[go: up one dir, main page]

WO2003100345A1 - Distributeurs - Google Patents

Distributeurs Download PDF

Info

Publication number
WO2003100345A1
WO2003100345A1 PCT/GB2003/002204 GB0302204W WO03100345A1 WO 2003100345 A1 WO2003100345 A1 WO 2003100345A1 GB 0302204 W GB0302204 W GB 0302204W WO 03100345 A1 WO03100345 A1 WO 03100345A1
Authority
WO
WIPO (PCT)
Prior art keywords
projectile
elements
dispersal
accordance
cavity
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.)
Ceased
Application number
PCT/GB2003/002204
Other languages
English (en)
Inventor
Philip David Morgans
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.)
BAE Systems PLC
Original Assignee
BAE Systems PLC
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 BAE Systems PLC filed Critical BAE Systems PLC
Priority to AU2003227961A priority Critical patent/AU2003227961A1/en
Publication of WO2003100345A1 publication Critical patent/WO2003100345A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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

  • This invention relates to the field of projectiles used for the dispersion of elements of material whilst in flight.
  • An example of the use of a system where targeted dispersal of elements of material is required is that of oil slick dispersal on water.
  • the invention described herein provides both the apparatus and a method for enabling the targeted dispersal of elements of material and further provides for the dispersal of said elements at a specific density.
  • the invention provides apparatus for the dispersal of elements, comprising a projectile body designed to rotate whilst in flight, said body comprising; at least one cavity within said projectile body,
  • said at least one cavity being designed to accommodate a plurality of elements of material
  • each said exit port having a retaining means for retaining said elements of material within said at least one cavity, said retaining means being so designed to allow said elements of material to be released through said exit port when said projectile is in flight.
  • each said at least one cavity describes a spiral about an axis substantially co-incident with the axis of rotation of said projectile body.
  • the projectile body is of substantially tubular axisymmetric shape and is designed to rotate about axis substantially co-incident with the flight path of said projectile whilst in flight.
  • each said at least one cavity describes a spiral about an axis substantially perpendicular to the axis of rotation of said projectile body.
  • the projectile body is of substantially disc axisymmetric shape and is designed to rotate about an axis substantially perpendicular to the flight path of said projectile body.
  • a projectile in accordance with any embodiment of the invention may be ballistically launched.
  • the projectile may be self-propelled. In any embodiment of the invention the projectile may be launched from an airborne platform or a sea vessel.
  • a plurality of said projectiles may form part of, or may be comprised within, a larger projectile.
  • the invention further provides a method of dispersing elements comprising the use of apparatus for the dispersal of elements, said apparatus comprising a projectile body designed to rotate whilst in flight, said body comprising;
  • said at least one cavity being designed to accommodate a plurality of elements of material
  • each said exit port having a retaining means for retaining said elements of material within each said at least one cavity, said retaining means being so designed to allow said elements of material to be released through said exit port when said projectile is in flight.
  • Figure 1 - shows a diagrammatic representation of projectile in accordance with a first embodiment of a the invention
  • FIG. 2 - shows a diagrammatic representation of an alternative first embodiment of a projectile in accordance with the invention
  • Figure 3 - shows a diagrammatic representation of section A-A in Figure 1
  • Figure 4 - shows a diagrammatic representation of a projectile in accordance with a second embodiment of a the invention
  • Figure 5 - shows a diagrammatic representation of section B-B in Figure 4
  • Figure 6 - shows a diagrammatic representation of the in-flight dispersal of elements of material using a projectile in accordance with the first embodiment of the invention as described.
  • a projectile in accordance with a first preferred embodiment of the invention is shown 2, said projectile typically having an body surface 4, an aerodynamic nose cone 6, and a longitudinal axis 8 about which the projectile body is substantially axisymmetric.
  • the projectile 2 is shown being of substantially tubular axisymmetric shape, but this is feature should not be construed as limiting and any other shape capable of containing such cavities 30 (shown at figure 3) and corresponding elements of material 28 shall be considered encompassed within the scope of the invention.
  • the projectile 2 may typically comprise a plurality of fin means 10 to provide the aerodynamic forces required to rotate the projectile 2 about its longitudinal axis 8 whilst in-flight.
  • the fins 10 are shown in a deployed position but equally may be of a design which provides for said fins 10 to be maintained in a collapsed position folded against the body of the projectile 2 whilst in storage or held within a launch tube. Once the projectile is propelled into flight such fins 10 comprising a collapsing mechanism will deployed into position by the action of a spring mechanism or the like acting on the fin 10.
