GB2494060A

GB2494060A - Missile device

Info

Publication number: GB2494060A
Application number: GB1215181.7A
Authority: GB
Inventors: Simon Mckay; Paul Jefferson
Original assignee: SPEX KINETICS Ltd
Current assignee: SPEX KINETICS Ltd
Priority date: 2011-08-26
Filing date: 2012-08-24
Publication date: 2013-02-27
Anticipated expiration: 2032-08-24
Also published as: US20140238222A1; WO2013030557A1; GB2494061A; GB2494060B; GB201215181D0; WO2013030558A1; GB201215182D0; GB2494061B; GB201114805D0

Abstract

A missile device 10 comprises a longitudinally extending body 12 defining a fore 14 and an aft region 16. A first driving plate 30, 32 is movably coupled to the aft region 16 for receiving a launching force and transmitting the launching force to the body 12 to propel the body 12 towards a target. A force absorbing member 34 operatively interposes the body 12 and the first driving plate 30, 32 so as to reduce or limit the peak value of the launching force transmitted to the body 12.

Description

Force absorbing means The present invention relates to apparatus for neutralising, rendering safe, or at least impairing the performance of ground ordnance. In particular, but not exclusively, the invention relates to apparatus for neutralising, at least partly excavating, and separating components of improvised explosive devices (tEDs).

The use of explosives to target military forces in conflict is known and mines have been used frequently to attack vehicles and dismounted personnel. Similarly, IEDs have been used by insurgent and terrorist groups for many years.

However, the terms lED' and mine' are not synonymous.

The lED is a device placed oi fabricated in an improvised manner incorporating destructive, lethal, noxious, pyrotechnic or incendiary chemicals and designed to destroy, incapacitate, harass or distract. It is normally constructed from non-military components, and often comprises a number of separate components which are spaced apart. The initiator, power supply, main charge and firing switch of an lED are often packaged separately and thus represent a larger and more complex target to neutralise. There are many variants of IEDs and they are often constructed to a highly variable build standard.

A mine is an integral explosive munition designed to be placed under, on or near the ground or other surface area and to be actuated by the presence, proximity or contact of a person, land vehicle, aircraft, or boat. The military mine most often has all of the principal components packaged into a single container and is built to a more consistent and higher build standard.

Therefore, the lED typically represents a greater threat than a conventional mine.

More recently, particularly in Iraq and Afghanistan, the lED has become the insurgent weapon of choice and is a major cause of casualties, both to coalition forces and the indigenous population. The techniques and weapons that are employed to render safe mines tend to be wholly inappropriate or ineffective for the rendering safe of buried IEDs.

Both mines and IEDs are capable of being initiated in a variety of ways. Time initiation uses mechanical, electronic or chemical means of delay. Command initiation uses physical or electronic means of initiating an explosive charge by remote control. Victim operation relies on some form of stimulus provided by the victim to trigger the explosive charge. The most simple and effective means of victim operated device is the pressure plate, which can be designed to operate when a minimum specific weight is applied to the plate in order to target a specific category of target, for example a single person or a vehicle. The overwhelming majority of IEDs that have been encountered in Afghanistan have been of the victim operated, simple pressure plate variety.

Most IEDs in Afghanistan are buried in the ground and the principal components of the lED such as the initiator, the main explosive charge and container, the firing switch and power supply are not normally visible. This complicates significantly the task of the Explosive Ordnance Disposal (EOD) operator who is required to make the lED safe. The complete burial and camouflaging of the lED components also increases the hazard posed to the EOD operator as he or she may be required to physically touch the ground and soil that is in close proximity to highly sensitive lED components. The ground in which IEDs tend to be buried in Afghanistan is extremely hard and has a high rock content. For most of the year the water content in the soil is very low and this further enhances the hardness of the ground.

