CN210952527U

CN210952527U - Wireless instruction guidance rocket projectile and controlled infrared beacon for 40mm rocket launcher

Info

Publication number: CN210952527U
Application number: CN201920759238.0U
Authority: CN
Inventors: 于剑桥; 蒋军
Original assignee: Beijing Hengxing Jianxiang Technology Co ltd
Current assignee: Beijing Hengxing Jianxiang Technology Co ltd
Priority date: 2019-05-24
Filing date: 2019-05-24
Publication date: 2020-07-07
Anticipated expiration: 2029-05-24

Abstract

The utility model provides a 40mm is wireless instruction guidance rocket projectile and has accuse infrared beacon for rocket launcher, rocket projectile increase actuating mechanism, wireless instruction receiving arrangement, play control module and beacon module, actuating mechanism installs in rocket projectile head radome fairing, the beacon module is installed at rocket projectile afterbody, adopts and does not have accuse counter weight beacon or has accuse infrared beacon, sets up general mechanical interface on the beacon module, can switch between two kinds of beacons; the adopted controlled infrared beacon not only successfully avoids the problem of wiring in a high bore pressure area in the rocket tube, but also solves the problem of high bore pressure resistance of the beacon, and effectively reduces the comprehensive cost of the system through the modularized interchangeable design. The utility model discloses not only can guarantee the precision of hitting of near range battle, can promote the firepower scope of striking of 40mm rocket launcher to static and moving target by a wide margin moreover.

Description

Wireless instruction guidance rocket projectile and controlled infrared beacon for 40mm rocket launcher

Technical Field

The utility model relates to a guidance rocket projectile technical field, concretely relates to 40mm rocket launcher is with wireless instruction guidance rocket projectile and have accuse infrared beacon.

Background

A40 mm individual rocket launcher is a conventional hard-attacking weapon 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, all the existing ammunitions of the platform are uncontrolled rocket projectiles, and under the condition that the dispersion accuracy CEP (circular probability error) is 0.45m, the farthest range of the platform to a static target is only 300m, and the range of the platform to a moving target is further reduced. This greatly limits the operational effectiveness of the individual weapon platform and fails to meet the operational requirements of modern warfare. Therefore, it is necessary to develop a guided rocket projectile with an effective shooting distance of more than 1500 meters and with the capability of accurately striking static and moving targets.

However, due to the special launching environment, the combat use condition and the low cost requirement of the 40mm rocket tube, the difficulty of developing an accurate guided rocket projectile for the rocket tube is very large. When the rocket projectile is launched, the bore pressure in the rocket tube can reach more than 80 MPa, which puts severe requirements on the development of the guidance control part on the projectile and the wiring of an electrical system on the projectile. Meanwhile, the 40mm rocket tube is a single-soldier weapon, and the short-distance combat using conditions are very many, so that the guided rocket projectile has to reach the same hitting precision as the uncontrolled rocket projectile at the range within 300 meters. Generally, a guidance control system of a guidance cartridge has a start-control convergence section when the guidance control system starts to work, and the trajectory precision of the section is low, so that the requirement of near range on precision is difficult to meet. Further, the requirement for cost reduction also limits the adoption of complex guidance control components. It is due to the above limitations that although 40mm rocket launchers began to be heavily equipped since the last 70 th century, no guided rocket projectile solution has been proposed for their use.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model provides a 40mm is wireless instruction guidance rocket projectile and has accuse infrared beacon for rocket launcher not only can guarantee the precision of hitting of close range battle, can promote the firepower scope of hitting of 40mm rocket launcher to static and moving target by a wide margin moreover.

