EP0064433B1 - Guided missile - Google Patents

Guided missile Download PDF

Info

Publication number
EP0064433B1
EP0064433B1 EP82400634A EP82400634A EP0064433B1 EP 0064433 B1 EP0064433 B1 EP 0064433B1 EP 82400634 A EP82400634 A EP 82400634A EP 82400634 A EP82400634 A EP 82400634A EP 0064433 B1 EP0064433 B1 EP 0064433B1
Authority
EP
European Patent Office
Prior art keywords
projectile
nozzles
gas
pipes
valve
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP82400634A
Other languages
German (de)
French (fr)
Other versions
EP0064433A1 (en
Inventor
Roger Crepin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Priority to AT82400634T priority Critical patent/ATE18096T1/en
Publication of EP0064433A1 publication Critical patent/EP0064433A1/en
Application granted granted Critical
Publication of EP0064433B1 publication Critical patent/EP0064433B1/en
Expired legal-status Critical Current

Links

Images

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 invention relates to a guided projectile, the flight path of which can be modified by the controlled ejection of lateral gas jets in the flight plans.
  • a guided projectile such as a missile, comprises in particular propulsion means, guidance means intended to measure the deviations from the trajectory relative to the position of the targeted target and piloting means making it possible to reduce these deviations for the purpose minimize its passing distance to the right of the target.
  • Control of the flight path of a guided projectile can be accomplished by the application of a lateral thrust force supplied by jets of material whose flow and direction can be changed.
  • a thrust force can be obtained from numerous energy sources, such as liquid propellants or compressed gases which supply suitable control means.
  • the energy source necessary for piloting in the direction and jointly with maintaining the flight speed is it constituted by a solid propellant whose combustion provides a flow of gas continued.
  • a solid propellant whose combustion provides a flow of gas continued.
  • the projectile comprises a gas generator, of the solid propellant type, which feeds a pair of diametrically opposite fixed nozzles.
  • the invention therefore relates to a projectile guided by lateral gas jets, comprising an energy source constituted by a solid propellant whose combustion provides a gas flow of substantially constant flow to a plurality of equally spaced lateral nozzles, each of these nozzles comprising a valve for regulating the flow of gas passing through, characterized in that it comprises two pairs of diametrically opposite nozzles situated respectively in two mutually orthogonal guide planes, and in which each of the adjustment valves comprises a pivoting pallet, one of which of the faces constitutes a wall of the nozzle, and in that the pallets corresponding to each pair of nozzles are secured and positioned by parallelogram mechanisms whose transverse elements are the driving elements.
  • Another object of the invention is a guided projectile, the two positioning jacks of the valves for adjusting the relative flow rate of the gas jets are mutually nested in their middle part.
  • Another object of the invention is a guided projectile in which the control means are combined with the propulsion means.
  • Another object of the invention is a guided projectile in which the total effective passage section of the nozzles is kept constant while the unitary passage section of the nozzles is modified.
  • Figure 1 relates to the prior art. It represents, in partial view, a projectile equipped with a piloting section using lateral gas jets.
  • This piloting section 1 comprises a pair of diametrically opposite fixed ejection nozzles 2 located in the piloting plane of the projectile. These ejection nozzles are supplied with gas by divergent conduits 3 whose common inlet constitutes the nozzle throat and receives a continuous flow of gas supplied by a primary source of energy.
  • the means for adjusting the relative flow rate of gases passing through the nozzles comprise a single valve positioned by a pneumatic cylinder.
  • the adjustment valve essentially comprises a pivoting vane 5, of triangular shape, articulated around an axis 6 perpendicular to the plane containing the nozzles.
  • This pivoting pallet is partially engaged in the nozzle neck 4 and its lateral faces 7 constitute one of the walls of the divergent conduits, it is provided with a lug 8 which is housed in a notch 9 formed in the piston of the jack 10.
  • the position of the jack is controlled by a servovalve 11 comprising an air inlet 12 for supply and electromagnets excited by electrical signals representative of the control commands.
  • FIG. 2 represents, in a schematic form, the basic concepts of a guided projectile according to the invention.
  • This projectile comprises, in particular, a piloting section proper, in which are arranged two pairs of fixed nozzles T 1 , T 3 and T 2 , T 4 respectively , all identical.
  • the thrust forces F 1 to F 4 supplied by the ejection nozzles converge at the same point P located on the longitudinal axis XX 'of the projectile, this point P being substantially coincident with the center of gravity G of the projectile .
  • Each pair of diametrically opposite nozzles is situated in the corresponding piloting plane, the two piloting planes being advantageously orthogonal.
  • Each of the nozzles is supplied through divergent conduits 20, of rectangular section, by a gas source (not shown) which provides a continuous gas flow resulting from the combustion of a solid propellant placed in a combustion chamber;
  • the gas source can comprise two substantially identical gas generators arranged on either side of the piloting section and operating in parallel, by means of gas conduits arranged parallel to the axis XX , of the projectile and between the nozzles.
  • Each of the four nozzles; and more precisely each of the divergent conduits 20 is provided with a valve for adjusting the flow rate of gas passing through; these valves being essentially constituted by a pivoting pallet 30, one of the lateral faces 31 of which supplies, at least partially, one of the walls of these divergent conduits.
  • the pivot axes 32 of these pallets are located in the same plane perpendicular to the longitudinal axis XX 'of the projectile.
  • the diametrically opposite pallets are physically joined by an articulated mechanism forming a deformable parallelogram whose transverse branch 40 constitutes the driving element; the longitudinal branches 41 constitute the connecting elements, the fourth branch 42, shown in dotted lines and passing through the pivot axes of the pallets, being provided by the structure itself of the projectile.
  • the ejection nozzles are inclined more or less on the longitudinal axis of the projectile, to create a thrust force F whose components provide longitudinal thrust forces F L and transverse F T allowing respectively d '' maintain the flight speed of the projectile and modify its flight direction.
  • the transverse branches 40 of the operating mechanism of the pallets are made concurrent by nesting their middle part.
  • Figures 3a to 3d show an embodiment of the piloting section of a guided projectile according to the invention.
  • the four ejection nozzles are oriented towards the rear of the projectile to provide a longitudinal thrust component and the positioning cylinders of the gas flow adjustment valves are nested in their middle part.
  • FIG. 3a represents a front view of the piloting section; this section comprises two elements: a first element 1a including the four nozzles provided with their respective valves and a second element 1b carrying the positioning cylinders of the valves.
  • FIG. 3a shows the relative positions of the two pairs of nozzles, respectively T I , T 3 and T 2 , T 4 which are arranged at the periphery of the first element 1 a of the piloting section.
  • These nozzles all identical, have a rectangular section and the divergent conduits 20 open onto convergent conduits 21 which constitute the gas flow inlets.
  • the pivot axes 32 of the pivoting pallets are located in the same plane and are parallel to the larger walls of the nozzles.
  • FIG. 3a also shows the gas passage conduits 50 ensuring the connection between the gas generators located on either side of the piloting section.
  • one of the pallets is shown in the open position and the other in the closed position; however, it should be understood that these pallets can occupy all the intermediate symmetrical positions.
  • the jack body has two gas inlets E 1 and E ' ⁇ connected to the outlet of a servovalve not shown. The pneumatic energy necessary for the operation of the cylinders can be borrowed from the gas flow supplied by the gas generators.
  • Figure 3c shows, in a sectional view, the elements that make up the control means according to the second control plane. These elements are essentially identical to those described in the previous figure, only the difference between the embodiment of the piston 40 of the pneumatic cylinder for positioning the corresponding pivoting pallets.
  • This piston 40 is a cylindrical part in the middle part of which is formed an opening 40d allowing the free translational movement of the cylindrical element 40c already described in Figure 3b.
  • the gas inlets E 2 and E ' 2 are connected to a second control solenoid valve, not shown.
  • Figure 3d shows an embodiment of the pallet 30 aimed at reducing its inertia; for this purpose, the non-active parts of the pallet are hollowed out so as to leave only a stiffening “wing” 35 in which the notch 33 is formed.
  • the parts subjected to the action of gases must be made of a refractory material and resistant to erosion, for example, graphite or molybdenum.
  • the invention is not strictly limited to the embodiment described and shown; for example, the notch 33, formed in the pallets 30, can be transferred to the pistons 40 of the pneumatic cylinders and the rods 41 can be integral with the pallets.
  • the pistons 40 can comprise a rack driven by a bidirectional rotary motor of the electric or pneumatic type and means can be provided on these pistons for coupling a position sensor.
  • the profiles of the nozzles, gas conduits and vanes have been given for illustrative purposes only. Finally, it is by no means essential that the center of thrust P of the ejection nozzles be confused with the center of gravity G of the projectile.
  • the invention applies, in particular, to missiles stabilized in roll or in autorotation.

