CN104897002A - Modular common-frame launch device - Google Patents
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- CN104897002A CN104897002A CN201510243905.6A CN201510243905A CN104897002A CN 104897002 A CN104897002 A CN 104897002A CN 201510243905 A CN201510243905 A CN 201510243905A CN 104897002 A CN104897002 A CN 104897002A
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Abstract
The invention provides a modular common-frame launch device. The modular common-frame launch device is formed by a plurality of launch unit modules through splicing and comprises a flow guide pipe, a flow guide device, a motor I and a plurality of launch pipes, wherein the flow guide pipe, the flow guide device, the motor I and the plurality of launch pipes are fixed through a launch frame; the flow guide device is driven by the motor I; the launch frame is provided with installation interfaces; every two adjacent launch unit modules are fixedly connected with each other through the corresponding installation interface in a detachable mode. According to the modular common-frame launch device, the common-frame vertical launch function of a launch pipe module which can independently rotate is achieved, the modular design is achieved, the launch unit modules can be arranged according to needs of the ship installation space and bearing capacity, the manufacturing cycle is shortened, and the installation and the update are convenient; the invisibility is good, semi-finished missile drugs can be fully launched, the modular common-frame launch device is not affected by the ship superstructure or other fighting positions after the vertical launch technology is adopted, the fire power is fully achieved, the firing area is expanded, and the all-dimensional attack on targets is implemented; the structure is simple, the operation and the maintenance are easy, the manufacturing cost is low, and the ship navigation performance stability is good.
Description
Patent application of the present invention is application number: 201210437262.5, denomination of invention: a kind of modularization Common-frame vertical launch device, and the applying date is: the divisional application of the patent of invention on November 5th, 2012.
Technical field
The invention belongs to MISSILE LAUNCHING frame for movement technical field, especially relate to a kind of modularization Common-frame vertical launch device of shipborne weapon.
Background technology
Carrier-borne VLS is a kind of missile release system be used on submarine and some water surface naval vessel, results from the emission system of ballistic missile the earliest, have high emissivity, bullet-loading capacity large, without launching the advantages such as blind area.The extensive use in the naval equipment of countries in the world of current carrier-borne Vertical Launch mode, from strategic missile, guided missile vertical launching technology reaches its maturity, and launching tower is just towards the future development of versatility flexibility.Missile release system is generally divided into pop-up and heat emission two kinds of modes, in heat emission mode, heat emission system utilizes the engine of guided missile itself to produce thrust and guided missile is penetrated transmitting tube, therefore system itself unpowered, and have the mechanism of row's flame exhaust, the advantage of heat emission system is that efficiency is higher, can save the volume and weight of emission system and reduce its maintenance cost.
Traditional guided missile launcher is made up of thousands of moving components, and arbitrary link breaks down and all likely makes whole armament systems be out of action.As notification number is: a kind of deep sea submarine missile launcher that the Chinese utility model patent of CN201096482Y provides, it has a Missile Body, motor is provided with at Missile Body afterbody, the output shaft of motor is drawn by missile mainbody tail end, the output shaft of motor is provided with impeller, in Missile Body, be provided with fuel cell and high-energy battery, described fuel cell is connected with the power end of motor respectively by switching controller with high-energy battery.The moving component of the missile launcher that this patent provides integrates the complete combat gear of formation one, but because composition component is more, dismounting is very inconvenient, maintenance trouble, quantity and the position of missile gear can not be arranged according to fight demand simultaneously, take up room comparatively large, it is inflexible to use, underaction.
Summary of the invention
The present invention is mainly more for the component existing for existing guided missile launcher, complex structure, take up room the problem of comparatively large, dismounting and inconvenient maintenance, use underaction, there is provided a kind of structure simple, the degree of modularity is high, take up room little, dismounting and easy to maintenance, can according to the modularization common frame of launching equipment of fight demand flexible arrangement.
