CN110108161B - Missile launching device - Google Patents
Missile launching device Download PDFInfo
- Publication number
- CN110108161B CN110108161B CN201910393872.1A CN201910393872A CN110108161B CN 110108161 B CN110108161 B CN 110108161B CN 201910393872 A CN201910393872 A CN 201910393872A CN 110108161 B CN110108161 B CN 110108161B
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- China
- Prior art keywords
- launcher
- support
- machine assembly
- supporting part
- launching
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Classifications
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- 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
- F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G5/00—Elevating or traversing control systems for guns
- F41G5/06—Elevating or traversing control systems for guns using electric means for remote control
Abstract
The invention provides a missile launching device, which comprises a fixed supporting part and a movable supporting part, wherein the fixed supporting part and the movable supporting part are detachably connected through an adjusting mechanism; the adjusting mechanism comprises an azimuth machine assembly and/or a height machine assembly; the movable supporting part comprises a pitching support, the pitching support comprises a mounting frame and a launcher support, and one or more launcher supports are arranged on the mounting frame; the launching frame support is connected with a launching frame support body, and one or more cartridge projectiles are mounted on the launching frame support body. The missile launcher provided by the invention can be rapidly disassembled into an electric control box, a combination of a direction machine assembly and a high-low machine assembly, a tripod and a pitching support, and is convenient to carry manually.
Description
Technical Field
The invention relates to the technical field of missile launching, in particular to a missile launching device, and particularly relates to a portable missile launching device capable of realizing double-launching and simultaneous launching.
Background
Tactical missile (tactical missile): a missile for destroying tactical targets. The range of the missile is usually within 1000 kilometers, and the missile belongs to a short-range missile. The device is mainly used for attacking targets such as nuclear attack weapons, aggregated troops, tanks, airplanes, ships, radars, command posts, airports, ports, railway hubs and bridges in the battle tactical depth of enemies. After the 50 s of the 20 th century, conventional tactical missiles were used in large numbers in many local wars and became one of the important weapons in modern wars.
Tactical missiles include portable individual missiles and vehicle-mounted missiles, which are usually provided with launching devices, but the launching devices in the prior art mainly have the following problems: firstly, the assembly or disassembly cannot be conveniently carried out; secondly, a launching device which can be carried by a single soldier and can launch a plurality of missiles simultaneously is lacked; and thirdly, a stable mounting and adjusting platform of the aiming guide device cannot be provided.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a missile launching device.
The missile launching device provided by the invention comprises a fixed supporting part and a movable supporting part, wherein the fixed supporting part and the movable supporting part are detachably connected through an adjusting mechanism; the adjusting mechanism comprises an azimuth machine assembly and/or a height machine assembly;
the movable supporting part comprises a pitching support, the pitching support comprises a mounting frame and a launcher support, and one or more launcher supports are arranged on the mounting frame; the launching frame support is connected with a launching frame support body, and one or more cartridge projectiles are mounted on the launching frame support body.
Preferably, the fixed support comprises a tripod, and the adjustment mechanism further comprises an electrical control box;
the tripod, the electrical control box, the azimuth machine assembly, the height machine assembly, the pitching support, the mounting rack and the launching rack support are connected in sequence.
Preferably, the tripod is detachably connected with the electric control box through a hoop; the electric control box is connected with the azimuth machine assembly through a set first screw; the azimuth machine assembly is connected with the elevation machine assembly through a second screw; the high-low machine assembly is connected with the pitching support through a third screw.
Preferably, the plurality of launcher frames comprise a first launcher frame and a second launcher frame;
the first launcher support and the second launcher support are symmetrically arranged on two sides of the mounting rack.
Preferably, a pressing beam is arranged on the launcher body; one end of the two ends of the pressing beam in the length extending direction is arranged on the body of the launching frame through a hinge;
the pressing beam rotates around the hinge and can be switched between an opening state and a closing state;
the launcher frame body is provided with a containing hole, and in the closed state, the pressing beam limits the cartridge bomb in the containing hole.
