CN1653313A - Projectile for radially deploying sub-projectiles - Google Patents
Projectile for radially deploying sub-projectiles Download PDFInfo
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- CN1653313A CN1653313A CNA028138457A CN02813845A CN1653313A CN 1653313 A CN1653313 A CN 1653313A CN A028138457 A CNA028138457 A CN A028138457A CN 02813845 A CN02813845 A CN 02813845A CN 1653313 A CN1653313 A CN 1653313A
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
- F41H11/00—Defence installations; Defence devices
- F41H11/02—Anti-aircraft or anti-guided missile or anti-torpedo defence installations or systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A19/00—Firing or trigger mechanisms; Cocking mechanisms
- F41A19/58—Electric firing mechanisms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A19/00—Firing or trigger mechanisms; Cocking mechanisms
- F41A19/58—Electric firing mechanisms
- F41A19/68—Electric firing mechanisms for multibarrel guns or multibarrel rocket launchers or multicanisters
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
- F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
- F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
- F42B12/70—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies for dispensing radar chaff or infrared material
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
A projectile (10) for firing from a barrel, said projectile including a multiplicity of barrel assemblies (12, 13, 14) radially disposed from the centre of mass of the projectile, wherein each of said multiplicity of barrel assemblies includes a plurality of sub-projectiles (16) axially disposed within a barrel; each of said sub-projectiles associated with a discrete propellent charge (17) for propelling a respective sub-projectile from the barrel, wherein said projectile is capable of selectively firing sub-projectiles (16), suitably with the aid of primers (18) each coupled to an electronic controller (15), to provide a predetermined pattern of deployed sub-projectiles. A defence system employing projectiles of the type described is also disclosed, together with a method for disguising the launch location of a projectile utilising divert propulsion.
Description
Technical field
The present invention relates to scatter has the object of projectile character, special but and non-exclusive, relate to and utilize female projectile to form the predetermined sub-projectile pattern that scatters, also relate to a kind of projectile launch method that is used to shelter the projectile launch position simultaneously.
Background of invention
The projectile that contains explosive has been used as fragment and has killed and wounded device (fragmentationdevice), and this fragment kills and wounds device in order to many shell fragments that scatter.In a kind of simple form, in case ignition charge, the shell of this projectile just is split into fragment, makes single shell fragment radially scatter, thereby forms the shell fragment pattern on almost spherical surface.
In other structure, can change the shape of explosive and the structure of shell, with control fragment pattern.But this fragment projectile can only produce a kind of broken shell pattern that approaches, is similar to shell.People wish to increase or to control the thickness of this fragment.
This projectile is particularly suitable for being used for defending the appointed area, can avoid simultaneously threat location is eliminated after the danger that becomes of this zone, and this situation can occur in for example traditional minefield.
The existing system that is used for defensive attack generally includes and is used to catch and the system of monitor objects track, and this object comprises flyer for example rocket and guided missile.Track is caught and the example of surveillance is described in people's such as people's such as Boeck U.S. Patent No. 4,622,458 and Pfeiffer the U.S. Patent No. 5,960,097.
Recently, the accurate system of defense that is used to defend to threaten can be derived the position of projectile firing apparatus according to the track of projectile, thereby calculates the attack source, and wherein, this threat comprises with the howitzer of high angle emission it is flung at or throws to object mortar for example.
Summary of the invention
A purpose of specific embodiment of the present invention provides a kind of projectile, this projectile can be used to according to certain predetermined pattern sub-projectile that scatters, thereby by increasing or control fragment or be used to defend effective selection of purpose to solve prior art problems by providing a kind of at least.
Another purpose of specific embodiment of the present invention provides a kind of system of defense, and this system of defense can be improved control to scattering of projectile, and can not make defend the zone for later dangerous for civilian.
The purpose of other embodiment of the present invention provides a kind of system of defense, and this system of defense is by turning to this projectile in the projectile flight course, and the position that can shelter projectile firing apparatus can not or at least more be difficult to derive the position of this projectile firing apparatus thus.
According to first kind of form of the present invention, a kind of projectile is provided, this projectile comprises a plurality of barrel assemblies that radially are provided with from its center, wherein, in described a plurality of barrel assembly each all comprises a plurality of sub-projectiles that are axially disposed within the gun tube, each described sub-projectile all combines with discrete propellant charges, and this propellant charges is used for each sub-projectile is propelled out gun tube, and described projectile optionally is provided by scattered the to provide predetermined pattern of sub-projectile of sub-projectile.
Preferably, projectile of the present invention is particularly suitable for launching this projectile by gun barrel and scatters, rather than is scattered by automatic pusher guided missile or this projectile of rocket launching, and this guided missile or rocket are launched from tube or platform.In other embodiments, can be by mobile platform for example aircraft or ship and utilize gravitation to throw in projectile of the present invention this projectile that scatters, perhaps be suitable for throwing projectile of the present invention this projectile that scatters in the mode that is similar to traditional hand-thrown type howitzer by soldier or defence officer.
First aspect is suitable for can be used for tackling or smashing into boosted missile from the projectile of the present invention that gun barrel is launched, particularly the guided missile of the higher type of trajectory height above sea level.Second aspect the invention provides a kind of method of interception guided missile, comprises step: determine the guided missile path; The projectile of type described here is injected in the path of described guided missile; And the selected sub-projectile of emission with in the guided missile path of determining and near the predetermined pattern of this sub-projectile of formation.
Projectile of the present invention also can be used for vehicle and defends oneself.Vehicle under attack, the vehicle that particularly is subjected to close attack can be launched the projectile of type described here towards the assailant, and among the assailant sub-projectile is scattered and be predetermined pattern.The third aspect the invention provides a kind of self-defence method of vehicle defensive attack power, comprises step: the position of determining attack; Near the fixed attack of the projectile directive position with type described here; And the selected sub-projectile of emission with the attack position of determining and near the predetermined pattern of this sub-projectile of formation.
Projectile of the present invention can be used for beating back infantry's attack.Fourth aspect the invention provides a kind of method of the infantry's of beating back attack, comprises step: the position of determining the infantry; Near at least one fixed infantry of projectile directive position of sending out type described here; And the selected sub-projectile of emission with the infantry position of determining and near the predetermined pattern of this sub-projectile of formation.
Projectile of the present invention can be used for forming aerial image (airborne images), for example pyrotechnics.The 5th aspect the invention provides a kind of method that forms the air image, comprises step: the projectile of type described here is injected in the air; And launch selected sub-projectile with image forming material, in air, to form the predetermined pattern of this image forming material.
