CN109579615B - Individual rocket launching system capable of being used in limited space - Google Patents
Individual rocket launching system capable of being used in limited space Download PDFInfo
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- CN109579615B CN109579615B CN201811565366.8A CN201811565366A CN109579615B CN 109579615 B CN109579615 B CN 109579615B CN 201811565366 A CN201811565366 A CN 201811565366A CN 109579615 B CN109579615 B CN 109579615B
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- Prior art keywords
- rocket
- engine
- special
- fixing plate
- spray pipe
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 30
- 239000007921 spray Substances 0.000 claims abstract description 30
- 239000007787 solid Substances 0.000 claims abstract description 27
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 9
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 9
- 239000003292 glue Substances 0.000 claims abstract description 4
- 230000030279 gene silencing Effects 0.000 claims description 30
- 239000011229 interlayer Substances 0.000 claims description 12
- 230000003584 silencer Effects 0.000 claims description 9
- 239000004449 solid propellant Substances 0.000 claims description 3
- 238000010008 shearing Methods 0.000 claims description 2
- 235000017166 Bambusa arundinacea Nutrition 0.000 claims 2
- 235000017491 Bambusa tulda Nutrition 0.000 claims 2
- 241001330002 Bambuseae Species 0.000 claims 2
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims 2
- 239000011425 bamboo Substances 0.000 claims 2
- 239000002737 fuel gas Substances 0.000 description 19
- 239000011148 porous material Substances 0.000 description 8
- 239000007789 gas Substances 0.000 description 7
- 239000002360 explosive Substances 0.000 description 6
- 239000000843 powder Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 238000002156 mixing Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000002159 abnormal effect Effects 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000013016 damping Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- 239000000779 smoke Substances 0.000 description 2
- 206010066054 Dysmorphism Diseases 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 235000019994 cava Nutrition 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to the technical field of antitank weapons, in particular to an individual rocket launching system. An individual rocket launching system capable of being used in a limited space is provided, which adopts the technical scheme that: the rocket engine combustion chamber comprises: the device comprises an engine shell, a tubular solid charge, a charge fixing plate, a special-shaped spray pipe and an integral igniter blanking cover structure; the surface of the charge fixing plate is provided with vent holes matched with the tubular solid charge, and the edge of the charge fixing plate is provided with an air passing groove structure; the special-shaped spray pipe comprises: a circular convergent section, a throat and a binary divergent section; the utility model provides an integral type stopper structure of some firearm includes: ignition cartridge and aluminum blanking cover; the integral igniter blanking cover structure is arranged at the throat of the special-shaped spray pipe; the rocket bomb part is connected with the front end socket of the engine, the front end socket of the engine is connected with the engine shell through a shear pin, and the charging fixing plate is in glue connection with the front end socket of the engine and the tubular solid charging; the special-shaped spray pipe is fixedly arranged in the tail part of the engine shell. The invention ensures the safety of the shooter and the transmitting concealment.
Description
Technical Field
The invention relates to the technical field of antitank weapons, in particular to an individual rocket launching system.
Background
In a complex battlefield environment, in order to complete various striking tasks, the portable individual rocket should have good battlefield environmental adaptability and have the ability of shooting in a narrow space and in a house. With the development of weapon equipment technology, many countries in the world have raised requirements for the ability of portable antitank weapons to shoot in streets, alleys, houses, caves, field operations with roof, and other narrow works.
When an individual rocket provided with launching power by adopting a recoilless gun is launched in a limited space, high-pressure fuel gas generated by the gun pushes the rocket out of a muzzle, and a large amount of fuel gas is discharged from a tail nozzle, so that generated noise, harmful fuel gas and tail flame can possibly cause different degrees of damage to a shooter.
Disclosure of Invention
The purpose of the invention is that: in order to reduce strong noise, overpressure and tail flame during launching, the invention provides an individual rocket launching system based on the working principle of a solid rocket engine.
The technical scheme of the invention is as follows: an individual rocket launching system usable in confined spaces, comprising: rocket barrels, rocket warheads, and rocket engine combustion chambers;
the rocket engine combustion chamber comprises: the device comprises an engine shell, a tubular solid charge, a charge fixing plate, a special-shaped spray pipe and an integral igniter blanking cover structure; the tubular solid charge adopts a thin-wall porous solid propellant grain with low smoke and high burning speed; the surface of the charging fixing plate is provided with vent holes matched with the tubular solid charging, the edge of the charging fixing plate is provided with an air passing groove structure, and the charging fixing plate has air pressure balancing capability; the special-shaped spray pipe comprises: a circular convergent section, a throat and a binary divergent section; the utility model provides an integral type stopper structure of some firearm includes: ignition cartridge and aluminum blanking cover; the integral igniter blanking cover structure is arranged at the throat of the special-shaped spray pipe;
the rocket bomb part and the rocket engine combustion chamber are arranged in the rocket launcher, the rocket bomb part is connected with the engine front end socket through threads, the engine front end socket is connected with the engine shell through a shear pin, and the charge fixing plate is in glue connection with the engine front end socket and the tubular solid charge; the special-shaped spray pipe is fixedly arranged in the engine shell.
