EP0604263A1 - Actuator especially for moving thrust nozzles of a missile - Google Patents

Actuator especially for moving thrust nozzles of a missile Download PDF

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Publication number
EP0604263A1
EP0604263A1 EP93402963A EP93402963A EP0604263A1 EP 0604263 A1 EP0604263 A1 EP 0604263A1 EP 93402963 A EP93402963 A EP 93402963A EP 93402963 A EP93402963 A EP 93402963A EP 0604263 A1 EP0604263 A1 EP 0604263A1
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EP
European Patent Office
Prior art keywords
chamber
distributor
conduit
rod
passage
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
EP93402963A
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German (de)
French (fr)
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EP0604263B1 (en
Inventor
Jean-Louis Girardeau
Joel Farges
Augustin Grossi
Patrick Fiandesio
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Airbus Group SAS
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Airbus Group SAS
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Publication date
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Publication of EP0604263A1 publication Critical patent/EP0604263A1/en
Application granted granted Critical
Publication of EP0604263B1 publication Critical patent/EP0604263B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/663—Steering by varying intensity or direction of thrust using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves

Definitions

  • the present invention relates to a device for actuating a mechanical member from a fluid supply source.
  • the device according to the invention is more particularly intended for piloting, in particular in force, aircraft such as for example missiles.
  • a control unit comprising a plurality of lateral nozzles which are distributed around the structure of said missile and whose flow of the gas jet can be deflected by a mechanical member associated with each lateral nozzle and controlled by an actuating device.
  • the latter generally comprises a controllable distributor capable of being traversed by the gas jet coming from the main propulsion generator of the missile or from an auxiliary generator, and supplying the nozzles.
  • the distributor acts, by means of the gas jet, on the mechanical member which makes it possible, by its change of position, to deflect the gas jet at the outlet of the corresponding lateral nozzle, so as to modify the trajectory of the missile.
  • the object of the present invention is to remedy these drawbacks.
  • the piston when the distributor is active, closing for example the communication between the first conduit connected to the outlet orifice, and said chamber of said distributor, the piston is in the retracted position for which said member occupies a first operating position, under the action of the fluid source acting in the second chamber of the jack through the third conduit, which empties the first chamber of the jack outward through the second conduit, the chamber of said distributor and the outlet orifice of the body.
  • the distributor when the distributor 'is inactive, then putting the second conduit into communication with the first conduit, via the distributor chamber, the piston slides to its extended position for which said member occupies a second operating position, under the action of the fluid source acting in the first chamber of the jack, which empties then the second bedroom through the third conduit.
  • the device according to the invention overcomes the aforementioned drawbacks, since it allows said chamber of the distributor to be placed in communication with the gas jet only sequentially, that is to say only when the organ must be controlled to divert the flow of the gas jet leaving the nozzle, and since it completely isolates the organ to be controlled from the jet or gas flow emitted by the fluid source, such as the missile propulsion generator.
  • the first position of said member associated with one of the lateral nozzles of the missile does not affect the trajectory of the missile, since the gas jet does not pass through the chamber of the device and therefore does not act on the piston of the jack , while the second position of said member makes it possible to deflect the flow of the gaseous jet at the outlet of the nozzle then modifying the trajectory of said missile.
  • said actuating device in the form of a body uniting the jack and the distributor thus constitutes a construction unit, facilitating its practical realization, as well as the assembly and disassembly operations with a view to its maintenance or of his replacement.
  • the cross section of the first chamber of said cylinder is greater than the annular cross section of the second chamber of the piston, defined by the difference in surfaces between the head and the rod of said piston.
  • the difference in piston cross-sections in the two chambers allows, during operation of the distributor, the exit of said piston despite an identical pressure from the gas flow in the two chambers.
  • seals are provided between said piston and said chambers and they are made of a material resistant to high temperatures and pressures. For example, graphite seals are particularly suitable for this type of application.
  • said connecting means between said piston and said member may be constituted by at least one articulation with an axis, ball joint or the like, capable of causing said member to move from a first position to a second position, and vice versa, by following the sliding of said piston.
  • said connecting means between said piston and said member may be constituted by at least one articulation with an axis, ball joint or the like, capable of causing said member to move from a first position to a second position, and vice versa, by following the sliding of said piston.
  • said distributor comprises a controllable electromagnet, connected to said body, and an axially displaceable element comprising a rod which passes through an axial passage, formed in said body and comprising said chamber, said rod having a shoulder situated at the level of said chamber of said axial passage and capable of cooperating either with an upstream bearing surface of said passage, through which opens said first conduit, when said electromagnet is excited, or with a downstream bearing surface of said passage, opening towards said body outlet orifice , when said electromagnet is de-energized.
  • the contact of the shoulder of the rod with the upstream range or the downstream range of the passage closes, respectively, the first supply duct of said distributor chamber, the second distributor discharge duct being in communication with the outlet or exhaust port, or the outlet port of said chamber of the distributor, the first conduit being in communication with the second conduit.
  • the diameter of said shoulder is slightly greater than the internal diameters of the upstream and downstream spans of said passage, while the diameter of said rod is slightly less than those of said spans.
  • said outlet orifice of said body is coaxial with said passage and extends the downstream reach of said passage, and the rod ends, at its end opposite to that facing the electromagnet, by a cylindrical tip whose diameter is close of the diameter of said rod and which is located in said outlet orifice.
  • the outlet orifice of the body it is also advantageous for the outlet orifice of the body to flare outwards.
  • said upstream and downstream ranges are defined by rings fixed in said passage of the body and traversed by said sliding rod whose shoulder is provided between said rings.
  • said inlet port of the body is provided with a fixed ferrule to said body and provided with an axial channel in connection with said fluid source and opening laterally into external annular grooves communicating with each other and with said first and third conduits.
  • an actuating device in communication with the gas flow can advantageously be associated with at least one nozzle, the actuating device being capable, when actuated, of controlling the orientation of a mechanical member linked to said nozzle, to modify the direction of flow of the gaseous jet leaving said nozzle and, therefore, the trajectory of the missile.
  • FIG. 1 schematically illustrates, in partial longitudinal section, a missile equipped with actuation devices of the invention, for its piloting.
  • Figure 2 shows, in section, a schematic embodiment of an actuating device according to the invention, in its inactive operating configuration.
  • FIG. 2A shows an enlargement of a detail of the device illustrated in FIG. 2.
  • FIG. 3 shows, similarly, the device of Figure 2 in its active operating configuration.
  • Figures 4 and 5 illustrate exterior views, in two perpendicular planes, of a concrete embodiment of the actuating device, in the inactive configuration, for controlling an adjustable nozzle skirt.
  • Figures 6 and 7 are respectively sectional views of the device along lines VI-VI and VII-VII of Figure 4.
  • Figures 8 and 9 are respectively sectional views of the device along lines VIII-VIII and IX-IX of Figure 5.
  • FIG. 10 is a section of the device along the line X-X of FIG. 6.
  • Figures 11 and 12 are views similar to those of Figures 7 and 8, in the active configuration of said device.
  • Figure 13 is a side view of Figure 9, showing the orientation of the skirt of the nozzle, as a result of actuation of the device.
  • the actuating device 1 according to the invention will be described below with regard to its preferred application relating to the force piloting of a missile 2 shown diagrammatically in FIG. 1.
  • This missile 2 comprises an elongated structure 3 of axis XX equipped, in the usual manner, with wings 4 provided with control surfaces 5.
  • a block 6 for the piloting the missile in force comprising lateral nozzles 7, for example four in number, two to two diametrically opposite.
  • the control unit 6 is located between two combustion chambers 8A of a gas generator 8, preferably with solid propellant.
  • the side nozzles 7 are connected to the generator chambers by conduits 9 and each of them is advantageously controlled by an actuating device 1 according to the invention.
  • this device makes it possible to act, when it is stressed, on a mechanical member 10 whose purpose is to deflect the gas jet leaving the lateral nozzle and coming from the combustion chambers of the gas generator, to then modify the trajectory of the missile.
  • the actuating device 1 shown schematically in Figures 2 and 3, comprises a single body 11 which is intended, in this application, to be fixed to the structure 3 of the missile and in which are arranged on the one hand a distributor of control 12 and, on the other hand, an actuating cylinder 14 of said member to be moved by articulation means 13.
  • a first conduit 15 connects a chamber 16 of the distributor 12 to an inlet orifice 17 of the body, which is in direct communication with the gas jet delivered by the gas generator.
  • a second conduit 18 connects the chamber 16 of the distributor with a first chamber 19A of the jack 14. Depending on the inactive or active state of the distributor, this second conduit 18 can be in communication, via the chamber 16 of the distributor , with the first conduit 15 or with an outlet orifice 20 of the body in connection with the surrounding external environment.
  • a third conduit 21 finally connects the second chamber 19B of the jack to the inlet orifice 17 of the body.
  • the distributor 12 consists of a controllable electromagnet 22A, connected by a link 22A1 to a power supply (not shown), and of a displaceable element 22B extending the electromagnet axially.
  • This the latter is housed in a casing 23 which is connected, by screwing, to said body 11.
  • the movable element 22B is constituted, in known manner, by a pallet 24, turned towards the electromagnet and housed in the bottom of the casing , and by a rod 25 integral with the pallet 24 and passing through the bottom of the casing to open coaxially in a passage 26 which is provided in said body 11 and in which the chamber 16 of the distributor 12 is formed.
  • the rod 25 has, in the vicinity of its end opposite to that screwed onto the pallet, an annular shoulder 25A which is then located at the level of the chamber 16 of said passage 26.
  • the shoulder 25A is thus capable of cooperating, depending on the sliding of the rod controlled by the electromagnet, either with an upstream surface 27 of said passage, through which the first conduit 15 opens, or with a downstream surface 28 of said passage communicating with the outlet orifice 20 of the body.
  • the chamber 16 of the distributor is then delimited by the upstream and downstream ranges 27, 28 of the passage, while the second conduit 18 opens laterally into the latter while being in communication either with the first conduit 15 or with the outlet orifice 20.
  • the diameter Dt of the rod 25 is slightly smaller than the identical internal diameters d of the upstream 27 and downstream 28 bearings of the passage, and that the diameter D of said shoulder 25A is greater, but slightly, than the identical internal diameters d of the upstream 27 and downstream 28 bearings of the passage 26, which are defined, for example, by rings 29, 30 fixedly engaged in said passage.
  • the rod 25 thus passes through the rings 29.30 and the shoulder 25A is located between them.
  • conical surfaces 25B and 25C terminate the two sides of the shoulder, so that optimum sealing is obtained when one or the other of the conical surfaces 25B and 25C is in abutment, by the sliding of the rod, against the corresponding bearing.
  • the displacement stroke of the sliding element 25, and therefore of the shoulder of the rod between the rings depending on whether the electromagnet is excited or not.
  • the outlet orifice 20 is coaxial with the passage 26 of the dispenser and it is advantageously defined by the downstream annular ring 30.
  • the outlet orifice 20 widens further towards the outside.
  • the rod 25 ends in a cylindrical endpiece 25D extending the shoulder 25A by having a diameter close to, but less than, the latter. This nozzle 25D engages in the outlet orifice 20 of the body, defined by the downstream ring 30.
  • the actuating cylinder 14 comprises a piston 31 capable of sliding with sealing in the chambers 19A and 19B formed by a passage 19 formed in the body. More particularly, the piston 31 consists of a head 31A sealingly separating the two chambers 19A and 19B and a rod 31B extending the head from the side of the second chamber 19B and projecting outwardly relative to the body 11 , to be associated with the member to be controlled by connecting means 13, as will be seen later.
  • the rod 31B and, therefore, the member to be controlled are external to the gas jet and are not, therefore, in contact with the latter.
  • Seals 32 are provided on the one hand around the head 31A of the piston and, on the other hand, around the rod 31B and they are produced, due to the temperatures and pressures present, with a material resistant to graphite base. Furthermore, it can be seen in FIGS. 2 and 3 that the cross section S of the first chamber 19A in communication with the second conduit 18 is optimal, since it corresponds to the transverse surface of the head 31A of the piston, and greater than the cross section s of the second chamber 19B in communication with the third conduit 21, since it corresponds to the difference between the cross section of the head 31A and the section transverse of the rod 31B.
  • FIGS. 2 and 3 The schematic representation of the actuating device 1, illustrated in FIGS. 2 and 3, advantageously makes it possible to view on the same section plane the electromagnetic distributor 12, the jack 14 and the various conduits and passages provided in the body 11.
  • the embodiment of the device 1 turns out to be quite different, as can be seen in FIGS. 4 and 5 showing the external contour of the actuating device 1, the distributor 12 of which is recognized and the jack 14 arranged in the same single body 11, which is associated with one of the side nozzles 7 of the force control block 6 of the missile 2.
  • the numerical references assigned to the different parts of the device described in the figures 2 and 3 have been kept for the device described in FIGS. 6 to 10.
  • this concrete embodiment of the actuating device 1 shows the member to be moved 10 by through the actuator, as well as other specific details of the device which will be described below.
  • the member 10 making it possible to deflect, if necessary, the gas jet coming from the generator and passing through the lateral nozzle 7 is defined, in this example, by a skirt 10A substantially of frustoconical shape, which surrounds the downstream end 7A of the nozzle to extend beyond the latter, its upstream end 7B communicating with the conduit 9.
  • the frustoconical skirt 10A is pivotally mounted relative to the nozzle 7 about an orthogonal axis 10B to the longitudinal axis LL of said nozzle.
  • the skirt is, moreover, provided with a yoke in the form of a yoke 10C which straddles the end of the rod 31B of said piston so as to be associated with it by the connecting means 13, defined by an axis, parallel to the pivot axis 10B.
  • the inlet orifice 17 of the gas jet is provided with a cylindrical ferrule 34 fixedly housed in the body and provided with an axial channel 34A in connection with the conduit 9 and opening out laterally in annular grooves 34B interconnected to then communicate with the first supply duct 15 of the distributor 12 and the third supply duct 21 of the second chamber 19B.
  • the purpose of the arrangement of this ferrule is to brake and cool the gas jet generated by the generators in the direction of the force control block 6 consisting of the actuating devices 1 and the side nozzles 7.
  • each device 1 is initially in the inactive configuration shown in Figures 2 and 4 to 10, for which the trajectory of the missile 2 is not changed.
  • the electromagnet 22A is supplied, by the link 22A1, and attracts the movable element 22B towards it.
  • the conical section 25B of the shoulder 25A provided on the rod 25 integral with the pallet 24, is applied against the upstream bearing 27 of the ring 29, closing the passage 26 and, in particular, the communication between the first conduit 15 and the chamber 16 of the distributor. Consequently, the flow of the gas jet, passing through the channel 34A and the grooves 34B of the shell 34, then the first conduit 15 to open into the passage 26, is stopped at the level of the shoulder contact 25A - ring 29.
  • the chamber 16 of the distributor places the first chamber 19A of the jack in communication with the outside, respectively by the second conduit 18 and the outlet orifice 20 of the body. Simultaneously with the supply of the first conduit 15, the gas jet passes through the third conduit 21, so that the piston 31, under the action of the pressure exerted on its surface s then prevailing in the second chamber 19B, is pushed back until it occupies a retracted position by emptying the first chamber 19A in communication with the outside. Consequently, in the retracted position of the jack 14, obtained when the distributor 12 is supplied, corresponds a first, neutral position, of the skirt 10A, in the axial extension of the lateral nozzle 7, not influencing the trajectory of the missile.
  • the orientable skirt 10A, the articulation means 13 and the rod part 31B leaving said body towards the outside environment are not affected by the gas jet emitted.
  • the chamber 16 of the distributor and the first chamber 19A of the jack are isolated from the hot gas jet, avoiding the risks of deformation or the like, as long as the electromagnetic distributor 12 closes the first supply conduit 15.
  • the low difference between the diameter Dt of the rod 25A and the diameter d of the upstream seat 27 requires only an effort minimum of the electromagnet, so that it can have a reduced size and, therefore, a small footprint.
  • the electromagnet 22A of the distributor 11 is no longer supplied by the link 22A1.
  • This supply break instantly causes a natural movement away from the movable element 22B which is no longer attracted by the electromagnet, thanks to the gas jet leaving the first conduit 15 towards the passage 26.
  • the rod 25 is pushed back until the conical surface 25C of the shoulder 25A comes to bear against the downstream bearing 28 of the ring 30.
  • the displacement of the rod 25 on the stroke c then establishes the fluid communication between the first conduit 15 and the second conduit 18 through the chamber 16 of the distributor, since the conical surface 25B of the shoulder has moved away, from the stroke c , from the upstream surface 27 of the ring 29.
  • the contact between the conical surface 29C of the shoulder and the downstream surface 28 of the ring closes the outlet or exhaust port 20 of the distributor, and thus cuts the communication between the second conduit 18 and the latter.
  • the gas jet after having passed through the first conduit 15, the chamber 16 and the second conduit 18, enters the first chamber 19A of the jack 14, so that the pressure of the gas jet is established in the two chambers 19A and 19B by the respective conduits 18 and 21.
  • the piston 31 slides in the passage 19 towards its extended position, so that its rod 31B causes, by means of the articulation 13, the pivoting, in this case, of the orientable skirt 10A of the lateral nozzle 7 around the axis 10B.
  • the device 1 then occupies its active configuration shown in FIGS. 3, 11 and 12, for which the member to be controlled, such as the skirt 10A, is in a second position, deviated by an angle ⁇ relative to the axis LL of the lateral nozzle 7, as shown in FIGS. 1 and 13, which thus makes it possible to modify the trajectory of missile 1.
  • the member to be controlled such as the skirt 10A
  • the flow of the hot gas jet in the device is carried out only sequentially, during the flight phases of the missile requiring abrupt modifications of its trajectory, and that the control force of the sliding element by the electromagnet is minimal due to the close diameters between the rod and the bearings and is only necessary in one direction of movement, towards the downstream range of the distributor .
  • the production of a single body, bringing together the actuator and the distributor generates a significant gain in bulk.
  • the member to be controlled could be different, and be, for example, in the form of another type of nozzle, a fin, a control surface and the like.