The utility model adopts the following technical scheme:

the rocket launcher is characterized in that a rocket launcher with the diameter of 40mm is guided by wireless instructions, an execution mechanism, a wireless instruction receiving device, an on-rocket control module and a beacon module are additionally arranged on the rocket launcher, and a peripheral device is a ground launching control device;

the executing mechanism is arranged in a fairing at the head of the rocket projectile, the beacon module is arranged at the tail of the rocket projectile, an uncontrolled counterweight beacon or a controlled infrared beacon is adopted, and a universal mechanical interface is arranged on the beacon module and can be switched between the two beacons;

when the uncontrolled counterweight beacon works, the ground launching control device is wirelessly connected with the rocket projectile, a guidance control system on the rocket projectile does not work, and the rocket projectile flies in an uncontrolled manner;

when the controlled infrared beacon works, the controlled infrared beacon and the ground are wirelessly connected to transmit an infrared signal, the ground is wirelessly connected with the wireless instruction receiving device on the rocket projectile, the ground is wirelessly connected with the relative position information of the rocket projectile, which is acquired, relative to an aiming line, of the rocket projectile is transmitted to the wireless instruction receiving device, the wireless instruction receiving device is electrically connected with the projectile upper control module, the projectile upper control module is electrically connected with the execution mechanism, and the projectile upper control module transmits a control instruction to the execution mechanism.

Further, the executing mechanism adopts a cold air jet flow control device or a gas jet flow control device.

Furthermore, the executing mechanism adopts a single-channel or double-channel steering engine.

Furthermore, the cold air jet flow control device comprises a body, an air bottle, an electric actuator for opening the air bottle, two electromagnetic valves and two nozzles;

the two electromagnetic valves are symmetrically arranged on the outer circumference of the body, the two nozzles are symmetrically arranged on the outer circumference of the body, and cavities of the two electromagnetic valves are respectively communicated with the two nozzles;

the gas cylinder is fixed at one end of the body, and the gas cylinder opening electric actuator is fixed at the other end of the body and closes the opening of the gas cylinder; the body is provided with a pipeline communicated with the electromagnetic valve cavity, and when the gas cylinder electric actuator works, the gas cylinder is communicated with the electromagnetic valve cavity through the pipeline; and the electromagnetic valve is opened, and the cavity of the electromagnetic valve is communicated with the nozzle.

Furthermore, the uncontrolled counterweight beacon is composed of a counterweight metal structural part and is used for ensuring the pneumatic appearance and quality characteristics of the rocket projectile in an uncontrolled mode.

Furthermore, the controlled infrared beacon is a gunpowder energy infrared beacon and comprises a beacon shell, gunpowder, a tantalum sheet and a separable protection mechanism;

the gunpowder is arranged in the beacon shell, and the beacon shell is provided with a fire transfer hole which is used as a channel for igniting the gunpowder in the beacon shell by external high-pressure gas; the device comprises a beacon shell, a fire hole, a tantalum sheet, a gunpowder burning hole, a fire transmission hole, a fire control hole and a fire control hole, wherein the beacon shell is arranged on the beacon shell, high-pressure gas outside the beacon shell ignites the gunpowder through the fire transmission hole, and the gunpowder burns to burn and burn the tantalum sheet, so that the tantalum sheet; the separable protection mechanism is used for protecting the internal structure of the beacon shell during launching, is arranged at the tail part of the beacon shell, and realizes separation after launching.

Furthermore, the controllable infrared beacon is an electric energy infrared beacon and comprises a beacon shell, a light-emitting diode, a processing circuit, a power supply and a separable protection mechanism;

the light-emitting diode, the processing circuit and the power supply are arranged in the beacon shell, and the light-emitting diode is connected with the power supply through the processing circuit; the separable protection mechanism is arranged at the tail part of the beacon shell and used for protecting the internal structure of the beacon shell during launching and realizing separation after launching.

Further, the separable protection mechanism comprises a protection mechanism shell, a piston and a shear screw;

a piston groove is formed in the protection mechanism shell, and a piston is arranged in the piston groove and forms a sealed cavity with the protection mechanism shell; the protection mechanism shell is connected with the beacon shell through a shearing screw, the protection mechanism shell is provided with an air guide hole, high-temperature gas generated by rocket projectile propellant powder enters the sealing cavity through the air guide hole during launching, after the rocket is ejected out of the barrel, pressure difference is formed between high pressure in the sealing cavity and the projectile, the shearing screw is sheared, and the separable protection mechanism realizes separation.

