EP0482421A1 - Dispenseur de sous-projectiles - Google Patents

Dispenseur de sous-projectiles Download PDF

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Publication number
EP0482421A1
EP0482421A1 EP91117165A EP91117165A EP0482421A1 EP 0482421 A1 EP0482421 A1 EP 0482421A1 EP 91117165 A EP91117165 A EP 91117165A EP 91117165 A EP91117165 A EP 91117165A EP 0482421 A1 EP0482421 A1 EP 0482421A1
Authority
EP
European Patent Office
Prior art keywords
ejection
pistons
gas generator
module
ejection module
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP91117165A
Other languages
German (de)
English (en)
Other versions
EP0482421B1 (fr
Inventor
Ulrich Rieger
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.)
Airbus Defence and Space GmbH
Original Assignee
Daimler Benz Aerospace AG
Messerschmitt Bolkow Blohm AG
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 Daimler Benz Aerospace AG, Messerschmitt Bolkow Blohm AG filed Critical Daimler Benz Aerospace AG
Publication of EP0482421A1 publication Critical patent/EP0482421A1/fr
Application granted granted Critical
Publication of EP0482421B1 publication Critical patent/EP0482421B1/fr
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
    • F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially

Definitions

  • the invention relates to an ejection module for a submunition container according to the preamble of claim 1.
  • Such an ejection module is known from EP 0 169 956 A1.
  • a bomb or a missile with a warhead in which two sets of nine submunitions each are present in two circular arrangements one behind the other.
  • Each submunition body has an ejection piston which is arranged in a cylinder and which can be acted upon by propellant gas from a pyrotechnic cookie inserted at the bottom of the cylinder.
  • the cookies When the cookies are ignited, the submunitions are expelled radially outwards by the ejection pistons. It can therefore only be used as a bomb in vertical or parabolic flight, with the submunitions occupying an approximately circular target area.
  • an ejection module is known from DE-PS 30 48 469, in which the submunition container has a plurality of ejection modules with ejection tubes arranged transversely to the direction of flight.
  • the submunitions are inserted into the entire width of the submunition container and are expelled by a central gas generator such as pistons. This arrangement is therefore only suitable for the size of the ejection tubes of submunitions.
  • the invention has for its object to provide an ejection module of the type mentioned, with which large bulky submunitions can be ejected in horizontal flight at high ejection speed and moderate acceleration.
  • the main advantage of the invention is that the arrangement of the carriers means that bulky submunitions can also be ejected in a substantially horizontal direction, being brought to a high ejection speed with moderate acceleration.
  • the ejection module according to the invention it is possible to perform an almost reaction-free ejection of at least two opposing submunitions.
  • a longer target area can be covered with submunitions when the submunitions of the individual ejection modules are ejected one after the other.
  • a series of ejections can also take place in horizontal flight over a longer period of time.
  • the output is generated in a known manner by gas pressure from only one gas generator.
  • various options for the arrangement of the exhaust pistons with the carriers and the gas generator are characterized.
  • Ejection piston 2 and gas generator 4 lie transversely to the direction of flight of the ejection module 1 indicated by an arrow 3
  • Carriers 5 for submunitions (SM) 7 are connected to the ejection piston 2.
  • SM 7 submunitions
  • the gas generator 4 is located in a tube 17 which is inserted into the ejection piston 2 and serves as a guide during the ejection process. Possibly.
  • two sealing and sliding elements 8 are arranged between tube 17 and ejection piston.
  • the ejection module 1 is mounted in a submunition container 9 indicated by dashed lines.
  • the ejection pistons 2 are driven out of the submunition container 9 directly by the gases of the ignited gas generator 4 in the direction of the arrows 11 and 12.
  • the SM 7 detach from the drivers 5 and the intermediate layers 6 and fly away in the direction of the arrows 13 to 16.
  • FIG. 5 shows a top view of an ejection module 20 with a gas generator 4 arranged in the direction of flight 3, the propellant gases of which flow into a gas guide tube 21 which is inserted into ejection pistons 2a and serves as a guide during the ejection process.
  • Carriers 5 are in turn attached to the ejection pistons 2a. Only two of the SM 7 are shown, which are separated by an intermediate layer 6.
  • the carrier structure 9 of the submunition container is indicated by dashed lines.
  • an ejection module 25 is shown, in which e.g. for large SM 7 there are two ejection pistons 2a, each of which is connected via a driver 5a.
  • the propellant gas flows from the gas generator 4 into gas guide tubes 21.
  • the ejection pistons 2a can have a smaller cross section than those in FIG. 1, as a result of which the overall dimensions of the submunition container 9 can be kept small.
  • FIGS. 7 and 8 show views of the ejection modules 20 and 25 in the flight direction, the ejection module in FIG. 8 having a slight V position.
  • the SMs not shown here can be provided with a vertical speed component during ejection, which means e.g. the throwing path is increased compared to the ejection height during leads to further throwing distances of the SM.
  • the reaction forces that occur on the support structure are only small in the case of small V-positions.
  • An ejection module 30 according to FIGS. 9 and 10 shows a very flat solution, in which the ejection pistons and the gas guide tubes 32 do not have a rotationally symmetrical cross section, as can be seen particularly from the phantom image of FIG. 10.
  • the ejection pistons form a structural unit 31 with the drivers, whereby the drivers contribute to the stiffening.
  • One end of the structural unit 31 lying in the plane of the drawing is shown in section in the phantom image, as a result of which one of the gas guide tubes 32 segmented into a plurality of parts acting in parallel is clearly visible.
  • the ejection pistons of the exemplary embodiments described so far have a length that is less than half the width of the container modules, in the following exemplary embodiments the ejection pistons extend over the full width of the ejection modules. This has the advantage of the greatest possible acceleration distances, so that the highest ejection speeds for the SM can be achieved with low acceleration.
  • 11 to 13 show an ejection module 40 in which the gas generator 4 is arranged axially parallel between two ejection pistons 41 which slide in cylinders 43 and 44. At both ends of the gas generator 4 there are overflow slots 45 and 46 through which the gas can act on the discharge pistons 41.
  • driver structures 48 are fastened to the ejection piston 41 on both sides at the front.
  • FIGS. 14 to 16 show in three views an ejection module 50, in which the gas generator 4 can be accommodated in the longitudinal structure of the submunition container (not shown here).
  • the gas flow from the gas generator 4 to behind the ejection pistons 41 takes place through a central overflow slot 51 and gas channel 52.
  • the cylinders 43 and 44 and the driver structures 48 correspond to those of FIGS. 11 to 13.
  • the advantage of this arrangement is the small lateral distance between the ejection pistons 41 and thus the low reaction moments.
  • Double ejection pistons 61 and 62 in a cylinder unit 63, overflow slots 64 and gas channels 65 are constructed mirror-symmetrically around the axis of the ejection module 60.
  • Each of the ejection pistons 61 and 62 consists of two longitudinal tubes 61 a, 61 b and 62a, 62b, which are connected to one another in piston heads 61c and 62c.
  • the gas flow in the piston heads 61c and 62c and the gas channels 65 are constructed to equalize pressure, so that the pressure in each of the four piston tubes is the same.
  • the gas generator 4 is arranged centrally in the direction of flight.
  • Driver structures 67 are fastened to the piston heads 61c and 62c. In the phantom image of FIG. 19, the ejection pistons are shown partially pushed out for better illustration.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
  • Sampling And Sample Adjustment (AREA)
EP91117165A 1990-10-20 1991-10-09 Dispenseur de sous-projectiles Expired - Lifetime EP0482421B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4033476A DE4033476C2 (de) 1990-10-20 1990-10-20 Ausstoßmodul für Submunitionsbehälter
DE4033476 1990-10-20

