CN113624075A - Rocket projectile for 40 mm rocket tube based on straight nozzle extended-range engine - Google Patents
Rocket projectile for 40 mm rocket tube based on straight nozzle extended-range engine Download PDFInfo
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- CN113624075A CN113624075A CN202011590495.XA CN202011590495A CN113624075A CN 113624075 A CN113624075 A CN 113624075A CN 202011590495 A CN202011590495 A CN 202011590495A CN 113624075 A CN113624075 A CN 113624075A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
- F41G7/30—Command link guidance systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/04—Stabilising arrangements using fixed fins
- F42B10/06—Tail fins
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/38—Range-increasing arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides a rocket projectile for a 40 mm rocket tube based on a straight nozzle range-extending engine, which comprises a guidance assembly, a projectile loading control module, an execution mechanism, a warhead, the straight nozzle range-extending engine, a tail wing assembly and a launching mechanism, wherein the rocket projectile is formed by sequentially connecting the guidance assembly, the projectile loading control module, the execution mechanism, the warhead, the straight nozzle range-extending engine, the tail wing assembly and the launching mechanism from head to tail, and the tail wing assembly is arranged on a nozzle of the straight nozzle range-extending engine; the launching mechanism provides initial power for the rocket projectile, and after the straight jet pipe extended-range engine works, the generated fuel gas forms certain pressure to separate the launching mechanism from the empennage assembly, and the straight jet pipe extended-range engine continues to provide power for the rocket projectile; the guidance assembly is communicated with the missile-borne control module, the guidance information is transmitted to the missile-borne control module, the missile-borne control module is communicated with the executing mechanism, the generated track correction control instruction is sent to the executing mechanism, and the executing mechanism 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 present invention has the capability of accurately striking and suppressing a moving and static target at a long range.
Description
Technical Field
The invention relates to the technical field of guided rocket projectiles, in particular to a rocket projectile for a 40-millimeter rocket tube based on a straight nozzle extended-range engine.
Background
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, 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 platform does not require the hitting accuracy. This greatly limits the effectiveness of the 40 mm rocket launcher platform for long distance combat.
Disclosure of Invention
In view of the above, the invention provides a rocket projectile for a 40 mm rocket tube based on a straight nozzle extended range engine, which has the capability of accurately striking and pressing a moving and static target at a long range.
The technical scheme adopted by the invention is as follows:
the rocket projectile for the rocket launcher with the length of 40 mm based on the straight nozzle range-extending engine comprises a guidance assembly, a projectile-loaded control module, an execution mechanism, a warhead, the straight nozzle range-extending engine, a tail wing assembly and a launching mechanism;
the rocket projectile comprises a guidance assembly, a projectile loading control module, an actuating mechanism, a warhead, a straight jet pipe range-extended engine, a tail wing assembly and a launching mechanism which are sequentially connected from head to tail to form the rocket projectile, wherein the tail wing assembly is arranged on a jet pipe of the straight jet pipe range-extended engine;
the launching mechanism provides initial power for the rocket projectile, and after the straight jet pipe extended-range engine works, the generated fuel gas forms certain pressure to separate the launching mechanism from the empennage assembly, and the straight jet pipe extended-range engine continues to provide flight power for the rocket projectile; the guidance assembly is communicated with the missile-borne control module, the guidance information is transmitted to the missile-borne control module, the missile-borne control module is communicated with the executing mechanism, the generated track correction control instruction is sent to the executing mechanism, and the executing mechanism is used for executing action according to the control instruction to enable the rocket projectile to fly until the rocket projectile hits a target.
Further, the tail wing assembly comprises a tail wing, a tail wing mounting seat and a connecting cylinder;
the tail wing mounting seat is fixedly connected to the rear part of the spray pipe, and the tail wing is rotatably mounted on the tail wing mounting seat; the connecting cylinder is a cylinder with one open end and one closed end, a circular boss is arranged at the port of the open end, threads are arranged on the inner surface of the circular boss, and a sawtooth cutting angle is arranged on the end surface of the inner side of the circular boss; the circular boss of the connecting cylinder is in threaded connection with the rear end of the spray pipe; the gas sprayed out of the spray pipe forms a certain pressure in the inner cavity of the connecting cylinder, and the sawtooth cutting angle is broken.