Preferably, under the closed state, the other end of the launcher frame body along the length extension direction is connected with the launcher frame body through a buckle.
Preferably, a launch control system and a guide device are arranged on the pitching support;
the directing device comprises an infrared detection device.
Preferably, the plurality of cartridge bullets are symmetrically arranged at two radial sides of the infrared detection device;
the two side tube bullets are arranged in an eight-out arrangement on the horizontal plane projection; when a plurality of cartridges exist on one side, the mounting heights of the plurality of cartridges are sequentially lowered in the direction from the inside to the outside.
Preferably, in a rectangular spatial coordinate system, in an XOZ plane, an optical axis of the infrared detection device is inclined downwards by an angle α, and a cylinder axis of the cylinder bomb is horizontal;
in the XOY plane, an optical axis of the infrared detection device and a cylinder axis of the cylinder bullet form an angle beta;
in the YOZ plane, the connecting line of the centers of the cartridge bombs on the two sides forms a gamma angle with a vertical axis passing through the center of the infrared detection device.
Preferably, the optical axis of the cartridge is parallel to the optical axis of the infrared detection device.
Compared with the prior art, the invention has the following beneficial effects:
1. the foot stool type portable missile launcher provided by the invention can be rapidly disassembled into an electric control box, a combination of a position machine assembly and a high-low machine assembly, a tripod and a pitching support, and is convenient to carry manually.
2. Through the design of the 'eight outside' type of the launching cradle, the barrel-loading bullets on the left side and the right side of the bracket of the launching cradle are led in the initial prepositive quantity (one is positive and the other is negative) in the direction, and the missiles attack targets according to different flight tracks after being discharged from the barrels, so that the weapon system has the double-firing and uniform-firing capability.
3. The invention is suitable for the guided missile with a preset angle and ensures that the optical axis of the guiding device is parallel to the optical axis of the barrel missile.
4. The arrangement of the azimuth machine assembly and the elevation machine assembly is beneficial to adjusting the angle and the height of the missile aiming at the target position.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is an integral component of a launcher;
FIG. 2 is a schematic view of the attachment of the tripod to the electrical control box;
FIG. 3 is a schematic view of the connection between the electrical control box and the azimuth machine assembly;
FIG. 4 is a schematic view of the connection between the azimuth axis assembly and the elevation axis assembly;
FIG. 5 is a schematic view of the connection between the elevating and lowering mechanism and the pitching mounting;
FIG. 6 is a schematic view of a pitch support assembly;
FIG. 7 is a schematic view of the cartridge being mounted on left and right launchers;
FIG. 8 is a schematic diagram of an included angle between a barrel axis of the barrel bullet and an optical axis of the infrared detection device in an XOZ plane;
FIG. 9 is a schematic diagram of an included angle between the installation position of the cartridge and the position of the infrared detection device in the YOZ plane;
fig. 10 is a schematic diagram of the angle between the tube axis of the tube bomb and the optical axis of the infrared detection device in the XOY plane.
The figures show that:
second screw 11 of tripod 1
Hoop 2 third screw 12
First launcher support 13 of electrical control box 3
High-low machine assembly 5 second launcher support 15
Cartridge 6 hinge 16
Pitching support 7 pressure beam 17
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
As shown in FIG. 1, the missile launching device provided by the invention comprises a fixed supporting part and a movable supporting part, wherein the fixed supporting part and the movable supporting part are detachably connected through an adjusting mechanism; the adjusting mechanism comprises a square computer assembly 4 and/or a high-low machine assembly 5; the movable supporting part comprises a pitching support 7, the pitching support 7 comprises a mounting frame 14 and a launcher support, and one or more launcher supports are arranged on the mounting frame 14; the launcher support is connected with a launcher support body 19, and one or more cartridge projectiles 6 are mounted on the launcher support body 19. In an embodiment, the fixed support comprises a tripod 1, and the adjustment mechanism further comprises an electrical control box 3; the tripod 1, the electric control box 3, the azimuth machine assembly 4, the height machine assembly 5, the pitching support 7, the mounting frame 14 and the launcher support are connected in sequence. The tripod 1 is detachably connected with the electric control box 3 through an anchor ear 2; the electrical control box 3 is connected with the azimuth machine assembly 4 through a first screw 10; the azimuth machine assembly 4 is connected with the high-low machine assembly 5 through a second screw 11; the elevating machine assembly 5 is connected with the pitching support 7 through a third screw 12.
