EP0062750A1 - Procédé pour disperser des charges actives à partir d'un engin porteur - Google Patents

Procédé pour disperser des charges actives à partir d'un engin porteur Download PDF

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Publication number
EP0062750A1
EP0062750A1 EP82101490A EP82101490A EP0062750A1 EP 0062750 A1 EP0062750 A1 EP 0062750A1 EP 82101490 A EP82101490 A EP 82101490A EP 82101490 A EP82101490 A EP 82101490A EP 0062750 A1 EP0062750 A1 EP 0062750A1
Authority
EP
European Patent Office
Prior art keywords
submunition
distribution unit
distribution
carrier
individuals
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
EP82101490A
Other languages
German (de)
English (en)
Other versions
EP0062750B1 (fr
Inventor
Klaus Fischer
Heinz Kroschel
Joachim Nicodemus
Willi Dr. Petters
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.)
Dynamit Nobel AG
Original Assignee
Dynamit Nobel 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 Dynamit Nobel AG filed Critical Dynamit Nobel AG
Publication of EP0062750A1 publication Critical patent/EP0062750A1/fr
Application granted granted Critical
Publication of EP0062750B1 publication Critical patent/EP0062750B1/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
    • F42B12/62—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 method for distributing submunitions according to the preamble of the claim
  • the distribution of submunitions using carrier missiles is generally known.
  • the submunition can be mines, bomblets, daughter levels, interfering bodies or the like. Rockets in particular are considered as carrier missiles, but also grenades, for example.
  • the warheads of the launchers or the grenades above the target area are generally dismantled in various ways and all individual bodies or individuals of submunition are released immediately.
  • DE-OS 21 53 994 it is also known to arrange submunitions or general ejection bodies in the warhead of a missile, which is provided with a special distribution unit.
  • This distribution unit has a payload carrier plate with a plurality of pivotally attached ejection tubes containing the ejection bodies, which are spread apart before being distributed.
  • the distribution unit can be braked before the release of the ejection bodies by additional braking measures, for example by means of a brake parachute or by airbrakes, so that it sinks vertically downwards.
  • the distribution unit can still be connected to the remaining rocket or can also be separated from it and transferred to the vertical path on its own.
  • the invention has for its object, in particular the to avoid the above disadvantages, ie to carry out a method for distributing submunition in accordance with the preamble of claim 1 in such a way that collisions and other undesirable loads and thus a reduction in the functional reliability of the submunition are at least largely avoided.
  • the distribution unit is preferably ejected in the direction of flight of the carrier missile.
  • the defined guidance during the ejection movement can e.g. can be achieved in that the distribution units designed as cylindrical or tubular bodies are guided like bullets in corresponding tubular ejection devices of the carrier missile.
  • the distribution units can be ejected from individual tubes or in a row one behind the other and / or next to one another, in each case in an ejection tube, if necessary via a sabot. Guided tours in the manner of start rails are also possible.
  • the distribution units are provided with aerodynamic stabilization devices, for example guide surfaces, in order to avoid undefined flight movements.
  • the at least one distribution unit which initially moves at a distance from one another on the same trajectory, and the rest of the carrier missile are then delayed differently ballistically.
  • the distribution unit is provided with a braking device which has a stabilizing effect at the same time, so that the distribution unit is decelerated more and is thereby deflected downward and the carrier missile largely flies over the distribution unit on the ballistic path of the original missile.
  • the distance of the distribution unit from the carrier missile generated by the defined primary ejection from the carrier missile and its braking are coordinated with one another in such a way that the distribution unit nevertheless remains at a sufficient distance from the carrier missile when re-approaching due to the braking. Subsequently, the individuals of the submunition can be expelled from the distribution unit and thus released for individual distribution in the secondary output. In this way, possible collisions of the remaining parts of the carrier missile with the distribution unit and also with the submunition are excluded and reproducible ballistic conditions are achieved.
  • the submunition individuals are accommodated in a plurality of distribution units which are arranged next to and / or one behind the other as secondary bodies in the carrier missile.
