CN1395674A - Anti-missile missiles - Google Patents
Anti-missile missiles Download PDFInfo
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- CN1395674A CN1395674A CN01804035A CN01804035A CN1395674A CN 1395674 A CN1395674 A CN 1395674A CN 01804035 A CN01804035 A CN 01804035A CN 01804035 A CN01804035 A CN 01804035A CN 1395674 A CN1395674 A CN 1395674A
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- China
- Prior art keywords
- missile
- antimissile
- invasion
- projectile
- guided missile
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
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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
- F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/12—Target-seeking control
Abstract
Anti-missile missile (10) includes a missile configured to track and intercept an incoming missile travelling along path (12). Missile (10) includes at least one barrel assembly (13) having a multiplicity of projectiles stacked axially within barrel assembly (13), together with discrete selectively ignitable propellant charges for propelling the multiplicity of projectiles sequentially through the muzzle of barrel assembly (13). The multiplicities of projectiles produce a fragment column (20) along path (12) to destroy the incoming missile. Alternatively, anti-missile missile (10) can be guided to produce a direct hit at point (18) on the incoming missile. Barrel assembly (13) can include an aiming mechanism so that barrel assembly (13) can be rotated through sector (15, 16) to target path (12).
Description
The present invention relates to antimissile missile, and be used for destruction or make the incapabitated method of invasion guided missile.
Guided missile flies to target at a high speed, so be difficult to intercept and capture so that destroy or make its incapacitation.Tackle the invasion guided missile though can dispose numerous defence artillery fires around target, as the initial unique reaction to threatening, this is unsatisfactory.Usually, interception invasion guided missile is very approaching with target in the manner described above, and if initial reaction can not destroy guided missile or make its incapacitation, then permit no. out second and react.In addition, if destroying guided missile or making its incapacitation near the position of target, then invading guided missile also is a serious threat to target.For example, destroy guided missile in the position near target, the blast of generation also is enough to prang, and the fragment that the invasion guided missile generates has the momentum that is enough to prang, perhaps produces a large amount of refuses around target.
By earlier detection invasion guided missile, allow to take some countermeasures with the form of disposing antimissile missile.Antimissile missile relies on and invades the guided missile collision or explodes near the invasion guided missile.Because the little flying speed of volume of invasion guided missile is fast, so even control by the navigation and the direction of complexity, antimissile missile is also very little with the possibility that the invasion guided missile bumps against.The ability that antimissile missile comes the later stage to revise flight path according to the later stage deviation of invasion guided missile also is limited.
Near the antimissile missile that explodes the invasion guided missile can generate a large amount of fragments on the path of invasion guided missile, and if enough approaching, just can destroy the invasion guided missile or make its incapacitation.
We find, by using following combustion-chamber assembly, it is the combustion-chamber assembly that axially-aligned has many projectiles and can select flammable propellant powder separately in its combustion chamber, just can improve greatly and destroy the invasion guided missile or make its incapabitated probability, wherein propellant powder advances projectile by the combustion chamber gun muzzle on the antimissile missile in proper order.
Therefore, in one embodiment, the invention provides a kind of antimissile missile, comprise that one piece of configuration is used for tackling the guided missile of invasion guided missile, wherein said antimissile missile also comprises at least one combustion-chamber assembly, this assembly has the flammable propellant powder that axially-aligned has many projectiles and can select separately in its at least one combustion chamber, and wherein propellant powder advances numerous projectiles gun muzzle by at least one combustion-chamber assembly in proper order.
In second embodiment, the invention provides a kind of destruction invasion guided missile or make its incapabitated method, this method may further comprise the steps, launch one piece of antimissile missile, wherein said antimissile missile comprises that one piece of configuration is used for tackling the guided missile of described invasion guided missile, and wherein said antimissile missile also comprises at least one combustion-chamber assembly, this assembly has the flammable propellant powder that axially-aligned has many projectiles and can select separately in its at least one combustion chamber, wherein propellant powder advances numerous projectiles gun muzzle by at least one combustion-chamber assembly in proper order, and to the described numerous projectiles of described invasion guided missile sequential transmission.
Usually, the invasion guided missile that is extensive use of such as the ballistic missile of high-altitude is attacked weapon as long distance, and reason is that they are not only very effective, and is difficult in time detect so that take correct defensive measure.Therefore ballistic missile outside atmosphere is difficult to tackle to hit the mode of smashing with the flight of very high speed, wherein hits to smash to depend on antimissile missile and hit, and perhaps explodes near the invasion guided missile.In some embodiments, the invention provides a kind of antimissile missile, the latter can improve the extraatmospheric ballistic missile of destruction or make its incapabitated probability.Simultaneously, can use the present invention when destroying other guided missiles or making its incapacitation, other guided missiles comprise ground-to-air missile, air-to-ground guided missile, air-to-air missile, ground-to-ground missile, ship-to-ship missile, air-to-ship missile and other combinations.The concrete property of invasion guided missile is not restricted to definition of the present invention.
Antimissile missile (that is defending missile) can be for tackling any general type of invasion guided missile.Antimissile missile preferably can hit the invasion guided missile or explode near the invasion guided missile, thereby destroys the invasion guided missile or make its incapacitation.Usually, antimissile missile comprises fuselage, propulsion system, navigation system or explosive (optional), and wherein explosive is used for destroying the invasion guided missile or making its incapacitation.
Antimissile missile generally includes navigation system, and navigation system is followed the tracks of the path of invasion guided missile, and antimissile missile is on the path of interception invasion guided missile.Navigation system is equipped with the path direction-finding device, and the sighting device of this device and at least one combustion-chamber assembly is shaped on the pass.Navigation system preferably has the later stage pointing correction, so that combustion-chamber assembly accurately is advanced to numerous projectiles on the path of invasion guided missile.Even can not proofread and correct the path of antimissile missile,, also can improve the probability that destroys the invasion guided missile by numerous projectiles are advanced on its path.