Projectile of the present invention can be used for fire-fighting.The 6th aspect the invention provides a kind of fire-fighting method, comprises step: determine fire location; Near at least one fixed fire location of projectile directive of sending out type described here; The selected sub-projectile of emission with the fire location place that determines and near the predetermined pattern of this sub-projectile of formation; And by the sub-projectile dispersion extinguishing chemical of being launched.
Projectile of the present invention can be used for causing fuel-air burst.The 7th aspect the invention provides a kind of method that causes fuel-air burst, comprises step: fuel-air burst place of selecting expection; With at least one projectile directive of sending out type described here should fuel-air burst place of expection near; Emission comprises the selected sub-projectile of fuel to form the predetermined pattern of this sub-projectile; By the sub-projectile dispersion fuel of being launched; Emission comprises the selected sub-projectile of detonator to form the predetermined pattern of this sub-projectile; Ignite described detonator to cause fuel-air burst.
Projectile of the present invention can be used for disperseing various payload (payload).Eight aspect the invention provides a kind of method of disperseing payload, comprises step: the transmission load of selecting expection; With at least one projectile directive of sending out type described here should payload position of expection near; Emission has the selected sub-projectile of described payload to form the predetermined pattern of this sub-projectile; And disperse described payload by the sub-projectile of being launched.
Projectile of the present invention can be used for defending the appointed area.The 9th aspect broadly, the invention reside in a kind of system of defense that is used to defend the appointed area, and described system of defense comprises:
At least one monitor is used to monitor this appointed area, to survey any zone that occurs new things in it;
Defence installation, can make the personnel that appear at any position in the long-range appointed area become weak (debilitating), described defence installation comprises a kind of weapon of launching projectile, this projectile comprises the barrel assembly array that radially is provided with from its center, each barrel assembly all has a plurality of auxiliary or sub-projectiles that are axially disposed within the gun tube, this sub-projectile combines with the propellant charges that disperses, this propellant charges is used for sequentially described sub-projectile being propelled out gun tube, described barrel assembly array is this sub-projectile of emission in selected gun tube optionally, described thus projectile this sub-projectile that can scatter according to predetermined sub-projectile pattern; And
Communicator provides communicating by letter between this monitor and the defence installation, optionally starting this defence installation, thereby weak sexual assault is carried out in the zone of detecting.
This monitor comprises one or more presence detector that are dispersed in the appointed area, perhaps the remote probe device of arranging away from this appointed area.Optionally, this monitor had both comprised presence detector, comprised the remote probe device again.
This monitor also can provide the vision of the appointed area that is monitored to show, can start manual override (mannal override means) so when needed, with a complete set of defence installation of manual control.
Can in a plurality of gun tubes, emission side by side assist in a large number or sub-projectiles, perhaps in a gun tube, launch a large amount of auxiliary or sub-projectiles one by one.In this layout, can transmit electronic signal in the outside of gun tube, perhaps can transmit electronic signal via the auxiliary projectile of stack, this auxiliary projectile can be folded mutually and be pressed from both sides the circuit that passes this gun tube with connection, and perhaps this auxiliary projectile can mutual electric adjacency.This sub-projectile can load control circuit, and perhaps they can form a kind of circuit with gun tube.
The barrel assembly array can be arranged near the front end or tail end of projectile,, perhaps the barrel assembly array be arranged on the centre of projectile, laterally to move this projectile with the attitude (attitude) that changes this projectile effectively.Optionally, heading control loop can comprise near the barrel assembly array that is positioned at this projectile front end and the tail end.
This barrel assembly array or each row barrel assembly can be towards the direction emission sub-projectiles with longitudinal component, thereby provide extra kinetic energy for projectile; Perhaps can be towards a kind of like this direction emission sub-projectile, this direction has the component that is tangential on the guided missile y direction, thereby causes projectile around its longitudinal axis rotation or change the rotation of this projectile around its longitudinal axis.Barrel assembly can be transverse to flying surface flying wing emission sub-projectile for example, to cause the further steering effect to this projectile.Optionally, the extensible airfoil (aerofoil surface) of crossing of barrel assembly is to launch towards both direction.This can strengthen the structural strength of pneumatic design.
If desired, can provide the only or relative barrel assembly of itemizing, with of the rotation of control projectile around its longitudinal axis.This row structure can comprise that relative barrel assembly is right, can side by side launch this barrel assembly to only to change the rotation of projectile around its longitudinal axis effectively.Form heading control loop in the auxiliary projectile of being launched, thus cancellation or to use projectile this before the effect of its longitudinal axis rotation and/or afterwards, optionally promoter projectile.
In certain embodiments of the present invention, provide attitude and/or heading energy needed by selected certainly barrel assembly emission sub-projectile in order to change female projectile.
According to second kind of form of the present invention, provide a kind of method that is used to shelter the transmitting site of projectile firing apparatus.The method comprising the steps of: at least one emission bullet of emission in barrel assembly, described barrel assembly have gun tube, a plurality of discrete propellant charges that radially is arranged on the projectile that functionally is sealed and matched with the bore with this gun tube in this gun tube and is used for propelling out in proper order via gun muzzle of this gun tube each projectile; Simultaneously when described at least one projectile is in the flight course, at least one the sub-projectile of row steering propulsion unit emission that in it, comprises, each steering propulsion unit comprises a plurality of sub-projectiles that turn in the propelling gun tube that are axially disposed within, in this turned to the propelling gun tube, sub-projectile combined so that described sub-projectile is propelled out this in proper order with second propellant charges that disperses and turns to the propelling gun tube; Wherein, described turning to advances the barrel assembly array optionally to advance gun tube emission sub-projectile from selected turning to, and can utilize the reaction force of the described sub-projectile of emission to quicken described projectile thus.
The global shape of this sub-projectile is not strict important, because sub-projectile is a kind of like this material, second propellant is given with respect to this sub-projectile and turned to the breech effect that advances gun tube and apply reaction force.In the scope of this form of the present invention, this breech can advance in the gun tube and forms with follow-up sub-projectile that the bore of this gun tube is sealed and matched by staying to turn to.Reaction force advances the breech of gun tube to be transferred to projectile by assisting or turning to, thereby causes this projectile to quicken.
The barrel assembly array can radially be provided with from the center of projectile.This barrel assembly structure is specially adapted to not possess the object of flight propulsion system, that is, and and rocket and guided missile.Except displacement and the apparent orbit, the emission sub-projectile can mobile simply projectile, and this projectile continues to advance along its track.
