CN112179213A

CN112179213A - Missile interception method, memory and server

Info

Publication number: CN112179213A
Application number: CN202011156095.8A
Authority: CN
Inventors: 张春林
Original assignee: Landspace Technology Co Ltd
Current assignee: Landspace Technology Co Ltd
Priority date: 2018-08-06
Filing date: 2019-01-08
Publication date: 2021-01-05
Anticipated expiration: 2039-01-08
Also published as: CN109141128A; CN110145969B; CN110145969A; CN109631675A; CN209588843U; CN109631675B; CN112179213B

Abstract

The invention provides a missile interception method, a memory and a server. The missile interception method comprises the following steps: detecting the flight trajectory and the flight speed of an incoming missile; calculating the preset launching time and the preset flight trajectory of the interceptor according to the flight speed and the flight trajectory; wherein the interceptor carries primary and secondary ammunition; enabling the interceptor to be launched at the preset launching time and fly along the preset flight trajectory, so as to enter an ammunition throwing area aiming at the incoming missile at a first moment; and the interceptor puts primary and secondary ammunition into the incoming missile at the ammunition putting area, so that the primary and secondary ammunition is detonated at the intercepting area to destroy the incoming missile. According to the missile interception method, the memory and the server, the primary and secondary ammunition groups are deployed near the flight trajectory of the incoming missile, so that various suspicious targets carried by the missile can be cleared in a large range, and the safety of a missile attacker is protected.

Description

Missile interception method, memory and server

The application is a divisional application of an invention patent with the patent name of 'missile interceptor', which is applied for 1, 8 and 2019 on the application date, the application number of 201910014107.4.

Technical Field

The invention relates to the technical field of missile defense, in particular to a missile interception method, a memory and a server.

Background

With the rapid development of missile weapon technology, the missile weapon technology has gradually become a core interest in modern war. The missile weapon can be said to be a miniature image of national military force. In order to improve the missile attack effectiveness, the missile usually has certain penetration capability, which is also an important index for whether the missile can survive.

For the defending party, in order to avoid being attacked by the missile, the missile of the attacking party needs to be effectively intercepted. At present, military strong countries such as the United states and the Russia and the like accelerate the establishment of a defense system of a propelling missile.

In addition, missiles often carry multiple warheads or a large amount of baits and other defense penetration technologies when attacking targets, traditional missile interception is often tired of in actual combat, and a missile interceptor capable of intercepting and being provided with multiple defense penetration technologies is urgently needed, so that the safety of the missile is protected.

Disclosure of Invention

Aiming at the technical problems in the prior art, the invention provides a missile interception method, a memory and a server. Primary and secondary ammunitions can be deployed in the flight trajectory or the nearby area of an incoming missile, and various suspicious targets carried by the missile during flight can be cleared in a large range.

One aspect of the present invention provides a missile interception method, including:

detecting the flight trajectory and the flight speed of an incoming missile; calculating the preset launching time and the preset flight trajectory of the interceptor according to the flight speed and the flight trajectory; wherein the interceptor carries primary and secondary ammunition; enabling the interceptor to be launched at the preset launching time and fly along the preset flight trajectory, so as to enter an ammunition throwing area aiming at the incoming missile at a first moment; and the interceptor puts primary and secondary ammunition into the incoming missile at the ammunition putting area, so that the primary and secondary ammunition is detonated at the intercepting area to destroy the incoming missile.

In one embodiment, the detecting the flight trajectory and flight speed of the incoming missile comprises: detecting radar reflection of the incoming missile and the area nearby the incoming missile so as to calculate the boundary range of the interception area according to the radar reflection; the interceptor puts primary and secondary ammunition into the intercepting area at the putting area, so that the primary and secondary ammunition destroys incoming missiles at the intercepting area, comprising: and the interceptor puts primary and secondary ammunitions according to the boundary range of the interception area, so that the put primary and secondary ammunitions are detonated by a delay detonator and/or a trigger detonator when meeting with the boundary range of the interception area, and suspicious targets in the boundary range are destroyed.

In one embodiment, the predetermined flight trajectory of the interceptor at least partially coincides with the mid-flight trajectory of the incoming missile, the interceptor releases primary and secondary ammunition before contacting the boundary range, so that the primary and secondary ammunition move relative to the incoming missile along the coinciding portion, and the primary and secondary ammunition detonates when at least partially meeting the boundary range.

In one embodiment, the interceptor delivers primary and secondary ammunition according to the shape and shape variations of the boundary extent, such that the delivered primary and secondary ammunition moves in a first three-dimensional shape toward the incoming missile and detonates upon meeting at least 50% of each other with the boundary extent.

In one embodiment, the first three-dimensional shape is at least one of an umbrella shape with an opening facing the incoming missile, a cone shape with a cone tip facing the incoming missile, a rhombus with a rhombus corner facing the incoming missile, and a cylinder shape with an axis coinciding with a flight trajectory direction of the incoming missile.