Abstract

The invention relates to a device for actuating a mechanical member, by means of a fluid source such as a gas generator of a missile, of the type with a controllable distributor connected to the said source. Advantageously, it comprises: . a body (11) including the said distributor (12) and connected, via an inlet orifice (17), to the said fluid source; . a first pipe (15) capable of connecting the said inlet orifice to one chamber (16) of the said distributor; . a jack (14) arranged in the said body and including a first and a second coaxial chamber (19A, 19B) separated by a sliding piston (31), of which the rod (31B) projects externally with respect to the said body in order to be associated with the said mechanical member; . a second pipe (18) connecting the chamber (16) of the said distributor to the first chamber (19A) of the said jack, it being possible for the said second pipe to be placed in communication, via the said chamber of the distributor, either with the said first pipe (15) or with an outlet orifice (20) outside the body, depending on the position of the distributor; and . a third pipe (21) connecting the said second chamber (19B) of the jack to the said inlet orifice (17) of the said body. <IMAGE>

Description

La présente invention concerne un dispositif d'actionnement d'un organe mécanique à partir d'une source fluidique d'alimentation.The present invention relates to a device for actuating a mechanical member from a fluid supply source.

Quoique non exclusivement, le dispositif selon l'invention est plus particulièrement destiné au pilotage, notamment en force, d'aéronefs tels que par exemple les missiles.Although not exclusively, the device according to the invention is more particularly intended for piloting, in particular in force, aircraft such as for example missiles.