The present invention is applied to area-denial especially, and wherein, this zone is subjected to by container (pod) the bombarding of projectile of mortar case emission for example.Certainly should be appreciated that the present invention also can be applicable to pretend the transmitting site of other projectile launch or activating system.
In a kind of preferred embodiment, can select apparent orbit, so that firepower spontaneous emission device is attracted to other enemy position.
Projectile of the present invention preferably adopts the barrel assembly of type described in international patent application Nos.PCT/AU94/00124 and the PCT/AU96/00459.This barrel assembly comprises gun tube, a plurality of discrete propellant charges that is axially disposed within the projectile that functionally is sealed and matched with the bore with this gun tube in this gun tube and is used for propelling out in proper order via gun muzzle of this gun tube each sub-projectile.
This sub-projectile can be circular, conventional shape or javelin shape, its fin of can setovering, with when this javelin shape sub-projectile from being the stable spin of generation when propelling out the gun tube of flat thorax gun tube.If desired, be loaded with the projectile of sub-projectile can be substantially for cylindrical, oval or spherical.
Propellant charges can be the solid block form, functionally being the projectile slot milling in gun tube, perhaps this propellant charges can be encapsulated in metal or other stiff case, this housing can comprise the flush type detonator with outside contact device, and a kind of pre-determined bit electronic contact that this outside contact device is suitable for linking to each other with this gun tube contacts.For example, this detonator can have a kind of the contact on spring, and this contact is collapsible inserts in the gun tube with explosive that will encapsulation, in case this contact with after aliging in the gun tube hole, this contact just is ejected in the gun tube hole, to contact with gun tube operating of contacts that it matches.If desired, external shell can be fusible, and perhaps it can be in the burning of auxiliary propellant aspect the chemical property.In addition, can provide a kind of explosive and sub-projectile assembly that piles up bonding or encapsulation separately, with the gun tube that recharges.
Each sub-projectile can comprise head and extension apparatus, and this extension apparatus defines propellant space at least in part.This extension apparatus comprises a gasket assembly, and this gasket assembly extends back and near adjacent sub-projectile assembly from head.
Extensible propellant space and the head crossed of this gasket assembly is thus directly via transmitting compressive load with adjacent gasket assembly adjacency.In this structure, this gasket assembly can strengthen the support to extension apparatus, and this extension apparatus can be the thin cylindrical rear of head.In addition, this extension apparatus can form functionally to seal and contact with the bore of gun tube, leaks sub-projectile to prevent burning.
This gasket assembly can comprise a rigidity axle collar, this stiff shaft hoop is outer to be extended to engage with the thin cylindrical rear of extending head, this extending head non-operational ground contacts with the bore sealing of gun tube, can directly between gasket assembly, transmit axial compression load thus, thereby avoid this extending leading edge deformation.
Complementary lozenges can be set on this gasket assembly and head respectively, thus can be in response to compressing to axial and impel this head to engage between this gasket assembly and the head with the bore of gun tube.In this configuration, head and gasket assembly can be packed in the gun tube, produce an axial displacement then, to guarantee excellent sealing between sub-projectile and the gun tube.Suitably, impel this extension apparatus to engage with the bore of gun tube.
The rear end of this head can limit a bellmouth, a complementary cone-shaped plug that is arranged on the gasket assembly front end is contained in this bellmouth, wherein, moving to axial between this head and the complementary cone-shaped plug produces a radial expansion force, and sub-projectile is given in this footpath dilatation shaft power effect.
Gun tube can be nonmetal, and the bore of this gun tube can have groove, and this groove holds igniter wholly or in part.In this structure, electric connection is housed in the gun tube, this electric connection impels between control device and this igniter and is electrically connected.Therefore this structure can be applied to use up the barrel assembly that promptly abandons, the igniting life-span of this barrel assembly is limited, this igniter and control line and gun tube can be manufactured one.
Barrel assembly optionally comprises the fire hole that is positioned at gun tube, igniter is arranged on this gun tube outside and this fire hole near.A kind of nonmetal outside gun tube can be around this gun tube, and this nonmetal outside gun tube can have and is applicable to the groove that holds igniter.This outside gun tube also can hold electronic joint, and this electronic joint impels between control device and the igniter and is electrically connected.This outside gun tube can be configured as a kind of interlayer plastics gun tube, and this interlayer plastics gun tube can comprise the printed circuit interlayer that is used for igniter.
This barrel assembly can have adjacent and separate sub-projectile, the positioner that utilization is independent of this sub-projectile keeps this sub-projectile to be in the relation of space, each sub-projectile can comprise a kind of extensile sealing device, and the sealing device is used for forming the operability sealing with the bore of gun tube.This positioner can be the propellant charges between the adjacent sub-projectile, and the sealing device is suitable for comprising the side edge part that is positioned on each sub-projectile, and during load in being subjected to gun tube (in-barrelload), this side edge part just outwards stretches.Can apply load in this gun tube in the process of sub-projectile is installed or after installing, for example usually compacting and with sub-projectile and propellant charges fixed be column, perhaps apply load in this gun tube by lighting the particularly adjacent outside sub-projectile of outside sub-projectile.
The rear end of this sub-projectile can comprise a lateral margin, this lateral margin is around the groove that inwardly dwindles for example conical socket or part ball recess etc., propellant charges stretches in this groove, and sub-projectile is around the mobile backward lateral margin radial dilatation that will cause this sub-projectile of this groove.This moving backward can utilize compression to realize, this compression is that wedge shape moves generation because sub-projectile is done backward along the front portion of propellant charges, and it is to produce owing to metal flow to the so not heavy side edge part of its quality from the heavier front portion of this sub-projectile quality that this wedge shape backward moves.
Optionally, this sub-projectile can have the outspreading backwards circumferential sealing flange or the axle collar, and when sub-projectile is mobile backward, thereby this flange or the axle collar are sealed and matched to extrinsic deflection and bore.In addition, can realize sealing like this, by sub-projectile being inserted in the heating gun tube and this heating gun tube is retracted on each sealing of this sub-projectile.Sub-projectile can comprise harder mandrel segment, utilize propellant charges to locate this mandrel segment, and this mandrel segment with form a kind of single sub-projectile around the molded deformable ring-type of this axle partly cooperates, this single sub-projectile relies on the metal flow between its nose and the afterbody, come to expand outwardly, thereby be sealed and matched with the bore of gun tube around this mandrel segment.