In one embodiment, the first three-dimensional shape is larger in size than the boundary extent in at least two spatial dimensions.

In one embodiment, the interceptor enters the boundary range at a second time and drops and detonates primary and secondary ammunition within the boundary range, thereby destroying targets within the boundary range.

In one embodiment, the primary and secondary ammunition is detonated when the degree of coincidence with the boundary range is maximized to destroy suspect targets within the boundary range.

In one embodiment, the interceptor projects primary and secondary ammunition into the interception area at the ammunition projection area, such that the primary and secondary ammunition comprises, prior to detonation at the interception area to destroy an incoming missile: monitoring the movement speed and the shape change of the boundary range in the space, and calculating the throwing time and the throwing interval of the primary and secondary ammunition, throwing batches and the number of the primary and secondary ammunition thrown in each batch according to the movement speed and the shape change; the interceptor throws primary and secondary ammunition to the interception area at the ammunition throwing area, so that the primary and secondary ammunition is detonated at the interception area to destroy an incoming missile comprises: and the interceptor puts primary and secondary ammunitions into the boundary range according to the putting opportunity, the putting interval, the release batches and the number of the primary and secondary ammunitions put into each batch, so that the put primary and secondary ammunitions are detonated by a delay fuse and/or a trigger fuse when meeting with the boundary range.

In one embodiment, the interceptor further comprises, prior to dispensing primary and secondary ammunition: and calculating the relative speed and the relative position of the interceptor and the boundary range, selecting the throwing time of the primary and secondary ammunition according to the relative speed and the relative position, and selecting throwing batches, throwing intervals among the batches and the quantity of the primary ammunition in each batch according to the shape and the shape change of the boundary range.

In one embodiment, the release batches of primary and secondary ammunition include a first batch, an intermediate batch and a final batch in turn according to release time, and the number of primary and secondary ammunition released in the intermediate batch is greater than the release amount of primary and secondary ammunition released in the first batch and the final batch.

In one embodiment, the intermediate batches include a plurality of batches, and the number of primary and secondary ammunition thrown in each intermediate batch is greater than the number of primary and secondary ammunition thrown in each of the first and final batches.

In one embodiment, the batches of primary and secondary ammunition are comprised of a plurality, and from the first batch to the last batch, the interval between the primary and secondary ammunition is decreased and then increased, and the amount of ammunition to be thrown per batch is increased and then decreased.

Another aspect of the invention provides a memory having computer-readable instructions stored therein. The missile interception method described above is performed when the computer readable instructions are invoked.

Yet another aspect of the present invention provides a server, wherein the server includes a memory storing an executable program and a processor for calling the executable program to execute the missile interception method according to the embodiment of the present invention.

According to the missile interceptor provided by the embodiment of the invention, a large number of primary and secondary ammunitions are deployed on the flight trajectory of an incoming missile, so that the incoming missile and various incoming targets carried by the incoming missile can be eliminated in a large space range.

Those skilled in the art will recognize additional features and advantages upon reading the detailed description, and upon viewing the accompanying drawings.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

FIG. 1 is a block diagram of a missile interceptor in accordance with an embodiment of the present invention.

FIG. 2 is a schematic flow chart of a missile interception method according to an embodiment of the invention.

Fig. 3 is a schematic diagram of an interceptor of an embodiment of the present invention launching multiple batches of primary and secondary ammunition to attack an attack target.

Fig. 4 is a schematic diagram of the boundary range of the intercepting region according to the embodiment of the present invention.

Fig. 5 is a schematic diagram of primary and secondary ammunition flying relative to an oncoming target with the flight trajectory at least partially coincident in accordance with an embodiment of the present invention.

Fig. 6a-6e are schematic diagrams of primary and secondary ammunition configurations in space deployment according to embodiments of the present invention.

Detailed Description

The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings. Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.

In describing the present invention, two similar terms, namely, an incoming missile and an incoming target, are used simultaneously. Those skilled in the art will appreciate that the entities referred to by different terms are not substantially different. During the initial stages of firing of a ballistic missile, all suspicious targets to be deployed are carried by the ballistic missile. As ballistic missiles become more distant from the earth, they gradually enter the mid-flight phase. For example, after a ballistic missile enters a mid-flight phase, the loads it carries, such as real warheads, false warheads, baits, and other penetration precautions, are released and the targets fly together in space. It follows that these targets are all part of the initial separation of ballistic missiles and therefore may be referred to as incoming missiles. Also, since these objects all belong to suspicious objects, they may also be referred to as suspicious objects. The specific entities referred to by different words employed in this application may be considered similar. For example, these references may be only true warheads, true warheads containing a large number of decoys, multiple warheads, or a combination of multiple warheads and decoys. Those skilled in the art should not be able to narrow, alter or misinterpret the scope of the present invention by interpreting the above-described words in a limiting sense.