Furthermore, the launching mechanism adopts a launching tail rod or a launching transmitter filled with propellant powder.
Furthermore, the actuating mechanism adopts an electric steering engine or a pulse engine or a damping sheet actuating mechanism.
Has the advantages that:
1. the invention adopts the straight spray pipe range-extending engine, the missile-borne control module and the actuating mechanism, has the controlled flight capability with the range of 5000m, improves the fire striking range from 300m to 5000m, realizes the accurate striking of a moving target and a static target by utilizing the communication coordination among the guidance component module, the missile-borne control module and the actuating mechanism, adopts the straight spray pipe range-extending engine, and completely uses the thrust to push a missile body to move forwards, thereby effectively improving the utilization efficiency of the thrust of the engine;
secondly, adopt the design scheme of launching mechanism and projectile body separation, effectively reduced the projectile body weight when the rocket projectile flies, be favorable to improving the range of rocket projectile.
2. The invention adopts the design scheme that the tail wing assembly and the engine spray pipe are integrated, thereby avoiding the pneumatic interference of the tail wing caused by the gas sprayed by the engine and saving the layout space of the rocket projectile.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of the flight condition of the present invention;
FIG. 3 is a schematic illustration of the structure of the tail assembly of the present invention;
FIG. 4 is an enlarged schematic view of the connection of the tail assembly to the firing tail of the present invention;
the system comprises a satellite guidance component module, a missile-borne control module, an electric steering engine, a warhead, a straight nozzle range-extending engine, a tail wing component 6, a launching tail rod 7, a nozzle 8, a tail wing 9 and a connecting cylinder 10, wherein the satellite guidance component module is 1, the missile-borne control module is 2, the electric steering engine is 3, the warhead is 4, the straight nozzle range-extending engine is 5, the tail wing component 6, the launching tail rod 7, the nozzle 8, the tail wing and the connecting cylinder 10 are 10.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The embodiment provides a rocket projectile for a 40-millimeter rocket tube based on a straight nozzle range-extending engine, the rocket projectile is used as a launching platform by using the 40-millimeter rocket tube, as shown in fig. 1, a satellite guidance component module 1 (comprising a satellite signal receiver and a fuse), a projectile loading control module 2, an electric steering engine 3, a warhead 4, a straight nozzle range-extending engine 5, a tail wing component 6 and a launching tail rod 7 are sequentially connected from head to tail to form the rocket projectile, and the tail wing component is installed on a nozzle of the straight nozzle range-extending engine 5. The missile-borne control module 2, the electric steering engine 3, the warhead 4, the straight jet pipe range-extending engine 5, the tail wing assembly 6 and the launching tail rod 7 are sequentially connected from head to tail to form a general range-extending controlled missile platform, and the head of the missile platform is butted with the guidance assembly through a general mechanical-electrical interface module to form a rocket missile.
Besides the satellite guidance component module 1, the guidance component can also adopt guidance components of guidance systems such as laser semi-active guidance, infrared semi-active guidance, television guidance, inertial guidance and the like.
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 loading control module 2. The satellite guidance assembly module 1 can also be replaced by a television guidance assembly, a laser semi-active guidance assembly, an inertial guidance assembly and an infrared guidance module.
The missile-borne control module 2 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 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 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 electric steering engine 3 comprises a rudder piece, a transmission mechanism, a motor and a driver, and receives a control instruction given by the projectile loading control module 2 to generate a control force and a control moment, so that the rocket projectile flies according to a preset trajectory by correcting the trajectory of the rocket projectile. The actuating mechanism adopted in the embodiment is an electric steering engine 3, and the actuating mechanism can also be replaced by a pulse engine or a damping sheet actuating mechanism.
The warhead 4 consists of a security mechanism, a detonating tube and a warhead body.
The straight nozzle range-extended engine 5 adopts a launching overload activation delay ignition mode to realize delay ignition; the straight jet pipe range-extending engine 5 continues to provide continuous thrust for flying rocket projectiles after the launching tail rod 7 is separated from the tail wing assembly 6, so that the projectile body is ensured to have the flying capacity of more than 5000 m. The diameter of the structural shell of the engine combustion chamber is larger than the caliber of a rocket tube, and the diameter of the spray pipe 8 is smaller than the caliber of the rocket tube. The spray pipe 8 is a tubular part, the front section of the inner cavity of the spray pipe 8 is a cylindrical cavity, the rear section of the inner cavity is horn-shaped, and the cylindrical cavity is used for guiding fuel gas generated when the straight spray pipe range-extended engine 5 works out to the nozzle part of the spray pipe 8; the rear section of the inner cavity is a nozzle 8 of a spray pipe and is used for spraying gas to generate thrust for propelling the rocket projectile to move. And external threads are arranged at two ends of the spray pipe 8, and the front end of the spray pipe 8 is connected with the shell of the straight spray pipe range-extended engine 5 through threads.
