CN211012681U - Universal extended-range controlled projectile body platform for 40mm rocket tube - Google Patents
Universal extended-range controlled projectile body platform for 40mm rocket tube Download PDFInfo
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- CN211012681U CN211012681U CN201920838432.8U CN201920838432U CN211012681U CN 211012681 U CN211012681 U CN 211012681U CN 201920838432 U CN201920838432 U CN 201920838432U CN 211012681 U CN211012681 U CN 211012681U
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Abstract
The utility model provides a universal range-extending controlled projectile body platform for a 40mm rocket launcher, which comprises an electric steering engine, a warhead, a missile-borne control module, a range-extending engine, a flight engine and a tail wing assembly; the electric steering engine, the warhead, the missile loading control module, the range extending engine, the flight engine and the tail wing assembly are sequentially connected to form a missile body platform; the projectile body platform is in butt joint with an external guidance component module by adopting a universal mechanical electrical interface module to form a guidance rocket projectile; the range-extending engine provides thrust required by range extension for the guided rocket projectile; the guidance component module is communicated with the missile-borne control module, different guidance information is transmitted to the missile-borne control module, the missile-borne control module is communicated with the electric steering engine, the generated track correction control instruction is sent to the electric steering engine, and the electric steering engine is used for executing action according to the control instruction to enable the rocket projectile to fly until the rocket projectile hits a target. The utility model discloses possess the accurate striking and the suppression ability to moving and static target on the far range.
Description
Technical Field
The utility model relates to a guidance rocket projectile technical field, concretely relates to 40mm rocket launcher is with general journey that increases has accuse projectile body platform.
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, the farthest range of the platform to a static target is only 300m under the condition that the dispersion accuracy CEP (circle probability error) is 0.45m, and the flying distance of the rocket projectile is only about 1500m even if the target hitting accuracy is not required. This greatly limits the effectiveness of the 40mm rocket mount long range combat.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides a 40mm rocket launcher is with general range of increasing accuse projectile body platform possesses accurate striking and suppression ability to moving and static target on the far range.
The utility model adopts the following technical scheme:
a universal range-extending controlled projectile body platform for a 40mm rocket tube comprises an electric steering engine, a warhead, a projectile load control module, a range-extending engine, a flight engine and a tail wing assembly;
the electric steering engine is arranged at the head, and the electric steering engine, the warhead, the missile load control module, the range extending engine, the flight engine and the tail wing assembly are sequentially connected to form a missile body platform; the projectile body platform is in butt joint with an external guidance component module by adopting a universal mechanical-electrical interface module to form a guidance rocket projectile; the range-extending engine provides thrust required by range extension for the guided rocket projectile; the guidance component module is communicated with the missile-borne control module, different guidance information is transmitted to the missile-borne control module, the missile-borne control module is communicated with the electric steering engine, a generated track correction control instruction is sent to the electric steering engine, and the electric steering engine is used for executing action according to the control instruction to enable the rocket projectile to fly until the rocket projectile hits a target.
Furthermore, a turbulent flow control device is adopted to replace an electric steering engine, and the turbulent flow control device is arranged on the end face of the tail part of the range-extended engine.
Further, the projectile body platform further comprises a turbulent flow control device, and the turbulent flow control device is installed on the tail end face of the extended-range engine.
Furthermore, the extended-range engine adopts an inclined spray pipe ultra-caliber extended-range engine or a straight spray pipe ultra-caliber extended-range engine.
Furthermore, the turbulent flow control device comprises a turbulent flow sheet, a transmission rod, a turbulent flow body and an electromagnet assembly;
the electromagnet assembly is arranged in the spoiler body, the end part of the transmission rod is fixedly connected with the spoiler, the transmission rod moves along the radial direction of the range-extended engine under the action of the magnetic field of the electromagnet assembly, and the airflow direction of the range-extended engine with the inclined spray pipe is changed through the spoiler.