The working principle is as follows: the ignition powder box in the integral igniter plug structure is activated to ignite the ignition powder, high-temperature fuel gas generated by the ignition powder quickly ignites the tubular solid charge, when the combustion chamber of the rocket engine reaches the set ignition pressure, the aluminum plug can be quickly opened, the prefabricated weak ring specially designed for the aluminum plug can realize high sensitivity to the opening pressure threshold, the accurate control of pressure and time is realized, the peak value and delay of the initial ignition pressure are reduced, and then noise and overpressure are reduced; the explosive loading fixing plate adopts a vent hole and edge gas passing groove structure matched with the tubular solid explosive loading to quickly balance the pressure in the combustion chamber, reduce the pressure peak value, prevent the abnormal work caused by the instantaneous unbalance of the pressure in the rocket combustion chamber, and further reduce noise and overpressure; the high-temperature fuel gas passes through the circular convergent section and the binary expansion section of the special-shaped spray pipe, so that the fuel gas is expanded to an over-expansion or complete expansion state, and the noise of the fuel gas is reduced.
Furthermore, on the basis of the scheme, the tail part of the rocket tube is also provided with a silencing sleeve; the sound damping sleeve includes: a muffler shell, a silencing interlayer in the cylinder and a micro-pore plate silencing structure; wherein: the silencer shell is arranged at the tail part of the rocket tube, the in-tube silencing interlayer is adhered to the inner wall of the silencer shell, the micro-pore plate silencing structure is arranged in the in-tube silencing interlayer and positioned through a built-in clamping groove of the silencer shell, and the micro-pore plate silencing structure is provided with a built-in gas channel.
When high-speed fuel gas passes through the fuel gas channel of the micropore plate silencing structure in the silencing sleeve, the gas in the micropore makes the sound wave and the micropore wall surface mutually rub under the action of sound pressure, and part of sound energy is converted into heat energy, so that the aim of noise attenuation is fulfilled. The noise-reducing interlayer in the rocket barrel absorbs part of noise in the rocket barrel in the process of launching the rocket warhead, thereby achieving the purpose of reducing noise.
Furthermore, on the basis of the scheme, the binary expansion section of the special-shaped spray pipe is provided with an inclined guide rib structure. The inclined guide rib structure can enable the high-speed fuel gas wake to rotate, turbulent mixing is enhanced through the cyclone effect, jet energy is dissipated, and tail flame length and noise are reduced.
Furthermore, on the basis of the scheme, a sawtooth silencing structure is arranged at the outlet eave of the binary expansion section of the special-shaped spray pipe. The sawtooth silencing structure further enhances turbulent injection effect, changes the mixing characteristic of engine tail flame, and reduces the tail flame length and noise.
Furthermore, on the basis of the scheme, the inner diameter of the throat is matched with the size of the combustion surface of the tubular solid charge. The large jet pipe diameter is used under the condition of large fuel surface flow, so that the high thrust requirement of the engine under low pressure can be realized, and the occurrence of overpressure is prevented.
The beneficial effects are that: the invention can realize the low-noise and low-overpressure launching of the individual rocket in a limited space, and ensures the safety and the launching concealment of the shooter.
(1) Through integral type some firearm blanking cover structural design, when realizing that the combustion chamber is sealed, when the inside pressure of combustion chamber reached the pressure threshold value of settlement, aluminium system blanking cover can accurate response, open fast, reduces initial ignition pressure peak value, and then noise and superpressure reduction.
(2) The explosive loading fixing plate adopts a vent hole and edge shearing groove structure matched with the tubular solid explosive loading, so that the pressure in the combustion chamber is balanced, the pressure peak value is reduced, the abnormal work caused by the instantaneous unbalance of the pressure in the combustion chamber is prevented, and the noise and the overpressure are further reduced.
(3) The diameter of the pipe-shaped solid charge combustion face is matched with that of the jet throat, and the large jet pipe diameter is used under the condition of large combustion face flow, so that the requirement of large thrust under low pressure of the combustion chamber can be met, and overpressure is prevented.
