CN212253846U - Low-altitude low-speed small target low-cost interception system - Google Patents
Low-altitude low-speed small target low-cost interception system Download PDFInfo
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- CN212253846U CN212253846U CN202021835664.7U CN202021835664U CN212253846U CN 212253846 U CN212253846 U CN 212253846U CN 202021835664 U CN202021835664 U CN 202021835664U CN 212253846 U CN212253846 U CN 212253846U
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Abstract
The utility model discloses a low-altitude slow-speed small-sized target low-cost interception system, which consists of a vehicle-mounted multi-connected launching system, a multi-target detection and positioning indication radar, a data transmission ground end, a ground control system and an interception bullet; according to the method, a plurality of interception targets can be detected and positioned and indicated through the multi-target detection and positioning indication radar, the interception bomb is electrically driven, the wing surface can be folded and unfolded, a strapdown image seeker and a navigation and flight control system are carried, the interception cost can be greatly reduced under the condition that the interception precision is guaranteed, and meanwhile, due to the fact that the interception bomb is far in flight distance and is guided in a flight path, the targets can be intercepted in the far distance.
Description
Technical Field
The utility model belongs to the technical field of the aircraft interception, concretely relates to low-altitude low-cost interception system of small-size target at a slow speed.
Background
The low-slow small target generally refers to an aircraft with the flying height of not more than 1000m, the flying speed of not more than 200km/h and the radar reflection area of not more than 2m2, and has the characteristics of low cost, mature technology, small target characteristics and the like. With the maturity of unmanned aerial vehicle technology and the popularization of unmanned aerial vehicle products with various purposes, the low-slow small aircraft is extremely easy to obtain and operate, is continuously used for carrying dangerous articles such as explosives and the like by lawless persons and hostile forces to execute various attack and destruction activities, and particularly when a plurality of low-slow small targets attack specific targets in a group attack mode, how to effectively intercept and dispose the low-slow small targets becomes an urgent demand for defending the low-slow small targets.
At present, various interception technologies are developed for effectively dealing with low-speed and small-size targets, and comprise short-range air defense missiles, high-energy lasers, anti-unmanned aerial vehicle interference guns, net missiles, high-energy microwaves and the like, wherein the short-range air defense missiles are in a traditional interception mode, and the single-shot interception cost is high; the interception distance of the high-energy laser is short, the requirement on ground tracking precision is high, and a plurality of targets cannot be intercepted simultaneously; the interference distance of the anti-unmanned aerial vehicle interference gun is short; the net bomb has short interception distance, and has large interception difficulty for targets with higher flying height and larger size; the high-energy microwave has large energy requirement and short interception distance.
Therefore, it is urgently needed to develop a low-altitude slow-speed small target low-cost interception system to solve the above problems.
Disclosure of Invention
For solving the problem that proposes among the above-mentioned background art, the utility model provides a low-altitude is low-cost interception system of small-size target at a slow speed.
In order to achieve the above object, the utility model provides a following technical scheme:
a low-altitude slow-speed small-target low-cost interception system, comprising:
the vehicle-mounted multi-connected launching system is used for loading and launching the intercepting bullets for interception; a plurality of intercepting bullets are installed in the vehicle-mounted multi-connected launching system;
the multi-target detection and positioning indication radar is used for detecting and positioning and indicating the intercepted targets and acquiring the space position coordinates of all the attacking intercepted targets in real time;
the data transmission ground end is used for transmitting the position coordinate information of the intercepted targets acquired by the multi-target detection and positioning indication radar to each intercepted projectile in real time and receiving the downloaded flight state information of each intercepted projectile;
the ground control system is used for target distribution, giving out emission instructions and task decisions;
the plurality of intercepting bullets are used for carrying a warhead and intercepting an attacking intercepting target;
the ground control system is in communication connection with the multi-target detection and positioning indication radar and the data transmission ground end respectively, a control signal output end of the ground control system is fixedly connected with a control signal input end of the vehicle-mounted multi-connected launching system, and the data transmission ground end is in communication connection with the plurality of intercepting bullets.
