EP0434505B1 - Peripheriemantel für einen rohrabgeschossenen gelenkten Flugkörper - Google Patents

Peripheriemantel für einen rohrabgeschossenen gelenkten Flugkörper Download PDF

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Publication number
EP0434505B1
EP0434505B1 EP90403545A EP90403545A EP0434505B1 EP 0434505 B1 EP0434505 B1 EP 0434505B1 EP 90403545 A EP90403545 A EP 90403545A EP 90403545 A EP90403545 A EP 90403545A EP 0434505 B1 EP0434505 B1 EP 0434505B1
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EP
European Patent Office
Prior art keywords
subassembly
weapon
subassemblies
casing
sub
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP90403545A
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English (en)
French (fr)
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EP0434505A1 (de
Inventor
Philippe Arnaud
Marc Bernard
Hervé Boubault
René Thouron
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
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Publication date
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Publication of EP0434505A1 publication Critical patent/EP0434505A1/de
Application granted granted Critical
Publication of EP0434505B1 publication Critical patent/EP0434505B1/de
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
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile

Definitions

  • the invention relates to a guided munition, fired from a launching system by cannon effect. It relates more particularly to the external structure of a munition, that is to say the peripheral envelope allowing cohesion of the different sub-assemblies constituting the guided munition.
  • the object of the invention is to provide a guided munition structure fired by a cannon effect to ensure the tightness of the sub-assemblies placed inside the munition, protection of the sensitive parts against external aggressions, a maximum range, a locking and unlocking of deployable bearing surface and rigidity of the entire munition.
  • a French patent FR-A-1,579,025 discloses an embodiment of a military charge comprising a first sub-assembly placed at the front of the munition, rear submunitions positioned behind the first sub-assembly and an envelope cylindrical jettisonable, positioned around the periphery of the rear sub-assemblies secured at its rear end to an ejectable rear sub-assembly placed at the rear of the ammunition and resting on its front end on a rear part of the first sub-assembly , this envelope being connected to a first rear sub-assembly by first attachment means, the first rear sub-assembly and the sub-assemblies located in front of it being connected to each other by second attachment means.
  • the object of the invention is a guided munition as described by claim 1.
  • FIG. 1 represents the diagram of a guided munition 1, equipped with a releasable cylindrical envelope 2 according to the invention.
  • Ammunition 1 comprises different sub-assemblies, for example, juxtaposed and positioned along an axis X′X which is the longitudinal axis of ammunition 1; these sub-assemblies are composed, for example, of a first sub-assembly, for example a self-director 3, placed at the front of the ammunition 1, and of rear sub-assemblies, for example, a guide electronics and its components 4, a military charge 5, a braking system, for example, a parachute 8, of a gas generator, for example a propellant making it possible to increase the range of the munition 1 and the releasable casing 2 secured at a rear end 22 of an ejectable sub-assembly, for example, a parachute 8.
  • a first sub-assembly for example a self-director 3
  • This envelope 2 positioned after embedding of the various sub-assemblies does not entirely cover all of the sub-assemblies constituting the ammunition.
  • the casing 2 does not cover the auto-director 3 of the munition 1 placed on the front part of the munition 1.
  • a front end 23 of the casing 2 comes to bear on a rear part 10 of the self-director 3 so that a bearing face 24 of the envelope 2 rests on a face 25 of the self-director 3 ensuring an alignment of the surfaces of the two elements so that the external surface of the ammunition has, for example, a homogeneous and cylindrical structure on the periphery.
  • the homogeneity facilitates the various manipulations of the ammunition whether it is, for example, during the storage of the ammunition or, for example, during the installation in launching systems by ensuring a tightness of the various sub-assemblies as well as protection of sensitive parts of the ammunition against external aggressions.
  • the cylindrical geometry of the structure allows a reduction in aerodynamic drag during a first phase of the munition 1 called the ballistic phase. This phase, following the firing of the munition, for example from a cannon, requires rigidity to withstand the forces due to acceleration in the tube; moreover a smooth surface minimizes friction inside the tube but also a sufficient mass also promotes the range of the ammunition.
  • connecting means have been arranged between each of the sub-assemblies, for example, at locations A, B and C as shown in Figure 1. This embodiment is not limiting and the number of locations may vary if there are more or less sub-assemblies constituting the munition.