The purpose of configuration antimissile missile is an interception invasion guided missile.The configuration of antimissile missile is not restricted to the present invention, as long as antimissile missile can carry at least one combustion-chamber assembly, and the path that at least one combustion-chamber assembly can rotate aiming invasion guided missile gets final product.
Can utilize the conventional equipment such as continental rise firing base, boats and ships, aircraft, the emission antimissile missile.
Antimissile missile comprises at least one combustion-chamber assembly, this assembly has the flammable propellant powder that many projectiles is arranged and can select separately of axially-aligned in its at least one combustion chamber, and wherein propellant powder advances numerous projectiles gun muzzle by at least one combustion chamber in proper order.
Combustion-chamber assembly comprises a combustion chamber, many projectiles of axially-aligned in the combustion chamber, and the propellant powder that separates, and wherein projectile is used for the bore of sealed combustion chamber, and propellant powder is used for gun muzzle that order advances the combustion chamber that each projectile uses by the present invention.Above-mentioned combustion-chamber assembly is described in International Patent Application PCT/AU94/00124, PCT/AU96/00459 and PCT/AU97/00713.
That projectile can be is circular, conventional shape or rocket shape, and its empennage can be setovered, so that form stable rotation during from the combustion chamber booster rocket, wherein the combustion chamber is a smooth bore combustion chamber.
The projectile medicine can for solid block with the projectile in effective isolation combustion chamber, also promoting drug can be contained in metal or other rigid containers, the latter comprises an embedded primer with outside contact device, and outside contact device is suitable for contacting and related with the combustion chamber prepositionedly electrically contacts.For example, can equip spring contact to primer, the spring contact of wherein can withdrawing so that cased gunpowder is inserted in the combustion chamber, and when alignment aperture, is ejected in the aperture, combustion chamber, thereby contacts with the contact, combustion chamber that matches.If desired, shell is fusible, perhaps assists propellant combustion with chemical mode.In addition, a pile coupling assembly can be provided or be contained in gunpowder in the shell separately, so that load the combustion chamber again.
Each projectile can comprise a projectile head or expanding unit, so that to small part definition propelling space.Expanding unit can comprise a distance member, and the latter expands backward from projectile head, and adjacent with contiguous projectile assemblies.
Distance member expands to and advances space and projectile head, directly is sent to adjacent distance member thereby will compress powder charge.In this configuration, distance member provides support to extension element, and extension element can be the thin circumferential section in projectile head rear portion.In addition, expanding unit constitutes sealing with the bore of combustion chamber and contacts, and is leaked to projectile head to prevent burning.
Distance member can comprise a rigidity axle bush, axle bush is outwards expanded, so that the thin circumferential section in the projectile head rear portion that is ductile that its sealing contact was lost efficacy, bore engagement with the combustion chamber, so that between distance member, directly transmit the compression powder charge of axial flow, thereby the projectile head of avoiding being ductile is out of shape.
Can be deployed to respectively on distance member and the projectile head replenishing wedging surface, thereby the compression to axial between responding time intervals device and the projectile head impels the bore engagement of projectile head and combustion chamber.In said structure, projectile head and distance member can be loaded in the combustion chamber, and carry out axial displacement, to guarantee the excellent sealing between projectile head and the combustion chamber.Impel the bore engagement of expanding unit and combustion chamber.
Projectile head can be in its taper aperture of definition, rear portion, and in the taper aperture, the accommodation section is deployed in the additional taper on the distance member front end, and wherein moving to axial between projectile head and the additional taper applies radial extension power to projectile head.
The combustion chamber can be nonmetal, and the bore of combustion chamber can comprise groove, all or part of igniter of holding of groove.In this configuration, be embedded in electric lead in the combustion chamber, the latter makes things convenient for the electronic communication between control device and the igniter.For disposable combustion-chamber assembly with finite burn life-span, can utilize above-mentioned configuration, thus can be with integrated manufacturing igniter in combustion chamber and control circuit.
As selection, combustion-chamber assembly can comprise an igniting aperture in the combustion chamber, and igniter is deployed in the position of outside, combustion chamber near this aperture.Utilize a nonmetal combustor outer casing to surround the combustion chamber, and comprise the groove that is used for holding igniter on the shell.Hold electric lead by combustor outer casing, the latter is convenient to the electronic communication between control device and the igniter.Combustor outer casing can be made the component layer plastic casing, the latter comprises the printed circuit layering plastics that are used for igniter.
Combustion-chamber assembly has adjacent projectile separated from one another, and the positioner that separates with projectile of utilization keeps separation relation, and each projectile can comprise an expandable sealing device, so that effectively seal with the bore of combustion chamber.Positioner can be the powder charge between the adjacent projectile, and sealing device comprises the protective cover part on each projectile, and when powder charge in the combustion chamber, each projectile is expanded backward.Can carry out powder charge in the combustion chamber during installing projectile additional or behind the loading projectile (for example, by filling), with arrangement projectile and powder charge formation, the latter is by powder charge in the outside projectile of emission (particularly adjacent outside projectile) the generation combustion chamber.
The rear portion of projectile comprises a protective cover, is a groove that inwardly dwindles around it, is spherical groove as a cone-shaped groove or a part, and charge segment expands in the groove, and projectile moves the expansion that causes the projectile protective cover backward.Because compression, so move to occur backward, compression is to be produced by projectile back moving to wedging of portion before the powder charge, and it is because the anterior metal flow to lighter protective cover part of heavier projectile takes place.
As selection, can be equipped with the peripheral seal flange or the axle bush of diffusion backward for projectile, when projectile was mobile backward, sealing flange or axle bush were to extrinsic deflection, with the bore sealed engagement.In addition, in the bore that projectile is inserted into heat, also can realize sealing, wherein bore shrinks on each hermetic unit of projectile.Projectile can comprise a harder mandrel segment, by powder charge apotting spindle part, axle and the strain circular portion cooperation that can center on the axle mold pressing, to form a single projectile, the latter relies on the metal flow between projectile bullet and the afterbody thereof, so that outwards expand, form sealed engagement with the combustion chamber bore around mandrel segment.
