CN112824820A - Reverse-low small slow target air defense missile system for 40 mm rocket launcher and intercepting method - Google Patents
Reverse-low small slow target air defense missile system for 40 mm rocket launcher and intercepting method Download PDFInfo
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- 230000001960 triggered effect Effects 0.000 claims description 2
- 108010066278 cabin-4 Proteins 0.000 description 5
- 239000002737 fuel gas Substances 0.000 description 5
- 210000003128 head Anatomy 0.000 description 3
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- 238000010304 firing Methods 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
- F41H11/00—Defence installations; Defence devices
- F41H11/02—Anti-aircraft or anti-guided missile or anti-torpedo defence installations or systems
Abstract
The invention provides a reverse low small slow target air-defense missile system for a 40 mm rocket launcher and an interception method, wherein a seeker, a guidance system, a steering engine, a control cabin, a flight engine, a tail wing assembly and a solid rocket launching engine are sequentially connected to form a guided rocket launcher; the ground fire control instrument is fixedly connected to the 40 mm rocket launcher and is used for tracking a target, resolving and predicting a target track and providing target initial alignment information for a guided rocket projectile; the method comprises the following steps that a solid rocket launching engine is ignited to launch a guided rocket projectile, a flying engine provides power after the guided rocket projectile leaves a barrel, a control cabin uses initial alignment information as a reference to solve the real-time position of the guided rocket projectile, closed-loop control is formed between the real-time position and a predicted target position, and the guided rocket projectile enters a middle guidance mode; after the target is locked by the seeker, the guided rocket bomb enters a self-searching guidance mode, flies to the target and destroys the target by the guidance system. The seeker can capture and lock a remote infrared characteristic weak target.
Description
Technical Field
The invention relates to the technical field of small-caliber guided munitions, in particular to a reverse-low small-slow target air-defense missile system for a 40-millimeter rocket tube and an intercepting method.
Background
With the development of technologies such as information, materials, navigation and the like, the technology of small-sized fixed-wing and rotor unmanned aerial vehicles with functions of investigation, attack and evaluation has been rapidly developed. The aerial targets are small in size, weak in signal characteristics and typical in low-small-slow characteristics, are used in a large amount in modern land battlefields, become main threats to ground personnel and equipment, and have a very large challenge to single-soldier low-altitude short-range air defense weaponry equipment due to the interception problem of the aerial targets, and the aerial targets are hot spots of research in the technical field of air defense of all major military and strong countries in the world. The traditional medium-long distance air defense missile usually adopts a scheme of medium guidance and terminal guidance, and can realize target capture and target locking before launching for a large target with obvious infrared characteristics, but in order to realize the function of locking before launching, not only complex ground equipment such as large radars, photoelectric tracking and the like is required for assistance, but also the difficulty of the scheme of a guidance section in the missile can be increased, and the attack target of an individual soldier is a low-altitude medium-small slow small fixed wing, a rotor unmanned plane and the like, the infrared characteristics of the individual soldier are weak, and meanwhile, the large auxiliary equipment is not suitable for the individual soldier, so that the guidance head of a shoulder anti-infrared or television guidance air defense missile used by the individual soldier is difficult to realize target locking before launching and is difficult to realize reliable interception. Therefore, reliable interception of low, small and slow targets must be proposed as a new guidance scheme, first solving the problem of reliable capture of targets by guidance heads.
A40 mm single rocket launcher is a conventional hard weapon attacking platform for infantry short-distance anti-personnel, tanks, armors and workers, is favored due to the characteristics of low cost, light weight, simple operation and convenient carrying, is still greatly equipped and used by various countries at present, and the total equipment amount reaches more than one million doors. However, the ammunitions of the current shaping equipment of the platform are all uncontrolled rocket projectiles, and under the condition that the dispersion accuracy CEP (circular probability error) is 0.45 m, the farthest range to a static target is only 300 m, and the range to a moving target is further reduced. This greatly limits the operational effectiveness and operational use of the individual weapon platform and fails to meet the operational requirements of modern warfare. By combining the requirements and the current equipment situation of the 40 mm rocket tube, if a new bullet with the capacity of intercepting the small, medium and low slow targets can be developed for the platform, the method has great practical significance undoubtedly.