  • These connecting means appear in more detail in FIGS. 2, 3 and 4 respectively representing the locations A, B and C when the envelope 2 is supported on the self-director 3.
  • the casing 2 Before the different sub-assemblies are covered by the casing 2, the latter are held together, for example, by locking and unlocking means or connecting means which are positioned on the periphery of the sub-assemblies; these connecting means are, for example, elastic or pyrotechnic and allow assembly of the sub-assemblies without deterioration of the sensitive parts fitted to each of the sub-assemblies.
  • an elastic means consisting, for example, of a leaf spring is placed between each of the sub-assemblies, the machining of which allows, for example, the embedding of the second sub-assembly in the first sub-assembly in the occurrence, in the embodiment, of the guide electronics 4 in the auto-director 3.
  • FIG. 2 representing a detailed view of the location A in FIG. 1, after covering by the envelope 2 , shows the connection between the casing 2 fixed to the propellant not shown in this figure 2 and, for example, the military charge 5.
  • the casing 2 has a structure, for example, made of metal. This structure is machined, at this location A, so that, on the one hand, hooking means, for example a notch 11 positioned, for example, on the internal periphery allow a first connecting means 12 to lock the casing 2 to the rest of the ammunition comprising the various sub-assemblies mentioned above and, secondly, that the connecting means 12 ensures the contacting of a first part 13 of the structure of the military charge 5 against a second part 14 of the structure of the envelope 2.
  • the notch 11 of the envelope 2 has an oblique edge 17 which, during activation of the connecting means 12, allows the latter to remove the clearance which existed between the first part 13 and the second part 14, by means of a translation movement in the opposite direction to the longitudinal axis X′X of the structure of military charge 5, along the envelope loppe 2.
  • Unchecks consisting, inter alia, of the first part 13 and the second part 14 placed respectively on the structure of the military charge 5 and on the structure of the envelope 2 were produced so as to facilitate on the one hand, the machining of each of the sub-assemblies and on the other hand, the translation of the envelope 2 on the different sub-assemblies, the envelope 2 sliding on the sub-assemblies along the axis X′X.
  • the connecting means 12 placed, for example, at the outer periphery of the structure of the military charge 5 is positioned, for example, in a groove 18 situated at the rear of the structure of the military charge 5.
  • This means of link 12 is, for example, a pyrotechnic device which is shown in the diagram of Figure 6 in an unlocked position.
  • the groove 18 In the groove 18, is housed a circlip 27, the ends of which form two spaced apart ears 28, directed inwards, and contained in a hollow part 26.
  • the circlip 7 On its outer periphery, the circlip 7 has teeth 29 regularly spaced apart, directed outwards.
  • the groove 18 is deep enough that the circlip 27 with its teeth 29 is capable of fully entering it when it is tightened.
  • the circlip when the circlip is in its initial state, or deployed state, its teeth 29 are out of the groove 18. In the presence of the casing 2 on the structure of the military charge 5, the teeth 29 are then engaged in the corresponding notches 11 provided in the internal part of the casing 2.
  • Each lug 28 of the circlip 26 comprises an oblique opening 31 of substantially radial direction, by which it is articulated with one end of a link 32.
  • the links 32 are pivotally mounted , substantially in their median part, around axes 33 perpendicular to the plane of the circlip 27.
  • the other ends of the links 32 carry rollers 34, substantially in the plane of the circlip 27.
  • the presence of the rollers 34 is not strictly necessary for the operation, but they make it possible, by reducing friction, to obtain a reduction in the energy necessary for actuating the device.
  • the bottom of the hollow part 26 has a radial groove 35 whose external end communicates with a lumen 36 in the internal part of the envelope 2. Inwardly, the groove 35 widens by each side before the rollers 34 and it extends, thus widened, beyond said rollers.
  • a slider 37 is engaged which may or may not be between the rollers 34, depending on its position in the groove.
  • the slide 37 has its end directed outwards in the shape of a point, so as to be able to engage between the rollers 34 when the latter are brought together.
  • the bottom of the groove 36 in the rear part thereof, has a second narrow groove 38, in which is engaged the rod 39 of a pyrotechnic piston 40.
  • the rod 39 protrudes above the groove 38, so as to be able to push the slide 37 outwards.
  • the pyrotechnic piston is controlled by electronic means, not shown, which thus ensures the locking and unlocking of the connecting means 12. Unlocking takes place by energizing the pyrotechnic piston 40, the rod 39 of which pushes the slide towards the outside between the rollers 34 which brings the ends of the circlip 27 together and retracts the teeth 29 which extend into the notches 11.