Further, the electromagnet assembly comprises a spring, an armature, an iron core, a coil and a cover plate;
the iron core is arranged on the outer side of the armature and is fixed in the turbulent flow body through the cover plate; the transmission rod is arranged in the center of the iron core, one end of the transmission rod penetrates through the cover plate to extend out, the other end of the transmission rod is fixedly connected with the armature, and the transmission rod is limited to move towards the armature by a boss arranged on the transmission rod; the spring is sleeved on the transmission rod and compressed between the bottom surface of the cover plate and the end surface of the boss of the transmission rod; the coil is wound around the core.
Furthermore, the universal mechanical-electrical interface module comprises an active end and a passive end, wherein the active end is arranged on the guidance component module, and the passive end is arranged on the electric steering engine;
the active end comprises an interface active body, an installation positioning block, a rotation stopping positioning block and a telescopic electric contact pin; the connector driving body is a cylinder, the mounting positioning block is a protruding structure arranged on the outer circumferential surface of the connector driving body, and the rotation stopping positioning block is arranged on the mounting positioning block, protrudes along the axis direction of the elastomer and is opposite to the extending direction of the telescopic electric contact pin; the telescopic electric contact pin is arranged on the matched end surface of the interface driving body and the interface driven body;
the passive end comprises an interface passive body and a sliding ring plate; the interface passive body is a cylinder, and the end surface matched with the interface active body is provided with an installation positioning groove which is matched with an installation positioning block; an annular groove for the rotation of the driving end is formed in the interface driven body, and the axial length of the annular groove is greater than that of the mounting positioning block; the end face of the inner side of the annular groove, which is far away from the opening, is fixedly connected with a slip ring plate, the slip ring plate is vertical to the axial direction of the cylinder, and a conductive slip ring is arranged on the slip ring plate; and a rotation stopping positioning groove is formed in the end face, opposite to the sliding ring plate, of the annular groove, and the included angle between the rotation stopping positioning groove and the installation positioning groove is a set angle.
Furthermore, the outer walls of the interface driving body and the interface driven body are provided with positioning lines, and after the interface driving body rotates for a set angle, the positioning lines on the interface driving body are aligned with the positioning lines on the outer wall of the interface driven body.
Has the advantages that:
1. the utility model adopts the extended-range engine, the missile-borne control module and the actuating mechanism, has the controlled flight capability with the range of 5000m, improves the firepower striking range from 300m to 5000m, and realizes the accurate striking of the mobile and static targets by utilizing the communication coordination among the guidance component module, the missile-borne control module and the actuating mechanism;
secondly, the universal mechanical and electrical interface module is adopted to realize modularized rapid butt joint, different guidance component modules are adapted to different striking targets, the fighting efficiency of a 40mm rocket launcher is greatly improved, and the application of rocket projectiles with various guidance control modes on the rocket launcher is realized.
2. The utility model discloses a put spray tube super bore extended range engine to one side, effectively reduced engine spray tube spun gas to the heat radiation influence of rocket projectile, also avoided producing pneumatic interference to the fin simultaneously, can also save rocket projectile layout space.
3. The utility model discloses a vortex controlling means belongs to thrust vector controlling means, can produce stable control power and control torque under low-speed and big angle of attack, can compensate the not enough of duck formula overall arrangement rudder, jointly use it and electric steering wheel, can realize the combined control of thrust vector and aerodynamic under the unified control of year control module of bullet, can fine satisfy the demand that modularization guidance load is to rocket projectile control mode and controllability.
