EP3396300A1 - Actuating device for ejecting at least one removable part of a missile, in particular a fairing - Google Patents

Actuating device for ejecting at least one removable part of a missile, in particular a fairing Download PDF

Info

Publication number
EP3396300A1
EP3396300A1 EP18290030.8A EP18290030A EP3396300A1 EP 3396300 A1 EP3396300 A1 EP 3396300A1 EP 18290030 A EP18290030 A EP 18290030A EP 3396300 A1 EP3396300 A1 EP 3396300A1
Authority
EP
European Patent Office
Prior art keywords
missile
holding rod
piston
pyrotechnic
thermal insulation
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP18290030.8A
Other languages
German (de)
French (fr)
Other versions
EP3396300B1 (en
Inventor
Clément Quertelet
Clyde Laheyne
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.)
MBDA France SAS
Original Assignee
MBDA France SAS
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 MBDA France SAS filed Critical MBDA France SAS
Priority to PL18290030T priority Critical patent/PL3396300T3/en
Publication of EP3396300A1 publication Critical patent/EP3396300A1/en
Application granted granted Critical
Publication of EP3396300B1 publication Critical patent/EP3396300B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • 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
    • F42B15/34—Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements

Definitions

  • the present invention relates to an actuating device for ejecting at least one removable part of a missile, and a missile provided with at least one such actuating device.
  • the present invention can be applied to a missile comprising at least one propellable propellant stage and a terminal vehicle which is arranged at the front of the propulsion stage.
  • a terminal vehicle generally comprises, in particular, a sensor forming for example part of a homing device and capable of being sensitive to temperature.
  • the present invention is applicable to a missile having a flight domain remaining in the atmosphere and which has kinematic performance such that the terminal vehicle can be brought to hypersonic speeds. At these high speeds, the surface temperature of the missile can reach several hundred degrees Celsius under the effect of the aerothermal flow, which can be detrimental to the strength and performance of structures, electronic equipment and sensors present.
  • a cap generally comprising several individual shells, is arranged at the front of the missile, so as to thermally and mechanically protect the terminal vehicle during the flight phase of the missile. The cap is then ejected at the appropriate time to allow, in particular, the use of the sensor arranged on the terminal vehicle, during the terminal phase of the flight.
  • the ejection of the cap is implemented by an actuator configured to generate a sufficient force to separate the individual shells in a very short time to make the sensor quickly operational and to avoid any disruption of the performance of the missile during the ejection phase of the cap.
  • the actuating device must take into account the thermal and mechanical stresses to which the individual hulls are subjected before the terminal phase of flight.
  • One solution could be to use a pyrotechnic actuator such as an ejector pyrotechnic bolt, to generate the force required to separate the individual shells in very short times.
  • a pyrotechnic actuator such as an ejector pyrotechnic bolt
  • the temperatures of several hundred degrees Celsius to which the individual shells are subjected may degrade the operation of the pyrotechnic actuator fixed thereto, or even trigger it inadvertently.
  • the ejected products and the blast effect of the pyrotechnic reaction are liable to damage the sensor of the terminal vehicle or to impair its measuring capacity by deposition of powder residues for example. This solution is therefore not applicable.
  • the present invention aims to overcome these disadvantages. It relates to an actuating device for ejecting at least one removable part of a missile, in particular at least one individual shell of a cap.
  • said pyrotechnic actuator is configured to be able to generate a force capable of breaking said at least one holding rod.
  • a first end of said at least one holding rod and one end of said pyrotechnic actuator are intended to be fixed on a missile element and a second end, opposite said first end of said at least one holding rod, is intended to be fixed to said removable part of the missile.
  • an actuating device for ejecting a removable part of a missile, such as an individual shell of a cap, which comprises a pyrotechnic actuator whose operation is made compatible. with the thermal and mechanical constraints of the missile by the arrangement of at least one thermal insulation element and at least one holding rod.
  • the pyrotechnic charge which is an element of the pyrotechnic actuator sensitive to the high temperatures to which the individual shells are subjected, is isolated from the heat flows in the cap by the arrangement of at least one thermal insulation element.
  • this localized thermal protection minimizes the weight and bulk of the onboard actuator.
  • the actuating device ensures mechanical support during the flight phase.
  • the pyrotechnic actuator being fixed solely to the removable part, preferably a cap shell, at one of its ends, the device actuator is provided with one or more holding rods which provide the mechanical connection between this removable portion and a fastener, for example two individual shells of a cap.
  • these holding rods are configured to withstand in particular the mechanical stresses of the cap during the phase of flight preceding the ejection of the cap.
  • these retaining rods comprise at least one integral part of said pyrotechnic actuator via a mechanical clevis, which ensures, for example, a better stability of the device against mechanical stresses during the flight phase of the missile and ejection of the cap.
  • said at least one holding rod has a zone of weakness, which is preferably located near the free end of the piston.
  • said at least one holding rod is provided with at least one retaining element, located at the level of the mechanical clevis.
  • This retention element is advantageously arranged to prevent any translational movement of the at least one holding rod relative to the pyrotechnic actuator.
  • said at least one holding rod is provided with at least one thermal insulation sleeve, at least on a section of the latter.
  • Said at least one thermal insulation sleeve is preferably at the level of the mechanical clevis.
  • the advantageous arrangement of said at least one sleeve contributes to the thermal insulation of said pyrotechnic actuator.
  • said thermal insulation elements may be made of a material of mica, mullite or muscovite type.
  • the second end of said holding rod is advantageously provided with a thread, arranged to allow the fixing of said holding rod to a solid element of the removable part of the missile by means of a nut.
  • the present invention also relates to a missile which is provided with an actuating device such as that described above, said actuating device being fixed by a first end to a fastening element of a first part of the missile, by example an individual shell of a cap or a fixed element of the missile structure and a second end, opposite the first end, to an attachment element of a removable part of the missile.
  • this removable part may correspond to any element to be ejected from the missile during its flight, and preferably to an individual shell of a cap.
  • said missile is provided with a cap comprising at least two individual shells, said first portion represents one of said individual shells and said second removable portion represents the other individual shell.
  • the actuating device is configured to simultaneously separate and discard the two individual shells in order to eject them from the missile.
  • At least one thermal insulation element is advantageously fixed on a fastening element of at least one of said removable parts of the missile, and arranged opposite the free end of said piston.
  • the Figures 1 and 2 schematically show an example of missile with cap, respectively, during the flight phase and during the ejection phase.
  • the figure 3 shows the arrangement of a particular embodiment of an actuating device on one of the individual shells of the cap.
  • the figures 4 and 5 are schematic views, respectively, in perspective and in median section of the actuating device.
  • the present invention applies to a missile 1 diagrammatically represented on the Figures 1 and 2 , which is provided at the front (in the direction of movement F of said missile 1) of a cap (protective) 2 having a plurality of removable parts, in this case a plurality of shells 3, 4.
  • the present invention relates to a actuating device 7 for the ejection of the cap 2.
  • the present invention can be applied to any type of missile 1 having at least one removable portion to be ejected.
  • the missile 1 with longitudinal axis LL comprises at least one propellable stage 5 releasable and a terminal vehicle 6 which is arranged in front of this propulsion stage 5.
  • such a flying terminal vehicle 6 comprises, in particular, at least one sensor 8 arranged upstream, forming for example part of a homing device and capable of being sensitive to temperature.
  • the propulsion stage 5 and the terminal vehicle 6, which may be of any conventional type, are not described further in the following description.
  • the propulsion stage or stages 5 of such a missile 1 are intended for the propulsion of said missile 1, from the firing to the approach of a target (to be neutralized by the missile 1).
  • the terminal phase of the flight is, in turn, carried out autonomously by the terminal vehicle 6, which uses in particular the information from the onboard sensor 8, for example an optoelectronic sensor intended to assist in the detection of the target.
  • the terminal vehicle 6 includes all the usual means (not further described), which are necessary to achieve this terminal flight.
  • the cap 2 is released or at least open, after separation of the different shells 3 and 4, by the activation of the actuating device 7, to release the terminal vehicle 6 (steering wheel) which then separates from the rest of the missile 1.
  • the missile 1 is therefore provided upstream of a separable cap 2 which is intended, in particular, to thermally and mechanically protect the vehicle terminal 6.
  • This cap 2 must however be able to be removed at the appropriate time, in particular to allow the use of the sensor 8 placed on the terminal vehicle 6 in the terminal phase of the flight.
  • the cap 2 is mounted on the missile 1 in an operating position (or protection).
  • the vehicle terminal 6 is mounted inside the cap 2 which is represented by dashes.
  • the shells 3 and 4 are separating, as illustrated respectively by arrows ⁇ 1 and ⁇ 2, during an opening or unloading phase of the cap 2.
  • the release of the shells 3 and 4 and the pulse to generate the movements illustrated by the arrows ⁇ 1 and ⁇ 2, are generated by the actuating device 7 preferably arranged upstream of the cap 2 (inside the latter), as shown in FIGS. figures 1 and 3 .
  • This phase of opening or releasing of the cap 2 allows the release of the terminal vehicle 6.
  • the present invention can be applied more particularly to a missile 1 having a field of flight remaining in the atmosphere and has kinematic performance to bring the vehicle terminal 6 at hypersonic speeds. At these high speeds, the surface temperature of the missile 1 can reach several hundred degrees Celsius under the effect of the aerothermal flow, which requires the provision of a cap 2 effective to allow the holding and performance of structures, electronic equipment and embedded sensors.
  • the present invention can be applied to a missile 1 evolving in all cases of the flight domain (in and out of the atmosphere) and for speeds ranging from subsonic to supersonic high / hypersonic.
  • the actuating device 7 for ejecting the hulls 3 and 4 of the missile 1 is arranged upstream of the cap 2, between the hulls 3 and 4, in a plane transverse to the longitudinal axis LL of the missile 1.
  • the Z axis corresponds to the longitudinal axis L-L of the missile 1.
  • the front and rear adverbs are defined with respect to the direction of movement of the piston 14, which is represented by the arrow G and described below.
  • the pyrotechnic actuator 9 comprises an activatable pyrotechnic charge 12, a combustion chamber 13 arranged at the rear of the pyrotechnic actuator 9 in the same transverse plane YZ as the pyrotechnic charge 12, and a piston 14 arranged along the longitudinal axis X, whose head 15 is in the extension of the combustion chamber 13.
  • the pyrotechnic actuator 9 is triggered by the activation of the pyrotechnic charge 12, which is carried out in the usual manner, by an order given automatically by a control unit (not shown) of the missile 1.
  • the pyrotechnic charge 12 When the pyrotechnic charge 12 is activated, it produces an overpressure in the combustion chamber 13 which generates the displacement of the piston 14 in the direction of the arrow G.
  • the piston 14 moves until one of its ends, opposite to the piston head 15, said free end 16, bears against a fastening element 17 which is fixed to the shell 3.
  • the pyrotechnic actuator 9 may, for example, be a pyrotechnic jack configured to contain the debris and the powder residues of the pyrotechnic reaction that are likely to damage the sensor 8 of the terminal vehicle 6 or to impair its measurement capacity.
  • the pyrotechnic actuator 9 is fixed by a first end, located at the rear of the pyrotechnic device 7, to a fastening element 18 which is fixed to the shell 4.
  • a second end of the pyrotechnic actuator 9, opposite to said first end, is free.
  • the holding rods 10A and 10B also have a first end located at the rear of the pyrotechnic device 7 and a second end located at the front of the pyrotechnic device 7.
  • Each holding rod 10A, 10B is fixed, as specified below. by its first end to the fastening element 17 of the shell 3 and by its second end to the fastening element 18 of the shell 4.
  • the holding rods 10A and 10B provide the mechanical connection between the shells 3 and 4 of the cap 2, especially during the flight phase of the missile 1.
  • one of the two ends of each of the holding rods 10A and 10B is provided with a thread 19A, 19B which makes it possible to screw the holding rods 10A and 10B to the fastening element 17, 18 by via a nut 20A, 20B.
  • the position of the nut 20A, 20B along the thread determines the screwing of the holding rods 10A and 10B in one of the fastening elements 17, 18 of one of the shells 3, 4, which fixes the force exerted by the hulls 3 and 4 on each other during the flight phase of the missile 1. This force is called mechanical prestressing.
  • the holding rods 10A and 10B are connected to the pyrotechnic actuator 9 via mechanical clevises 21A, 21B.
  • mechanical clevises 21A and 21B are fixed on either side of the pyrotechnic actuator 9, at the piston body 14 in the mounting position, and surround a section of holding rods 10A and 10B.
  • the mechanical clevises 21A and 21B may correspond to lateral extensions of the pyrotechnic actuator 9.
  • each holding rod 10A, 10B is provided with an embrittlement zone 22A, 22B located, preferably, in the same transverse plane YZ as the free end 16 of the piston 14 in the mounting position, between the fixing element 17 and the mechanical clevis 19A, 19B.
  • Each of the weakening zones 22A and 22B corresponds to a circular recess on a longitudinal portion of the holding rods 10A and 10B, which reduces their mechanical strength.
  • a retaining element 23A, 23B for example a pin or a collar, is arranged around the holding rod 10A, 10B, against the end of the mechanical clevis 21A, 21B the closest to the weakening zone 22A, 22B.
  • This retaining element 23A, 23B retains the holding rod 10A, 10B in the mechanical clevis 21A, 22B in the longitudinal direction X.
  • thermal insulation elements 11A, 11B, 11C, 11D are arranged on parts of the pyrotechnic actuator 9 in order to isolate it from the heat flows to which the shells 3 and 4 of the cap 2 are subjected during the flight phase. .
  • a thermal insulation element 11A is located between the fixing element 18 of the shell 4 and the pyrotechnic charge 12 to prevent the heat of the shell 4 is transmitted to the pyrotechnic charge 12 and inadvertently triggers the pyrotechnic actuator 9.
  • Two other thermal insulation elements are arranged, in the form of sleeves 11B and 11C, around the sections of the holding rods 10A and 10B which pass through the mechanical clevises 21A and 21B to prevent the heat flows circulating between them. shells 3 and 4 through the holding rods 10A and 10B do not pass the pyrotechnic actuator 9.
  • a thermal insulation element 11D can be arranged opposite the free end 16 of the piston 14, and attached to the fastening element 17 of the hull 3 of the missile 1.
  • the thermal insulation elements 11A, 11B, 11C, 11D protect the pyrotechnic actuator 9 by isolating only the pyrotechnic charge 12.
  • the thermal insulation elements 11A, 11B, 11C and 11D are made of one of the following materials: mica, mullite, muscovite. These materials, while being excellent heat insulators, have a hardness sufficient not to damp the force generated by the pyrotechnic actuator 9 to separate the shells 3 and 4.
  • the operating mode of the actuating device is as follows.
  • the cap 2 is kept closed by means of the holding rods 10A and 10B which are fixed at their ends to fastening elements 17 and 18 of the shells 3 and 4.
  • the stability of the cap 2 depends on the mechanical prestressing exerted between the shells 3 and 4.
  • This mechanical preload is managed by the holding rods 10A and 10B by adjusting the position of the nut 20A, 20B along the thread of one end of the holding rods 10A and 10B.
  • the cap 2 undergoes high thermal stress during the flight phase. These heat flows circulate between the shells 3 and 4, in particular by means of the holding rods 10A and 10B which create a thermal bridge between the fastening elements 17 and 18 of the shells 3 and 4.
  • the thermal insulation elements 11A, 11B, 11C, 11D are arranged judiciously between the pyrotechnic charge 12 and the fastening element 18 of the shell 4, and between the holding rods 10A and 10B and the clevises mechanical 21A and 21 B.
  • a signal activates the pyrotechnic charge 12 of the pyrotechnic actuator 9.
  • An overpressure then occurs in the combustion chamber 13, which generates a thrust force on the piston 14 which moves in the direction of the arrow G.
  • the piston 14 transmits the thrust force to the shell 3. Since the pyrotechnic device 7 is attached to the two shells 3 and 4 through the holding rods 10A and 10B, the shell 3 is subjected to an equal thrust force, but in the opposite direction, to that acting on the shell 4.
  • the retaining elements 23A and 23B arranged on the holding rods 10A and 10B at the mechanical clevises 21A and 21B, block any translational movement of the rods relative to the pyrotechnic actuator 9, the shells 3 and 4 separate and deviate from one another simultaneously by pivoting about rotating elements 24, for example hinges. This leads to the ejection of the hulls 3 and 4 of the missile 1.
  • the actuating device 7, as described above, is a unitary unit whose architecture makes it possible to fulfill, on the one hand, the function of maintaining the stability of the cap 2, in particular during the flight phase and secondly the fast ejection function of the shells 3 and 4.
  • the architecture of the actuating device 7 makes compatible the use of a pyrotechnic actuator 9 capable of generating a large force in a very short time. short, despite the high temperatures to which the hulls 3 and 4 are subjected.
  • the arrangement of the thermal insulation elements 11A, 11B, 11C, 11D as well as the configuration of the holding rods 10A and 10B preserve the operation of the pyrotechnic actuator 9 by isolating it from the thermal and mechanical stresses experienced by the shells 3 and 4.
  • the cap 2 must be ejected very rapidly to allow the use of the sensor 8
  • the pyrotechnic actuator 9 makes this rapid ejection possible by generating a force sufficient to break the previously weakened holding rods 10A and 10B.
  • the thermal insulation elements 11A, 11B, 11C, 11D form a localized protection which makes it possible to minimize the mass and the bulk of the on-board actuating device 7.
  • the pyrotechnic actuating device 7 also has the advantage of being adaptable to the holding and ejection of any removable part of missile 1 in a high temperature environment. Finally, the actuating device 7 operates in all cases of the flight envelope (in and out of the atmosphere) of a missile 1 and for speeds ranging from subsonic to supersonic high / hypersonic.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Actuator (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

