JP2004534202A - Projectiles that deploy subprojectiles radially - Google Patents

Abstract

A projectile (10) fired from a launch tube. The projectile includes a number of firing tube assemblies (12,13,14) radially disposed from a center of the body of the projectile, wherein each of the number of firing tube assemblies includes a plurality of firing tube assemblies. A plurality of sub-projectiles (16) are disposed axially within the tube. Each sub-projectile is associated with a separate propellant charge (17) for propelling the individual sub-projectiles from the launch tube. The projectiles can selectively fire sub-projectiles (16) with the appropriate assistance of a primer (18) each connected to an electronic controller (15), thereby deploying the sub-projectiles Provides a default pattern for the body. The defense system using the projectile will be described together with a method of hiding the launch position of the projectile using the direction change propulsion means.

Description

【Technical field】
[0001]
The present invention relates to the deployment of objects such as projectiles, and in particular, but not exclusively, a parent projectile that forms a predefined pattern of deployed sub-projectiles and hides the projectile launch location. About the method.
[Background Art]
[0002]
Artillery shells combined with explosives have been used as crushing devices to deploy a plurality of projectiles. In a simple construction, the case of such projectiles would be fragmented upon explosion of the explosive, and the individual fragments of the case would radially unfold to form a fragmentation pattern that would form a generally spherical surface.
[0003]
In other constructions, the shape of the powder and the configuration of the case can be varied to control the crushing pattern. However, such fractured projectiles create a relatively thin shell-like debris case pattern. Desirably, the crushing depth can be increased or controlled.
[0004]
Such projectiles are particularly suitable for protecting a given area and avoiding that given area becoming dangerous after the threat situation has been reduced, as is the case with conventional land mines.
[Patent Document 1]
Current defenses against attacks include systems for capturing and monitoring the trajectory of objects, including flying objects such as rockets and missiles. Examples of orbit acquisition and monitoring systems are disclosed in U.S. Patent Nos. 4,622,458 to Boeck et al. And 5,960,097 to Pfeiffer et al.
[0005]
In particular, recent defense systems against threats, such as the characteristics of mortars, which include shells that fire at a relatively large angle to fire at a target point, such as the characteristics of mortars, have been developed from projectile trajectory to projectile launcher The attack source can be calculated by deriving the position of.
DISCLOSURE OF THE INVENTION
[Problems to be solved by the invention]
[0006]
Purpose of the invention
It is an object of one embodiment of the present invention to provide a projectile that can be used to deploy sub-projectiles in a predetermined pattern that eliminates the conventional problems by providing increased or controlled debris. At least provide a viable choice for defense purposes.
[0007]
It is another object of one embodiment of the present invention to provide a defense system that improves control over projectile deployment and prevents certain areas from becoming unsafe for later use by non-combatants.
[0008]
It is an object of another embodiment of the invention to change the direction of the projectile during flight, thereby making it impossible or at least difficult to derive the position of the projectile launcher, Provide a defense system that can hide the location of
[Means for Solving the Problems]
[0009]
Disclosure of the invention
According to a first aspect of the present invention, there is provided a number of launch tube assemblies radially disposed from a center of a projectile body. Each of the multiple launch tube assemblies comprises a plurality of sub-projectors axially disposed within the launch tube, each sub-projector having a separate sub-projector for firing individual projectiles from the launch tube. It also has a propellant, and each projectile selectively fires a sub-projectile to provide a predefined pattern of deployed sub-projectiles.
[0010]
Desirably, the projectile of the present invention is not a self-propelled missile fired from a gun barrel or gantry, but is particularly suited for deployment by firing from a gun barrel. In other embodiments, the projectiles of the present invention can be deployed by dropping from a mobile platform such as an aircraft or ship using gravitational forces for dropping, or thrown by conventional hand. Suitable for throwing by military personnel or defense officials as well as grenades.
[0011]
A projectile of the present invention suitable for launching from a launch tube can be used, in a first aspect, for intercepting and destroying particularly advanced ballistic missiles. In a second aspect, the present invention provides a method for intercepting a missile. The method includes the steps of determining a missile path, firing a projectile of the type described herein onto the missile path, and launching a selected sub-projectile into and within the missile determined path. Forming a predefined pattern of sub-projectiles nearby.
[0012]
The projectile of the present invention can be used for self-defense of a vehicle. Vehicles, especially those that arrive under attack from the enclosed area, will fire the projectile described here toward the attacking person and place the projectile within the attacker. Can be expanded in the default pattern. In a third aspect, the present invention provides a method for self-defending a vehicle from an offensive. The method includes the steps of determining the location of the offensive power, firing the projectile described herein near the determined location of the offensive power, and firing the selected sub-projectile to determine the location of the offensive power. Forming a predefined pattern of sub-projectiles in and near.
[0013]
The projectile of the present invention can be used to intercept infantry units. In a fourth aspect, the present invention provides a method for repelling infantry units. The method includes the steps of determining the position of an infantry unit, firing at least one of the projectiles described herein near the determined position of the infantry unit, and firing the selected sub-projectile to enable infantry Forming a predefined pattern of sub-projectiles within and near the determined location of the unit.
[0014]
The present invention can be used to form a flight image such as an anti-aircraft fire. In a fifth aspect, the present invention provides a method for forming a flight image. The method includes firing a projectile described herein into the air, and firing a selected sub-projectile containing the image-forming object to form a predetermined pattern of the image-forming object in the air.