4. The utility model discloses a general mechanical electrical interface module not only can guarantee quick assembly disassembly at the butt joint in-process, can reliably guarantee electric signal transmission's reliability, mechanical connection's reliability and guidance module and projectile body platform's phase relation and positioning accuracy simultaneously.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
fig. 2(a) and 2(b) are schematic structural diagrams of the active end of the universal mechanical electrical interface module;
FIGS. 3(a) and 3(b) are schematic diagrams of a passive end of a universal mechanical electrical interface module structure;
FIG. 4 is a schematic structural view of an inclined nozzle ultra-caliber range-extended engine;
fig. 5(a) and 5(b) are schematic structural diagrams of the turbulent flow control device when the turbulent flow control device is powered off and powered on, respectively;
FIG. 6 is a schematic diagram of the electromagnet;
wherein, 1-a satellite guidance component module, 2-a universal mechanical and electrical interface module, 3-an electric steering engine, 4-a warhead, 5-a missile-borne control module, 6-an inclined nozzle ultra-caliber range-increasing engine, 7-a turbulent flow control device, 8-a flight engine, 9-a tail wing component, 10-an interface driving body, 11-an installation positioning block, 12-a telescopic electric contact pin, 13-a rotation stopping positioning block, 14-an interface driven body, 15-a slip ring plate, 16-an installation positioning groove, 17-a rotation stopping positioning groove, 18-a slip ring, 19-a fixing screw, 20-an engine shell, 21-range-increasing propellant, 22-an inclined nozzle, 23-a delay igniter, 24-an ignition explosive package and 25-a turbulent flow sheet, 26-cover plate, 27-electromagnet, 28-spoiler body, 29-transmission rod, 30-compression spring, 31-iron core, 32-coil and 33-armature.
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 universal extended-range controlled projectile body platform for a 40mm rocket tube, wherein the head of the projectile body platform is provided with a universal mechanical-electrical interface module 2, and the projectile body platform is butted with an external guidance component module through the universal mechanical-electrical interface module 2 to form a guidance rocket projectile; the guidance component module can adopt a satellite guidance component module or a laser semi-active guidance head module or a television/infrared/millimeter wave active guidance head module, and the guidance component module of the embodiment adopts a satellite guidance component module 1.
The rocket projectile adopts an ultra-caliber range-extending engine, the ultra-caliber refers to the diameter of a rocket tube with the caliber larger than 40mm, and the rocket projectile is further provided with a universal mechanical-electrical interface module 2, a projectile loading control module 5 and an actuating mechanism. The ultra-caliber range-increasing engine adopts an inclined spray pipe ultra-caliber range-increasing engine 6, and can also adopt a straight spray pipe ultra-caliber range-increasing engine on the premise of well performing rear rocket projectile thermal protection treatment and keeping a certain phase relation between a tail wing and an engine spray pipe. The executing mechanism adopts an electric steering engine 3 or a turbulent flow control device 7 or simultaneously uses the electric steering engine 3 and the turbulent flow control device 7 or adopts an integrated one-dimensional or two-dimensional correction component (comprising a satellite signal receiver and a simple steering engine) to complete the guidance and control of the rocket projectile.
As shown in fig. 1, a satellite guidance component module 1 (including a satellite signal receiver and a fuse), a universal mechanical electrical interface module 2, an electric steering engine 3, a warhead 4, a missile-borne control module 5, an inclined nozzle ultra-caliber range-extending engine 6, a turbulent flow control device 7, a flight engine 8 and a tail wing component 9 are sequentially connected from head to tail to form a rocket projectile.
The satellite guidance assembly module 1 consists of a satellite signal receiver (GPS) and a fuse and is arranged at the head of the rocket projectile. In the process of rocket projectile flying, the coordinate position of the rocket projectile is output in real time after GPS positioning, and the coordinate position is sent to the projectile load control module 5.
The universal mechanical electrical interface module 2 is used for realizing the rapid butt joint of the satellite guidance component module 1 and the universal extended-range controlled projectile body platform. As shown in fig. 2(a) and 2(b), the universal mechanical-electrical interface module 2 includes an active end and a passive end, the active end is disposed on the satellite guidance module 1, and the passive end is disposed on the electric steering engine 3.