A variety of EOD weapons and systems have been developed to assist EOD operators in the rendering safe of IEDs. Most EOD weapons are designed to operate against IEDs that are on the surface and their performance against buried IEDs is sub optimal. On occasion, the use of conventional EOD weapons may even make the lED more hazardous to the EOD operator. Another disadvantage of existing EOD weapons is that they seldom render the lED safe in a single step and require the EOD operator to make multiple approaches to the lED. This is contrary to two of the core principles of lED disposal, which are to minimise the time spent at the lED and to minimise the number of approaches made, in order to reduce the overall level of hazard to which the EOD operator is exposed.

EOD operators are also required to conduct lED render safe operations in environments where there is a significant likelihood that they, their team, and other supporting forces will be attacked by other means by terrorists or insurgents.

It is desirable to provide an apparatus which can be assembled expeditiously and taken into action in a shorter period of time, such as less than five minutes. It is desirable to provide an apparatus which is man portable and does not require the use of special vehicles to be brought into action.

It is desirable to provide an apparatus that can be operated to render safe ground ordnance using a reduced number of stages, such as a single stage, thus reducing the time that the operator is required to spend at the ground ordnance.

It is desirable to provide an apparatus which employs propulsion means capable of penetrating hard ground, thus eliminating the need to disturb the ground immediately adjacent to the ground ordnance or its components.

It is desirable to provide an apparatus which is suitable for use with ground ordnance, such as IEDs, which comprise a number of separate components, one or more of which may be spaced apart from each other. It is desirable to provide an apparatus which employs a warhead component that disrupts, separates and then expels ground ordnance components from the ground.

It is desirable to provide an apparatus which employs a warhead component that can be varied by the operator so as to achieve an initiation rather than a disruptive effect on the ground ordnance main explosive charge.

It is desirable to provide an apparatus which operates in a fail safe mode'.

According to a first aspect of the present invention there is provided a missile device, the missile device comprising: a longitudinally extending body defining a fore and an aft region; a first driving plate movably coupled to the aft region for receiving a launching force and transmitting the launching force to the body to propel the body towards a target; and a force absorbing member operatively interposing the body and the first driving plate so as to reduce or limit the peak value of the launching force transmitted to the body.

The missile device may include a plurality of driving plates arranged in series in a longitudinal direction. A force absorbing member may operatively interpose each adjacent driving plate.

One or more of the material properties, arrangement and the geometry of the force absorbing member may be selected to produce a predetermined peak value, or proportion of the peak value, of the launching force transmitted to the body.

The force absorbing member may comprise a resilient member. The resilient member may be formed from an elastomer. Alternatively, the force absorbing member may comprise a damper, such as a hydraulic damper. The force absorbing member may comprise a low density material.

The missile device may include a propulsion device which includes the first driving plate. The propulsion device may be releasably connected to the body.

The releasable connection may comprise one or both of a Morse taper and a push fit connection.

The piopulsion device may include guide means for constraining movement of the first driving plate in all but the longitudinal direction. The guide means may be adapted to constrain movement of the resilient member in all but the longitudinal direction.

The body may comprise a casing adapted to house an explosive material. The explosive material may comprise C4, PE4 or the like. The casing may be adapted to house up to 300 g of explosive material, preferably up to 250 g.

Alternatively, the explosive material may be a low explosive material. The explosive material may be a non-detonating material. The explosive material may comprise a material which is reactive to produce a high volume of a gas.

The explosive material may comprise a strong oxidising material. The low explosive material may comprise a perchlorate, such as potassium perchlorate or ammonium perchlorate.

The casing may include a plurality of grooves or slots. The grooves or slots may be longitudinally orientated.

The missile device may include an initiator device. The initiator device may be located at the propulsion device and longitudinally extend into the casing. The initiator device may comprise a shock tube.

The first driving plate may be circular. The first driving plate may include an aperture for receiving the initiator device. This assists to constrain movement of the first driving plate in all but the longitudinal direction. The force absorbing member may include an aperture for receiving the initiator device.

