CN118999275A - Air-defense missile overall layout system and target interception method - Google Patents
Air-defense missile overall layout system and target interception method Download PDFInfo
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- CN118999275A CN118999275A CN202411022993.2A CN202411022993A CN118999275A CN 118999275 A CN118999275 A CN 118999275A CN 202411022993 A CN202411022993 A CN 202411022993A CN 118999275 A CN118999275 A CN 118999275A
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- 230000010365 information processing Effects 0.000 claims description 8
- 230000005540 biological transmission Effects 0.000 claims description 5
- 238000004364 calculation method Methods 0.000 claims description 5
- 238000012545 processing Methods 0.000 claims description 5
- 230000008569 process Effects 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 230000006641 stabilisation Effects 0.000 claims description 3
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Combustion & Propulsion (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides an air defense missile overall layout system, which comprises: a missile main stage component and a missile booster stage component; the missile main stage component includes: a head cap, a warhead cabin and a rudder cabin; the missile booster stage component comprises: an interstage cabin and a boost engine; a guide head or target characteristic enhancement equipment is arranged in the head cover to form 2 types of missile main-level component types, namely a guide head type and a no-guide head type; the boosting engine is of 3 types of long-distance, medium-distance and short-distance; wherein, according to the configuration combination of missile main level part and missile boost level part, can form 6 types of missiles. According to the missile provided by the invention, for different interception distances, the boosting stage is provided with 3 boosting engines, when an object is intercepted, ground equipment can reasonably select the type of the missile for intercepting according to the situation of the air, so that the interception cost is reduced.
Description
Technical Field
The invention relates to the field of missile weapons, in particular to an air defense missile overall layout system and a target interception method.
Background
The problem of high technical weapon cost is always plagued by the military of each country, and also brings heavy burden to the finance of each country. Recent local warfare indicates that missile attack and defense fight will become the main fight pattern of future high-tech warfare, so the cost reduction of missile weapons has a special significance. The guide head of the air-defense missile is advanced in technology, complex in structure and large in proportion of missile cost, so that the cost reduction of the guidance subsystem is an important way for realizing the low cost of the air-defense missile.
Patent publication No. US20100084505A1 discloses a multi-stage ultra-high speed kinetic energy missile (HVKEM) employing a "in one missile configuration, wherein the HVKEM comprises 1 first stage flying missiles and 2 stages killing missiles comprising KE stick penetrators. The flying missile cruises at a relatively low speed (less than mach 1.5, typically less than mach 1) to save propellant (weight) and allow for efficient guidance and maneuvering until the missile approaches the target. When the missile is within the deadly range of the KE rod penetrator, the killing missile will separate and lift to a higher velocity (greater than mach 3, typically greater than mach 5) and fly unguided, striking the target in less than one second. Waiting to lift the KE stick until "last second" reduces the total propellant (weight) required to deliver the KE stick to the target and simplifies instruction.
The invention is different from the existing conventional missile, the missile main-stage rudder cabin is provided with the target characteristic enhancement equipment, and the guide head-free missile main stage is also provided with the target characteristic enhancement equipment on the head cover, so that the ground equipment can be helped to quickly search and track the missile main stage after the missile boosting stage is separated. The ground equipment completes the calculation of the missile relative relation data on the premise of considering communication delay, and sends the calculated missile relative relation to the missile main stage. And forming a guidance instruction by the missile main stage according to the received missile-target relative relation, and flying to the target. The guided missile main stage without a seeker carries out guidance in a command guidance mode in the whole course; the missile main stage with the seeker uses an instruction guidance mode to conduct guidance before the seeker intercepts a target, and uses target information intercepted by the seeker to conduct end guidance of the seeker after the seeker intercepts the target. After the target enters the working distance of the missile main level fuze, the missile main level detonates the fighter part to hit down the target; unlike conventional missile, the main stage of missile is not equipped with engine, and the space for installing engine can be used for installing warhead, so that the killing radius can be effectively increased, and the defect of insufficient instruction guidance precision is overcome.
Disclosure of Invention
In view of the drawbacks of the prior art, an object of the present invention is to provide an air defense missile overall layout system, comprising: a missile main stage component and a missile booster stage component;
the missile main stage component includes: a head cap, a warhead cabin and a rudder cabin; the missile booster stage component includes: an interstage cabin and a boost engine;
A guide head or target characteristic enhancement equipment is arranged in the head cover to form 2 types of missile main-level parts, namely a guide head type and a no-guide head type;
the boosting engine is of 3 types of long-distance, medium-distance and short-distance;
Wherein, according to the configuration combination of missile main level part and missile boost level part, can form 6 types of missiles.