  • Their number is small in relation to the total number of individuals per carrier unit.
  • approximately the same distribution of the distribution units per carrier missile is achieved in the primary ejection according to the static laws, which has an expansion corresponding to the ejection height. If the number of individuals per distribution unit is now also low, a more or less perfect uniform distribution is achieved with secondary output, based on the individual distribution unit. Since the second ejection point is lower than the first, the less extensive uniform distribution of the individuals per distribution unit advantageously overlaps the equal distribution of the distribution units to a uniform distribution of all individuals of a carrier missile.
  • the known distribution methods also cause the individuals to accumulate at the release point when the submunition is released immediately from the carrier missile. This increases the likelihood of collision between individuals and significantly increased with parts of the disassembled carrier missile. This disadvantage is also avoided if the submunition is accommodated in several distribution units, the number of which is correspondingly smaller than the number of individuals.
  • the individuals of the submunition are preferably arranged one behind the other in a stack or column-like manner in the distribution unit. Depending on the direction of ejection from the distribution unit, they are furthermore preferably oriented in such a way that they do not have to roll over after being ejected, for example, in order to assume their intended position during the flight. This secondary ejection from the distribution unit can take place in its flight direction.
  • the individuals of the submunition are preferably ejected from the distribution unit against the direction of flight or these are withdrawn to the front, so to speak. The distribution unit is additionally accelerated in the direction of flight, while the submunitions are decelerated.
  • the speed of the distribution unit is greatly increased, so that a clear distance is again generated between the distribution unit and the submunition. Due to the subsequent different ballistic delay, the trajectories of the two components then diverge in such a way that a collision is not to be feared in the further course of the distribution process.
  • the double ejection according to the invention also offers the possibility, according to claim 4, of achieving an optimal deceleration of the distribution unit on the one hand and of the individuals of submunition on the other hand, for example by the distribution unit is slowed down with a brake parachute designed for supersonic speed, while the individuals e.g. with brake parachutes designed for subsonic speeds are so delayed that they do not exceed an intended impact speed on the ground.
  • a directed impact on the ground is achieved with correspondingly defined loading directions for which the submunition can be designed.
  • the random distribution of the submunition individuals can be e.g. can be extended to a larger area through asymmetrical openings in the brake parachutes.
  • the 1 shows the primary ejection after the carrier missile 1 with the sleeve-shaped distribution unit 2 containing the submunition has reached the ballistic ejection point above the target area.
  • the output of the distribution unit 2 takes place after an ignition pulse from a timer or to the ground appealing distance igniter by means of a pyrotechnic discharge charge.
  • the ogive 3 is blown off beforehand or simultaneously with the ejection.
  • the distribution unit 2 stabilized by means of the supersonic screen 4 and, like the carrier missile 1, moves on a defined trajectory is shown immediately after the ejection process, ie still close to the carrier missile 1.
  • the distance between the two bodies is initially increased until the retarding effect of the parachute 4 predominates and the distribution unit 2 swings into its own flight path according to FIG. 2.
  • the remaining carrier missile 1 flies over the distribution unit at a sufficient distance so that collisions are excluded.
  • the submunition here five mines 5
  • the submunition is ejected against the direction of flight again with the aid of a pyrotechnic charge from the distribution envelope 2 ′′ closed at its front end 2 ′ after a predetermined delay time from the primary emission.
  • the time delay can be based on pyrotechnic, mechanical or electronic
  • the brake parachute 4 is also separated.
  • the mines 5 arranged in the distribution shell 2 ′′ as a dense stack with their subsonic parachute 6 are separated by the strong successive braking and finally float stabilized and braked according to FIG. 4 in approximately equal distribution to the ground.
  • the distribution of the mines 5 on the ground can be influenced.