  • bal.istically launched projectile ballistically launched being construed herein as meaning the launch of a projectile which utilises energy imparted it at launch to follow its flight path and trajectory
  • rotation initiation and control may be employed, namely:
  • one mechanism by which the rotation of the substantially 'disc' shaped projectile may be initiated may be by the use of a projectile launch mechanism similar to that used for the launching of clay pidgins as used by shotgun enthusiasts.
  • a launch mechanism would offer the capability of propelling a substantially disc shaped projectile in a targeted direction whilst imparting spin to the projectile at a known rotation rate.
  • a plurality of exit ports 12 are shown in a substantially straight line at spaced positions along the length of the projectile body 4.
  • Each of said exit ports 12 are shown having a corresponding exit, thereby describing a plurality of pairs of said exit ports 16, each exit port of said pair 16 being positioned substantially 180 degrees apart around the circumference of said body 4, each of said exit port pairs 16 being located at substantially the same position along the length of said longitudinal axis 8 of said body 4.
  • each pair of said exit ports 16 are so positioned along the length of said body 4 so as to describe a spiral.
  • Each of said pair of exit ports 16 are maintained in a substantially 180 degree spaced relationship around the circumference of said body surface 4, the angular position of each adjacent exit port pair 16 relative to the next being increased by an angular increment for each said pair 16 so as to provide for a helical type arrangement of exit port holes 22 running the length of the projectile body.
  • the angular increment for each of said adjacent pairs of exit hole 16 may be random.
  • Figure 3 is a section A-A through the projectile 2 shown in Figure 1 , the section passing through the centre of a pair of exit ports 16.
  • a pair of spiral cavities 30 are shown having exit ports 24, each of said exit ports 24 having corresponding retaining means 26 to retain the elements 28 within said cavities until required to be distributed.
  • the means of retention 26 may comprise a hermetic seal to help protect any elements held within said cavities 30 from the effects of moisture ingress and the like.
  • the elements 26 are slideably insertable and removable within said cavities 30 and one filled with the desired number and type of elements 28, each of said cavities 30 may be covered or sealed by a retaining means 26.
  • the selection of the type of retaining means 26 utilised will depend of the required storage time for the projectile prior to use and the physical and chemical characteristics of the elements to be held within said cavities 30 and eventually deployed.
  • Typical types of retaining means 26 may include, but are not limited to, plastic, synthetic material or metallic covers which are designed to rupture or be displaced when the force exerted on such a cover by the centrifugal force acting on the elements 28 held within a cavity 30 reaches a pre-determined level.
  • covers may be designed to be detached by the action of launching the projectile 2, such detachment being provided by such means as physical connection (i.e. wires of the like) or in a yet further embodiment covers may be designed to be detached by aerodynamic forces acting on them following the launch of the projectile 2 (i.e.' torn off' by the action of the fluid flow over them).
  • the geometry of the spiral cavities is be so designed to provide for the progressive increasing radial acceleration of elements within the cavity 30, the motivation for the movement of the elements 28 being provided by the forces generated by the in-flight rotation if the projectile 2.
  • the elements 28 are shown in the preferred embodiment as spherical, but the invention applies equally to use of non-spherical elements and references to the use of spherical elements 28 should not be construed as limiting.
  • the primary geometric consideration to be met when selecting elements for use with the invention is that said elements can pass down the cavities 30 under the action of the forces generated by the rotation of the projectile and if required rupture the retaining means 26.
  • different types of elements 28 may be combined within one cavity 30, or alternatively such different elements 28 may be loaded into separate cavities 30 of the same projectile 2.
  • the area 32 surrounding the centre of projectile 2 running along the longitudinal axis 8 is shown hollow. This area may be used to house fuel for propulsion in a self-powered embodiment of the invention, or alternatively may be provided for mounting a ballistically launched version of the projectile 2 on a guide rail or pole. Alternatively the central core 32 of the projectile 2 may remain as a void for the purposes of weight saving.
  • Figure 4 shows a diagrammatic view of the side of a substantially disc shaped projectile 36 in accordance with a second preferred embodiment of the invention.