[0015]
The projectile of the present invention can be used for fire fighting. In a sixth aspect, the present invention provides a fire fighting method. The method includes the steps of determining the location of a fire, firing at least one of the projectiles described herein near the location of the fire, and launching the selected sub-projectile to determine the location of the fire. Forming a predefined pattern of or near the sub-projectile and deploying a fire retardant from the launched sub-projectile.
[0016]
The projectile of the present invention can be used to generate a vapor explosion. In a seventh aspect, the present invention provides a method for generating a vapor explosion. The method includes selecting a desired location for a vaporization explosion, firing at least one of the projectiles described herein near the desired location for the vaporization explosion, and selecting a selected sub-projectile including fuel. To form a predefined pattern of sub-projectiles, spraying fuel from the sub-projectiles, and firing selected sub-projectiles, including the detonator, to form a predefined pattern of hub projectiles And exploding the detonator to generate a vaporized explosion.
[0017]
The projectile of the present invention can be used to deploy a payload. The present invention provides a method for deploying a payload. In an eighth aspect, the method comprises selecting a desired location for launch of the payload, launching at least one of the projectiles described herein near a desired location of the payload, Launching a predefined pattern of sub-projectiles, and deploying a payload from the launched sub-projectiles.
[0018]
The projectile of the present invention can be used to protect a predetermined area. In a ninth aspect, the present invention relates to a system for protecting a roughly designated area. The system is
At least one monitoring device for monitoring a predetermined area to detect an area where a new advance appears;
A defensive means comprising a weapon capable of repelling an intruder present in a remote predetermined area and firing a projectile, wherein the projectile is arranged radially from the center of the body of the projectile. An array of fired tube assemblies, each projectile tube assembly having a plurality of second or sub-projectiles radially disposed within the fired tube, the sub-projectiles being continuous from the fired tube. An array of firing tube assemblies comprising individual propellants for firing sub-projectiles, the array of firing tube assemblies selectively firing the sub-projectiles from the selected firing tube. Defense means by which the projectile can deploy a predefined pattern of sub-projectiles;
Communication means for providing communication between the monitoring device and the defense means for selectively activating the defense means and performing a repulsive attack on the detected area.
[0019]
The monitoring device includes one or more on-site sensors located on a remote sensor device located within or remote from the predetermined area. As another example, the monitoring device may include both on-site and remote sensor devices.
[0020]
The monitoring device can also provide a visual indication of the predetermined area being monitored so that, if necessary, a manual override device can be activated to manually control the configured protection device. it can.
[0021]
Multiple secondary or sub-projectiles can be fired simultaneously from multiple launch tubes or instantaneously consecutively from one projectile. In such a configuration, the electron firing signal can be transmitted via circuitry from outside the firing tube. Alternatively, the electron firing signal can be transmitted via a laminated sub-firing tube. The sub-projectiles may be tied together and connected to an electronic circuit through a launch tube, or the sub-projectiles may be adjacent in electrical contact with one another. Each of the sub-projectiles may include a control circuit.
[0022]
The array of launch tube assemblies can be located near the rear or leading end of the projectile to effectively change the attitude of the projectile, or to displace the projectile laterally. It can also be located in the center. In another example, the directional control system can include an array of launch tube assemblies at both the leading and trailing ends of the projectile.
[0023]
An array of firing tube assemblies or each array can fire sub-projectiles in a direction having an axial component to provide a necessary increase in kinetic energy of the projectile, or Each array of assemblies can also fire sub-projectiles in a direction having a component that is longitudinally tangential to the missile axis to impart or change the rotation of the projectile about the missile axis. . The launch tube assembly may launch a second projectile in a direction across the plane of flight, such as a wing, to cause an additional steering effect on the projectile. In another example, the launch tube assembly may extend through the plane of the airfoil to launch in both directions. This can add structural strength to the aerodynamic design.
[0024]
If desired, a spaced-apart or opposing array of launch tube assemblies can be provided to control the rotation of the projectile about the projectile's longitudinal axis. The arrangement of the arrangement comprises opposed pairs of launch tube assemblies that are fired simultaneously to cause rotation only about the longitudinal axis of the projectile. A second projectile is fired from the directional control system to negate the effect on the projectile of rotation about its longitudinal axis or to selectively utilize the sub-projector before and / or after use. Can be launched.
[0025]
In one embodiment of the present invention, the energy required to change the attitude and / or flight direction of the parent projectile is provided by firing sub-projectiles from one or more selected launch tube assemblies. can do.
[0026]
According to a second aspect of the present invention, there is provided a method of hiding a launch location of a projectile launch device. The method comprises the step of firing at least one projectile from a firing tube assembly, wherein the firing tube assembly has a firing tube, and a plurality of projectiles are radially disposed within the firing tube. A firing step, wherein the firing tube assembly also has a separate propellant charge for sequentially and individually firing projectiles from the muzzle of the firing tube. And firing at least one sub-projectile from an array of diverting propulsion assemblies incorporated therein while the at least one projectile is in flight, and wherein each diverting propulsion assembly includes a diverting propulsion firing. A step having a plurality of sub-projectiles radially disposed within the tube, the sub-projectile being associated with a second individual propellant for sequentially firing the sub-projectiles from a turning propulsion firing tube. And the turning propulsion launch tube assembly Column, can be selectively firing sub-projectiles from diverting launch tube body selected, thereby including a step of promoting the projectile, by the reaction generated by the firing of sub-projectiles.