Taking ballistic missiles as an example, the defense includes takeoff section defense, ascent section defense, middle section defense and end section defense. The flight time of the ballistic missile in the middle section is relatively long, and the defense time of the defense party is more, so that the establishment of the middle section defense system is also the key point of ballistic missile defense. However, in order to ensure the penetration capability of a ballistic missile, ballistic missiles (particularly ballistic missiles carrying nuclear weapons) are generally equipped with various types of penetration means. These penetration measures include a false warhead, a bait, an aluminum foil, etc. to interfere with radar detection by the defender, so that the defender cannot identify a true warhead target from many targets, and the true warhead can break through the missile defense system of the defender under the shield of these shield devices. In addition, under the condition that the effective load is multiple warheads, the traditional impact interception mode can hardly intercept all missile warheads, so that a large number of real warheads attack the homeland of a defender, and the national security of the attacked party is seriously threatened.

The missile interceptor can be used for intercepting incoming missiles carrying a plurality of warheads or equipped with a large number of sudden prevention measures such as aluminum foils or baits and the like, can completely hit a large number of warheads and baits in a network, and is particularly suitable for intercepting incoming ballistic missiles in the middle section. The application scope of the invention is not limited to intercepting ballistic missiles, but can be other types of incoming missiles.

The invention provides a missile interceptor. Referring to fig. 1, the missile interceptor 2 may include: signal receiver 100, controller 200, advancing mechanism 300, ammunition dispensing mechanism 400. Wherein the ammunition dispensing mechanism 400 stores parent and child ammunition. The signal receiver 100 is used for receiving a firing command signal, and the controller 200 is used for controlling the propulsion mechanism 300 to fire when the signal receiver 100 receives the firing command signal so as to push the missile interceptor to enter a preset flight trajectory. The controller 200 is further configured to control the distribution mechanism 400 to release the primary and secondary ammunition at the preset flight trajectory to form a primary and secondary ammunition group for intercepting an incoming target. According to the missile interceptor, the primary and secondary ammunition groups are distributed in the preset flight trajectory, so that the incoming targets can be cleared in a large range, and the requirement for identifying the true and false incoming targets is greatly reduced.

For example, the primary and secondary ammunition may be equipped with a time delay fuse and/or a trigger fuse, and the controller 200 may be configured to control the primary and secondary ammunition meeting the target of the attack to detonate the target of the attack. Wherein, the controller 200 can control the detonation time of the primary and secondary ammunition, thereby destroying the target of the attack to the maximum extent. For example, when primary and secondary ammunition are simultaneously provided with a trigger fuse, the primary and secondary ammunition detonate upon contact with an oncoming target.

For example, the propulsion mechanism 300 may be a conventional solid propulsion system, in particular a solid rocket propulsion system or a solid missile propulsion system.

In addition, the invention also provides a missile interception method. Referring to fig. 2, the missile interception method includes: s1, detecting the flight trajectory and the flight speed of the incoming missile; s2, calculating the preset launching time and the preset flight trajectory of the interceptor according to the flight speed and the flight trajectory; wherein the interceptor carries primary and secondary ammunition; s3, enabling the interceptor to be launched at the preset launching time and fly along the preset flight trajectory, so as to enter an ammunition throwing area aiming at the incoming missile at the first moment; s4, the interceptor puts primary and secondary ammunition into the incoming missile at the ammunition putting area, so that the primary and secondary ammunition is detonated at the intercepting area to destroy the incoming missile. According to the middle section interception method of the ballistic missile, the primary and secondary ammunition is deployed on the flight trajectory of the incoming missile, so that the suspicious target containing the incoming missile can be destroyed in a large range, the requirement on the interception precision of the ballistic missile is greatly reduced, and the interception success rate of the missile is improved.

For example, in step S1, the midsection-based radar may be used to detect the trajectory and flight speed of an incoming missile. For example, the trajectory of an incoming missile may be determined by radar tracking over a period of time, and the flight speed may be calculated by detecting the positions of the incoming missile at two points in time and the time taken to pass through the two positions. In addition, a reconnaissance satellite deployed in space can be used for detecting the flight trajectory and the speed of the ballistic missile. In this case, for example, the reconnaissance satellite may return information on the flying speed and the flying trajectory of the missile to the ground in real time so that the ground defense system may launch the interceptor according to the flying speed and the flying trajectory of the missile in real time.

The primary and secondary ammunition referred to in the present invention may include, for example, a small bomb which can be deployed in a wide space range, or may be a small nuclear bomb which can be independently detonated. The choice of primary and secondary ammunition may be determined by the nature of the target of attack. For example, in the case of small-sized ammunition, the more the incoming missile is from the military france, the greater the explosive power of the small-sized bomb tends to be (mainly considering that the warheads of the military france are mostly reinforced). For example, in the case of small-sized nuclear ammunition, the equivalent weight of the small-sized nuclear ammunition has no specific requirement because the nuclear ammunition can destroy the target with a high probability. However, since the nuclear bomb may pose a certain threat to the local environment even when it explodes in the outer space, the smaller the equivalent of the small nuclear bomb, the better, and the principle of not detonating the nuclear bomb of the other party as much as possible. In addition, it should be understood that the value of the nuclear bomb carried by the missile of the destruction adversary through the small nuclear bomb is far greater than the hazard brought by the explosion of the small nuclear bomb in the outer space (even including the hazard brought by the small nuclear bomb which can detonate the nuclear bomb of the opponent to the home country). In order to avoid as much as possible the nuclear explosions that may occur in outer space, the primary and secondary ammunition of the present invention is preferably conventional ammunition. For example, these primary and secondary munitions may be independently equipped with guidance systems (e.g., guidance systems may be infrared guidance or satellite guidance) to provide more precise interception of a wide range of incoming targets.