The controlled infrared beacon for the wireless instruction guided rocket projectile for the rocket launcher with the diameter of 40mm comprises a beacon shell, an infrared signal generating mechanism, a protection mechanism shell, a piston and a shear screw;

the infrared signal generating mechanism is arranged in the beacon shell and used for sending out an infrared signal; a piston groove is formed in the protection mechanism shell, and a piston is arranged in the piston groove and forms a sealed cavity with the protection mechanism shell; the protection mechanism shell is connected to the tail of the beacon shell through a shear screw and used for protecting the infrared signal generation mechanism during emission; the protection mechanism shell is provided with an air guide hole for providing a channel for external high-temperature gas to enter the sealing cavity.

Further, the infrared signal generating mechanism adopts a gunpowder energy device or an electric energy device;

the gunpowder energy device comprises gunpowder and a tantalum sheet; the gunpowder is arranged in the beacon shell, and the beacon shell is provided with a fire transfer hole which is used as a channel for igniting the gunpowder in the beacon shell by external high-pressure gas; the device comprises a beacon shell, a fire hole, a tantalum sheet, a gunpowder burning hole, a fire transmission hole, a fire control hole and a fire control hole, wherein the beacon shell is arranged on the beacon shell, high-pressure gas outside the beacon shell ignites the gunpowder through the fire transmission hole, and the gunpowder burns to burn and burn the tantalum sheet, so that the tantalum sheet;

the electric energy device comprises a light-emitting diode, a processing circuit and a power supply; the light emitting diode, the processing circuit and the power supply are arranged in the beacon shell, and the light emitting diode is connected with the power supply through the processing circuit.

Has the advantages that:

1. the utility model discloses a beacon module, not only successfully avoided in the rocket section of thick bamboo high thorax to press the district wiring problem, also solved the anti high thorax of beacon and pressed the problem, through the interchangeable design thought of modularization moreover, effectively reduced the comprehensive cost of system.

Secondly, the actuating mechanism is arranged in a fairing at the head of the rocket projectile, so that the limited space on the projectile is reasonably utilized; meanwhile, the device is arranged in front and is far away from the center of mass of the projectile body, and a long force arm can generate larger moment, so that the control of the projectile body is facilitated; and the front device belongs to a duck-type layout, the direction of the control force generated by jet flow is consistent with the direction of the lift force of an attack angle, and the device can provide a large maneuvering overload capacity for a projectile body.

The utility model discloses a wireless instruction guidance rocket bomb can promote the firepower control range of 40mm rocket launcher more than 1500 meters by 300 meters, promotes 40mm rocket launcher by a wide margin and strikes the scope to static and moving target's firepower, and the efficiency of operation of lift system, and this guidance rocket bomb can realize on exceeding 1500 meters range that CEP is less than 0.45 m's control accuracy, has greatly improved the accurate attack ability of 40mm rocket launcher to remote static and moving target.

2. The utility model discloses an air conditioning jet control device or gas jet control device do not need to increase the control surface structure outside the projectile body as actuating mechanism, do not change the pneumatic overall arrangement of former bullet type, have guaranteed the transmission precision under the nearly range uncontrolled condition, and when adopting air conditioning jet control device, and the control power is produced by compressed gas, does not adopt complicated transmission structure, can reduce production manufacturing cost by a wide margin.

3. The utility model discloses a single channel or binary channels steering wheel can use under the condition that requires not high to low coverage target precision as actuating mechanism, can provide continuous control power at rocket projectile flight in-process, is favorable to improving the control accuracy of rocket projectile on the long and medium range. And the single-channel or double-channel steering engine is mature in technology, and is more favorable for realizing long-term storage of guided rocket projectiles.

Drawings

FIG. 1 is a schematic view of the general structure of a guided rocket projectile;

FIG. 2 is a schematic diagram of a gunpowder energy infrared beacon structure;

FIG. 3 is a schematic diagram of an electrical energy infrared beacon structure;

FIG. 4 is a schematic structural diagram of an uncontrolled weight beacon;

FIG. 5 is a schematic view of a cold air jet control device;

FIG. 6 is a front view of the ground launch control device;

fig. 7 is a right side view of the ground launch control device.