As shown in fig. 3, the tail assembly 6 includes a tail 9, a tail mount and a connecting barrel 10.
The empennage mounting seat is fixedly connected to the rear portion of the spray pipe 8, the empennage 9 is rotatably connected to the empennage mounting seat through a wing shaft and a torsion spring, and folding and automatic unfolding of fins of the empennage 9 can be achieved.
As shown in fig. 4, the connecting cylinder 10 is a connecting piece of the tail wing assembly 6 and the tail rod 7, the connecting cylinder 10 is a cylinder with one open end and one closed end, a circular boss is arranged at the port of the open end, threads are arranged on the inner surface of the circular boss and used for being connected with the spray pipe 8, a sawtooth cutting angle is arranged on the end surface of the inner side of the circular boss, and the sawtooth cutting angle is broken under certain pressure and is called as a shear key; the end face of the closed end of the connecting cylinder 10 is provided with a threaded column for connecting with the launching tail rod 7. The circular boss of the connecting cylinder 10 is in threaded connection with the rear end of the spray pipe 8;
before the straight nozzle extended-range engine 5 works in the rocket projectile service state and the launching state, the tail fin assembly 6 and the launching tail rod 7 are connected together through the connecting cylinder 10; when the straight spray pipe extended-range engine 5 works after rocket projectile is launched, propellant inside the straight spray pipe extended-range engine 5 burns to generate fuel gas, the fuel gas is sprayed out through a spray pipe 8 of an empennage assembly 6, the spray pipe 8 is connected with a connecting cylinder 10, the bottom end of the connecting cylinder 10 is sealed, the fuel gas forms high pressure in an inner cavity of the connecting cylinder 10, a shear key is damaged due to shearing force applied to the structure of the shear key under high pressure, the connecting cylinder 10 is broken and separated, the inner wall of the shear key is connected with the spray pipe 8 of the empennage assembly 6 through threads, the end face of the closed end of the connecting cylinder 10 is connected with a launching tail rod 7, when the shear key is separated from the connecting cylinder 10, the launching tail rod 7 is separated from the empennage assembly 6, and then the separation of the front part of a rocket projectile body and the launching tail rod 7 is realized.
The launching tail rod 7 is arranged at the tail part of the rocket projectile, consists of a tail rod and a propellant powder and is used for launching the rocket projectile. The tail rod is of a hollow cylindrical tubular structure, and the front end face is communicated with the rear end face. The outer wall of the front end of the tail rod is a threaded surface and is used for being connected with the connecting cylinder 10, and a plurality of round holes are formed in the wall surface of the tail rod and used for leading out fuel gas when propellant powder is combusted. The propellant powder is arranged inside the tubular structure of the tail rod. The launching mechanism can also adopt a launching engine to launch besides adopting a launching tail rod 7 filled with propellant powder.
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 shooting hand pulls a trigger to ignite the propellant powder on the shooting tail rod 7, the propellant powder pushes a rocket projectile to accelerate to a preset speed after being ignited, and the shooting overload generated in the process simultaneously activates a thermal battery on the projectile and a delay igniter of the straight nozzle range-extended engine 5; after the thermal battery is discharged from the blast hole for about 0.5s, the thermal battery works normally and stably; the straight-jet-pipe range-extended engine 5 is ignited at about 1s of the outlet of the gun and continuously provides thrust, and meanwhile, the tail rod 7 is separated from the front part of the projectile platform, as shown in fig. 2; 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 command is transmitted to the electric steering engine 3 to control the rocket projectile to fly along the planned trajectory until the rocket projectile hits the target.