The original launching mode of the 40 mm rocket launcher is gunpowder launching, although the bore pressure in the launcher can reach more than 80 MPa, the launching energy utilization rate is still very low, and a large amount of high-temperature and high-speed gas formed at the tail of the launcher puts very strict requirements on the missile upper guidance control part and the wiring of a missile body electrical system under the conventional structural layout condition; because the 40 mm launching tube adopts a recoilless gun mode, when the 40 mm rocket projectile is launched at a shoulder carrying height and a large angle, the launching tail flame can bounce to the ground and endanger the safety of a shooter, so the launching angle can not exceed 30 degrees when the rocket projectile is launched, and the use of a 40 mm rocket tube platform in the field of air defense is greatly limited. Due to the constraints of the above constraints, 40 mm rocket launchers, although largely equipped since the last 70 s, have never been equipped with a bullet species with precise interception capability against airborne moving objects.
Disclosure of Invention
In view of the above, the invention provides an anti-low small slow target air defense missile system and an interception method for a 40 mm rocket launcher, and a seeker can capture and lock a remote infrared characteristic weak target.
The technical scheme adopted by the invention is as follows:
a reverse low small slow target air-defense missile system for a 40 mm rocket launcher comprises a seeker, a missile launching system, a steering engine, a control cabin, a flight engine, a tail wing assembly, a solid rocket launching engine and a ground fire control instrument;
the seeker, the fighting guidance system, the steering engine, the control cabin, the flight engine, the empennage assembly and the solid rocket launching engine are sequentially connected to form a guided rocket projectile;
the ground fire control instrument is fixedly connected to the 40 mm rocket launcher and is used for tracking a target, resolving and predicting a target track and providing target initial alignment information for a guided rocket projectile; the guided rocket projectile is launched by igniting the solid rocket launching engine, the flight engine provides power after the guided rocket projectile leaves the barrel, and the tail wing assembly is used for stabilizing the flight state of the guided rocket projectile; the control cabin uses the initial alignment information as a reference to calculate the real-time position of the guided rocket projectile, and the real-time position and the predicted target position form closed-loop control, so that the guided rocket projectile enters a middle guidance mode; and after the target is locked by the seeker, the guided rocket bomb enters a self-searching guidance mode, flies to the target and destroys the target by the guidance system.
Furthermore, the ground fire control instrument comprises a fire control computer, a white light/red appearance aiming module, a ground inertial navigation module and a power supply, wherein the white light/infrared observation aiming module is used for aiming and tracking a target by a shooter; the fire control computer is used for resolving a predicted flight path of a target and managing a launching process of a guided rocket projectile; the ground inertial navigation module is used for measuring the rotation angular velocity of a bullet line in the process of tracking a target by a shooter, providing the rotation angular velocity to the fire control computer for resolving a target prediction flight path, and providing target initial alignment information for a guided rocket projectile; the power supply is used for supplying power for the ground fire control instrument and the guided rocket projectile before launching.
A reverse low small slow target interception method for a 40 mm rocket tube adopts the air defense missile system, and comprises the following steps:
step one, after a shooter enters a position, a guided rocket bomb is loaded into a rocket tube, an aerial target is observed visually, and an intercepted target is determined;
searching and tracking a target through a ground fire controller, predicting a target track and transmitting target initial alignment information to a guided rocket projectile;
thirdly, after the shooter is triggered, the solid rocket launching engine is ignited to push the guided rocket projectile away from the rocket tube;
fourthly, the control cabin controls the flight engine to ignite so as to accelerate the guided rocket projectile;
step five, the control cabin uses the initial alignment information as a reference to calculate the real-time position of the guided rocket projectile, forms closed-loop control with the predicted target position, starts middle guidance and guides the guided rocket projectile to fly to the target;
sixthly, the seeker performs searching judgment in the middle guidance process, and after the target is determined to enter the seeker view field, the seeker locks the target;
and step seven, the guided rocket projectile enters a self-seeking guided working mode, flies to and destroys the target.
Further, the method for predicting the target motion law in the second step comprises the following steps: and a ground inertial navigation module on the ground fire control instrument continuously outputs the bullet line rotation angular velocity in the yaw direction and the pitching direction in the process of sensing the target tracking of the shooter, and a fire control computer on the ground fire control instrument carries out resolving and predicting of a target track according to the bullet line rotation angular velocity output by the ground inertial navigation module.