Wherein, 1-cold air jet flow control device, 2-wireless instruction receiving device, 3-on-missile control module, 4-on-missile power supply, 5-flight engine, 6-beacon module, 7-warhead, 8-detonating tube, 9-fuze and security mechanism, 10-microstrip annular surface-mounted antenna, 11-tail rod, 12-tail wing, 13-beacon shell I, 14-gunpowder, 15-tantalum sheet, 16-pressing screw, 17-protection mechanism shell, 18-piston, 19-sealing ring, 20-fire hole, 21-shearing screw, 22-air guide hole, 23-sealing cavity, 24-beacon shell II, 25-power supply, 26-processing circuit, 27-light emitting diode, 28-connecting screw rod, 29-insulating pad, 30-counterweight metal structural part, 31-body, 32-steel ball, 33-electromagnetic valve, 34-gas cylinder electric actuator, 35-gas cylinder, 36-nozzle, 37-telescopic rod, 38-ground emission control device, 39-instruction transmitting antenna, 40-white light/red appearance aiming module, 41-transmitting barrel support, 42-trigger, 43-rocket barrel and 44-infrared angle measuring module.

Detailed Description

The present invention will be described in detail below with reference to the accompanying drawings by way of examples.

The embodiment provides a wireless instruction guided rocket projectile for a 40mm rocket tube, which comprises an actuating mechanism, a warfare guiding system, a wireless instruction receiving device 2, an on-projectile control module 3, an on-projectile power supply 4, a flight engine 5, a tail wing 12 assembly and a beacon module 6, wherein the peripheral equipment is a ground launching control device 38, as shown in fig. 1.

The reasonable scheme for solving the problem of near-range engagement is that the guided rocket projectile works in an uncontrolled manner on the near-range, and the precision of the rocket projectile on the near-range is ensured by depending on the launching precision of the rocket tube 43. Therefore, the guided rocket projectile is required to have an aerodynamic shape close to that of the uncontrolled rocket projectile, and when the guided rocket projectile attacks a close-range target, structures which affect the static stability and the uncontrolled ballistic accuracy of the projectile body, such as an aerodynamic control surface extending out of the surface of the projectile body, cannot exist. Therefore, the present embodiment provides a cold air jet flow control device 1 which does not need to use a control surface as an actuator and is installed in a cowling of a rocket projectile head. As shown in fig. 5, the cold air jet control device 1 includes a main body 31, an air bottle 35, an electric actuator 34 for opening the air bottle, two electromagnetic valves 33 and two nozzles 36, the two electromagnetic valves 33 are symmetrically installed on the outer circumference of the main body 31, the two nozzles 36 are symmetrically fixed on the outer circumference of the main body 31 by a threaded connection, the cavities of the two electromagnetic valves 33 are respectively communicated with the two nozzles 36, the end of an expansion link 37 of the electromagnetic valve 33 is fixedly connected with a steel ball 32, and the steel ball 32 is used for closing the communication ports of the cavities and the nozzles 36. The gas cylinder 35 is fixed at one end of the body 31, the gas cylinder opening electric actuator 34 is fixed at the other end of the body 31, and the opening of the gas cylinder 35 is closed; the body 31 is provided with a pipeline communicated with the cavity of the electromagnetic valve 33, and after the gas cylinder opening electric actuator 34 acts according to the working time sequence, the gas cylinder 35 is communicated with the cavity of the electromagnetic valve 33 through the pipeline. When the electromagnetic valve 33 receives a closing signal of the pop-up control module 3, the telescopic rod 37 of the electromagnetic valve 33 sucks back to drive the steel ball 32 to move, the communication port is closed, and at the moment, the cavity of the electromagnetic valve 33 is not communicated with the nozzle 36. When the electromagnetic valve 33 receives an opening signal of the pop-up control module 3, the telescopic rod 37 of the electromagnetic valve 33 extends out to push the steel ball 32 to move, the communication port is opened, and at the moment, the cavity of the electromagnetic valve 33 is communicated with the nozzle 36.