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. The rocket projectile for the 40-millimeter rocket tube based on the straight nozzle extended range engine is characterized by comprising a guidance assembly, a projectile loading control module, an execution mechanism, a warhead, the straight nozzle extended range engine, a tail wing assembly and a launching mechanism;
the rocket projectile comprises a guidance assembly, a projectile loading control module, an actuating mechanism, a warhead, a straight jet pipe range-extended engine, a tail wing assembly and a launching mechanism which are sequentially connected from head to tail to form the rocket projectile, wherein the tail wing assembly is arranged on a jet pipe of the straight jet pipe range-extended engine;
the launching mechanism provides initial power for the rocket projectile, and after the straight jet pipe extended-range engine works, the generated fuel gas forms certain pressure to separate the launching mechanism from the empennage assembly, and the straight jet pipe extended-range engine continues to provide flight power for the rocket projectile; the guidance assembly is communicated with the missile-borne control module, the guidance information is transmitted to the missile-borne control module, the missile-borne control module is communicated with the executing mechanism, the generated track correction control instruction is sent to the executing mechanism, and the executing mechanism 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 straight-jet-pipe-extended-range-engine-based 40-mm rocket launcher for rocket launchers according to claim 1, wherein said tail assembly comprises a tail, a tail mount, and a connecting socket;
the tail wing mounting seat is fixedly connected to the rear part of the spray pipe, and the tail wing is rotatably mounted on the tail wing mounting seat; the connecting cylinder is a cylinder with one open end and one closed end, a circular boss is arranged at the port of the open end, threads are arranged on the inner surface of the circular boss, and a sawtooth cutting angle is arranged on the end surface of the inner side of the circular boss; the circular boss of the connecting cylinder is in threaded connection with the rear end of the spray pipe; the gas sprayed out of the spray pipe forms a certain pressure in the inner cavity of the connecting cylinder, and the sawtooth cutting angle is broken.
3. The straight-jet extended-range engine-based 40-mm rocket launcher for rocket launchers according to claim 1, wherein said launching mechanism employs a launching tail or a launching launcher containing propellant powder.
4. The rocket projectile for the 40 mm rocket tube based on the straight nozzle extended range engine as claimed in claim 1, wherein the actuator is an electric steering engine or a pulse engine or a damping fin actuator.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2020207223800 | 2020-05-06 | ||
| CN2020103730247 | 2020-05-06 | ||
| CN202010373024 | 2020-05-06 | ||
| CN202020722380 | 2020-05-06 |
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| Publication Number | Publication Date |
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| CN113624075A true CN113624075A (en) | 2021-11-09 |
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| CN202011590495.XA Pending CN113624075A (en) | 2020-05-06 | 2020-12-29 | Rocket projectile for 40 mm rocket tube based on straight nozzle extended-range engine |
| CN202023238079.1U Active CN214620888U (en) | 2020-05-06 | 2020-12-29 | Rocket projectile for 40 mm rocket tube based on straight nozzle extended-range engine |
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| CN202023238079.1U Active CN214620888U (en) | 2020-05-06 | 2020-12-29 | Rocket projectile for 40 mm rocket tube based on straight nozzle extended-range engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114370791A (en) * | 2021-12-30 | 2022-04-19 | 北京理工大学 | Rocket projectile launching control system and method based on inductive communication |
| RU2785835C1 (en) * | 2022-02-11 | 2022-12-14 | Лев Алексеевич Розанов | Method for increasing the flight range of an artillery projectile with a rocket-ramjet engine and an artillery projectile implementing it (options) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115164646B (en) * | 2022-06-28 | 2023-09-15 | 中国人民解放军63863部队 | Method and device for calculating basic data of table of composite guided projectile |
-
2020
- 2020-12-29 CN CN202011590495.XA patent/CN113624075A/en active Pending
- 2020-12-29 CN CN202023238079.1U patent/CN214620888U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114370791A (en) * | 2021-12-30 | 2022-04-19 | 北京理工大学 | Rocket projectile launching control system and method based on inductive communication |
| CN114370791B (en) * | 2021-12-30 | 2023-01-17 | 北京理工大学 | Rocket projectile launching control system and method based on inductive communication |
| RU2785835C1 (en) * | 2022-02-11 | 2022-12-14 | Лев Алексеевич Розанов | Method for increasing the flight range of an artillery projectile with a rocket-ramjet engine and an artillery projectile implementing it (options) |
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| Publication number | Publication date |
|---|---|
| CN214620888U (en) | 2021-11-05 |
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