En effet, on sait que, pour modifier brusquement la trajectoire d'un missile, on utilise un bloc de pilotage comprenant une pluralité de tuyères latérales qui sont réparties autour de la structure dudit missile et dont l'écoulement du jet gazeux peut être dévié par un organe mécanique associé à chaque tuyère latérale et commandé par un dispositif d'actionnement. Ce dernier comprend généralement un distributeur commandable susceptible d'être traversé par le jet gazeux issu du générateur de propulsion principal du missile ou d'un générateur auxiliaire, et alimentant les tuyères. Le distributeur agit, par l'intermédiaire du jet gazeux, sur l'organe mécanique qui permet, par son changement de position, de dévier le jet gazeux en sortie de la tuyère latérale correspondante, pour ainsi modifier la trajectoire du missile.Indeed, we know that, to suddenly change the trajectory of a missile, we use a control unit comprising a plurality of lateral nozzles which are distributed around the structure of said missile and whose flow of the gas jet can be deflected by a mechanical member associated with each lateral nozzle and controlled by an actuating device. The latter generally comprises a controllable distributor capable of being traversed by the gas jet coming from the main propulsion generator of the missile or from an auxiliary generator, and supplying the nozzles. The distributor acts, by means of the gas jet, on the mechanical member which makes it possible, by its change of position, to deflect the gas jet at the outlet of the corresponding lateral nozzle, so as to modify the trajectory of the missile.

Bien que ces dispositifs de commande soient largement utilisés pour le pilotage en force des missiles, des risques de dysfonctionnement peuvent apparaître au niveau du distributeur et de l'organe à commander à cause du milieu fluidique, particulièrement sévère, auquel ils sont soumis, dû à la pression importante et à la température élevée du jet gazeux sortant du générateur.Although these control devices are widely used for the force piloting of missiles, risks of dysfunction can appear at the level of the distributor and of the member to be controlled because of the fluid environment, particularly severe, to which they are subjected, due to the high pressure and the high temperature of the gas jet leaving the generator.

La présente invention a pour but de remédier à ces inconvénients.The object of the present invention is to remedy these drawbacks.

A cet effet, le dispositif pour actionner un organe mécanique, à partir d'une source fluidique telle que notamment un générateur de gaz d'un missile, du type à distributeur commandable relié à ladite source fluidique, est remarquable, selon l'invention, en ce qu'il comprend :

  • un corps dans lequel est agencé ledit distributeur et qui est raccordé, par un orifice d'entrée, à ladite source fluidique ;
  • un premier conduit susceptible de relier ledit orifice d'entrée à une chambre dudit distributeur commandable ;
  • un vérin agencé dans ledit corps et comportant une première et une seconde chambres coaxiales séparées l'une de l'autre par une tête de piston coulissant, dont la tige fait saillie extérieurement par rapport audit corps pour être associée, par des moyens de liaison, audit organe mécanique ;
  • un deuxième conduit reliant la chambre dudit distributeur à la première chambre dudit vérin, ledit deuxième conduit pouvant être mis en communication, par l'intermédiaire de ladite chambre du distributeur, soit avec ledit premier conduit, soit avec un orifice de sortie extérieur du corps, selon que le distributeur est actif ou inactif ; et
  • un troisième conduit reliant ladite seconde chambre du vérin audit orifice d'entrée dudit corps.
To this end, the device for actuating a mechanical member, from a fluid source such as in particular a gas generator of a missile, of the type with controllable distributor connected to said fluid source, is remarkable, according to the invention, in that it includes:
  • a body in which said distributor is arranged and which is connected, by an inlet orifice, to said fluid source;
  • a first conduit capable of connecting said inlet orifice to a chamber of said controllable distributor;
  • a jack arranged in said body and comprising first and second coaxial chambers separated from each other by a sliding piston head, the rod of which protrudes externally relative to said body so as to be associated, by connecting means, said mechanical organ;
  • a second conduit connecting the chamber of said distributor to the first chamber of said cylinder, said second conduit being able to be put in communication, via said chamber of the distributor, either with said first conduit, or with an outlet orifice outside the body, depending on whether the distributor is active or inactive; and
  • a third conduit connecting said second chamber of the jack to said inlet orifice of said body.

Ainsi, lorsque le distributeur est actif, obturant par exemple la communication entre le premier conduit relié à l'orifice de sortie, et ladite chambre dudit distributeur, le piston est en position rentrée pour laquelle ledit organe occupe une première position de fonctionnement, sous l'action de la source fluidique agissant dans la seconde chambre du vérin par le troisième conduit, ce qui vide la première chambre du vérin vers l'extérieur par le deuxième conduit, la chambre dudit distributeur et l'orifice de sortie du corps. En revanche, lorsque le distributeur' est inactif, mettant alors en communication le deuxième conduit avec le premier conduit, par l'intermédiaire de la chambre du distributeur, le piston coulisse vers sa position sortie pour laquelle ledit organe occupe une seconde position de fonctionnement, sous l'action de la source fluidique agissant dans la première chambre du vérin, ce qui vide alors la seconde chambre par le troisième conduit.Thus, when the distributor is active, closing for example the communication between the first conduit connected to the outlet orifice, and said chamber of said distributor, the piston is in the retracted position for which said member occupies a first operating position, under the action of the fluid source acting in the second chamber of the jack through the third conduit, which empties the first chamber of the jack outward through the second conduit, the chamber of said distributor and the outlet orifice of the body. On the other hand, when the distributor 'is inactive, then putting the second conduit into communication with the first conduit, via the distributor chamber, the piston slides to its extended position for which said member occupies a second operating position, under the action of the fluid source acting in the first chamber of the jack, which empties then the second bedroom through the third conduit.

Par conséquent, le dispositif selon l'invention s'affranchit des inconvénients précités, puisqu'il permet à ladite chambre du distributeur de n'être mise en communication avec le jet gazeux que séquentiellement, c'est-à-dire uniquement lorsque l'organe doit être commandé pour dévier l'écoulement du jet gazeux sortant de la tuyère, et puisqu'il isole totalement l'organe à commander du jet ou du flux gazeux émis par la source fluidique, telle que le générateur de propulsion du missile. Dans ce cas, la première position dudit organe associée à l'une des tuyères latérales du missile n'affecte pas la trajectoire du missile, puisque le jet gazeux ne traverse pas la chambre du dispositif et donc n'agit pas sur le piston du vérin, tandis que la seconde position dudit organe permet de dévier l'écoulement du jet gazeux en sortie de la tuyère modifiant alors la trajectoire dudit missile.Consequently, the device according to the invention overcomes the aforementioned drawbacks, since it allows said chamber of the distributor to be placed in communication with the gas jet only sequentially, that is to say only when the organ must be controlled to divert the flow of the gas jet leaving the nozzle, and since it completely isolates the organ to be controlled from the jet or gas flow emitted by the fluid source, such as the missile propulsion generator. In this case, the first position of said member associated with one of the lateral nozzles of the missile does not affect the trajectory of the missile, since the gas jet does not pass through the chamber of the device and therefore does not act on the piston of the jack , while the second position of said member makes it possible to deflect the flow of the gaseous jet at the outlet of the nozzle then modifying the trajectory of said missile.

Par ailleurs, la conception dudit dispositif d'actionnement sous la forme d'un corps réunissant le vérin et le distributeur constitue ainsi une unité de construction, facilitant sa réalisation pratique, ainsi que les opérations de montage et de démontage en vue de sa maintenance ou de son remplacement.Furthermore, the design of said actuating device in the form of a body uniting the jack and the distributor thus constitutes a construction unit, facilitating its practical realization, as well as the assembly and disassembly operations with a view to its maintenance or of his replacement.

Avantageusement, la section transversale de la première chambre dudit vérin est supérieure à la section transversale annulaire de la seconde chambre du piston, définie par la différence de surfaces entre la tête et la tige dudit piston. De la sorte, la différence des sections du piston dans les deux chambres permet, lors du fonctionnement du distributeur, la sortie dudit piston malgré une pression identique issu du flux gazeux dans les deux chambres. Bien évidemment, des joints d'étanchéité sont prévus entre ledit piston et lesdites chambres et ils sont réalisés en une matière résistant aux températures et aux pressions élevées. A titre d'exemple, des joints d'étanchéité en graphite conviennent tout particulièrement pour ce type d'application.Advantageously, the cross section of the first chamber of said cylinder is greater than the annular cross section of the second chamber of the piston, defined by the difference in surfaces between the head and the rod of said piston. In this way, the difference in piston cross-sections in the two chambers allows, during operation of the distributor, the exit of said piston despite an identical pressure from the gas flow in the two chambers. Obviously, seals are provided between said piston and said chambers and they are made of a material resistant to high temperatures and pressures. For example, graphite seals are particularly suitable for this type of application.

En outre, lesdits moyens de liaison entre ledit piston et ledit organe peuvent être constitués par au moins une articulation à axe, rotule ou analogue, susceptible d'entraîner le déplacement dudit organe d'une première position vers une seconde position, et réciproquement, par suite du coulissement dudit piston. Ainsi, à chaque type d'organe, peut être adaptée l'articulation la plus appropriée.In addition, said connecting means between said piston and said member may be constituted by at least one articulation with an axis, ball joint or the like, capable of causing said member to move from a first position to a second position, and vice versa, by following the sliding of said piston. Thus, for each type of organ, the most appropriate joint can be adapted.