According to the missile interceptor and the middle section intercepting method, a large amount of primary and secondary ammunition released by the missile interceptor can be scattered in space, which is equivalent to that a large amount of explosion points are arranged at intervals in a certain space range. These explosion points can not only destroy the target directly by explosion, but also several explosion points can form a high temperature center after explosion, so that all suspicious targets entering the high temperature center are destroyed or burnt. For example, each detonation point may employ either a delayed detonation or a percussion detonation. And preferably, each explosion point is simultaneously provided with two detonation modes, so that the miss-target phenomenon possibly caused by single impact detonation is avoided, and the situation that the attack precision caused by single delayed detonation is not high is avoided.

Referring to fig. 3, for example, in order to improve the probability of destruction of a threat target, it is also possible to deploy multiple primary and

secondary ammunition clusters

21,22,23 at intervals in the flight direction S1 of an incoming target (within the range of the rectangular structure in fig. 3, incoming missiles and other suspicious targets are included, but the rectangular structure is merely illustrative, and the shape of the boundary formed by the incoming target is not limited to a rectangle) 1, so as to implement multi-stage destruction on the incoming target 1. For example, the first group of primary and secondary ammunition 21 closest to the incoming target 1 may contain the most primary and secondary ammunition. For example, the number of primary and secondary ammunition in each batch of primary and secondary ammunition groups may decrease step by step as the distance from an incoming missile increases. In this case, primary and secondary ammunition contained in the first batch of primary and secondary ammunition clusters 21 may perform a first destruction of the suspect target. For example, the suspicious target 1 is mostly destroyed after the first defeat blow. In special cases (for example, some warheads adopt ultra-strong explosion-proof and high-temperature-proof measures), some trawl fishes can be destroyed for the second time by the secondary batch of primary and secondary ammunition groups 22. At this time, because the suspicious target 1 is damaged at least to some extent after being destroyed by the first primary and secondary ammunition groups, the suspicious target can be easily destroyed after being struck by the second primary and secondary ammunition groups. For example, only a small number of primary and secondary ammunition batches from third primary and secondary ammunition cluster 23 may be deployed to destroy the remaining targets that may be present. According to the missile interceptor and the missile intercepting method provided by the embodiment of the invention, the success rate of missile interception is further improved by carrying out multi-stage destruction on the attacking target, so that the national and local safety is better protected.

In one embodiment, referring to FIG. 4, flying with incoming missile 11 may also include other suspicious targets 12. The real warhead 11 and other suspicious objects 12 may, for example, cover a certain range in space. For example, in the case of a missile deploying a real warhead and various defense measures, the position of the real warhead is difficult to detect through a conventional detection mode. Therefore, in order to completely hit various suspicious targets in the coverage area, primary and secondary ammunition can be deployed by taking the boundary 13 of the coverage area as a reference of the interception area. Specifically, the detection device may map a boundary range of an interception area for the suspicious target according to the detected radar reflection signal area. According to the embodiment of the invention, the primary ammunition and the secondary ammunition can be better deployed by drawing the boundary range of the suspicious target, so that the interception probability of various suspicious targets is improved.

In some embodiments, for example, the boundary range of the suspicious target may also be detected by a detector of the missile interceptor in real time, or the ground detection device cooperates with a detector on the missile interceptor, so that the controller can control the ammunition distributing mechanism to distribute the ammunition according to the boundary range of the suspicious target.

In one embodiment, the detecting the flight trajectory and flight speed of the incoming missile S1 may include: the radar reflections of the incoming missile and its vicinity are detected to calculate the boundary range 13 of the interception area from the radar reflections. Controller 200 of interceptor 2 may deliver primary and secondary ammunition to interception area 13 at the delivery area so that the primary and secondary ammunition destroys incoming missile at interception area 13S 4 includes: the controller 200 of the interceptor 2 controls the ammunition scattering mechanism 400 to throw primary and secondary ammunitions according to the boundary range 13 of the intercepting area, so that the controller 200 controls the thrown primary and secondary ammunitions to be detonated through a delay detonator and/or a trigger detonator when the thrown primary and secondary ammunitions meet with the boundary range 13 of the intercepting area, so as to destroy suspicious targets in the boundary range 13. According to the missile interceptor provided by the embodiment of the invention, the suspicious target in the boundary range can be integrally cleared through the boundary range of the suspicious target and adopting the delay and/or trigger fuze for detonation, so that the interception success rate is greatly improved.