(4) The structural design of the circular convergent section and the binary divergent section of the special-shaped spray pipe ensures that the gas is expanded to an overstretched or fully expanded state, and the gas noise is reduced.
(5) Circular convergent section, binary expansion section and the interior sawtooth amortization structure of spray tube export eaves of dysmorphism spray tube strengthen turbulent injection effect, change combustion chamber tail flame blending characteristic, reduce tail flame length, reduce flame temperature, reduce the superpressure, reduce noise.
(6) The inclined guide rib structure of the special-shaped spray pipe expansion section can cause the tail flame of the combustion chamber to swirl, reduce the flame temperature, avoid overpressure and reduce noise.
(7) The silencing sleeve is arranged at the tail of the rocket tube, high-speed fuel gas is silenced through the micro-pore plates in the silencing sleeve in the launching process, and the silencing interlayer in the rocket tube absorbs part of noise in the launching process at the same time, so that the purpose of noise reduction is achieved.
Drawings
FIG. 1 is a schematic structural diagram of embodiment 1 of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
FIG. 3 is a partial enlarged view at B in FIG. 1;
FIG. 4 is a schematic view of the structure of a charge holder plate according to the present invention;
FIG. 5 is a schematic structural diagram of embodiment 2 of the present invention;
FIG. 6 is an enlarged view of a portion of FIG. 5 at A;
FIG. 7 is a partial enlarged view at B in FIG. 5;
in the figure: 1-a silencing sleeve and 2-a tubular solid charge; 3-special-shaped spray pipes; 4-muffler shell, 5-in-cylinder silencing interlayer, 6-micropore plate silencing structure, 7-integral igniter plugging structure, 8-rocket tube, 9-rocket warhead, 10-rocket engine combustion chamber, 11-engine front end enclosure, 12-charge fixing plate, 13-shear pin and 14-engine shell.
Detailed Description
Example 1, see fig. 1, an individual rocket launching system for use in confined spaces, comprising: rocket launcher 8, rocket warhead 9, and rocket engine combustion chamber 10;
referring to fig. 2, 3, and 4, rocket engine combustion chamber 10 includes: the engine shell 14, the tubular solid charge 2, the charge fixing plate 12, the special-shaped spray pipe 3 and the integral igniter blanking cover structure 7; the tubular solid charge 2 adopts a thin-wall porous solid propellant grain with low smoke and high burning speed; the surface of the charge fixing plate 12 is provided with vent holes matched with the tubular solid charge 2, the edge of the charge fixing plate 12 is provided with an air passing groove structure, and the charge fixing plate 12 has air pressure balancing capability; the special-shaped spray pipe 3 comprises: a circular convergent section, a throat and a binary divergent section; the integral igniter blanking cover structure 7 includes: ignition cartridge and aluminum blanking cover; the integral igniter blanking cover structure 7 is arranged at the throat of the special-shaped spray pipe 3; the inner diameter of the spray throat is matched with the size of the combustion surface of the tubular solid charge 2;
the rocket bomb part 9 and the rocket engine combustion chamber 10 are arranged in the rocket launcher 8, the rocket bomb part 9 is connected with the engine front end cover 11 through threads, the engine front end cover 11 is connected with the engine shell 14 through a shear pin 13, and the charge fixing plate 12 is in glue connection with the engine front end cover 11 and the tubular solid charge 2; the profiled nozzle 3 is fixedly mounted in the engine housing 14.
The working principle is as follows: the ignition powder box in the integral igniter plug structure 7 is activated to ignite the ignition powder, high-temperature fuel gas generated by the ignition powder quickly ignites the tubular solid charge 2, when the set ignition pressure in the rocket engine combustion chamber 10 is reached, the aluminum plug can be quickly opened, the prefabricated weak ring specially designed for the aluminum plug can realize high sensitivity to the opening pressure threshold, the accurate control of pressure and time is realized, the initial ignition pressure peak value and delay are reduced, and then noise and overpressure are reduced; the explosive loading fixing plate 12 adopts a vent hole and edge gas passing groove structure matched with the tubular solid explosive loading 2 to quickly balance the pressure in the combustion chamber, reduce the pressure peak value, prevent the abnormal work caused by the instantaneous unbalance of the pressure in the rocket combustion chamber, and further reduce noise and overpressure; the high-temperature fuel gas passes through the circular convergent section and the binary expansion section of the special-shaped spray pipe 3, so that the fuel gas is expanded to an over-expansion or full-expansion state, and the fuel gas noise is reduced; the inner diameter of the spray throat is matched with the size of the combustion surface of the tubular solid charge 2. The large jet pipe diameter is used under the condition of large fuel surface flow, so that the high thrust requirement of the engine under low pressure can be realized, and the occurrence of overpressure is prevented.