The active end comprises an interface active body 10, a mounting positioning block 11, a rotation stopping positioning block 13 and a telescopic electric contact pin 12; the interface driving body 10 is a cylinder, the mounting positioning block 11 is a protruding structure arranged on the outer circumferential surface of the interface driving body 10, and the rotation stopping positioning block 13 is arranged on the mounting positioning block 11, protrudes along the axis direction of the rocket projectile and is opposite to the extending direction of the telescopic electrical contact pin 12; the retractable electrical pins 12 are disposed on the end surfaces of the interface active body 10 that mate with the interface passive body 14.
As shown in fig. 3(a) and 3(b), the passive end includes an interface passive body 14 and a slip ring plate 15; the interface passive body 14 is a cylinder, an installation positioning groove 16 is arranged on the end surface matched with the interface active body 10, and the installation positioning groove 16 is matched with the installation positioning block 11; an annular groove for the rotation of the driving end is formed in the interface driven body 14, and the axial length of the annular groove is greater than that of the mounting and positioning block 11; the end face of the inner side of the annular groove, which is far away from the opening, is fixedly connected with a sliding ring plate 15 through a fixing screw 19, the sliding ring plate 15 is vertical to the axial direction of the cylinder, and a conductive sliding ring 18 is arranged on the sliding ring plate 15; the end face of the annular groove opposite to the sliding ring plate 15 is provided with a rotation stopping positioning groove 17, and the included angle between the rotation stopping positioning groove 17 and the installation positioning groove 16 is 90 degrees. The outer walls of the interface driving body 10 and the interface driven body 14 are provided with positioning lines, and after the interface driving body 10 rotates by 90 degrees, the positioning lines on the interface driving body 10 are aligned with the positioning lines on the outer wall of the interface driven body 14.
The working principle is that the mounting positioning block 11 on the interface driving body 10 and the mounting positioning groove 16 on the interface driven body 14 are quickly positioned, the interface driving body 10 is pressed towards the tail direction after positioning and is clockwise rotated by 90 degrees to be in place, and at the moment, the positioning line on the interface driving body 10 is aligned with the positioning line on the interface driven body 14; after the connector is in place, the rotation stopping positioning block 13 is aligned with the rotation stopping positioning groove 17, the pressing force applied to the tail direction of the bullet is removed, the connector driving body 10 is pushed to move towards the bullet direction by virtue of the telescopic springs in the eight groups of electrical contact pins, the rotation stopping positioning block 13 is pushed into the rotation stopping positioning groove 17 of the connector driven body 14, and the circumferential positioning between the connector driving body 10 and the connector driven body 14 is realized; meanwhile, the end surface limit of the interface passive body 14 with the upper rotary positioning groove 17 and the elasticity applied to the interface passive body 14 by the inner telescopic springs of the eight groups of electric pins on the interface active body 10 ensure the axial positioning of the interface active body 10 and the interface passive body 14, so that the positioning and reliable contact of the electric pins and the sliding ring 18 are realized; during disassembly, the interface driving body 10 is pressed towards the direction of the tail of the bullet, so that the rotation stopping positioning block 13 on the interface driving body 10 is separated from the rotation stopping positioning groove 17 on the interface driven body 14, after the rotation is performed by 90 degrees anticlockwise, the installation positioning block 11 on the interface driving body 10 is aligned with the installation positioning groove 16 on the interface driven body 14, and the connection is separated under the action of the telescopic spring of the electrical contact pin.
The electric steering engine 3 is composed of a rudder sheet, a transmission mechanism, a motor, a driver and the like, receives a controller command given by the projectile loading control module 5 to generate control force and control moment, and accordingly enables the rocket projectile to fly according to a preset trajectory.
The warhead 4 consists of a security mechanism, a detonating tube and a warhead body.
