WO2003100345A1

WO2003100345A1 - Dispensers

Info

Publication number: WO2003100345A1
Application number: PCT/GB2003/002204
Authority: WO
Inventors: Philip David Morgans
Original assignee: BAE Systems PLC
Current assignee: BAE Systems PLC
Priority date: 2002-05-23
Filing date: 2003-05-21
Publication date: 2003-12-04
Anticipated expiration: 2004-11-23
Also published as: GB0212145D0; AU2003227961A1

Abstract

A projectile for dispersing elements (28) which utilises cavities (30) within the body of the projectile to house the elements (28), which are released through exit ports (24) when the projectile is in flight.

Description

Dispensers

This invention relates to the field of projectiles used for the dispersion of elements of material whilst in flight.

State of the art methods of providing for the dispersion of elements of mateπal in the form of pellets, tablets or grains and the like rely on means such as the forced projection of a number of such elements from a static tube or a container, or the use of a projectile which either disintegrates in flight or is ruptured or disintegrates on impact scattering or distributing such elements. The term elements shall be taken to mean all types of materials capable of being utilised in accordance with the invention.

The use of such dispersal systems can provide for generally targeted deployment of such elements, but the accuracy of known systems cannot readily be relied upon to provide a repeatable pattern of coverage over a known target area.

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. In such circumstances there may be a requirement for the dispersal of elements of detergent and cleaning chemical pellets or tablets over a specified area, with a specific density of elements required within the area in order to provide for a specific physical or chemical effect.

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.

Accordingly 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,

said at least one cavity having an exit port,

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.

In a first preferred embodiment of the invention each said at least one cavity describes a spiral about an axis substantially co-incident with the axis of rotation of said projectile body.

Preferably in said first embodiment, 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.

In a second embodiment of the invention each said at least one cavity describes a spiral about an axis substantially perpendicular to the axis of rotation of said projectile body.

Preferably in said second embodiment, 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.

In any embodiment of the invention 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.

In a further embodiment of the invention, 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;

at least one cavity within said projectile body,

said at least one cavity having an exit port,

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.

The invention will now be described by way of example only with reference to the following drawings in which:-

Figure 1 - shows a diagrammatic representation of projectile in accordance with a first embodiment of a the invention,

Figure 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.

In figure 1 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.

In the case of a 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) the following methods of rotation initiation and control may be employed, namely:-

1 the initiation of rotation by the projectile launch means itself, for example by such means as rifling the launch tube, or 2 the use of aerodynamic strake means 20 standing proud of the body surface 4 running spirally along the longitudinal axis 8 of the projectile 2, or,

3 the use of gas thrusters to provide said rotation.

In the case of a self propelled projectile, i.e. a projectile which itself comprises or is attached to a propulsion means, the following means of initiating and controlling rotation may be employed, namely:-

1 the use of off axis main propulsion thrusters to generate rotation, or

2 the use of aerodynamic strake means 20 or separate gas thrusters, both as described here above.

In the case of a projectile in accordance with the second embodiment of the invention described herein, a non-limiting example of which is illustrated in figures 4 and 5, 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. Such 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.

It will be readily apparent to the skilled reader that various other state of the art methods may be utilised to provide the required rotation of projectile in accordance with the invention and such methods shall be construed as being incorporated within the scope of the invention as described.

In figure 1 , 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. In an alternative embodiment of the invention shown in Figure 2, 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. In a yet further embodiment of the invention 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. Alternatively such 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).

In the preferred embodiments of the invention 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. Furthermore 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. It will be readily appreciated by the skilled man in the art that 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. In a further embodiment of the invention 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 similarity between the first and second specific embodiments of the invention as illustrated by figures 1 and 4 accordingly serve to emphasise the unity of invention between the two embodiments, the differences residing in the direction of rotation of said projectiles 2 and 36 relative to their directions of flight, i.e. substantially parallel and orthogonally respectively.

Furthermore, the particular arrangement of cavities illustrated in figure 5 represents a embodiment illustrating an increase in the number of cavities illustrated in figure 3

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.

Once all of the cavities 30 within the projectile 2 have been filled and their respective exit ports 24 fitted with retaining means, 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.

When it is required to launch the projectile 2, 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.

When the centrifugal forces acting on the elements 28 within each of said cavities 30 reaches a predetermined limit, 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 characteristics of the launch and dispersal of elements in accordance with the second embodiment the invention as illustrated by figures 4 and 5 will be substantially similar to that of the description relating to Figure 6, the material differences being the apparatus utilised for the launch of said projectile 36 and the fact that the direction of spin of said projectile 36 will be substantially perpendicular to the direction of flight path 50 of said projectile 36.

In any embodiment of the invention 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.

In a yet further alternative embodiment of the invention there are 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. In one further embodiment of the invention, 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.

The embodiments of the invention described herein shall be regarded as representative of the inventive concept and not limiting in their application or scope. Additional embodiments of the invention and all known mechanical equivalents comprised in the state of the art will be readily appreciated by the skilled man and such are be deemed comprised within the scope of the invention.

Claims

1. 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 having an exit port,

2. Apparatus for the dispersal of elements in accordance with claim 1 wherein each said at least one cavity describes a spiral about an axis substantially co-incident with the axis of rotation of said projectile body

3. Apparatus for the dispersal of elements in accordance with claim 1 wherein said at least one cavity describes a spiral about an axis substantially perpendicular to the axis of rotation of said projectile body

4. Apparatus for the dispersal of elements in accordance with claims 1 to 3 wherein said projectile is self-propelled.

5. Apparatus for the dispersal of elements in accordance with claims Λ to 4, wherein said projectile is ballistically launched.

6. Apparatus for the dispersal of elements comprising a plurality of said projectiles in accordance with claims 1 to 5, wherein said projectiles form part of, or are comprised within, a larger projectile.

7. Apparatus for the dispersal of elements in accordance with claims 1 to 6, wherein said projectile is launched from a sea vessel.

8. Apparatus for the dispersal of elements in accordance with claims 1 to 6, wherein said projectile is launched from an airborne platform

9. A method of dispersing elements comprising the use of apparatus in accordance with any of claims 1 to 8.

10. Apparatus for the dispersal of elements substantially as hereinbefore described with reference to the accompanying drawings and description.

11. A method for the dispersal of elements substantially as hereinbefore described with reference to the accompanying drawings and description.