofreins 10 de la sous-munition 7 et le corps de la sous-munition 7' éjectée juste avant la sous-munition 7. Le câble 27 faciliterait alors le dégagement du dispositif de maintien 15 de la sous-munition 7.If the presence of the cable 27 were maintained, it would then be fixed between the device for holding the airbrakes 10 of the submunition 7 and the body of the submunition 7 'ejected just before the submunition 7. The cable 27 would then facilitate the release of the holding device 15 from the submunition 7.

Selon une variante de réalisation illustrée à la figure 7, la coupelle 23 du dispositif de maintien 15 est percée d'une ouverture centrale 30.According to an alternative embodiment illustrated in FIG. 7, the cup 23 of the holding device 15 is pierced with a central opening 30.

Les figures 8 et 9 représentent un dispositif de maintien selon un autre mode de réalisation de l'invention.Figures 8 and 9 show a holding device according to another embodiment of the invention.

Dans ce mode de réalisation les pattes de maintien 20 sont constituées par des goupilles cylindriques, régulièrement réparties angulairement et fixées par soudage à la coupelle 23.In this embodiment, the holding tabs 20 are formed by cylindrical pins, regularly distributed angularly and fixed by welding to the cup 23.

Chaque goupille pénètre dans un trou 24 aménagé sur le corps de la sous munition 7.Each pin enters a hole 24 arranged on the body of the submunition 7.

Ce mode de réalisation présente l'avantage d'être de fabrication simple. De plus, le maintien assuré par les goupilles est plus rigide que celui permis par des pattes minces et il permet également de réduire encore les frottements. En effet, le contact entre les goupilles et, d'une part les aérofrein 10, et d'autre part la paroi interne de l'enveloppe ou du culot s'effectue suivant une surface réduite qui est celles des génératrices des goupilles.This embodiment has the advantage of being simple to manufacture. In addition, the support provided by the pins is more rigid than that allowed by thin legs and it also makes it possible to further reduce friction. Indeed, the contact between the pins and, on the one hand the airbrakes 10, and on the other hand the internal wall of the casing or of the base takes place along a reduced surface which is that of the generators of the pins.

Claims (12)