Preferably, a missile-borne data chain, inertial measurement equipment and an information data processing module are also arranged in the head cover;
When the main-stage component is provided with the seeker, the information processing control module is connected with the seeker, the missile-borne data chain and the inertial measurement device; when the main-level component has no guide head, the information processing control module is connected with the missile-borne data chain and the inertial measurement device;
A fuze and a warhead are arranged in the warhead cabin; according to actual needs, whether the strake wings are installed in the warhead cabin or not is selected;
and a steering engine and target characteristic enhancement equipment are arranged in the steering engine cabin.
Preferably, the missile-borne data link is responsible for transmitting and receiving data, and transmitting data of the missile-borne main component to ground equipment, wherein the data comprise attitude, position, speed and satellite time data; and receiving the relative relationship data of the bullets sent by the ground equipment, wherein the relative relationship data comprises relative positions of the bullets and relative speed data of the bullets.
Preferably, an interstage separation device, a cutting lock assembly and a separation spring are arranged in the interstage cabin;
The interstage cabin is used for igniting the interstage separation device after receiving the interstage separation signal sent by the information processing control module, the cutting lock assembly generates high-temperature high-pressure air flow, the interstage cabin body is cut off, and the boosting stage component is separated from the main stage component under the action of aerodynamic resistance and the separation spring.
Preferably, the boosting engine is arranged at the rear part of the boosting stage part, and a single-stage solid engine is adopted.
Aiming at the defects in the prior art, the invention aims to provide a target interception method applying an air defense missile overall layout system, which comprises the following steps:
step S1: the ground equipment performs preparation work, selects an interception scheme and sends out a missile launching signal according to the received target parameters;
Step S2: in the missile flight process, the boosting stage component is separated from the main stage component, and when the data of the missile main stage component received and tracked by the ground equipment are consistent, a ground connection instruction is sent to the missile main stage component;
step S3: the ground equipment calculates according to the data transmitted by the missile main-level component, and transmits the calculated missile-mesh relative relationship to the missile main-level component;
step S4: after receiving the relative relation between the ground connection instruction and the missile target, the missile main-stage component flies towards the target according to the guidance instruction until the target enters a preset distance, and the missile main-stage component detonates the warhead to finish the shooting-down task.
Preferably, step S1 includes:
Step S1.1: when intercepting a target, the ground equipment selects the type of guided missiles for intercepting in the launch box according to target parameters; the target parameters comprise target distance, target speed and target type;
Step S1.3: according to the selected missile type, determining a missile main-stage component guidance mode:
The guidance mode without the seeker is as follows: initial guidance and instruction guidance; the guidance mode of the guidance head is as follows: initial guidance, instruction guidance, and tip guidance;
Step S1.3: after the model selection is completed, the ground equipment sends out missile launching signals.
Preferably, step S2 includes:
Step S2.1: after the missile is launched, missile initiation guidance is carried out on a working section of the boosting engine, and missile stabilization loop control is completed by a rudder cabin, so that the missile can stably fly;
step S2.2: after the boosting engine works, the boosting stage component is separated from the main stage component, and ground equipment tracks the missile main stage component in real time through target characteristic enhancement equipment of the missile main stage;
Step S2.3: the missile-borne data link transmits data of the missile-borne main level component to ground equipment, the ground equipment compares the received data of the missile-borne main level component with the data of the missile-borne main level component tracked by the ground equipment, and when the ground equipment judges that the data are consistent, the ground equipment transmits a ground connection command to the missile-borne main level component.
Preferably, step S3 includes:
Step S3.1: the ground equipment calculates the delay delta t of the data sent to the missile main level component by the ground equipment according to the satellite time contained in the real-time transmission data between the missile main level component and the ground equipment;
step S3.2: the ground equipment calculates the target position and the target speed after deltat by combining the current flight parameters of the target;
Step S3.3: the ground equipment calculates the missile position and the missile speed after delta t by running a trajectory simulation program and combining the current flight parameters of the missile;
Step S3.4: the ground equipment integrates the target position, the target speed, the missile position and the missile speed after the deltat is calculated into a missile-target relative relation and sends the missile-target relative relation to a missile main-stage component;
The relative relationship includes the relative position of the bullet mesh and the relative speed of the bullet mesh.
Preferably, step S4 includes:
Step S4.1: after receiving the ground connection command, the missile main-level component receives missile-target relative relation data sent by ground equipment; the missile main-stage component flies towards the target according to the guidance instruction by utilizing the received missile-target relative relation; the guided missile main-stage component without the guide head carries out guidance in a whole course by utilizing an instruction guidance mode; the missile main-stage component with the seeker uses an instruction guidance mode for guidance before the seeker intercepts a target;
Step S4.2: after the guided missile main-level component with the guide head intercepts a target, the guide head terminal guidance is carried out by utilizing target information intercepted by the guide head;
step S4.3: after the target enters the working distance of the fuze of the missile main-stage component, the missile main-stage component detonates the fighter and knocks down the target.