Specifically, as shown in fig. 2 to 5, the electrical control box is fixedly connected with a tripod 1 through an anchor ear 2; the electric control box 3 is fixedly connected with the azimuth machine assembly 4 through screws; the azimuth machine assembly 4 is fixedly connected with the high-low machine assembly 5 through screws; the pitching support 7 is fixedly connected with the high-low machine assembly 5 through a screw; the emission control and infrared detection device 9 is fixedly connected with the pitching support 7 through a screw. The hoop 2 is provided with a handle which can be loosened and pressed, so that the tripod 1 and the electric control box 3 can be quickly disassembled and assembled; the screw connection between the pitching support 7 and the high-low machine assembly 5 is convenient to disassemble and assemble, and the disassembly and the assembly between the pitching support and the high-low machine assembly can be realized.
The tripod 1 is supported on the ground and plays a bearing role for other components of the launcher; the electric control box 3 is internally provided with electric elements such as a follow-up control unit, a relay and the like; the azimuth motor is arranged in the azimuth machine assembly 4 and can drive the elevation machine assembly 5 and the pitching support 7 to carry out azimuth turning; a high-low motor is arranged in the high-low machine assembly 5 and can drive the pitching support 7 to pitch and rotate; the pitching support 7 can be provided with multiple missiles. The tripod 1 plays a supporting role, the azimuth machine assembly 4 plays a role in azimuth turning, the height machine assembly 5 plays a role in elevation turning, and the cartridge bomb 6 is installed on the pitching support 7.
As shown in fig. 6, the plurality of launcher frames include a first launcher frame 13 frame and a second launcher frame 15 frame; the first launcher 13 bracket and the second launcher 15 bracket are symmetrically arranged on two sides of the mounting bracket 14. As shown in fig. 7, a pressing beam 17 is arranged on the launcher frame body 19; one of two ends of the pressing beam 17 in the length extension direction is mounted on the launcher frame body 19 through a hinge 16; the pressing beam 17 can be switched between the open state and the closed state by rotating around the hinge 16; the launcher frame 19 is provided with a receiving hole, and in the closed state, the cartridge 6 is limited in the receiving hole by the pressing beam 17. Preferably, in the closed state, the other end of the launcher frame 19 in the length extending direction is connected with the launcher frame 19 by the arranged buckle 18. And a launch control system 8 and a guide device are arranged on the pitching support 7.
In an embodiment, the guiding device comprises an infrared detection device 9, the infrared detection device 9 being used for identifying and tracking the target. As shown in fig. 8 to 10, the plurality of cartridges 6 are symmetrically arranged on both sides in the radial direction of the infrared detection device 9; the cylindrical bullets 6 at the two sides are arranged in an eight-out shape on the horizontal plane projection; when a plurality of cartridges 6 exist on one side, the mounting heights of the plurality of cartridges 6 are sequentially lowered in the direction from the inside to the outside. In a space rectangular coordinate system, in an XOZ plane, the optical axis of the infrared detection device 9 inclines downwards by an angle alpha, and the cylinder axis of the cylinder bullet 6 is horizontal; in the XOY plane, the optical axis of the infrared detection device 9 and the cylinder axis of the cylinder bullet 6 form an angle beta; in the YOZ plane, the central connecting line of the cylindrical bullets 6 at the two sides forms a gamma angle with a vertical axis passing through the center of the infrared detection device 9; the photoelectric axis mounted on the pitching support 7 is made parallel to the optical axis of the cartridge 6 by the angle combination on the pitching support 7.