The sub-projectile assembly can comprise outspreading backwards datum level (anvil surface), and this datum level is around supporting a sealing axle collar, and when this sub-projectile moves past gun tube forward, is sealed and matched thereby this datum level is suitable for the bore of radial dilatation and gun tube.In this configuration, propellant charges preferably has cylindrical forward portion, the planar end surface of this cylindrical forward portion next-door neighbour sub-projectile.
Sub-projectile be suitable for being located in and/or be positioned in the circular trough or bore in circumferential rib in or in the helicla flute in the bore, and can comprise a metallic support, this metallic support encapsulates the outer end of sub-projectile at least.Sub-projectile can have telescopic circumferential registration ring, and this locating ring outwards stretches in the interior cannelure of gun tube, and in this locating ring retraction sub-projectile, freely passes gun tube to allow this sub-projectile when igniting.
The electronic ignition operation is used for sequentially lighting the propellant charges of barrel assembly, this electronic ignition operation preferably includes step: light the front end propellant charges by sending ignition signal via the sub-projectile that piles up, and light this front end propellant charges, and prepare to utilize next ignition signal to start next propellant charges.Suitably, be arranged between the electronic contact of common closure, make the end of bootstrap loading gun tube play inside whole propellant charges and all can not detonate by inserting each insulation fuse and the fuse that will insulate.
But electronics is realized lighting of propellant, and perhaps this is lighted and can adopt conventional igniting pin formula method, for example uses a kind of center fire detonator to light the sub-projectile of outermost end, then according to the propellant charges of lighting follow-up shell through the order of control.This can control burning gases and leaks backward, or sub-projectile is passed in the burning of control fusion post.
In other embodiments, utilize each propellant charges that links to each other with detonator to come the combustion of electronics control point, utilize special igniting signal to start this detonator.For example, can be according to the order of firing pulse width requirement increase, arrange this and pile up the interior detonator of propellant charges, Electronic Control can optionally send the firing pulse that pulse width increases thus, sequentially to light propellant charges according to selected time sequencing.But preferred, light propellant charges by the pulse width signal of setting, the burning of front end propellant charges, and prepare to utilize next transmitted pulse to start next propellant charges.
Suitable, be arranged between the electronic contact of common closure by inserting each insulation fuse and the fuse that will insulate, making the end of bootstrap loading gun tube play inside whole propellant charges all can not detonate, in above-mentioned this embodiment, make these fuse fuel, thereby these contacts are closed after transmitting suitable enabling signal, and each insulation fuse is all opened to light this propellant charges to each front end propellant charges.
Although can adopt the barrel assembly of antiaircraft gun mouth pressure, in certain embodiments, this barrel assembly can be low-pressure type, and this low-pressure type barrel assembly emission is similar to the sub-projectile of howitzer.Each barrel assembly can load different sub-projectiles, and this barrel assembly can have the different size bore that is used to hold the different size sub-projectile.
Suitably, each sub-projectile comprises a tail end axle collar, and this tail end axle collar is installed on the main body of sub-projectile, and when in the gun tube that it is packed into, this tail end axle collar extends back and leans against on the nose of afterbody sub-projectile main body with wedge.Suitable, a narrow wedge-shaped part provides wedging action, thus in use, the tail end of this axle collar is extended functionally to be sealed and matched with gun tube.
This tail end axle collar is mounted to and can does limited moving axially with respect to the sub-projectile main body, the front end of this axle collar has an annular sealing surface, this annular sealing surface cooperates with complementary surface on being formed on the sub-projectile main body, thus, the reaction of propellant gas makes sub-projectile move backward, and moving backward of this sub-projectile just forces the annular sealing surface on its complementary surface and the axle collar front end to be sealed and matched.
But this complementary surface and annular sealing surface approximate radial are extended, and both complementary sealings.But preferred, these surfaces are complementary part conical seal (contact) face, and this conical seal (contact) face is wedged mutually to seal tightly cooperation.This leading section is also extensible, to be sealed and matched with the gun tube operability.Suitably, being fixed between the part conical seal (contact) face is more precipitous surface, and the front end of this axle collar functionally is not sealed and matched with gun tube with regard to not stretching under wedging action thus.
Under the low pressure situation, preferred, each sub-projectile links to each other with a kind of high pressure propellant chamber, and this high pressure propellant chamber is to each low pressure propellant chamber exhaust, and this low pressure propellant chamber is formed between the adjacent sub-projectile, to carry out effectively low muzzle velocity operation.The high pressure propellant chamber can be integrally formed with the sub-projectile main body or the tail end axle collar, and perhaps this high pressure propellant chamber can be positioned at the outside of gun tube, and be communicated with this gun tube via the opening that passes the gun tube wall.
Suitably, the propellant of having lighted will diffuse in certain space, and the structure in this space and the character of propellant are such, make that promptly only producing low gun tube in use presses, for example within about 2000psi to 5000psi.Usually, when this axle collar is in relaxed state, no matter be for loading purpose or in emission process, it can not hinder projectile and freely move past gun tube.
One pressure pad is installed on the shell of open rear end inside.After lighting propellant, the axle collar will leave cooperation position and be relocated, and utilize pressure pad to make this axle collar remain on relaxed state, so that projectile is by gun tube and go out gun muzzle of this gun tube.
Projectile can be traditional type, and launch this projectile according to traditional approach, perhaps preferably be suitable for this projectile of emission in a kind of like this barrel assembly, this barrel assembly comprises a plurality of projectiles that are axially disposed within this gun tube, each described projectile combines with the discrete type propellant charges, and this propellant charges is used for described projectile is propelled out this gun tube.
In a kind of preferred form, it is spherical that this projectile is generally, and have a plurality of barrel assemblies that radially are provided with from this sphere center.These barrel assemblies can be same or different.For example, the major diameter gun tube can be from the center setting of this sphere projectile, and the gun tube than minor diameter can be arranged on this than between the major diameter gun tube simultaneously, so that maximum sub-projectile density to be provided in projectile.People are desirable to provide the projectile that has maximum gun tube packing density, also has maximum fire thus.Optionally, people are desirable to provide the projectile with various gun tube bores, to adopt the sub-projectile of various different bores.
This projectile can be a band shell projectile, so that scatter.The hull shape of spherical projectile can be become a kind of shape of in traditional diverging system, launching of being easier to, for example the shape of conventional ammunition.Optionally, increase muzzle velocity if desired, band shell projectile can hold more propellant charges, and does not need to limit barrel length.
The barrel assembly that radially is provided with from the projectile center allows this projectile with mode conventional and that be easy to the control sub-projectile that scatters.The barrel assembly that radially is provided with from the projectile center allows this projectile to keep its attitude.According to a kind of like this mode sub-projectile that scatters, this mode will produce zero active force to projectile, and this projectile can be kept the track of its expection thus.