Above-mentioned technical problem of the present invention is mainly solved by following technical proposals: a kind of modularization common frame of launching equipment, it is spliced by multiple transmitter unit module, transmitter unit module comprises mozzle, air deflector, motor I and several transmitting tubes fixed by launcher, air deflector is driven by motor I, several transmitting tubes are connected with mozzle by air deflector, launcher is provided with mounting interface, and adjacent transmission unit module is connected by mounting interface is removable, described air deflector is positioned at bottom transmitting tube and mozzle, and transmitting tube has four, and four transmitting tubes are evenly laid in around mozzle, and four transmitting tubes are all connected with mozzle by air deflector, described air deflector comprises diaphragm valve and the second baffle, second baffle is positioned at below transmitting tube, diaphragm valve is between the second baffle and transmitting tube, second baffle is provided with four directed fluid inlet II, four directed fluid inlet II are communicated with and are "X" shape distribution, the bottom surface of four directed fluid inlet II is circular arc camber and is connected smoothly, the middle part of diaphragm valve is provided with valve port I, valve port I is corresponding with the position of mozzle and be communicated with mozzle, diaphragm valve is also provided with four valve ports II, the position one_to_one corresponding of valve port II and transmitting tube and being communicated with corresponding transmitting tube, motor I have four and with valve port II one_to_one corresponding, the position one_to_one corresponding of four valve ports II and four directed fluid inlet II and being communicated with corresponding directed fluid inlet II, valve port II is provided with valve gap, valve port II place is provided with " n " shape position-limited edge that can hold valve gap and pass, valve gap is provided with " V " v notch v, motor I is connected with rocking bar, rocking bar is hinged with the connecting rod be active in " V " v notch v, connecting rod is connected with the center of valve gap.
Air deflector, mozzle and transmitting tube form the transmitting inner core of this emitter jointly, launch inner core to take out from launcher, this launching tower adopts modular construction, be spliced by multiple transmitter unit module, many groups transmitting tube shares a mozzle, each transmitting tube unit independently can select transmit direction, ammunition spontaneous emission pipe launches away, the high-temperature fuel gas produced passes through air deflector, to enter in mozzle and to discharge, air deflector is driven by motor I, this module can be carried out different assemblings according to mission requirements and naval vessel condition and change to be applicable to different warship types, eliminate the complex operations needed for the filling transmitting of Shi Dan storehouse, deck and control assembly, improve the reliability of system, reduce maintenance work amount, decrease naval vessels to take up room, the generalization of guided missile launcher achieves multiple guided missile Common-frame launch.Four groups of transmitting tubes share a mozzle, and each transmitting tube unit independently can select transmit direction, and four groups of transmitting tubes are all connected with mozzle by air deflector.The program has set up diaphragm valve between the second baffle and transmitting tube, motor I drives rocking bar, rocking bar drivening rod, connecting rod drives valve gap to move in position-limited edge, position-limited edge is to the mobile limited location effect of valve gap, when valve gap moves to corresponding valve port II, this valve port II closes, gas extraction system is closed, when valve gap shifts out valve port II, this valve port II is opened, gas extraction system is opened, at this moment the high-temperature fuel gas in transmitting tube is by valve port II, enter in directed fluid inlet II, gas in directed fluid inlet II enters in mozzle by valve port I again, and then by mozzle, high-temperature fuel gas is discharged.
As preferably, described diaphragm valve is provided with dust cap, and dust cap is between transmitting tube and diaphragm valve, and dust cap is provided with five via holes, the position of valve port I and valve port II and five via hole one_to_one corresponding.During MISSILE LAUNCHING; a large amount of solid particle can be produced; solid particle can enter diaphragm valve with combustion gas; likely block diaphragm valve assembly; make it cisco unity malfunction, thus in scheme two, add dust cap on diaphragm valve top; via hole on dust cap is for being communicated with valve port and transmitting tube or mozzle, and dust cap can stop solid particle to enter diaphragm valve.
As preferably, described launcher comprises frame and is arranged in the top board of frame, plate and base plate, top board, middle plate and base plate are connected to the top of transmitting tube and mozzle, middle part and bottom, top board, middle plate and the through transmitting tube of base plate and mozzle be matched in clearance with transmitting tube, be connected with mozzle, top board, middle plate are connected by support bar with base plate, and middle plate is provided with motor III and gear-box II, motor III is electrically connected with gear-box II, and gear-box II is connected with transmitting tube.Top board, middle plate are connected transmitting tube and mozzle with base plate, and motor III driven gear case II, the operation of motor III is converted into the rotary motion of transmitting tube by gear-box II, has been convenient to the emission process of guided missile.
