CN202903017U - Modular common-frame vertical launching device - Google Patents
Modular common-frame vertical launching device Download PDFInfo
- Publication number
- CN202903017U CN202903017U CN 201220578458 CN201220578458U CN202903017U CN 202903017 U CN202903017 U CN 202903017U CN 201220578458 CN201220578458 CN 201220578458 CN 201220578458 U CN201220578458 U CN 201220578458U CN 202903017 U CN202903017 U CN 202903017U
- Authority
- CN
- China
- Prior art keywords
- frame
- mozzle
- transmitting tube
- motor
- water conservancy
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
Images
Landscapes
- Mechanically-Actuated Valves (AREA)
Abstract
The utility model relates to a modular common-frame vertical launching device for shipborne weapons. The modular common-frame vertical launching device for shipborne weapons is formed by splicing a plurality of launch unit modules. Each launch unit module comprises a guide tube fixed via a launch rack, a guide device, a motor I and a plurality of launch tubes, wherein the guide device is driven by the motor I, and the launch rack is provided with a mounting joint. The adjacent launch unit modules are detachably and fixedly connected through the mounting joints. The modular common-frame vertical launching device for shipborne weapons has the advantages that the device has a common-frame vertical launching function of independently rotatable launch tube modules and has the modular design, the launch unit modules can be dispatched on demand according to ship mounting space and bearing capacity, manufacturing cycle is shortened, and installation and update are facilitated; the device is highly invisible and capable of launching half-guided munitions all-dimensionally, the application of the vertical launching technology avoids the effects of ship superstructure and other battle stations, fire power is given to full play, firing area is enlarged, and all-range attack on targets can be achieved; the device is simple in structure, easy to operate and maintain and low in manufacturing cost, and sailing stability of ships is high.
Description
Technical field
The utility model belongs to MISSILE LAUNCHING frame for movement technical field, and the modularization that especially relates to a kind of shipborne weapon is total to the frame launching tower.
Background technology
Carrier-borne VLS is a kind of missile release system that is used on submarine and some water surface naval vessel, results from the earliest the emission system of ballistic missile, have high emissivity, bullet-loading capacity large, without advantages such as emission blind areas.The extensive use in the naval equipment of countries in the world of present carrier-borne Vertical Launch mode begins guided missile Vertical Launch technology from strategic missile and reaches its maturity, and launching tower is just towards the future development of versatility flexibility.Missile release system generally is divided into pop-up and heat emission dual mode, in the heat emission mode as example, the heat emission system utilizes the engine of guided missile itself to produce thrust guided missile is penetrated transmitting tube, therefore system itself is also unpowered, and have a mechanism of row's flame exhaust, the heat emission advantage of system is that efficient is higher, can save the volume and weight of emission system and reduce its maintenance cost.
Traditional guided missile launcher is comprised of thousands of moving components, and arbitrary link breaks down whole armament systems are out of action.Such as notification number be: a kind of deep sea submarine missile launcher that the Chinese utility model patent of CN201096482Y provides, it has a Missile Body, be provided with motor at the Missile Body afterbody, the output shaft of motor is drawn by the missile mainbody tail end, output shaft at motor is equipped with impeller, be provided with fuel cell and high-energy battery in Missile Body, described fuel cell is connected with high-energy battery by switching controller and is connected with the power end of motor.The moving component of the missile launcher that this patent provides integrates and consists of a complete combat gear, but because it is more to form member, dismounting is inconvenience very, the maintenance trouble, can not arrange according to the fight demand simultaneously quantity and the position of missile gear, it is larger to take up room, and it is inflexible to use, underaction.
The utility model content
The utility model mainly is more for the existing member of existing guided missile launcher, complex structure, the problem of large, dismounting and inconvenient maintenance, use underaction takes up room, provide a kind of simple in structure, the degree of modularity is high, take up room little, dismounting and easy to maintenance, can be according to the modularization of fight demand flexible arrangement frame launching tower altogether.
Above-mentioned technical problem of the present utility model is mainly solved by following technical proposals: a kind of modularization is the frame launching tower altogether, it is spliced by a plurality of transmitter unit modules, the transmitter unit module comprises by launcher fixing mozzle, air deflector, motor I and several transmitting tubes, air deflector is driven by the motor I, several transmitting tubes connect with mozzle by air deflector, launcher is provided with mounting interface, and the adjacent transmission unit module is connected by mounting interface is removable.Air deflector, mozzle and transmitting tube form the emission inner core of this emitter jointly, the emission inner core can take out from launcher, this launching tower adopts modular construction, be spliced by a plurality of transmitter unit modules, many group transmitting tubes share a mozzle, transmit direction can independently be selected in each transmitting tube unit, ammunition spontaneous emission pipe launches away, the high-temperature fuel gas that produces passes through air deflector, enter in the mozzle and discharge, air deflector is driven by the motor I, and this module can be carried out different assemblings and change to be applicable to different warship types according to mission requirements and naval vessel condition, has saved required complex operations and the control assembly of formula bullet storehouse, deck filling emission, improved the reliability of system, reduced the maintenance work amount, reduced naval vessels and taken up room, the generalization of guided missile launcher has realized the altogether frame emission of multiple guided missile.
