EP0077954B1 - Missile - Google Patents

Missile Download PDF

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Publication number
EP0077954B1
EP0077954B1 EP82109324A EP82109324A EP0077954B1 EP 0077954 B1 EP0077954 B1 EP 0077954B1 EP 82109324 A EP82109324 A EP 82109324A EP 82109324 A EP82109324 A EP 82109324A EP 0077954 B1 EP0077954 B1 EP 0077954B1
Authority
EP
European Patent Office
Prior art keywords
projectile
segments
fact
accordance
missile
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
EP82109324A
Other languages
German (de)
English (en)
Other versions
EP0077954A2 (fr
EP0077954A3 (en
Inventor
Dieter Dipl.-Ing. Böder
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall GmbH
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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0077954A2 publication Critical patent/EP0077954A2/fr
Publication of EP0077954A3 publication Critical patent/EP0077954A3/de
Application granted granted Critical
Publication of EP0077954B1 publication Critical patent/EP0077954B1/fr
Expired 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
    • F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially

Definitions

  • the invention relates to a missile for transporting a plurality of payloads to be launched at a predetermined point in the trajectory with the features of the preamble of claim 1.
  • Such a missile is described in DE-A-29 20 347.
  • the design according to this OS does not have any segments lying against one another with their side walls, which could form the supporting outer jacket of the projectile and which could withstand the considerable acceleration values both in the longitudinal direction and in the circumferential direction when the missile was launched and flown.
  • there is a supporting frame consisting of an inner frame and attached jacket sections. In between, outlet openings are formed which are covered by thin metal sheets which rest on the walls with a frictional connection.
  • This is a very complex and cumbersome construction, especially since ejection bellows, which are pneumatically operated, are required to push the sheets out.
  • a missile with a supporting outer jacket without support internals is formed solely by segment-shaped outer wall parts.
  • US-A-3 088 404 discloses a missile with ejectable payloads, which consists of a one-piece metallic cylindrical shell. On its inner wall, segment-shaped holding plates are arranged transversely to the longitudinal direction of the casing, which are connected to one another by means of a tongue and groove connection with the aid of rivet bolts. To repel the payloads, the rivet bolts and the casing should be disassembled by explosion in a manner not described in detail. No reference to the present invention can be inferred from this either.
  • the object of the invention is to improve a missile of the type mentioned in such a way that a shell of low weight is formed from segments without internal support internals which can withstand the considerable acceleration values occurring in the longitudinal axis direction and in the circumferential direction when the missile is moving, and yet with its own Spring force that can only be easily thrown off at the same time by interlocking segments.
  • FIG. 1 shows a schematic representation of a missile for transporting a plurality of payloads ejected at a predeterminable point of the flight path.
  • the tail unit 2 arranged at the rear of the missile there is an essentially hollow-cylindrical part of the missile 10, which is delimited on the outside by a tubular casing 12.
  • This envelope 12 encloses a payload space 4, in which payloads 11 are arranged separately, if necessary, by floors 24 extending transversely to the longitudinal axis of the missile 10.
  • these payloads 11 In order to be able to cover the widest possible terrain strip along the trajectory of the missile with payloads 11 to be ejected, these payloads 11 must be ejected in the radial direction, that is, perpendicular to the direction of travel of the missile 10. For this purpose, it is necessary that at a predeterminable point in time, namely when the missile 10 has reached a specific point on its trajectory, the tubular envelope surrounding the payload space 4 is removed in order to enable the payloads to be ejected in the radial direction.
  • the invention is particularly concerned with the configuration of the tubular shell 12 of the missile, which has to withstand considerable acceleration values both in the longitudinal axis direction of the missile 10 and in the circumferential direction when the missile 10 is launched and moved.
  • the cover 12 must nevertheless be easily ejectable in order to enable the unimpeded ejection of the payloads 11.
  • FIG. 2 shows a partial sectional illustration in the longitudinal axis direction of the missile 10 in the region of the payload space of the missile 10.
  • FIG. 3 shows a view of a cross-sectional plane of the missile 10 as viewed from line 3 - 3 according to FIG. Fig. 2.
  • FIG. 4 shows a detailed illustration from FIG. 3 on a substantially enlarged scale.
  • the tubular casing 12 consists of a plurality of segments 13, 13 'which are detachably connected to one another and which abut one another with their side edges 16, 16' in such a way that they essentially form a cylinder jacket surface.