Projectile assemblies comprises a contact face that expands backward, and contact face supports the sealing axle bush, and when projectile is advanced through the combustion chamber, be radially expanded in case with combustion chamber bore sealed engagement.In above-mentioned configuration, powder charge preferably has cylindrical forward portion, the flat horizontal surface adjacency of the latter and projectile.
Projectile is suitable for sealing and/or the location in the groove or utilize annular rib in the bore or the rifling groove in the bore on every side, and can comprise a metal bullet case, and the latter wraps to the rear portion of major general's projectile.Projectile is furnished with reducible peripheral location wing, and wing outwards expands in the interior annular groove of bore, and withdrawal is projectile when emission, so that freely pass through the combustion chamber.
The electronic ignition of the powder charge of order ignition combustion chamber component preferably includes following steps: send ignition signal through stacked projectiles, light the guiding powder charge; Make lighting of guiding powder charge equip next powder charge, so that utilize next ignition signal to encourage.By being inserted in the insulation fuse of disposing between the electrically contacting of normally closing,, inwardly remove the arms of all powder charges from loading the afterbody of combustion chamber.
Can realize the igniting of propellant powder in the electronics mode, igniting also can be used conventional striker type method, and as using the centre-fire primer, primer is lighted outmost projectile, and controlled-ignition is lighted the powder charge of follow-up shell in proper order.Its implementation is that the control burning gases are revealed backward, perhaps control the burning of the fuse row that extend through projectile.
In another form, utilize the separately powder charge related, control igniting, wherein utilize different ignition signals to trigger primer in the electronics mode with primer.For example, can the order of primer sequence in the powder charge with piling up, increase the pulse firing requirement, thereby Electronic Control can select to send the firing pulse that pulse width increases gradually, according to the times selected order, order is lighted powder charge.Yet, preferably utilize set of pulses width signal to light powder charge, and guide the burning of powder charge to equip with arms next powder charge, so that utilize next transmitted pulse to encourage.
In the above-described embodiment, by being inserted in the fuse of disposing between the electrically contacting of normally closing that respectively insulate, from loading the afterbody of combustion chamber, inwardly remove the arms of all powder charges, when transmitting suitable triggering signal to separately guiding powder charge and the insulation fuse is opened, make the contact close by burning fuse.
For example, can perhaps in a continuous manner, perhaps respond the manual repeat actuation of trigger simultaneously, launch many projectiles.In said structure, can transmit the signal of telecommunication from the outside of combustion chamber, perhaps transmit by overlapping projectile, wherein overlapping projectile utilizes cartridge clip to clamp mutually, so that the signal of telecommunication perhaps transmits the signal of telecommunication to electrically contact mode by the combustion chamber.Projectile can comprise control circuit, also can form circuit with the combustion chamber.
Defending missile can carry one or more combustion-chamber assemblies, and all firearms are arranged as: in the front and back of the guided missile of being predicted to the belligerent position of guided missile, to the path scattering or the deployment fragment of invasion guided missile.As selection, also can use a combustion-chamber assembly, on the front and back path of the guided missile of being predicted, advance fragment to the belligerent position of guided missile.Simultaneously, combustion-chamber assembly also can fire shells in the opposite direction, drops to minimum level with the variation with the flight path of antimissile missile.
Projectile is preferably the projectile that can explode as grenade on the path of invasion guided missile, so that forms the fragment column that the invasion guided missile must pass through.Destroy the invasion guided missile or make its incapabitated probability thereby improve.
Can from the combustion chamber that has rifling, launch projectile, and projectile can use the spin counter to measure the distance of flight path/regularly.When launching numerous projectile in the combustion-chamber assembly from the above description, can set in advance the spin counter of each projectile, the time delay of relevant shooting sequence is provided at the desired spacing or the mixture of the fragment of flight path deploy.As selection, the relevant timing mechanism that flies is adjusted in the suitable input that can utilize invasion guided missile path detection device to provide.
Utilize base on the defending missile along the rotation of its axis, realize the pointing correction of combustion-chamber assembly, base itself also can rotate along the guided missile axis.Compare the easier realization of above-mentioned correction with the flight path of later stage deflection defending missile.Can monitor and realize above-mentioned correction on the cycle long approaching, thereby keep low relatively corrective action, open fire so that firearms aim at the mark.
Combustion-chamber assembly can be launched projectile, and projectile explodes when arriving predetermined guided missile path, so as around the invasion guided missile scattering fragment or dispose fragment, be transported to collision probability between the fragment on its path thereby improve invasion guided missile and defending missile.Fragment has enough quality, thereby loses the part ability at least with the feasible invasion of the collision guided missile of fragment, and fragment also can be blast fragment or explosive.Preferably with projectile launch or the guided missile that is deployed to and predicted on the adjacent path, the belligerent position of guided missile, thereby make emission and dispose time delay between the fragment or guided missile to the belligerent Min. that reaches of guided missile so that the flight path of antimissile missile, invasion guided missile and projectile changed drop to minimum level.
We find, for any fixed system, invasion guided missile with known speed given, antimissile missile with known speed, combustion-chamber assembly with known muzzle velocity, the angle of the combustion-chamber assembly that control are constants, and with the length and the location independent of fragment column.Above-mentioned conclusion is applicable to the fragment column of the prediction position of collision front and back of invasion guided missile and antimissile missile, wherein the direction skew 180 of combustion-chamber assembly is spent.Above-mentioned feature advantageous particularly of the present invention, because it allows identical or opposite emission, so that under the situation that influences minimum to the direction of antimissile missile, formation fragment column before and after the prediction position of collision of invasion guided missile and antimissile missile.
More than the defence method of Shuo Ming invasion guided missile constitutes other aspects of the present invention.
Following accompanying drawing and example with reference to the exemplary embodiment that the present invention is described, so that understand the present invention better and realize the present invention, wherein accompanying drawing is:
Fig. 1 schematically illustrates typical antimissile missile and operation thereof.
Fig. 2 represents the typical trajectory analysis.