- Dispositif d'actionnement pour l'éjection d'au moins une partie amovible de missile, en particulier d'une coiffe.
- Le dispositif (7) est un ensemble unitaire qui comprend un actionneur pyrotechnique (9) comprenant une charge pyrotechnique (12) apte à générer une surpression et un piston (14) configuré pour se déplacer dans une direction longitudinale, de sorte qu'une des extrémités du piston (14) peut agir sur la partie amovible du missile, au moins une tige de maintien (10A, 10B), et au moins un élément d'isolation thermique (11A, 11B, 11C) agencé de manière à isoler thermiquement au moins la charge pyrotechnique (12), l'actionneur pyrotechnique (9) étant configuré pour générer une force apte à rompre la tige de maintien (10A, 10B), une première extrémité de la tige de maintien (10A, 10B) et une extrémité de l'actionneur pyrotechnique (9) étant fixées sur un élément de fixation (18) du missile, et une seconde extrémité, opposée à la première extrémité de la tige de maintien (10A, 10B), étant fixée à un élément de fixation de la partie amovible du missile.

Figure imgaf001
- Actuating device for ejecting at least one removable part of a missile, in particular a cap.
- The device (7) is a unitary assembly which comprises a pyrotechnic actuator (9) comprising a pyrotechnic charge (12) capable of generating an overpressure and a piston (14) configured to move in a longitudinal direction, so that a ends of the piston (14) can act on the removable part of the missile, at least one holding rod (10A, 10B), and at least one thermal insulation element (11A, 11B, 11C) arranged to thermally isolate at least the pyrotechnic charge (12), the pyrotechnic actuator (9) being configured to generate a force capable of breaking the holding rod (10A, 10B), a first end of the holding rod (10A, 10B) and a end of the pyrotechnic actuator (9) being attached to a fastener (18) of the missile, and a second end, opposite the first end of the holding rod (10A, 10B), being attached to a fastener of the removable part of the missile.
Figure imgaf001

Description

DOMAINE TECHNIQUETECHNICAL AREA

La présente invention concerne un dispositif d'actionnement permettant l'éjection d'au moins une partie amovible d'un missile, et un missile pourvu d'au moins un tel dispositif d'actionnement.The present invention relates to an actuating device for ejecting at least one removable part of a missile, and a missile provided with at least one such actuating device.