  • FIG. 3 represents a detailed view of location B of FIG. 1 showing a second connecting device 41 positioned, for example, between the guide electronics 4 and the structure of the military charge 5, the assembly being covered with the casing 2.
  • This connecting device 41 comprises, for example, a rod, for example, elastic 42 positioned, for example, around the external periphery of the structure of the military charge 5 and on its front end 44.
  • the rod 42 is inserted into a groove 45, for example, rectangular and has, for example, a thickness H less than or equal to the depth of the groove 45 so as to which, for example, when embedding the front end 44 of the structure of the military charge 5 on the rear part 46 of the guide electronics 4, the operation is carried out easily, avoiding all the problems of stops created by poor sizing of the machined parts.
  • the rod 42 is traversed, for example, by at least one hole 47 which, for example, has been threaded to allow screwing, for example, at least one screw 48. This screw 48 is brought into contact with the rod 42, for example, by at least a first hole 49 which has been drilled, for example, on the rear part 46 of the guide electronics 4.
  • access means consisting, for example, of at least one second hole 55 are made in the casing 2.
  • This hole 55 is positioned so that that, after covering the rear sub-assemblies by the casing 2, the diameter of the hole 55 is, for example, opposite the diameter of the first hole 49 of the rear part 46 of the guide electronics 4. In this way, it is possible to screw the screw 48 so that the end 54 of the guide electronics 4 comes to bear against the stop 53 preventing, after tightening, any displacement of one of the subsets with respect to the others.
  • FIG. 4 represents a detailed view of the location C of FIG. 1.
  • FIG. 4 represents more particularly the connection between the first subset of the ammunition, for example, a self-director 3 and one of the rear sub-assemblies of the ammunition, for example, the guide electronics 4.
  • the operations carried out and described in FIG. 3 are carried out in the same way on the location C, the only difference being that the casing 2 does not cover, for example, the self-director 3 but it is in abutment on the rear part 10 of the structure of the self-director 3.
  • the munition After carrying out the last screwing operation at location C, there is no play inside the munition and the latter is ready for use.
  • This munition being placed inside a launch system, for example a cannon, the munition can be fired.
  • the propellant 9 positioned on the rear part of the ammunition is ignited. It allows, thanks to the ejection of a predetermined volume of gas, to increase the range of the ammunition by giving it an optimal propulsion. This propulsion being completed the guided phase of the ammunition begins. During this phase, any unnecessary mass impairs its proper functioning. It is therefore essential to minimize the mass of the ammunition structure.
  • the propellant and the envelope acting only during the ballistic phase the mass of the propellant as well as that of the envelope which is attached by a fixing system can be ejected to improve the guided phase of the ammunition.
  • the ammunition may include, for example, a guidance system positioned at the periphery of the guide electronics 4 and consisting of wings 6, for example, deployable along two perpendicular axes not shown so that the profile of each of the wings is parallel to the longitudinal axis X′X of the munition after deployment and a stabilization system positioned at the periphery of the military load 5 and consisting of fins 7 deployable according to the same orientation means as the deployable wings, these two systems being shown in FIG. 1.
  • at least one locking and unlocking system is required to hold the wings and fins against the body of the ammunition and for, at the time of the guided phase, to release these wings and fins ensuring the guidance and stability of the ammunition.
  • the envelope 2 covering these two systems, during the ballistic phase of the ammunition, will be used, in our embodiment, as a locking and unlocking system.
  • the envelope 2 shown in dotted lines covers the wings 6 and the fins 7 until the end of the ballistic phase.
  • ejection means make it possible to separate the propellant from the rest of the ammunition. Then, as soon as the self-director 3 of the ammunition has detected the ground, opening means, not shown, allow the deployment, for example, of the parachute to slow down the speed of the ammunition.
  • the braking being carried out, means of detection, for example of the speed of the ammunition trigger the energization of the pyrotechnic piston 40 which unlocks the connecting device 12 releasing the casing 2 and the parachute 8 on which it is fixed for the rest rear sub-assemblies.
  • the envelope 2 thus releases, firstly, the wings 6 which deploy, for example, along an oblique axis 19 so that that each section 21 of wings 6 is parallel to the longitudinal axis X′X of the munition and, in a second step, the fins 7 according to the same orientation means as those used for the wings 6.
  • the invention applies to any guided ammunition drawn from a launching system by cannon effect, the peripheral envelope being able to be fixed to any ejectable part of an ammunition, the propellant being a nonlimiting example.