[0027]
The sub-projectile is the target on which the second propellant is actuated, and the reaction force acts on the transition propulsion launch tube transition piece, so the overall shape of the sub-projectile is strictly critical. is not. In the context of that aspect of the invention, the transition piece may be formed by a subsequent sub-projectile in sealing engagement with the turning propulsion launch tube within the launch tube. The reaction force is transmitted to the projectile from the transition piece of the second or turning propulsion launch tube, thereby accelerating the projectile.
[0028]
The array of firing tube assemblies can be radially arranged from the center of the projectile body. Such a launch tube assembly configuration is particularly suitable for objects not incorporated into a flight propulsion system, such as rockets and missiles. The firing of the sub-projectile simply displaces the projectile, without which the projectile continues to travel on its orbit.
[0029]
The invention has particular application to self-control systems in areas that are vulnerable to ammunition fired from pods, such as mortars. Of course, it will be appreciated that the invention also has application in identifying the launch location of other projectiles or fire systems.
[0030]
In the preferred embodiment, a clear trajectory can be selected to derive an attack from the launcher at another enemy location.
[0031]
The projectile of the present invention can desirably utilize a launch tube assembly of the type disclosed in International Patent Applications Nos. PCT / AU94 / 00124 and PCT / AU96 / 00449. Such a firing tube assembly includes a firing tube, a plurality of sub-projectors axially disposed within the firing tube operatively sealingly engaging the firing tube bore, and a firing tube gun. A separate propellant for sequentially firing the individual sub-projectiles from the mouth.
[0032]
The sub-projectile can be a sphere, a conventional shape or a dart-like, and its fins can be offset to form a smooth fired-bore launch tube. A stabilizing spin can be generated when a dart is fired from. If necessary, the projectile with the sub-projectile may be substantially cylindrical, oval or spherical.
[0033]
The propellant charge is shaped like a solid block and the sub-projectile is placed in the launch tube, or the propellant charge has an external contact member that contacts a pre-positioned electrical contact with the launch tube It can be surrounded by a metal or other rigid case that can be provided with an embedded primer. For example, the primer can be shrunk so that the cased explosive can be inserted into the projectile, and the projectile can be aligned with the contact of the engaging projectile with the gun cavity that is in operation. The gun cavity may be provided with a spring-loaded contact to release. If necessary, the outer case can be a consumable or it can be a chemical aid in the combustion of the explosive. Further, an explosive and sub-projectile assembly, stacked and glued or housed in separate cases, can be provided to refill the launch tube.
[0034]
Each sub-projectile may include a head and an enlarged portion for at least partially defining a powder space. The enlarged portion extends rearward from the head portion and may include a spacer assembly that strikes an adjacent sub-projectile assembly.
[0035]
The spacer assembly extends through the explosive space and the head, so that the compressible powder is conveyed directly through the abutting spacer assembly. In such a configuration, the spacer assembly adds reinforcement to the enlarged portion that becomes the thin cylindrical rear portion of the head. Further, the enlarged portion can form an operable sealing contact with the projectile bore to prevent combustion leakage through the sub-projectile.
[0036]
The spacer assembly can include a rigid collar that extends outwardly to engage a thin cylindrical rear portion of the malleable head that does not make sealing contact with the firing bore of the firing tube body, The axially compressible gunpowder can be carried directly between the spacer assemblies to prevent deformation of the malleable head.
[0037]
Complementary wedge surfaces can be located on each of the spacer assembly and the head to engage the head with the projectile bore in response to relative axial compression between the spacer and the head. . In such an arrangement, the head and spacer assembly can be incorporated into the projectile, after which an axial displacement occurs to create a good seal between the sub-projectile and the projectile. It is desirable to have the flared portion engage the firing tube bore.
[0038]
The head defines a tapered shape hole at its rear end, into which a complementary tapered shape plug located at the distal end of the spacer assembly is inserted, between the head and the complementary tapered plug. Relative axial movement of the sub-projectile exerts a radially expanding force.
[0039]
The launch tube may be non-metallic and the bore of the launch tube may include a recess to accommodate all or a portion of the igniter. In that configuration, the launch tube houses an electrical conductor that facilitates electrical communication between the control device and the ignition device. This configuration can be used for a disposable firing tube assembly with limited ignition life, and the igniter and control wires can be made integral with the firing tube.
[0040]
The launch tube assembly may have an ignition hole in the launch tube and the igniter may be located outside the launch tube and near the hole. A non-metallic outer firing tube having a recess suitable for accommodating the igniter may surround the firing tube. The outer firing tube may surround an electrical conductor that facilitates electrical communication between the control device and the ignition device. The outer firing tube may be formed like a laminated plastic firing tube that includes a thin layer of printed circuit board for the igniter.
[0041]
The launch tube assembly has adjacent sub-projectiles, which are spaced apart from each other and held in a spatially separated relationship by an arrangement member spaced from the sub-projectile. Each sub-projectile may include an expandable sealing means that forms an operative seal with the bore of the launch tube. The locating member may be a propellant charge between adjacent sub-projectiles, and the sealing means includes a skirt on each sub-projectile that expands outwardly when subjected to a launch tube internal load. The firing tube internal load is exploited during installation of the sub-projectiles or after loading by packing the sub-projectiles and the propellant rows in an integrated manner, or the outer sub-projectiles, especially adjacent outer projectiles. Caused by firing.
[0042]
The rear end of the sub-projectile may include a skirt around the recess that decreases inward, such as a conical recess or partial sphere, into which the propellant charges extend, Around it, the rearward movement of the sub-projectile results in a radial expansion of the skirt of the sub-projectile. The rearward movement is caused by the pressure created by the rearward wedge movement of the sub-projectile along the propellant tip. It can also result from metal deformation from the relatively heavy tip of the sub-projectile to its lightly weighted skirt.