Can be side by side or launch a large amount of sub-projectiles one by one.In this configuration, electronic signal can be sent to the outside of gun tube, perhaps can send electronic signal via the sub-projectile of stack, this sub-projectile can be folded mutually and press from both sides the circuit that passes this gun tube with connection, and perhaps this sub-projectile can mutual electric adjacency.This sub-projectile can deliver control circuit, and perhaps they can form a kind of circuit with gun tube.
The projectile of the present invention sub-projectile that can scatter according to predetermined pattern can be according to this predetermined pattern of specific application choice.For example, in order to tackle or to destroy into boosted missile, wish to scatter in such a way sub-projectile, make one or the multiple sub-projectile of this mode maximum possible clash into this guided missile.People have adopted the shell fragment system that the shell fragment of projectile is distributed in the path of boosted missile.But the system that is similar to this blast projectile produces a kind of like this shell fragment zone usually, and this shell fragment disperses and form the spherical shell of an expansion.Projectile can spread out into sub-projectile of the present invention in the whole space that predetermined pattern covers according to mode more equably.By the launch time of control sub-projectile, can set up a kind of three-dimensional " fragment " pattern, this pattern distributes sub-projectile basically equably.Optionally, sub-projectile is concentrated in the zone of most possibly intercepting guided missile, to increase the validity of the sub-projectile that is scattered.
This sub-projectile can comprise the material that forms aerial image.This image forming material for example can comprise, explosive substance, flammability material, meets thermoluminescent property material or photism material or other in order to the material of strong visible moment image to be provided.Optionally, this image forming material can comprise cigarette, gas, particle or thin slice or band, can spread to form the material of image as natural husk or other.Accordingly, preferably adopt projectile of the present invention to launch counter measure from military aircraft.This image forming material also can comprise and be used to delay its device from the downward sinking speed of diffusion position, for example parachute etc.
In a single day sub-projectile can be arranged in the barrel assembly like this, make and launch this sub-projectile and the image forming material that scatters, just can form aerial image of desirable moment.The sub-projectile that contains different images formation material sequentially can be written in each barrel assembly, this different images forms material and has different colors or shape.
Can disperse image forming material like this, for example, utilize destructor, utilize stored energy or separate to expose this image forming material or to utilize other any suitable distributor by the separating component that makes sub-projectile.
Image forming material can be included in the housing, and this housing can have any suitable structure, and this housing is used to hold image forming material, and is suitable for this casing structure for cooperating with the tail end of the expansible axle collar of projectile formerly.Preferably, this housing is the sort of type that howitzer class projectile is adopted, and has shorter more and stout shape, but also can adopt the projectile with thin-long casing.
This housing is suitable for being formed by biodegradable material and/or combustible material.This material is based on natural products for example wood chip or artificial material, for example biodegradable polymer.
Preferably, projectile of the present invention can disperse the sub-projectile selected, with the track of control projectile.This dispersion process can be regarded as a kind of propulsion system that turns to, and can be used for effectively limited correction being done in the projectile position, with the remaining sub-projectile that scatters according to the pattern of expecting.
Projectile of the present invention is suitable for being used in the sort of type system of defense described in the applicant's the international patent application No.PCT/AU00/01351.
Brief description of drawings
In order to be easier to understand and be easier to implement the present invention, now with reference to the following drawings the preferred embodiment of the present invention is described, wherein:
Fig. 1 is the cross sectional representation according to a kind of projectile of the preferred embodiment of the present invention;
Fig. 2 is a kind of cross sectional representation with the shell projectile, and this band shell projectile is used in a kind of like this barrel assembly, has the band shell projectile of a plurality of axial settings in this barrel assembly;
Fig. 3 is the cross sectional representation of emission band shell projectile shown in Figure 2;
Fig. 4 is the side view according to a kind of system of defense of the another kind of embodiment of the present invention;
Fig. 5 is the perspective view of another kind of system of defense embodiment.
Detailed description of preferred embodiment
Fig. 1 has represented a kind of projectile (projectile) 10, and this projectile 10 has the suitable big boring pipe 12 of six (6) individual bores, but has only represented four (4) individual big boring pipes 12 in this cross sectional representation.All the other two (2) individual big boring pipes (extending perpendicular to paper) are designated 11.This cross sectional representation has also been represented the middle boring pipe 13 that four (4) individual bores are medium, and the less little boring pipe 14 of 48 (48) individual bores.As shown in the figure, each big boring pipe 12, middle boring pipe 13 and little boring pipe 14 all comprise the sub-projectile 16 of many axial settings.This sub-projectile 16 combines with propellant charges 17 and igniter 18, will light this igniter 18 subsequently under a kind of control of electronic controller 15.In certain embodiments, this projectile 10 also can comprise the explosive that is used for final ignition.
In such an embodiment, this electronic controller 15 is positioned at the central authorities of projectile 10 and the rear of boring pipe 11,12, and this electronic controller 15 can comprise sensor, and this sensor is used for following the tracks of the guided missile in target approach district when flight.Optionally, this electronic controller 15 can be via the firing order of communication line reception from remote tracking station.Can adjust a large amount of sub-projectiles of emission subsequently thus, to improve attack to target invasion guided missile or similar threat.
Fig. 2 represents to have the type projectile shown in Figure 1 of shell case 20, wherein for the sake of simplicity, has omitted sub-projectile.Projectile 10 is positioned at the gun tube of these shell case 20 inside.This shell case 20 comprises preceding shell case part 21, back shell case part 22 and expansion sleeve 23, and this expansion sleeve 23 is around the rear portion skewed surface 24 of back shell case part 22.Ignite and light be positioned at before the propellant charges of shell case part 21 this back shell case part 22 is pressed to expand sleeve 23, thereby cause this expansion sleeve sealably to engage with the hole of female gun tube.
Fig. 3 represents wherein have a plurality of original gun tubes 31,32 and 33 from a series of projectiles 10 of original barrel assembly 30 ejaculations.Projectile 10A penetrates from gun tube 33, and has abandoned its shell case (not shown).Projectile 10B penetrates from gun tube 32, shown in shell case 20 be in just in abandoned process.Expansion sleeve 23 separates with back shell case part 22, and this back shell case part 22 is also separated with projectile 10B.Similarly, preceding shell case part 21 is separated with this projectile 10B.Projectile 10C is up-to-date from gun tube 31 ejaculations, and shell case 20 has begun to separate with projectile 10C.