Claims (5)

  1. Lenkmunition mit einer ersten Untergruppe (3), die vor der Munition (1) angeordnet ist, hinteren Untergruppen (4, 5, 8), die hinter der ersten Untergruppe (3) entlang einer Achse (X′X) angeordnet sind, die die Längsachse der Munition ist, und einer zylindrischen, abwerfbaren Hülle (2), die um den Umfang der hinteren Untergruppen (4, 5, 8) angeordnet und mit ihrem hinteren Ende (22) fest mit einer hinteren, auswerfbaren Untergruppe (8) verbunden ist, die hinter der Munition angeordnet ist, und mit ihrem vorderen Ende (23) an einem hinteren Teil (10) der ersten Untergruppe anliegt, wobei diese Hülle (2) mit einer ersten hinteren Untergruppe (5) durch erste Kopplungsmittel verbunden ist und die erste hintere Untergruppe (5) und die vor dieser angeordneten Untergruppen (3, 4) untereinander durch zweite Kopplungsmittel verbunden sind, dadurch gekennzeichnet, daß die ersten Kopplungsmittel durch wenigstens einen mit einem schrägen Rand (17) versehenen und am Innenumfang der Hülle (2) angeordneten Einschnitt (11) und einen Sicherungsbügel (27) gebildet sind, der in einer Nut (18) der ersten hinteren Untergruppe (5) angeordnet ist und in seinem ausgebreiteten Zustand in den Einschnitt (11) eingreift, wobei der Übergang von dem ausgebreiteten Zustand zu dem zusammengezogenen Zustand durch eine pyrotechnische Vorrichtung (40) bewirkt wird, die zweiten Kopplungsmittel zur Verbindung zweier aufeinanderfolgender Untergruppen durch einen mit einem schrägen Rand (52) versehenen, am Innenumfang einer (3, 4) dieser beiden aufeinanderfolgenden Untergruppen (3, 4; 4, 5), eine Rille (45), die am Außenumfang der anderen (4, 5) dieser beiden Untergruppen angeordnet ist, und einen elastischen Sprengring (42) gebildet sind, der in die Rille (45) eingesetzt ist und ein Gewindeloch (47) aufweist, in das eine Schraube (48) eingeschraubt ist, wobei eine Seite (51) des oberen Teils des elastischen Sprengrings (42) durch das Einschrauben der Schraube (48) mit dem schrägen Teil (52) in Kontakt gebracht ist; und wobei erste Löcher (49) gegenüber zweiten Löchern (55) in der Hülle (2) angeordnet sind, wenn diese die hinteren Untergruppen überdeckt, um einen Zugang zum elastischen Sprengring zu schaffen.
  2. Munition nach Anspruch 1, dadurch gekennzeichnet, daß die Hülle ein Führungssystem und ein Stabilisierungssystem umgibt, die am Umfang der hinteren Untergruppen der Munitionsteile angeordnet sind, um ein Verriegelungs- und Entriegelungssystem zu bilden.
  3. Munition nach Anspruch 1, dadurch gekennzeichnet, daß die erste Untergruppe der Munition (1) ein Zielsucher (3) ist.
  4. Munition nach Anspruch 1, dadurch gekennzeichnet, daß die auswerfbare, hinter der Munition angeordnete Untergruppe ein Gasgenerator ist.
  5. Munition nach Anspruch 4, dadurch gekennzeichnet, daß der Gasgenerator ein Triebwerk (9) ist.
EP90403545A 1989-12-19 1990-12-12 Peripheriemantel für einen rohrabgeschossenen gelenkten Flugkörper Expired - Lifetime EP0434505B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8916791 1989-12-19
FR8916791A FR2656081B1 (fr) 1989-12-19 1989-12-19 Enveloppe peripherique pour une munition guidee tiree par effet canon.