  • the segments 13, 13 ' are expediently made of an elastic material, so that their bending on a cylindrical surface causes a resetting force.
  • the segments 13, 13 ' can therefore only be forced into the cylinder shape using a prestress and can be braced in this position.
  • FIG. 5 shows a partial sectional view in the longitudinal axis direction of the missile 10 in the region of such a rod 18.
  • the rod 18 has eccentric and / or conical or stepped seats 19 in the region of the hook-shaped extensions 15, 15 ', to which the hook-shaped extensions 15, 15 'can create, whereby they can be clamped against each other when the rod 18 moves relative to the hook-shaped extensions 15, 15'.
  • this bracing is achieved by moving the rod 18 during the assembly of the segments 13, 13 'in the longitudinal axis direction of the missile 10.
  • the hook-shaped extensions 15, 15 ' can be braced by rotating the rod 18 about its longitudinal axis and / or simultaneous longitudinal movement of the rod 18 in the longitudinal axis direction of the missile 10.
  • the locking of the segments 13, 13 'achieved with the aid of the rod 18 can be canceled in a simple manner after the predetermined ejection point of the payloads 11 has been reached by the rod 18 being moved and / or rotated in the opposite direction, as in the case of assembly.
  • This longitudinal or rotational movement of the rod 18 naturally requires a certain force.
  • This can be provided in a particularly simple and reliable manner by means of a pyrotechnic charge 20 provided with an optionally electrically activatable igniter 21.
  • the rod 18 is expediently designed as a hollow cylinder which is closed on one side and rests with its open end piece 22 on the pyrotechnic charge 20.
  • the gases generated when the pyrotechnic charge 20 is ignited can consequently penetrate through the open end piece 22 of the rod 18 into its interior and exert a force on its end face opposite the open end piece. Since the pyrotechnic charge 20 also acts on the circular surface of the rod 18 with which it rests on the pyrotechnic charge 20, a pressure-tensile force on the rod 18 results in a particularly advantageous manner, which moves it in the longitudinal axis direction of the missile and thereby unlocking the segments 13, 13 'leads.
  • floors 24 are provided which extend transversely to the longitudinal axis of the missile 10, on the lateral surface 25 of which the segments 13, 13 'rest with their inner surface.
  • grooves 26 are embedded in the lateral surfaces 25 of the bottoms, into which a collar 27 arranged on the segments 13, 13' engages.
  • grooves 26 and collar 27 are preferably wedge-shaped in cross section (FIG. 6).
  • the missile At launch, the missile is given a rotational movement about its longitudinal axis, which can also be maintained or reinforced during flight, if necessary, by additionally arranged engines.
  • This rotational movement leads to force components directed transversely to the longitudinal axis, which act on the segments 12, 13 'forming the shell 12 with the aim of torsion.
  • the segments 13, 13' and the bottoms 24 are either hooked in the area of their wedge-shaped connection (FIG. 7) or equipped with interlocking teeth 28 (FIG. 8).
  • Fig. 8 shows a sectional view along the line 8 - gem.
  • the segments 13, 13 ' are preferably produced from light metals commonly used in aircraft construction or also from plastic, in particular fiber-reinforced plastic.
  • a support structure extending in the longitudinal axis direction of the missile is advantageously provided, which on the one hand divides the payload space 4 into individual compartments 4 'for receiving a payload 11 each and which on the other hand offers support points or support surfaces 29 to which the segments 13, 13 'can also support with their inner surface 14.
  • the support structure expediently comprises partition walls 30 which are arranged parallel to the longitudinal axis of the missile and which enclose an angle between them and which partition off the rods 18, the hook-shaped extensions 15, 15 'and the joints between the segments 13, 13' in relation to the payloads 11 .
  • the segments 13, 13 'simultaneously serve to hold additional or correction engines, which, for example during the flight phase of the missile 10, maintain or reinforce the swirl communicated to it during takeoff. These additional or correction engines are then separated from the missile together with the segments 13, 13 'when unlocked.
  • the unlocking of the segments 13, 13 ' can be carried out simultaneously or with a time delay if necessary.
  • the chronological order can be checked by activating the pyrotechnic charges 20.
  • the ejection of the payloads 11 can either take place simultaneously with the separation of the segments 13, 13 'or take place with a time delay.
  • the latter possibility allows the targeted ejection of a payload 11 in correlation to the rotational movement of the missile 10 with respect to its longitudinal axis. This proves to be particularly expedient in those cases in which a large radial throw range is aimed at when the payloads 11 are ejected.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
  • Elimination Of Static Electricity (AREA)