With reference to Figure 4 and 5 as seen, utilize the field sensor array 41 that is distributed in the appointed area 40 to monitor this appointed area that will defend 40, this field sensor 41 can be any suitable type, for example pressure, acoustics or vibration type sensor.
Shown in the weapon form that adopts of system of defense 42 be a pair of howitzer case 43, each howitzer case 43 all adopts barrel assembly 30 and is connected with a receiving element 49 with a remote probe device 44, this receiving element 49 links to each other with field sensor 41.In the present embodiment, this remote probe device 44 is installed on the pylon, and it is suitable for utilizing photoelectric technology or microwave technology scanning appointed area 40, invades this appointed area 40 to monitor anyone, vehicle or other invador.
In the present embodiment, receiving element 49 is suitable for utilizing the signal of radio frequency (RF) communication line (but in other alternative mode, also can adopt cable run) reception from field sensor array 41.In case detect anyone or thing intrusion appointed area 40, just utilize the projectile 10 aiming invasion zones of howitzer case 43 emissions, regional to isolate this invasion.Thus, can utilize one of field sensor array 41 and remote probe device 44 or both to monitor appointed area 40.
People wish each howitzer case 43 all is arranged on hidden substantially position, for example in the hole, a hole in.In case after setting, can carry out backfill, thereby can not produce any adverse effect to this operation of cheating the barrel assembly 30 in the hole to the hole, hole of placing this howitzer case 43.In another kind is provided with, can easily howitzer case 43 be hidden among the leaf, and utilizes the screw jack 48 that combines with the bearing 47 that is used for the howitzer case to regulate this howitzer case 43.
One auxiliary control circuit 43a (referring to Fig. 5) is as the plug-in type connector of this howitzer case 43, at the scene rather than this auxiliary control circuit 43a is installed in transportation, and to guarantee the safety of weapon in the transportation.In case this control circuit 43a is installed, and weapon just is in war footing, and prepare to launch according to the control that provides by sensor unit 44 and/or receiving element 49.If desired, this control circuit can be suitably with each projectile in electronic controller 15 communicate.
Central-remote detector 44 shown in Figure 5 is connected with a plurality of howitzer casees 43 via each control circuit 43a.In use, detected the invador and enter this search coverage if for example be designated any location in 50 to 59 in some zones, the howitzer case 43 that just can start appointment is to that specific region emission one or multiple projectile 45.According to previously selected order or under Long-distance Control, can after each projectile 45 of emission, then launch sub-projectile, the sub-projectile predetermined pattern that scatters with formation.It is desirable to, according to this sub-projectile pattern of type selecting of invador.
Enter invadors in the appointed area 40 and can be any in a large amount of types, and can comprise a plurality of invadors.A kind of invador can be the army personnel of infantry's class.Optionally, the invador can also be manned or unmanned vehicle, for example panzer or Plutarch.This invador may have perfect system of defense, and this system of defense can be followed the tracks of the track of the projectile of penetrating, and calculates the position of emitter, thereby the previous emitter of hiding is attacked.The system of defense of present embodiment can change the track of projectile, thereby make the invador follow the tracks of apparent track, but can shelter the physical location of emitter by the emission sub-projectile in flight course.If feasible, can select this apparent orbit will guide other enemy's position into towards the enemy firepower of system of defense 42.
Although above system of defense is based upon the land, another aspect of the present invention relates to the projectile that can be described as submarine mine.These submarine mines are launched by a ship and are kept floating in water, utilize the Long-distance Control of sensor-based system on the ship or independent operation to start these submarine mines, and sensor-based system comprises radar, sonar or infrared ray sensor on this ship.These submarine mines can adopt the firm or anchor such as sash weight one class, and this submarine mine of row can be set, so that a kind of maritime defense band that can start as required or not start to be provided.
In another kind scatters pattern, can from aircraft for example helicopter cast projectile of the present invention.Can provide firm or anchor spike thing for example, on a position that this projectile is fixed and held at ground.The ground floor sub-projectile can comprise sensing system, launches this ground floor sub-projectile to survey existing of adversary forces or vehicle, utilizes the howitzer of subsequent layer in each projectile gun tube and this adversary forces or vehicle belligerent then as required.In other layer, also can provide other in order to measure belligerent result's sensor.
Also have a kind of pattern of scattering to provide projectile, can grasp this projectile easily and, be similar to traditional grenade by throwing this projectile that scatters with a kind of like this size.But, in the gun tube of this hand-thrown type projectile, adopt sub-projectile just to make it can be used in the running fire pattern (repeating mode), this running fire pattern adopts Preset Time to postpone or remote control.This is just for belligerent some advantage that provides in the enclosure space is provided, for example war of cities or comprise the landform war in cave of this enclosure space.Under the jointly attack situation, this sub-projectile can comprise non-lethal bullet and a kind of sonification system that is used to warn, if besieged evil person refusal is surrendered immediately, can launch other bullet so.
Projectile of the present invention can be transported to space and also send into as required around in planet or the lunar orbit, in fact this planet or the moon include satellite.Owing to can in a spherical substantially object, radially disperse this barrel assembly, therefore this barrel assembly can be revised the position of satellite in the track quite effectively, prevent to have space junk, aerolite etc. in the zone around important satellite, perhaps be used for carrying out belligerent with enemy's spaceship or satellite.Because by the sub-projectile of emission solid rather than as by gas burst the enemy being left in the conventional satellite, therefore in the less environment of gravitation, change in location can more promptly be carried out.Be suitable for constructing this satellite projectile like this, thereby make and consume by burning when they reenter atmosphere after track descends.
In a kind of particular form, this satellite can comprise a kind of especially big projectile, can exhale projectile of the present invention in the barrel assembly that radially is provided with in this especially big projectile conversely, these projectiles that scatter self can be equipped with sub-projectile, thereby a kind of pair of layering system of defense is provided.In suitably using, other can certainly adopt this pair of layering system of defense.
Certainly should be appreciated that, below only provided explanation of the present invention in the mode of one exemplary embodiment of the present invention, but it will be readily apparent to one skilled in the art that all improvement and changes to it all drop in the broad scope of setting forth as following claims of the present invention.
Claims (39)
1. the projectile of head for target thing emission, described projectile comprises:
The a plurality of barrel assemblies that radially are provided with from the mass centre of described projectile, wherein, each in described a plurality of barrel assemblies all comprises a plurality of sub-projectiles that are axially disposed within the described gun tube;
Each described sub-projectile all combines with discrete propellant charges, and described propellant charges is used for each sub-projectile is propelled out described gun tube, and wherein, described projectile optionally is provided by the predetermined pattern of the sub-projectile that sub-projectile scattered to provide.