The missile-borne control module 5 consists of a wireless loading and receiving module, an attitude measuring device, a missile-borne computer and a missile-borne power supply. The wireless setting receiving module is used for receiving geomagnetic reference, target position information, altitude information, meteorological condition information and ephemeris data wirelessly transmitted by the ground simple fire control setter module before shooting, and information such as rocket tube shooting angle and shooting direction calculated by ground simple fire control. The attitude measurement device is integrated with an inertial device and a geomagnetic element, and can measure information such as a rolling angle, a pitching angle, a yaw angular velocity, acceleration and the like in the moving process of the projectile body platform so as to meet the requirements of various control laws. And the on-board computer manages the platform working process, calculates according to the received satellite positioning device information and the attitude measuring device information, plans a flight trajectory, generates a control instruction and sends the generated control instruction to the turbulence control device 7 and the electric steering engine 3. The pop-up power source employs a thermal battery activated by launch overload for powering the pop-up electrical system.
The inclined nozzle ultra-caliber range-increasing engine 6 consists of an engine shell 20, inclined nozzles 22 arranged on two sides of the engine shell 20 and forming a certain angle with the axis of a rocket projectile, a range-increasing propellant 21, an ignition explosive package 24 and a delay igniter, and realizes delay ignition by adopting an ignition mode of launching overload activation delay igniters 23; the inclined nozzle super-caliber range-increasing engine 6 provides continuous thrust for flying rocket projectiles to ensure that the projectile platform has the flying capacity of more than 5000m, and the structure of the inclined nozzle super-caliber range-increasing engine is shown in fig. 4.
As shown in fig. 5(a), 5(b), and 6, the spoiler control device 7 is a low-cost thrust vector control mechanism. In the working process of the inclined nozzle ultra-caliber extended-range engine 6, the spoiler 25 is driven to move by the attraction action of the electromagnet 27, and the spoiler 25 and the engine jet flow interact to generate thrust eccentricity to form control force and control moment on the rocket projectile.
The turbulent flow control device 7 is arranged on the tail end face of the inclined nozzle super-caliber range-extended engine 6 and comprises a turbulent flow plate 25, a transmission rod 29, a turbulent flow body 28, a compression spring 30, an armature 33, an iron core 31, a coil 32 and a cover plate 26; the iron core 31 is arranged on the outer side of the armature 33, and the iron core 31 is fixed in the spoiler body 28 through the cover plate 26; the transmission rod 29 is arranged in the center of the iron core 31, one end of the transmission rod penetrates through the cover plate 26 to extend out and is fixedly connected with the spoiler 25, the other end of the transmission rod is fixedly connected with the armature 33, and the transmission rod 29 limits the transmission rod to move towards the armature 33 by virtue of a boss arranged on the transmission rod 29; the compression spring 30 is sleeved on the transmission rod 29 and compressed between the bottom surface of the cover plate 26 and the boss end surface of the transmission rod 29; the coil 32 is wound around the core 31. The transmission rod 29 moves along the radial direction of the inclined nozzle super-caliber range-increasing engine 6 under the action of the magnetic field of the electromagnet 27, and the airflow direction of the inclined nozzle super-caliber range-increasing engine 6 is changed through the spoiler 25.
The working principle is as follows: when the coil 32 is energized, the core 31 and the armature 33 are magnetized into two magnets of opposite polarities, creating an attractive force. When the suction force is greater than the reaction force of the compression spring 30, the armature 33 moves towards the iron core 31 to drive the transmission rod 29 to move, so that the spoiler 25 is close to the nozzle of the inclined nozzle super-caliber extended-range engine 6 to change the direction of the airflow; when the coil 32 is de-energized, the armature 33 is far away from the iron core 31 under the counter-force of the compression spring 30, and drives the transmission rod 29 to move until the boss of the transmission rod 29 is in contact limit with the iron core 31, and at the moment, the spoiler 25 leaves the nozzle orifice without changing the airflow direction.
The flying engine 8 is used for providing primary acceleration for the projectile body platform after the projectile body platform is launched, and when precision launching is not required, the range can reach 1500 m.