Fig. 3 represents the approximate analysis of extraatmospheric guided missile and projectile trajectory.
Fig. 1 schematically illustrates defending missile 10, and guided missile 10 is along crossedpath 11 flights towards the path 12 of invading ballistic missile.In the present embodiment, in order to illustrate path 11 and 12 is depicted as the right angle.As shown in Figure 2, more may intersect with the obtuse angle about 135 degree in path 11 and 12.
Defending missile 10 comprises a gun turret 13, the combustion-chamber assembly of the one or more the above-mentioned types of The latter, each has loaded the projectile of grenade type, rifling engagement in projectile and the combustion chamber, so that notice projectile spin when emission, thereby each projectile is in the blast of distance defending missile 10 selected distance places, and its position is consistent with the prediction flight path 12 of invasion guided missile, wherein utilizes the blast of spin counter controls.
During emission, gun turret 13 can be rotated to and flight path 11 position in line, so that, dispose the fragment column of blaster's howitzer along the coverage of invading the missile flight path (for example, in 300 feet scopes in prediction invasion missile flight path 12).As selection, gun turret also can be maintained fixed, and pass through with friction speed chief of breech howitzer, generation is along the needed different angles of flight path location blaster's howitzer, so that the velocity vector that produces by the speed of defending missile, along the emission rate of the speed of the defending missile of flight path 11 and guided missile is provided, thereby obtains the result of vector 15,16 and vector representation therebetween.
The flight path of defending missile 11 is fit to the flight path 12 of interception invasion guided missile, so that directly hit 18, its objective is and destroys the invasion guided missile.Yet if can not directly hit, the destruction that guided missile suffers during by fragment column 20 also can stop it to arrive the destination, perhaps makes its self-destruction when flying towards the target area.For ballistic missile, when downwards by earth atmosphere, above-mentioned situation may appear.
As shown in Figure 2, gun turret is shot under two kinds of independent occasions.At first, on the path 12 of the invasion guided missile of position of collision 18, generate fragment column 20, on the rightabout of position of collision, generate fragment column then, so that after passing through prediction position of collision 18, on the path 12 of invasion guided missile, form another fragment zone 21.
With reference to Fig. 2, as can be seen, before the gun turret shooting generated guiding fragment zone 20, the gun turret shooting generated hangover fragment zone 21.
The example in its time interval that comprises as an illustration, imagination utilize with the defending missile interception of 3,400 feet flights of the per second strategic missile with 26,000 feet flights of per second.For the emission first time for the gun turret that generates hangover fragment zone 21, the imagination gun turret is launched backward with the speed of 2,685 feet of per seconds on the direction parallel with intrusion flight path 12, and its vertical component is 610 feet of per seconds.In addition, the imagination emission? the emission duration of piece projectile is 0.012 second, finishes in 0.559 second, position of collision 18 preceding 1900 feet, and outside position of collision 18, along generating about 300 feet long fragment column on the path 12 of invasion guided missile.
Then, by rotating turret 13, or by rotating defending missile 10 along its longitudinal axis, rotating turret is with the other end emission from antimissile missile.Gun turret is on the direction parallel with path 12, and with the speed emission of 4,193 feet of per seconds, its vertical component is 736 feet of per seconds.Emission beginning 0.456 second, and position of collision 18 preceding 1,552 foot.About 0.012 second of emission duration, and emission? piece projectile, thus the invasion strategic missile near preceding 400 feet, enters fragment column 20 at position of collision 18, and before collision, by 300 feet long fragment column.
By using the combustion-chamber assembly of the above-mentioned type, just can realize said structure, thereby can in the very short duration (in this example, in 0.012 second launch time), advance a large amount of projectiles that when with invasion guided missile path 12 in line the time, projectile explodes.In addition, owing to control combustion-chamber assembly in the electronics mode fully,,, thereby obtain required result with adjustment flight course or pre-flight timing so its circuit can comprise adjustable spin counting and timing device.
Although, also can adopt independent gun turret to shoot to two ends for weight is reduced to minimum level and adopted a gun turret.In addition, also can arrange many gun turrets in guided missile, have predetermined direction and gunpowder, purpose is to generate row's fragment around the expection collision area, thereby increases the effective area of defending missile, and the collision probability of raising and invasion guided missile.
Fig. 3 represents to determine the shooting time of particular case and the approximate calculation of shooting angle.Invasion guided missile 31 is along the ballistic flight of x axle 32 definition, and estimate in the position 33 with antimissile missile 32 collisions, if the angle of attack of antimissile missile with and speed be known, then can calculate the angle of departure from the projectile (not shown) of combustion-chamber assembly 34a and 34b.
E represents that along the distance of invasion missile trajectory, projectile is invaded guided missile at this apart from interception.Phase
Between, the flying distance of invasion guided missile is e, the flying distance of antimissile missile is c:
a＝c×cos(θ-180)
b＝c×sin(θ-180)
θ is the angle of attack of antimissile missile with respect to invasion guided missile direction:
β=α+θ-90 wherein β is a combustion-chamber assembly with respect to the angle of antimissile missile direction (be applicable to the prediction position of collision of invasion guided missile and antimissile missile after emission).
γ=180-β wherein γ is the angle (be applicable to the prediction position of collision preceding emission of invasion guided missile and antimissile missile) of combustion-chamber assembly with respect to the antimissile missile direction.
Commit time (the t of projectile and invasion guided missile
i).
Flight time (the t of projectile
f).
(t launch time of projectile
Emission).
t
Emission=t
i-t
f
According to above formula, can determine the time and the position of projectile interception invasion guided missile, in example 8, list under different invasion missile velocity, different antimissile missile speed and the projectile velocities result of calculation of the intercepting position of the angle-of-attack of antimissile missile and projectile and invasion guided missile in example 1.For convenience's sake, selected some middle point of impingement, but should be appreciated that, the present invention allows a large amount of projectiles of emission in very short time, is wherein launching in very near the scope of invading guided missile.Be appreciated that the approaching more invasion guided missile of emission, error margin is more little, and destroys the invasion guided missile or make its incapabitated possibility also big more.