Abstract

A guided projectile comprising an energy source supplying a gas flow which feeds two pairs of exhaust nozzles, each pair of nozzles being disposed in the corresponding steering plane. Each of these nozzles is provided with a valve for regulating the relative flowrates of the throughflowing gases; this valve being formed essentially by a pivoting vane hinged about an axis; these vanes are interlocked in pairs and positioned by means of two independent mechanisms formed by a deformable parallelogram, the element 40 being the drive element. According to the invention, the directions of the thrust forces created by the nozzles converge at a point P situated on the axis of the projectile and this point P may merge with the center of gravity G of the projectile.

Description

L'invention concerne un projectile guidé dont la trajectoire de vol peut ête modifiée par l'éjection contrôlée de jets de gaz latéraux dans les plans de pilotage.The invention relates to a guided projectile, the flight path of which can be modified by the controlled ejection of lateral gas jets in the flight plans.

Un projectile guidé, tel qu'un missile, comprend notamment des moyens de propulsion, des moyens de guidage destinés à mesurer les écarts de trajectoire par rapport à la position de la cible visée et des moyens de pilotage permettant de réduire ces écarts dans le but de minimiser sa distance de passage au droit de la cible. Le contrôle de la trajectoire de vol d'un projectile guidé, ce terme recouvrant notamment les missiles, les roquettes, les engins, etc..., peut être accompli par l'application d'une force de poussée latérale fournie par des jets de matière dont le débit et la direction peuvent être modifiés. Une force de poussée peut être obtenue à partir de nombreuses sources d'énergie, telles que des propergols liquides ou des gaz comprimés qui alimentent des moyens de pilotage adaptés. Tandis que ces moyens de pilotage sont relativement simples et souples du fait qu'ils peuvent être activés ou désactivés de façon intermittente, sans danger pour le projectile, ils présentent, plus ou moins, l'inconvénient d'un poids excessif, une certaine sensibilité à la température et, surtout, d'être difficilement stockables sur de longues périodes de temps. Aussi, dans le projectile guidé de l'invention, la source d'énergie nécessaire au pilotage en direction et conjointement au main- ,tien de la vitesse de vol, est-elle constituée par un propergol solide dont la combustion fournit un flux de gaz continu. Une difficulté inhérente à l'utilisation d'un propergol solide est qu'une fois 'la combustion amorcée, elle doit se maintenir à pression substantiellement constante, ce qui implique un débit gazeux qui varie dans de faibles limites. En effet, un accroissement du débit des gaz conduirait à l'extinction de la combustion et inversement une réduction de ce débit conduirait à une augmentation prohibitive de la pression de combustion avec, pour conséquence, l'explosion de la chambre de combustion. Un autre problème qui se pose, lors de la conception d'un projectile guidé mettant en oeuvre des tuyères d'éjection de gaz, est d'obtenir que les directions des forces de poussées élementaires concourent en un seul point avantageusement situé au voisinage du centre de gravité du projectile.A guided projectile, such as a missile, comprises in particular propulsion means, guidance means intended to measure the deviations from the trajectory relative to the position of the targeted target and piloting means making it possible to reduce these deviations for the purpose minimize its passing distance to the right of the target. Control of the flight path of a guided projectile, this term covering in particular missiles, rockets, missiles, etc., can be accomplished by the application of a lateral thrust force supplied by jets of material whose flow and direction can be changed. A thrust force can be obtained from numerous energy sources, such as liquid propellants or compressed gases which supply suitable control means. While these control means are relatively simple and flexible because they can be activated or deactivated intermittently, without danger to the projectile, they have, more or less, the disadvantage of excessive weight, a certain sensitivity at temperature and, above all, to be difficult to store over long periods of time. Also, in the guided projectile of the invention, the energy source necessary for piloting in the direction and jointly with maintaining the flight speed, is it constituted by a solid propellant whose combustion provides a flow of gas continued. An inherent difficulty in using a solid propellant is that once combustion has started, it must be maintained at substantially constant pressure, which implies a gas flow which varies within low limits. Indeed, an increase in the gas flow would lead to the extinction of combustion and conversely a reduction in this flow would lead to a prohibitive increase in the combustion pressure with, as a consequence, the explosion of the combustion chamber. Another problem which arises, when designing a guided projectile using gas ejection nozzles, is to obtain that the directions of the elementary thrust forces compete at a single point advantageously situated in the vicinity of the center. of projectile gravity.