As preferably, the top of described frame is provided with cover, one end of cover by rotating shaft and frame hinged, frame is provided with motor II, and motor II is electrically connected with rotating shaft.For preventing foreign matter from entering transmitting tube and mozzle, cover can be set at frame top, cover and frame hinged, motor II drives cover to overturn, and controls the opening and closing of cover by motor II.
As preferably, the described frame side of being frame, four sides of frame are equipped with mounting interface, and mounting interface comprises the upper interface being located at frame upper end and the lower interface being located at frame lower end, upper interface and lower interface are all connected with foundation bolt, and adjacent transmission unit module is fixed by foundation bolt.Four sides of frame are equipped with mounting interface, and thus can carry out different assemblings according to mission requirements and naval vessel condition and change to be applicable to different warship types, combined and instant be flexible; Adjacent transmission unit module is fixed by foundation bolt, and fixation is reliable, easy accessibility.
As preferably, described motor I is stepper motor.Motor I is stepper motor, and along with different transmitting tube sequential transmission guided missile, motor I can turn an angle according to instruction, ensures that the opening of rotary inner core and directed fluid inlet I are connected.
therefore, the invention has the beneficial effects as follows: the Common-frame vertical launch function 1, possessing independently rotary transmitting tube module, adopt modularized design, transmitter unit module can be configured as required according to naval vessel installing space and bearing capacity, shorten the manufacturing cycle, be convenient to install and upgrade; 2, stealth is good, can omnidirectional emission half guided munition, after adopting vertical launching technology, by the impact of naval vessel superstructure with other battle stations, firepower can not be given full play to, expands firing area, comprehensive attack is implemented to target, and the dome-type spatial domain of 360 ° can be covered, identical in all orientation can emission probability, naval vessel operation respond, can realize implementing to attack to multiple target; 3, structure is simple, Operation and Maintenance is easy, at the bottom of manufacturing expense, ship navigation stability is good, and the present invention is specially adapted to the Vertical Launch of middle-size and small-size ammunition.
Accompanying drawing explanation
Accompanying drawing 1 is a kind of structural representation that the present invention adopts two groups of transmitter unit module splicings;
Accompanying drawing 2 is a kind of structural representations of single group transmitter unit module in the present invention;
Accompanying drawing 3 is a kind of structural representations launching inner core in the present invention;
Accompanying drawing 4 adopts the A-A sectional view in the accompanying drawing 3 of embodiment 1 structure;
Accompanying drawing 5 adopts the A-A sectional view in the accompanying drawing 3 of embodiment 2 structure;
Accompanying drawing 6 is a kind of structural representations of the first baffle in the present invention;
Accompanying drawing 7 is a kind of structural representations of diaphragm valve in the present invention;
Accompanying drawing 8 is a kind of structural representations of the second baffle in the present invention;
Accompanying drawing 9 is a kind of structural representations of dust cap in the present invention.
Shown in figure: 1-transmitter unit module, 2-launcher, 21-frame, 22-top board, plate in 23-, 24-base plate, 25-support bar, 26-motor III, 27-gear-box II, 28-cover, 29-motor II, 3-mozzle, 4-air deflector, 41-first baffle, 411-connecting hole, 412-directed fluid inlet I, 42-rotary inner core, 421-opening, 43-gear-box I, 44-diaphragm valve, 441-valve port I, 442-valve port II, 443-connecting rod, 444-valve gap, 445-position-limited edge, 446-breach, 447-rocking bar, 45-second baffle, 451-directed fluid inlet II, 46-dust cap, 461-via hole, 5-motor I, 6-transmitting tube, 7-mounting interface, the upper interface of 71-, 72-lower interface.
Detailed description of the invention
Below by embodiment, and by reference to the accompanying drawings, technical scheme of the present invention is described in further detail.