Specifically, the catch bomb includes:
the missile wing can be folded into a missile body;
a warhead; the warhead is arranged at the head part in the foldable missile body with the missile wing;
the laser proximity fuse is used for sensing the intercepted target after the intercepted bomb reaches the vicinity of the target;
a collision fuse; the collision blasting fuse is arranged at the rear end of the low attached blasting warhead and is used for detonating the warhead after the interception bomb collides with the target;
a strapdown image seeker; the strapdown image seeker is mounted on the intercepting bullet part and used for automatically capturing and tracking an intercepting target;
the navigation and flight control system is used for sensing the flight state and stabilizing the flight attitude when the intercepting bullet flies, controlling the intercepting bullet to fly according to a route and controlling the intercepting bullet to autonomously fly to an intercepting target under the guidance of the strapdown image seeker;
the satellite positioning antenna is used for providing satellite positioning information for the navigation and flight control system;
a power management system;
an energy battery pack;
a data transmission missile-borne end;
a power system; the power system is arranged at the tail part of the missile wing foldable missile body;
the data transmission missile-borne terminal is in communication connection with the data transmission ground terminal; the action ends of the laser proximity fuse and the collision fuse are connected with the warhead; the signal output end of the satellite positioning antenna and the signal output end of the strapdown image seeker are connected with the signal input end of the navigation and flight control system; the data transmission missile-borne end is in communication connection with the navigation and flight control system; the signal output end of the navigation and flight control system is connected with the signal input end of the power system; the energy battery pack is electrically connected with the laser proximity fuse, the strapdown image seeker, the navigation and flight control system, the satellite positioning antenna, the data transmission missile-borne terminal and the power system through the power management system.
Specifically, the warhead includes a housing and a main charge disposed within the housing.
Preferably, the housing is a low density non-metallic material housing.
Further, the housing is made of nylon 66.
Preferably, the laser proximity fuse comprises three detection units, the three detection units are uniformly distributed along the circumferential direction of the missile body, any two detection units are arranged at an interval of 120 degrees, and the three detection units are arranged at the head of the missile wing foldable missile body.
Compared with the prior art, the beneficial effects of the utility model are that:
1. the intercepting bullet is driven by electric power, is distributed with a high lift-drag ratio, can cruise for a long time, is provided with a data transmission bullet carrying end, can remotely transmit remote control and remote measurement information, automatically captures and tracks a target by adopting an image guide head at the tail end, automatically updates a task route according to a target point updated in real time by a navigation and flight control system, can intercept the target remotely, and has high autonomy degree;
2. the intercepting bullet adopts a foldable wing surface type bullet body, so that loading and quick launching of a plurality of multi-connected launching barrels are facilitated;
3. the interception bullet adopts a low-density non-metallic material shell to blast the warhead, and the damage range is small when the target is intercepted;
4. the multi-target detection and positioning indication radar is adopted, the space position coordinates of a plurality of incoming low-slow small targets can be given at the same time, the detection tracking and real-time positioning indication can be carried out on the plurality of incoming low-slow small targets, meanwhile, a plurality of interception bombs can be launched rapidly and continuously by adopting a multi-connected launcher, and the purpose of intercepting the plurality of incoming low-slow small targets at the same time can be realized;
5. guidance in the intercepting bullet adopts route guidance updated in real time according to the position coordinates of the target, so that the final guidance section target can be ensured to enter a view field of a seeker during long-distance interception, and the target capturing probability is improved;
6. the guidance in the intercepting bomb adopts real-time updated route guidance according to the coordinates of the target position, and the final guidance adopts image guidance, so that the intercepting precision of the terminal intercepting bomb can be improved while the long-distance intercepting distance is realized, and the requirements on the precision of the multi-target detection and positioning indication radar are reduced.