On connaît déjà, notamment par la demande de brevet français déposée le 8 avril 1977 et publiée sous le numéro 2386802, au nom de la Demanderesse, un projectile guidé dans lequel la trajectoire de vol est modifié par l'éjection de jets de gaz latéraux. Selon un mode de réalisation décrit, correspondant au pilotage dans un plan unique, le projectile comprend un générateur de gaz, du type à propergol solide, qui alimente une paire de tuyères fixes diamétralement opposées. Pour modifier le débit relatif des gaz traversant ces deux tuyères, il est proposé de disposer, à la sortie de la source de gaz et pla!>;;e dans les conduits divergents d'alimentation des deux tuyères, une unique vanne comportant une palette pivotante autour d'un axe, située sur l'axe longitudinal du projectile, perpendiculairement au plan de pilotage contenant les deux tuyères. La configuration des moyens de réglage du débit relatif des flux de gaz traversants, particulièrement adaptés au pilotage dans un seul plan présente de nombreux avantages, notamment le débit du flux de gaz est maintenu dans des limites très étroites, la palette pivotante est équilibrée par les forces de pression des gaz agissant sur ses faces latérales et les moyens de positionnement de la palette sont de réalisation simple.Already known, in particular from the French patent application filed on April 8, 1977 and published under the number 2386802, in the name of the Applicant, a guided projectile in which the flight path is modified by the ejection of lateral gas jets. According to an embodiment described, corresponding to piloting in a single plane, the projectile comprises a gas generator, of the solid propellant type, which feeds a pair of diametrically opposite fixed nozzles. To modify the relative flow rate of gases passing through these two nozzles, it is proposed to have, at the outlet of the gas source and pla!> ;; e in the divergent supply conduits of the two nozzles, a single valve comprising a pallet pivoting about an axis, located on the longitudinal axis of the projectile, perpendicular to the piloting plane containing the two nozzles. The configuration of the means for adjusting the relative flow rate of the through gas flows, which are particularly suitable for piloting in a single plane has many advantages, in particular the flow rate of the gas flow is kept within very narrow limits, the pivoting pallet is balanced by the gas pressure forces acting on its lateral faces and the means for positioning the pallet are simple to produce.

Par le brevet américain No 3 530 886 délivré le 29 septembre 1970, on connait un dispositif de pilotage par jets de gaz comprenant une source de gaz et trois tuyères latérales, chacune de ces tuyères étant munie d'une valve de contrôle du débit du gaz traversant. Ces valves de contrôle sont accouplées mécaniquement afin d'ouvrir ou de fermer sélectivement la communication entre la source de gaz et les tuyères latérales. Ce dispositif de pilotage de l'art antérieur ne permet pas de piloter un projectile suivant deux plans mutuellement orthogonaux.By US Patent No. 3,530,886 issued September 29, 1970, there is known a gas jet control device comprising a gas source and three side nozzles, each of these nozzles being provided with a gas flow control valve crossing. These control valves are mechanically coupled to selectively open or close the communication between the gas source and the side nozzles. This piloting device of the prior art does not make it possible to pilot a projectile in two mutually orthogonal planes.

L'invention concerne donc un projectile guidé par jets de gaz latéraux, comprenant une source d'énergie constituée par un propergol solide dont la combustion fournit un flux de gaz de débit sensiblement constant à une pluralité de tuyères latérales également espacées, chacune de ces tuyères comportant une vanne de réglage du débit de gaz traversant, caractérisé en ce qu'il comprend deux paires de tuyères diamétralement opposées situées respectivement dans deux plans de guidage mutuellement orthogoraux, et dans lesquelles chacune des vannes de réglage comprend une palette pivotante dont l'une des faces constitue une paroi de la tuyère, et en ce que les palettes correspondant à chaque paire de tuyères sont solidarisées et positionnées par des mécanismes à parallélogramme dont les éléments transverses sont les éléments moteurs.The invention therefore relates to a projectile guided by lateral gas jets, comprising an energy source constituted by a solid propellant whose combustion provides a gas flow of substantially constant flow to a plurality of equally spaced lateral nozzles, each of these nozzles comprising a valve for regulating the flow of gas passing through, characterized in that it comprises two pairs of diametrically opposite nozzles situated respectively in two mutually orthogonal guide planes, and in which each of the adjustment valves comprises a pivoting pallet, one of which of the faces constitutes a wall of the nozzle, and in that the pallets corresponding to each pair of nozzles are secured and positioned by parallelogram mechanisms whose transverse elements are the driving elements.

Un autre objet de l'invention est un projectile guidé dont les deux vérins de positionnement des vannes de réglage du débit relatif des jets de gaz sont mutuellement imbriqués dans leur partie médiane.Another object of the invention is a guided projectile, the two positioning jacks of the valves for adjusting the relative flow rate of the gas jets are mutually nested in their middle part.