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)
EP82101490A 1981-03-26 1982-02-26 Procédé pour disperser des charges actives à partir d'un engin porteur Expired EP0062750B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19813111907 DE3111907A1 (de) 1981-03-26 1981-03-26 Verfahren zum verteilen von submunition
DE3111907 1981-03-26

Publications (2)

Publication Number Publication Date
EP0062750A1 true EP0062750A1 (fr) 1982-10-20
EP0062750B1 EP0062750B1 (fr) 1987-05-13

Family

ID=6128332

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82101490A Expired EP0062750B1 (fr) 1981-03-26 1982-02-26 Procédé pour disperser des charges actives à partir d'un engin porteur

Country Status (4)

Country Link
US (1) US4498393A (fr)
EP (1) EP0062750B1 (fr)
CA (1) CA1216774A (fr)
DE (2) DE3111907A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0794405A1 (fr) * 1996-03-08 1997-09-10 DIEHL GMBH & CO. Procédé et dispositif pour disperser une charge utile de gros calibre au-dessus d'un objectif

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2547910B1 (fr) * 1983-06-27 1987-01-23 Lacroix E Tous Artifices Projectile pour dispersion de munitions
DE3414414A1 (de) * 1984-04-17 1985-10-17 Dynamit Nobel Ag, 5210 Troisdorf Flugkoerper mit einem fernwirkenden gefechtskopf
US4614318A (en) * 1984-07-17 1986-09-30 The Boeing Company Passive separation device and method for finned booster
DE8437159U1 (de) * 1984-12-19 1986-04-10 Diehl GmbH & Co, 8500 Nürnberg Zünder für ein Bomblet
US4750403A (en) * 1986-01-31 1988-06-14 Loral Corporation Spin dispensing method and apparatus
US4676167A (en) * 1986-01-31 1987-06-30 Goodyear Aerospace Corporation Spin dispensing method and apparatus
US4750423A (en) * 1986-01-31 1988-06-14 Loral Corporation Method and system for dispensing sub-units to achieve a selected target impact pattern
DE3608107C1 (de) * 1986-03-12 1987-10-01 Diehl Gmbh & Co Traegerprojektil fuer Submunition
DE3823823A1 (de) * 1988-07-14 1990-01-18 Diehl Gmbh & Co Gefechtskopf
DE3937762C2 (de) * 1989-11-14 1993-11-25 Diehl Gmbh & Co Artilleriegeschoß-Submunition
DE4026813C1 (de) * 1990-08-24 1996-09-26 Rheinmetall Ind Gmbh Flugkörper zur Bekämpfung eines Hubschraubers
US5076511A (en) * 1990-12-19 1991-12-31 Honeywell Inc. Discrete impulse spinning-body hard-kill (disk)
SE9103081L (sv) * 1991-10-23 1993-02-08 Bofors Ab Saett att fraan en skyddskanister separera substridsdelar samt skyddskanister
FR2684754B1 (fr) * 1991-12-10 1995-04-07 Thomson Brandt Armements Obus dont le culot fait office de pot de parachute d'une sous-munition.
DE19517844A1 (de) * 1995-05-16 1996-11-21 Diehl Gmbh & Co Dispenser zur Verbringung von Submunition über ein Ziel
DE19630796C2 (de) * 1996-07-31 1998-07-09 Diehl Stiftung & Co Verbringungseinrichtung für großkalibrige Submunition
US6302359B1 (en) * 2000-04-13 2001-10-16 Capewell Components Company Limited Partnership Free fall payload distribution device and method
SE540780C2 (sv) 2016-04-06 2018-11-06 Bae Systems Bofors Ab Delningsbar granat med fallskärmsanordning
US10508892B1 (en) * 2016-08-15 2019-12-17 The United States Of America As Represented By The Secretary Of The Navy Distributed fuze architecture for highly reliable submunitions
SE541612C2 (sv) * 2016-09-15 2019-11-12 Bae Systems Bofors Ab Modifierbar delningsbar projektil och metod för att modifiera en projektil
SE2300079A1 (en) * 2023-09-25 2025-03-26 Bae Systems Bofors Ab Projectile and method for distributing submunitions