Below only utilize example that the present invention has been described,, can make various changes and modification and do not deviate from scope of the present invention and essence those of skill in the art.
Example 1
The invasion guided missile
Speed 7924.8ms
-1
Antimissile missile
Speed 1036.32ms
-1
Angle of attack 220 degree
Projectile firing apparatus
Muzzle velocity 426.72ms
-1
| For the first time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile-152.4000-129.5400-106.6800-83.8200-60.9600 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 315.6309 315.6309 315.6309 315.6309 315.6309 (degree) of antimissile missile axle with respect to the collision of invasion guided missile and antimissile missile launch time (second)-0.4133-0.3513-0.2893-0.2273-0.1653 is with respect to the collision of invading guided missile and antimissile missile, projectile is tackled between the time-0.0192-0.0163-0.0135-0.0106-0.0077 that invades guided missile (second) |
| For the second time belligerent with respect to invading 0.0000 guided missile with the collision interception of antimissile missile, the time of (rice) antimissile missile interception invasion guided missile, (second) 0.0000 |
| For the third time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile 152.4000 175.2600 198.1200 220.9800 243.8400 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 135.6309 135.6309 135.6309 135.6309 135.6309 (degree) of antimissile missile axle with respect to launch time (second) of the collision of invasion guided missile and antimissile missile-0.3748-0.4311-0.4873-0.5435-0.5997 with respect to the collision of invading guided missile and antimissile missile, projectile tackle invade guided missile the time 0.0192 0.0221 0.0250 0.0279 0.0308 (second) |
Example 2
The invasion guided missile
Speed 7924.8ms
-1
Antimissile missile
Speed 1676.4ms
-1
Angle of attack 220 degree
Projectile firing apparatus
Muzzle velocity 426.72ms
-1
| For the first time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile-152.4000-129.5400-106.6800-83.8200-60.9600 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 313.3260 313.3260 313.3260 313.3260 313.3260 (degree) of antimissile missile axle with respect to the collision of invasion guided missile and antimissile missile launch time (second)-0.4371-0.3715-0.3060-0.2404-0.1748 is with respect to the collision of invading guided missile and antimissile missile, projectile is tackled between the time-0.0192-0.0163-0.0135-0.0106-0.0077 that invades guided missile (second) |
| For the second time belligerent with respect to invading 0.0000 guided missile with the collision interception of antimissile missile, the time of (rice) antimissile missile interception invasion guided missile, (second) 0.0000 |
| For the third time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile 152.4000 175.2600 198.1200 220.9800 243.8400 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 133.3260 133.3260 133.3260 133.3260 133.3260 (degree) of antimissile missile axle with respect to launch time (second) of the collision of invasion guided missile and antimissile missile-0.3986-0.4584-0.5182-0.5780-0.6378 with respect to the collision of invading guided missile and antimissile missile, projectile tackle invade guided missile the time 0.0192 0.0221 0.0250 0.0279 0.0308 (second) |
Example 3
The invasion guided missile
Speed 7924.8ms
-1
Antimissile missile
Speed 1036.32ms
-1
Angle of attack 220 degree
Projectile firing apparatus
Muzzle velocity 426.72ms
-1
| For the first time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile-152.4000-129.5400-106.6800-83.8200-60.9600 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 348.8475 348.8475 348.8475 348.8475 348.8475 (degree) of antimissile missile axle with respect to the collision of invasion guided missile and antimissile missile launch time (second)-0.4224-0.3591-0.2957-0.2323-0.1690 is with respect to the collision of invading guided missile and antimissile missile, projectile is tackled between the time-0.0192-0.0163-0.0135-0.0106-0.0077 that invades guided missile (second) |
| For the second time belligerent with respect to tackling the time (second) 0.0000 of invading guided missile with collision interception invasion guided missile (rice) 0.0000 antimissile missile of antimissile missile |
| For the third time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile 152.4000 175.2600 198.1200 220.9800 243.8400 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 168.8475 168.8475 168.8475 168.8475 168.8475 (degree) of antimissile missile axle with respect to launch time (second) of the collision of invasion guided missile and antimissile missile-0.3840-0.4416-0.4992-0.5568-0.6144 with respect to the collision of invading guided missile and antimissile missile, projectile tackle invade guided missile the time 0.0192 0.0221 0.0250 0.0279 0.0308 (second) |
Example 4
The invasion guided missile
Speed 7924.8ms
-1
Antimissile missile
Speed 1036.32ms
-1
Angle of attack 220 degree
Projectile firing apparatus
Muzzle velocity 853.44ms
-1
| For the first time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile-152.4000-129.5400-106.6800-83.8200-60.9600 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 315.6309 315.6309 315.6309 315.6309 315.6309 (degree) of antimissile missile axle with respect to the collision of invasion guided missile and antimissile missile launch time (second)-0.2163-0.1838-0.1514-0.1189-0.0865 is with respect to the collision of invading guided missile and antimissile missile, projectile is tackled between the time-0.0192-0.0163-0.0135-0.0106-0.0077 that invades guided missile (second) |
| For the second time belligerent with respect to invading 0.0000 guided missile with the collision interception of antimissile missile, the time of (rice) antimissile missile interception invasion guided missile, (second) 0.0000 |
| For the third time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile 152.4000 175.2600 198.1200 220.9800 243.8400 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 135.6309 135.6309 135.6309 135.6309 135.6309 (degree) of antimissile missile axle with respect to launch time (second) of the collision of invasion guided missile and antimissile missile-0.1778-0.2045-0.2311-0.2578-0.2845 with respect to the collision of invading guided missile and antimissile missile, projectile tackle invade guided missile the time 0.0192 0.0221 0.0250 0.0279 0.0308 (second) |
Example 5
The invasion guided missile
Speed 7924.8ms
-1
Antimissile missile
Speed 1036.32ms
-1
Angle of attack 290 degree
Projectile firing apparatus
Muzzle velocity 426.72ms
-1