Compared with the prior art, the invention has the following beneficial effects:
1. The missile provided by the invention consists of a main stage and a boosting stage, wherein for different interception distances, the boosting stage is provided with 3 boosting engines, when an object is intercepted, ground equipment can reasonably select the type of the missile for intercepting according to an empty situation, so that optimal task selection is realized, and on one hand, accurate striking is realized; on the other hand, the interception cost is reduced;
2. According to the air defense missile overall layout system, the missile main stage is provided with the target characteristic enhancement equipment, so that ground equipment can be helped to quickly search and track the missile main stage after the missile boosting stage is separated;
3. The method for intercepting the air defense missile target eliminates the system errors caused by different measuring equipment, only has the measurement variance of a single radar, and improves the measurement accuracy;
4. According to the air defense missile target interception method provided by the invention, ground equipment completes calculation of missile relative relation data under the premise of considering communication delay, and sends the calculated missile relative relation to a missile main stage, so that measurement errors caused by data transmission are eliminated;
5. According to the air defense missile overall layout system provided by the invention, the main missile stage is not provided with the engine, the space for installing the engine is used for installing the warhead, the killing radius can be effectively increased, and the defect of insufficient instruction guidance precision is overcome.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of the overall layout of an air-defense missile of the present invention;
FIG. 2 is a schematic illustration of an air defense missile guidance mode of the present invention;
FIG. 3 is a schematic view of an air defense missile ground launching device according to the present invention;
FIG. 4 is a schematic diagram of the type of missile according to the present invention to selectively intercept based on target parameters.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
Specifically, in one embodiment, an air defense missile overall layout system and a target interception method include: the main stage part comprises a head cover, a fighter part cabin and a rudder cabin; a boost stage, the boost stage component comprising: inter-stage cabin, boost engine.
Further, a missile-borne data chain, inertial measurement equipment, an information data processing module and a guide head or target characteristic enhancement equipment (a guide head type is provided, namely, the guide head is arranged in the head cover, and a guide head-free type is provided, namely, the target characteristic enhancement equipment is arranged in the head cover) are arranged in the main-stage head cover; a fuze and a warhead are arranged in the main warhead cabin; the main-stage warhead cabin is provided with a strake wing (the main-stage warhead cabin of a close-range interception type is provided with a strake wing, and the main-stage warhead cabin of a medium-range and far-range interception type is not provided with a strake wing); and a steering engine and target characteristic enhancement equipment are arranged in the main-stage steering engine cabin.
Further, an interstage separation device, a cutting lock assembly and a separation spring are arranged in the boosting stage interstage cabin; the boosting engine of the boosting stage is arranged at the rear part of the boosting stage, adopts a single-stage solid engine, and is provided with a tail wing.
As shown in fig. 1, there are 2 states according to whether there is a leader division at the missile main stage; according to the thrust division of the boosting engine, the three-way engine has 3 states of long distance, medium distance and short distance. After combination, there are 6 states: near-distance with a seeker, middle-distance with a seeker, far-distance with a seeker, near-distance without a seeker, middle-distance without a seeker, and far-distance without a seeker.
As shown in figure 2, the missile main level guidance without the guide head is primary guidance and instruction guidance; the missile main stage has guidance modes of primary guidance, instruction guidance and guidance at the tail end of the guidance head.
The initial guidance working stage is that the ignition of the boosting engine is separated to the boosting section for stabilizing the posture.
After boosting separation, the device enters an instruction guidance working stage. After the missile main stage without a seeker completes boosting separation, guiding is carried out in a whole course by utilizing an instruction guiding mode; after the missile main stage with the seeker completes boosting separation, the seeker uses an instruction guidance mode to conduct guidance before intercepting a target.
After the guide head captures a target, the guided missile main stage with the guide head conducts guide head terminal guidance by utilizing target information captured by the guide head.
The hood-mounted devices are therefore divided into two cases:
1. The device comprises a missile-borne data chain, inertial measurement equipment, an information data processing module and a seeker;
2. The device comprises a missile-borne data chain, inertial measurement equipment, an information data processing module and target characteristic enhancement equipment;
when the main-stage component is provided with a seeker, the information processing control module is connected with the seeker, the missile-borne data chain and the inertial measurement device;
When the main-stage component does not have a seeker, the information processing control module is connected with the missile-borne data chain and the inertial measurement device.