Embodiment 1:
As Figure of description 1, 2, shown in 3, a kind of modularization common frame of launching equipment, be spliced by two groups of transmitter unit modules 1, transmitter unit module 1 comprises launcher 2, mozzle 3, air deflector 4, motor I 5 and four transmitting tubes 6, four transmitting tubes 6 are evenly laid in around mozzle 3, air deflector 4 is positioned at bottom transmitting tube 6 and mozzle 3, four transmitting tubes 6 are all connected with mozzle 3 by air deflector 4, launcher 2 comprises frame 21 and is positioned at the top board 22 of frame 21, middle plate 23 and base plate 24, top board 22, middle plate 23 and base plate 24 are connected to the top of transmitting tube 6 and mozzle 3, middle part and bottom, top board 22, middle plate 23 and the through transmitting tube 6 of base plate 24 and mozzle 3 be matched in clearance with transmitting tube 6, be connected with mozzle 3, top board 22, middle plate 23 is connected by support bar 25 with base plate 24, middle plate 23 is provided with motor III 26 and gear-box II 27, motor III 26 is electrically connected with gear-box II 27, gear-box II 27 is connected with four transmitting tubes 6 respectively, the top of frame 21 is provided with cover 28, one end of cover 28 by rotating shaft and frame 21 hinged, frame 21 is provided with motor II 29, motor II 29 is electrically connected with rotating shaft, frame 21 side of being frame, four sides of frame 21 are equipped with mounting interface 7, mounting interface 7 comprises the upper interface 71 being located at frame 21 upper end and the lower interface 72 being located at frame 21 lower end, upper interface 71 and lower interface 72 are all connected with foundation bolt, adjacent transmission unit module 1 is fixed by foundation bolt, as Figure of description 4, shown in 6, air deflector 4 comprises the first baffle 41, rotary inner core 42 and gear-box I 43, first baffle 41 is provided with connecting hole 411, rotary inner core 42 be positioned at connecting hole 411 and with the first baffle 41 matched in clearance, motor I 5 is stepper motor, motor I 5 to be fixed on the first baffle 41 and to be electrically connected with gear-box I 43, gear-box I 43 is connected with rotary inner core 42, first baffle 41 is provided with four directed fluid inlet I 412, the position one_to_one corresponding of directed fluid inlet I 412 and transmitting tube 6 and being communicated with corresponding transmitting tube 6, four directed fluid inlet I 412 to be evenly laid in around connecting hole 411 and to be communicated with connecting hole 411, rotary inner core 42 is provided with the pipe of opening 421 for side, opening 421 is in the same size with directed fluid inlet I 412, the bottom surface of directed fluid inlet I 412 is circular arc camber, the bottom surface of rotary inner core 42 is circular arc camber, the bottom surface of directed fluid inlet I 412 and the bottom surface of rotary inner core 42 seamlessly transit and the two surrounds a semicircle cavity, rotary inner core 42 is corresponding with the position of mozzle 3 and be communicated with mozzle 3.
Cover is driven to open by motor II, arming in the transmitting tube of each transmitting tube module, driven the transmitting tube 360 ° rotation that ammunition is housed by gear-box I by motor III, the orientation that selection will be launched, when after ammunition engine start, promote ammunition to fly out from transmitting tube, the air-flow simultaneously produced enters air deflector from transmitting tube lower port, when adopting air deflector scheme for the moment, motor I drives rotary inner core to rotate in the first baffle by gear-box I, select and be communicated with to be in the transmitting tube of emission state and the lower port of mozzle, air-flow is by the guiding of circular arc camber, enter mozzle smoothly and discharge from emitter.