| For the first time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile-152.4000-129.5400-106.6800-83.8200-60.9600 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 242.6699 242.6699 242.6699 242.6699 242.6699 (degree) of antimissile missile axle with respect to the collision of invasion guided missile and antimissile missile launch time (second)-0.3632-0.3087-0.2542-0.1998-0.1453 is with respect to the collision of invading guided missile and antimissile missile, projectile is tackled between the time-0.0192-0.0163-0.0135-0.0106-0.0077 that invades guided missile (second) |
| For the second time belligerent with respect to invading 0.0000 guided missile with the collision interception of antimissile missile, the time of (rice) antimissile missile interception invasion guided missile, (second) 0.0000 |
| For the third time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile 152.4000 175.2600 198.1200 220.9800 243.8400 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 62.6699 62.6699 62.6699 62.6699 62.6699 (degree) of antimissile missile axle with respect to launch time (second) of the collision of invasion guided missile and antimissile missile-0.3247-0.3735-0.4222-0.4709-0.5196 with respect to the collision of invading guided missile and antimissile missile, projectile tackle invade guided missile the time 0.0192 0.0221 0.0250 0.0279 0.0308 (second) |
Example 6
The invasion guided missile
Speed 7924.8ms
-1
Antimissile missile
Speed 1036.32ms
-1
Angle of attack 345 degree
Projectile firing apparatus
Muzzle velocity 426.72ms
-1
| For the first time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile-152.4000-129.5400-106.6800-83.8200-60.9600 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 192.7815 192.7815 192.7815 192.7815 192.7815 (degree) of antimissile missile axle with respect to the collision of invasion guided missile and antimissile missile launch time (second)-0.3315-0.2818-0.2320-0.1823-0.1326 is with respect to the collision of invading guided missile and antimissile missile, projectile is tackled between the time-0.0192-0.0163-0.0135-0.0106-0.0077 that invades guided missile (second) |
| For the second time belligerent with respect to invading 0.0000 guided missile with the collision interception of antimissile missile, the time of (rice) antimissile missile interception invasion guided missile, (second) 0.0000 |
| For the third time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile 152.4000 175.2600 198.1200 220.9800 243.8400 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 12.7815 12.7815 12.7815 12.7815 12.7815 (degree) of antimissile missile axle with respect to launch time (second) of the collision of invasion guided missile and antimissile missile-0.2930-0.3370-0.3809-0.4249-0.4689 with respect to the collision of invading guided missile and antimissile missile, projectile tackle invade guided missile the time 0.0192 0.0221 0.0250 0.0279 0.0308 (second) |
Example 7
The invasion guided missile
Speed 7924.8ms
-1
Antimissile missile
Speed 1036.32ms
-1
Angle of attack 220 degree
Projectile firing apparatus
Muzzle velocity 426.72ms
-1
| For the first time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile-152.4000-129.5400-106.6800-83.8200-60.9600 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 315.6309 315.6309 315.6309 315.6309 315.6309 (degree) of antimissile missile axle with respect to the collision of invasion guided missile and antimissile missile launch time (second)-0.4133-0.3513-0.2893-0.2273-0.1653 is with respect to the collision of invading guided missile and antimissile missile, projectile is tackled between the time-0.0192-0.0163-0.0135-0.0106-0.0077 that invades guided missile (second) |
| For the second time belligerent with respect to invading 0.0000 guided missile with the collision interception of antimissile missile, the time of (rice) antimissile missile interception invasion guided missile, (second) 0.0000 |
| For the third time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile 67.2084 92.4215 117.6376 142.8537 168.0667 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 135.6309 135.6309 135.6309 135.6309 135.6309 (degree) of antimissile missile axle with respect to launch time (second) of the collision of invasion guided missile and antimissile missile-0.1653-0.2273-0.2893-0.3514-0.4134 with respect to the collision of invading guided missile and antimissile missile, projectile tackle invade guided missile the time 0.0085 0.0117 0.0148 0.0180 0.0212 (second) |
Example 8
The invasion guided missile
Speed 7924.8ms
-1
Antimissile missile
Speed 1036.32ms
-1
Angle of attack 345 degree
Projectile firing apparatus
Muzzle velocity 426.72ms
-1
| For the first time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile-152.4000-129.5400-106.6800-83.8200-60.9600 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 192.7815 192.7815 192.7815 192.7815 192.7815 (degree) of antimissile missile axle with respect to the collision of invasion guided missile and antimissile missile launch time (second)-0.3315-0.2818-0.2320-0.1823-0.1326 is with respect to the collision of invading guided missile and antimissile missile, projectile is tackled between the time-0.0192-0.0163-0.0135-0.0106-0.0077 that invades guided missile (second) |
| For the second time belligerent with respect to invading 0.0000 guided missile with the collision interception of antimissile missile, the time of (rice) antimissile missile interception invasion guided missile, (second) 0.0000 |
| For the third time in the middle of the belligerent primary collision in the middle of the collision in the middle of the collision the final collision of collision with respect to impact interception invasion guided missile 68.9762 94.8538 120.7313 146.6088 172.4863 (rice) combustion-chamber assembly of antimissile missile with respect to the angle 12.7815 12.7815 12.7815 12.7815 12.7815 (degree) of antimissile missile axle with respect to launch time (second) of the collision of invasion guided missile and antimissile missile-0.1326-0.1824-0.2321-0.2819-0.3317 with respect to the collision of invading guided missile and antimissile missile, projectile tackle invade guided missile the time 0.0087 0.0120 0.0152 0.0185 0.0218 (second) |
Claims (15)
1. antimissile missile, comprise that one piece of configuration is used for tackling the guided missile of invasion guided missile, wherein said antimissile missile also comprises at least one combustion-chamber assembly, this assembly has the flammable propellant powder that axially-aligned has many projectiles and can select separately in its at least one combustion chamber, and wherein propellant powder advances numerous projectiles gun muzzle by at least one combustion-chamber assembly in proper order.