Système de freinage aérodynamique d'une sous-munition (7) éjectée d'un obus cargo (1), comprenant une enveloppe (2) fermée par un culot (5), en étant animée d'un mouvement de rotation, ce système comprenant plusieurs aérofreins (10) articulés qui sont repliés autour du corps de la sous-munition (7) et destinés à se déployer ou s'ouvrir après l'éjection de la sous-munition (7), caractérisé en ce qu' il comprend un dispositif de maintien (15) des aérofreins (10) dans leur position repliée à l'intérieur de l'obus (1), dispositif de maintien (15) qui est libéré suite à l'éjection de la sous-munition (7) pour permettre l'ouverture des aéro-freins (10) hors de l'enveloppe (2) de l'obus (1), le dispositif de maintien (15) étant constitué par des barrettes ou pattes (20) interposées entre les aérofreins (10) et l'enveloppe (2) ou le culot (5) de l'obus, ces pattes (20) étant solidaires d'un support (22) rapporté contre une face d'extrémité de la sous-munition (7).Aerodynamic braking system of a submunition (7) ejected from a cargo shell (1), comprising an envelope (2) closed by a base (5), being driven by a rotational movement, this system comprising several articulated airbrakes (10) which are folded around the body of the submunition (7) and intended to deploy or open after the ejection of the submunition (7), characterized in that it comprises a holding device (15) for airbrakes (10) in their folded position inside the shell (1), holding device (15) which is released following the ejection of the submunition (7) for allow the air brakes (10) to open out of the shell (2) of the shell (1), the holding device (15) consisting of bars or lugs (20) interposed between the air brakes (10 ) and the shell (2) or the base (5) of the shell, these tabs (20) being integral with a support (22) attached against an end face of the submunition (7). Système de freinage selon la revendication 1, caractérisé en ce que le support (22) est constitué d'une coupelle (23), les pattes (20) étant raccordées par une extrémité à la périphérie de la coupelle (23) en s'étendant d'un même côté de celle-ci suivant une direction sensiblement perpendiculaire au plan de la coupelle (23).Braking system according to claim 1, characterized in that the support (22) consists of a cup (23), the tabs (20) being connected by one end to the periphery of the cup (23) extending on the same side thereof in a direction substantially perpendicular to the plane of the cup (23). Système de freinage selon la revendication 2, caractérisé en ce que les pattes (20) sont régulièrement espacées angulairement autour de la coupelle (23).Braking system according to claim 2, characterized in that the tabs (20) are regularly angularly spaced around the cup (23). Système de freinage selon la revendication 2 ou 3, caractérisé en ce que les pattes (20) sont fixées à la coupelle (23) par une opération de soudage ou collage.Braking system according to claim 2 or 3, characterized in that the tabs (20) are fixed to the cup (23) by a welding or gluing operation. Système de freinage selon la revendication 2 ou 3, caractérisé en ce que les pattes (20) et la coupelle (23) sont venues d'une même pièce.Braking system according to claim 2 or 3, characterized in that the lugs (20) and the cup (23) came from one piece. Système de freinage selon une des revendications 2 à 4, caractérisé en ce que les pattes (20) sont des goupilles cylindriques.Braking system according to one of claims 2 to 4, characterized in that the tabs (20) are cylindrical pins. Système de freinage selon l'une quelconque des revendications précédentes, caractérisé en ce que lorsque les aérofreins (10) sont positionnés en regard de la paroi latérale (5a) du culot (5) de l'obus (1) pour une sous-munition (7) qui est en partie logée dans le culot (5), les extrémités libres des pattes (20) viennent s'engager dans des trous ou encoches (24) aménagés dans le corps de la sous-munition (7).Braking system according to any one of the preceding claims, characterized in that when the airbrakes (10) are positioned opposite the side wall (5a) of the base (5) of the shell (1) for a submunition (7) which is partly housed in the base (5), the free ends of the legs (20) engage in holes or notches (24) arranged in the body of the submunition (7). Système de freinage selon la revendication 7, caractérisé en ce qu'il comprend un moyen élastique (29) monté entre le culot (5) et la sous-munition (7) pour séparer le culot (5) de la sous-munition (7), lorsque l'ensemble culot-sous-munition est éjecté hors de l'enveloppe (2).Braking system according to claim 7, characterized in that it comprises an elastic means (29) mounted between the base (5) and the submunition (7) to separate the base (5) from the submunition (7 ), when the base-submunition assembly is ejected from the envelope (2). Système de freinage selon la revendication 8, caractérisé en ce que le moyen élastique (29) est constitué par une rondelle Belleville mise en compression une fois le culot (5) fixé à l'enveloppe (2) de l'obus.Braking system according to claim 8, characterized in that the elastic means (29) is constituted by a Belleville washer placed in compression once the base (5) is fixed to the shell (2) of the shell. Système de freinage selon l'une quelconque des revendications 8 ou 9, caractérisé en ce qu'il comprend également un élément de liaison (25) fixé au dispositif de maintien (15) d'une part et au culot (5) d'autre part, pour dégager les pattes (20) des trous ou encoches (24) de la sous-munition (7) et libérer le dispositif de maintien (15) lorsque le culot (5) est séparé de la sous-munition (7).Braking system according to any one of claims 8 or 9, characterized in that it also comprises a connecting element (25) fixed to the holding device (15) on the one hand and to the base (5) on the other part, to release the tabs (20) from the holes or notches (24) of the submunition (7) and release the holding device (15) when the base (5) is separated from the submunition (7). Système de freinage selon la revendication 10, caractérisé en ce que le moyen de liaison (25) est déroulable et constitué par un câble ou une chaînette (27).Braking system according to claim 10, characterized in that the connecting means (25) is unrollable and consists of a cable or a chain (27). Système de freinage selon l'une quelconque des revendications 1 à 6, caractérisé en ce que, lorsque les aérofreins (10) sont positionnés en regard de l'enveloppe (2) de l'obus (1), le dispositif de maintien (15) des aérofreins (10) est libéré de la sous-munition (7) par l'action de la force centrifuge exercée sur les pattes (20).Braking system according to any one of Claims 1 to 6, characterized in that, when the airbrakes (10) are positioned facing the shell (2) of the shell (1), the holding device (15 ) airbrakes (10) is released from the submunition (7) by the action of centrifugal force exerted on the legs (20).
EP19960401987 1995-10-06 1996-09-19 Spin braking system for a cargo ammunition submissile Expired - Lifetime EP0767356B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9511773 1995-10-06
FR9511773A FR2739682B1 (en) 1995-10-06 1995-10-06 IMPROVEMENT PROVIDED TO AN AERODYNAMIC BRAKING SYSTEM OF A SUBMUNITION EJECTED FROM A CARGO SHELL BEING DRIVEN BY A ROTATION MOVEMENT

Publications (2)

Publication Number Publication Date
EP0767356A1 true EP0767356A1 (en) 1997-04-09
EP0767356B1 EP0767356B1 (en) 2000-01-19

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Application Number Title Priority Date Filing Date
EP19960401987 Expired - Lifetime EP0767356B1 (en) 1995-10-06 1996-09-19 Spin braking system for a cargo ammunition submissile

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EP (1) EP0767356B1 (en)
DE (1) DE69606254T2 (en)
FR (1) FR2739682B1 (en)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0274579A1 (en) * 1986-12-18 1988-07-20 Rheinmetall GmbH Projectile
EP0464589A1 (en) * 1990-07-02 1992-01-08 Alliant Techsystems Inc. Projectile base plug with enhanced drag-producing separation capability
EP0481795A1 (en) * 1990-10-19 1992-04-22 Gec-Marconi Limited Air-launched buoys
FR2679641A1 (en) * 1991-07-25 1993-01-29 Rheinmetall Gmbh DEVICE FOR REDUCING THE SPEED OF A SUBMUNITION.

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0274579A1 (en) * 1986-12-18 1988-07-20 Rheinmetall GmbH Projectile
EP0464589A1 (en) * 1990-07-02 1992-01-08 Alliant Techsystems Inc. Projectile base plug with enhanced drag-producing separation capability
EP0481795A1 (en) * 1990-10-19 1992-04-22 Gec-Marconi Limited Air-launched buoys
FR2679641A1 (en) * 1991-07-25 1993-01-29 Rheinmetall Gmbh DEVICE FOR REDUCING THE SPEED OF A SUBMUNITION.

Also Published As

Publication number Publication date
FR2739682B1 (en) 1997-12-05
DE69606254D1 (en) 2000-02-24
FR2739682A1 (en) 1997-04-11
DE69606254T2 (en) 2000-05-18
EP0767356B1 (en) 2000-01-19

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