The empennage assembly 9 is arranged at the tail part of the rocket projectile, consists of a tail rod, an empennage and a rotation guide turbine and is used for stabilizing the flying posture of the rocket projectile and providing the rotating speed of the rocket projectile away from a barrel.
When the system works, after a shooter enters a position, the target state is determined according to the instruction of a superior command system or by adopting a foresight device, and then the corresponding guidance assembly module is determined to be selected, wherein the satellite guidance assembly module 1 is selected in the embodiment. The launcher butts the satellite guidance assembly module 1 with the general extended-range controlled projectile body platform to form a full-standby projectile, and then the simple fire control setter module is used for setting geomagnetic geographical reference information, target position information, meteorological condition information, ephemeris data, altitude information and shooting angle and shooting direction calculated by simple fire control to the projectile body platform. After the operations are finished, the shooter loads the full-ready cartridge into the rocket tube, places the rocket tube on the shoulder, and adjusts the launching angle to a set range through the rocket tube sighting device. The shooter pulls a trigger to ignite the propellant powder, the propellant powder pushes a rocket bomb to accelerate to a preset speed after being ignited, and the propellant overload generated in the process simultaneously activates a thermal battery on the bomb and a delay igniter 23 of the inclined nozzle super-caliber range-increasing engine 6; after the thermal battery is discharged from the blast hole for about 0.5s, the thermal battery works normally and stably; the inclined spray pipe ultra-caliber range-increasing engine 6 is ignited at a blast outlet for about 1s and continuously provides thrust; after a satellite signal receiver (GPS) of the satellite guidance component module 1 is powered on for about 5s, positioning is completed and position information is continuously output; the rocket projectile attitude measuring device comprises a projectile computer, a rocket projectile space position measuring device and a rocket projectile attitude measuring device, wherein the projectile computer is used for receiving rocket projectile space position information and attitude information output by the rocket projectile space position measuring device and then generating a control instruction; and the control instruction is distributed to the turbulence control device 7 and the electric steering engine 3 to control the rocket projectile to fly along the planned trajectory.
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 (8)
1. A universal range-extending controlled projectile body platform for a 40mm rocket tube is characterized by comprising an electric steering engine, a warhead, a projectile load control module, a range-extending engine, a flight engine and a tail wing assembly;
the electric steering engine is arranged at the head, and the electric steering engine, the warhead, the missile load control module, the range extending engine, the flight engine and the tail wing assembly are sequentially connected to form a missile body platform; the projectile body platform is in butt joint with an external guidance component module by adopting a universal mechanical-electrical interface module to form a guidance rocket projectile; the range-extending engine provides thrust required by range extension for the guided rocket projectile; the guidance component module is communicated with the missile-borne control module, different guidance information is transmitted to the missile-borne control module, the missile-borne control module is communicated with the electric steering engine, a generated track correction control instruction is sent to the electric steering engine, and the electric steering engine is used for executing action according to the control instruction to enable the rocket projectile to fly until the rocket projectile hits a target.
2. The universal extended-range controlled projectile platform for a 40mm rocket launcher according to claim 1, wherein a spoiler control device is used instead of an electric steering engine, said spoiler control device being mounted on the end face of the tail of the extended-range engine.
3. The universal extended-range controlled projectile platform for a 40mm rocket launcher according to claim 1, wherein said projectile platform further comprises turbulation control means.
4. The universal extended-range controlled projectile platform for a 40mm rocket launcher according to claim 3, wherein said extended-range engine is an inclined nozzle ultra-bore extended-range engine or a straight nozzle ultra-bore extended-range engine.
5. The universal extended-range controlled projectile platform for a 40mm rocket launcher according to claim 3, wherein said spoiler control means comprises a spoiler, a drive link, a spoiler body, and an electromagnet assembly;
the electromagnet assembly is arranged in the spoiler body, the end part of the transmission rod is fixedly connected with the spoiler, the transmission rod moves along the radial direction of the range-extended engine under the action of the magnetic field of the electromagnet assembly, and the airflow direction of the range-extended engine with the inclined spray pipe is changed through the spoiler.