The first driving plate may have a first face which is non-normal to the longitudinal axis. The first face may be the exterior or most aft face. The first face may be conical, having an apex which points in the aft longitudinal direction.

The first face may have an orientation which is between 10 and 20 degrees, preferably 15 degrees, to a plane which is normal to the longitudinal axis.

Alternatively, the first face may be convex.

The propulsion device may be adapted to receive the explosive material such that the material is shaped' by the first driving plate. Therefore, the explosive material has a surface which is complementary to the profile of the first face.

The missile device may be adapted for neutralising ground ordnance.

The missile device may include a nose portion provided at the fore region of the body. The nose portion may be pointed for penetrating an intercepting material, such as the ground.

The nose portion may be releasably connected to the body. The releasable connection may comprise one or both of a Morse taper and a push fit connection.

The nose portion may at least partially define a recess for receiving an explosive material. The nose portion may be adapted to allow a user to vary the amount of explosive material within the recess.

Optional features of the first aspect of the present invention may be incorporated into any of the other aspects of the present invention and vice versa.

According to a second aspect of the present invention there is provided an apparatus comprising: a body defining a fore and an aft region; a first driving plate movably coupled to the aft region for receiving a launching force and transmitting the launching force to the body to propel the body away from the first driving plate; and a force absorbing means, operatively interposing the body and the first driving plate so as to reduce or limit the peak value of the launching force transmitted to the body.

The apparatus may include two or more driving plates moveably coupled to the aft region for receiving the launching force and transmitting the launching force to the body, the two or more driving plates may be arranged in series in a longitudinal direction.

A force absorbing means may operatively interpose each adjacent driving plate.

One or more of the material properties, arrangement and the geometry of the force absorbing means may be selected to produce a predetermined peak value, or proportion of the peak value, of the launching force transmitted to the body.

The force absorbing means may be a gap between the two or more driving plates. The gap may be filled with air.

The two or more driving plates may be releasably attached to a frame to maintain a predetermined distance between the two or more driving plates before the launching force is transmitted to the body.

The body may be a longitudinally extending body defining the fore and an aft region.

S

The first or the two or more driving plates may be movably coupled to the aft region for receiving the launching force and transmitting the launching force to the body to propel the body towards a target.

The force absorbing means may be a force absorbing member.

The force absorbing member may comprise a resilient member. The resilient member may be formed from an elastomer. Alternatively, the force absorbing member may comprise a damper, such as a hydraulic damper.

Optional features of the second aspect of the present invention may be incorporated into any of the other aspects of the present invention and vice versa.

According to a third aspect of the present invention there is provided a missile device, the missile device comprising: a longitudinally extending body defining a fore and an aft region; and a first driving plate movably coupled to the aft region for receiving a launching force and transmitting the launching force to the body to propel the body towards a target, wherein the first driving plate has a first face which is non-normal to the longitudinal axis.

The first face may be the exterior or most aft face. The first face may be conical, having an apex which points in the aft longitudinal direction. The first face may have an orientation which is between 10 and 20 degrees, preferably 15 degrees, to a plane which is normal to the longitudinal axis. Alternatively, the first face may be convex.

The missile device may include a propulsion device which includes the first driving plate.

The propulsion device may be adapted for receiving an explosive material. The propulsion device may be adapted to receive the explosive material such that the material is shaped' by the first driving plate.

The missile device may include a force absorbing member operatively interposing the body and the first driving plate so as to reduce or limit the peak value of the launching force transmitted to the body.

The body may comprise a casing adapted to house an explosive material. The casing may include a plurality of grooves or slots. The grooves or slots may be longitudinally orientated.

The missile device may include an initiator device. The initiator device may be located in the recess and longitudinally extend into the casing. The initiator device may comprise a shock tube.

The first driving plate may be circular. The first driving plate may include an aperture for receiving the initiator device.

Optional features of the third aspect of the present invention may be incorporated into any of the other aspects of the present invention and vice versa.