Dans un mode préféré de réalisation, ledit distributeur comprend un électro-aimant commandable, relié audit corps, et un élément axialement déplaçable comportant une tige qui traverse un passage axial, ménagé dans ledit corps et comprenant ladite chambre, ladite tige présentant un épaulement situé au niveau de ladite chambre dudit passage axial et susceptible de coopérer soit avec une portée amont dudit passage, par laquelle débouche ledit premier conduit, lorsque ledit électro-aimant est excité, soit avec une portée aval dudit passage, débouchant vers ledit orifice de sortie du corps, lorsque ledit électro-aimant est désexcité. Ainsi, le contact de l'épaulement de la tige avec la portée amont ou la portée aval du passage obture, respectivement, le premier conduit d'alimentation de ladite chambre du distributeur, le deuxième conduit de refoulement du distributeur étant en communication avec l'orifice de sortie ou d'échappement, ou l'orifice de sortie de ladite chambre du distributeur, le premier conduit étant en communication avec le deuxième conduit.In a preferred embodiment, said distributor comprises a controllable electromagnet, connected to said body, and an axially displaceable element comprising a rod which passes through an axial passage, formed in said body and comprising said chamber, said rod having a shoulder situated at the level of said chamber of said axial passage and capable of cooperating either with an upstream bearing surface of said passage, through which opens said first conduit, when said electromagnet is excited, or with a downstream bearing surface of said passage, opening towards said body outlet orifice , when said electromagnet is de-energized. Thus, the contact of the shoulder of the rod with the upstream range or the downstream range of the passage closes, respectively, the first supply duct of said distributor chamber, the second distributor discharge duct being in communication with the outlet or exhaust port, or the outlet port of said chamber of the distributor, the first conduit being in communication with the second conduit.

Avantageusement, le diamètre dudit épaulement est légèrement supérieur aux diamètres internes des portées amont et aval dudit passage, tandis que le diamètre de ladite tige est légèrement inférieur à ceux desdites portées. Ces considérations géométriques permettent d'utiliser un électro-aimant de faible puissance puisqu'alors un effort minimal est nécessaire pour déplacer la tige, ce qui permet, en outre, de réduire l'encombrement dudit électro-aimant. Plus particulièrement, ledit épaulement présente deux surfaces coniques aptes à coopérer respectivement avec les portées amont et aval dudit passage axial. Ainsi, le contact entre les surfaces coniques et les portées amont et aval s'avère fiable et garantit une bonne étanchéité.Advantageously, the diameter of said shoulder is slightly greater than the internal diameters of the upstream and downstream spans of said passage, while the diameter of said rod is slightly less than those of said spans. These geometric considerations make it possible to use a low power electromagnet since then minimal effort is required to move the rod, which also makes it possible to reduce the size of said electromagnet. More particularly, said shoulder has two conical surfaces capable of cooperating respectively with the upstream and downstream surfaces of said axial passage. Thus, the contact between the conical surfaces and the upstream and downstream surfaces is reliable and guarantees a good seal.

De préférence, ledit orifice de sortie dudit corps est coaxial audit passage et prolonge la portée aval dudit passage, et la tige se termine, à son extrémité opposée à celle tournée vers l'électro-aimant, par un embout cylindrique dont le diamètre est proche du diamètre de ladite tige et qui est situé dans ledit orifice de sortie. Dans ce cas, il est également avantageux que l'orifice de sortie du corps s'évase vers l'extérieur.Preferably, said outlet orifice of said body is coaxial with said passage and extends the downstream reach of said passage, and the rod ends, at its end opposite to that facing the electromagnet, by a cylindrical tip whose diameter is close of the diameter of said rod and which is located in said outlet orifice. In this case, it is also advantageous for the outlet orifice of the body to flare outwards.

Dans un mode préféré de réalisation, lesdites portées amont et aval sont définies par des bagues fixées dans ledit passage du corps et traversées par ladite tige coulissante dont l'épaulement est prévu entre lesdites bagues. Ainsi, on remarque la simplicité de réalisation desdites portées définies par des bagues.In a preferred embodiment, said upstream and downstream ranges are defined by rings fixed in said passage of the body and traversed by said sliding rod whose shoulder is provided between said rings. Thus, we note the simplicity of making said scopes defined by rings.

Afin de filtrer le jet de gaz chaud issu de la source fluidique, telle que le générateur de gaz d'un missile, ledit orifice d'entrée du corps est muni d'une virole fixée audit corps et pourvue d'un canal axial en liaison avec ladite source fluidique et débouchant latéralement dans des gorges annulaires externes communiquant entre elles et avec lesdits premier et troisième conduits. Ce parcours forcé du jet gazeux "atténue" ainsi ses caractéristiques de propreté et de température.In order to filter the jet of hot gas from the fluid source, such as the gas generator of a missile, said inlet port of the body is provided with a fixed ferrule to said body and provided with an axial channel in connection with said fluid source and opening laterally into external annular grooves communicating with each other and with said first and third conduits. This forced course of the gas jet thus "attenuates" its characteristics of cleanliness and temperature.

Une application spécifique de ce dispositif d'actionnement concerne le pilotage, notamment à force, d'un missile à partir des jets gazeux sortant du générateur de gaz et susceptibles de traverser des tuyères latérales. Ainsi, un dispositif d'actionnement en communication avec le flux gazeux peut être avantageusement associé à au moins une tuyère, le dispositif d'actionnement étant susceptible, lorsqu'il est actionné, de commander l'orientation d'un organe mécanique lié à ladite tuyère, pour modifier la direction d'écoulement du jet gazeux sortant de ladite tuyère et, donc, la trajectoire du missile.A specific application of this actuation device relates to piloting, in particular by force, of a missile from gaseous jets leaving the gas generator and capable of passing through lateral nozzles. Thus, an actuating device in communication with the gas flow can advantageously be associated with at least one nozzle, the actuating device being capable, when actuated, of controlling the orientation of a mechanical member linked to said nozzle, to modify the direction of flow of the gaseous jet leaving said nozzle and, therefore, the trajectory of the missile.

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

La figure 1 illustre schématiquement, en coupe longitudinale partielle, un missile équipé de dispositifs d'actionnement de l'invention, pour son pilotage.FIG. 1 schematically illustrates, in partial longitudinal section, a missile equipped with actuation devices of the invention, for its piloting.

La figure 2 représente, en coupe, une réalisation schématique d'un dispositif d'actionnement conforme à l'invention, dans sa configuration inactive de fonctionnement.Figure 2 shows, in section, a schematic embodiment of an actuating device according to the invention, in its inactive operating configuration.

La figure 2A montre un agrandissement d'un détail du dispositif illustré sur la figure 2.FIG. 2A shows an enlargement of a detail of the device illustrated in FIG. 2.

La figure 3 représente, de façon analogue, le dispositif de la figure 2 dans sa configuration active de fonctionnement.Figure 3 shows, similarly, the device of Figure 2 in its active operating configuration.

Les figures 4 et 5 illustrent des vues extérieures, selon deux plans perpendiculaires, d'une réalisation concrète du dispositif d'actionnement, en configuration inactive, pour la commande d'une jupe orientable de tuyère.Figures 4 and 5 illustrate exterior views, in two perpendicular planes, of a concrete embodiment of the actuating device, in the inactive configuration, for controlling an adjustable nozzle skirt.

Les figures 6 et 7 sont respectivement des vues en coupe du dispositif selon les lignes VI-VI et VII-VII de la figure 4.Figures 6 and 7 are respectively sectional views of the device along lines VI-VI and VII-VII of Figure 4.

Les figures 8 et 9 sont respectivement des vues en coupe du dispositif selon les lignes VIII-VIII et IX-IX de la figure 5.Figures 8 and 9 are respectively sectional views of the device along lines VIII-VIII and IX-IX of Figure 5.

La figure 10 est une coupe du dispositif selon la ligne X-X de la figure 6.FIG. 10 is a section of the device along the line X-X of FIG. 6.

Les figures 11 et 12 sont des vues analogues à celles des figures 7 et 8, dans la configuration active dudit dispositif.Figures 11 and 12 are views similar to those of Figures 7 and 8, in the active configuration of said device.

La figure 13 est une vue de côté de la figure 9, montrant l'orientation de la jupe de la tuyère, par suite de l'actionnement du dispositif.Figure 13 is a side view of Figure 9, showing the orientation of the skirt of the nozzle, as a result of actuation of the device.

Le dispositif d'actionnement 1 selon l'invention sera décrit ci-après en regard de son application préférentielle relative au pilotage en force d'un missile 2 montré schématiquement sur la figure 1.The actuating device 1 according to the invention will be described below with regard to its preferred application relating to the force piloting of a missile 2 shown diagrammatically in FIG. 1.

Ce missile 2 comprend une structure allongée 3 d'axe X-X équipée, de façon usuelle, d'ailes 4 pourvues de gouvernes 5. Dans la structure 3 du missile est prévu, au voisinage de son centre de gravité G, un bloc 6 pour le pilotage en force du missile comportant des tuyères latérales 7 par exemple au nombre de quatre, deux à deux diamétralement opposées. Dans cet exemple de réalisation, le bloc de pilotage 6 est situé entre deux chambres de combustion 8A d'un générateur de gaz 8, à propergol solide de préférence. Les tuyères latérales 7 sont reliées aux chambres du générateur par des conduits 9 et chacune d'elles est commandée avantageusement par un dispositif d'actionnement 1 conforme à l'invention. Comme on le verra plus en détail par la suite, ce dispositif permet d'agir, lorsqu'il est sollicité, sur un organe mécanique 10 dont le but est de dévier le jet gazeux sortant de la tuyère latérale et issu des chambres de combustion du générateur de gaz, pour modifier alors la trajectoire du missile.This missile 2 comprises an elongated structure 3 of axis XX equipped, in the usual manner, with wings 4 provided with control surfaces 5. In the structure 3 of the missile is provided, in the vicinity of its center of gravity G, a block 6 for the piloting the missile in force comprising lateral nozzles 7, for example four in number, two to two diametrically opposite. In this exemplary embodiment, the control unit 6 is located between two combustion chambers 8A of a gas generator 8, preferably with solid propellant. The side nozzles 7 are connected to the generator chambers by conduits 9 and each of them is advantageously controlled by an actuating device 1 according to the invention. As will be seen in more detail below, this device makes it possible to act, when it is stressed, on a mechanical member 10 whose purpose is to deflect the gas jet leaving the lateral nozzle and coming from the combustion chambers of the gas generator, to then modify the trajectory of the missile.