2. according to the antimissile missile of claim 1, wherein antimissile missile comprises navigation system, and navigation system is followed the tracks of the path of invasion guided missile, and antimissile missile is on the path of interception invasion guided missile.
3. according to the antimissile missile of claim 2, wherein navigation system is equipped with the path direction-finding device, and the sighting device of this device and at least one combustion-chamber assembly is shaped on the pass.
4. according to the antimissile missile of claim 1, wherein at least one combustion-chamber assembly comprises a combustion chamber, many projectiles of axially-aligned in the combustion chamber, and the propellant powder that separates, wherein projectile is used for the bore of effective sealed combustion chamber, and propellant powder is used for order and advances each projectile gun muzzle by the combustion chamber
5. according to the antimissile missile of claim 1, wherein from the projectile group of circular, conventional shape or rocket shape, select projectile, its empennage can be setovered, so that form stable rotation during from the combustion chamber booster rocket.
6. according to the antimissile missile of claim 1, wherein utilize propellant powder from least one combustion-chamber assembly, to advance projectile, utilize electric charge to light propellant powder in proper order.
7. according to the antimissile missile of claim 1, wherein arrange at least one combustion-chamber assembly, so that, projectile is deployed on the path of invasion guided missile in the front and back of antimissile missile with the prediction position of collision of invasion guided missile.
8. according to the antimissile missile of claim 1, wherein arrange a combustion-chamber assembly, so that, projectile is deployed on the path of invasion guided missile in the front and back of antimissile missile with the prediction position of collision of invasion guided missile.
9. according to the antimissile missile of claim 1, wherein combustion-chamber assembly is launched projectile simultaneously in the opposite direction, so that the variation of the flight path of antimissile missile is dropped to minimum level.
10. according to the antimissile missile of claim 1, wherein the projectile of projectile for exploding on the path of invasion guided missile as grenade consequently forms the fragment column that the invasion guided missile must pass through.
11. according to the antimissile missile of claim 10, wherein projectile uses the spin counter, measures the distance of projectile and the intersection location in invasion guided missile path/regularly, and in this position blast.
12. antimissile missile according to claim 11, wherein from least one combustion-chamber assembly, launch numerous projectiles, have the spin counter that sets in advance for each projectile, the time delay of relevant shooting sequence is provided at the desired spacing or the mixture of the fragment of the flight path deploy of invading guided missile.
13. according to the antimissile missile of claim 10, aloft timing mechanism is adjusted in the input that wherein can utilize invasion guided missile path sensor to provide.
14. according to the antimissile missile of claim 1, wherein utilize base on the antimissile missile, realize the pointing correction of at least one combustion-chamber assembly along the rotation of its axis and/or the rotation of guided missile axle.
15. one kind is destroyed the invasion guided missile or makes its incapabitated method, may further comprise the steps: launch one piece of antimissile missile, wherein said antimissile missile comprises that one piece of configuration is used for tackling the guided missile of described invasion guided missile, and wherein said antimissile missile also comprises at least one combustion-chamber assembly, this assembly has the flammable propellant powder that axially-aligned has many projectiles and can select separately in its at least one combustion chamber, wherein propellant powder advances numerous projectiles gun muzzle by at least one combustion-chamber assembly in proper order, and to the described numerous projectiles of described invasion guided missile sequential transmission.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| AUPQ5240A AUPQ524000A0 (en) | 2000-01-24 | 2000-01-24 | Anti-missile missiles |
| AUPQ5240 | 2000-01-24 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1395674A true CN1395674A (en) | 2003-02-05 |
Family
ID=3819366
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN01804035A Pending CN1395674A (en) | 2000-01-24 | 2001-01-24 | Anti-missile missiles |
Country Status (13)
| Country | Link |
|---|---|
| US (2) | US20030172832A1 (en) |
| EP (1) | EP1250561A4 (en) |
| JP (1) | JP2003520937A (en) |
| KR (1) | KR20020070505A (en) |
| CN (1) | CN1395674A (en) |
| AU (1) | AUPQ524000A0 (en) |
| BR (1) | BR0107852A (en) |
| CA (1) | CA2396074A1 (en) |
| IL (1) | IL150563A0 (en) |
| MX (1) | MXPA02007157A (en) |
| RU (1) | RU2002120899A (en) |
| WO (1) | WO2001053770A1 (en) |
| ZA (1) | ZA200205339B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109631675A (en) * | 2018-08-06 | 2019-04-16 | 北京蓝箭空间科技有限公司 | Missile intercept device |
| CN110109476A (en) * | 2019-05-06 | 2019-08-09 | 中国人民解放军军事科学院国防科技创新研究院 | Isomery unmanned vehicle independent anti-collision warning method based on collision probability |
| CN110906795A (en) * | 2019-12-13 | 2020-03-24 | 陈忠响 | Middle section interception missile, system and method |
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| US6997110B2 (en) * | 2001-09-05 | 2006-02-14 | Omnitek Partners, Llc. | Deployable bullets |
| AU2002950846A0 (en) * | 2002-08-16 | 2002-09-12 | Metal Storm Limited | Interception missile and method of interception |