According to a fourth aspect of the present invention there is provided a missile device, the missile device comprising: a longitudinally extending body defining a fore and an aft region and comprising a casing adapted to house an explosive material, wherein the casing includes one or more shaping features to assist the formation of projectiles upon initiation of the explosive material.

The or each shaping feature may be longitudinally orientated so as to produce longitudinally orientated projectiles.

The shaping feature may comprise a plurality of grooves or slots. Alternatively or in addition, the casing may be formed from at least two materials, the first material being more yieldable, brittle or combustible than the second material.

The explosive material may comprise C4, PE4 or the like. Alternatively, the explosive material may be a low explosive material. The casing may be adapted to house up to 300 g of explosive material, preferably up to 250 g.

The missile device may include a first driving plate movably coupled to the aft region for receiving a launching force and transmitting the launching force to the body to propel the body towards a target. The first driving plate may have a first face which is non-normal to the longitudinal axis.

I

The missile device may include a propulsion device which includes the first driving plate. The missile device may include an initiator device. The missile device may be adapted for neutralising ground ordnance.

Optional features of the fourth aspect of the present invention may be incorporated into any of the other aspects of the present invention and vice versa.

According to a fifth aspect of the present invention there is provided an apparatus for neutralising ground ordnance, the apparatus comprising: a longitudinally extending body defining a fore and an aft region and a casing which houses an explosive material; penetrating means to assist the apparatus penetrating the ground in the vicinity of the ground ordnance; and initiating means for causing initiation of the explosive material when the apparatus has penetrated the ground in the vicinity of the ground ordnance, wherein the explosive material comprising a low explosive material such that initiation of the explosive material avoids sympathetic initiation of the ground ordnance.

The explosive material may comprise a material which is reactive to produce a high volume of a gas. The explosive material may comprise a strong oxidising material. The explosive material may comprise a perchlorate, such as potassium perchlorate or ammonium perchlorate.

The ground ordnance may comprise an lED.

The penetrating means may comprise a nose portion provided at the fore region of the body. The nose portion may be pointed for penetrating the ground.

The initiating means may comprise a shock tube.

The apparatus may include a propulsion device. The propulsion device may include a first driving plate movably coupled to the aft region for receiving a launching force and transmitting the launching force to the body to propel the body towards a target.

The apparatus may include a force absorbing member operatively interposing the body and the first driving plate so as to reduce or limit the peak value of the launching force transmitted to the body.

The apparatus may include a plurality of driving plates arranged in series in a longitudinal direction. A force absorbing member may operatively interpose each adjacent driving plate. The first driving plate may have a first face which is non-normal to the longitudinal axis.

Optional features of the fifth aspect of the present invention may be incorporated into any of the other aspects of the present invention and vice versa.

According to a sixth aspect of the present invention there is provided a method of neutralising ground ordnance, the method comprising: providing a missile device comprising a longitudinally extending body defining a fore and an aft region and a casing which houses an explosive material; penetrating the ground with the missile device in the vicinity of the ground ordnance; and initiating the explosive material, wherein the explosive material comprising a low explosive material such that initiation of the explosive material avoids sympathetic initiation of the ground ordnance.

Initiating the explosive material may include detonating the explosive material.

Indeed, the initiation may be a detonation.

Optional features of the sixth aspect of the present invention may be incorporated into any of the other aspects of the present invention and vice versa.

Embodiments of the present invention will now be described, by way of example only, with reference to the accompanying drawings in which: Figure 1 is a sectional side view of a missile device; Figure 2 is a sectional side view of a propulsion device of the missile device of Figure 1; Figure 3 is a sectional side view of a body of the missile device of Figure 1; Figure 4 is a sectional side view of a nose portion of the missile device of Figure 1; Figure 5 is a diagrammatic side view of the missile device of Figure 1 at set up; Figure 6 is a diagrammatic side view of the missile device of Figure 1 following launch; and Figure 7 is a diagrammatic side view of the missile device of Figure 1 following initiation.