Publications (2)

Publication Number Publication Date
EP0482421A1 true EP0482421A1 (fr) 1992-04-29
EP0482421B1 EP0482421B1 (fr) 1996-01-24

Family

ID=6416763

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91117165A Expired - Lifetime EP0482421B1 (fr) 1990-10-20 1991-10-09 Dispenseur de sous-projectiles

Country Status (3)

Country Link
US (1) US5206453A (fr)
EP (1) EP0482421B1 (fr)
DE (2) DE4033476C2 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2709818B1 (fr) * 1993-09-06 1995-12-01 Lacroix E Tous Artifices Munition formant chargeur pour lance-cartouches, notamment pour lance-cartouches de contre-mesures pour aéronef.
DE102004059991B4 (de) * 2004-12-13 2007-03-15 Nico-Pyrotechnik Hanns-Jürgen Diederichs GmbH & Co. KG Irritationskörper
DE102004061658A1 (de) * 2004-12-22 2006-07-13 Diehl Bgt Defence Gmbh & Co. Kg Verfahren und System zum Ausstoßen einer Submunition aus einem Flugkörper

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1346448A (fr) * 1962-11-08 1963-12-20 Soc Tech De Rech Ind Charge explosive à éclats
DE3219535A1 (de) * 1982-05-25 1983-12-01 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Flugkoerper zum absetzen von streumunition
US4455943A (en) * 1981-08-21 1984-06-26 The Boeing Company Missile deployment apparatus
FR2594219A1 (fr) * 1986-02-13 1987-08-14 Rafaut & Cie Dispositif d'ejection, en particulier pour munitions

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2979991A (en) * 1951-10-10 1961-04-18 Martin Co Rapid firing recoilless bomb projecting device
US4307650A (en) * 1978-07-05 1981-12-29 Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung Weapons system for the ballistic and guided attack on multiple targets, especially by an aircraft
US4172407A (en) * 1978-08-25 1979-10-30 General Dynamics Corporation Submunition dispenser system
DE3048469C1 (de) * 1980-12-22 1988-12-15 Messerschmitt Boelkow Blohm Streumunitionsbehaelter
FR2557286B1 (fr) * 1983-12-27 1986-12-05 Brandt Armements Charge militaire a tetes multiples
GB2204388B (en) * 1984-05-10 1989-05-17 Messerschmitt Boelkow Blohm Container for dispersion ammunition
US4750403A (en) * 1986-01-31 1988-06-14 Loral Corporation Spin dispensing method and apparatus
DE3636055C1 (de) * 1986-10-23 1989-12-21 Messerschmitt Boelkow Blohm Einrichtung zum Ausstoss von Submunition
DE3843164C1 (fr) * 1988-12-22 1990-05-10 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De
US5005481A (en) * 1989-06-26 1991-04-09 Olin Corporation Inflatable bladder submunition dispensing system

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1346448A (fr) * 1962-11-08 1963-12-20 Soc Tech De Rech Ind Charge explosive à éclats
US4455943A (en) * 1981-08-21 1984-06-26 The Boeing Company Missile deployment apparatus
DE3219535A1 (de) * 1982-05-25 1983-12-01 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Flugkoerper zum absetzen von streumunition
FR2594219A1 (fr) * 1986-02-13 1987-08-14 Rafaut & Cie Dispositif d'ejection, en particulier pour munitions

Also Published As

Publication number Publication date
EP0482421B1 (fr) 1996-01-24
DE4033476A1 (de) 1992-04-23
DE4033476C2 (de) 1994-10-13
US5206453A (en) 1993-04-27
DE59107301D1 (de) 1996-03-07

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