| EP1620693A2 (en) | 2003-05-06 | 2006-02-01 | Bae Systems Applied Technologies, Inc. | Air-based vertical launch ballistic missile defense |
| US8130137B1 (en) | 2005-07-26 | 2012-03-06 | Lockheed Martin Corporation | Template updated boost algorithm |
| US8809755B1 (en) * | 2005-12-02 | 2014-08-19 | Orbital Research Inc. | Aircraft, missile, projectile or underwater vehicle with improved control system and method of using |
| USH2236H1 (en) * | 2006-09-29 | 2010-04-06 | The United States Of America As Represented By The Secretary Of The Navy | Method for defeating a warhead that carries submunitions |
| IL179224A (en) * | 2006-11-13 | 2012-09-24 | Rafael Advanced Defense Sys | Warhead for intercepting system |
| US8106340B1 (en) * | 2009-03-02 | 2012-01-31 | Lockheed Martin Corporation | Generalized midcourse missile guidance |
| CN102252567B (en) * | 2010-09-21 | 2013-10-09 | 哈尔滨工业大学 | Light energy-storage-type rapid unfolding mechanism |
| CN103090745A (en) * | 2013-02-05 | 2013-05-08 | 朱旭望 | Guided missile with middle-section speed change and anti-intercept method thereof |
| IL232301B (en) | 2014-04-28 | 2018-11-29 | Rafael Advanced Defense Systems Ltd | System and method for neutralizing shaped-charge threats |
| RU2646183C1 (en) * | 2017-04-21 | 2018-03-01 | Николай Евгеньевич Староверов | Ballistic platform with anti-missiles |
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| US1303877A (en) * | 1919-05-20 | frawcofs | ||
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| US2925965A (en) * | 1956-03-07 | 1960-02-23 | Collins Radio Co | Guided missile ordnance system |
| US3153367A (en) * | 1959-07-23 | 1964-10-20 | Frederick W Ross | Anti-missile system |
| US4210082A (en) * | 1971-07-30 | 1980-07-01 | The United States Of America As Represented By The Secretary Of The Army | Sub projectile or flechette launch system |
| US3984175A (en) * | 1975-03-13 | 1976-10-05 | International Tools (1973) Ltd. | Pavement marker |
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| US4444117A (en) * | 1981-03-30 | 1984-04-24 | The Boeing Company | Stacked tube submunition dispenser |
| GB8531282D0 (en) * | 1985-12-19 | 1999-10-27 | Short Brothers Plc | Method of,and projectile for,engaging a target |
| US4925129A (en) * | 1986-04-26 | 1990-05-15 | British Aerospace Public Limited Company | Missile defence system |
| DE3636055C1 (en) * | 1986-10-23 | 1989-12-21 | Messerschmitt Boelkow Blohm | Submunition release device |
| GB2226624B (en) * | 1987-12-12 | 1991-07-03 | Thorn Emi Electronics Ltd | Projectile |
| DE8812000U1 (en) * | 1988-09-22 | 1990-02-08 | Rheinmetall Gmbh, 4000 Duesseldorf, De | |
| DE3835888A1 (en) * | 1988-10-21 | 1990-04-26 | Rheinmetall Gmbh | GRENADE BULLET |
| GB8918267D0 (en) * | 1989-08-10 | 1990-04-25 | British Aerospace | Weapon systems |
| GB9014653D0 (en) * | 1989-10-18 | 1997-11-05 | Messerschmitt Boelkow Blohm | Auswerfen und verteilen von submunition |
| DE4133405C2 (en) * | 1991-10-09 | 1995-02-23 | Deutsche Aerospace | Submunition for low-flying use |
| US5191169A (en) * | 1991-12-23 | 1993-03-02 | Olin Corporation | Multiple EFP cluster module warhead |
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| CA2251076A1 (en) * | 1997-10-31 | 1999-04-30 | David P. Smith | Countermeasure apparatus for deploying interceptor elements from a spin stabilized rocket |
-
2000
- 2000-01-24 AU AUPQ5240A patent/AUPQ524000A0/en not_active Abandoned
-
2001
- 2001-01-24 EP EP01911237A patent/EP1250561A4/en not_active Withdrawn
- 2001-01-24 US US10/181,453 patent/US20030172832A1/en not_active Abandoned
- 2001-01-24 RU RU2002120899/02A patent/RU2002120899A/en not_active Application Discontinuation
- 2001-01-24 JP JP2001554012A patent/JP2003520937A/en active Pending
- 2001-01-24 WO PCT/AU2001/000063 patent/WO2001053770A1/en not_active Application Discontinuation
- 2001-01-24 IL IL15056301A patent/IL150563A0/en unknown
- 2001-01-24 KR KR1020027009442A patent/KR20020070505A/en not_active Application Discontinuation
- 2001-01-24 CA CA002396074A patent/CA2396074A1/en not_active Abandoned
- 2001-01-24 CN CN01804035A patent/CN1395674A/en active Pending
- 2001-01-24 MX MXPA02007157A patent/MXPA02007157A/en unknown
- 2001-01-24 BR BR0107852-6A patent/BR0107852A/en not_active IP Right Cessation
-
2002
- 2002-07-04 ZA ZA200205339A patent/ZA200205339B/en unknown
-
2005
- 2005-01-24 US US11/039,836 patent/US20060065150A1/en not_active Abandoned
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109631675A (en) * | 2018-08-06 | 2019-04-16 | 北京蓝箭空间科技有限公司 | Missile intercept device |
| CN110145969A (en) * | 2018-08-06 | 2019-08-20 | 蓝箭航天空间科技股份有限公司 | Missile intercept method and server |
| CN109631675B (en) * | 2018-08-06 | 2024-03-26 | 蓝箭航天空间科技股份有限公司 | Missile interceptor |
| CN110109476A (en) * | 2019-05-06 | 2019-08-09 | 中国人民解放军军事科学院国防科技创新研究院 | Isomery unmanned vehicle independent anti-collision warning method based on collision probability |
| CN110906795A (en) * | 2019-12-13 | 2020-03-24 | 陈忠响 | Middle section interception missile, system and method |
| CN110906795B (en) * | 2019-12-13 | 2022-07-05 | 谢勋 | Middle section interception missile, system and method |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2002120899A (en) | 2004-02-20 |
| KR20020070505A (en) | 2002-09-09 |
| US20030172832A1 (en) | 2003-09-18 |
| MXPA02007157A (en) | 2004-09-06 |
| JP2003520937A (en) | 2003-07-08 |
| AUPQ524000A0 (en) | 2000-06-15 |
| CA2396074A1 (en) | 2001-07-26 |
| US20060065150A1 (en) | 2006-03-30 |
| BR0107852A (en) | 2002-10-29 |
| ZA200205339B (en) | 2003-08-25 |
| IL150563A0 (en) | 2003-02-12 |
| EP1250561A4 (en) | 2003-04-16 |
| EP1250561A1 (en) | 2002-10-23 |
| WO2001053770A1 (en) | 2001-07-26 |
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