Air deflector, mozzle and transmitting tube form the transmitting inner core of this emitter jointly, as shown in Figure of description 3, it is overall for launching inner core, can middle taking-up suitable for reading from launcher in handling ammunition or maintenance process, desirablely after opening cover goes out to launch inner core.The transmitting tube of this guided missile launcher is pipe, is equally applicable to square tube.
embodiment 2:
As Figure of description 1, shown in 2, a kind of modularization common frame of launching equipment, be spliced by two groups of transmitter unit modules 1, transmitter unit module 1 comprises launcher 2, mozzle 3, air deflector 4, motor I 5 and four transmitting tubes 6, four transmitting tubes 6 are evenly laid in around mozzle 3, air deflector 4 is positioned at bottom transmitting tube 6 and mozzle 3, four transmitting tubes 6 are all connected with mozzle 3 by air deflector 4, launcher 2 comprises frame 21 and is positioned at the top board 22 of frame 21, middle plate 23 and base plate 24, top board 22, middle plate 23 and base plate 24 are connected to the top of transmitting tube 6 and mozzle 3, middle part and bottom, top board 22, middle plate 23 and the through transmitting tube 6 of base plate 24 and mozzle 3 be matched in clearance with transmitting tube 6, be connected with mozzle 3, top board 22, middle plate 23 is connected by support bar 25 with base plate 24, middle plate 23 is provided with motor III 26 and gear-box II 27, motor III 26 is electrically connected with gear-box II 27, gear-box II 27 is connected with four transmitting tubes 6 respectively, the top of frame 21 is provided with cover 28, one end of cover 28 by rotating shaft and frame 21 hinged, frame 21 is provided with motor II 29, motor II 29 is electrically connected with rotating shaft, frame 21 side of being frame, four sides of frame 21 are equipped with mounting interface 7, mounting interface 7 comprises the upper interface 71 being located at frame 21 upper end and the lower interface 72 being located at frame 21 lower end, upper interface 71 and lower interface 72 are all connected with foundation bolt, adjacent transmission unit module 1 is fixed by foundation bolt, as shown in Figure of description 5, air deflector 4 comprises diaphragm valve 44 and the second baffle 45, second baffle 45 is positioned at below transmitting tube 6, diaphragm valve 44 is between the second baffle 45 and transmitting tube 6, as shown in Figure of description 8, second baffle 45 is provided with four directed fluid inlet II 451, four directed fluid inlet II 451 are communicated with and are "X" shape distribution, the bottom surface of four directed fluid inlet II 451 is circular arc camber and is connected smoothly, as shown in Figure of description 7, the middle part of diaphragm valve 44 is provided with valve port I 441, valve port I 441 is corresponding with the position of mozzle 3 and be communicated with mozzle 3, diaphragm valve 44 is also provided with four valve ports II 442, the position one_to_one corresponding of valve port II 442 and transmitting tube 6 and being communicated with corresponding transmitting tube 6, motor I 5 is stepper motor, motor I 5 have four and with valve port II 442 one_to_one corresponding, the position one_to_one corresponding of four valve ports II 442 and four directed fluid inlet II 451 and being communicated with corresponding directed fluid inlet II 451, valve port II 442 is provided with valve gap 444, valve port II 442 place is provided with " n " shape position-limited edge 445 that can hold valve gap 444 and pass, valve gap 444 is provided with " V " v notch v 446, motor I 5 is connected with rocking bar 447, rocking bar 447 is hinged with the connecting rod 443 be active in " V " v notch v 446, connecting rod 443 is connected with the center of valve gap 444, as shown in Figure of description 9, diaphragm valve 44 is provided with dust cap 46, dust cap 46 is between transmitting tube 6 and diaphragm valve 44, dust cap 46 is provided with five via holes 461, the position of valve port I 441 and valve port II 442 and five via hole 461 one_to_one corresponding.
Cover is driven to open by motor II, arming in the transmitting tube of each transmitting tube module, driven the transmitting tube 360 ° rotation that ammunition is housed by gear-box I by motor III, the orientation that selection will be launched, when after ammunition engine start, promote ammunition to fly out from transmitting tube, the air-flow simultaneously produced enters air deflector from transmitting tube lower port, when adopting two of air deflector scheme, motor I is driven by connecting rod and makes valve gap opening and closing, valve port II is by the effect of four groups of valve members of diaphragm valve, can realize opening or closing, and be communicated with transmitting tube and mozzle by the second baffle.Air-flow enters the second baffle, is entered mozzle smoothly by the guide effect of circular arc camber and is discharged from emitter.Now launch and complete with water conservancy diversion process, two schemes is suitable for the transmitting of other each transmitting tube module equally.