The actuator may also be a gas jet control device, with gunpowder instead of compressed gas to provide the control force. Meanwhile, under the condition of low requirements on the precision and the cost of the near-distance target, a single-channel electric air steering engine or a double-channel electric air steering engine can be adopted.

The detonator system consists of a detonator 8, a warhead 7, a detonator and a security mechanism 9.

The wireless instruction receiving device 2 is composed of a microstrip annular surface-mounted antenna 10 and a signal demodulation circuit.

The on-board control module 3 comprises a roll angle measuring device, an on-board computer and an interface drive circuit. The roll angle measuring device consists of a Hall geomagnetic sensitive sensor and a signal resolving circuit and is used for outputting a roll attitude angle of the rocket projectile in the flight process; the missile-borne computer is used for receiving the control information demodulated by the wireless command receiving device 2 and generating a control command by combining the roll angle of the projectile body given by the roll angle measuring device. The interface driving circuit is respectively and electrically connected with the flying engine 5, the cold air jet flow control device 1, the fuze and security mechanism 9, the pop-up power supply 4 and the wireless command receiving device 2.

The pop-up power supply 4 employs a thermal battery, activated by a launch overload, for powering a pop-up electrical system.

The flying engine 5 is used for accelerating the rocket projectile after the rocket projectile is launched.

The tail 12 assembly consists of a tail rod 11 and a tail 12, is used for stabilizing the flying state of the rocket projectile, and is arranged at the rear end of the flying engine 5.

The beacon module 6 is arranged at the tail part of the rocket projectile and adopts an uncontrolled counterweight beacon or a controlled infrared beacon, and the beacon module 6 is provided with a general mechanical interface which can be switched between the two beacons.

The uncontrolled weight beacon is composed of a weight metal structure 30 for ensuring the aerodynamic shape and quality characteristics of the rocket projectile in an uncontrolled mode, as shown in fig. 4, the end of the weight metal structure 30 extends out, and an external thread is processed on the outer circumference of the extending part for realizing threaded connection with the inner wall of the tail end of the tail rod 11.

The controlled infrared beacon is a gunpowder energy infrared beacon or an electric energy infrared beacon. The gunpowder energy infrared beacon has the advantages of low cost, simple use and maintenance, but weak anti-interference capability, and can work under the conditions of short target distance, good weather condition and no interference source in a battlefield. The electric energy infrared beacon has the advantages that the frequency coding modulation of infrared signals can be realized through a programming driving circuit, the acting distance is long, the anti-interference capability is strong, but the cost is higher compared with that of a gunpowder energy infrared beacon, and the use and the maintenance are relatively complex.

As shown in FIG. 2, the gunpowder energy infrared beacon comprises a beacon shell I13, gunpowder 14, a tantalum sheet 15, a press screw 16 and a separable protection mechanism; the gunpowder 14 is arranged in the beacon shell I13, and the beacon shell I13 is provided with a fire transfer hole 20 which is used as a channel for igniting the gunpowder 14 in the beacon shell I13 by external high-pressure gas; the tantalum sheet 15 is installed on the beacon shell I13 through the pressing screw 16, external high-pressure fuel gas ignites the gunpowder 14 through the fire transfer hole 20, and high temperature generated by burning of the gunpowder 14 burns the tantalum sheet 15, so that the tantalum sheet 15 generates heat to generate an infrared signal. An extending part is arranged at the end part of the beacon shell I13, an external thread is processed on the outer circumference of the extending part and is in threaded connection with the inner wall of the tail end of the tail rod 11, and the connection of the gunpowder energy infrared beacon and the tail rod 11 is achieved. The separable protection mechanism comprises a protection mechanism shell 17, a piston 18, a sealing ring 19 and a shear screw 21; a piston 18 groove is arranged on the protection mechanism shell 17, and a sealing cavity 23 is formed by the piston 18 and a sealing ring 19 which are arranged in the piston 18 groove and the protection mechanism shell 17; the protection mechanism shell 17 is connected to the tail of the beacon shell through two shearing screws 21, the protection mechanism shell 17 is provided with air guide holes 22, high-temperature gas generated by rocket projectile propellant powder enters the sealed cavity 23 through the air guide holes 22 during launching, after a rocket is ejected out of the barrel, pressure difference is formed between high pressure in the sealed cavity 23 and the projectile, the two shearing screws 21 are sheared, and the separable protection mechanism can be separated reliably.