ETAT DE LA TECHNIQUESTATE OF THE ART

Bien que non exclusivement, la présente invention peut s'appliquer à un missile comprenant au moins un étage propulsif largable et un véhicule terminal qui est agencé à l'avant de l'étage propulsif. Un tel véhicule terminal comprend généralement, notamment, un capteur faisant par exemple partie d'un autodirecteur et susceptible d'être sensible à la température.Although not exclusively, the present invention can be applied to a missile comprising at least one propellable propellant stage and a terminal vehicle which is arranged at the front of the propulsion stage. Such a terminal vehicle generally comprises, in particular, a sensor forming for example part of a homing device and capable of being sensitive to temperature.

Plus particulièrement, la présente invention peut s'appliquer à un missile présentant un domaine de vol restant dans l'atmosphère et qui dispose de performances cinématiques telles que le véhicule terminal peut être amené à des vitesses hypersoniques. A ces hautes vitesses, la température de surface du missile peut atteindre plusieurs centaines de degré Celsius sous l'effet du flux aérothermique, ce qui peut être préjudiciable pour la tenue et les performances des structures, des équipements électroniques et des capteurs présents. Aussi, une coiffe (de protection), comprenant généralement plusieurs coques individuelles, est agencée à l'avant du missile, de manière à protéger thermiquement et mécaniquement le véhicule terminal lors de la phase de vol du missile. La coiffe est ensuite éjectée au moment opportun pour permettre, notamment, l'utilisation du capteur agencé sur le véhicule terminal, lors de la phase terminale du vol.More particularly, the present invention is applicable to a missile having a flight domain remaining in the atmosphere and which has kinematic performance such that the terminal vehicle can be brought to hypersonic speeds. At these high speeds, the surface temperature of the missile can reach several hundred degrees Celsius under the effect of the aerothermal flow, which can be detrimental to the strength and performance of structures, electronic equipment and sensors present. Also, a cap (protection), generally comprising several individual shells, is arranged at the front of the missile, so as to thermally and mechanically protect the terminal vehicle during the flight phase of the missile. The cap is then ejected at the appropriate time to allow, in particular, the use of the sensor arranged on the terminal vehicle, during the terminal phase of the flight.

L'éjection de la coiffe est mise en oeuvre par un dispositif d'actionnement configuré pour générer une force suffisante pour séparer les coques individuelles en un temps très court afin de rendre le capteur rapidement opérationnel et d'éviter toute perturbation des performances du missile lors de la phase d'éjection de la coiffe. De plus, le dispositif d'actionnement doit tenir compte des contraintes thermique et mécanique auxquelles sont soumises les coques individuelles avant la phase terminale de vol.The ejection of the cap is implemented by an actuator configured to generate a sufficient force to separate the individual shells in a very short time to make the sensor quickly operational and to avoid any disruption of the performance of the missile during the ejection phase of the cap. In addition, the actuating device must take into account the thermal and mechanical stresses to which the individual hulls are subjected before the terminal phase of flight.

Une solution pourrait consister à utiliser un actionneur pyrotechnique tel qu'un boulon pyrotechnique éjecteur, pour générer la force nécessaire à la séparation des coques individuelles en des temps très courts. Cependant, les températures de plusieurs centaines de degré Celsius auxquelles sont soumises les coques individuelles risquent de dégrader le fonctionnement de l'actionneur pyrotechnique fixé à celles-ci, voire de le déclencher de façon intempestive. En outre, les produits éjectés et l'effet de souffle de la réaction pyrotechnique sont susceptibles d'endommager le capteur du véhicule terminal ou d'obérer sa capacité de mesure par dépôt de résidus de poudre par exemple. Cette solution n'est donc pas applicable.One solution could be to use a pyrotechnic actuator such as an ejector pyrotechnic bolt, to generate the force required to separate the individual shells in very short times. However, the temperatures of several hundred degrees Celsius to which the individual shells are subjected may degrade the operation of the pyrotechnic actuator fixed thereto, or even trigger it inadvertently. In addition, the ejected products and the blast effect of the pyrotechnic reaction are liable to damage the sensor of the terminal vehicle or to impair its measuring capacity by deposition of powder residues for example. This solution is therefore not applicable.

EXPOSE DE L'INVENTIONSUMMARY OF THE INVENTION

La présente invention a pour but de remédier à ces inconvénients. Elle concerne un dispositif d'actionnement permettant l'éjection d'au moins une partie amovible d'un missile, en particulier au moins une coque individuelle d'une coiffe.The present invention aims to overcome these disadvantages. It relates to an actuating device for ejecting at least one removable part of a missile, in particular at least one individual shell of a cap.

Selon l'invention, ledit dispositif d'actionnement est un ensemble unitaire comprenant :

  • un actionneur pyrotechnique comprenant une charge pyrotechnique activable apte à générer une surpression et un piston configuré pour se déplacer dans une direction longitudinale sous l'effet de la surpression générée sur la tête dudit piston par la charge pyrotechnique, de sorte qu'une extrémité du piston opposée à la tête dudit piston, dite extrémité libre, est destinée à agir sur ladite partie amovible du missile,
  • au moins une tige de maintien,
  • au moins un élément d'isolation thermique agencé de manière à isoler thermiquement au moins la charge pyrotechnique.
According to the invention, said actuating device is a unitary assembly comprising:
  • a pyrotechnic actuator comprising an activatable pyrotechnic charge capable of generating an overpressure and a piston configured to move in a longitudinal direction under the effect of the overpressure generated on the head of said piston by the pyrotechnic charge, so that an end of the piston opposite the head of said piston, said free end, is intended to act on said removable part of the missile,
  • at least one holding rod,
  • at least one thermal insulation element arranged to thermally isolate at least the pyrotechnic charge.

De plus, selon l'invention, ledit actionneur pyrotechnique est configuré pour pouvoir générer une force apte à rompre ladite au moins une tige de maintien.In addition, according to the invention, said pyrotechnic actuator is configured to be able to generate a force capable of breaking said at least one holding rod.

En outre, selon l'invention, une première extrémité de ladite au moins une tige de maintien et une extrémité dudit actionneur pyrotechnique sont destinées à être fixées sur un élément du missile et une seconde extrémité, opposée à ladite première extrémité de ladite au moins une tige de maintien, est destinée à être fixée à ladite partie amovible du missile.In addition, according to the invention, a first end of said at least one holding rod and one end of said pyrotechnic actuator are intended to be fixed on a missile element and a second end, opposite said first end of said at least one holding rod, is intended to be fixed to said removable part of the missile.

Ainsi, grâce à l'invention, on prévoit un dispositif d'actionnement destiné à l'éjection d'une partie amovible de missile, telle qu'une coque individuelle d'une coiffe, qui comprend un actionneur pyrotechnique dont le fonctionnement est rendu compatible avec les contraintes thermique et mécanique du missile par l'agencement d'au moins un élément d'isolation thermique et d'au moins une tige de maintien. En effet, la charge pyrotechnique, qui est un élément de l'actionneur pyrotechnique sensible aux températures élevées auxquelles sont soumises les coques individuelles, est isolée des flux thermiques dans la coiffe par l'agencement d'au moins un élément d'isolation thermique. En plus de prévenir une dégradation du fonctionnement de l'actionneur pyrotechnique voire son déclenchement intempestif, cette protection thermique localisée permet de minimiser la masse et l'encombrement du dispositif d'actionnement embarqué.Thus, thanks to the invention, an actuating device is provided for ejecting a removable part of a missile, such as an individual shell of a cap, which comprises a pyrotechnic actuator whose operation is made compatible. with the thermal and mechanical constraints of the missile by the arrangement of at least one thermal insulation element and at least one holding rod. In fact, the pyrotechnic charge, which is an element of the pyrotechnic actuator sensitive to the high temperatures to which the individual shells are subjected, is isolated from the heat flows in the cap by the arrangement of at least one thermal insulation element. In addition to preventing degradation of the operation of the pyrotechnic actuator or its inadvertent tripping, this localized thermal protection minimizes the weight and bulk of the onboard actuator.

En outre, le dispositif d'actionnement conforme à l'invention garantit un maintien mécanique pendant la phase de vol. L'actionneur pyrotechnique étant uniquement fixé à la partie amovible, de préférence une coque de coiffe, par une de ses extrémités, le dispositif d'actionnement est pourvu d'une ou plusieurs tiges de maintien qui assurent la liaison mécanique entre cette partie amovible et un élément de fixation, par exemple deux coques individuelles d'une coiffe.In addition, the actuating device according to the invention ensures mechanical support during the flight phase. The pyrotechnic actuator being fixed solely to the removable part, preferably a cap shell, at one of its ends, the device actuator is provided with one or more holding rods which provide the mechanical connection between this removable portion and a fastener, for example two individual shells of a cap.

Agencées avantageusement de part et d'autre du piston, dans un même plan, et sensiblement parallèles entre elles et avec l'axe de déplacement du piston, ces tiges de maintien sont configurées pour supporter notamment les contraintes mécaniques de la coiffe lors de la phase de vol précédant l'éjection de la coiffe. De plus, ces tiges de maintien comprennent au moins une partie solidaire dudit actionneur pyrotechnique par l'intermédiaire d'une chape mécanique, ce qui assure, par exemple, une meilleure stabilité du dispositif face aux contraintes mécaniques lors de la phase de vol du missile et d'éjection de la coiffe.Advantageously arranged on either side of the piston, in the same plane, and substantially parallel to each other and with the axis of movement of the piston, these holding rods are configured to withstand in particular the mechanical stresses of the cap during the phase of flight preceding the ejection of the cap. In addition, these retaining rods comprise at least one integral part of said pyrotechnic actuator via a mechanical clevis, which ensures, for example, a better stability of the device against mechanical stresses during the flight phase of the missile and ejection of the cap.