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3221656A (en) * 1964-03-23 1965-12-07 Adrian P Sutten Apparatus for high-velocity recovery
DE1208220B (de) * 1960-04-30 1965-12-30 Heinrich Klein Dr Ing Gefechtskopf fuer einen angetriebenen Flugkoerper
FR1533978A (fr) * 1967-06-13 1968-07-26 Thomson Houston Comp Francaise Projectile perfectionné à charge utile devant être libérée en un point de la trajectoire
FR1579025A (fr) * 1968-06-17 1969-08-22
DE2004637A1 (de) * 1970-02-03 1971-08-12 Dynamit Nobel Ag, 5210 Troisdorf Gefechtskopf
FR2144917A5 (fr) * 1971-07-02 1973-02-16 Serat
FR2159034A5 (fr) * 1971-10-29 1973-06-15 Dynamit Nobel Ag
US3797394A (en) * 1972-09-11 1974-03-19 Thiokol Chemical Corp Chaff dispenser, method of dispersing chaff
US3834312A (en) * 1973-03-14 1974-09-10 Bofors Ab Parachute-borne flare assemblage
FR2392355A1 (fr) * 1977-05-27 1978-12-22 Lacroix Tous Artifices E Charge eclairante lancee a effet continu
EP0020226A1 (fr) * 1979-05-23 1980-12-10 Thomson-Brandt Dispositif de transport et de largage d'une pluralité de charges contenues dans un conteneur

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1365865A (en) * 1918-06-27 1921-01-18 Jaroslav A Svejda Illuminating-projectile
US3113752A (en) * 1962-01-23 1963-12-10 Aeronca Mfg Corp Parachute control apparatus
DE2654827A1 (de) * 1976-12-03 1978-06-08 Rheinmetall Gmbh Mittels eines traegergeschosses verschiessbare hohlladungstochtergeschosse
US4333400A (en) * 1980-02-01 1982-06-08 The United States Of America As Represented By The Secretary Of The Navy Two stage parachute fuze recovery system

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1208220B (de) * 1960-04-30 1965-12-30 Heinrich Klein Dr Ing Gefechtskopf fuer einen angetriebenen Flugkoerper
US3221656A (en) * 1964-03-23 1965-12-07 Adrian P Sutten Apparatus for high-velocity recovery
FR1533978A (fr) * 1967-06-13 1968-07-26 Thomson Houston Comp Francaise Projectile perfectionné à charge utile devant être libérée en un point de la trajectoire
FR1579025A (fr) * 1968-06-17 1969-08-22
DE2004637A1 (de) * 1970-02-03 1971-08-12 Dynamit Nobel Ag, 5210 Troisdorf Gefechtskopf
FR2144917A5 (fr) * 1971-07-02 1973-02-16 Serat
FR2159034A5 (fr) * 1971-10-29 1973-06-15 Dynamit Nobel Ag
US3797394A (en) * 1972-09-11 1974-03-19 Thiokol Chemical Corp Chaff dispenser, method of dispersing chaff
US3834312A (en) * 1973-03-14 1974-09-10 Bofors Ab Parachute-borne flare assemblage
FR2392355A1 (fr) * 1977-05-27 1978-12-22 Lacroix Tous Artifices E Charge eclairante lancee a effet continu
EP0020226A1 (fr) * 1979-05-23 1980-12-10 Thomson-Brandt Dispositif de transport et de largage d'une pluralité de charges contenues dans un conteneur

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0794405A1 (fr) * 1996-03-08 1997-09-10 DIEHL GMBH & CO. Procédé et dispositif pour disperser une charge utile de gros calibre au-dessus d'un objectif
US5760330A (en) * 1996-03-08 1998-06-02 Diehl Gmbh & Co. Method and apparatus for conveying a large-calibre payload over an operational terrain

Also Published As

Publication number Publication date
DE3111907A1 (de) 1982-10-07
CA1216774A (fr) 1987-01-20
DE3276340D1 (en) 1987-06-19
EP0062750B1 (fr) 1987-05-13
US4498393A (en) 1985-02-12

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