Air deflector, mozzle and transmitting tube form the transmitting inner core of this emitter jointly, as shown in Figure of description 3, it is overall for launching inner core, can middle taking-up suitable for reading from launcher in handling ammunition or maintenance process, desirablely after opening cover goes out to launch inner core.The transmitting tube of this guided missile launcher is pipe, is equally applicable to square tube.
Guided missile VLS adopts modularized design, and structure is simple, and reliability is high, and it has also generally used the isolation technique of redundancy, except warship power source lose except, there is not the Single Point of Faliure of influential system fighting capacity, this to whole system improve reliability and availability all helpful.In addition, in guided missile VLS, every piece of guided missile is encapsulated in respective storing and transporting box before transmission all the time, provides effective environmental protection and handling protection, substantially increases the reliability of guided missile.Storing and transporting box is loaded on below deck, has the protection of armoring hatchcover above, can avoid the destruction by enemy firepower.
This launching tower adopts modular construction, be spliced by multiple transmitter unit module, many groups transmitting tube shares a mozzle, each transmitting tube unit independently can select transmit direction, ammunition spontaneous emission pipe launches away, the high-temperature fuel gas produced passes through air deflector, to enter in mozzle and to discharge, this module can be carried out different assemblings according to mission requirements and naval vessel condition and change to be applicable to different warship types, eliminate the complex operations needed for the filling transmitting of Shi Dan storehouse, deck and control assembly, improve the reliability of system, reduce maintenance work amount, decrease naval vessels to take up room, the generalization of guided missile launcher achieves multiple guided missile Common-frame launch.
Should be understood that this embodiment is only not used in for illustration of the present invention to limit the scope of the invention.In addition should be understood that those skilled in the art can make various changes or modifications the present invention, and these equivalent form of values fall within the application's appended claims limited range equally after the content of having read the present invention's instruction.
Claims (6)
1. a modularization common frame of launching equipment, it is characterized in that, it is spliced by multiple transmitter unit module (1), transmitter unit module (1) comprises by fixing mozzle (3), air deflector (4), motor I (5) and several transmitting tubes (6) of launcher (2), air deflector (4) is driven by motor I (5), several transmitting tubes (6) are connected with mozzle (3) by air deflector (4), launcher (2) is provided with mounting interface (7), and adjacent transmission unit module (1) is connected by mounting interface (7) is removable, described air deflector (4) is positioned at transmitting tube (6) and mozzle (3) bottom, transmitting tube (6) has four, four transmitting tubes (6) are evenly laid in mozzle (3) around, and four transmitting tubes (6) are all connected with mozzle (3) by air deflector (4), described air deflector (4) comprises diaphragm valve (44) and the second baffle (45), second baffle (45) is positioned at transmitting tube (6) below, diaphragm valve (44) is positioned between the second baffle (45) and transmitting tube (6), second baffle (45) is provided with four directed fluid inlet II (451), four directed fluid inlet II (451) are communicated with and are "X" shape distribution, the bottom surface of four directed fluid inlet II (451) is circular arc camber and is connected smoothly, the middle part of diaphragm valve (44) is provided with valve port I (441), valve port I (441) is corresponding with the position of mozzle (3) and be communicated with mozzle (3), diaphragm valve (44) is also provided with four valve ports II (442), the position one_to_one corresponding of valve port II (442) and transmitting tube (6) and being communicated with corresponding transmitting tube (6), motor I (5) have four and with valve port II (442) one_to_one corresponding, the position one_to_one corresponding of four valve ports II (442) and four directed fluid inlet II (451) and being communicated with corresponding directed fluid inlet II (451), valve port II (442) is provided with valve gap (444), valve port II (442) place is provided with " n " shape position-limited edge (445) can held valve gap (444) and pass, valve gap (444) is provided with " V " v notch v (446), motor I (5) is connected with rocking bar (447), rocking bar (447) is hinged with the connecting rod (443) be active in " V " v notch v (446), connecting rod (443) is connected with the center of valve gap (444).
2. modularization common frame of launching equipment according to claim 1, it is characterized in that, described diaphragm valve (44) is provided with dust cap (46), dust cap (46) is positioned between transmitting tube (6) and diaphragm valve (44), dust cap (46) is provided with five via holes (461), the position of valve port I (441) and valve port II (442) and five via hole (461) one_to_one corresponding.