Un autre objet de l'invention est un projectile guidé dans lequel les moyens de pilotage sont combinés aux moyens de propulsion.Another object of the invention is a guided projectile in which the control means are combined with the propulsion means.

Un autre objet de l'invention est un projectile guidé dans lequel la section de passage effective totale des tuyères est maintenue constante alors que la section de passage unitaire des tuyères est modifiée.Another object of the invention is a guided projectile in which the total effective passage section of the nozzles is kept constant while the unitary passage section of the nozzles is modified.

D'autres caractéristiques et avantages appa- raîtront dans la description détaillée qui va suivre, d'un mode de réalisation d'un projectile guidé selon l'invention, faite en regard des figures annexées; sur ces figures:

  • - la fig. 1 représente, selon l'art antérieur, un projectile guidé équipé d'une section de pilotage par jets de gaz latéraux,
  • - la fig. 2 représente, sous une forme schématique, les concepts de base d'un projectile guidé selon l'invention,
  • - les fig. 3a à 3d représentent un mode de réalisation d'une section de pilotage d'un projectile guidé conforme à l'invention,
  • - la fig. 3a représente, selon une vue frontale, la disposition des principaux éléments qui constituent les moyens de pilotage
  • - la fig. 3b représente, selon une vue en coupe, les détails de réalisation des éléments correspondants à un premier plan de pilotage,
  • - la fig. 3c représente, selon une vue en coupe, les détails de réalisation des éléments correspondant au second plan de pilotage,
  • - la fig. 3d représente, selon une vue en perspective, une variante de réalisation de la palette d'une vanne de réglage du débit de gaz.
Other characteristics and advantages will appear in the detailed description which follows, of an embodiment of a guided projectile according to the invention, made with reference to the appended figures; in these figures:
  • - fig. 1 represents, according to the prior art, a guided projectile equipped with a piloting section by lateral gas jets,
  • - fig. 2 represents, in a schematic form, the basic concepts of a guided projectile according to the invention,
  • - figs. 3a to 3d represent an embodiment of a section for piloting a guided projectile in accordance with the invention,
  • - fig. 3a shows, in a front view, the arrangement of the main elements which constitute the control means
  • - fig. 3b represents, in a sectional view, the details of embodiment of the elements corresponding to a first control plane,
  • - fig. 3c represents, in a sectional view, the details of production of the elements corresponding to the second control plane,
  • - fig. 3d shows, in a perspective view, an alternative embodiment of the pallet of a gas flow control valve.

La figure 1 se rapporte à l'art antérieur. Elle représente, en vue partielle, un projectile équipé d'une section de pilotage mettant en oeuvre des jets de gaz latéraux. Cette section de pilotage 1 comprend une paire de tuyères d'éjection fixes 2 diamétralement opposées et situées dans le plan de pilotage du projectile. Ces tuyères d'éjection sont alimentées en gaz par des conduits divergents 3 dont l'entrée commune constitue le col de tuyère et reçoit un flux de gaz continu fourni par une source primaire d'énergie. Les moyens permettant de régler le débit relatif des gaz traversant les tuyères comprennent une vanne unique positionnée par un vérin pneumatique. La vanne de réglage comprend essentiellement une palette pivotante 5, de forme triangulaire, articulée autour d'un axe 6 perpendiculaire au plan contenant les tuyères. Cette palette pivotante est engagée partiellement dans le col de tuyère 4 et ses faces latérales 7 constituent l'une des parois des conduits divergents, elle est munie d'un ergot 8 qui est logé dans une échancrure 9 ménagée dans le piston du vérin 10. La position du vérin est commandée par une servovalve 11 comportant une entrée d'air 12 d'alimentation et des électroaimants excités par des signaux électriques représentatifs des ordres de pilotage.Figure 1 relates to the prior art. It represents, in partial view, a projectile equipped with a piloting section using lateral gas jets. This piloting section 1 comprises a pair of diametrically opposite fixed ejection nozzles 2 located in the piloting plane of the projectile. These ejection nozzles are supplied with gas by divergent conduits 3 whose common inlet constitutes the nozzle throat and receives a continuous flow of gas supplied by a primary source of energy. The means for adjusting the relative flow rate of gases passing through the nozzles comprise a single valve positioned by a pneumatic cylinder. The adjustment valve essentially comprises a pivoting vane 5, of triangular shape, articulated around an axis 6 perpendicular to the plane containing the nozzles. This pivoting pallet is partially engaged in the nozzle neck 4 and its lateral faces 7 constitute one of the walls of the divergent conduits, it is provided with a lug 8 which is housed in a notch 9 formed in the piston of the jack 10. The position of the jack is controlled by a servovalve 11 comprising an air inlet 12 for supply and electromagnets excited by electrical signals representative of the control commands.

La figure 2 représente, sous une forme schématique, les concepts de base d'un projectile guidé selon l'invention. Ce projectile comprend, notamment, une section de pilotage proprement dite, dans laquelle sont disposées deux paires de tuyères fixes respectivement T1, T3 et T2, T4, toutes identiques. Par construction, les forces de poussée F1 à F4 fournies par les tuyères d'éjection convergent en un même point P situé sur l'axe longitudinal X-X' du projectile, ce point P étant sensiblement confondu avec le centre de gravité G du projectile. Chaque paire de tuyères diamétralement opposées est située dans le plan de pilotage correspondant, les deux plans de pilotage étant avantageusement orthogonaux. Chacune des tuyères est alimentée à travers des conduits divergents 20, de section rectangulaire, par une source de gaz non représentée qui fournit un flux de gaz continu résultant de la combustion d'un propergol solide placé dans une chambre de combustion; selon l'invention, la source de gaz peut comporter deux générateurs de gaz sensiblement identiques disposés de part et d'autre de la section de pilotage et opérant en parallèle, par l'intermédiaire de conduits de gaz disposés parallèlement à l'axe X-X, du projectile et entre les tuyères.FIG. 2 represents, in a schematic form, the basic concepts of a guided projectile according to the invention. This projectile comprises, in particular, a piloting section proper, in which are arranged two pairs of fixed nozzles T 1 , T 3 and T 2 , T 4 respectively , all identical. By construction, the thrust forces F 1 to F 4 supplied by the ejection nozzles converge at the same point P located on the longitudinal axis XX 'of the projectile, this point P being substantially coincident with the center of gravity G of the projectile . Each pair of diametrically opposite nozzles is situated in the corresponding piloting plane, the two piloting planes being advantageously orthogonal. Each of the nozzles is supplied through divergent conduits 20, of rectangular section, by a gas source (not shown) which provides a continuous gas flow resulting from the combustion of a solid propellant placed in a combustion chamber; according to the invention, the gas source can comprise two substantially identical gas generators arranged on either side of the piloting section and operating in parallel, by means of gas conduits arranged parallel to the axis XX , of the projectile and between the nozzles.