  • the outer surface of the body of the said disc projectile 38 comprises a plurality of exit ports 40, the physical characteristics of said exit ports 40 being substantially the same as those of the exit ports 16,24 described with reference to figure 3 above.
  • Figure 4 illustrates an example of an embodiment comprising 2 layers of exit ports 40 and corresponding cavities 42, but the number of exit ports 40 and corresponding cavities 42 may be increased.
  • the embodiment described in figure can be created by combining a plurality of projectiles as illustrated in figure 4 into a 'tubular' projectile arrangement, with the addition of the features of a nose cone 6 and fin assembly 10.
  • a projectile 2 comprises a plurality of individual projectile elements 36 which when assembled together form the body of said projectile 2
  • Figure 5 shows a diagrammatic representation of a section B-B through the disc projectile 36 shown at figure 4.
  • the physical characteristics of the elements comprised in the description of the section A-A in figure 3 are substantially the same as for the elements comprising the section B-B shown in figure 5, wherein the cavities 42 correspond to said cavities 30, the exit ports 40 correspond to said exit ports 16,24, elements 28 correspond to said elements 44, and retaining means 46 correspond to said retaining means 26. All corresponding references to characteristics, features and the alternative arrangements of elements comprised in the description shall be construed as being equally applicable to the corresponding references described here above.
  • the chemical composition of said elements 28 may be selected to produce a wide range of effects depending, on the nature of the task for which they are being utilised. Such effects may include but are not limited to the dispersion of oil on water, or for example the dispersion of. a chemical composition which reacts with water to produce a physical effect (i.e. effervescence, localised heating, cooling or luminescence).
  • Figure 6 shows a diagrammatic representation of the launch a projectile 2 in accordance with the invention and the representation of the dispersal of elements 28 whilst in-flight.
  • a launch tube 34 is shown onboard a sea vessel 48, the launch tube 34 being the means for providing the ballistic launch of a projectile 2
  • Cavities 30 are provided along the length of the body 4 of the projectile 2 and are each filled with elements 28. Following their filling, the exit ports 24 of each of said cavities 30 are covered with a retaining means 26 by way of a plastic cover plate to prevent the elements 28 held within the each of the cavities 28 from being released until the projectile 2 is in-flight.
  • the projectile 2 is lowered into the launch tube 34 with the projectile's fin means 10 folded towards the body 4 of the projectile 2 against mechanical spring pressure.
  • the lunch tube firing mechanism (not shown) propels the projectile 2 out of the launch tube 34 and the fin means 10 are deployed by spring action.
  • the forward in-flight motion of the projectile through the air acts aerodynamically on the fin means 10 to rotate the projectile 2 thereby generating centrifugal forces on each of said elements of material 28 held within said cavities 30.
  • the projectile 2 is shown rotating in the sense 50 indicated, along a longitudinal axis substantially co-incident with its flight path 52.
  • the retaining means 26 at the exit ports of each of the cavities 26 are displaced and the elements within are dispersed whilst the projectile is in flight.
  • the rotation of the projectile 22 and the geometry of the spiral cavities 30 provide the forces required to propel each of the elements 28 away from the body of the projectile, thereby providing the dispersion of said elements 28 both along the longitudinal axis of the direction of travel of the projectile 2 and perpendicular to its path.
  • the density of elements dispersed, distance away from the launch site at which the dispersion begins and the perpendicular distance away from the path of the projectile to which elements can be dispersed can be adapted by changing the following characteristics of the projectile, namely:-
  • Density control - factors include number of pairs of cavities filled and forward speed of the projectile
  • Dispersion distance start away from launch tube - factors include rupture / displacement strength of the retaining means, speed of launch, fin rotation speed design;
  • Perpendicular distance away from track - factors include rotation speed (i.e. fin design etc), speed of launch, material element mass and geometry of cavity spiral.
  • the direction of spin of the projectile may be the same as that of the direction of said spiral or alternatively may be in a sense opposite to the direction of said spiral.
  • a plurality of spiral cavities wherein certain of said cavities are formed the opposite sense, for example, each alternate spiral may be manufactured in an opposite direction.
  • This particular embodiment of the invention may offer advantages it certain circumstances over particular ranges of spin velocity or forward track velocity of a projectile.
  • a plurality of projectiles in accordance with the invention may be housed within he body of a larger projectile and deployed from said larger projectile whilst in flight. This would provide for even greater dispersion of elements over both a greater range and wider track.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)