Le dispositif d'actionnement 1, montré schématiquement sur les figures 2 et 3, comprend un corps unique 11 qui est destiné, dans cette application, à être fixé à la structure 3 du missile et dans lequel sont agencés d'une part un distributeur de commande 12 et, d'autre part, un vérin d'actionnement 14 dudit organe à déplacer par des moyens d'articulation 13.The actuating device 1, shown schematically in Figures 2 and 3, comprises a single body 11 which is intended, in this application, to be fixed to the structure 3 of the missile and in which are arranged on the one hand a distributor of control 12 and, on the other hand, an actuating cylinder 14 of said member to be moved by articulation means 13.

Plusieurs conduits et orifices sont ménagés dans le corps. Tout d'abord, un premier conduit 15 relie une chambre 16 du distributeur 12 à un orifice d'entrée 17 du corps, qui est en communication directe avec le jet gazeux délivré par le générateur de gaz. Un deuxième conduit 18 met en communication la chambre 16 du distributeur avec une première chambre 19A du vérin 14. Selon l'état inactif ou actif du distributeur, ce deuxième conduit 18 peut être en communication, par l'intermédiaire de la chambre 16 du distributeur, avec le premier conduit 15 ou avec un orifice de sortie 20 du corps en liaison avec le milieu extérieur environnant. Un troisième conduit 21 relie enfin la seconde chambre 19B du vérin à l'orifice d'entrée 17 du corps.Several conduits and orifices are provided in the body. First, a first conduit 15 connects a chamber 16 of the distributor 12 to an inlet orifice 17 of the body, which is in direct communication with the gas jet delivered by the gas generator. A second conduit 18 connects the chamber 16 of the distributor with a first chamber 19A of the jack 14. Depending on the inactive or active state of the distributor, this second conduit 18 can be in communication, via the chamber 16 of the distributor , with the first conduit 15 or with an outlet orifice 20 of the body in connection with the surrounding external environment. A third conduit 21 finally connects the second chamber 19B of the jack to the inlet orifice 17 of the body.

Plus particulièrement, le distributeur 12 se compose d'un électro-aimant commandable 22A, relié par une liaison 22A1 à une alimentation électrique non représentée, et d'un élément déplaçable 22B prolongeant axialement l'électro-aimant. Ce dernier est logé dans un carter 23 qui est raccordé, par vissage, sur ledit corps 11. L'élément déplaçable 22B est constitué, de façon connue, par une palette 24, tournée vers l'électro-aimant et logée dans le fond du carter, et par une tige 25 solidaire de la palette 24 et traversant le fond du carter pour déboucher coaxialement dans un passage 26 qui est prévu dans ledit corps 11 et dans lequel est ménagée la chambre 16 du distributeur 12. Avantageusement, la tige 25 présente, au voisinage de son extrémité opposée à celle vissée sur la palette, un épaulement annulaire 25A qui est situé alors au niveau de la chambre 16 dudit passage 26. L'épaulement 25A est ainsi susceptible de coopérer, selon le coulissement de la tige commandée par l'électro-aimant, soit avec une portée amont 27 dudit passage, par laquelle débouche le premier conduit 15, soit avec une portée aval 28 dudit passage communiquant avec l'orifice de sortie 20 du corps. La chambre 16 du distributeur est alors délimitée par les portées amont et aval 27,28 du passage, tandis que le deuxième conduit 18 débouche latéralement dans celle-ci en étant en communication soit avec le premier conduit 15, soit avec l'orifice de sortie 20.More particularly, the distributor 12 consists of a controllable electromagnet 22A, connected by a link 22A1 to a power supply (not shown), and of a displaceable element 22B extending the electromagnet axially. This the latter is housed in a casing 23 which is connected, by screwing, to said body 11. The movable element 22B is constituted, in known manner, by a pallet 24, turned towards the electromagnet and housed in the bottom of the casing , and by a rod 25 integral with the pallet 24 and passing through the bottom of the casing to open coaxially in a passage 26 which is provided in said body 11 and in which the chamber 16 of the distributor 12 is formed. Advantageously, the rod 25 has, in the vicinity of its end opposite to that screwed onto the pallet, an annular shoulder 25A which is then located at the level of the chamber 16 of said passage 26. The shoulder 25A is thus capable of cooperating, depending on the sliding of the rod controlled by the electromagnet, either with an upstream surface 27 of said passage, through which the first conduit 15 opens, or with a downstream surface 28 of said passage communicating with the outlet orifice 20 of the body. The chamber 16 of the distributor is then delimited by the upstream and downstream ranges 27, 28 of the passage, while the second conduit 18 opens laterally into the latter while being in communication either with the first conduit 15 or with the outlet orifice 20.

Par ailleurs, on remarque plus particulièrement sur l'agrandissement de la figure 2A, que le diamètre Dt de la tige 25 est inférieur, légèrement, aux diamètres internes identiques d des portées amont 27 et aval 28 du passage, et que le diamètre D dudit épaulement 25A est supérieur, mais légèrement, aux diamètres internes identiques d des portées amont 27 et aval 28 du passage 26, lesquelles sont définies, par exemple, par des bagues 29,30 engagées fixement dans ledit passage. La tige 25 traverse ainsi les bagues 29,30 et l'épaulement 25A se trouve situé entre celles-ci. De plus, pour assurer un contact efficace entre l'épaulement 25A et les portées 27,28 desdites bagues, des surfaces coniques 25B et 25C terminent les deux côtés de l'épaulement, de sorte qu'une étanchéité optimale est obtenue lorsque l'une ou l'autre des surfaces coniques 25B et 25C est en appui, par le coulissement de la tige, contre la portée correspondante. A ce propos, on a représenté en c sur les figures, la course de déplacement de l'élément coulissant 25, et donc de l'épaulement de la tige entre les bagues, selon que l'électro-aimant est excité ou non.Furthermore, it can be noted more particularly on the enlargement of FIG. 2A, that the diameter Dt of the rod 25 is slightly smaller than the identical internal diameters d of the upstream 27 and downstream 28 bearings of the passage, and that the diameter D of said shoulder 25A is greater, but slightly, than the identical internal diameters d of the upstream 27 and downstream 28 bearings of the passage 26, which are defined, for example, by rings 29, 30 fixedly engaged in said passage. The rod 25 thus passes through the rings 29.30 and the shoulder 25A is located between them. In addition, to ensure effective contact between the shoulder 25A and the bearing surfaces 27, 28 of said rings, conical surfaces 25B and 25C terminate the two sides of the shoulder, so that optimum sealing is obtained when one or the other of the conical surfaces 25B and 25C is in abutment, by the sliding of the rod, against the corresponding bearing. In this regard, there is shown at c in the figures, the displacement stroke of the sliding element 25, and therefore of the shoulder of the rod between the rings, depending on whether the electromagnet is excited or not.

En outre, dans cet exemple de réalisation, l'orifice de sortie 20 est coaxial au passage 26 du distributeur et il est défini avantageusement par la bague annulaire aval 30. L'orifice de sortie 20 s'évase de plus vers l'extérieur. Aussi, la tige 25 se termine par un embout cylindrique 25D prolongeant l'épaulement 25A en ayant un diamètre proche, mais inférieur, à ce dernier. Cet embout 25D s'engage dans l'orifice de sortie 20 du corps, défini par la bague aval 30.Furthermore, in this exemplary embodiment, the outlet orifice 20 is coaxial with the passage 26 of the dispenser and it is advantageously defined by the downstream annular ring 30. The outlet orifice 20 widens further towards the outside. Also, the rod 25 ends in a cylindrical endpiece 25D extending the shoulder 25A by having a diameter close to, but less than, the latter. This nozzle 25D engages in the outlet orifice 20 of the body, defined by the downstream ring 30.

Quant au vérin d'actionnement 14, il comprend un piston 31 susceptible de coulisser avec étanchéité dans les chambres 19A et 19B formées par un passage 19 ménagé dans le corps. Plus particulièrement, le piston 31 se compose d'une tête 31A séparant, de façon étanche, les deux chambres 19A et 19B et d'une tige 31B prolongeant la tête du côté de la seconde chambre 19B et faisant saillie extérieurement par rapport au corps 11, pour être associée à l'organe à commander par des moyens de liaison 13, comme on le verra ultérieurement. On constate néanmoins que la tige 31B et, donc, l'organe à commander sont extérieurs au jet gazeux et ne sont pas, par conséquent, au contact de celui-ci. Des joints d'étanchéité 32 sont prévus d'une part autour de la tête 31A du piston et, d'autre part, autour de la tige 31B et ils sont réalisés, en raison des températures et pressions en présence, avec une matière résistante à base de graphite. Par ailleurs, on remarque sur les figures 2 et 3 que la section transversale S de la première chambre 19A en communication avec le deuxième conduit 18 est optimale, puisqu'elle correspond à la surface transversale de la tête 31A du piston, et supérieure à la section transversale s de la seconde chambre 19B en communication avec le troisième conduit 21, puisqu'elle correspond à la différence entre la section transversale de la tête 31A et la section transversale de la tige 31B.As for the actuating cylinder 14, it comprises a piston 31 capable of sliding with sealing in the chambers 19A and 19B formed by a passage 19 formed in the body. More particularly, the piston 31 consists of a head 31A sealingly separating the two chambers 19A and 19B and a rod 31B extending the head from the side of the second chamber 19B and projecting outwardly relative to the body 11 , to be associated with the member to be controlled by connecting means 13, as will be seen later. However, it can be seen that the rod 31B and, therefore, the member to be controlled are external to the gas jet and are not, therefore, in contact with the latter. Seals 32 are provided on the one hand around the head 31A of the piston and, on the other hand, around the rod 31B and they are produced, due to the temperatures and pressures present, with a material resistant to graphite base. Furthermore, it can be seen in FIGS. 2 and 3 that the cross section S of the first chamber 19A in communication with the second conduit 18 is optimal, since it corresponds to the transverse surface of the head 31A of the piston, and greater than the cross section s of the second chamber 19B in communication with the third conduit 21, since it corresponds to the difference between the cross section of the head 31A and the section transverse of the rod 31B.