As shown in fig. 3, a communication antenna is arranged beside the ground launching device of the low-cost air defense missile and is used for communication transmission with a ground equipment command system. The launch device utilizes a vertical arm and turntable to effect launch box pitch and azimuth maneuvers. All 6 low-cost air defense missiles in states can be installed in the launch box.
As shown in fig. 4, the ground equipment judges the importance level of the target and the difficulty level of interception according to the target parameters (target distance, target speed, target type, etc.), and selects the missile type for implementing interception from among the 6-state missiles according to the target judgment result; missile type Mi missile type M i; m1, a seeker is arranged in the short range; m2, a middle-range guiding head is arranged; m3, a remote guiding head is arranged; m4, short-range no-seeker; m5, middle-range no-leader; m6, remote no-leader; target parameter T j; t1, target distance; t2, target speed … … Tn, target type;
the boosting stage has 3 boosting engines of far distance, middle distance and near distance for different interception distances. Whether the missile main stage has a seeker or not is classified into a seeker type and a seeker-free type 2 types. The main stage and the boosting stage are combined to obtain 6 missile types. The guided missile with the guide head can be decoupled with ground equipment, has high interception precision and strong multi-target interception capability, but has higher cost; the guided missile without the seeker can not be decoupled from ground equipment, has low interception precision and weak multi-target interception capability, but has lower cost; after combination, when the target is intercepted, the ground equipment can reasonably select the type of the guided missile for intercepting according to the situation of the sky, so that the intercepting cost is reduced. Air-defense missile overall layout system and target interception method
The invention also provides a target interception method of the air-defense missile, which can be realized by executing a module of the air-defense missile overall layout system, namely, a person skilled in the art can understand the air-defense missile overall layout system as a preferred implementation mode of the target interception method of the air-defense missile.
The invention also provides a target interception method of the air defense missile, which comprises the following steps:
Step one: when intercepting a target, the ground equipment judges the importance level of the target and the intercepting difficulty level according to target parameters (target distance, target speed, target type and the like), and selects the missile type for intercepting from the missiles in 6 states according to the judging result.
Step two: after the missile is launched, missile initial guidance is carried out on a working section of the boosting engine, and the main-level rudder cabin is used for completing missile stabilization loop control so as to realize stable missile attitude and flight;
Step three: after the boost stage engine is finished, the boost stage is separated from the main stage. The missile main stage is provided with target characteristic enhancement equipment, so that ground equipment can be quickly searched and tracked to the missile main stage after the missile boosting stage is separated.
Step four: the missile-borne data link transmits various data (attitude, position, speed, satellite time and the like) of the missile main level to ground equipment, the ground equipment compares the received missile main level data with the searched and tracked missile main level data of the ground equipment, and if the ground equipment judging data are consistent, the ground equipment transmits a ground instruction connection command to the missile;
Step five: the ground equipment completes the calculation of the missile relative relation data on the premise of considering communication delay, and sends the calculated missile relative relation to the missile main stage. The specific calculation process is as follows: the ground equipment calculates the delay delta t of the ground equipment sent to the missile main level data according to the satellite time contained in the real-time transmission data between the missile main level and the ground equipment; the ground equipment combines the current flight parameters of the target, and extrapolates the target position and the target speed after deltat; the ground equipment is combined with the current flight parameters of the missile, a trajectory simulation program is operated, and the position and the speed of the missile after delta t are calculated; the ground equipment sends the relative relationship of the missile meshes (relative missile mesh positions, relative missile mesh speeds and the like) after deltat to a missile main stage;
Step six: after receiving a ground instruction connection command, the missile main stage receives missile-target relative relation data sent by ground equipment; the missile main stage forms a guidance instruction by utilizing the received missile-target relative relation and flies towards a target; the guided missile main stage without a seeker carries out guidance in a command guidance mode in the whole course; the missile main stage with the seeker uses an instruction guidance mode to conduct guidance before the seeker intercepts a target;
Step seven: after the guided missile main stage with the guide head captures a target, the guide head terminal guidance is carried out by utilizing target information captured by the guide head;
step eight: after the target enters the working distance of the missile main fuze, the missile main fuze detonates the warhead to hit down the target.
In summary, the invention provides an air defense missile overall layout system and an interception method thereof, and when intercepting a target, ground equipment reasonably selects the type of a missile for intercepting according to an air situation, thereby realizing the reduction of the interception cost.
The foregoing describes specific embodiments of the present application. It is to be understood that the application is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the application. The embodiments of the application and the features of the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
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| CN202411022993.2A CN118999275A (en) | 2024-07-29 | 2024-07-29 | Air-defense missile overall layout system and target interception method |
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