Publications (2)

Publication Number Publication Date
EP0434505A1 EP0434505A1 (de) 1991-06-26
EP0434505B1 true EP0434505B1 (de) 1994-09-07

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EP90403545A Expired - Lifetime EP0434505B1 (de) 1989-12-19 1990-12-12 Peripheriemantel für einen rohrabgeschossenen gelenkten Flugkörper

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Country Link
US (1) US5103734A (de)
EP (1) EP0434505B1 (de)
CA (1) CA2032223A1 (de)
DE (1) DE69012300T2 (de)
FR (1) FR2656081B1 (de)

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US6408762B1 (en) 1997-12-11 2002-06-25 Lockheed Martin Corporation Clamp assembly for shrouded aerial bomb
US6389977B1 (en) 1997-12-11 2002-05-21 Lockheed Martin Corporation Shrouded aerial bomb
US6374744B1 (en) 2000-05-25 2002-04-23 Lockheed Martin Corporation Shrouded bomb
US6435097B1 (en) * 2001-04-09 2002-08-20 The United States Of America As Represented By The Secretary Of The Army Protective device for deployable fins of artillery projectiles
US7905182B2 (en) * 2005-06-02 2011-03-15 Raytheon Company Multi-mode modular projectile
US7681834B2 (en) * 2006-03-31 2010-03-23 Raytheon Company Composite missile nose cone
US8156867B2 (en) * 2006-07-17 2012-04-17 Raytheon Company Methods and apparatus for multiple part missile
US8350201B2 (en) 2010-10-14 2013-01-08 Raytheon Company Systems, apparatus and methods to compensate for roll orientation variations in missile components
IL214191A (en) * 2011-07-19 2017-06-29 Elkayam Ami Ammunition guidance system and method for assembly
US9933097B2 (en) * 2014-07-30 2018-04-03 Simmonds Precision Products, Inc. Ring couplings
US9810513B2 (en) * 2014-08-04 2017-11-07 Raytheon Company Munition modification kit and method of modifying munition
DE102015013350A1 (de) * 2015-10-15 2017-04-20 Mbda Deutschland Gmbh Lenkflugkörper und Verfahren zum Herstellen eines Lenkflugkörpers
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Also Published As

Publication number Publication date
DE69012300T2 (de) 1995-01-05
CA2032223A1 (fr) 1991-06-20
EP0434505A1 (de) 1991-06-26
FR2656081A1 (fr) 1991-06-21
US5103734A (en) 1992-04-14
DE69012300D1 (de) 1994-10-13
FR2656081B1 (fr) 1992-02-28

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