[0043]
In another example, the sub-projectile has a rearward diverging sealing flange or collar that deflects outwardly into sealing engagement with the gun bore when rearward movement of the sub-projectile occurs. Can be prepared. In addition, the seal may be affected by inserting the sub-projectile into a heated firing tube that has been shrink-fitted to make a secure connection with the individual seal portion of the sub-projectile. The sub-projectile includes a relatively stiff main shaft portion located near the propellant charge and cooperating with a deformable annulus, the annulus being integrally formed about the main shaft portion to form an integral unit. A sub-projectile is formed, which relies on metal deformation to expand outwardly about a main shaft that sealingly engages the bore of the launch tube between the tip of the sub-projectile and its tail.
[0044]
The sub-projectile assembly includes a rearwardly extending anvil surface, which retains a seal collar therearound and, upon movement of the sub-projectile forward through the firing tube, the firing tube body cavity. It expands radially to make a seal engagement. In such a configuration, it is desirable for the propellant to have a cylindrical tip that abuts the flat end surface of the sub-projectile.
[0045]
The sub-projectile is located in the annular groove or by an annular rib in the gun cavity or in a striation groove in the gun cavity, surrounding at least the outer end portion of the sub-projectile. A metal jacket may be provided. The sub-projectile can be provided with a contractible outer rim placement ring, which extends outwardly into an annular groove in the launch tube and also has a free passage through the launch tube When the sub-projectile is fired to allow for, it shrinks towards that sub-projectile.
[0046]
The electrical ignition for continuously igniting the propellant charge of the launch tube assembly preferably ignites the forward propellant charge by sending an ignition signal through the stacked sub-projectiles and the propulsion of the forward charge. Preparing for the explosion of the next propellant charge to function with the next ignition signal by the firing of the explosive. Desirably, all propellants inward from the end of the loaded launch tube can be prepared for explosion by inserting respective insulating fuses, usually located between closed electrical contacts.
[0047]
Ignition of the propellant charge can be accomplished electrically, or ignition can be accomplished in a conventional firing pin type manner, such as a central firing primer to ignite the outermost subprojectile and subsequent firing of the propellant charge of the subsequent round. Controlled continuous ignition can be used. Controlled aft leakage of the combustion gases or controlled combustion of the fuse array extending through the sub-projectiles can achieve this.
[0048]
In another embodiment, the ignition is electrically controlled with the individual propellant associated with the primer triggered by the individual ignition signal. For example, the primers in the stacked propellant charge can be arranged in a certain order to increase the pulse width ignition demand, whereby the electronic control unit selectively sends and selects the ignition pulse of increased pulse width. The propellant can be ignited continuously in a time sequence. Preferably, however, the propellant charge is ignited by a set of pulse width signals and prepares the next propellant charge so that combustion of the propellant charge at the tip will function with the next output pulse.
[0049]
Desirably in such an embodiment, all propellant powder inward from the end of the loaded launch tube will explode by inserting respective insulating fuses, usually located between closed electrical contacts. And the fuses are set to burn to close the contacts when the appropriate trigger signal is delivered, and each insulated fuse is propelled at its individual tip for ignition by it. Open to
[0050]
In one embodiment, a high pressure muzzle firing tube assembly may be used, but the firing tube assembly may be of a low pressure type, which fires a sub-projectile such as a grenade. Individual firing tube assemblies can be loaded with different sub-projectiles, and the firing tube assemblies can have different sized calibers to accommodate different sized projectiles.
[0051]
Desirably, each sub-projectile has a trailing edge collar attachable to the body of the sub-projectile and, when retracted in the firing tube, is driven rearward so as to wedge the distal end of the body of the trailing-edge sub-projectile. Extending towards. Desirably, the shallow wedge provides a wedge effect, whereby in use the tail of the collar expands into operative sealing engagement with the firing tube.
[0052]
A tail collar can be provided for limited axial movement of the sub-projectile relative to the body, and the distal end of the collar has an annular shape that engages a complementary surface formed on the sub-projectile. Of the sub-projectile, caused by the reaction of the propellant gas, causes a rearward movement of the main body of the sub-projectile to apply a force to its complementary surface to seal the annular projecting surface with the annular sealing surface at the tip of the collar An engagement is formed.
[0053]
The complementary surface and the annular sealing surface can extend substantially radially, and they form complementary sealing features. However, it is preferred that the surfaces be complementary partially conical sealing surfaces that wedge in such a way as to provide a tight sealing engagement with each other. The tip may extend into sealing engagement with the launch tube. Preferably, however, the wedge portion between the partial conical upper surfaces is a relatively steep slope, whereby the tip of the collar extends into sealing engagement with the firing tube by wedge action. do not do.
[0054]
In low pressure applications, each projectile is desirably connected to a high pressure propellant charge chamber, which is an individual low pressure propellant charge formed between adjacent projectiles for effective muzzle slow operation. Exhaust the chamber. The high pressure propellant chamber may be formed integrally with the body or trailing edge collar of the sub-projectile, and may be provided external to the projectile and communicate therewith via a port through the wall of the projectile. It may be.
[0055]
Preferably, the structure of the space in which the ignited propellant spreads and the performance of the propellant are such that only a low pressure of the firing tube, such as about 2,000 psi to 5,000 psi, is generated in use. Typically, the collar is of such a degree that it does not impede the free movement of the projectile in the firing tube for mounting purposes or during firing in a tension-free position.