Has the advantages that:
1. the invention adopts a guidance scheme of terminal guidance of guidance and self-seeking in target track prediction tracking, and solves the problem that a guide head captures and locks a remote infrared characteristic weak target; meanwhile, the solid rocket launching engine is adopted to replace an original launching system of a rocket launcher with the diameter of 40 mm, the missile can be quickly pushed out of the rocket launcher by the thrust generated when the solid rocket launching engine launches, fuel gas enters the rocket launcher through the spray pipe after being fully combusted in the engine combustion chamber, the pressure of the fuel gas is quickly reduced to below 1 MPa after the fuel gas is secondarily expanded in the tail cavity of the rocket launcher, the temperature and the noise are both obviously reduced, most of the fuel gas generated in the launching process of the engine is discharged through the spray pipe, the generated recoil is small, and meanwhile, harmful components of the fuel gas discharged from the tail of the rocket launcher and sprayed flames are greatly reduced, so that the secondary damage to a shooter is reduced, and the problem of launching with a large elevation angle is solved.
Therefore, the air-defense missile system can be completely suitable for the launching condition and the operational use requirement of a 40-millimeter rocket tube, and can reliably intercept small and slow targets in the air such as small-sized fixed wing unmanned planes and multi-rotor unmanned planes at the range exceeding 1500 meters.
2. The ground fire control instrument adopts a human-in-loop target tracking mode, senses the process of tracking the target by a shooter through the ground inertial navigation module, thereby forming a predicted flight path of the target, and has small volume and light weight, thereby being completely suitable for being used by a single-soldier system.
Drawings
FIG. 1 is a schematic view of the overall structure of a guided rocket projectile according to the present invention;
FIG. 2 is a schematic structural diagram of a ground fire control instrument;
FIG. 3 is a schematic diagram of a terminal guidance trajectory of guidance plus self-seeking in track prediction tracking;
FIG. 4 is a schematic view of the flight trajectory of the air defense missile system;
the system comprises an infrared/television seeker 1, a missile system 2, a steering engine 3, a control cabin 4, a flight engine 5, a tail wing assembly 6, a solid rocket launching engine 7, a ground inertial navigation module 8, a white light/red appearance aiming module 9, an eyepiece 10, a fire control computer 11, a power supply 12, an inertial navigation system on a missile 14 and a computer on the missile.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The embodiment provides a reverse low small slow target air defense missile system for a millimeter rocket launcher, which comprises a guided rocket projectile and a ground fire control instrument.
As shown in figure 1, an infrared/television seeker 1, a war-guiding system 2, a steering engine 3, a control cabin 4, a flight engine 5, a tail wing assembly 6 and a solid rocket launching engine 7 are sequentially connected to form a guided rocket projectile. The rocket projectile body positioned outside the rocket launcher is an ultra-caliber cabin section, the infrared/television seeker 1, the missile system 2, the steering engine 3 and the control cabin 4 are all positioned in the ultra-caliber cabin section, and the flight engine 5, the empennage assembly 6 and the solid rocket launching engine 7 are all positioned in the rocket launcher.
Infrared/tv seeker 1: the system is used for locking and tracking a target at a final guide section, and outputting the line rotation angular speed of the target to the missile-borne computer 14 to generate a proportional guide command.
The war induction system 2: the detonator is composed of a detonator, a security mechanism, a detonating tube and a prefabricated fragment warhead.
Steering engine 3: and executing the instructions output by the missile-borne computer 14 to generate control force and moment to control the missile to fly.
The control cabin 4: including a pop-up computer 14, a pop-up power supply, and a pop-up inertial navigation system 13. The missile computer 14 is used for receiving the missile inertial navigation 13 and the seeker information, resolving to generate a control instruction and sending the control instruction to the steering engine 3; the missile power supply adopts a thermal battery, is powered and activated by a power supply 12 of the ground fire control instrument before launching and is used for supplying power to an electrical system on the guided missile; the on-board inertial navigation system 13 is used for providing position and attitude information of the guided rocket projectile in the flight process.
The flight engine 5: the two-stage speed increasing device is used for two-stage speed increasing of the launching of the pilot rocket projectile.