Drawings
FIG. 1 is a block diagram of the intercepting system of the present application;
FIG. 2 is a schematic view of the structure of the interceptor projectile of the present application;
FIG. 3 is a schematic flow diagram of an interception method of the present application;
in the figure: the method comprises the following steps of 1-strapdown image seeker, 2-laser proximity fuse, 3-satellite positioning antenna, 4-power management system, 5-energy battery pack, 6-data transmission missile-borne end, 7-power system, 8-navigation and flight control system, 9-collision fuse and 10-warhead.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
The utility model provides a following technical scheme:
as shown in fig. 1, a low-altitude slow-speed small target low-cost interception system includes:
the vehicle-mounted multi-connected launching system is used for loading and launching the intercepting bullets for interception; a plurality of intercepting bullets are installed in the vehicle-mounted multi-connected launching system; the vehicle-mounted multi-connected launching system generally comprises a vehicle-mounted multi-connected launching tube, wherein a plurality of intercepting bullets are stored in the vehicle-mounted multi-connected launching tube;
the multi-target detection and positioning indication radar is used for detecting and positioning and indicating the intercepted targets and acquiring the space position coordinates of all the attacking intercepted targets in real time;
the data transmission ground end is used for transmitting the position coordinate information of the intercepted targets acquired by the multi-target detection and positioning indication radar to each intercepted projectile in real time and receiving the downloaded flight state information of each intercepted projectile;
the ground control system is used for target distribution, giving out emission instructions and task decisions;
a plurality of interception bullets for carrying the warhead 10 and intercepting an incoming interception target;
the ground control system is in communication connection with the multi-target detection and positioning indication radar and the data transmission ground end respectively, a control signal output end of the ground control system is fixedly connected with a control signal input end of the vehicle-mounted multi-connected launching system, and the data transmission ground end is in communication connection with the plurality of intercepting bullets.
As shown in fig. 2, the catching bomb includes:
the missile wing can be folded into a missile body;
a warhead 10; the warhead 10 is arranged at the inner head of the foldable missile body with missile wings;
the laser proximity fuse 2 is used for sensing the intercepted target after the intercepted bomb reaches the vicinity of the target;
a collision fuse 9; the collision blasting fuse 9 is arranged at the rear end of the low attached blasting warhead 10 and is used for detonating the warhead 10 after the interception bomb collides with the target;
a strapdown image seeker 1; the strapdown image seeker 1 is arranged at the head part of the intercepting bullet and is used for automatically capturing and tracking an intercepting target;
the navigation and flight control system 8 is used for sensing the flight state and stabilizing the flight attitude when the intercepting bullet flies, controlling the intercepting bullet to fly according to a route and controlling the intercepting bullet to autonomously fly to an intercepting target under the guidance of the strapdown image seeker 1;
a satellite positioning antenna 3 for providing satellite positioning information to the navigation and flight control system 8;
a power management system 4;
an energy battery pack 5;
a data transmission missile-borne end 6;
a power system 7; the power system 7 is arranged at the tail part of the missile wing foldable missile body;
the data transmission missile-borne terminal 6 is in communication connection with the data transmission ground terminal; the action ends of the laser proximity fuse 2 and the collision fuse 9 are connected with the warhead 10; the signal output end of the satellite positioning antenna 3 and the signal output end of the strapdown image seeker 1 are connected with the signal input end of the navigation and flight control system 8; the data transmission missile-borne end 6 is in communication connection with a navigation and flight control system 8; the signal output end of the navigation and flight control system 8 is connected with the signal input end of the power system 7; the energy battery pack 5 is in power supply connection with the laser proximity fuse 2, the strapdown image seeker 1, the navigation and flight control system 8, the satellite positioning antenna 3, the data transmission missile-borne terminal 6 and the power system 7 through the power management system 4.
In some embodiments, the missile wing foldable missile body can be folded when being loaded into the launching tube of the vehicle-mounted multi-combined-loading launching system, the outer diameter of each wing surface does not exceed the maximum outer contour circle diameter of the missile body after being folded, the length of each wing surface does not exceed the maximum length of the missile body, and each wing surface can be automatically unfolded and locked without rebounding after the missile body is launched out of the launching tube, so that loading and quick launching through the multi-combined-loading launching tube are facilitated.
In the embodiment, the navigation and flight control system 8 adopts a low-cost MEMS device, and the cost of the single interception bomb is low.