Chacune des quatre tuyères; et plus précisément chacun des conduits divergents 20 est muni d'une vanne de réglage du débit de gaz traversant; ces vannes étant essentiellement constituées par une palette pivotante 30 dont l'une des faces latérales 31 fournit, tout au moins partiellement, l'une des parois de ces conduits divergents. Les axes de pivotement 32 de ces palettes sont situés dans un même plan perpendiculaire à l'axe longitudinal X-X' du projectile.Each of the four nozzles; and more precisely each of the divergent conduits 20 is provided with a valve for adjusting the flow rate of gas passing through; these valves being essentially constituted by a pivoting pallet 30, one of the lateral faces 31 of which supplies, at least partially, one of the walls of these divergent conduits. The pivot axes 32 of these pallets are located in the same plane perpendicular to the longitudinal axis XX 'of the projectile.

Les palettes diamétralement opposées sont solidarisées physiquement par un mécanisme articulé formant un parallélogramme déformable dont la branche transverse 40 constitue l'élément moteur; les branches longitudinales 41 constituent les éléments de liaison, la quatrième branche 42, représentée en pointillé et passant par les axes de pivotement des palettes, étant fournie par la structure elle-même du projectile.The diametrically opposite pallets are physically joined by an articulated mechanism forming a deformable parallelogram whose transverse branch 40 constitutes the driving element; the longitudinal branches 41 constitute the connecting elements, the fourth branch 42, shown in dotted lines and passing through the pivot axes of the pallets, being provided by the structure itself of the projectile.

Selon un mode de réalisation préféré, les tuyères d'éjection sont inclinées plus ou moins sur l'axe longitudinal du projectile, pour créer une force de poussée F dont les composantes fournissent des forces de poussée longitudinale FL et transversale FT permettant respectivement d'entretenir la vitesse de vol du projectile et de modifier la direction de vol de celui-ci.According to a preferred embodiment, the ejection nozzles are inclined more or less on the longitudinal axis of the projectile, to create a thrust force F whose components provide longitudinal thrust forces F L and transverse F T allowing respectively d '' maintain the flight speed of the projectile and modify its flight direction.

Selon une variante de réalisation, les branches transverses 40 du mécanisme de fonctionnement des palettes sont rendues concourantes par imbrication de leur partie médiane.According to an alternative embodiment, the transverse branches 40 of the operating mechanism of the pallets are made concurrent by nesting their middle part.

Les figures 3a à 3d représentent un mode de réalisation de la section de pilotage d'un projectile guidé conforme à l'invention. Selon ce mode de réalisation, les quatre tuyères d'éjection sont orientées vers l'arrière du projectile pour fournir une composante de poussée longitudinale et les vérins de positionnement des vannes de réglage des débits de gaz sont imbriqués dans leur partie médiane.Figures 3a to 3d show an embodiment of the piloting section of a guided projectile according to the invention. According to this embodiment, the four ejection nozzles are oriented towards the rear of the projectile to provide a longitudinal thrust component and the positioning cylinders of the gas flow adjustment valves are nested in their middle part.

La figure 3a représente une vue frontale de la section de pilotage; cette section comprend deux éléments: un premier élément 1a incluant les quatre tuyères munies de leurs vannes respectives et un second élément 1b portant les vérins de positionnement des vannes.FIG. 3a represents a front view of the piloting section; this section comprises two elements: a first element 1a including the four nozzles provided with their respective valves and a second element 1b carrying the positioning cylinders of the valves.

Sur cette figure 3a sont indiquées les positions relatives des deux paires de tuyères, respectivement TI, T3 et T2, T4 lesquelles sont disposées à la périphérie du premier élément 1 a de la section de pilotage. Ces tuyères, toutes identiques, on une section rectangulaire et les conduits divergents 20 débouchent sur des conduits convergents 21 qui constituent les entrées du flux de gaz. Les axes de pivotement 32 des palettes pivotantes sont situés dans un même plan et sont parallèles aux parois de plus grande dimension des tuyères. Sur cette figure 3a, on a aussi représenté les conduits 50 de passage de gaz assurant la liaison entre les générateurs de gaz situés de part et d'autre de la section de pilotage.In this figure 3a are indicated the relative positions of the two pairs of nozzles, respectively T I , T 3 and T 2 , T 4 which are arranged at the periphery of the first element 1 a of the piloting section. These nozzles, all identical, have a rectangular section and the divergent conduits 20 open onto convergent conduits 21 which constitute the gas flow inlets. The pivot axes 32 of the pivoting pallets are located in the same plane and are parallel to the larger walls of the nozzles This FIG. 3a also shows the gas passage conduits 50 ensuring the connection between the gas generators located on either side of the piloting section.