3. modularization common frame of launching equipment according to claim 1 and 2, it is characterized in that, described launcher (2) comprises frame (21) and is positioned at the top board (22) of frame (21), middle plate (23) and base plate (24), top board (22), middle plate (23) and base plate (24) are connected to the top of transmitting tube (6) and mozzle (3), middle part and bottom, top board (22), middle plate (23) and base plate (24) through transmitting tube (6) be matched in clearance with transmitting tube (6), be connected with mozzle (3), top board (22), middle plate (23) is connected by support bar (25) with base plate (24), middle plate (23) is provided with motor III (26) and gear-box II (27), motor III (26) is electrically connected with gear-box II (27), gear-box II (27) is connected with transmitting tube (6).
4. modularization common frame of launching equipment according to claim 3, it is characterized in that, the top of described frame (21) is provided with cover (28), one end of cover (28) by rotating shaft and frame (21) hinged, frame (21) is provided with motor II (29), and motor II (29) is electrically connected with rotating shaft.
5. modularization common frame of launching equipment according to claim 4, it is characterized in that, described frame (21) is square frame, four sides of frame (21) are equipped with mounting interface (7), mounting interface (7) comprises the upper interface (71) being located at frame (21) upper end and the lower interface (72) being located at frame (21) lower end, upper interface (71) and lower interface (72) are all connected with foundation bolt, and adjacent transmission unit module (1) is fixed by foundation bolt.
6. modularization common frame of launching equipment according to claim 1 and 2, is characterized in that, described motor I (5) is stepper motor.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210437262.5A CN103808206B (en) | 2012-11-05 | 2012-11-05 | A kind of modularization Common-frame vertical launch device |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210437262.5A Division CN103808206B (en) | 2012-11-05 | 2012-11-05 | A kind of modularization Common-frame vertical launch device |
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| CN104897002A true CN104897002A (en) | 2015-09-09 |
| CN104897002B CN104897002B (en) | 2016-07-13 |
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| CN201210437262.5A Active CN103808206B (en) | 2012-11-05 | 2012-11-05 | A kind of modularization Common-frame vertical launch device |
| CN201510243905.6A Active CN104897002B (en) | 2012-11-05 | 2012-11-05 | Modularity Common-frame vertical launch device |
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| WO1997048959A1 (en) * | 1996-06-20 | 1997-12-24 | Dynamit Nobel Graz Ges.Mbh | High angle fire gun, in particular grenade launching weapon |
| WO1998012495A1 (en) * | 1996-09-17 | 1998-03-26 | Forsvarets Forskningsinstitutt | Arrangement for launching smoke hand grenades |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107054569A (en) * | 2017-02-14 | 2017-08-18 | 佛山市三水区希望火炬教育科技有限公司 | A kind of special dual peacetime type guided missile cargo ship of teenager's defence education |
| CN107054569B (en) * | 2017-02-14 | 2019-01-08 | 王海南 | A kind of dedicated dual peacetime type guided missile cargo ship model of teenager's defence education |
| CN107144170A (en) * | 2017-07-04 | 2017-09-08 | 北京理工大学 | A kind of big cambered surface air deflector of monoblock type for Vertical Launch duplex multiple missile |
| CN110834786A (en) * | 2019-10-30 | 2020-02-25 | 中船华南船舶机械有限公司 | Protection type integrated form filling box |
| CN110834786B (en) * | 2019-10-30 | 2021-09-07 | 中船华南船舶机械有限公司 | Protection type integrated form filling box |
| CN111912293A (en) * | 2020-07-02 | 2020-11-10 | 上海机电工程研究所 | Large and small missile co-frame mechanism with variable transportation-launching state structure |
| CN111912293B (en) * | 2020-07-02 | 2022-08-12 | 上海机电工程研究所 | Large and small missile co-frame mechanism with variable transportation-launching state structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104897002B (en) | 2016-07-13 |
| CN103808206A (en) | 2014-05-21 |
| CN103808206B (en) | 2015-09-02 |
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