In the embodiment 2, referring to fig. 5, 6 and 7, on the basis of the embodiment 1, a silencing sleeve 1 is further arranged at the tail part of the rocket tube 8; the sound damping sleeve 1 includes: a muffler housing 4, an in-cylinder sound deadening partition 5, and a microplate sound deadening structure 6; wherein: the silencer shell 4 is arranged at the tail part of the rocket tube 8, the in-tube silencing interlayer 5 is adhered to the inner wall of the silencer shell 4, the micro-pore plate silencing structure 6 is arranged in the in-tube silencing interlayer 5 and positioned through a built-in clamping groove of the silencer shell 4, and the micro-pore plate silencing structure 6 is provided with a built-in fuel gas channel.
Further, the binary expansion section of the special-shaped spray pipe 3 is provided with an inclined guide rib structure; the outlet eave of the binary expansion section of the special-shaped spray pipe 3 is provided with a sawtooth silencing structure.
The inclined flow guide rib structure of the special-shaped spray pipe 3 can enable the high-speed fuel gas wake to rotate, turbulent mixing is enhanced through a cyclone effect, jet energy is dissipated, tail flame length and noise are reduced, the sawtooth silencing structure further enhances a turbulent injection effect, the tail flame mixing characteristic of an engine is changed, and tail flame length and noise are reduced; when high-speed fuel gas passes through the fuel gas channel of the micro-pore plate silencing structure 6 in the silencing sleeve 1, the gas in the small holes makes the sound wave and the micro-pore wall surface rub with each other under the action of sound pressure, and part of sound energy is converted into heat energy, so that the aim of noise attenuation is achieved. The noise-reducing interlayer in the rocket tube absorbs part of noise in the rocket tube 8 in the process of launching the rocket warhead 9, thereby achieving the purpose of reducing noise. The scheme ensures that the single rocket can realize low-noise and low-overpressure launching in a limited space, thereby ensuring the safety of a shooter and the launching concealment.
While the invention has been described in detail in the foregoing general description and specific examples, it will be apparent to those skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications or improvements may be made without departing from the spirit of the invention and are intended to be within the scope of the invention as claimed.
Claims (5)
1. An individual rocket launch system usable in a confined space comprising: rocket launcher (8), rocket warhead (9) and rocket engine combustion chamber (10), its characterized in that:
the rocket engine combustion chamber (10) comprises: the device comprises an engine shell (14), a tubular solid charge (2), a charge fixing plate (12), a special-shaped spray pipe (3) and an integral igniter blanking cover structure (7); the tubular solid charge (2) adopts a thin-wall porous solid propellant grain; the surface of the charging fixing plate (12) is provided with vent holes matched with the tubular solid charging (2), the edge of the charging fixing plate (12) is provided with an air passing groove structure, and the charging fixing plate (12) has air pressure balancing capability; the profiled nozzle (3) comprises: a circular convergent section, a throat and a binary divergent section; the integral igniter blanking cover structure (7) comprises: ignition cartridge and aluminum blanking cover; the integral igniter blanking cover structure (7) is arranged at the throat of the special-shaped spray pipe (3);
the rocket bomb part (9) and the rocket engine combustion chamber (10) are arranged in the rocket barrel (8), the rocket bomb part (9) is connected with an engine front end socket (11) through threads, the engine front end socket (11) is connected with the engine shell (14) through a shearing pin (13), and the charge fixing plate (12) is in glue connection with the engine front end socket (11) and the tubular solid charge (2); the special-shaped spray pipe (3) is fixedly arranged in the tail part of the engine shell (14).
2. An individual rocket launch system usable in confined spaces as recited in claim 1 wherein: the tail part of the rocket tube (8) is also provided with a silencing sleeve (1); the sound-deadening sleeve (1) includes: a muffler shell (4), a silencing interlayer (5) in the cylinder and a micropore plate silencing structure (6); wherein: the silencer casing (4) is installed the afterbody of rocket tube (8), section of thick bamboo amortization interlayer (5) bond in silencer casing (4) inner wall, micropore board amortization structure (6) are installed section of thick bamboo amortization interlayer (5) are interior and are passed through the built-in draw-in groove of silencer casing (4) is fixed a position, micropore board amortization structure (6) are equipped with built-in gas passageway.