Claims (10)

1. Missile (10) pour transporter une multiplicité de charges utiles (11) à éjecter à un point prédéterminé de la trajectoire, comportant une enveloppe (12) tubulaire entourant le compartiment des charges utiles (4) et comportant des segments amovibles (13,13') tenus par précontrainte, et des moyens pour éjecter la charge utile, caractérisé en ce qu'une multiplicité de segments (13,13,) adjacents l'un à l'autre par leurs arêtes latérales (16,16') constituent l'enveloppe tubulaire, que les segments sont forcés par précontrainte à prendre la forme cylindrique et sont serrés dans cette position, qu'au voisinage de chaque arête latérale (16,16') de chaque segment (13, 13') sont disposés sur la surface intérieure (14) de chaque segment des prolongements (15,15') en forme de crochets saillant à l'intérieur du missile (10) de telle sorte qu'ils dépassent l'arête latérale correspondante du segment (13,13') qui leur est associé, en direction du segment voisin, et sont décalés en hauteur de telle sorte qu'ils entourent un évidement (17) à la façon d'une tenaille en se recouvrant l'un l'autre, que les évidements (17) entourés par les prolongements (15, 15') de segments voisins (13, 13') coincident l'un avec l'autre, et qu'on prévoit, à chaque endroit de jonction de segments adjacents (13, 13'), une barre (18) qui est disposée parallèlement à l'axe longitudinal du missile (10) et traverse tous les évidements alignés (17), la barre (18) comportant dans la zone des prolongements (15,15') en forme de crochets des sièges (19) réalisés excentrés et/ou coniques ou à décrochement, sur lesquels les prolongements (15, 14') en forme de crochets s'appuient et peuvent de cette façon être serrés l'un contre l'autre lors d'un mouvement relatif de la barre (18).
2. Missile selon la revendication 1, caractérisé en ce que la barre (18) peut se déplacer dans le sens axial du missile (10) et/ou tourner autour de son axe longitudinal.
3. Missile selon la revendication 1 ou 2, caractérisé en ce que la barre (18) est réalisée sous la forme d'un cylindre creux fermé d'un côté, dont l'extrémité ouverte (22) repose sur une charge pyrotechnique (20) munie d'un détonateur (21).
4. Missile selon l'une des revendications 1 à 3, caractérisé en ce que les parties terminales (22, 22') de la barre (18) sont montées dans des guidages (23, 23').
5. Missile selon l'une des revendications 1 à 4, caractérisé en ce qu'on prévoit, pour localiser et/ou isoler le compartiment des charges utiles, des fonds (24) disposés transversalement à l'axe longitudinal du missile (10), sur la surface latérale (25) desquels les segments (13,13') appuient par leur surface intérieure, une gorge (26) dans ... laquelle pénètre une collerette (27) disposée sur les segments (13, 13') étant ménagée dans la surface latérale (25) de chaque fond (24).
6. Missile selon l'une des revendications 2 à 5, caractérisé en ce que les gorges (26) et les collerettes (27) ont en section transversale la forme de coins.
7. Missile selon l'une des revendications 1 à 6, caractérisé en ce que les surfaces en vis-à-vis de la gorge (26) et de la collerette (27) sont munies de dents (28) s'interpénétrant.
8. Missile selon l'une des revendications 1 à 7, caractérisé en ce que les segments (13, 13') sont en métal ou en matière plastique, notamment en matière plastique renforcée de fibres.
9. Missile selon l'une des revendications 1 à 8, caractérisé en ce que les segments (13, 13') s'appuient par leur surface intérieure (14) contre des surfaces d'appui (29) disposées à l'intérieur du missile.
10. Missile selon l'une des revendications 1 à 9, caractérisé en ce que les barres (18), sont isolées des charges utiles à l'aide de cloisons de séparation (30) disposées parallèlement à l'axe longitudinal du missile (10).
EP82109324A 1981-10-24 1982-10-08 Missile Expired EP0077954B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3142313 1981-10-24
DE19813142313 DE3142313A1 (de) 1981-10-24 1981-10-24 Flugkoerper