It should be noted that the area of the missile interceptor 2 for putting in the primary and secondary ammunition may be outside the boundary range of the suspicious target, and the putting area may also partially coincide with the boundary range or be within the boundary range. For example, in the case of relative movement between the missile interceptor and the suspicious target, the drop region may be in front of the movement of the suspicious target (the front is in front of the suspicious target in the movement direction of the suspicious target), so that dropped primary and secondary ammunition may have more sufficient time to disperse and deploy, so as to achieve overall destruction of the suspicious target in a better spatial arrangement state.

Referring to fig. 5, in one embodiment, the controller 200 of the interceptor 2 is configured to preset a flight trajectory at least partially coincident with the flight trajectory of the incoming target 11 during the mid-flight period (the coincident portion is a trajectory segment shown as 3 in the figure). The controller 200 of the interceptor 2 may control the ammunition dispensing mechanism 400 to dispense primary and

secondary ammunition

21,22 prior to contact with the boundary extent 13 so that the primary and secondary ammunition move relative to the oncoming target 1 along the overlap 13, and the controller 200 controls the primary and

secondary ammunition

21,22 to detonate upon at least partial intersection with the boundary extent 13.

In this embodiment, the interceptor 2 shown in fig. 5 is launched with primary and secondary ammunition before reaching the coinciding ballistic portion, so that these primary and secondary ammunition meet the incoming target 1 at the coinciding portion 3 after entering the coinciding portion 3. For example, the interceptor 2 may release primary and secondary ammunition from top to bottom before the interceptor 2 reaches the coincident trajectory 3, so that the primary and secondary ammunition enter the coincident trajectory 3. Thereafter, for example, the interceptor 2 may enter the coinciding trajectory 3, thereby further increasing the interception success probability by the interceptor colliding with the incoming target 1 within the coinciding trajectory 3. For example, in this case, the interceptor may be set to end infrared or radar guidance and driven by the thruster to hit the most suspicious target.

In this embodiment, the interceptor 2 may also fly in reverse in the flight trajectory of the oncoming target 1, so that the interceptor 2 may release primary and secondary ammunition ahead of the direction of motion of the interceptor 2 before meeting the oncoming target 1. Under the general condition, the detonation velocity of the conventional explosive is 1000-8500 m/s, and the velocity of the ballistic missile during the middle-section flight is 3000-6000 m/s, so that the primary and secondary ammunitions are detonated when meeting with the attacking target part, and the detonation shock wave of the primary and secondary ammunitions can rapidly reach all the attacking targets, so that the purpose of destroying the targets is achieved.

In addition, the controller 200 may further calculate the shape and the diffusion condition of the blast shock wave when the primary and secondary ammunitions are detonated according to the distribution condition of the primary and secondary ammunitions, the distance between the primary and secondary ammunitions, and the explosion power of each primary and secondary ammunition, so that the center of the interception area meets the blast shock wave when the blast shock wave is diffused to the maximum (based on the fact that the incoming real warhead can be destroyed), thereby further improving the destruction efficacy of the incoming target.

According to the embodiment of the invention, the flight trajectory of the interceptor is partially overlapped with the flight trajectory of the incoming target, and the interceptor, the primary and secondary ammunition and the incoming target fly relatively, so that the impact force of the interceptor, the primary and secondary ammunition and the incoming target can be improved, and the destruction effect of the explosion shock wave of the primary and secondary ammunition on the incoming target can be ensured.

Referring to fig. 6a, in one embodiment, the controller 200 of the interceptor 2 may control the ammunition dispensing mechanism 400 to dispense primary and secondary ammunition 21 according to the shape and shape change of the boundary range such that the dispensed primary and secondary ammunition 21 moves toward the incoming target 1 in a first three-dimensional shape, and the controller 200 may control the primary and secondary ammunition 21 to detonate after meeting each other at least 50% of the boundary range. In fig. 6a, h is the length of the attack target 1 in the flight direction, and h1 is the intersection length of the primary and secondary ammunition 21 and the attack target 1. According to the embodiment of the invention, the primary and secondary ammunitions are detonated when at least more than 50% of the boundary range intersects with each other, and various attacking targets in the boundary range can be better destroyed by enabling a large amount of the primary and secondary ammunitions to enter the boundary range filled with suspicious targets, so that the probability of destroying the true warheads is further improved. The proportion of the above-mentioned fraction of encounters may be greater than 70% in order to improve the effectiveness of the destruction of the suspicious target.

It is noted that according to the illustration of fig. 6a, the primary and secondary ammunition and the target of the incoming attack are located in close proximity to each other after the meeting. In fact, however, the attack targets are often spread in a large space (i.e. the primary and secondary ammunitions are far away from the attack targets), so that the distributed primary and secondary ammunitions are difficult to directly impact the attack targets without adopting a navigation guidance method, which is one of the reasons that the traditional impact interception method has great difficulty in intercepting the attack targets in the middle section.