In a preferred embodiment, in the rectangular spatial coordinate system, in the XOZ plane, the optical axis of the infrared detection device 9 is inclined downward by 5 degrees, the cylinder axis of the cylinder bullet 6 is horizontal, and in the XOY plane, the optical axis of the infrared detection device 9 forms an included angle of 5 degrees with the cylinder axis of the cylinder bullet 6; in the YOZ plane, the central connecting line of the tube bullets 6 at the two sides forms an included angle of 45 degrees with the vertical axis passing through the center of the infrared detection device 9. Thus, the included angle of 7 degrees is formed between the cylinder shaft of the cylinder bullet 6 and the optical axis of the infrared detection device 9, and the optical axis of the cylinder bullet 6 is parallel to the optical axis of the infrared detection device 9.
The realization of the double-emission simultaneous emission function: through the design of the 'eight outside' type of the launching cradle, the barrel-loading bullets on the left side and the right side of the bracket of the launching cradle are led in the initial prepositive quantity (one is positive and the other is negative) in the direction, and the missiles attack targets according to different flight tracks after being discharged from the barrels, so that the weapon system has the double-firing and uniform-firing capability. In conclusion, the foot stool type portable missile launcher provided by the invention can be rapidly disassembled into an electric control box, a combination of a direction machine assembly and a high-low machine assembly, a tripod and a pitching support, and each part can be carried by manpower. The dual-firing simultaneous firing device is suitable for missiles with preset angles and achieves dual-firing simultaneous firing.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (5)
1. A missile launching device is characterized by comprising a fixed supporting part and a movable supporting part, wherein the fixed supporting part and the movable supporting part are detachably connected through an adjusting mechanism; the adjusting mechanism comprises a square machine assembly (4) and/or a high-low machine assembly (5);
the movable supporting part comprises a pitching support (7), the pitching support (7) comprises a mounting frame (14) and a launcher support, and one or more launcher supports are arranged on the mounting frame (14); the launching frame support is connected with a launching frame body (19), and one or more cartridge projectiles (6) are mounted on the launching frame body (19);
the plurality of launcher brackets comprise a first launcher bracket (13) and a second launcher bracket (15);
the first launcher support (13) and the second launcher support (15) are symmetrically arranged on two sides of the mounting rack (14);
a launch control system (8) and a guide device are arranged on the pitching support (7);
the guiding device comprises an infrared detection device (9);
the plurality of the tube bullets (6) are symmetrically arranged at two radial sides of the infrared detection device (9);
the cylindrical bullets (6) at the two sides are arranged in an eight-out shape on the horizontal plane projection; when a plurality of the tube bullets (6) exist on one side, the installation heights of the tube bullets (6) are sequentially reduced in the direction from the inner side to the outer side;
in a space rectangular coordinate system, in an XOZ plane, the optical axis of the infrared detection device (9) inclines downwards by an alpha angle, and the cylinder axis of the cylinder bullet (6) is horizontal;
in the XOY plane, the optical axis of the infrared detection device (9) and the cylinder axis of the cylinder bullet (6) form an angle beta;
in the YOZ plane, the central connecting line of the cylindrical bullets (6) at the two sides forms a gamma angle with a vertical axis passing through the center of the infrared detection device (9);
the optical axis of the cartridge (6) is parallel to the optical axis of the infrared detection device (9).
2. Missile launching device according to claim 1, characterised in that the fixed support comprises a tripod (1) and the adjustment mechanism further comprises an electrical control box (3);
the tripod (1), the electrical control box (3), the azimuth machine assembly (4), the height machine assembly (5), the pitching support (7), the mounting rack (14) and the launching rack support are connected in sequence.