La figure 3b représente, selon une vue en coupe, les éléments qui composent les moyens de pilotage selon un premier plan de pilotage. Disposés dans le premier élément 1 a de la section de pilotage 1, on trouve:

  • - les deux tuyères T1 et T3 diamétralement opposées et leurs conduits divergents 20 et 21,
  • - les deux palettes pivotantes 30 articulées sur leur axe de pivotement 32, la face latérale 31 de ces palettes constitue l'une des parois des conduits divergents 20; la position de l'axe de pivotement 32 est telle que la direction de la résultante des forces s'exerçant sur la face latérale 31 passe sensiblement par cet axe de pivotement; les palettes sont munies d'une échancrure 33 destinée au logement d'une tige de liaison 41 avec le vérin de commande correspondant.
Figure 3b shows, in a sectional view, the elements that make up the control means according to a first control plane. Arranged in the first element 1 a of the piloting section 1, there are:
  • - the two diametrically opposite nozzles T 1 and T 3 and their divergent conduits 20 and 21,
  • - the two pivoting pallets 30 articulated on their pivot axis 32, the lateral face 31 of these pallets constitutes one of the walls of the divergent conduits 20; the position of the pivot axis 32 is such that the direction of the resultant of the forces exerted on the lateral face 31 passes substantially through this pivot axis; the pallets are provided with a notch 33 intended for housing a connecting rod 41 with the corresponding control cylinder.

Disposés dans le second élément 1 b de la section de pilotage 1, on trouve:

  • - un vérin fixe à double effet dont le piston 40 est logé dans un corps de vérin 45; ce corps de vérin comporte deux ouvertures 46a et 46b permettant le libre mouvement de translation des tiges de liaison 41 et deux bouchons de fermeture 47a et47b servant conjointement de butée au piston 40; le piston 40 comprend deux éléments cylindriques 40a et 40b solidarisés par un élément cylindrique 40c, de plus faible diamètre.
Arranged in the second element 1 b of the piloting section 1, there are:
  • a fixed double-acting cylinder, the piston 40 of which is housed in a cylinder body 45; this jack body has two openings 46a and 46b allowing the free translational movement of the connecting rods 41 and two closure plugs 47a and47b serving jointly as a stop for the piston 40; the piston 40 comprises two cylindrical elements 40a and 40b secured by a cylindrical element 40c, of smaller diameter.

Sur cette figure 3b, l'une des palettes est représentée en position ouverte et l'autre en position fermée; toutefois, il faut comprendre que ces palettes peuvent occuper toutes les positions symétriques intermédiaires. En outre, le corps de vérin comporte deux entrées de gaz E1 et E'↑ reliées à la sortie d'une servovalve non représentée. L'énergie pneumatique nécessaire au fonctionnement des vérins peut être empruntée au flux de gaz fourni par les générateurs de gaz.In this FIG. 3b, one of the pallets is shown in the open position and the other in the closed position; however, it should be understood that these pallets can occupy all the intermediate symmetrical positions. In addition, the jack body has two gas inlets E 1 and E '↑ connected to the outlet of a servovalve not shown. The pneumatic energy necessary for the operation of the cylinders can be borrowed from the gas flow supplied by the gas generators.

La figure 3c représente, selon une vue en coupe, les éléments qui composent les moyens de pilotage selon le second plan de pilotage. Ces éléments sont essentiellement identiques à ceux décrits à la figure précédente, seul, diffère le mode de réalisation du piston 40 du vérin pneumatique de positionnement des palettes pivotantes correspondantes. Ce piston 40 est une pièce cylindrique dans la partie médiane de laquelle est ménagée une ouverture 40d autorisant le libre mouvement de translation de l'élément cylindrique 40c déjà décrit à la figure 3b. Les entrées de gaz E2 et E'2 sont reliées à une seconde électrovalve de commande non représentée.Figure 3c shows, in a sectional view, the elements that make up the control means according to the second control plane. These elements are essentially identical to those described in the previous figure, only the difference between the embodiment of the piston 40 of the pneumatic cylinder for positioning the corresponding pivoting pallets. This piston 40 is a cylindrical part in the middle part of which is formed an opening 40d allowing the free translational movement of the cylindrical element 40c already described in Figure 3b. The gas inlets E 2 and E ' 2 are connected to a second control solenoid valve, not shown.

La figure 3d représente un mode de réalisation de la palette 30 visant à réduire son inertie; à cet effet, les parties non actives de la palette sont évidées pour ne laisser qu'une «aile» de raidissement 35 dans laquelle est ménagée l'échancrure 33. Les pièces soumises à l'action des gaz doivent être réalisées en un matériau réfractaire et résistant à l'érosion, par exemple, en graphite ou en molybdène.Figure 3d shows an embodiment of the pallet 30 aimed at reducing its inertia; for this purpose, the non-active parts of the pallet are hollowed out so as to leave only a stiffening “wing” 35 in which the notch 33 is formed. The parts subjected to the action of gases must be made of a refractory material and resistant to erosion, for example, graphite or molybdenum.

On voit maintenant plus clairement les avantages et les caractéristiques de l'invention. En plus de la caractéristique selon laquelle les direction des forces de poussée élémentaires crées par les tuyères convergent en un seul point, le projectile peut être piloté indépendamment dans deux plans de pilotage. D'autre part, le mécanisme de réglage des débits de gaz est extrêmement robuste et compact.We now see more clearly the advantages and characteristics of the invention. In addition to the characteristic that the directions of the elementary thrust forces created by the nozzles converge at a single point, the projectile can be piloted independently in two piloting planes. On the other hand, the gas flow rate adjustment mechanism is extremely robust and compact.

L'invention n'est pas strictement limitée au mode de réalisation décrit et représenté; par exemple, l'échancrure 33, ménagée dans les palettes 30, peut être reportée sur les pistons 40 des vérins pneumatiques et les tiges 41 peuvent être solidaires des palettes. Selon une variante de réalisation, les pistons 40 peuvent comporter une crémaillère entraînée par un moteur rotatif bidirectionnel du type électrique ou pneumatique et des moyens peuvent être prévus sur ces pistons pour accoupler un capteur de position. De même, les profils des tuyères, des conduits de gaz et des palettes n'ont été donnés qu'à titre illustratif non limitatif. Enfin, il n'est nullement indispensable que le centre de poussée P des tuyères d'éjection soit confondu avec le centre de gravité G du projectile.The invention is not strictly limited to the embodiment described and shown; for example, the notch 33, formed in the pallets 30, can be transferred to the pistons 40 of the pneumatic cylinders and the rods 41 can be integral with the pallets. According to an alternative embodiment, the pistons 40 can comprise a rack driven by a bidirectional rotary motor of the electric or pneumatic type and means can be provided on these pistons for coupling a position sensor. Likewise, the profiles of the nozzles, gas conduits and vanes have been given for illustrative purposes only. Finally, it is by no means essential that the center of thrust P of the ejection nozzles be confused with the center of gravity G of the projectile.