As shown in fig. 3, the electrical energy infrared beacon comprises a beacon housing ii 24, a light emitting diode 27, a processing circuit 26, a power supply 25, an insulating pad 29, a connecting screw 28 and a detachable protection mechanism; the light emitting diode 27, the processing circuit 26 and the power supply 25 are installed in the beacon shell II 24, the power supply 25 is fixed in front of the interior of the beacon shell II 24, one end of the connecting screw 28 extends out and is in threaded connection with the inner wall of the tail end of the tail rod 11 through external threads of the extending end, the other end of the connecting screw 28 limits the power supply 25, and an insulating pad 29 is arranged between the connecting screw 28 and the power supply 25. The light emitting diode 27 is fixed at the rear part inside the beacon shell II 24 and is connected with the power supply 25 through the processing circuit 26, and a fixing filler is coated between the light emitting diode 27 and the beacon shell II 24; after the power supply 25 is activated by overload and stably outputs in the transmitting process, the light emitting diode 27 enters a working state according to the frequency set by a program, and starts to transmit the infrared signal of the frequency coding. The separable protection mechanism and the gunpowder energy infrared beacon adopt the same structure, are used for protecting the internal structure of the second 24 beacon shell during transmission, are arranged at the tail part of the second 24 beacon shell, and realize reliable separation after transmission.

As shown in fig. 6 and 7, the ground emission control device 38 is composed of a white light/infrared observation module 40, an infrared angle measurement module 44, a wireless transmission module and an external command transmitting antenna 39. The guided rocket projectile takes a three-point method as a guide rule, an infrared angle measuring module 44 is used for measuring the angular deviation between the rocket projectile and a target, the guide information generated by the angular deviation is transmitted through a wireless transmitting module, and the wireless transmitting module is used for modulating a low-frequency signal to be sent to the projectile into a high-frequency signal and transmitting the high-frequency signal through an instruction transmitting antenna 39; the micro-strip annular surface-mounted antenna 10 of the on-missile wireless instruction receiving device 2 receives a high-frequency signal, converts the high-frequency signal into a low-frequency signal through a signal demodulation circuit, and transmits the low-frequency signal to the on-missile control module 3, and the on-missile control module 3 generates an execution mechanism control instruction according to the information, so that the cold air jet flow control device 1 is driven to work, and the rocket missile is controlled to fly along the aiming line.

The working process is as follows:

a shooter visually observes a target after entering a position, selects a counterweight beacon or a proper infrared beacon to be installed at the tail of a projectile body according to the target distance and battlefield environment, loads a guided rocket projectile into a rocket tube 43, selects a 'controlled' mode or an 'uncontrolled' mode on a ground launching control device 38 of the rocket tube 43, selects the 'controlled' mode when the shooting distance exceeds 300 meters, and selects the 'uncontrolled' mode when the shooting distance is within 300 meters. After the above work is completed, the shooter puts the rocket tube 43 on the shoulder through the rocket tube holder 41, searches and aims the target through the white/red appearance aiming module 40 of the ground emission control device 38, and after the target is stably aimed, the shooter pulls the trigger 42 to ignite the propellant powder of the rocket projectile. The high pressure gas generated after the propellant powder is ignited acts on the projectile body to push the guided rocket projectile out of the rocket tube 43. The thermal battery as the pop-up power source 4 is activated under the action of the firing overload.