As shown in fig. 2, the strapdown image seeker 1 is positioned at the missile wing foldable missile body head; the laser proximity detonator 2 is positioned at the head of the missile wing foldable missile body; the satellite positioning antenna 3 is leaked on the surface of the missile wing foldable missile body; the power management system 4 is positioned behind the collision fuse 9; the energy battery pack 5 is positioned behind the power management system 4, and the energy battery pack 5 is connected with the power management system 4 through a power supply cable; the data transmission missile-borne end 6 is hung above the navigation and flight control system 8, and a bottom plate of the data transmission missile-borne end 6 is used as an intercepting missile cabin cover and connected with the missile wing foldable missile body framework, so that heat dissipation of the data transmission missile-borne end 6 in the flight process is facilitated; the navigation and flight control system 8 is positioned below the data transmission missile-borne end 6 and fixedly connected with the foldable missile body framework of the missile wing.
Specifically, the warhead 10 includes a housing and a main charge disposed within the housing.
Preferably, the housing is a low density non-metallic material housing.
In the embodiment, the low-incidental-blasting warhead 10 is loaded by the intercepting bomb, the damage to the target is realized through the detonation wave, and the shell of the warhead 10 is made of a low-density non-metallic material, so that the incidental damage after the detonation of the warhead 10 can be reduced.
Further, the housing is made of nylon 66.
Preferably, the laser proximity fuse 2 comprises three detection units, the three detection units are uniformly distributed along the circumferential direction of the missile body, any two detection units are arranged at an interval of 120 degrees, and the three detection units are arranged at the head of the missile wing foldable missile body.
As shown in fig. 3, the intercepting method of the low-altitude slow-speed small target low-cost intercepting system includes the following steps:
s1, finding and continuously tracking the intercepted target by the multi-target detection and positioning indication radar;
s2, resolving the space position coordinates of the intercepted targets in real time by the multi-target detection and positioning indication radar, and transmitting the space position coordinates to the ground control system in real time;
s3, the ground command control system completes the distribution of the interception targets and determines the number, the serial numbers and the emission sequence of the interception bombs to be emitted;
s4, powering on the interception bomb to be launched by the vehicle-mounted multi-connected launching system according to the instruction of the ground instruction control system, and completing self-checking;
s5, binding the spatial position coordinates of the interception targets acquired by the multi-target detection and positioning indication radar to each interception bullet according to the task allocation condition by the ground control system;
s6, each interception bullet automatically finishes planning a mission route according to the bound interception target position coordinates and is in a waiting state;
s7, the ground control system sends an interception bullet transmitting instruction to the vehicle-mounted multi-connected transmitting system according to a preset transmitting sequence;
s8, launching the intercepting projectile out of the barrel, unfolding and locking each wing surface, starting the power system 7, flying to an intercepting target according to an initially planned mission route after climbing to a safe height, and entering a middle guidance section guided by a planned route; in the process of climbing the intercepting bullet, keeping a given climbing angle and a given rolling angle to climb to a preset safety height;
s9, uploading the coordinates of the interception target positions positioned by the multi-target detection and positioning indication radar in real time to each interception bullet by the data transmission ground end;
s10, each interception bullet automatically updates a task route according to the updated interception target position coordinates acquired in real time, and continues flying to approach the interception target;
s11, judging whether the interception target enters the capture distance of the strapdown image seeker 1, if so, entering the step S12, and otherwise, entering the step S10;
s12, the intercepting missile guiding head automatically captures the intercepting target and continuously tracks the intercepting target; the interception bullet automatically enters a final guide section, and the navigation and flight control system 8 enters an attack mode;
s13, the intercepting bullet automatically enters an image guidance attack mode and flies to an intercepting target under the action of the strapdown image seeker 1;
s14, whether the laser proximity fuse 2 detects an interception target or not is judged, if yes, the step S15 is executed, and if not, the step S16 is executed;
s15, detecting the intercepted target under the action of the laser proximity fuse 2, and entering the step S19 after sensing the intercepted target;
s16, judging whether the object collides with the interception target, if so, entering a step S17, otherwise, entering a step S18;
s17, the collision fuse 9 acts, and the step S19 is carried out;