Figure 1 shows a missile device 10 which, in this embodiment, is suitable for neutralising ground ordnance in the form of an lED 110. The device 10 comprises three main structural portions: a body 12 or warhead assembly, a propulsion device 20, and a nose portion 50. The device 10 can be fabricated from a variety of materials including one or more of stainless steel, mild steel, titanium, aluminium and composite material.

The longitudinally extending body 12 defines a fore 14 and an aft 16 region. The body 12 also defines a casing 18 adapted to house an explosive material. The explosive material can be a high explosive, such as PE4. However, in another embodiment, the material can be a low explosive.

A propulsion device 20 is provided at the aft region 16 of the body 12 and includes a number of driving plates 30, 32 which are arranged in series in a longitudinal direction and movably coupled to the aft region 16. The plates receive a launching force produced by initiation of the explosive material 100 and sequentially transmit this launching force to the body 12 to propel the body 12 towards a target.

A force absorbing member in the form of a resilient plate 34 made from a rubber material operatively interposes 34A each adjacent driving plate. This reduces or limits the peak value of the launching force transmitted to the body 12 and so assists to maintain the integrity of the body 12. Other low density materials may be employed between the driving plates to achieve the same effect.

The missile device 10 includes an initiator 40. The missile device 10 may be initiated electrically or by a shock tube, depending on the type of initiator employed. The initiator 40 is located at the propulsion device 20 and longitudinally extends into the propelling explosive charge 100. A length of shock tube 42A is embedded in the propelling explosive charge 100 and this tube runs to a second delay initiator which is a delayed initiator embedded in the casing 18.

An electrical wire, or shock tube, 42 is connected to the initiator control 44.

Activation of the initiator control 44 causes initiation of the propelling explosive charge 100. The initiation of the propelling explosive charge 100 causes the shock tube 42A to initiate the delay initiator embedded in the explosive charge in the casing 18.

The driving plates 30, 32 and resilient plates 34 are circular with an aperture for receiving the initiator 40. This provides guide means to constrain movement of the plates in all but the longitudinal direction. The shock tube is embedded in the bulk explosive within the propulsion housing 22 such that the initiator 40 can only be initiated by the initiation of the propelling explosive charge. This prevents the missile device 10 from functioning in the event of a failure in the propelling charge.

The initiator 40 is held in a collar 44, in intimate contact with the main explosive charge, so as to prevent set back during the firing of the propulsion charge. A range of initiator delays may be employed but those in the range of 10 to 100 ms are appropriate for safe use against live lED targets. A number of pins 22 can be inserted within apertures in the collar 44 and then into bores of the propulsion device 20 so that they are arranged circumferentially around the driving plates 30, 32 and resilient plates 34. This provides further guide means for constraining movement of the plates in all but the longitudinal direction. Alternatively, a plastic cup may be employed to provide both environmental protection and a means of securing the driving plates and the propelling explosive charge.

The first driving plate 30 has a first or exterior face 34 which is non-normal to the longitudinal axis. This face 34 is conical, having an apex which points in the aft longitudinal direction and a surface orientation which is 15 degrees to a plane which is normal to the longitudinal axis. The explosive material 100 is packed in contact with the exterior face 34 of the first driving plate 30 so that the material is shaped' by the first driving plate 30. Therefore, the explosive material has a surface which is complementary to the profile of the first face 34. The user can pack the explosive material 100 immediately prior to use and decide upon the amount of material to use.

The shape of the first driving plate 30 is important to achieving reliable performance and the orientation of the exterior face 34 aids focussing of the launching force. The driving plates 30, 32 and resilient plates 34 co-operate to reduce the peak force transmitted to the body 12. These are each sequentially compressed at launch and increase the time over which the force generated by the propulsion system is applied to the body 12. This reduction in the peak force applied to the body 12 maintains the structural integrity of the body 12 and aids in the penetration of very hard ground.