6. The universal extended-range controlled projectile platform for a 40mm rocket launcher according to claim 5, wherein said electromagnet assembly comprises a spring, an armature, an iron core, a coil, and a cover plate;
the iron core is arranged on the outer side of the armature and is fixed in the turbulent flow body through the cover plate; the transmission rod is arranged in the center of the iron core, one end of the transmission rod penetrates through the cover plate to extend out, the other end of the transmission rod is fixedly connected with the armature, and the transmission rod is limited to move towards the armature by a boss arranged on the transmission rod; the spring is sleeved on the transmission rod and compressed between the bottom surface of the cover plate and the end surface of the boss of the transmission rod; the coil is wound around the core.
7. The universal extended-range controlled projectile platform for a 40mm rocket launcher according to claim 1, wherein said universal mechanical-electrical interface module comprises an active end and a passive end, wherein said active end is disposed on said guidance assembly module, and said passive end is disposed on said electric steering engine;
the active end comprises an interface active body, an installation positioning block, a rotation stopping positioning block and a telescopic electric contact pin; the connector driving body is a cylinder, the mounting positioning block is a protruding structure arranged on the outer circumferential surface of the connector driving body, and the rotation stopping positioning block is arranged on the mounting positioning block, protrudes along the axis direction of the elastomer and is opposite to the extending direction of the telescopic electric contact pin; the telescopic electric contact pin is arranged on the matched end surface of the interface driving body and the interface driven body;
the passive end comprises an interface passive body and a sliding ring plate; the interface passive body is a cylinder, and the end surface matched with the interface active body is provided with an installation positioning groove which is matched with an installation positioning block; an annular groove for the rotation of the driving end is formed in the interface driven body, and the axial length of the annular groove is greater than that of the mounting positioning block; the end face of the inner side of the annular groove, which is far away from the opening, is fixedly connected with a slip ring plate, the slip ring plate is vertical to the axial direction of the cylinder, and a conductive slip ring is arranged on the slip ring plate; and a rotation stopping positioning groove is formed in the end face, opposite to the sliding ring plate, of the annular groove, and the included angle between the rotation stopping positioning groove and the installation positioning groove is a set angle.
8. The universal extended-range controlled projectile platform of claim 7 wherein the outer walls of said interface active and passive bodies are provided with alignment lines, and after said interface active body is rotated a predetermined angle, said alignment lines on said interface active body are aligned with said alignment lines on said outer wall of said interface passive body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920838432.8U CN211012681U (en) | 2019-06-05 | 2019-06-05 | Universal extended-range controlled projectile body platform for 40mm rocket tube |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920838432.8U CN211012681U (en) | 2019-06-05 | 2019-06-05 | Universal extended-range controlled projectile body platform for 40mm rocket tube |
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| CN211012681U true CN211012681U (en) | 2020-07-14 |
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| CN201920838432.8U Withdrawn - After Issue CN211012681U (en) | 2019-06-05 | 2019-06-05 | Universal extended-range controlled projectile body platform for 40mm rocket tube |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112050690A (en) * | 2019-06-05 | 2020-12-08 | 北京恒星箭翔科技有限公司 | Universal extended-range controlled projectile body platform for 40mm rocket tube |
-
2019
- 2019-06-05 CN CN201920838432.8U patent/CN211012681U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112050690A (en) * | 2019-06-05 | 2020-12-08 | 北京恒星箭翔科技有限公司 | Universal extended-range controlled projectile body platform for 40mm rocket tube |
| CN112050690B (en) * | 2019-06-05 | 2024-09-03 | 北京恒星箭翔科技有限公司 | Universal range-extending controlled projectile body platform for 40mm rocket tube |
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