3. An individual rocket launch system usable in confined spaces as claimed in claim 1 or 2 wherein: the binary expansion section of the special-shaped spray pipe (3) is provided with an inclined guide rib structure.
4. An individual rocket launch system usable in confined spaces as claimed in claim 1 or 2 wherein: and a sawtooth silencing structure is arranged at the outlet tail eave of the binary expansion section of the special-shaped spray pipe (3).
5. An individual rocket launch system usable in confined spaces as claimed in claim 1 or 2 wherein: the inner diameter of the throat is matched with the size of the combustion surface of the tubular solid charge (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811565366.8A CN109579615B (en) | 2018-12-20 | 2018-12-20 | Individual rocket launching system capable of being used in limited space |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811565366.8A CN109579615B (en) | 2018-12-20 | 2018-12-20 | Individual rocket launching system capable of being used in limited space |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109579615A CN109579615A (en) | 2019-04-05 |
| CN109579615B true CN109579615B (en) | 2024-01-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811565366.8A Active CN109579615B (en) | 2018-12-20 | 2018-12-20 | Individual rocket launching system capable of being used in limited space |
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| Country | Link |
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| CN (1) | CN109579615B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112431690B (en) * | 2020-10-26 | 2022-04-01 | 北京机械设备研究所 | Embedded thrust adjusting solid engine |
| CN114636349B (en) * | 2020-12-16 | 2025-06-24 | 北京恒星箭翔科技有限公司 | A high-elevation-angle launch protection device for a 40mm rocket launcher |
| CN115972310B (en) * | 2022-12-05 | 2025-04-22 | 中国科学院沈阳自动化研究所 | A high pressure gas cover opening device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0056789A2 (en) * | 1981-01-20 | 1982-07-28 | FIDES TREUHAND GmbH | Recoilless missile system |
| CN101363699A (en) * | 2007-08-06 | 2009-02-11 | 孙再庸 | Spinning stability fire-fighting rocket bomb, launching set thereof and system |
| CN201569371U (en) * | 2009-12-24 | 2010-09-01 | 中国船舶重工集团公司第七一○研究所 | Rocket bomb used for forest fire extinction |
| CN201997023U (en) * | 2010-12-28 | 2011-10-05 | 国营第一○四厂 | Shoulder-fired forest fire-extinguishing bomb |
| US8545646B1 (en) * | 2005-06-10 | 2013-10-01 | The United States Of America As Represented By The Secretary Of The Navy | High-density rocket propellant |
| SE1600349A1 (en) * | 2016-12-21 | 2018-06-22 | Saab Ab | Multi-stage launcher |
| CN207886550U (en) * | 2018-01-25 | 2018-09-21 | 安徽东风机电科技股份有限公司 | A kind of fire extinguisher bomb power and stabilising arrangement |
| CN209524811U (en) * | 2018-12-20 | 2019-10-22 | 北京恒星箭翔科技有限公司 | It is a kind of can be in the individual rocket emission system that the confined space uses |
-
2018
- 2018-12-20 CN CN201811565366.8A patent/CN109579615B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0056789A2 (en) * | 1981-01-20 | 1982-07-28 | FIDES TREUHAND GmbH | Recoilless missile system |
| US8545646B1 (en) * | 2005-06-10 | 2013-10-01 | The United States Of America As Represented By The Secretary Of The Navy | High-density rocket propellant |
| CN101363699A (en) * | 2007-08-06 | 2009-02-11 | 孙再庸 | Spinning stability fire-fighting rocket bomb, launching set thereof and system |
| CN201569371U (en) * | 2009-12-24 | 2010-09-01 | 中国船舶重工集团公司第七一○研究所 | Rocket bomb used for forest fire extinction |
| CN201997023U (en) * | 2010-12-28 | 2011-10-05 | 国营第一○四厂 | Shoulder-fired forest fire-extinguishing bomb |
| SE1600349A1 (en) * | 2016-12-21 | 2018-06-22 | Saab Ab | Multi-stage launcher |
| CN207886550U (en) * | 2018-01-25 | 2018-09-21 | 安徽东风机电科技股份有限公司 | A kind of fire extinguisher bomb power and stabilising arrangement |
| CN209524811U (en) * | 2018-12-20 | 2019-10-22 | 北京恒星箭翔科技有限公司 | It is a kind of can be in the individual rocket emission system that the confined space uses |
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| Publication number | Publication date |
|---|---|
| CN109579615A (en) | 2019-04-05 |
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