Dans un mode de réalisation préféré, ladite au moins une tige de maintien possède une zone de fragilisation, qui est située de préférence à proximité de l'extrémité libre du piston. Ainsi, lorsque l'actionneur pyrotechnique est déclenché par activation de la charge pyrotechnique, il génère une force réduite mais suffisante pour séparer les coques individuelles l'une de l'autre. La tige de maintien, qui assure la liaison entre les coques individuelles, se rompt en deux parties au niveau de la zone de fragilisation sans produire de débris susceptibles d'endommager les performances du missile.In a preferred embodiment, said at least one holding rod has a zone of weakness, which is preferably located near the free end of the piston. Thus, when the pyrotechnic actuator is triggered by activation of the pyrotechnic charge, it generates a reduced but sufficient force to separate the individual shells from each other. The holding rod, which ensures the connection between the individual hulls, breaks in two parts at the weakening zone without producing debris likely to damage the performance of the missile.

De plus, ladite au moins une tige de maintien est pourvue d'au moins un élément de retenue, situé au niveau de la chape mécanique. Cet élément de retenue est avantageusement agencé pour prévenir tout mouvement de translation de ladite au moins une tige de maintien par rapport à l'actionneur pyrotechnique.In addition, said at least one holding rod is provided with at least one retaining element, located at the level of the mechanical clevis. This retention element is advantageously arranged to prevent any translational movement of the at least one holding rod relative to the pyrotechnic actuator.

Par ailleurs, de manière avantageuse, ladite au moins une tige de maintien est pourvue au moins d'un manchon d'isolation thermique, au moins sur un tronçon de cette dernière. Ledit au moins un manchon d'isolation thermique se situe de préférence au niveau de la chape mécanique. L'agencement avantageux dudit au moins un manchon participe à l'isolation thermique dudit actionneur pyrotechnique.Furthermore, advantageously, said at least one holding rod is provided with at least one thermal insulation sleeve, at least on a section of the latter. Said at least one thermal insulation sleeve is preferably at the level of the mechanical clevis. The advantageous arrangement of said at least one sleeve contributes to the thermal insulation of said pyrotechnic actuator.

En outre, avantageusement, lesdits éléments d'isolation thermique peuvent être réalisés dans un matériau de type mica, mullite, ou muscovite.In addition, advantageously, said thermal insulation elements may be made of a material of mica, mullite or muscovite type.

Par ailleurs, la seconde extrémité de ladite tige de maintien est avantageusement pourvue d'un filetage, agencé pour permettre la fixation de ladite tige de maintien à un élément solide de la partie amovible du missile par l'intermédiaire d'un écrou.Furthermore, the second end of said holding rod is advantageously provided with a thread, arranged to allow the fixing of said holding rod to a solid element of the removable part of the missile by means of a nut.

La présente invention concerne également un missile qui est pourvu d'un dispositif d'actionnement tel que celui décrit ci-dessus, ledit dispositif d'actionnement étant fixé par une première extrémité à un élément de fixation d'une première partie du missile, par exemple une coque individuelle d'une coiffe ou un élément fixe de la structure du missile et par une seconde extrémité, opposée à la première extrémité, à un élément de fixation d'une partie amovible du missile.The present invention also relates to a missile which is provided with an actuating device such as that described above, said actuating device being fixed by a first end to a fastening element of a first part of the missile, by example an individual shell of a cap or a fixed element of the missile structure and a second end, opposite the first end, to an attachment element of a removable part of the missile.

Dans le cadre de la présente invention, cette partie amovible peut correspondre à tout élément devant être éjecté du missile lors de son vol, et de préférence à une coque individuelle d'une coiffe.In the context of the present invention, this removable part may correspond to any element to be ejected from the missile during its flight, and preferably to an individual shell of a cap.

Dans un mode de réalisation préféré, ledit missile est pourvu d'une coiffe comprenant au moins deux coques individuelles, ladite première partie représente l'une desdites coques individuelles et ladite seconde partie amovible représente l'autre coque individuelle. De manière avantageuse, le dispositif d'actionnement est configuré pour séparer et écarter simultanément les deux coques individuelles afin de les éjecter du missile.In a preferred embodiment, said missile is provided with a cap comprising at least two individual shells, said first portion represents one of said individual shells and said second removable portion represents the other individual shell. Advantageously, the actuating device is configured to simultaneously separate and discard the two individual shells in order to eject them from the missile.

De plus, au moins un élément d'isolation thermique est avantageusement fixée sur un élément de fixation d'au moins une desdites parties amovibles du missile, et agencée en face de l'extrémité libre dudit piston.In addition, at least one thermal insulation element is advantageously fixed on a fastening element of at least one of said removable parts of the missile, and arranged opposite the free end of said piston.

BREVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

Les figures annexées feront bien comprendre comment l'invention peut être réalisée. Sur ces figures, des références identiques désignent des éléments semblables.The appended figures will make it clear how the invention can be realized. In these figures, identical references designate similar elements.

Les figures 1 et 2 montrent schématiquement un exemple de missile avec coiffe, respectivement, pendant la phase de vol et pendant la phase d'éjection.The Figures 1 and 2 schematically show an example of missile with cap, respectively, during the flight phase and during the ejection phase.

La figure 3 montre l'agencement d'un mode de réalisation particulier d'un dispositif d'actionnement sur l'une des coques individuelles de la coiffe.The figure 3 shows the arrangement of a particular embodiment of an actuating device on one of the individual shells of the cap.

Les figures 4 et 5 sont des vues schématiques, respectivement, en perspective et en coupe médiane du dispositif d'actionnement.The figures 4 and 5 are schematic views, respectively, in perspective and in median section of the actuating device.

DESCRIPTION DETAILLEEDETAILED DESCRIPTION

La présente invention s'applique à un missile 1 représenté schématiquement sur les figures 1 et 2, qui est pourvu à l'avant (dans le sens de déplacement F dudit missile 1) d'une coiffe (de protection) 2 comportant plusieurs parties amovibles, en l'occurrence une pluralité de coques 3, 4. La présente invention concerne un dispositif d'actionnement 7 pour l'éjection de la coiffe 2. Toutefois, la présente invention peut s'appliquer à tout type de missile 1 comportant au moins une partie amovible devant être éjectée.The present invention applies to a missile 1 diagrammatically represented on the Figures 1 and 2 , which is provided at the front (in the direction of movement F of said missile 1) of a cap (protective) 2 having a plurality of removable parts, in this case a plurality of shells 3, 4. The present invention relates to a actuating device 7 for the ejection of the cap 2. However, the present invention can be applied to any type of missile 1 having at least one removable portion to be ejected.

Comme représenté sur les figures 1 et 2, le missile 1 d'axe longitudinal L-L, comprend au moins un étage propulsif 5 largable et un véhicule terminal 6 qui est agencé devant cet étage propulsif 5.As shown on Figures 1 and 2 , the missile 1 with longitudinal axis LL, comprises at least one propellable stage 5 releasable and a terminal vehicle 6 which is arranged in front of this propulsion stage 5.

En général, un tel véhicule terminal 6 volant comprend, notamment, au moins un capteur 8 agencé en amont, faisant par exemple partie d'un autodirecteur et susceptible d'être sensible à la température. L'étage propulsif 5 et le véhicule terminal 6 qui peuvent être de tout type usuel, ne sont pas décrits davantage dans la description suivante.In general, such a flying terminal vehicle 6 comprises, in particular, at least one sensor 8 arranged upstream, forming for example part of a homing device and capable of being sensitive to temperature. The propulsion stage 5 and the terminal vehicle 6, which may be of any conventional type, are not described further in the following description.

De façon usuelle, le ou les étages propulsifs 5 d'un tel missile 1 sont destinés à la propulsion dudit missile 1, à partir du tir jusqu'à l'approche d'une cible (devant être neutralisée par le missile 1). La phase terminale du vol est, quant à elle, réalisée de façon autonome par le véhicule terminal 6, qui utilise notamment les informations issues du capteur 8 embarqué, par exemple un capteur optoélectronique destiné à aider à la détection de la cible. Pour ce faire, le véhicule terminal 6 comprend tous les moyens usuels (non décrits davantage), qui sont nécessaires pour réaliser ce vol terminal. Avant de mettre en oeuvre la phase terminale, la coiffe 2 est larguée ou tout au moins ouverte, après une séparation des différentes coques 3 et 4, par l'activation du dispositif d'actionnement 7, pour libérer le véhicule terminal 6 (volant) qui se sépare ensuite du reste du missile 1.In the usual way, the propulsion stage or stages 5 of such a missile 1 are intended for the propulsion of said missile 1, from the firing to the approach of a target (to be neutralized by the missile 1). The terminal phase of the flight is, in turn, carried out autonomously by the terminal vehicle 6, which uses in particular the information from the onboard sensor 8, for example an optoelectronic sensor intended to assist in the detection of the target. To do this, the terminal vehicle 6 includes all the usual means (not further described), which are necessary to achieve this terminal flight. Before implementing the terminal phase, the cap 2 is released or at least open, after separation of the different shells 3 and 4, by the activation of the actuating device 7, to release the terminal vehicle 6 (steering wheel) which then separates from the rest of the missile 1.

Le missile 1 est donc pourvu en amont d'une coiffe 2 séparable qui est destinée, notamment, à protéger thermiquement et mécaniquement le véhicule terminal 6. Cette coiffe 2 doit cependant pourvoir être enlevée au moment opportun, notamment pour permettre l'utilisation du capteur 8 placé sur le véhicule terminal 6 dans la phase terminale du vol.The missile 1 is therefore provided upstream of a separable cap 2 which is intended, in particular, to thermally and mechanically protect the vehicle terminal 6. This cap 2 must however be able to be removed at the appropriate time, in particular to allow the use of the sensor 8 placed on the terminal vehicle 6 in the terminal phase of the flight.

Dans la situation de la figure 1, la coiffe 2 est montée sur le missile 1 dans une position de fonctionnement (ou de protection). Le véhicule terminal 6 est monté à l'intérieur de la coiffe 2 qui est représentée par des tirets.In the situation of figure 1 , the cap 2 is mounted on the missile 1 in an operating position (or protection). The vehicle terminal 6 is mounted inside the cap 2 which is represented by dashes.