Abstract

Cette invention a trait à un projectile destiné à disperser certains éléments (28), projectile dans le corps duquel ont été ménagées des cavités (30) contenant lesdits éléments (28) qui sont expulsés par des orifices de sortie (24) lorsque le projectile est en vol.
PCT/GB2003/002204 2002-05-23 2003-05-21 Distributeurs Ceased WO2003100345A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU2003227961A AU2003227961A1 (en) 2002-05-23 2003-05-21 Dispensers

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0212145A GB0212145D0 (en) 2002-05-23 2002-05-23 Dispensers
GB0212145.7 2002-05-23

Publications (1)

Publication Number Publication Date
WO2003100345A1 true WO2003100345A1 (fr) 2003-12-04

Family

ID=9937473

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2003/002204 Ceased WO2003100345A1 (fr) 2002-05-23 2003-05-21 Distributeurs

Country Status (3)

Country Link
AU (1) AU2003227961A1 (fr)
GB (1) GB0212145D0 (fr)
WO (1) WO2003100345A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019108105A1 (fr) * 2017-11-28 2019-06-06 Bae Systems Bofors Ab Dispositif et procédé pour obtenir un motif de dispersion horizontale

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1350339A (en) * 1919-10-13 1920-08-24 Richards James Edwin Shell
GB1588114A (en) * 1969-11-19 1981-04-15 Messerschmitt Boelkow Blohm Airborne projectile container
US6279482B1 (en) * 1996-07-25 2001-08-28 Trw Inc. Countermeasure apparatus for deploying interceptor elements from a spin stabilized rocket
WO2003006915A1 (fr) * 2001-07-11 2003-01-23 Metal Storm Limited Projectile permettant de deployer radialement des sous-projectiles

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1350339A (en) * 1919-10-13 1920-08-24 Richards James Edwin Shell
GB1588114A (en) * 1969-11-19 1981-04-15 Messerschmitt Boelkow Blohm Airborne projectile container
US6279482B1 (en) * 1996-07-25 2001-08-28 Trw Inc. Countermeasure apparatus for deploying interceptor elements from a spin stabilized rocket
WO2003006915A1 (fr) * 2001-07-11 2003-01-23 Metal Storm Limited Projectile permettant de deployer radialement des sous-projectiles

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019108105A1 (fr) * 2017-11-28 2019-06-06 Bae Systems Bofors Ab Dispositif et procédé pour obtenir un motif de dispersion horizontale
KR20200097738A (ko) * 2017-11-28 2020-08-19 비에이이 시스템즈 보포즈 아베 수평 분산 패턴을 제공하는 디바이스 및 방법
JP2021504669A (ja) * 2017-11-28 2021-02-15 ベーアーエー・システムズ・ボフォース・アクチエボラグＢａｅ Ｓｙｓｔｅｍｓ Ｂｏｆｏｒｓ Ａｂ 水平分散パターンを提供するための装置および方法
JP7178419B2 (ja) 2017-11-28 2022-11-25 ベーアーエー・システムズ・ボフォース・アクチエボラグ 水平分散パターンを提供するための装置および方法
US11725918B2 (en) 2017-11-28 2023-08-15 Bae Systems Bofors Ab Device and method for obtaining a horizontal dispersion pattern
KR102662185B1 (ko) 2017-11-28 2024-04-29 비에이이 시스템즈 보포즈 아베 수평 분산 패턴을 제공하는 디바이스 및 방법
IL274922B1 (en) * 2017-11-28 2024-08-01 Bae Systems Bofors Ab Device and method for obtaining a horizontal dispersion pattern

Also Published As

Publication number Publication date
GB0212145D0 (en) 2002-12-18
AU2003227961A1 (en) 2003-12-12

Similar Documents

Publication Publication Date Title
US8661981B2 (en) Weapon and weapon system employing the same
EP0718590B1 (fr) Munition à éclats ayant un déploiement radial à faible vitesse avec motif prédéterminé
US10401135B2 (en) Penetrator munition with enhanced fragmentation
JP3065669B2 (ja) 水中の目標に対して使用するための航学力学的に安定した弾丸システム
EP0747660B1 (fr) Projectile comportant des moyens pour disperser des éléments radialement selon une distribution prédéterminée
US3935817A (en) Penetrating spear
US3903804A (en) Rocket-propelled cluster weapon
US20100282053A1 (en) Deployable projectile
EP0502221A1 (fr) Projectile rayé avec des propriétés aérodynamiques améliorées
US7690311B1 (en) Non-lethal projectile with flowable payload
US6957609B2 (en) Method and device for dispersing submunitions
WO2003100345A1 (fr) Distributeurs
US11725918B2 (en) Device and method for obtaining a horizontal dispersion pattern
US7284490B1 (en) Rod warhead systems and associated methods
JP2007508524A (ja) 地雷防護システム
US7100513B2 (en) Programmable pyrotechnic projectile and methods for producing firework patterns therewith
US3408935A (en) Flexible line delivery method and device for chemical and incapacitating agents
KR820002065Y1 (ko) 탄 약
JPH10501881A (ja) 水中の目的に対して使用するためのジャイロスコープ効果で安定にされた弾丸システム

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NO NZ OM PH PL PT RO RU SC SD SE SG SK SL TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): GH GM KE LS MW MZ SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LU MC NL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG

121 Ep: the epo has been informed by wipo that ep was designated in this application
DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
122 Ep: pct application non-entry in european phase
NENP Non-entry into the national phase

Ref country code: JP

WWW Wipo information: withdrawn in national office

Country of ref document: JP