[0056]
A pressure pad is provided inside the open trailing edge end of the housing. The collar is repositioned out of engagement when the propellant charge is ignited and is maintained unstressed by the pressure pad so as to pass through the firing tube and exit the muzzle of the firing tube.
[0057]
The projectiles may be of a conventional type, fired in a conventional manner, or preferably fired from a firing tube assembly, which comprises a plurality of projectiles axially disposed within the firing tube body, each projectile being Have a separate propellant charge for firing the projectile from a launch tube.
[0058]
In a preferred embodiment, the projectile is generally spherical and has a number of launch tube assemblies arranged radially from the center of the sphere. The firing tube assemblies may be the same or different. For example, a large diameter launch tube may be positioned from the center of a spherical projectile. A smaller diameter launch tube may be positioned between the larger diameter launch tubes to provide maximum sub-projectile density of the projectile. It is desirable to provide the projectile with maximum launch tube packing density, ie, launch capability. As another example, it may be desirable to provide the projectiles with different firing tube bores to use sub-projectors of different diameters.
[0059]
The projectile may be a saboted projectile for a reduced caliber projectile to provide an advantageous deployment. Spherical projectiles can be subtended into more convenient shapes so that they can be fired from conventional deployment systems in conventional bullet shapes. In another example, if it is desired to provide increased muzzle velocity, the sabotted projectile may contain increased propellant charge without requiring an abnormal firing tube length. it can.
[0060]
The launch tube assembly radially disposed from the center of the projectile body allows the projectile to deploy the sub-projectiles in a normal and easy control manner. A launch tube assembly radially disposed from the center of the projectile body allows the projectile to maintain its attitude. By deploying the sub-projectile in a manner that would apply zero resultant reaction force to the projectile, the projectile can be maintained on a desired orbit.
[0061]
A number of sub-projectiles can be fired simultaneously or instantaneously in succession. In such a configuration, electrical signals can be transmitted from outside the launch tube, or can be interconnected and connected to an electrical circuit via the launch tube, or abutted to make electrical contact with each other. The electric signal is transmitted via such a sub-projectile loaded. The sub-projectiles have control circuitry, or they can form a circuit with the launch tube.
[0062]
The projectiles of the present invention can deploy sub-projectiles in a predefined pattern that can be selected for a particular application. For example, to intercept and destroy an oncoming missile, it may be desirable to deploy the sub-projectiles to increase the likelihood of one or more sub-projectiles impacting the missile. A fragmentation system (fragment bomb system) is used to disperse projectile fragments into the path of the incoming missile. However, such a system for detonating a projectile generally creates a band of spreading debris and forms an expanding spherical bullet. The projectile can deploy the sub-projectiles of the present invention in a more uniform manner throughout the space occupied by the predetermined pattern. By controlling the timing of firing of the sub-projectiles, a three-dimensional "fragment grenade" pattern with a substantially uniform array of sub-projectiles can be established. Alternatively, the sub-projectiles may be concentrated at locations where they are more likely to intercept missiles to increase the effectiveness of the deployed sub-projectiles.
[0063]
The sub-projectile may comprise a material that forms a flight image. The image-forming substance may be, for example, an explosive substance, a flammable substance, an incandescent or luminescent substance, which provides a temporary image with high visibility. In another example, the image forming material can include particles or sheets or strips having characteristics such as smoke, gas, chaff, materials that can diffuse to form an image, and the like. Accordingly, the projectiles of the present invention can be advantageously used to launch countermeasures from military aircraft. The image forming material may also include means for slowing down from the diffusion position, such as a parachute.
[0064]
The subprojectile is positioned within the launch tube assembly such that once fired and the imaging material is deployed, the desired temporal aerial image is formed. Sub-projectiles containing image forming materials of different colors or shapes can be sequentially loaded into each launch tube assembly.
[0065]
The imaging material can be deployed, for example, to expose the imaging material to the outside by explosive devices, stored energy or separation of a separable portion of the sub-projectile, or by other suitable dispersing devices.
[0066]
The image forming material may be contained within a suitably configured housing that encloses the image forming material and engages the rear end of the expandable collar of the prior projectile. Desirably, the housing is of a type used with projectiles such as grenades having a relatively squat configuration, although projectiles having long housings may be utilized.
[0067]
The housing may be suitably formed from biodegradable and / or flammable materials. The material may be of natural origin, such as wood chips, or synthetic, such as a biodegradable polymer.
[0068]
Advantageously, the projectiles of the present invention can deploy selected sub-projectiles to control the path of the projectile. Such deployment is known as a turnaround propulsion system and can be used to affect limited modification of the projectile's position to deploy the remaining sub-projectiles in a desired pattern.
[0069]
The projectile of the present invention may also be suitably used in a defense system of the type disclosed in applicant's International Application No. PCT / AU00 / 01351.
BEST MODE FOR CARRYING OUT THE INVENTION
[0070]
In order to make the present invention easier to understand and to obtain practical effects, reference will be made to the accompanying drawings illustrating preferred embodiments of the present invention.
[0071]
FIG. 1 shows a projectile (or bullet) 10 with six large diameter launch tubes 12 of suitable internal diameter. However, only four are shown in the sectional view. The remaining two large launch tubes (which extend in a direction perpendicular to the drawing) are depicted as 11. The cross-section also shows a medium diameter firing tube 13 with a medium diameter and a small diameter firing tube 14 with a relatively small inside diameter. Each of the launch tubes of the large diameter hole 12, the medium diameter hole 13, and the small diameter hole 14, as shown, includes sub-projectiles 16 arranged along a plurality of axes. Attached to these sub-projectiles is a propellant charge 17 and an igniter 18, which can ignite sequentially under the control of an electronic controller 15. In some embodiments, projectile 10 may also include explosives for a terminal explosion.