The tail assembly 6: consists of a tail rod and a tail wing and is used for stabilizing the flying state of the rocket projectile.
Solid rocket launching engine 7: the gun-type projectile launcher is used for replacing the original projectile launcher of 40 mm rocket projectiles and providing initial power and speed for the projectile to leave the barrel, and the launcher engine can adopt a conventional post-ignition and wire-outgoing mode and can also adopt a flexible front-ignition and wire-outgoing mode according to the actual projectile body structural design. Meanwhile, the optimized design of mutual combination of engine charging and inner trajectory reduces the pressure peak value, further reduces noise and overpressure, and can meet the requirement of micro-aftereffect large thrust of the engine by using a large jet throat.
Ground fire control appearance: the ground fire control instrument is fixedly connected to the 40 mm rocket launcher and comprises a fire control computer 11, a white light/red appearance aiming module 9 (including an eyepiece 10), a ground inertial navigation module 8 and a power supply 12 as shown in fig. 2, wherein the infrared/white light appearance aiming module is fixedly connected with the ground inertial navigation module 8. The white light/red appearance aiming module 9 is used for aiming and tracking a target by a shooter, the fire control computer 11 is used for resolving a predicted track of the target and managing an emission process, and the emission process comprises the steps of aiming and tracking the target, predicting the target track, uploading information and emitting a guided rocket projectile. The ground inertial navigation module 8 is used for measuring the rotation angular velocity of the line of the missile eyes in the pitching and yawing directions in the target tracking process of the shooter and providing the rotation angular velocity of the line of the missile eyes to the fire control computer 11 for resolving and predicting the target track, and meanwhile, the ground inertial navigation module 8 is far higher in precision than the missile-borne inertial navigation module 13 and can provide more accurate initial attitude angles (yawing, pitching and rolling) as initial references to be uploaded to the missile-borne inertial navigation module 13. The power supply 12 is used for supplying power to the ground fire control instrument, supplying power for guiding the rocket projectile to upload data before launching and supplying thermal battery firing voltage to the projectile power supply. The ground fire control instrument adopts a target tracking mode of a person in a loop, and senses the process of tracking a target by a shooter through a ground inertial navigation module 8, so that the track of the target is resolved and predicted.
The method for intercepting the terminal guidance of guidance and self-seeking in track prediction and tracking comprises the following steps that an infrared seeker 1 is adopted:
step one, after a shooter enters a position, a guided rocket bomb is loaded into a rocket tube, an aerial target is observed visually, and an intercepted target is determined;
secondly, placing the rocket tube on the shoulder, and searching and stably tracking the target through a white light/infrared sighting module 9 on the ground fire control instrument, as shown in fig. 3;
in the process of tracking the target, continuously outputting the rotation angular velocity of the line of the bullet eyes in the yaw direction and the pitching direction by a ground inertial navigation module 8 on a ground fire control instrument in the process of sensing the target tracked by a shooter, and predicting the target track by a fire control computer 11 according to the rotation angular velocity of the line of the bullet eyes output by the ground inertial navigation module 8;
fourthly, the ground fire control instrument uploads the predicted target track and the initial alignment information to an on-missile computer 14 of the guided rocket missile control cabin 4;
fifthly, after the shooter fires, the solid rocket launching engine 7 is ignited to push the projectile away from the rocket barrel;
after the solid rocket launching engine 7 works for a certain time, the flying engine 5 is controlled to ignite by the missile computer 14, and the speed of the guided rocket missile continues to be increased;
step seven, after the guided rocket projectile leaves the barrel, the onboard inertial navigation system 13 uses the initial alignment information as a reference to solve the real-time position of the guided rocket projectile, forms closed-loop control with the predicted target position, starts intermediate guidance and guides the guided rocket projectile to fly to the target;
step eight, the infrared seeker starts to work in the middle guidance process, searching and judging are continuously carried out according to the infrared characteristics of the target, and the infrared seeker locks the target after the target enters the field of view of the infrared seeker;
and step nine, as shown in fig. 4, the guided rocket projectile enters a self-seeking terminal guidance working mode, the infrared seeker measures the linear rotation angular velocity of the projectile in real time and sends the linear rotation angular velocity to the projectile computer 14 to participate in forming a control instruction, the guided rocket projectile is controlled to fly, and the target is destroyed through the guidance system.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. A reverse low small slow target air-defense missile system for a 40 mm rocket launcher is characterized by comprising a seeker, a missile launching system, a steering engine, a control cabin, a flight engine, a tail wing assembly, a solid rocket launching engine and a ground fire control instrument;
the seeker, the fighting guidance system, the steering engine, the control cabin, the flight engine, the empennage assembly and the solid rocket launching engine are sequentially connected to form a guided rocket projectile;
the ground fire control instrument is fixedly connected to the 40 mm rocket launcher and is used for tracking a target, resolving and predicting a target track and providing target initial alignment information for a guided rocket projectile; the guided rocket projectile is launched by igniting the solid rocket launching engine, the flight engine provides power after the guided rocket projectile leaves the barrel, and the tail wing assembly is used for stabilizing the flight state of the guided rocket projectile; the control cabin uses the initial alignment information as a reference to calculate the real-time position of the guided rocket projectile, and the real-time position and the predicted target position form closed-loop control, so that the guided rocket projectile enters a middle guidance mode; and after the target is locked by the seeker, the guided rocket bomb enters a self-searching guidance mode, flies to the target and destroys the target by the guidance system.