En outre, dans la situation de la figure 2, les coques 3 et 4 sont en train de se séparer, comme illustré respectivement par des flèches α1 et α2, durant une phase d'ouverture ou de largage de la coiffe 2. La libération des coques 3 et 4 et l'impulsion pour générer les mouvements illustrés par les flèches α1 et α2, sont engendrées par le dispositif d'actionnement 7 agencé de préférence en amont de la coiffe 2 (à l'intérieur de cette dernière), comme représenté sur les figures 1 et 3. Cette phase d'ouverture ou de largage de la coiffe 2 permet la libération du véhicule terminal 6.In addition, in the situation of figure 2 the shells 3 and 4 are separating, as illustrated respectively by arrows α1 and α2, during an opening or unloading phase of the cap 2. The release of the shells 3 and 4 and the pulse to generate the movements illustrated by the arrows α1 and α2, are generated by the actuating device 7 preferably arranged upstream of the cap 2 (inside the latter), as shown in FIGS. figures 1 and 3 . This phase of opening or releasing of the cap 2 allows the release of the terminal vehicle 6.

Bien que non exclusivement, la présente invention peut s'appliquer plus particulièrement à un missile 1 présentant un domaine de vol restant dans l'atmosphère et qui dispose de performances cinématiques permettant d'amener le véhicule terminal 6 à des vitesses hypersoniques. A ces hautes vitesses, la température de surface du missile 1 peut atteindre plusieurs centaines de degrés Celsius sous l'effet du flux aérothermique, ce qui nécessite de prévoir une coiffe 2 efficace pour permettre la tenue et les performances des structures, des équipements électroniques et des capteurs embarqués. Toutefois, la présente invention peut s'appliquer à un missile 1 évoluant dans tous les cas du domaine de vol (en et hors atmosphère) et pour des vitesses allant du subsonique au haut supersonique/hypersonique.Although not exclusively, the present invention can be applied more particularly to a missile 1 having a field of flight remaining in the atmosphere and has kinematic performance to bring the vehicle terminal 6 at hypersonic speeds. At these high speeds, the surface temperature of the missile 1 can reach several hundred degrees Celsius under the effect of the aerothermal flow, which requires the provision of a cap 2 effective to allow the holding and performance of structures, electronic equipment and embedded sensors. However, the present invention can be applied to a missile 1 evolving in all cases of the flight domain (in and out of the atmosphere) and for speeds ranging from subsonic to supersonic high / hypersonic.

En se référant aux figures 1 et 3, le dispositif d'actionnement 7 permettant l'éjection des coques 3 et 4 du missile 1 est agencé en amont de la coiffe 2, entre les coques 3 et 4, dans un plan transversal à l'axe longitudinal L-L du missile 1.Referring to figures 1 and 3 , the actuating device 7 for ejecting the hulls 3 and 4 of the missile 1 is arranged upstream of the cap 2, between the hulls 3 and 4, in a plane transverse to the longitudinal axis LL of the missile 1.

Dans la suite de la description, on utilise un repère R associé au dispositif d'actionnement pyrotechnique 7 et défini selon trois axes orthogonaux, à savoir un axe dit longitudinal X qui est orienté selon le dispositif d'actionnement 7 qui est allongé, et deux axes Y et Z qui définissent un plan médian XY et un plan transversal YZ. L'axe Z correspond à l'axe longitudinal L-L du missile 1. De plus, les adverbes avant et arrière sont définis par rapport au sens de déplacement du piston 14, qui est représenté par la flèche G et décrit ci-après.In the remainder of the description, use is made of a mark R associated with the pyrotechnic actuating device 7 and defined along three orthogonal axes, namely a so-called longitudinal axis X which is oriented according to the actuating device 7 which is elongated, and two Y and Z axes which define a median plane XY and a transverse plane YZ. The Z axis corresponds to the longitudinal axis L-L of the missile 1. In addition, the front and rear adverbs are defined with respect to the direction of movement of the piston 14, which is represented by the arrow G and described below.

Comme représenté sur les figures 3, 4 et 5, le dispositif d'actionnement 7, selon l'invention, est un ensemble unitaire comportant :

  • un actionneur pyrotechnique 9 agencé selon l'axe longitudinal X,
  • deux tiges de maintien 10A et 10B, sensiblement parallèles entre elles et avec l'axe longitudinal X et agencées de part et d'autre de l'actionneur pyrotechnique 9, dans le plan médian XY, et
  • au moins un mais de préférence une pluralité d'éléments d'isolation thermique 11A, 11B, 11C et 11D agencés de manière à isoler localement l'actionneur pyrotechnique 9.
As shown on Figures 3, 4 and 5 , the actuating device 7, according to the invention, is a unitary assembly comprising:
  • a pyrotechnic actuator 9 arranged along the longitudinal axis X,
  • two holding rods 10A and 10B, substantially parallel to one another and to the longitudinal axis X and arranged on either side of the pyrotechnic actuator 9, in the median plane XY, and
  • at least one but preferably a plurality of thermal insulation elements 11A, 11B, 11C and 11D arranged to locally isolate the pyrotechnic actuator 9.

Dans un mode de réalisation préféré, représenté sur les figures 4 et 5, l'actionneur pyrotechnique 9 comprend une charge pyrotechnique 12 activable, une chambre de combustion 13 agencée à l'arrière de l'actionneur pyrotechnique 9 dans le même plan transversal YZ que la charge pyrotechnique 12, et un piston 14 agencé le long de l'axe longitudinal X, dont la tête 15 est dans le prolongement de la chambre de combustion 13. L'actionneur pyrotechnique 9 se déclenche par l'activation de la charge pyrotechnique 12, qui est réalisée de façon usuelle, par un ordre donné automatiquement par une unité de commande (non représentée) du missile 1. Lorsque la charge pyrotechnique 12 est activée, elle produit une surpression dans la chambre à combustion 13 qui génère le déplacement du piston 14 dans le sens de la flèche G. Le piston 14 se déplace jusqu'à ce qu'une de ses extrémités, opposée à la tête 15 du piston, dite extrémité libre 16, appuie contre un élément de fixation 17 lequel est fixé à la coque 3.In a preferred embodiment, shown in the figures 4 and 5 the pyrotechnic actuator 9 comprises an activatable pyrotechnic charge 12, a combustion chamber 13 arranged at the rear of the pyrotechnic actuator 9 in the same transverse plane YZ as the pyrotechnic charge 12, and a piston 14 arranged along the longitudinal axis X, whose head 15 is in the extension of the combustion chamber 13. The pyrotechnic actuator 9 is triggered by the activation of the pyrotechnic charge 12, which is carried out in the usual manner, by an order given automatically by a control unit (not shown) of the missile 1. When the pyrotechnic charge 12 is activated, it produces an overpressure in the combustion chamber 13 which generates the displacement of the piston 14 in the direction of the arrow G. The piston 14 moves until one of its ends, opposite to the piston head 15, said free end 16, bears against a fastening element 17 which is fixed to the shell 3.

L'actionneur pyrotechnique 9 peut, par exemple, être un vérin pyrotechnique configuré pour contenir les débris et les résidus de poudre de la réaction pyrotechnique qui sont susceptibles d'endommager le capteur 8 du véhicule terminal 6 ou d'obérer sa capacité de mesure.The pyrotechnic actuator 9 may, for example, be a pyrotechnic jack configured to contain the debris and the powder residues of the pyrotechnic reaction that are likely to damage the sensor 8 of the terminal vehicle 6 or to impair its measurement capacity.

Dans le mode de réalisation représenté par les figures 4 et 5, l'actionneur pyrotechnique 9 est fixé par une première extrémité, située à l'arrière du dispositif pyrotechnique 7, à un élément de fixation 18 lequel est fixé à la coque 4. Une seconde extrémité de l'actionneur pyrotechnique 9, opposée à ladite première extrémité, est libre.In the embodiment represented by the figures 4 and 5 , the pyrotechnic actuator 9 is fixed by a first end, located at the rear of the pyrotechnic device 7, to a fastening element 18 which is fixed to the shell 4. A second end of the pyrotechnic actuator 9, opposite to said first end, is free.

Les tiges de maintien 10A et 10B comportent également une première extrémité située à l'arrière du dispositif pyrotechnique 7 et une seconde extrémité située à l'avant du dispositif pyrotechnique 7. Chaque tige de maintien 10A, 10B est fixée, comme précisé ci-dessous, par sa première extrémité à l'élément de fixation 17 de la coque 3 et par sa seconde extrémité à l'élément de fixation 18 de la coque 4. Les tiges de maintien 10A et 10B assurent la liaison mécanique entre les coques 3 et 4 de la coiffe 2, notamment lors de la phase de vol du missile 1.The holding rods 10A and 10B also have a first end located at the rear of the pyrotechnic device 7 and a second end located at the front of the pyrotechnic device 7. Each holding rod 10A, 10B is fixed, as specified below. by its first end to the fastening element 17 of the shell 3 and by its second end to the fastening element 18 of the shell 4. The holding rods 10A and 10B provide the mechanical connection between the shells 3 and 4 of the cap 2, especially during the flight phase of the missile 1.

Dans un mode de réalisation particulier, une des deux extrémités de chacune des tiges de maintien 10A et 10B est pourvue d'un filetage 19A, 19B qui permet de visser les tiges de maintien 10A et 10B à l'élément de fixation 17, 18 par l'intermédiaire d'un écrou 20A, 20B. La position de l'écrou 20A, 20B le long du filetage détermine le vissage des tiges de maintien 10A et 10B dans un des éléments de fixation 17, 18 d'une des coques 3, 4, ce qui fixe la force qu'exercent les coques 3 et 4 l'une sur l'autre pendant la phase de vol du missile 1. Cette force est appelée précontrainte mécanique.In a particular embodiment, one of the two ends of each of the holding rods 10A and 10B is provided with a thread 19A, 19B which makes it possible to screw the holding rods 10A and 10B to the fastening element 17, 18 by via a nut 20A, 20B. The position of the nut 20A, 20B along the thread determines the screwing of the holding rods 10A and 10B in one of the fastening elements 17, 18 of one of the shells 3, 4, which fixes the force exerted by the hulls 3 and 4 on each other during the flight phase of the missile 1. This force is called mechanical prestressing.