In the 'controlled' mode, high-pressure gas generated during emission enters the interior of the separable protection mechanism through the gas guide hole 22 of the separable protection mechanism of the infrared beacon, and the same pressure as the emission pressure is formed. When the projectile flies off the rocket tube 43, the separable protection mechanisms of the infrared beacons are separated by the difference in internal and external pressures. After the projectile body flies away from the rocket tube 43 for about 0.5 second, the thermal battery works stably, and the catapult electric system starts to work normally. In the process, if the infrared beacon with the energy of the gunpowder 14 is selected, the emitted gas ignites the gunpowder 14 in the beacon through the fire transmitting hole 20 in the emission process to generate infrared luminous energy, and the infrared beacon with the energy of the gunpowder 14 emits an infrared signal outwards after the separable protection mechanism is separated. If the electric energy infrared beacon is selected, the self-contained power supply 25 is activated by overload in the transmitting process, the separable protection mechanism is separated after the electric energy infrared beacon is delivered out of a gun muzzle, the self-contained power supply 25 outputs stable light-emitting diodes 27 to enter a working state according to the frequency set by a program, and the electric energy infrared beacon starts to transmit the infrared signal with the frequency code. Meanwhile, the infrared angle measurement module 44 of the ground launch control device 38 measures the relative position of the rocket projectile relative to the line of sight, and the rocket projectile is encoded by the wireless launch module and then uploaded to the guided rocket projectile. After receiving the control information demodulated by the wireless instruction receiving device 2, the control module 3 on the guided rocket projectile forms a control instruction by combining the projectile body roll angle given by the roll angle measuring device, and sends the control instruction to the cold air jet flow control device 1 to control the flying posture of the projectile body until the target is destroyed.

In the 'uncontrolled' mode, the ground launch control device 38 sends specific coded information to the rocket projectile through the wireless launch module, and the guidance control system on the rocket projectile does not work and flies in an uncontrolled manner, and the precision of the rocket projectile on the near range is ensured by means of the launch precision of the rocket tube 43.

In summary, the above 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

The wireless instruction guided rocket projectile for the rocket tube of 1.40mm is characterized in that an actuating mechanism, a wireless instruction receiving device, an on-projectile control module and a beacon module are added to the rocket projectile, and a ground launching control device is used as peripheral equipment;

the executing mechanism is arranged in a fairing at the head of the rocket projectile, the beacon module is arranged at the tail of the rocket projectile, an uncontrolled counterweight beacon or a controlled infrared beacon is adopted, and a universal mechanical interface is arranged on the beacon module and can be switched between the two beacons;

when the uncontrolled counterweight beacon works, the ground launching control device is wirelessly connected with the rocket projectile, a guidance control system on the rocket projectile does not work, and the rocket projectile flies in an uncontrolled manner;

when the controlled infrared beacon works, the controlled infrared beacon and the ground are wirelessly connected to transmit an infrared signal, the ground is wirelessly connected with the wireless instruction receiving device on the rocket projectile, the ground is wirelessly connected with the relative position information of the rocket projectile, which is acquired, relative to an aiming line, of the rocket projectile is transmitted to the wireless instruction receiving device, the wireless instruction receiving device is electrically connected with the projectile upper control module, the projectile upper control module is electrically connected with the execution mechanism, and the projectile upper control module transmits a control instruction to the execution mechanism.
2. The wireless command guided rocket projectile for a 40mm rocket launcher according to claim 1 wherein said actuator is a cold air jet control device or a gas jet control device.
3. The wireless command guided rocket projectile for a 40mm rocket launcher according to claim 1 wherein said actuator employs a single or dual channel steering engine.
4. The wireless command guided rocket projectile for 40mm rocket cartridges as claimed in claim 2, wherein said cold air jet control means comprises a body, a gas cylinder electric actuator, two solenoid valves and two nozzles;

the two electromagnetic valves are symmetrically arranged on the outer circumference of the body, the two nozzles are symmetrically arranged on the outer circumference of the body, and cavities of the two electromagnetic valves are respectively communicated with the two nozzles;

the gas cylinder is fixed at one end of the body, and the gas cylinder opening electric actuator is fixed at the other end of the body and closes the opening of the gas cylinder; the body is provided with a pipeline communicated with the electromagnetic valve cavity, and when the gas cylinder electric actuator works, the gas cylinder is communicated with the electromagnetic valve cavity through the pipeline; and the electromagnetic valve is opened, and the cavity of the electromagnetic valve is communicated with the nozzle.
5. The wireless command guided projectile for a 40mm rocket launcher according to claim 1 wherein said uncontrollable weight beacon is comprised of a weighted metal structural member for ensuring aerodynamic shape and mass characteristics of the projectile in an uncontrolled mode.
6. The wireless command guided rocket projectile for a 40mm rocket case as claimed in claim 1 wherein said controlled infrared beacon is a gunpowder energy infrared beacon comprising a beacon housing, gunpowder, tantalum pellet and a detachable protection mechanism;