2. projectile as claimed in claim 1 is characterized in that described projectile is suitable for launching from gun tube.
3. projectile as claimed in claim 2 is characterized in that, described a plurality of sub-projectiles are axially disposed within the described gun tube, is used for functionally being sealed and matched with the bore of described gun tube.
4. as each described projectile in the claim 1 to 3, it is characterized in that it is spherical that the shape of described projectile is generally, and have a plurality of barrel assemblies that radially are provided with from the center of described sphere.
5. projectile as claimed in claim 4 is characterized in that, has the gun tube of various different-diameters, to be applied to the sub-projectile of various different bores.
6. as claim 4 or the described projectile of claim 5, it is characterized in that, center from described spherical projectile is provided with larger-diameter gun tube, than the gun tube of minor diameter between described larger-diameter gun tube, so that the maximization of the sub-projectile density in the described projectile.
7. as each described projectile in the claim 1 to 6, it is characterized in that described projectile has shell case.
8. as each described projectile in the claim 1 to 7, also comprise electronic controller, be used to control igniting of described propellant charges.
9. projectile as claimed in claim 8 is characterized in that, can be side by side or launch a large amount of sub-projectiles one by one.
10. as claim 8 or the described projectile of claim 9, it is characterized in that, described a plurality of barrel assembly is arranged so that the described sub-projectile that can scatter like this, and promptly described sub-projectile makes a concerted effort to minimize to the reaction of described projectile, thereby allows described projectile to keep the track of expection.
11. projectile as claimed in claim 8 also comprises sensor, is used to follow the tracks of menace or invador.
12. projectile as claimed in claim 8 is characterized in that, described electronic controller is via the firing order of communication line reception from remote tracking station.
13. as each described projectile in the claim 1 to 12, it is characterized in that, in order to change or to control the track of described projectile and disperse described sub-projectile.
14. the method for an interception guided missile, described method comprises step: the path of determining described guided missile; Each described projectile in the claim 1 to 13 is injected in the path of described guided missile; And the selected sub-projectile of emission with in described definite guided missile path and near the predetermined pattern of the described sub-projectile of formation.
15. the self-defence method of a vehicle defensive attack power comprises step: the position of determining described attack; Near the position with the described fixed attack of each described projectile directive in the claim 1 to 13; And the selected sub-projectile of emission with the position of described definite attack and near the predetermined pattern of the described sub-projectile of formation.
16. a method of beating back the infantry comprises step: the position of determining described infantry; Near the position with each described fixed infantry of described projectile directive at least one the claim 1 to 13; And the selected sub-projectile of emission with described definite infantry position and near the predetermined pattern of the described sub-projectile of formation.
17. a method that forms the air image comprises step: each described projectile in the claim 1 to 13 is injected in the air; And launch selected sub-projectile with image forming material, in air, to form the predetermined pattern of described image forming material.
18. a fire-fighting method comprises step: determine fire location; Near the position with the described fixed fire of each described projectile directive at least one the claim 1 to 13; The selected sub-projectile of emission with described definite fire location place and near the predetermined pattern of the described sub-projectile of formation; And by the sub-projectile dispersion extinguishing chemical of being launched.
19. a method that causes fuel-air burst comprises step: the position of selecting the fuel-air burst of expection; Near the position with the fuel-air burst of the described expection of each described projectile directive at least one the claim 1 to 13; Emission comprises the selected sub-projectile of fuel to form the predetermined pattern of described sub-projectile; By the sub-projectile dispersion fuel of being launched; Emission comprises the selected sub-projectile of detonator to form the predetermined pattern of described sub-projectile; Ignite described detonator to cause fuel-air burst.
20. a method of disperseing payload comprises step: the position of selecting the transmission payload of expection; Near the position with the payload of the described expection of each described projectile directive at least one the claim 1 to 13; Emission has the selected sub-projectile of described payload to form the predetermined pattern of described sub-projectile; And disperse described payload by the sub-projectile of being launched.
21. a system of defense that is used to defend the appointed area, described system of defense comprises:
At least one monitor is used to monitor described appointed area, to survey any zone of the appearance new things in it;
Defence installation, it can make the invador who appears at any position in the long-range appointed area become weak, and described defence installation comprises a kind of weapon of launching projectile, and described projectile comprises:
The barrel assembly array that radially is provided with from its mass centre, each barrel assembly all has a plurality of auxiliary or sub-projectiles that are axially disposed within the gun tube, described sub-projectile combines with the propellant charges that disperses, and described propellant charges is used for sequentially described sub-projectile being propelled out gun tube, and
Described barrel assembly array is the described sub-projectile of emission in selected gun tube optionally, the sub-projectile pattern that described thus projectile can scatter predetermined; And
Communicator, it provides communicating by letter between described monitor and the defence installation, optionally starting described defence installation, thereby weak sexual assault is carried out in the zone of detecting.
22. system of defense as claimed in claim 21 is characterized in that, described monitor comprises one or more presence detector that are dispersed in the appointed area, perhaps the remote probe device that disperses away from described appointed area.
23., it is characterized in that described monitor provides the vision of the appointed area that is monitored to show, can start manual override so when needed, so that can manually control described weapon as claim 21 or the described system of defense of claim 22.
24., it is characterized in that as each described system of defense in the claim 21 to 23, can in a plurality of gun tubes, side by side launch a large amount of sub-projectiles, perhaps in a gun tube, launch a large amount of sub-projectiles one by one.
25. system of defense as claimed in claim 24 is characterized in that, transmits by being positioned at described gun tube circuit external transmission electronics.
26. system of defense as claimed in claim 24 is characterized in that, by the sub-projectile transmission electronic signal of stack.
27. system of defense as claimed in claim 26 is characterized in that, described sub-projectile is clamped the circuit that passes described gun tube with connection mutually.
28. system of defense as claimed in claim 26 is characterized in that, the mutual electric adjacency of described sub-projectile.
29. system of defense as claimed in claim 24 is characterized in that, each described sub-projectile all carries control circuit.
30., it is characterized in that described barrel assembly array comprises near the gun tube that is arranged on described projectile one end as each described system of defense in the claim 21 to 29, be used for changing effectively the attitude of described projectile.
31., it is characterized in that described barrel assembly array comprises the gun tube in the middle of being arranged on, and is used for laterally moving described projectile as each described system of defense in the claim 21 to 30.