[0072]
The electronic controller 15 is, in this embodiment, located at the center of the projectile 10 behind the launch tubes 11, 12, and may include a sensor for tracking an approach missile during flight. As another example, electronic controller 15 may receive a firing command from a remote tracking station via a communication link. Thereby, successive firings of multiple sub-projectiles can be coordinated to obtain an improved probability of hitting a similar target, such as a targeted approach missile.
[0073]
FIG. 2 shows a projectile of the type shown in FIG. 1 with a projectile 20 in which sub-projectiles have been omitted for clarity. The projectile 10 is held in a firing tube inside a projectile 20. The ammunition barrel comprises a forward ammunition cylinder section 21, a rear ammunition cylinder section 22, and an enlarged sleeve 23 provided around a chamfered rear surface 24 of the rear ammunition cylinder section. Due to the explosion and firing of the propellant in front of the front feed cylinder 21, the rear feed cylinder 22 is pressed against the enlarged sleeve 23, and the enlarged sleeve is brought into close contact with the tube of the parent firing tube.
[0074]
FIG. 3 shows a series of projectiles 10 fired from a parent launch tube assembly 30 having a plurality of parent launch tubes 31, 32, and 33. The projectile 10A is fired from the firing tube 33, and its projectile (sabot) (not shown) is cut off. The projectile 10B is fired from the firing tube 32, and the state in which the projectile 20 is cut off is shown. The enlarged sleeve 23 is separated from the rear projectile cylinder 22, and the rear projectile cylinder 22 is also separated from the projectile 10B. The forward feed cylinder 21 is similarly separated from the projectile 10B. The projectile 10C is newly fired from the launch tube 31, and the projectile 20 has begun to separate from the projectile 10C.
[0075]
4 and 5, it can be seen that the designated area 40 to be protected is monitored by the field sensor 41. The field sensors 41 are located throughout the designated area and may be of any suitable type, such as pressure, acoustic or seismic type sensors.
[0076]
The illustrated defense system 42 employs weapons in the form of a pair of ammunition boxes 43, each of which uses a firing tube assembly 30 connected to a remote detection unit 44 and It is also connected to a receiver unit 49 associated with the sensor 41. In this embodiment, the remote sensing unit 44, which is mounted like a tower, sweeps to monitor entry into the designated area 40 by humans, vehicles or other intruders using electro-optic or micro-techniques. Suitable for.
[0077]
The receiver unit 49 is suitable for receiving signals from an array of field sensors 41 using radio frequency (RF) in this embodiment (although cable links may be used in another example). When an intrusion is detected in the area 40, the intruded area is separated and the projectile 10 fired from the bullet box 43 attacks. That is, the designated area 40 is monitored by one or both of the arrangement of the field sensors 41 and the remote detection unit 44.
[0078]
It is desirable that each bullet box 43 be placed in a substantially hidden position, such as in a hole in the ground. Once assembled, the hole in which the projectile box is located can be backfilled without damaging the launch tube assembly 30 therein. Alternatively, the fly box 43 can be hidden in the bush and can be adjusted by a screw jack 48 which is connected to a holding base 47 for the fly box.
[0079]
An auxiliary control circuit 43a (see FIG. 5), provided as a plug-in connection to the fly box 43, is installed on site rather than during transport to maintain weapons security during transport. When the control circuit 43a is installed, the weapon is ready for ignition according to the control provided by the detection unit 44 and / or the receiver unit 49. The control circuit can communicate with the electronic controller 15 of the individual projectile as needed.
[0080]
The central remote sensor 44 shown in FIG. 5 is connected to a number of bullet boxes 43 via individual control circuits 43a. In use, if an intrusion into the detected area is detected in any of the areas shown as 50 to 59, the selected bullet box 43 is moved to that particular area. One or more projectiles 45 can be activated to fire. The individual projectiles 45 of the sub-projectiles can be ignited in a pre-selected order or by remote control to form a predetermined pattern of deployed sub-projectiles. The appropriate pattern of the sub-projectile is selected depending on the state of penetration.
[0081]
An intruder into designated area 40 may take any of a number of forms, and may consist of multiple intruders. The intruder is often a soldier in the form of an infantry or walking army. Alternatively, intrusion may be performed by manned or unmanned vehicles such as armored vehicles or tanks. An intruder may have an elaborate defense system that can track the trajectory of incoming bullets to calculate the location of the launcher, and thus attack a hidden launcher. The defense system of this embodiment can divert the trajectory of the projectile by firing the sub-projectile, thereby tracking the apparent trajectory and obscuring the true location of the launcher. If possible, an apparent trajectory can be selected and directed to the defense system 42 to direct an enemy attack to another enemy location.
[0082]
Although the above defense system is located on the ground, another aspect of the invention relates to launches that may be referred to as at sea. Those at sea can launch from ships, float on the sea, and be activated for remote control or autonomous operation using self-contained sensor systems including radar, sonar, or infrared sensors. Rows of stabilizing or anchoring devices, such as suspended weights, can be lined up to form a marine defense circle that can be activated or deactivated as needed.