Referring to fig. 6b-6e, in this embodiment, for example, the first three-dimensional shape is at least one of an umbrella shape with an opening facing the incoming missile, a cone shape with a cone tip facing the incoming missile, a diamond shape with a diamond corner facing the incoming missile, and a cylindrical shape with an axis coinciding with a direction in which a flight trajectory of the incoming missile is located. According to the embodiment of the invention, the space shape of the primary and secondary ammunition is further arranged, so that an oncoming target can be destroyed better. For example, when the primary ammunition and the secondary ammunition adopt an umbrella-shaped structure, the primary ammunition and the secondary ammunition can be detonated through a delay fuse when most of suspicious targets fall into an umbrella mouth. Similarly, when the primary ammunition and the secondary ammunition are arranged in a cylindrical shape, the primary ammunition and the secondary ammunition can be detonated after the suspicious target completely enters the cylinder body, so that surrounding blasting from the periphery of the suspicious target to the suspicious target is realized, and the probability of destroying the suspicious target is further improved.

It is noted that the first three-dimensional shape may be formed on the one hand by the intermittent, batch-wise delivery of primary and secondary ammunition. However, only by adopting the mode of interval and batch delivery, the primary ammunition and the secondary ammunition can only form a relatively simple arrangement mode. On the other hand, the first three-dimensional shape may also be realized by an ammunition dispensing mechanism. Namely, the ammunition distributing mechanism 400 is used for releasing and shaping the primary ammunition and the secondary ammunition, so that the primary ammunition and the secondary ammunition form a specific shape when being released. For example, the first three-dimensional shape may also be implemented by the controller of the interceptor sending flight control instructions to the primary and secondary ammunition to control the motion attitude and speed of the primary and secondary ammunition.

In the above embodiment, the first three-dimensional shape is larger in size in at least two dimensions than the boundary extent. For example, the size of the first three-dimensional shape in three dimensions may be 5% larger than the corresponding size of the boundary range of the suspicious object, respectively, to better destroy the suspicious object. For example, the size of the umbrella opening of the primary and secondary ammunition deployed in an umbrella shape is suspicious larger than the size of the boundary range in the same direction, and the diameter of the cylindrical opening is larger than the maximum size of the boundary range of the suspicious target in the same direction. By adjusting the size of the first three-dimensional shape, the suspicious target can completely enter the opening of the deployed primary and secondary ammunition, so that the destroying effect of the suspicious target is further improved.

For example, the controller 200 may control that primary and secondary ammunition dispersed in the air may be detonated when the coincidence or degree of intersection with the boundary range is maximized to destroy suspicious targets within the boundary range. For example, when the enclosure formed by the dispersed primary and secondary ammunition is larger than the size of the boundary range of the suspicious target, the primary and secondary ammunition may be detonated when all suspicious targets enter the enclosure, thereby increasing the effectiveness of destroying the suspicious target.

In one embodiment, the interceptor may also enter the boundary range 13 of the suspicious target 1 at a second moment, and drop and detonate primary and secondary ammunition 21 within the boundary range 13, thereby destroying targets located within the boundary range 13. When the ammunition carried by the interceptor 2 is conventional ammunition, the distributed ammunition is detonated without being dispersed in time since the relative movement speed of the interceptor 2 and the target 1 is extremely high. In this case, the reach that can be covered by the explosion is greatly reduced, and therefore, a portion of the suspicious object located close to the boundary cannot be destroyed. Therefore, in this embodiment, the interceptor 2 may preferably carry a small nuclear bomb so that it can destroy all suspicious objects from within the boundary of the suspicious object.

In one embodiment, the interceptor further comprises a detector for monitoring the moving speed and the shape change of the boundary range in the space, and the controller 200 calculates the putting timing, the putting interval, the putting batches and the number of the primary and secondary ammunition put in each batch of the primary and secondary ammunition according to the moving speed and the shape change. And the controller controls the ammunition distributing mechanism to distribute the primary and secondary ammunitions to the boundary range according to the distribution time, the distribution interval, the release batches and the number of the primary and secondary ammunitions distributed in each batch, so that the distributed primary and secondary ammunitions are detonated by the delay fuze and/or the trigger fuze when meeting or before meeting with the boundary range. According to the embodiment of the invention, the throwing time, throwing interval, throwing batches, the number of the primary and secondary ammunition thrown in each batch and the like are determined according to the moving speed and shape change of the boundary range of the suspicious target in the air, so that the destroying effect on the suspicious target can be further improved.

For example, the detector 200 may calculate the relative velocity and relative position of the interceptor with respect to the boundary range, and the controller may select the timing of the delivery of primary and secondary ammunition based thereon, and select delivery batches, delivery intervals between batches, and the quantity of primary and secondary ammunition per batch based on the shape and shape variations of the boundary range. For example, the calculations may be performed autonomously by the controller 200 of the interceptor, in which case the interceptor may be equipped with a computer. In addition, the interceptor may also receive the ground radar or the space reconnaissance satellite through its signal receiver 100, and may perform the measurement result, that is, the detection of the suspicious object, by the ground radar or the space reconnaissance satellite, and then, the detection result may be transmitted to the signal receiver 100 of the interceptor. In addition, the controller of the interceptor can obtain the information of the attacking target through the detector and the ground detection system at the same time, thereby further improving the detection accuracy and the interception efficiency.