De plus, les tiges de maintien 10A et 10B sont liées à l'actionneur pyrotechnique 9 par l'intermédiaire de chapes mécaniques 21A, 21B. Comme représenté sur les figures 4 et 5, les chapes mécaniques 21A et 21B sont fixées de part et d'autre de l'actionneur pyrotechnique 9, au niveau du corps du piston 14 dans la position de montage, et entourent un tronçon dés tiges de maintien 10A et 10B. Dans un mode de réalisation particulier, les chapes mécaniques 21A et 21 B peuvent correspondre à des extensions latérales de l'actionneur pyrotechnique 9.In addition, the holding rods 10A and 10B are connected to the pyrotechnic actuator 9 via mechanical clevises 21A, 21B. As shown on figures 4 and 5 , mechanical clevises 21A and 21B are fixed on either side of the pyrotechnic actuator 9, at the piston body 14 in the mounting position, and surround a section of holding rods 10A and 10B. In a particular embodiment, the mechanical clevises 21A and 21B may correspond to lateral extensions of the pyrotechnic actuator 9.

En outre, chaque tige de maintien 10A, 10B est pourvue d'une zone de fragilisation 22A, 22B située, de préférence, dans le même plan transversal YZ que l'extrémité libre 16 du piston 14 dans la position de montage, entre l'élément de fixation 17 et la chape mécanique 19A, 19B. Chacune des zones de fragilisation 22A et 22B correspond à un évidement circulaire sur une partie longitudinale des tiges de maintien 10A et 10B, qui réduit leur résistance mécanique. Ainsi, sous l'effet de la force générée par l'actionneur pyrotechnique 9, les tiges de maintien 10A et 10B se rompent au niveau des zones de fragilisation 22A et 22B.In addition, each holding rod 10A, 10B is provided with an embrittlement zone 22A, 22B located, preferably, in the same transverse plane YZ as the free end 16 of the piston 14 in the mounting position, between the fixing element 17 and the mechanical clevis 19A, 19B. Each of the weakening zones 22A and 22B corresponds to a circular recess on a longitudinal portion of the holding rods 10A and 10B, which reduces their mechanical strength. Thus, under the effect of the force generated by the pyrotechnic actuator 9, the holding rods 10A and 10B break at the weakening zones 22A and 22B.

Comme représenté sur la figure 5, un élément de retenue 23A, 23B, par exemple une goupille ou un collier, est agencé autour de la tige de maintien 10A, 10B, contre l'extrémité de la chape mécanique 21A, 21B la plus proche de la zone de fragilisation 22A, 22B. Cet élément de retenue 23A, 23B retient la tige de maintien 10A, 10B dans la chape mécanique 21A, 22B dans la direction longitudinale X.As shown on the figure 5 a retaining element 23A, 23B, for example a pin or a collar, is arranged around the holding rod 10A, 10B, against the end of the mechanical clevis 21A, 21B the closest to the weakening zone 22A, 22B. This retaining element 23A, 23B retains the holding rod 10A, 10B in the mechanical clevis 21A, 22B in the longitudinal direction X.

Plusieurs éléments d'isolation thermique 11A, 11B, 11C, 11D sont agencés sur des parties de l'actionneur pyrotechnique 9 afin de l'isoler des flux de chaleur auxquels sont soumises les coques 3 et 4 de la coiffe 2 pendant la phase de vol.Several thermal insulation elements 11A, 11B, 11C, 11D are arranged on parts of the pyrotechnic actuator 9 in order to isolate it from the heat flows to which the shells 3 and 4 of the cap 2 are subjected during the flight phase. .

Ainsi, un élément d'isolation thermique 11A est situé entre l'élément de fixation 18 de la coque 4 et la charge pyrotechnique 12 pour éviter que la chaleur de la coque 4 se transmette à la charge pyrotechnique 12 et déclenche de façon intempestive l'actionneur pyrotechnique 9. Deux autres éléments d'isolation thermique sont agencés, sous forme de manchons 11B et 11C, autour des tronçons des tiges de maintien 10A et 10B qui traversent les chapes mécaniques 21A et 21B pour éviter que les flux de chaleur circulant entre les coques 3 et 4 par l'intermédiaire des tiges de maintien 10A et 10B ne passent pas l'actionneur pyrotechnique 9. En outre, un élément d'isolation thermique 11D peut être agencé en face de l'extrémité libre 16 du piston 14, et fixé à l'élément de fixation 17 de la coque 3 du missile 1.Thus, a thermal insulation element 11A is located between the fixing element 18 of the shell 4 and the pyrotechnic charge 12 to prevent the heat of the shell 4 is transmitted to the pyrotechnic charge 12 and inadvertently triggers the pyrotechnic actuator 9. Two other thermal insulation elements are arranged, in the form of sleeves 11B and 11C, around the sections of the holding rods 10A and 10B which pass through the mechanical clevises 21A and 21B to prevent the heat flows circulating between them. shells 3 and 4 through the holding rods 10A and 10B do not pass the pyrotechnic actuator 9. In addition, a thermal insulation element 11D can be arranged opposite the free end 16 of the piston 14, and attached to the fastening element 17 of the hull 3 of the missile 1.

Dans un mode de réalisation particulier, les éléments d'isolation thermique 11A, 11B, 11C, 11D protègent l'actionneur pyrotechnique 9 en isolant uniquement la charge pyrotechnique 12.In a particular embodiment, the thermal insulation elements 11A, 11B, 11C, 11D protect the pyrotechnic actuator 9 by isolating only the pyrotechnic charge 12.

Dans un mode de réalisation préféré, les éléments d'isolation thermique 11A, 11B, 11C et 11D sont réalisés dans un des matériaux suivants : mica, mullite, muscovite. Ces matériaux, tout en étant d'excellent isolants thermiques, possèdent une dureté suffisante pour ne pas amortir la force générée par l'actionneur pyrotechnique 9 afin de séparer les coques 3 et 4.In a preferred embodiment, the thermal insulation elements 11A, 11B, 11C and 11D are made of one of the following materials: mica, mullite, muscovite. These materials, while being excellent heat insulators, have a hardness sufficient not to damp the force generated by the pyrotechnic actuator 9 to separate the shells 3 and 4.

Le mode de fonctionnement du dispositif d'actionnement, tel que décrit ci-dessus, est le suivant.The operating mode of the actuating device, as described above, is as follows.

Lors de la phase de vol du missile 1, la coiffe 2 est maintenue fermée par l'intermédiaire des tiges de maintien 10A et 10B qui sont fixées par leurs extrémités à des éléments de fixation 17 et 18 des coques 3 et 4. De plus, la stabilité de la coiffe 2 dépend de la précontrainte mécanique exercée entre les coques 3 et 4. Cette précontrainte mécanique est gérée par les tiges de maintien 10A et 10B en réglant la position de l'écrou 20A, 20B le long du filetage d'une des extrémités des tiges de maintien 10A et 10B. En outre, la coiffe 2 subit de fortes contraintes thermiques lors de la phase de vol. Ces flux thermiques circulent entre les coques 3 et 4, notamment par le biais des tiges de maintien 10A et 10B qui créent un pont thermique entre les éléments de fixation 17 et 18 des coques 3 et 4. Pour éviter tout déclenchement intempestif de l'actionneur pyrotechnique 9, les éléments d'isolation thermique 11A, 11B, 11C, 11D sont disposés judicieusement entre la charge pyrotechnique 12 et l'élément de fixation 18 de la coque 4, ainsi qu'entre les tiges de maintien 10A et 10B et les chapes mécaniques 21A et 21 B.During the flight phase of the missile 1, the cap 2 is kept closed by means of the holding rods 10A and 10B which are fixed at their ends to fastening elements 17 and 18 of the shells 3 and 4. In addition, the stability of the cap 2 depends on the mechanical prestressing exerted between the shells 3 and 4. This mechanical preload is managed by the holding rods 10A and 10B by adjusting the position of the nut 20A, 20B along the thread of one end of the holding rods 10A and 10B. In addition, the cap 2 undergoes high thermal stress during the flight phase. These heat flows circulate between the shells 3 and 4, in particular by means of the holding rods 10A and 10B which create a thermal bridge between the fastening elements 17 and 18 of the shells 3 and 4. To prevent any inadvertent tripping of the actuator pyrotechnic 9, the thermal insulation elements 11A, 11B, 11C, 11D are arranged judiciously between the pyrotechnic charge 12 and the fastening element 18 of the shell 4, and between the holding rods 10A and 10B and the clevises mechanical 21A and 21 B.

Lorsque les coques 3, 4 de la coiffe 2 doivent être séparées, un signal active la charge pyrotechnique 12 de l'actionneur pyrotechnique 9. Il se produit alors une surpression dans la chambre de combustion 13, ce qui génère une force de poussée sur le piston 14 qui se déplace dans le sens de la flèche G. Lorsque l'extrémité libre 16 du piston 14 appuie contre l'élément de fixation 17 de la coque 4, le piston 14 transmet la force de poussée à la coque 3. Puisque le dispositif pyrotechnique 7 est fixé aux deux coques 3 et 4 par l'intermédiaire des tiges de maintien 10A et 10B, la coque 3 est soumise à une force de poussée égale, mais de sens opposé, à celle agissant sur la coque 4. Ces forces de sens opposés agissent sur les tiges de maintien 10A et 10B jusqu'à provoquer leur rupture au niveau des zones de fragilisation 22A et 22B. Comme les éléments de retenue 23A et 23B, agencés sur les tiges de maintien 10A et 10B au niveau des chapes mécaniques 21A et 21B, bloquent tout mouvement translationnel des tiges par rapport à l'actionneur pyrotechnique 9, les coques 3 et 4 se séparent et s'écartent l'une de l'autre simultanément en pivotant autour d'éléments de rotation 24, par exemple des charnières. On aboutit ainsi à l'éjection des coques 3 et 4 du missile 1.When the shells 3, 4 of the cap 2 must be separated, a signal activates the pyrotechnic charge 12 of the pyrotechnic actuator 9. An overpressure then occurs in the combustion chamber 13, which generates a thrust force on the piston 14 which moves in the direction of the arrow G. When the free end 16 of the piston 14 bears against the fastening element 17 of the shell 4, the piston 14 transmits the thrust force to the shell 3. Since the pyrotechnic device 7 is attached to the two shells 3 and 4 through the holding rods 10A and 10B, the shell 3 is subjected to an equal thrust force, but in the opposite direction, to that acting on the shell 4. These forces in opposite directions act on the holding rods 10A and 10B until they break at the weakening zones 22A and 22B. As the retaining elements 23A and 23B, arranged on the holding rods 10A and 10B at the mechanical clevises 21A and 21B, block any translational movement of the rods relative to the pyrotechnic actuator 9, the shells 3 and 4 separate and deviate from one another simultaneously by pivoting about rotating elements 24, for example hinges. This leads to the ejection of the hulls 3 and 4 of the missile 1.