[0083]
In another aspect of the deployment, the projectiles of the present invention can fall from an aircraft, such as a helicopter. A stabilizing or anchoring device, such as a spike, may be provided to hold the projectile fixedly in place on the ground. The first layer of the sub-projectiles may include a sensor system for initiating the detection of the presence of an enemy army or vehicle, which may be required by the projectiles of the next layer of the individual launch tubes of the projectile. Can engage in response. Additional sensors can be provided on other layers to investigate the outcome of the engagement.
[0084]
Another mode of deployment provides a projectile of a size that can be used as if it were hand held and thrown, similar to a conventional grenade. However, by incorporating the sub-projectile into the launch tube of the hand-throwable projectile, it can be used in a repetitive mode with a predefined time delay or remote control equipment. This can provide certain advantages in wars in urban areas or in combats that occur in enclosed spaces such as terrain, including caves and basements. The sub-projectile must combine a non-military ammunition with a voice declaration system, possibly in siege, to warn that additional ammunition can be fired if the enclosed enemy does not immediately surrender. Can be.
[0085]
The projectiles of the present invention can be transported into space and, if necessary, can be put into orbit around a planet or moon, in effect including a satellite. Since the launch tube assemblies can be radially dispersed within a generally spherical body, they modify the position of the satellite, protect certain areas of the expensive satellite from space debris, meteorites, etc. It works very effectively to engage spacecraft or satellites. The repositioning can be done very quickly in a low gravity environment, by dissipating energy by firing a solid sub-projectile, rather than a gas jet like a conventional satellite. The satellite's projectile is properly crafted to burn and deplete upon re-entry into the atmosphere following an orbital decline.
[0086]
In one particular configuration, the satellite may be comprised of a superprojectile, which may deploy a projectile of the present invention from a launch tube assembly radially disposed therein. Deployed projectiles can themselves have sub-projectiles, thereby providing a two-stage defense system. The two-tiered defense system can of course be used in other appropriately sized applications.
[0087]
It is to be understood that the foregoing has been presented by way of example only, and that modifications and variations which are obvious to those skilled in the art are intended to be within the broad scope and boundaries of the invention as defined by the appended claims. Should.
[Brief description of the drawings]
[0088]
FIG. 1 is a sectional view of a projectile according to a preferred embodiment of the present invention.
FIG. 2 is a cross-sectional view of a saboted projectile for use in a launch tube assembly having a plurality of axially disposed saboted projectiles.
FIG. 3 is a cross-sectional view of the launch of the suspended projectile shown in FIG. 2;
FIG. 4 is a side view of a defense system according to another embodiment of the present invention.
FIG. 5 is a perspective view of a defense system according to still another embodiment of the present invention.

Claims (39)

A plurality of firing tube assemblies radially arranged from the center of the body of the projectile, each of the plurality of firing tube assemblies including a plurality of sub-projectors axially disposed within the firing tube. Comprising a number of launch tube assemblies comprising:
Each sub-projectile has a separate propellant for firing individual projectiles from the launch tube, each projectile selectively firing a sub-projectile, and defining a deployed sub-projectile. A projectile that fires at a target, providing a pattern of The projectile of claim 1, wherein the projectile can fire from a barrel. 3. The projectile of claim 2, wherein the plurality of sub-projectiles are axially disposed within the barrel for effective sealing engagement with the barrel of the barrel. A projectile according to any one of claims 1 to 3, wherein the projectile is substantially spherical and has a number of firing tube assemblies radially arranged from the center of the sphere. 5. The projectile of claim 4, wherein the projectile has different types of different diameter launch tubes so that the projectile can use different diameter sub-projectors. 6. The projectile of claim 4 or 5, wherein a relatively large diameter launch tube is arranged from the center of said spherical projectile, and further a relatively small diameter launch tube is said relatively large diameter launch tube. A projectile positioned between the projectiles to maximize the density of sub-projectiles within the projectile. 7. The projectile of claim 1, wherein the projectile comprises a projectile. The projectile according to any one of claims 1 to 7, further comprising an electronic control unit for controlling ignition of the propellant. 9. The projectile of claim 8, wherein a number of sub-projectiles can be fired simultaneously or instantaneously in succession. 10. The projectile of claim 8 or 9, wherein the multiple launch tube assemblies are arranged to fire the sub-projectile with a minimum resultant reaction force on the projectile, whereby: A projectile capable of maintaining a desired trajectory. The projectile of claim 8, further comprising a sensor for tracking an enemy or intruder. 9. The projectile of claim 8, wherein the electronic controller receives an ignition indication from a remote tracking station via a communication link. 13. Projectile according to any of the preceding claims, wherein the sub-projectile is arranged to change or control the trajectory of the projectile. A method of intercepting a missile, determining a path of the missile, firing the projectile of any one of claims 1 to 13 onto the path of the missile, and firing a selected sub-projectile to the missile. Forming a predefined pattern of sub-projectiles in and near the determined path of the sub-projector. 14. A method of self-defending a vehicle from an attacking unit, wherein the step of determining the position of the attacking unit and the step of firing the projectile according to claim 1 near the determined position of the attacking unit. Firing a selected sub-projectile to form a predetermined pattern of sub-projectiles within and near the determined location of the attacking unit. 14. A method of repelling an infantry unit, wherein the step of determining a position of the infantry unit and the step of firing at least one of the projectiles according to any one of claims 1 to 13 near the determined position of the infantry unit. Firing a selected sub-projectile to form a predetermined pattern of sub-projectiles within and near the determined location of the infantry. 