In one embodiment, the release batches of primary and secondary ammunition include a first batch, an intermediate batch and a final batch in turn according to release time, and the number of primary and secondary ammunition released in the intermediate batch is greater than the release amount of primary and secondary ammunition released in the first batch and the final batch. For example, the intermediate batch includes a plurality of batches, and the number of primary and secondary ammunition put in each intermediate batch is greater than the number of primary and secondary ammunition put in the first batch and the final batch respectively. In the embodiment of the invention, the targeted multistage destruction can be realized by putting the primary and secondary ammunition in batches and adjusting the quantity of the primary and secondary ammunition put in each batch, and in addition, the probability of destroying the real ammunition can be improved by increasing the quantity of the primary and secondary ammunition in the middle batch (the real ammunition is usually hidden between the false ammunition and the bait for flying).

For example, in one embodiment, the batches of primary and secondary ammunition drops include a plurality, and from the first batch to the last batch, the drop interval of the primary and secondary ammunition decreases and then increases, and the number of the ammunition drops per batch increases and then decreases. For example, when an enemy missile employs various penetration measures, the true warhead tends to hide in a neutral position in order to avoid detection by an attacking detection device. For example, the first batch of dropped primary and secondary ammunition may be used to destroy a penetration measure deployed in front of the real warhead (relative to the direction of motion of the incoming target), and then the amount of primary and secondary ammunition may be substantially increased in order to destroy the corresponding real target, the real warhead, intercepted by the missile. Because the probability that the true warhead is at the tail of the suspicious target is reduced, the number of primary and secondary ammunition can be reduced.

It should be noted that the target of attack to which the present invention refers may include a real warhead (one or more real warheads), a false warhead (for example, a balloon camouflage warhead), various kinds of baits or aluminum foils, etc.

Another aspect of the invention provides a missile interception system. The interception system comprises a detection module, a control module and a release module. The detection module is used for detecting the flight trajectory and the flight speed of an incoming missile. The control module is used for: calculating the preset launching time and the preset flight trajectory of the interceptor according to the flight speed and the flight trajectory; wherein the interceptor carries primary and secondary ammunition; controlling the interceptor to be launched at the preset launching time and fly along the preset flight trajectory so as to enter an ammunition throwing area aiming at the incoming missile at a first moment; and controlling the throwing module to throw primary and secondary ammunition to the incoming missile in the ammunition throwing area, so that the primary and secondary ammunition is detonated in the intercepting area to destroy the incoming missile. According to the middle section intercepting system of the ballistic missile, provided by the invention, the primary and secondary ammunition is deployed in the flight direction of an incoming target, so that a suspicious target can be destroyed at a high probability, and the precision requirement of impact type interception on the intercepting missile is greatly reduced.

In one embodiment, the detection module comprises a radar. The radar is used for detecting radar reflection of the attacking target in the space. The control module is used for calculating the boundary range of the intercepting area according to the radar reflection; and controlling the throwing module to throw primary and secondary ammunition according to the boundary range of the interception area, so that the thrown primary and secondary ammunition is detonated when meeting or before meeting with the boundary range of the interception area, and suspicious targets in the boundary range are destroyed. According to the embodiment of the invention, radar reflection of an oncoming target is detected through the radar, and the boundary range of a suspicious target is calculated according to the reflection, so that the putting time and the putting mode of primary and secondary ammunition can be better determined, and the reliability of removing a threat target is further improved.

In one embodiment, the primary and secondary ammunition is configured with a time delay detonator and/or a trigger detonator. On one hand, the detonation time of the primary and secondary ammunition can be set in advance according to the position and the speed of the bullet and the speed of the target, so that the primary and secondary ammunition is detonated when moving to the proper position relative to the suspicious target, and the target is destroyed to the greatest extent. On the other hand, the primary and secondary ammunitions can be simultaneously provided with triggering detonating fuses, so that a large amount of ammunitions distributed in the air can be detonated when contacting with each suspicious target, and the destroying effect on the suspicious target is improved. For example, when the trigger detonator is not triggered, the delay detonator may be detonated at a preset time (with the goal of better defeating the target of the attack) to avoid primary and secondary ammunition failure.

In this embodiment, it is preferred that each primary and secondary ammunition is provided with a delay fuse and a trigger fuse simultaneously. For example, a delayed detonator may be activated to detonate primary and secondary ammunition only when the trigger detonator is not active for a certain period of time, thereby further improving the reliability of destruction of the suspect target.

According to the method and the system for intercepting the middle section of the ballistic missile, provided by the embodiment of the invention, a large number of primary and secondary ammunitions are deployed on the flight trajectory of an incoming missile, so that the threat of the effective load carried by the ballistic missile can be eliminated in a large range, and the homeland security of an attacked country is protected.