Le dispositif d'actionnement 7, tel que décrit ci-dessus, est un ensemble unitaire, dont l'architecture permet de remplir d'une part la fonction de maintien de la stabilité de la coiffe 2, notamment lors de la phase de vol et d'autre part la fonction d'éjection rapide des coques 3 et 4. L'architecture du dispositif d'actionnement 7 rend compatible l'utilisation d'un actionneur pyrotechnique 9 capable de générer une force importante en un temps très court, malgré les hautes températures auxquelles sont soumises les coques 3 et 4. Ainsi, lors de la phase de vol, la disposition des éléments d'isolation thermique 11A, 11B, 11C, 11D ainsi que la configuration des tiges de maintien 10A et 10B préservent le fonctionnement de l'actionneur pyrotechnique 9 en l'isolant des contraintes thermique et mécanique que subissent les coques 3 et 4. Lors de la phase d'éjection, la coiffe 2 doit être éjectée très rapidement pour permettre l'utilisation du capteur 8. L'actionneur pyrotechnique 9 rend possible cette éjection rapide en générant une force suffisante pour rompre les tiges de maintien 10A et 10B, préalablement fragilisées. En outre, les éléments d'isolation thermique 11A, 11B, 11C, 11D forment une protection localisée qui permet de minimiser la masse et l'encombrement du dispositif d'actionnement 7 embarqué.The actuating device 7, as described above, is a unitary unit whose architecture makes it possible to fulfill, on the one hand, the function of maintaining the stability of the cap 2, in particular during the flight phase and secondly the fast ejection function of the shells 3 and 4. The architecture of the actuating device 7 makes compatible the use of a pyrotechnic actuator 9 capable of generating a large force in a very short time. short, despite the high temperatures to which the hulls 3 and 4 are subjected. Thus, during the flight phase, the arrangement of the thermal insulation elements 11A, 11B, 11C, 11D as well as the configuration of the holding rods 10A and 10B preserve the operation of the pyrotechnic actuator 9 by isolating it from the thermal and mechanical stresses experienced by the shells 3 and 4. During the ejection phase, the cap 2 must be ejected very rapidly to allow the use of the sensor 8 The pyrotechnic actuator 9 makes this rapid ejection possible by generating a force sufficient to break the previously weakened holding rods 10A and 10B. In addition, the thermal insulation elements 11A, 11B, 11C, 11D form a localized protection which makes it possible to minimize the mass and the bulk of the on-board actuating device 7.

Le dispositif d'actionnement pyrotechnique 7 présente également l'avantage d'être adaptable au maintien et à l'éjection de toute partie amovible de missile 1 dans un environnement à hautes températures. Enfin, le dispositif d'actionnement 7 fonctionne dans tous les cas du domaine de vol (en et hors atmosphère) d'un missile 1 et pour des vitesses allant du subsonique au haut supersonique/hypersonique.The pyrotechnic actuating device 7 also has the advantage of being adaptable to the holding and ejection of any removable part of missile 1 in a high temperature environment. Finally, the actuating device 7 operates in all cases of the flight envelope (in and out of the atmosphere) of a missile 1 and for speeds ranging from subsonic to supersonic high / hypersonic.

Claims (14)

Dispositif d'actionnement pour l'éjection d'au moins une partie amovible (3, 4) d'un missile (1),
caractérisé en ce que ledit dispositif (7) est un ensemble unitaire comprenant : - un actionneur pyrotechnique (9) comprenant une charge pyrotechnique (12) activable apte à générer une surpression et un piston (14) configuré pour se déplacer dans une direction longitudinale sous l'effet de la surpression générée sur la tête (15) dudit piston (14) par la charge pyrotechnique (12), de sorte que l'extrémité du piston (14) opposée à ladite tête (15), dite extrémité libre (16), est destinée à agir sur ladite partie amovible (3, 4) du missile (1) ; - au moins une tige de maintien (10A, 10B), ladite au moins une tige de maintien (10A, 10B) comprenant au moins une partie solidaire dudit actionneur pyrotechnique (9) par l'intermédiaire d'une chape mécanique (21A, 21B) ; et - au moins un élément d'isolation thermique (11A, 11B, 11C, 11D) agencé de manière à isoler thermiquement au moins la charge pyrotechnique (12), en ce que ledit actionneur pyrotechnique (9) est configuré pour pouvoir générer une force apte à rompre ladite au moins une tige de maintien (10A, 10B), en ce qu'une première extrémité de ladite au moins une tige de maintien (10A, 10B) et une extrémité dudit actionneur pyrotechnique (9) sont destinées à être fixées sur un élément de fixation (18) du missile (1),
et en ce qu'une seconde extrémité, opposée à ladite première extrémité de ladite au moins une tige de maintien (10A, 10B), est destinée à être fixée à un élément de fixation (17) de ladite partie amovible du missile (1).Actuating device for ejecting at least one removable part (3, 4) of a missile (1),
characterized in that said device (7) is a unitary assembly comprising: a pyrotechnic actuator (9) comprising an activatable pyrotechnic charge (12) capable of generating an overpressure and a piston (14) configured to move in a longitudinal direction under the effect of the overpressure generated on the head (15) of said piston (14) by the pyrotechnic charge (12), so that the end of the piston (14) opposite said head (15), said free end (16), is intended to act on said removable part (3, 4) missile (1); at least one holding rod (10A, 10B), said at least one holding rod (10A, 10B) comprising at least one part integral with said pyrotechnic actuator (9) via a mechanical clevis (21A, 21B) ); and at least one thermal insulation element (11A, 11B, 11C, 11D) arranged to thermally isolate at least the pyrotechnic charge (12), in that said pyrotechnic actuator (9) is configured to be able to generate a force capable of breaking said at least one holding rod (10A, 10B), in that a first end of said at least one holding rod (10A, 10B) and an end of said pyrotechnic actuator (9) are intended to be fixed on a fastening element (18) of the missile (1),
and in that a second end, opposite said first end of said at least one holding rod (10A, 10B), is intended to be fastened to a fastening element (17) of said removable portion of the missile (1) . Dispositif selon la revendication 1,
caractérisé en ce qu'il comporte deux tiges de maintien (10A, 10B) sensiblement parallèles entre elles et avec un axe de déplacement du piston (14) et agencées de part et d'autre dudit piston (14) dans un même plan (XY).Device according to claim 1,
characterized in that it comprises two holding rods (10A, 10B) substantially parallel to one another and with a displacement axis of the piston (14) and arranged on either side of said piston (14) in the same plane (XY). Dispositif selon l'une quelconque des revendications précédentes,
caractérisé en ce que ladite au moins une tige de maintien (10A, 10B) possède au moins une zone de fragilisation (22A, 22B).Device according to any one of the preceding claims,
characterized in that said at least one holding rod (10A, 10B) has at least one embrittlement zone (22A, 22B). Dispositif selon l'une quelconque des revendications précédentes,
caractérisé en ce que ladite zone de fragilisation (22A, 22B) est située à proximité de l'extrémité libre (16) du piston (14).Device according to any one of the preceding claims,
characterized in that said embrittlement zone (22A, 22B) is located near the free end (16) of the piston (14). Dispositif selon l'une quelconque des revendications précédentes,
caractérisé en ce que ladite au moins une tige de maintien (10A, 10B) comprend au moins un élément de retenue (23A, 23B) par rapport à l'actionneur pyrotechnique (9).Device according to any one of the preceding claims,
characterized in that said at least one holding rod (10A, 10B) comprises at least one retaining element (23A, 23B) with respect to the pyrotechnic actuator (9). Dispositif selon les revendications 1 et 5,
caractérisé en ce que ledit au moins un élément de retenue (23A, 23B) est agencé au niveau de la chape mécanique (21A, 21 B).Device according to claims 1 and 5,
characterized in that said at least one retaining element (23A, 23B) is arranged at the mechanical clevis (21A, 21B). Dispositif selon l'une quelconque des revendications précédentes,
caractérisé en ce que ladite au moins une tige de maintien (10A, 10B) est pourvue au moins d'un manchon d'isolation thermique (11B, 11C), au moins sur un tronçon longitudinal de cette dernière (10A, 10B).Device according to any one of the preceding claims,
characterized in that said at least one holding rod (10A, 10B) is provided with at least one thermal insulation sleeve (11B, 11C), at least on a longitudinal section thereof (10A, 10B). Dispositif selon les revendications 1 et 7,
caractérisé en ce que ledit manchon d'isolation thermique (11B, 11C) est agencé au niveau de la chape mécanique (21A, 21B).Device according to claims 1 and 7,
characterized in that said thermal insulation sleeve (11B, 11C) is arranged at the mechanical clevis (21A, 21B). Dispositif selon l'une quelconque des revendications précédentes,
caractérisé en ce que ladite seconde extrémité de la tige de maintien (10A, 10B) est pourvue d'un filetage (19A, 19B), agencé pour permettre la fixation de ladite tige de maintien (10A, 10B) à un élément de fixation (17, 18) de la partie amovible (3, 4) du missile (1) par l'intermédiaire d'un écrou (20A, 20B).Device according to any one of the preceding claims,
characterized in that said second end of the holding rod (10A, 10B) is provided with a thread (19A, 19B), arranged to allow attachment of said holding rod (10A, 10B) to a fastener ( 17 18) of the removable part (3, 4) of the missile (1) via a nut (20A, 20B). Dispositif selon l'une quelconque des revendications précédentes,
caractérisé en ce que ledit élément d'isolation thermique (11A, 11B, 11C, 11D) est réalisé dans au moins l'un des matériaux suivants : mica, mullite, muscovite.Device according to any one of the preceding claims,
characterized in that said thermal insulation element (11A, 11B, 11C, 11D) is made of at least one of the following materials: mica, mullite, muscovite. Missile,
caractérisé en ce qu'il comporte un dispositif d'actionnement (7) tel que celui spécifié sous l'une quelconque des revendications précédentes, ledit dispositif d'actionnement (7) étant fixé par une première de ses extrémités à un élément de fixation (18) d'une première partie (4) du missile (1) et par une seconde extrémité, opposée à ladite première extrémité, à un élément de fixation (17) d'une deuxième partie (3), représentant ladite partie amovible du missile (1).Missile,
characterized in that it comprises an actuating device (7) such as that specified in any one of the preceding claims, said actuating device (7) being fixed by a first of its ends to a fastener ( 18) of a first part (4) of the missile (1) and a second end, opposite said first end, to a fastening element (17) of a second part (3), representing said removable part of the missile (1). Missile selon la revendication 11,
caractérisé en ce qu'il est pourvu d'une coiffe (2) comprenant au moins deux coques individuelles (3, 4), et en ce que ladite première partie (4) représente l'une desdites coques individuelles (4) et ladite deuxième partie (3) amovible représente l'autre coque individuelle (3).Missile according to claim 11,
characterized in that it is provided with a cap (2) comprising at least two individual shells (3, 4), and in that said first part (4) represents one of said individual shells (4) and said second shells (4). removable portion (3) represents the other individual shell (3). Missile selon les revendications 11 et 12,
caractérisé en ce que le dispositif d'actionnement (7) est configuré pour séparer et écarter simultanément les deux coques individuelles (3, 4).Missile according to claims 11 and 12,
characterized in that the actuating device (7) is configured to separate and separate simultaneously the two individual shells (3, 4). Missile selon l'une quelconque des revendications 11 à 13, caractérisé en ce qu'au moins un élément d'isolation thermique (11D) est agencé en face de l'extrémité libre (16) dudit piston (14), et fixé sur l'élément de fixation (17) de la partie amovible (3) du missile (1).Missile according to any one of claims 11 to 13, characterized in that at least one thermal insulation element (11D) is arranged facing the free end (16) of said piston (14), and fixed on the fixing element (17) of the removable part (3) of the missile (1).
EP18290030.8A 2017-04-28 2018-04-10 Actuating device for ejecting at least one removable part of a missile, in particular a fairing Active EP3396300B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL18290030T PL3396300T3 (en) 2017-04-28 2018-04-10 Actuating device for ejecting at least one removable part of a missile, in particular a fairing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1700467A FR3065798A1 (en) 2017-04-28 2017-04-28 ACTUATING DEVICE FOR EJECTING AT LEAST ONE REMOVABLE PORTION OF MISSILE, ESPECIALLY A HEAD