14. A method of forming a flight image, comprising: launching the projectile of any one of claims 1 to 13 in the air; and launching a selected sub-projectile including the image-forming object in the air. Forming a predefined pattern of A firefighting method, comprising: determining a location of a fire; firing at least one of the projectiles of any of claims 1 to 13 near the determined location of the fire; Firing a body to form a predefined pattern of sub-projectiles at or near the determined location of the fire. 14. A method for generating a vaporized explosion, the step of selecting a desired location of the vaporized explosion, and firing at least one of the projectiles of any of claims 1 to 13 near the desired location of the vaporized explosion. Firing a selected sub-projectile containing fuel to form a predetermined pattern of sub-projectiles; dispersing fuel from the sub-projectile; and selecting a sub-projectile including a detonator And forming a predetermined pattern of hub projectiles, and detonating the initiator to generate a vaporized explosion. 14. A method for deploying a payload, comprising selecting a desired location for launch of the payload, and placing at least one of the projectiles of any of claims 1-13 near the desired location of the payload. A method comprising: firing; firing a sub-projectile including the payload to form a predefined pattern of sub-projectiles; and deploying the payload from the launched sub-projectile. A defense system for defending a predetermined area,
At least one monitoring device that monitors the predetermined area to detect an area where a new advance appears;
A defense means comprising a weapon capable of repelling an intruder present in a remote predetermined area and firing a projectile, wherein the projectile comprises:
An array of firing tube assemblies radially disposed from a center of the projectile body, wherein each projectile tube assembly has a plurality of second or sub-projectiles radially disposed within the firing tube. An array of launch tube assemblies wherein the sub-projectiles comprise individual propellants for sequentially firing the sub-projectiles from the launch tube;
The array of firing tube assemblies can selectively fire the sub-projectiles from a selected firing tube, whereby the projectiles can develop a predefined pattern of sub-projectiles. , Defenses,
A communication means for providing communication between the monitoring device and the defense means for selectively activating the defense means, and performing a repulsive attack on the detected area. 22. The defense system of claim 21, wherein the monitoring device comprises one or more on-site sensors located on a remote sensor device located within or away from the predetermined area. 23. The defense system of claim 21 or 22, wherein the monitoring device provides a visual indication of the predetermined area being monitored to activate a manual release device as needed to enable manual control of the weapon. A defense system that provides equipment. 24. The defense system according to any one of claims 21 to 23, wherein a plurality of sub projectiles can be fired simultaneously from a plurality of launch tubes or instantaneously continuously from one projectile. 25. The protection system according to claim 24, wherein the electronic firing signal is transmitted from outside the firing tube via a circuit. 25. The protection system of claim 24, wherein the electronic firing signal is transmitted via a laminated sub-firing tube. 27. The defense system of claim 26, wherein the sub-projectiles are connected to each other and to the electronic circuit via the launch tube. 27. The defense system of claim 26, wherein the sub-projectiles are adjacent to each other in electrical contact with each other. 25. The defense system of claim 24, wherein each of the sub-projectiles comprises a control circuit. 30. The defense system of any of claims 21 to 29, wherein the array of firing tube assemblies is arranged near an end of the projectile to effectively alter the attitude of the projectile. A defense system with a body. 31. The defense system according to any of claims 21 to 30, wherein the array of launch tube assemblies comprises a centrally located launch tube for laterally displacing the projectile. 32. The defense system of any of claims 21 to 31, wherein each array of the firing tube assemblies sub-fires in a direction having an axial component to provide a necessary increase in kinetic energy of the projectile. A defense system that can fire the body. 32. The defense system of any of claims 21 to 31, wherein each array of the launch tube assemblies has an axis of the projectile to impart or change rotation of the projectile about the projectile axis. A defense system that can fire a sub-projectile in a direction with a longitudinal tangential component. 34. The defense system of any of claims 21 to 33, wherein at least some of the launch tube assemblies launch a second projectile in a direction across the plane of flight, such as a wing, to provide additional control of the projectile. Can cause a defense system. 34. The protection system of any of claims 21 to 33, wherein at least some of the launch tube assemblies extend through the plane of the airfoil to fire in both directions. 34. The defense system of any of claims 21 to 33, wherein a spaced apart or opposed arrangement of launch tube assemblies is provided for controlling rotation of the projectile about the longitudinal axis of the projectile. Defense system. 37. The defense system of claim 36, wherein the arrangement of arrangements comprises opposing pairs of launch tube assemblies that are fired simultaneously to cause rotation only about the longitudinal axis of the projectile. 38. The defense system of any of claims 21 to 37, wherein the energy required to change the attitude and trajectory of the projectile is provided by firing a sub-projectile from a selected launch tube assembly. system. A method of shielding a launch position of a projectile launch device,
(A) firing at least one projectile from a launch tube assembly, wherein the launch tube assembly has a launch tube, and wherein a plurality of projectiles are radially disposed within the launch tube; A separate propellant charge for effective sealing engagement with the firing bore of the launch tube and for the firing tube assembly to fire projectiles sequentially and individually from the muzzle of the firing tube. Having a firing step;
(B) said at least one projectile launches in flight at least one sub-projectile from an array of diverting propulsion assemblies incorporated therein, and each diverting propulsion assembly comprises a directional propulsion assembly; A second individual propellant charge having a plurality of sub-projectiles radially disposed within a launch tube for firing the sub-projectiles continuously from the turning propulsion launch tube. Steps associated with
(C) the array of turning propulsion firing tube assemblies can selectively fire the sub-projectiles from the selected turning firing tube, whereby the projectiles can Propelled by the reaction generated by the launch of the projectile.