32., it is characterized in that each row barrel assembly can be launched sub-projectile having on the direction of longitudinal component as each described system of defense in the claim 21 to 31, think that described projectile provides inevitable extra kinetic energy.
33. as each described system of defense in the claim 21 to 31, it is characterized in that, each row barrel assembly can be launched sub-projectile on such direction, described direction has the component on the y direction that is tangential on projectile, so that described projectile is around the rotation of its longitudinal axis or change the rotation of described projectile around its longitudinal axis.
34., it is characterized in that at least some barrel assemblies can cross for example flying wing emission auxiliary projectile of flying surface, to cause the further steering effect to described projectile as each described system of defense in the claim 21 to 33.
35., it is characterized in that at least some barrel assembly extend through airfoils are to launch as each described system of defense in the claim 21 to 33 on both direction.
36., it is characterized in that, be provided with the only or relative barrel assembly of itemizing, with of the rotation of control projectile around its longitudinal axis as each described system of defense in the claim 21 to 33.
37. system of defense as claimed in claim 36 is characterized in that, the structure of described barrel assembly array comprises that relative barrel assembly is right, and described barrel assembly is to can side by side launching only to change the rotation of described projectile around its longitudinal axis effectively.
38. as each described system of defense in the claim 21 to 37, it is characterized in that, provide attitude and track energy needed in order to change described projectile by selected certainly barrel assembly emission sub-projectile.
39. a method that is used to shelter the transmitting site of projectile firing apparatus, described method comprises step:
(a) at least one emission bullet of emission in barrel assembly, described barrel assembly have gun tube, a plurality of discrete propellant charges that radially is arranged on the projectile that functionally is sealed and matched with the bore with described gun tube in the described gun tube and is used for propelling out in proper order via gun muzzle of described gun tube each projectile; And
(b) when described at least one projectile is in the flight course, self-contained at least one sub-projectile of row steering propulsion unit emission within it, each steering propulsion unit has a plurality of sub-projectiles that turn in the propelling gun tube that are axially disposed within, wherein, sub-projectile combines with second propellant charges that disperses, and is used for described sub-projectile is propelled out the described propelling gun tube that turns in proper order; Wherein
(c) described turning to advances the barrel assembly array optionally to advance gun tube emission sub-projectile from selected turning to, and utilizes the reaction force that is produced by the described sub-projectile of emission to quicken described projectile thus.
Applications Claiming Priority (2)
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|---|---|---|---|
| AUPR6294A AUPR629401A0 (en) | 2001-07-11 | 2001-07-11 | Projectiles |
| AUPR6294 | 2001-07-11 |
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|---|---|
| CN1653313A true CN1653313A (en) | 2005-08-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA028138457A Pending CN1653313A (en) | 2001-07-11 | 2002-07-08 | Projectile for radially deploying sub-projectiles |
Country Status (12)
| Country | Link |
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| US (1) | US20040244628A1 (en) |
| EP (1) | EP1405028A1 (en) |
| JP (1) | JP2004534202A (en) |
| CN (1) | CN1653313A (en) |
| AU (1) | AUPR629401A0 (en) |
| BR (1) | BR0211231A (en) |
| CA (1) | CA2452487A1 (en) |
| IL (1) | IL159734A0 (en) |
| MX (1) | MXPA04000215A (en) |
| RU (1) | RU2293281C2 (en) |
| WO (1) | WO2003006915A1 (en) |
| ZA (1) | ZA200400071B (en) |
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| CN104776762A (en) * | 2015-04-14 | 2015-07-15 | 湖南工业大学 | Guided missile with pre-destroy and anti-interception functions and forming method thereof |
| CN104776761A (en) * | 2015-04-14 | 2015-07-15 | 湖南工业大学 | Guided missile with pre-destroying and anti-interception functions and construction method for guided missile |
| CN112179213A (en) * | 2018-08-06 | 2021-01-05 | 蓝箭航天空间科技股份有限公司 | Missile interception method, memory and server |
| CN112169232A (en) * | 2020-09-27 | 2021-01-05 | 周鹏 | Throwing type safety foam fire extinguisher |
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- 2001-07-11 AU AUPR6294A patent/AUPR629401A0/en not_active Abandoned
-
2002
- 2002-07-08 JP JP2003512636A patent/JP2004534202A/en active Pending
- 2002-07-08 CN CNA028138457A patent/CN1653313A/en active Pending
- 2002-07-08 EP EP02759871A patent/EP1405028A1/en not_active Withdrawn
- 2002-07-08 WO PCT/AU2002/000909 patent/WO2003006915A1/en active Application Filing
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- 2002-07-08 BR BR0211231-0A patent/BR0211231A/en active Search and Examination
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- 2002-07-08 CA CA002452487A patent/CA2452487A1/en not_active Abandoned
- 2002-07-08 RU RU2004100826/02A patent/RU2293281C2/en not_active IP Right Cessation
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2004
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104776762A (en) * | 2015-04-14 | 2015-07-15 | 湖南工业大学 | Guided missile with pre-destroy and anti-interception functions and forming method thereof |
| CN104776761A (en) * | 2015-04-14 | 2015-07-15 | 湖南工业大学 | Guided missile with pre-destroying and anti-interception functions and construction method for guided missile |
| CN112179213A (en) * | 2018-08-06 | 2021-01-05 | 蓝箭航天空间科技股份有限公司 | Missile interception method, memory and server |
| CN112179213B (en) * | 2018-08-06 | 2022-05-27 | 蓝箭航天空间科技股份有限公司 | Missile interception method, memory and server |
| CN112169232A (en) * | 2020-09-27 | 2021-01-05 | 周鹏 | Throwing type safety foam fire extinguisher |
| CN112169232B (en) * | 2020-09-27 | 2021-07-13 | 周鹏 | Throwing type safety foam fire extinguisher |
Also Published As
| Publication number | Publication date |
|---|---|
| MXPA04000215A (en) | 2004-07-23 |
| RU2004100826A (en) | 2005-06-10 |
| AUPR629401A0 (en) | 2001-08-02 |
| US20040244628A1 (en) | 2004-12-09 |
| EP1405028A1 (en) | 2004-04-07 |
| BR0211231A (en) | 2004-08-10 |
| IL159734A0 (en) | 2004-06-20 |
| JP2004534202A (en) | 2004-11-11 |
| RU2293281C2 (en) | 2007-02-10 |
| ZA200400071B (en) | 2005-04-06 |
| CA2452487A1 (en) | 2003-01-23 |
| WO2003006915A1 (en) | 2003-01-23 |
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