The missile device 10 includes a nose portion 50 releasably connected to the fore region of the body 12. The nose portion 50 is pointed for penetrating the ground. The nose portion 50 defines a recess 52 for receiving an explosive material and the user can vary the amount of explosive material within the recess.

The external surface of the lower section of the body 12 is configured with shaping features in the form of longitudinal grooves 24. These facilitate the creation of linear projectiles 120 upon initiation of the main explosive charge.

The high pressures generated cause the body 12 to expand along its radial axis.

The presence of grooves 24 on the outer surface of the warhead assembly results in the creation of linear explosively formed projectiles 120 as a result of the Misznay-Schardin effect. These high velocity projectiles 120 move out along a radial axis from the warhead assembly and disrupt and separate any lED components in their path. Eventually, the fragments are stopped due to the resistance of the ground.

The high velocity projectiles 120 initially move in front of the blast wave 122. The blast wave 122 follows the projectiles 120 and causes further separation of the lED components. The initiation of the main explosive charge also produces a significant volume of gaseous initiation products, including: carbon monoxide, carbon dioxide, water vapour, nitrogen and various oxides of nitrogen. The rapid expansion of these gases causes the formation of a crater and the expulsion of the lED components and the crater material from the ground.

Using a high explosive, it is more likely that there will be sympathetic initiation of the lED 110. An alternative type of warhead assembly has been developed which does not rely on a initiating explosive to achieve the desired disruptive effect. This non-detonating or low explosive variant employs a main charge based on potassium perchlorate, which when given the appropriate energetic stimulus, generates a high volume of gas. This warhead assembly will not sympathetically initiate an lED main charge, but it will separate components and expel them from the ground.

The body 12 is a user filled item and is only fitted with explosive and the means of initiation immediately prior to use. The quantity of explosive employed can be varied by the user between 50 and 250g, depending on the threat and required effect. To improve the speed of loading and the integrity of filling, the main explosive charge is placed into a number of plastic cylinders, each slightly less than the warhead bore diameter. In an alternative embodiment the main explosive charge is placed into a warhead charge holder which is slightly less than the warhead bore diameter.

The propulsion device 20 is slotted and releasably connected to the body 12 using both a Morse taper 25 and a push fit connection 26. Also, the nose portion is releasably connected to the body 12 using push fit connection. The use of a push fit system and Morse taper improves safety and is quicker to operate when compared to a screw threaded system.

The missile device 10 can therefore be quickly assembled and operated in a short period of time. Also, the device 10 can be used to neutralise ground ordnance in a single stage, reducing the time that the EOD operator is required to spend at the ground ordnance.

The propulsion means used is capable of penetrating hard ground, eliminating the need to disturb the ground immediately adjacent to the ground ordnance or its components.

Figure 5 shows the missile device 10 set up on a stand 60 and targeted at an area of the ground near to an lED 110 which comprises the lED main charge 112, power supply 114 and firing switch 116. The EOD operator 120 is located a safe distance from the lED 110.

The EOD operator 120 operates the initiator control 44 to launch the missile device 10 towards the ground. The device 10 impacts and penetrates the ground as shown in Figure 6. In one embodiment the pins 22 are pivoted outwards by the launching blast and these can be utilised to resist further penetration of the ground when the device 10 is at approximately the correct depth.

After the delay, the main explosive material in the body 12 is initiated. The blast wave 122 creates and carries the longitudinal projectiles 120 radially through the ground. Some of these projectiles 120 impact the lED components, which are disrupted, separated and expelled from the ground by the projectiles 120 or the blast wave 122.

Whilst specific embodiments of the present invention have been described above, it will be appreciated that departures from the described embodiments may still fall within the scope of the present invention.