2. The anti-low small slow target air defense missile system for a 40 mm rocket launcher of claim 1, wherein the ground fire control instrument comprises a fire control computer, a white light/red appearance aiming module, a ground inertial navigation module and a power supply, the white light/infrared aiming module is used for aiming and tracking a target by a shooter; the fire control computer is used for resolving a predicted flight path of a target and managing a launching process of a guided rocket projectile; the ground inertial navigation module is used for measuring the rotation angular velocity of a bullet line in the process of tracking a target by a shooter, providing the rotation angular velocity to the fire control computer for resolving a target prediction flight path, and providing target initial alignment information for a guided rocket projectile; the power supply is used for supplying power for the ground fire control instrument and the guided rocket projectile before launching.
3. A reverse-low small-slow target interception method for a 40 mm rocket tube, which is characterized in that the air-defense missile system of claim 1 is adopted, and the interception method comprises the following steps:
step one, after a shooter enters a position, a guided rocket bomb is loaded into a rocket tube, an aerial target is observed visually, and an intercepted target is determined;
searching and tracking a target through a ground fire controller, predicting a target track and transmitting target initial alignment information to a guided rocket projectile;
thirdly, after the shooter is triggered, the solid rocket launching engine is ignited to push the guided rocket projectile away from the rocket tube;
fourthly, the control cabin controls the flight engine to ignite so as to accelerate the guided rocket projectile;
step five, the control cabin uses the initial alignment information as a reference to calculate the real-time position of the guided rocket projectile, forms closed-loop control with the predicted target position, starts middle guidance and guides the guided rocket projectile to fly to the target;
sixthly, the seeker performs searching judgment in the middle guidance process, and after the target is determined to enter the seeker view field, the seeker locks the target;
and step seven, the guided rocket projectile enters a self-seeking guided working mode, flies to and destroys the target.
4. The method for intercepting small and slow targets for a 40 mm rocket tube according to claim 3, wherein the method for predicting the motion law of the targets in the second step is as follows: and a ground inertial navigation module on the ground fire control instrument continuously outputs the bullet line rotation angular velocity in the yaw direction and the pitching direction in the process of sensing the target tracking of the shooter, and a fire control computer on the ground fire control instrument carries out resolving and predicting of a target track according to the bullet line rotation angular velocity output by the ground inertial navigation module.
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| CN201911150963.9A CN112824820A (en) | 2019-11-21 | 2019-11-21 | Reverse-low small slow target air defense missile system for 40 mm rocket launcher and intercepting method |
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Cited By (2)
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| CN113790637A (en) * | 2021-06-30 | 2021-12-14 | 四川航天烽火伺服控制技术有限公司 | Miniature infrared inertial unit composite guidance control system and control method thereof |
| CN114963891A (en) * | 2022-06-15 | 2022-08-30 | 重庆航天工业有限公司 | Integrated control cabin |
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| CN114963891A (en) * | 2022-06-15 | 2022-08-30 | 重庆航天工业有限公司 | Integrated control cabin |
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