La représentation schématique du dispositif d'actionnement 1, illustrée sur les figures 2 et 3, permet avantageusement de visualiser sur un même plan de coupe le distributeur électromagnétique 12, le vérin 14 et les différents conduits et passages prévus dans le corps 11. Cependant, dans l'exemple d'application précité, le mode de réalisation du dispositif 1 s'avère tout autre, comme on peut le voir sur les figures 4 et 5 montrant le contour extérieur du dispositif d'actionnement 1, dont on reconnaît le distributeur 12 et le vérin 14 agencés dans un même corps unique 11, lequel est associé à l'une des tuyères latérales 7 du bloc de pilotage en force 6 du missile 2. Bien évidemment, les références numériques attribuées aux différentes pièces du dispositif décrit sur les figures 2 et 3 ont été conservées pour le dispositif décrit sur les figures 6 à 10. Ainsi, on retrouve par exemple, en regard de la figure 6, le piston 31 du vérin 14 susceptible de coulisser dans le passage 19 du corps, en regard de la figure 7, le troisième conduit 21 reliant la seconde chambre 19B du vérin audit orifice d'entrée 17 du jet gazeux, en regard de la figure 8, le distributeur 12 en coupe et le premier conduit 15 reliant la chambre 16 à l'orifice d'entrée 17, en regard de la figure 9, la tuyère latérale 7 équipée de l'organe 10 à déplacer par l'intermédiaire du vérin 14, et en regard de la figure 10, le deuxième conduit 18 mettant en communication la chambre 16 du distributeur avec la première chambre 19A du vérin.The schematic representation of the actuating device 1, illustrated in FIGS. 2 and 3, advantageously makes it possible to view on the same section plane the electromagnetic distributor 12, the jack 14 and the various conduits and passages provided in the body 11. However, in the aforementioned application example, the embodiment of the device 1 turns out to be quite different, as can be seen in FIGS. 4 and 5 showing the external contour of the actuating device 1, the distributor 12 of which is recognized and the jack 14 arranged in the same single body 11, which is associated with one of the side nozzles 7 of the force control block 6 of the missile 2. Obviously, the numerical references assigned to the different parts of the device described in the figures 2 and 3 have been kept for the device described in FIGS. 6 to 10. Thus, for example, with regard to FIG. 6, we find the piston 31 of the jack 14 capable of co smooth in the passage 19 of the body, opposite FIG. 7, the third conduit 21 connecting the second chamber 19B of the jack to said inlet orifice 17 of the gas jet, opposite FIG. 8, the distributor 12 in section and the first conduit 15 connecting the chamber 16 to the inlet orifice 17, opposite FIG. 9, the lateral nozzle 7 fitted with the member 10 to be moved via the jack 14, and opposite FIG. 10 , the second conduit 18 connecting the chamber 16 of the distributor with the first chamber 19A of the jack.

Par ailleurs, cette réalisation concrète du dispositif d'actionnement 1 montre l'organe à déplacer 10 par l'intermédiaire du vérin, ainsi que d'autres détails spécifiques du dispositif qui seront décrits ci-après.Furthermore, this concrete embodiment of the actuating device 1 shows the member to be moved 10 by through the actuator, as well as other specific details of the device which will be described below.

Plus particulièrement, l'organe 10 permettant de dévier, si nécessaire, le jet gazeux issu du générateur et traversant la tuyère latérale 7 est défini, dans cet exemple, par une jupe 10A sensiblement de forme tronconique, qui entoure l'extrémité aval 7A de la tuyère pour se prolonger au-delà de celle-ci, son extrémité amont 7B communiquant avec le conduit 9. Comme le montre la figure 9, la jupe tronconique 10A est montée pivotante par rapport à la tuyère 7 autour d'un axe 10B orthogonal à l'axe longitudinal L-L de ladite tuyère. La jupe est, en outre, pourvue d'une patte en forme de chape 10C qui chevauche le bout de la tige 31B dudit piston pour y être associée par les moyens de liaison 13, définis par un axe, parallèle à l'axe de pivotement 10B.More particularly, the member 10 making it possible to deflect, if necessary, the gas jet coming from the generator and passing through the lateral nozzle 7 is defined, in this example, by a skirt 10A substantially of frustoconical shape, which surrounds the downstream end 7A of the nozzle to extend beyond the latter, its upstream end 7B communicating with the conduit 9. As shown in FIG. 9, the frustoconical skirt 10A is pivotally mounted relative to the nozzle 7 about an orthogonal axis 10B to the longitudinal axis LL of said nozzle. The skirt is, moreover, provided with a yoke in the form of a yoke 10C which straddles the end of the rod 31B of said piston so as to be associated with it by the connecting means 13, defined by an axis, parallel to the pivot axis 10B.

On remarque également sur les figures 8 et 10 que l'orifice d'entrée 17 du jet gazeux est muni d'une virole cylindrique 34 logée fixement dans le corps et pourvue d'un canal axial 34A en liaison avec le conduit 9 et débouchant latéralement dans des gorges annulaires 34B reliées entre elles pour communiquer ensuite avec le premier conduit 15 d'alimentation du distributeur 12 et le troisième conduit 21 d'alimentation de la seconde chambre 19B. L'agencement de cette virole a pour but de freiner et de refroidir le jet gazeux engendré par les générateurs en direction du bloc de pilotage en force 6 constitué des dispositifs d'actionnement 1 et des tuyères latérales 7.It is also noted in FIGS. 8 and 10 that the inlet orifice 17 of the gas jet is provided with a cylindrical ferrule 34 fixedly housed in the body and provided with an axial channel 34A in connection with the conduit 9 and opening out laterally in annular grooves 34B interconnected to then communicate with the first supply duct 15 of the distributor 12 and the third supply duct 21 of the second chamber 19B. The purpose of the arrangement of this ferrule is to brake and cool the gas jet generated by the generators in the direction of the force control block 6 consisting of the actuating devices 1 and the side nozzles 7.

Le fonctionnement du dispositif d'actionnement 1 selon l'invention se déroule de la façon suivante. Tout d'abord, on suppose que chaque dispositif 1 se trouve initialement dans la configuration inactive représentée sur les figures 2 et 4 à 10, pour laquelle la trajectoire du missile 2 n'est pas modifiée.The operation of the actuating device 1 according to the invention takes place as follows. First, it is assumed that each device 1 is initially in the inactive configuration shown in Figures 2 and 4 to 10, for which the trajectory of the missile 2 is not changed.

Dans ce cas, l'électro-aimant 22A est alimenté, par la liaison 22A1, et attire l'élément mobile 22B vers lui. De la sorte, la section conique 25B de l'épaulement 25A, prévu sur la tige 25 solidaire de la palette 24, s'applique contre la portée amont 27 de la bague 29, obturant le passage 26 et, en particulier, la communication entre le premier conduit 15 et la chambre 16 du distributeur. Par conséquent, l'écoulement du jet gazeux, traversant le canal 34A et les gorges 34B de la virole 34, puis le premier conduit 15 pour déboucher dans le passage 26, est stoppé au niveau du contact épaulement 25A - bague 29. En revanche, puisque l'épaulement obture la portée amont 27, la chambre 16 du distributeur met en communication la première chambre 19A du vérin avec l'extérieur, respectivement par le deuxième conduit 18 et l'orifice de sortie 20 du corps. Simultanément à l'alimentation du premier conduit 15, le jet gazeux traverse le troisième conduit 21, de sorte que le piston 31, sous l'action de la pression s'exerçant sur sa surface s régnant alors dans la seconde chambre 19B, est repoussé jusqu'à occuper une position rentrée par la vidange de la première chambre 19A en communication avec l'extérieur. Par conséquent, à la position rentrée du vérin 14, obtenue lorsque le distributeur 12 est alimenté, correspond une première position, neutre, de la jupe 10A, dans le prolongement axial de la tuyère latérale 7, n'influençant pas la trajectoire du missile. On remarque ainsi que la jupe orientable 10A, les moyens d'articulation 13 et la partie de tige 31B sortant dudit corps vers le milieu extérieur ne sont pas affectés par le jet gazeux émis. De même, la chambre 16 du distributeur et la première chambre 19A du vérin sont isolées du jet gazeux chaud, évitant les risques de déformation ou autre, tant que le distributeur électromagnétique 12 obture le premier conduit d'alimentation 15. Par ailleurs, la faible différence entre le diamètre Dt de la tige 25A et le diamètre d de la portée amont 27 ne nécessite qu'un effort minimal de l'électro-aimant, de sorte qu'il peut avoir une dimension réduite et, donc, un faible encombrement.In this case, the electromagnet 22A is supplied, by the link 22A1, and attracts the movable element 22B towards it. In this way, the conical section 25B of the shoulder 25A, provided on the rod 25 integral with the pallet 24, is applied against the upstream bearing 27 of the ring 29, closing the passage 26 and, in particular, the communication between the first conduit 15 and the chamber 16 of the distributor. Consequently, the flow of the gas jet, passing through the channel 34A and the grooves 34B of the shell 34, then the first conduit 15 to open into the passage 26, is stopped at the level of the shoulder contact 25A - ring 29. On the other hand, since the shoulder closes the upstream bearing 27, the chamber 16 of the distributor places the first chamber 19A of the jack in communication with the outside, respectively by the second conduit 18 and the outlet orifice 20 of the body. Simultaneously with the supply of the first conduit 15, the gas jet passes through the third conduit 21, so that the piston 31, under the action of the pressure exerted on its surface s then prevailing in the second chamber 19B, is pushed back until it occupies a retracted position by emptying the first chamber 19A in communication with the outside. Consequently, in the retracted position of the jack 14, obtained when the distributor 12 is supplied, corresponds a first, neutral position, of the skirt 10A, in the axial extension of the lateral nozzle 7, not influencing the trajectory of the missile. It can thus be seen that the orientable skirt 10A, the articulation means 13 and the rod part 31B leaving said body towards the outside environment are not affected by the gas jet emitted. Similarly, the chamber 16 of the distributor and the first chamber 19A of the jack are isolated from the hot gas jet, avoiding the risks of deformation or the like, as long as the electromagnetic distributor 12 closes the first supply conduit 15. Furthermore, the low difference between the diameter Dt of the rod 25A and the diameter d of the upstream seat 27 requires only an effort minimum of the electromagnet, so that it can have a reduced size and, therefore, a small footprint.