the gunpowder is arranged in the beacon shell, and the beacon shell is provided with a fire transfer hole which is used as a channel for igniting the gunpowder in the beacon shell by external high-pressure gas; the device comprises a beacon shell, a fire hole, a tantalum sheet, a gunpowder burning hole, a fire transmission hole, a fire control hole and a fire control hole, wherein the beacon shell is arranged on the beacon shell, high-pressure gas outside the beacon shell ignites the gunpowder through the fire transmission hole, and the gunpowder burns to burn and burn the tantalum sheet, so that the tantalum sheet; the separable protection mechanism is used for protecting the internal structure of the beacon shell during launching, is arranged at the tail part of the beacon shell, and realizes separation after launching.
7. The wireless-command guided rocket projectile for a 40mm rocket launcher according to claim 1 wherein said controllable infrared beacon is an electrical energy infrared beacon comprising a beacon housing, a light emitting diode, processing circuitry, a power source and a detachable protection mechanism;

the light-emitting diode, the processing circuit and the power supply are arranged in the beacon shell, and the light-emitting diode is connected with the power supply through the processing circuit; the separable protection mechanism is arranged at the tail part of the beacon shell and used for protecting the internal structure of the beacon shell during launching and realizing separation after launching.
8. The wireless command guided rocket projectile for a 40mm rocket cartridge as defined in claim 6 or 7 wherein said separable protection mechanism comprises a protection mechanism housing, a piston and a shear screw;

a piston groove is formed in the protection mechanism shell, and a piston is arranged in the piston groove and forms a sealed cavity with the protection mechanism shell; the protection mechanism shell is connected with the beacon shell through a shearing screw, the protection mechanism shell is provided with an air guide hole, high-temperature gas generated by rocket projectile propellant powder enters the sealing cavity through the air guide hole during launching, after the rocket is ejected out of the barrel, pressure difference is formed between high pressure in the sealing cavity and the projectile, the shearing screw is sheared, and the separable protection mechanism realizes separation.
The controlled infrared beacon for the rocket projectile guided by the wireless instruction for the 9.40mm rocket tube is characterized by comprising a beacon shell, an infrared signal generating mechanism, a protection mechanism shell, a piston and a shear screw;

the infrared signal generating mechanism is arranged in the beacon shell and used for sending out an infrared signal; a piston groove is formed in the protection mechanism shell, and a piston is arranged in the piston groove and forms a sealed cavity with the protection mechanism shell; the protection mechanism shell is connected to the tail of the beacon shell through a shear screw and used for protecting the infrared signal generation mechanism during emission; the protection mechanism shell is provided with an air guide hole for providing a channel for external high-temperature gas to enter the sealing cavity.
10. The wireless command guided rocket projectile having controlled infrared beacons for the 40mm rocket launcher according to claim 9 wherein said infrared signal generating means employs pyrotechnic or electrical energy devices;

the gunpowder energy device comprises gunpowder and a tantalum sheet; the gunpowder is arranged in the beacon shell, and the beacon shell is provided with a fire transfer hole which is used as a channel for igniting the gunpowder in the beacon shell by external high-pressure gas; the device comprises a beacon shell, a fire hole, a tantalum sheet, a gunpowder burning hole, a fire transmission hole, a fire control hole and a fire control hole, wherein the beacon shell is arranged on the beacon shell, high-pressure gas outside the beacon shell ignites the gunpowder through the fire transmission hole, and the gunpowder burns to burn and burn the tantalum sheet, so that the tantalum sheet;

the electric energy device comprises a light-emitting diode, a processing circuit and a power supply; the light emitting diode, the processing circuit and the power supply are arranged in the beacon shell, and the light emitting diode is connected with the power supply through the processing circuit.