L'invention s'applique, notamment, aux missiles stabilisés en roulis ou en autorotation.The invention applies, in particular, to missiles stabilized in roll or in autorotation.

Claims (4)

1. Projectile guided by lateral gas jets, comprising an energy source constituted by a solid propergol whose combustion furnishes a gas flow of substantially constant throughput to a plurality of lateral equally spaced pipes, each of said pipes comprising a valve for regulating the throughput of the traversing gases, characterized in that it comprises two pairs of diametrically opposite pipes (Tl, T3 and T2, T4) situated respectively in two mutually orthogonal guide planes, and in which each regulating valve comprises a pivoting flap (30) whose one face (31) forms a wall of the pipe, and that the flaps corresponding to each pair of pipes are connected and positioned by parallelogram mechanisms (40, 41 and 42) whose transverse elements (40, 41) are the drive elements.
2. Projectile according to claim 1, characterized in that the drive elements (40) of the parallelogram mechanisms are situated in the same plane by imbrication of their centre portion.
3. Projectile according to claim 1, characterized in that the drive element (40) of the parallelogram mechanisms is a slide piston received in the body of a pneumatic double-action cylinder (45).
4. Projectile according to claim 3, characterized in that the slide piston of a first parallelogram mechanism comprises two cylindrical portions (40a and 40b) connected by a cylindrical portion (40c) of smaller diameter, and the slide piston of the second parallelogram mechanism comprises a cylindrical portion in the centre portion of which a rectangular opening (40d) is -formed.
EP82400634A 1981-04-21 1982-04-06 Guided missile Expired EP0064433B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT82400634T ATE18096T1 (en) 1981-04-21 1982-04-06 GUIDABLE MISSILE.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8107916A FR2504252B1 (en) 1981-04-21 1981-04-21 PROJECTILE GUIDE
FR8107916 1981-04-21

Publications (2)

Publication Number Publication Date
EP0064433A1 EP0064433A1 (en) 1982-11-10
EP0064433B1 true EP0064433B1 (en) 1986-02-19

Family

ID=9257617

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82400634A Expired EP0064433B1 (en) 1981-04-21 1982-04-06 Guided missile

Country Status (7)

Country Link
US (1) US4441670A (en)
EP (1) EP0064433B1 (en)
JP (1) JPS57181953A (en)
AT (1) ATE18096T1 (en)
CA (1) CA1185479A (en)
DE (1) DE3269123D1 (en)
FR (1) FR2504252B1 (en)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2504252B1 (en) * 1981-04-21 1987-03-06 Thomson Brandt PROJECTILE GUIDE
FR2538098B1 (en) * 1982-12-17 1987-11-20 Thomson Brandt SIDE GAS JET STEERING DEVICE
JPS60501366A (en) * 1983-01-20 1985-08-22 ローラル・エアロスペイス・コーポレイション Ram air combustion steering system for guided missiles
DE3317583C2 (en) * 1983-05-13 1986-01-23 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Device with a nozzle arrangement supplied by a propellant source
DE3340037A1 (en) * 1983-11-05 1985-05-23 Diehl GmbH & Co, 8500 Nürnberg ACTUATING SYSTEM FOR STEERED MISSIONS FLYING WITH SUPERVISOR SPEED
FR2557926B1 (en) * 1984-01-06 1986-04-11 Brandt Armements GAS PROPELLER FOR GUIDED PROJECTILE.
US4889699A (en) * 1987-05-19 1989-12-26 Texaco Inc. Partial oxidation process
FR2620812B1 (en) * 1987-09-18 1992-04-17 Thomson Brandt Armements LATERAL GAS JET SWITCHING DEVICE FOR PILOTAGE OF MACHINERY
FR2659734B1 (en) * 1990-03-14 1992-07-03 Aerospatiale SYSTEM FOR THE PILOTAGE OF A MISSILE USING LATERAL GAS JETS.
FR2659733B1 (en) * 1990-03-14 1994-07-01 Aerospatiale SYSTEM FOR THE PILOTAGE OF A MISSILE USING SIDE NOZZLES.
US6499696B1 (en) * 2001-03-16 2002-12-31 Lockheed Martin Corporation Rocket engine with reduced thrust and stagable venting system
US8319162B2 (en) 2008-12-08 2012-11-27 Raytheon Company Steerable spin-stabilized projectile and method
GB2473187B (en) * 2009-09-02 2016-05-11 Lynley Ashley Adrian Air intake stabilizing system
US8362408B2 (en) * 2009-10-22 2013-01-29 Honeywell International Inc. Steerable projectile charging system
US9279651B1 (en) 2014-09-09 2016-03-08 Marshall Phillip Goldberg Laser-guided projectile system