Lorsque le vol du missile 2 doit être brusquement modifié, il est alors nécessaire de faire fonctionner au moins l'une des tuyères latérales 7 du bloc de pilotage 6 pour obtenir le changement d'orientation souhaité et, donc, de trajectoire.When the flight of the missile 2 must be suddenly modified, it is then necessary to operate at least one of the side nozzles 7 of the control unit 6 to obtain the desired change in orientation and, therefore, in trajectory.

Pour cela, l'électro-aimant 22A du distributeur 11 n'est plus alimenté par la liaison 22A1. Cette rupture d'alimentation provoque instantanément un mouvement d'éloignement naturel de l'élément déplaçable 22B qui n'est plus attiré par l'électro-aimant, grâce au jet gazeux sortant du premier conduit 15 vers le passage 26. De la sorte, la tige 25 est repoussée jusqu'à ce que la surface conique 25C de l'épaulement 25A vienne s'appliquer contre la portée aval 28 de la bague 30. Le déplacement de la tige 25 sur la course c établit alors la communication fluidique entre le premier conduit 15 et le deuxième conduit 18 par la chambre 16 du distributeur, puisque la surface conique 25B de l'épaulement s'est éloignée, de la course c, de la portée amont 27 de la bague 29. Simultanément, le contact entre la surface conique 29C de l'épaulement et la portée aval 28 de la bague obture l'orifice de sortie ou d'échappement 20 du distributeur, et coupe ainsi la communication entre le deuxième conduit 18 et ce dernier.For this, the electromagnet 22A of the distributor 11 is no longer supplied by the link 22A1. This supply break instantly causes a natural movement away from the movable element 22B which is no longer attracted by the electromagnet, thanks to the gas jet leaving the first conduit 15 towards the passage 26. In this way, the rod 25 is pushed back until the conical surface 25C of the shoulder 25A comes to bear against the downstream bearing 28 of the ring 30. The displacement of the rod 25 on the stroke c then establishes the fluid communication between the first conduit 15 and the second conduit 18 through the chamber 16 of the distributor, since the conical surface 25B of the shoulder has moved away, from the stroke c , from the upstream surface 27 of the ring 29. Simultaneously, the contact between the conical surface 29C of the shoulder and the downstream surface 28 of the ring closes the outlet or exhaust port 20 of the distributor, and thus cuts the communication between the second conduit 18 and the latter.

A ce moment, le jet gazeux, après avoir traversé le premier conduit 15, la chambre 16 et le deuxième conduit 18, pénètre dans la première chambre 19A du vérin 14, de sorte que la pression du jet gazeux s'établit dans les deux chambres 19A et 19B par les conduits respectifs 18 et 21. Or, comme la section S du piston 31, définie par sa tête 31A dans la première chambre 19A, est plus grande que celle s dans la seconde chambre 19B, le piston 31 coulisse dans le passage 19 vers sa position sortie, de sorte que sa tige 31B provoque, par l'intermédiaire de l'articulation 13, le pivotement, dans ce cas, de la jupe orientable 10A de la tuyère latérale 7 autour de l'axe 10B.At this time, the gas jet, after having passed through the first conduit 15, the chamber 16 and the second conduit 18, enters the first chamber 19A of the jack 14, so that the pressure of the gas jet is established in the two chambers 19A and 19B by the respective conduits 18 and 21. However, as the section s of the piston 31, defined by its head 31A in the first chamber 19A, is greater than s in the second chamber 19B, the piston 31 slides in the passage 19 towards its extended position, so that its rod 31B causes, by means of the articulation 13, the pivoting, in this case, of the orientable skirt 10A of the lateral nozzle 7 around the axis 10B.

Le dispositif 1 occupe alors sa configuration active représentée sur les figures 3, 11 et 12, pour laquelle l'organe à commander, tel que la jupe 10A, est dans une seconde position, déviée d'un angle α par rapport à l'axe L-L de la tuyère latérale 7, comme le montrent les figures 1 et 13, ce qui permet de modifier ainsi la trajectoire du missile 1.The device 1 then occupies its active configuration shown in FIGS. 3, 11 and 12, for which the member to be controlled, such as the skirt 10A, is in a second position, deviated by an angle α relative to the axis LL of the lateral nozzle 7, as shown in FIGS. 1 and 13, which thus makes it possible to modify the trajectory of missile 1.

On remarque ainsi que, grâce au dispositif d'actionnement de l'invention, l'écoulement du jet gazeux chaud dans le dispositif ne s'effectue que de façon séquentielle, lors des phases de vol du missile requérant des modifications brusques de sa trajectoire, et que l'effort de commande de l'élément coulissant par l'électro-aimant est minime du fait des diamètres proches entre la tige et les portées et n'est nécessaire que dans un seul sens de déplacement, vers la portée aval du distributeur. Par ailleurs, la réalisation d'un corps unique, regroupant le vérin et le distributeur, engendre un gain d'encombrement important. Bien évidemment, il va de soi que l'organe à commander pourrait être différent, et se présenter, par exemple, sous la forme d'un autre type de tuyère, d'un aileron, d'une gouverne et analogues.It is thus noted that, thanks to the actuating device of the invention, the flow of the hot gas jet in the device is carried out only sequentially, during the flight phases of the missile requiring abrupt modifications of its trajectory, and that the control force of the sliding element by the electromagnet is minimal due to the close diameters between the rod and the bearings and is only necessary in one direction of movement, towards the downstream range of the distributor . Furthermore, the production of a single body, bringing together the actuator and the distributor, generates a significant gain in bulk. Obviously, it goes without saying that the member to be controlled could be different, and be, for example, in the form of another type of nozzle, a fin, a control surface and the like.

Claims (12)