3. Missile launching device according to claim 2, characterised in that the tripod (1) is removably connected to the electrical control box (3) by means of a set hoop (2); the electric control box (3) is connected with the azimuth machine assembly (4) through a first screw (10); the azimuth machine assembly (4) is connected with the high-low machine assembly (5) through a second screw (11); the high-low machine assembly (5) is connected with the pitching support (7) through a third screw (12).
4. Missile launching device according to claim 1, characterised in that the launcher body (19) is provided with a compression beam (17); one end of two ends of the pressure beam (17) along the length extension direction is arranged on the launcher frame body (19) through a hinge (16);
the pressing beam (17) rotates around the hinge (16) and can be switched between an opening state and a closing state;
the launcher frame body (19) is provided with a containing hole, and in the closed state, the pressing beam (17) limits the cartridge (6) in the containing hole.
5. Missile launcher arrangement according to claim 4, wherein the other end of the launcher body (19) in the direction of the length extension in the closed state is connected to the launcher body (19) by means of a provided snap (18).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910393872.1A CN110108161B (en) | 2019-05-13 | 2019-05-13 | Missile launching device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910393872.1A CN110108161B (en) | 2019-05-13 | 2019-05-13 | Missile launching device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110108161A CN110108161A (en) | 2019-08-09 |
| CN110108161B true CN110108161B (en) | 2021-05-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910393872.1A Active CN110108161B (en) | 2019-05-13 | 2019-05-13 | Missile launching device |
Country Status (1)
| Country | Link |
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| CN (1) | CN110108161B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113218245A (en) * | 2021-05-26 | 2021-08-06 | 上海机电工程研究所 | Compact high-low aircraft and missile launcher thereof |
| CN114111449B (en) * | 2021-11-17 | 2023-12-08 | 成都陵川特种工业有限责任公司 | Motorized and manual integrated height device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203550783U (en) * | 2013-11-01 | 2014-04-16 | 西安天伟电子系统工程有限公司 | Portable dual-mounted missile launcher |
| CN104634163A (en) * | 2014-12-23 | 2015-05-20 | 西安电子工程研究所 | Missile launcher structure for oblique launching |
| CN204478932U (en) * | 2015-03-11 | 2015-07-15 | 安徽大学 | A kind of control system for adjusting rocket launch platform inclination angle |
| CN204514188U (en) * | 2015-03-31 | 2015-07-29 | 金海重工（舟山）设计研究院有限公司 | Military project ship missile launcher |
| CN205090877U (en) * | 2015-09-29 | 2016-03-16 | 中国航天科工集团上海浦东开发中心 | Portable guided missile follow -up emitter |
| CN206695684U (en) * | 2017-01-20 | 2017-12-01 | 中国航天科工集团上海浦东开发中心 | A kind of robot weapon emitter of portable missile |
-
2019
- 2019-05-13 CN CN201910393872.1A patent/CN110108161B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203550783U (en) * | 2013-11-01 | 2014-04-16 | 西安天伟电子系统工程有限公司 | Portable dual-mounted missile launcher |
| CN104634163A (en) * | 2014-12-23 | 2015-05-20 | 西安电子工程研究所 | Missile launcher structure for oblique launching |
| CN204478932U (en) * | 2015-03-11 | 2015-07-15 | 安徽大学 | A kind of control system for adjusting rocket launch platform inclination angle |
| CN204514188U (en) * | 2015-03-31 | 2015-07-29 | 金海重工（舟山）设计研究院有限公司 | Military project ship missile launcher |
| CN205090877U (en) * | 2015-09-29 | 2016-03-16 | 中国航天科工集团上海浦东开发中心 | Portable guided missile follow -up emitter |
| CN206695684U (en) * | 2017-01-20 | 2017-12-01 | 中国航天科工集团上海浦东开发中心 | A kind of robot weapon emitter of portable missile |
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| Publication number | Publication date |
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| CN110108161A (en) | 2019-08-09 |
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