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE568066C (en) * 1930-08-02 1933-01-13 Elek Sche App M B H Ges Control for missiles and similar projectiles
FR916692A (en) * 1945-10-31 1946-12-12 App Controleurs Method and device for gas combustion by infusion through a refractory mass
US2726510A (en) * 1952-03-26 1955-12-13 Daniel And Florence Guggenhcim Flight-control apparatus involving steering combustion chambers
GB916692A (en) * 1958-06-19 1963-01-23 Snecma Improvements in jet control apparatus
FR1293654A (en) * 1961-04-07 1962-05-18 Snecma Fluid distribution device applicable in particular to the jet steering of vertical take-off airplanes
DE1232030B (en) * 1961-05-18 1967-01-05 Dornier Gmbh Control nozzle head for the jet control of aircraft
US3273825A (en) * 1961-10-30 1966-09-20 Emerson Electric Co Guidance systems
US3245620A (en) * 1961-12-13 1966-04-12 Gen Motors Corp Missile steering control
GB1073075A (en) * 1964-12-30 1967-06-21 Carter Day Company Distributor valve for controlling the distribution of a solids-gas mixture
US3530886A (en) * 1967-12-04 1970-09-29 Sperry Rand Corp Hydraulic control valve
US3986683A (en) * 1974-03-27 1976-10-19 The United States Of America As Represented By The Secretary Of The Air Force Jet tab steerable missile
US3927693A (en) * 1974-10-11 1975-12-23 Minnesota Mining & Mfg High-pressure valve
US4131246A (en) * 1977-02-04 1978-12-26 Textron Inc. Thrust vector control actuation system
FR2386802A1 (en) * 1977-04-08 1978-11-03 Thomson Brandt CONTROL DEVICE FOR PROJECTILE OF THE MISSILE GENUS, AND PROJECTILE EQUIPPED WITH THIS DEVICE
US4375276A (en) * 1980-06-02 1983-03-01 General Electric Company Variable geometry exhaust nozzle
FR2504252B1 (en) * 1981-04-21 1987-03-06 Thomson Brandt PROJECTILE GUIDE

Also Published As

Publication number Publication date
FR2504252A1 (en) 1982-10-22
ATE18096T1 (en) 1986-03-15
FR2504252B1 (en) 1987-03-06
EP0064433A1 (en) 1982-11-10
CA1185479A (en) 1985-04-16
DE3269123D1 (en) 1986-03-27
JPS57181953A (en) 1982-11-09
US4441670A (en) 1984-04-10

Similar Documents

Publication Publication Date Title
EP0064433B1 (en) Guided missile
EP0063979B1 (en) A control mechanism for gas jet steering and a missile equipped with such a mechanism
FR2483523A1 (en) EJECTION TUBE FOR GAS TURBINE ENGINE
EP0646525B1 (en) Bidimensional supersonic and hypersonic air intake with three mobile ramps for the combustion air of an aircraft engine
CH626167A5 (en)
EP0068972A1 (en) Guided missile directional control using gas jets
EP0447284B1 (en) Missile control system by means of lateral gas jets
EP0447283B1 (en) Missile control system by means of lateral nozzles
FR2536720A1 (en) SYSTEM FOR CONTROLLING A MISSILE USING LATERAL GAS JETS AND MISSILE HAVING SUCH A SYSTEM
EP0149947B1 (en) Gas jet propulsion for guided missiles
EP0112755B1 (en) Control device operating by lateral gas jet action
FR2691508A1 (en) Pressurized fluid cylinder and variable section nozzle when applied.
EP0604263B1 (en) Actuator especially for moving thrust nozzles of a missile
EP2573504B1 (en) System for piloting an aircraft using pairs of lateral nozzles
EP0152315A1 (en) Oscillating drive for a radar antenna
FR2933743A1 (en) Liquid or gas bipropellant injecting device for rocket engine, has annular channels oriented in converging manner by forming predefined angles to create liquid bipropellant bodies, where bodies create impact between them
EP0356280B1 (en) Bidimensional and symmetrical supersonic and hypersonic air intake for the combustion air of an aircraft engine
FR2745606A1 (en) EVOLUTIVE GEOMETRY STATOREACTOR FOR AIRCRAFT
EP2479386A1 (en) Device for controlling the passing of a gas jet in a jet nozzle of a flying vehicle, and flying vehicle comprising such devices
EP3368420B1 (en) More compact direct thrust flight control and attitude control system, and craft comprising such a system
EP1255032B1 (en) Air intake and flying vehicle, in particular a missile, with such air intake
FR2515264A1 (en) SUPERSONIC AIR INTAKE HALF-REVOLUTION BODY FOR REACTION PROPELLERS, ESPECIALLY FOR STATUS-ACTUATOR TYPE WITH SOLID PROPERGOLS
FR2784444A1 (en) Missile propulsion hot gas piston valve command having seat section valve sliding and second lower gas pressure closing valve when first gas supply depleted
FR2698920A1 (en) Cylinder system with three stable operating positions.
BE625086A (en)

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Designated state(s): AT BE CH DE GB IT LU NL SE

17P Request for examination filed

Effective date: 19821119

RBV Designated contracting states (corrected)

Designated state(s): AT BE CH DE GB IT LI NL SE

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: THOMSON BRANDT ARMEMENTS

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Designated state(s): AT BE CH DE GB IT LI NL SE

REF Corresponds to:

Ref document number: 18096

Country of ref document: AT

Date of ref document: 19860315

Kind code of ref document: T

ITF It: translation for a ep patent filed

Owner name: JACOBACCI & PERANI S.P.A.

REF Corresponds to:

Ref document number: 3269123

Country of ref document: DE

Date of ref document: 19860327

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 19920313

Year of fee payment: 11

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

Ref country code: NL

Payment date: 19920430

Year of fee payment: 11

Ref country code: AT

Payment date: 19920430

Year of fee payment: 11

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

Ref country code: AT

Effective date: 19930406

ITTA It: last paid annual fee
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Effective date: 19930430

Ref country code: CH

Effective date: 19930430

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

Ref country code: NL

Effective date: 19931101

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee
REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: BE

Payment date: 19940406

Year of fee payment: 13

EAL Se: european patent in force in sweden

Ref document number: 82400634.0

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

Ref country code: BE

Effective date: 19950430

BERE Be: lapsed

Owner name: THOMSON BRANDT ARMEMENTS

Effective date: 19950430

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

Ref country code: SE

Payment date: 19960321

Year of fee payment: 15

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

Ref country code: SE

Effective date: 19970407

EUG Se: european patent has lapsed

Ref document number: 82400634.0

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

Ref country code: DE

Payment date: 20010319

Year of fee payment: 20

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

Ref country code: GB

Payment date: 20010321

Year of fee payment: 20

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

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

Ref country code: GB

Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION

Effective date: 20020405

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Effective date: 20020405