Dispositif pour actionner un organe mécanique, à partir d'une source fluidique telle que notamment un générateur de gaz d'un missile, du type à distributeur commandable relié à ladite source fluidique,
caractérisé en ce qu'il comprend : - un corps (11) dans lequel est agencé ledit distributeur (12) et qui est raccordé, par un orifice d'entrée (17), à ladite source fluidique ; - un premier conduit (15) susceptible de relier ledit orifice d'entrée à une chambre (16) dudit distributeur commandable ; - un vérin (14) agencé dans ledit corps et comportant une première et une seconde chambres coaxiales (19A, 19B) séparées l'une de l'autre par une tête de piston (31) coulissant, dont la tige (31B) fait saillie extérieurement par rapport audit corps pour être associée, par des moyens de liaison, audit organe mécanique ; - un deuxième conduit (18) reliant la chambre (16) dudit distributeur à la première chambre (19A) dudit vérin, ledit deuxième conduit pouvant être mis en communication, par l'intermédiaire de ladite chambre du distributeur, soit avec ledit premier conduit (15), soit avec un orifice de sortie (20) extérieur du corps, selon que le distributeur est actif ou inactif ; et - un troisième conduit (21) reliant ladite seconde chambre (19B) du vérin audit orifice d'entrée (17) dudit corps. Device for actuating a mechanical member, from a fluid source such as in particular a gas generator of a missile, of the type with controllable distributor connected to said fluid source,
characterized in that it comprises: - a body (11) in which said distributor (12) is arranged and which is connected, by an inlet orifice (17), to said fluid source; - a first conduit (15) capable of connecting said inlet orifice to a chamber (16) of said controllable distributor; - a jack (14) arranged in said body and comprising first and second coaxial chambers (19A, 19B) separated from each other by a sliding piston head (31), the rod (31B) of which projects externally with respect to said body to be associated, by connecting means, with said mechanical member; - a second conduit (18) connecting the chamber (16) of said distributor to the first chamber (19A) of said cylinder, said second conduit being able to be placed in communication, via said distributor chamber, either with said first conduit ( 15), either with an outlet orifice (20) outside the body, depending on whether the distributor is active or inactive; and - A third conduit (21) connecting said second chamber (19B) of the jack to said inlet orifice (17) of said body. Dispositif selon la revendication 1,
caractérisé en ce que la section transversale de la première chambre (19A) dudit vérin (14) est supérieure à la section transversale annulaire de la seconde chambre (19B), définie par la différence de surfaces entre la tête (31A) et la tige (31B) dudit piston.Device according to claim 1,
characterized in that the cross section of the first chamber (19A) of said cylinder (14) is greater than the annular cross section of the second chamber (19B), defined by the difference in surfaces between the head (31A) and the rod ( 31B) of said piston. Dispositif selon l'une des revendications 1 ou 2,
caractérisé en ce que des joints d'étanchéité (32) sont prévus entre ledit piston et lesdites chambres et sont réalisés en une matière résistant aux températures et aux pressions élevées, à base de graphite notamment.Device according to one of claims 1 or 2,
characterized in that seals (32) are provided between said piston and said chambers and are made of a material resistant to high temperatures and pressures, in particular based on graphite. Dispositif selon l'une des revendications précédentes 1 à 3,
caractérisé en ce que lesdits moyens de liaison (13) entre ledit piston (31) et ledit organe (10) sont constitués par au moins une articulation à axe, rotule ou analogue, susceptible d'entraîner le déplacement dudit organe d'une première position vers une seconde position, et réciproquement, par suite du coulissement dudit piston.Device according to one of the preceding claims 1 to 3,
characterized in that said connecting means (13) between said piston (31) and said member (10) consist of at least one articulation with an axis, ball joint or the like, capable of causing said member to move from a first position towards a second position, and vice versa, as a result of the sliding of said piston. Dispositif selon l'une quelconque des revendications précédentes 1 à 4,
caractérisé en ce que ledit distributeur (12) comprend un électro-aimant commandable (22A), relié audit corps (11), et un élément axialement déplaçable (22B) comportant une tige (25) qui traverse un passage axial (26), ménagé dans ledit corps et comprenant ladite chambre (16), ladite tige présentant un épaulement (25A) situé au niveau de ladite chambre (16) dudit passage axial et susceptible de coopérer soit avec une portée amont (27) dudit passage par laquelle débouche ledit premier conduit (15), lorsque ledit électroaimant est excité, soit avec une portée aval (28) dudit passage, débouchant vers ledit orifice de sortie (20) du corps lorsque ledit électro-aimant est désexcité.Device according to any one of the preceding claims 1 to 4,
characterized in that said distributor (12) comprises a controllable electromagnet (22A), connected to said body (11), and an axially displaceable element (22B) comprising a rod (25) which passes through an axial passage (26), arranged in said body and comprising said chamber (16), said rod having a shoulder (25A) situated at the level of said chamber (16) of said axial passage and capable of cooperating either with an upstream bearing surface (27) of said passage through which opens said first conduit (15), when said electromagnet is excited, or with a downstream bearing surface (28) of said passage, opening towards said outlet orifice (20) of the body when said electromagnet is de-energized. Dispositif selon la revendication 5,
caractérisé en ce que le diamètre dudit épaulement (25A) est légèrement supérieur aux diamètres internes des portées amont (27) et aval (28) dudit passage, tandis que le diamètre de ladite tige (25) est légèrement inférieur à ceux desdites portées.Device according to claim 5,
characterized in that the diameter of said shoulder (25A) is slightly greater than the internal diameters of the upstream (27) and downstream (28) spans of said passage, while the diameter of said rod (25) is slightly less than those of said spans. Dispositif selon l'une des revendications 5 ou 6,
caractérisé en ce que ledit épaulement (25A) présente deux surfaces coniques (25B,25C) aptes à coopérer respectivement avec les portées amont (27) et aval (28) dudit passage axial.Device according to one of claims 5 or 6,
characterized in that said shoulder (25A) has two conical surfaces (25B, 25C) capable of cooperating respectively with the upstream (27) and downstream (28) bearing surfaces of said axial passage. Dispositif selon l'une des revendications précédentes 5 à 7,
caractérisé en ce que ledit orifice de sortie (20) dudit corps est coaxial audit passage (26) et prolonge la portée aval (28) dudit passage, et en ce que la tige (25) se termine, à son extrémité opposée à celle tournée vers l'électro-aimant, par un embout cylindrique (25D) dont le diamètre est proche du diamètre de ladite tige (25) et qui est situé dans ledit orifice de sortie (20).Device according to one of the preceding claims 5 to 7,
characterized in that said outlet orifice (20) of said body is coaxial with said passage (26) and extends the downstream reach (28) of said passage, and in that the rod (25) ends, at its end opposite to that turned to the electromagnet, by a cylindrical tip (25D) whose diameter is close to the diameter of said rod (25) and which is located in said outlet orifice (20). Dispositif selon la revendication 8,
caractérisé en ce que ledit orifice de sortie (20) du corps s'évase vers l'extérieur.Device according to claim 8,
characterized in that said body outlet (20) flares outward. Dispositif selon l'une quelconque des revendications précédentes 1 à 9,
caractérisé en ce que lesdites portées amont (27) et aval (28) sont définies par des bagues (29,30) fixées dans ledit passage du corps et traversées par ladite tige coulissante (25) dont l'épaulement (25A) est prévu entre lesdites bagues.Device according to any one of the preceding claims 1 to 9,
characterized in that said upstream (27) and downstream (28) bearing surfaces are defined by rings (29,30) fixed in said passage of the body and traversed by said sliding rod (25) whose shoulder (25A) is provided between said rings. Dispositif selon l'une quelconque des revendications précédentes 1 à 10,
caractérisé en ce que ledit orifice d'entrée du corps est muni d'une virole (34) fixée audit corps et pourvue d'un canal axial (34A) en liaison avec ladite source fluidique et débouchant latéralement dans des gorges annulaires externes (34B) communiquant entre elles et avec lesdits premier (15) et troisième (21) conduits.Device according to any one of the preceding claims 1 to 10,
characterized in that said body inlet orifice is provided with a ferrule (34) fixed to said body and provided with an axial channel (34A) in connection with said fluid source and opening laterally into external annular grooves (34B) communicating with each other and with said first (15) and third (21) conduits. Missile du type comportant un bloc de pilotage (6) à partir de jets gazeux délivrés par un générateur de gaz et comprenant une pluralité de tuyères latérales ou au moins une tuyère axiale (7) susceptibles d'être traversées par lesdits jets gazeux,
caractérisé en ce qu'un dispositif d'actionnement (1), tel que spécifié sous l'une des revendications précédentes 1 à 11, en communication avec ledit jet gazeux, est associé à au moins une tuyère (7), ledit dispositif d'actionnement étant susceptible, lorsqu'il est actionné, d'orienter un organe mécanique (10) lié à ladite tuyère (7) pour modifier la direction d'écoulement du jet gazeux sortant de ladite tuyère.Missile of the type comprising a pilot block (6) from gas jets delivered by a gas generator and comprising a plurality of lateral nozzles or at least one axial nozzle (7) capable of being traversed by said gas jets,
characterized in that an actuating device (1), as specified under one of the preceding claims 1 to 11, in communication with said gas jet, is associated with at least one nozzle (7), said device actuation being capable, when actuated, of orienting a mechanical member (10) linked to said nozzle (7) to modify the direction of flow of the gaseous jet leaving said nozzle.
EP93402963A 1992-12-22 1993-12-08 Actuator especially for moving thrust nozzles of a missile Expired - Lifetime EP0604263B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9215488 1992-12-22
FR9215488A FR2699610B1 (en) 1992-12-22 1992-12-22 Device for actuating a mechanical member, in particular for the force piloting of a missile, and missile equipped with said device.

Publications (2)

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EP0604263A1 true EP0604263A1 (en) 1994-06-29
EP0604263B1 EP0604263B1 (en) 1997-05-21

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EP (1) EP0604263B1 (en)
DE (1) DE69310884T2 (en)
ES (1) ES2102627T3 (en)
FR (1) FR2699610B1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2730303A1 (en) * 1995-02-03 1996-08-09 Loral Vought Systems Corp METHOD FOR RAPIDLY CHANGING THE DIRECTION OF MOVEMENT OF A VEHICLE, ESPECIALLY OF A MISSILE AND MACHINE FOR ITS IMPLEMENTATION
US6308911B1 (en) 1998-10-30 2001-10-30 Lockheed Martin Corp. Method and apparatus for rapidly turning a vehicle in a fluid medium

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5755401A (en) * 1995-10-31 1998-05-26 Thiokol Corporation Missile diverter integration method and system
US6315239B1 (en) * 1997-09-23 2001-11-13 Versatron, Inc. Variable coupling arrangement for an integrated missile steering system
FR2870932B1 (en) * 2004-05-27 2006-08-11 Mbda France Sa FLYING ENGINE FOR SOIL OBSERVATION
RU2591005C1 (en) * 2015-01-21 2016-07-10 Открытое Акционерное Общество "Государственный Ракетный Центр Имени Академика В.П. Макеева" Steering drive

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3091084A (en) * 1959-05-04 1963-05-28 Pneumo Dynamics Corp Solid propellant control system
US4078495A (en) * 1974-08-15 1978-03-14 The United States Of America As Represented By The Secretary Of The Navy Control after burnout for reaction steered missiles
US5028014A (en) * 1988-11-15 1991-07-02 Anderson Jr Carl W Radial bleed total thrust control apparatus and method for a rocket propelled missile

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2588372B1 (en) * 1985-10-08 1989-07-13 Thomson Brandt Armements PILOTAGE DEVICE FOR A GUIDED PROJECTILE USING SIDE NOZZLES
DE3838100A1 (en) * 1988-11-10 1990-05-17 Messerschmitt Boelkow Blohm FLUID DISTRIBUTOR
FR2659733B1 (en) * 1990-03-14 1994-07-01 Aerospatiale SYSTEM FOR THE PILOTAGE OF A MISSILE USING SIDE NOZZLES.

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3091084A (en) * 1959-05-04 1963-05-28 Pneumo Dynamics Corp Solid propellant control system
US4078495A (en) * 1974-08-15 1978-03-14 The United States Of America As Represented By The Secretary Of The Navy Control after burnout for reaction steered missiles
US5028014A (en) * 1988-11-15 1991-07-02 Anderson Jr Carl W Radial bleed total thrust control apparatus and method for a rocket propelled missile

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2730303A1 (en) * 1995-02-03 1996-08-09 Loral Vought Systems Corp METHOD FOR RAPIDLY CHANGING THE DIRECTION OF MOVEMENT OF A VEHICLE, ESPECIALLY OF A MISSILE AND MACHINE FOR ITS IMPLEMENTATION
FR2779246A1 (en) * 1995-02-03 1999-12-03 Loral Vought Systems Corp METHOD AND SYSTEM FOR QUICKLY CHANGING THE DIRECTION OF MOVEMENT OF A VEHICLE MOVING IN A FLUID MEDIUM
USRE37331E1 (en) 1995-02-03 2001-08-14 Lockheed Martin Corporation Dual-control scheme for improved missile maneuverability
US6308911B1 (en) 1998-10-30 2001-10-30 Lockheed Martin Corp. Method and apparatus for rapidly turning a vehicle in a fluid medium

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EP0604263B1 (en) 1997-05-21
FR2699610A1 (en) 1994-06-24
DE69310884D1 (en) 1997-06-26
US5405103A (en) 1995-04-11
ES2102627T3 (en) 1997-08-01
FR2699610B1 (en) 1995-02-10
DE69310884T2 (en) 1997-10-02

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