Yet another aspect of the invention provides a memory. Wherein the memory stores computer readable instructions. When the computer readable instructions are called, the method for the middle section interception of the ballistic missile is executed.

Yet another aspect of the invention provides a server. The server comprises a memory and a processor, the memory stores an executable program, and the controller is used for calling the executable program so as to execute the ballistic missile middle section interception method of the embodiment of the invention.

Those of ordinary skill in the art will appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware or combinations of computer software and electronic hardware. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the implementation. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.

It is clear to those skilled in the art that, for convenience and brevity of description, the specific working processes of the above-described systems, apparatuses and units may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again.

In the several embodiments provided in the present application, it should be understood that the disclosed system, apparatus and method may be implemented in other ways. For example, the above-described apparatus embodiments are merely illustrative, and for example, the division of the units is only one logical division, and other divisions may be realized in practice, for example, a plurality of units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection through some interfaces, devices or units, and may be in an electrical, mechanical or other form.

The units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, that is, may be located in one place. Or may be distributed over multiple network elements. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.

In addition, functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit.

The functions, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a computer readable memory. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a memory and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned memory comprises: a U disk, a mobile hard disk, and a Read-only memory (ROM). Various media capable of storing program check codes, such as Random Access Memory (RAM), magnetic disk, or optical disk.

The above-described embodiments of the present invention may be combined with each other with corresponding technical effects.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.

The parent application of the present application requires priority of a chinese patent application entitled "middle section interception method and system of ballistic missile" filed on 06.08.2018 with application number 201810884735.3, and filed by beijing blue arrow space science and technology limited company, so the divisional application also enjoys the priority.

Claims

1. A missile interception method is characterized by comprising the following steps:

the method is used for detecting the flight trajectory and the flight speed of an incoming missile, and specifically comprises the following steps: detecting radar reflection of the incoming missile and the area nearby the incoming missile so as to calculate the boundary range of the interception area according to the radar reflection;

calculating the preset launching time and the preset flight trajectory of the interceptor according to the flight speed and the flight trajectory; wherein the interceptor carries primary and secondary ammunition;

enabling the interceptor to be launched at the preset launching time and fly along the preset flight trajectory, so as to enter an ammunition throwing area aiming at the incoming missile at a first moment;

the interceptor throws primary and secondary ammunition to the incoming missile at the ammunition throwing area, so that the primary and secondary ammunition is detonated at the intercepting area to destroy the incoming missile;

wherein the interceptor projects primary and secondary ammunition into the interception area at the ammunition projection area, such that the primary and secondary ammunition comprises, prior to detonation at the interception area to destroy an incoming missile:

and monitoring the movement speed and the shape change of the boundary range in the space, and calculating the throwing time and the throwing interval of the primary and secondary ammunition, throwing batches and the number of the primary and secondary ammunition thrown in each batch according to the movement speed and the shape change.

2. The missile interception method of claim 1, wherein:

the interceptor throws primary and secondary ammunition to the interception area at the ammunition throwing area, so that the primary and secondary ammunition is detonated at the interception area to destroy an incoming missile comprises:

and the interceptor puts primary and secondary ammunitions into the boundary range according to the putting opportunity, the putting interval, the release batches and the number of the primary and secondary ammunitions put into each batch, so that the put primary and secondary ammunitions are detonated by a delay fuse and/or a trigger fuse when meeting with the boundary range.

3. The missile interception method of claim 2, wherein the interceptor further comprises, before the release of primary and secondary ammunition: and calculating the relative speed and the relative position of the interceptor and the boundary range, selecting the throwing time of the primary and secondary ammunition according to the relative speed and the relative position, and selecting throwing batches, throwing intervals among the batches and the quantity of the primary ammunition in each batch according to the shape and the shape change of the boundary range.

4. The missile interception method according to claim 3, wherein the delivery batches of primary and secondary ammunition include a first batch, an intermediate batch and a final batch in turn according to delivery time, and the number of primary and secondary ammunition delivered in the intermediate batch is greater than the delivery amount of primary and secondary ammunition in the first batch and the final batch.

5. The missile interception method according to claim 4, wherein the intermediate batches include a plurality of batches, and the number of primary and secondary ammunition put in each intermediate batch is greater than the number of primary and secondary ammunition put in each of the first batch and the final batch.

6. The missile interception method according to claim 4, wherein the delivery batches of primary and secondary ammunition include a plurality of batches, and the delivery interval time of the primary and secondary ammunition is decreased and then increased from the first batch to the last batch, and the amount of the delivered ammunition per batch is increased and then decreased.

7. A memory, wherein the memory stores computer readable instructions. The missile interception method of any one of claims 1 to 6 being performed when computer readable instructions are invoked.

8. A server, characterized in that the server comprises a memory storing an executable program and a processor for invoking the executable program for performing the missile interception method according to any one of claims 1 to 6.