Publications (3)

Publication Number Publication Date
EP0077954A2 EP0077954A2 (fr) 1983-05-04
EP0077954A3 EP0077954A3 (en) 1983-11-16
EP0077954B1 true EP0077954B1 (fr) 1986-08-13

Family

ID=6144802

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82109324A Expired EP0077954B1 (fr) 1981-10-24 1982-10-08 Missile

Country Status (7)

Country Link
US (1) US4524694A (fr)
EP (1) EP0077954B1 (fr)
JP (1) JPS5883199A (fr)
AU (1) AU555916B2 (fr)
CA (1) CA1186561A (fr)
DE (2) DE3142313A1 (fr)
ES (1) ES8309004A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2000853A6 (es) * 1986-08-08 1988-03-16 Esperanza & Cie Sa Proyectil portador para mortero
FR2617464B1 (fr) * 1987-07-03 1990-02-16 Thomson Brandt Armements Dispositif de fermeture ejectable, notamment pour roquettes a sous-munitions
FR2641858B1 (fr) * 1989-01-17 1991-03-15 Thomson Brandt Armements Dispositif de deverrouillage pneumatique pour munitions largables a partir d'un vecteur
FR2656414B1 (fr) * 1989-12-22 1993-01-22 Thomson Brandt Armements Systemes de retenue de sous-munitions embarquees dans un vecteur.
SE503719C2 (sv) * 1992-06-30 1996-08-12 Bofors Ab Sätt och anordning för separation av substridsdelar
US6003809A (en) * 1997-02-25 1999-12-21 Honigsbaum; Richard F. Process and apparatus for discouraging countermeasures against a weapon transport device

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE298070C (fr) *
US2450910A (en) * 1938-10-07 1948-10-12 George M O'rear Aerial bomb
GB589334A (en) * 1943-05-31 1947-06-18 Jack Imber Improvements in or relating to aerial bombs, flares and the like which are dropped from aircraft
US2604043A (en) * 1946-05-16 1952-07-22 Foster Wheeler Corp Bomb
US2809583A (en) * 1952-12-04 1957-10-15 Roman L Ortynsky Cluster bomb
US3016011A (en) * 1956-07-11 1962-01-09 Brown Fred Cluster opening method
US3088404A (en) * 1956-11-15 1963-05-07 Brown Fred Interlocking screw threads
US3215082A (en) * 1962-09-24 1965-11-02 Aerojet General Co Rapid release device for connecting rocket stages
US3253842A (en) * 1963-12-10 1966-05-31 Thiokol Chemical Corp Shear key joint
US3461801A (en) * 1968-01-25 1969-08-19 Us Navy Multi-canister ejecting device
DE1955777C3 (de) * 1969-11-06 1979-11-22 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Gefechtskopf
US4178851A (en) * 1972-03-08 1979-12-18 The United States Of America As Represented By The Secretary Of The Army Dual purpose munition
DE2558060C2 (de) * 1975-12-22 1986-01-23 Rheinmetall GmbH, 4000 Düsseldorf Trägergeschoß für ausstoßbare Körper
DE2739299C2 (de) * 1977-09-01 1984-01-19 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Halterung für Streuwaffengroßbehälter
US4120519A (en) * 1977-10-03 1978-10-17 The Bendix Corporation Collet type cylinder separation device
DE2903938A1 (de) * 1979-02-02 1980-08-14 Messerschmitt Boelkow Blohm Streumunition
DE2920347C2 (de) * 1979-05-19 1982-11-11 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Gefechtskopf mit ausstoßbaren Wirkkörpern

Also Published As

Publication number Publication date
CA1186561A (fr) 1985-05-07
AU555916B2 (en) 1986-10-16
ES516686A0 (es) 1983-10-16
DE3272598D1 (en) 1986-09-18
US4524694A (en) 1985-06-25
EP0077954A2 (fr) 1983-05-04
ES8309004A1 (es) 1983-10-16
AU8862682A (en) 1983-04-28
EP0077954A3 (en) 1983-11-16
JPS5883199A (ja) 1983-05-18
DE3142313A1 (de) 1983-05-05

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