Claims

<claim-text>Claims 1. A missile device, the missile device comprising: a longitudinally extending body defining a fore and an aft region; a first driving plate movably coupled to the aft region for receiving a launching force and transmitting the launching force to the body to propel the body towards a target; and a force absorbing member operatively interposing the body and the first driving plate so as to reduce or limit the peak value of the launching force transmitted to the body.</claim-text> <claim-text>2. A missile device as claimed in claim 1, including a plurality of driving plates arranged in series in a longitudinal direction.</claim-text> <claim-text>3. A missile device as claimed in claim 2, wherein a force absorbing member operatively interposes each adjacent driving plate.</claim-text> <claim-text>4. A missile device as claimed in any preceding claim, wherein one or more of the material properties, arrangement and the geometry of the force absorbing member may be selected to produce a predetermined peak value, or proportion of the peak value, of the launching force transmitted to the body.</claim-text> <claim-text>5. A missile device as claimed in any preceding claim, wherein the force absorbing member comprises a resilient member.</claim-text> <claim-text>6. A missile device as claimed in any preceding claim, including a propulsion device which includes the first driving plate.</claim-text> <claim-text>7. A missile device as claimed in claim 6, wherein the propulsion device is releasably connected to the body.</claim-text> <claim-text>8. A missile device as claimed in claim 6 or 7, wherein the propulsion device includes guide means for constraining movement of the first driving plate in all but the longitudinal direction.</claim-text> <claim-text>9. A missile device as claimed in claim 8, wherein the guide means is adapted to constrain movement of the resilient member in all but the longitudinal direction.</claim-text> <claim-text>10. A missile device as claimed in any preceding claim, wherein the body comprises a casing adapted to house an explosive material.</claim-text> <claim-text>11. A missile device as claimed in claim 10, wherein the casing is adapted to house up to 300 g of explosive material.</claim-text> <claim-text>12. A missile device as claimed in claim 10 or 11, wherein the explosive material is a low explosive material.</claim-text> <claim-text>13. A missile device as claimed in claim 12, wherein the explosive material comprises a material which is reactive to produce a high volume of a gas.</claim-text> <claim-text>14. A missile device as claimed in claim 13, wherein the explosive material comprises a perchlorate.</claim-text> <claim-text>15. A missile device as claimed in any of claims lOto 14, wherein the casing includes shaping means comprising a plurality of grooves or slots.</claim-text> <claim-text>16. A missile device as claimed in claim 15, wherein the grooves or slots are longitudinally orientated.</claim-text> <claim-text>17. A missile device as claimed in any preceding claim, including an initiator device located at the propulsion device and longitudinally extending into the casing.</claim-text> <claim-text>18. A missile device as claimed in claim 17, wherein the first driving plate is circular and has an aperture for receiving the initiator device.</claim-text> <claim-text>19. A missile device as claimed in claim 17 or 18, wherein the force absorbing member includes an aperture for receiving the initiator device.</claim-text> <claim-text>20. A missile device as claimed in any preceding claim, wherein the first driving plate has a first face which is non-normal to the longitudinal axis.</claim-text> <claim-text>21. A missile device as claimed in claim 20, wherein the first face is the exterior or most aft face.</claim-text> <claim-text>22. A missile device as claimed in claim 20 or 21, wherein the first face is conical, having an apex which points in the aft longitudinal direction.</claim-text> <claim-text>23. A missile device as claimed in any of claims 20 to 22, wherein the first face has an orientation which is between 10 and 20 degrees to a plane which is normal to the longitudinal axis.</claim-text> <claim-text>24. A missile device as claimed in any of claims 6 to 9, wherein the propulsion device is adapted to receive the explosive material such that the material is shaped by the first driving plate.</claim-text> <claim-text>25. A missile device as claimed in any preceding claim, wherein the missile device is adapted for neutralising ground ordnance.</claim-text> <claim-text>26. A missile device as claimed in claim 25, including a nose portion provided at the fore region of the body.</claim-text> <claim-text>27. A missile device as claimed in claim 26, wherein the nose portion is releasably connected to the body.</claim-text> <claim-text>28. A missile device as claimed in claim 26 or 27, wherein the nose portion at least partially defines a recess for receiving an explosive material.</claim-text>