Publications (2)

Publication Number Publication Date
EP3396300A1 true EP3396300A1 (en) 2018-10-31
EP3396300B1 EP3396300B1 (en) 2019-12-25

Family

ID=60019937

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18290030.8A Active EP3396300B1 (en) 2017-04-28 2018-04-10 Actuating device for ejecting at least one removable part of a missile, in particular a fairing

Country Status (8)

Country Link
US (1) US10942015B2 (en)
EP (1) EP3396300B1 (en)
JP (1) JP7029470B2 (en)
ES (1) ES2775446T3 (en)
FR (1) FR3065798A1 (en)
IL (1) IL269773B2 (en)
PL (1) PL3396300T3 (en)
WO (1) WO2018197760A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112284196A (en) * 2020-12-25 2021-01-29 星河动力(北京)空间科技有限公司 Fairing separation system for carrier rocket and carrier rocket
WO2024017767A1 (en) * 2022-07-21 2024-01-25 Safran Electronics & Defense Air vehicle having a protected front optical element

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113513951A (en) * 2021-04-30 2021-10-19 中国工程物理研究院总体工程研究所 Connection unlocking and heat-proof system of full-enclosed split head cover
CN113551565B (en) * 2021-09-18 2021-11-30 中国科学院力学研究所 Stage section pneumatic shape-preserving solid rocket and separation method

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1685362A2 (en) * 2003-11-17 2006-08-02 Raytheon Company Missile with multiple nosecones
WO2009095910A2 (en) * 2008-01-28 2009-08-06 Rafael Advanced Defense Systems Ltd. Apparatus and method for splitting and removing a shroud from an airborne vehicle
EP2960619A1 (en) * 2014-06-25 2015-12-30 MBDA France Structural wall of a missile, particularly for a thermal protective cap

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5235128A (en) * 1991-04-18 1993-08-10 Loral Corporation Separable missile nosecap
JP3770430B2 (en) * 1997-06-30 2006-04-26 株式会社アイ・エイチ・アイ・エアロスペース Nose fairing separation device for flying objects
DE102005030090B4 (en) * 2005-06-27 2007-03-22 Diehl Bgt Defence Gmbh & Co. Kg Throw-off hood and missile with detachable hood
FR2947808B1 (en) 2009-07-09 2011-12-09 Astrium Sas SOFT LINEAR SEPARATION DEVICE OF A FIRST PART AND A SECOND PART
FR2966919B1 (en) * 2010-10-29 2013-11-01 Tda Armements Sas A SECURE AERODYNAMIC COVER FOR GUIDED MUNITION AND GUIDEED MUNITION COMPRISING SUCH A BOX.

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1685362A2 (en) * 2003-11-17 2006-08-02 Raytheon Company Missile with multiple nosecones
WO2009095910A2 (en) * 2008-01-28 2009-08-06 Rafael Advanced Defense Systems Ltd. Apparatus and method for splitting and removing a shroud from an airborne vehicle
EP2960619A1 (en) * 2014-06-25 2015-12-30 MBDA France Structural wall of a missile, particularly for a thermal protective cap

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112284196A (en) * 2020-12-25 2021-01-29 星河动力(北京)空间科技有限公司 Fairing separation system for carrier rocket and carrier rocket
WO2024017767A1 (en) * 2022-07-21 2024-01-25 Safran Electronics & Defense Air vehicle having a protected front optical element
FR3138203A1 (en) * 2022-07-21 2024-01-26 Safran Electronics & Defense Aerial vehicle with protected frontal optics.

Also Published As

Publication number Publication date
US20200109929A1 (en) 2020-04-09
IL269773A (en) 2019-11-28
EP3396300B1 (en) 2019-12-25
IL269773B2 (en) 2024-04-01
FR3065798A1 (en) 2018-11-02
IL269773B1 (en) 2023-12-01
US10942015B2 (en) 2021-03-09
WO2018197760A1 (en) 2018-11-01
JP7029470B2 (en) 2022-03-03
ES2775446T3 (en) 2020-07-27
JP2020517882A (en) 2020-06-18
PL3396300T3 (en) 2020-06-29

Similar Documents

Publication Publication Date Title
EP3396300B1 (en) Actuating device for ejecting at least one removable part of a missile, in particular a fairing
EP2960618B1 (en) Missile with removable protective cap
EP2960619B1 (en) Structural wall of a missile, particularly for a thermal protective cap
FR3065521B1 (en) MISSILE PROVIDED WITH A SEPARABLE HEADBOARD COMPRISING AT LEAST ONE EJECTABLE SHELL COOPERATING WITH A SUPPORTING ELEMENT
EP3027511B1 (en) Method and device for connecting and separating two elements by means of connecting plates
FR3009282A1 (en) METHOD AND DEVICE FOR LINKING AND LINEAR SEPARATING TWO ELEMENTS WITH DECAL ENERGY MEANS
EP3617075B1 (en) Localised link device for controlled separation comprising a layer with multidirectional link
EP3027512B1 (en) Method and device for connecting and separating two elements with combined connecting and separating means
EP0246958A1 (en) Device for pyrotechnically separating two elements
EP3344547B1 (en) Method for the linear separation and connection of two elements
EP3512774B1 (en) Connection device with separation controlled by non-pyrotechnic thermal effect with reduced reaction time
EP3589550A1 (en) Method and device for the connection and linear separation of two elements stuck together
EP2701977A1 (en) Method for temporarily connecting two parts together, such as two stages of a space launcher, and assembly including two temporarily connected parts
EP2633262A1 (en) Ejectable aerodynamic cap for guided munition and guided munition comprising such a cap
FR2960055A1 (en) GUIDED MUNITION PROTECTED BY AERODYNAMIC COIFFE
FR2650639A1 (en) Unlockable fastening system for two elements, particularly for two elements of a munition
FR3109413A1 (en) Reusable, low impact hold and release device
EP0767356B1 (en) Spin braking system for a cargo ammunition submissile
FR3138123A1 (en) Annular intermediate stage enclosure of an aerospace launcher with fall retarder
FR3123892A1 (en) Method and device for deorbiting an artificial satellite from earth orbit
FR3074480A1 (en) SEPARATION IN TWO TIMES OF VIROLES BELONGING TO A LAUNCHER
FR2657158A1 (en) Cratering weapon for target with high mechanical strength
CH346117A (en) Set including several rockets suspended from each other

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20190423

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F42B 15/34 20060101AFI20190903BHEP

Ipc: F42B 15/36 20060101ALI20190903BHEP

INTG Intention to grant announced

Effective date: 20190927

RIN1 Information on inventor provided before grant (corrected)

Inventor name: LAHEYNE, CLYDE

Inventor name: QUERTELET, CLEMENT

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602018001790

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1217585

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200115

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: NO

Ref legal event code: T2

Effective date: 20191225

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200325

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200326

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2775446

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20200727

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200425

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602018001790

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1217585

Country of ref document: AT

Kind code of ref document: T

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

26N No opposition filed

Effective date: 20200928

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200410

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200410

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210430

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220410

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230703

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: PL

Payment date: 20240326

Year of fee payment: 7

Ref country code: NO

Payment date: 20240325

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240425

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240409

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20240506

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20240409

Year of fee payment: 7

Ref country code: FR

Payment date: 20240423

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: TR

Payment date: 20240404

Year of fee payment: 7

Ref country code: SE

Payment date: 20240423

Year of fee payment: 7