s18, the interception bomb is self-destroyed under the action of the collision blasting fuse 9 after falling to the ground;
and S19, detonating the warhead 10 to damage the target and complete the interception of the target.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. A low-altitude slow-speed small-size target low-cost interception system is characterized by comprising:
the vehicle-mounted multi-connected launching system is used for loading and launching the intercepting bullets for interception; a plurality of intercepting bullets are installed in the vehicle-mounted multi-connected launching system;
the multi-target detection and positioning indication radar is used for detecting and positioning and indicating the intercepted targets and acquiring the space position coordinates of all the attacking intercepted targets in real time;
the data transmission ground end is used for transmitting the position coordinate information of the intercepted targets acquired by the multi-target detection and positioning indication radar to each intercepted projectile in real time and receiving the downloaded flight state information of each intercepted projectile;
the ground control system is used for target distribution, giving out emission instructions and task decisions;
the plurality of intercepting bullets are used for carrying a warhead and intercepting an attacking intercepting target;
the ground control system is in communication connection with the multi-target detection and positioning indication radar and the data transmission ground end respectively, a control signal output end of the ground control system is fixedly connected with a control signal input end of the vehicle-mounted multi-connected launching system, and the data transmission ground end is in communication connection with the plurality of intercepting bullets.
2. A low-altitude slow-speed small-sized target low-cost interception system according to claim 1, characterized in that said interception bullet comprises:
the missile wing can be folded into a missile body;
a warhead; the warhead is arranged at the head part in the foldable missile body with the missile wing;
the laser proximity fuse is used for sensing the intercepted target after the intercepted bomb reaches the vicinity of the target;
a collision fuse; the collision blasting fuse is arranged at the rear end of the low attached blasting warhead and is used for detonating the warhead after the interception bomb collides with the target;
a strapdown image seeker; the strapdown image seeker is mounted on the intercepting bullet part and used for automatically capturing and tracking an intercepting target;
the navigation and flight control system is used for sensing the flight state and stabilizing the flight attitude when the intercepting bullet flies, controlling the intercepting bullet to fly according to a route and controlling the intercepting bullet to autonomously fly to an intercepting target under the guidance of the strapdown image seeker;
the satellite positioning antenna is used for providing satellite positioning information for the navigation and flight control system;
a power management system;
an energy battery pack;
a data transmission missile-borne end;
a power system; the power system is arranged at the tail part of the missile wing foldable missile body;
the data transmission missile-borne terminal is in communication connection with the data transmission ground terminal; the action ends of the laser proximity fuse and the collision fuse are connected with the warhead; the signal output end of the satellite positioning antenna and the signal output end of the strapdown image seeker are connected with the signal input end of the navigation and flight control system; the data transmission missile-borne end is in communication connection with the navigation and flight control system; the signal output end of the navigation and flight control system is connected with the signal input end of the power system; the energy battery pack is electrically connected with the laser proximity fuse, the strapdown image seeker, the navigation and flight control system, the satellite positioning antenna, the data transmission missile-borne terminal and the power system through the power management system.
3. A low altitude, slow speed, small object, low cost interception system according to claim 2 wherein the warhead comprises a housing and a main charge placed inside the housing.
4. A low altitude, slow speed, small object, low cost interception system according to claim 3 characterized by the fact that said housing is a low density non-metallic material housing.
5. A low altitude slow speed small object low cost interception system according to claim 4 characterized by that said housing is made of nylon 66.
6. The low-altitude slow-speed small-size target low-cost interception system according to claim 2, wherein the laser proximity fuse comprises three detection units, the three detection units are uniformly distributed along the circumference of the bomb body, any two detection units are arranged at an interval of 120 degrees, and the three detection units are arranged at the head of the bomb wing foldable bomb body.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111879180A (en) * | 2020-08-28 | 2020-11-03 | 中国工程物理研究院总体工程研究所 | Low-altitude low-speed small target low-cost interception system and method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111879180A (en) * | 2020-08-28 | 2020-11-03 | 中国工程物理研究院总体工程研究所 | Low-altitude low-speed small target low-cost interception system and method |
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