As preferably, described air deflector is positioned at transmitting tube and mozzle bottom, and transmitting tube has four, and four transmitting tubes evenly are laid in around the mozzle, and four transmitting tubes all connect with mozzle by air deflector.Four groups of transmitting tubes share a mozzle, and transmit direction can independently be selected in each transmitting tube unit, and four groups of transmitting tubes all are connected with mozzle by air deflector.
As preferably, described air deflector comprises the first baffle, rotary inner core and gear-box I, the first baffle is provided with connecting hole, rotary inner core be positioned at connecting hole and with the first baffle matched in clearance, the motor I is fixed on the first baffle and with the gear-box I and is electrically connected, the gear-box I is connected with rotary inner core, the first baffle is provided with four water conservancy diversion entrance I, the position of water conservancy diversion entrance I and transmitting tube is corresponding and be communicated with corresponding transmitting tube one by one, four water conservancy diversion entrance I evenly are laid in around the connecting hole and with connecting hole and are communicated with, rotary inner core is the pipe that the side is provided with opening, the in the same size of opening and water conservancy diversion entrance I, rotary inner core is corresponding with the position of mozzle and be communicated with mozzle.Can produce a large amount of high-temperature fuel gas during MISSILE LAUNCHING, these combustion gas all can produce very serious ablation to emitter and relevant devices, and it is vital therefore quickly and effectively these jet exhausts being gone out.This scheme arranges the first baffle in the transmitting tube bottom, motor I connection teeth roller box I, the gear-box I connects rotary inner core, the gear-box I is converted into rotatablely moving of rotary inner core with the operation of motor I, after four transmitting tubes are launched a guided missile successively by the front and back order, rotary inner core rotates, when turning to corresponding transmitting tube, the corresponding water conservancy diversion entrance I that is opened on of rotary inner core is communicated with, high-temperature fuel gas can enter water conservancy diversion entrance I by transmitting tube, enter again rotary inner core, then enter mozzle, finally discharge by mozzle.
As preferably, described air deflector comprises diaphragm valve and the second baffle, the second baffle is positioned at the transmitting tube below, diaphragm valve is between the second baffle and transmitting tube, the second baffle is provided with four water conservancy diversion entrance II, four water conservancy diversion entrance II connections also are "X" shape distribution, the bottom surface of four water conservancy diversion entrance II is circular arc camber and is connected smoothly, the middle part of diaphragm valve is provided with the valve port I, the valve port I is corresponding with the position of mozzle and be communicated with mozzle, also be provided with four valve port II on the diaphragm valve, the position of valve port II and transmitting tube is corresponding and be communicated with corresponding transmitting tube one by one, and the motor I has four and corresponding one by one with the valve port II, and the position of four valve port II and four water conservancy diversion entrance II is corresponding and be communicated with corresponding water conservancy diversion entrance II one by one, the valve port II is provided with valve gap, valve port II place is provided with and can holds " n " shape position-limited edge that valve gap passes, and valve gap is provided with " V " v notch v, and the motor I is connected with rocking bar, rocking bar is hinged with the connecting rod that is active in " V " v notch v, and connecting rod is connected with the center of valve gap.This scheme has been set up diaphragm valve between the second baffle and transmitting tube, the motor I drives rocking bar, the rocking bar drivening rod, it is mobile in position-limited edge that connecting rod drives valve gap, 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 is closed, and gas extraction system is closed, when valve gap shifts out the valve port II, this valve port II is opened, gas extraction system is opened, and at this moment the high-temperature fuel gas in the transmitting tube enters in the water conservancy diversion entrance II by the valve port II, gas in the water conservancy diversion entrance II enters in the mozzle by the 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, and the position of valve port I and valve port II is corresponding one by one with five via holes.During MISSILE LAUNCHING; can produce a large amount of solid particles; solid particle can enter diaphragm valve with combustion gas; might block the diaphragm valve assembly; make it cisco unity malfunction, thereby in scheme two, increased dust cap on diaphragm valve top; via hole on the dust cap is used 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 top board, plate and the base plate of frame, top board, middle plate and base plate are connected to top, middle part and the bottom of transmitting tube and mozzle, top board, middle plate and base plate connect transmitting tube and mozzle and with transmitting tube be matched in clearance, be connected with mozzle, top board, middle plate are connected support bar with base plate and connect, and middle plate is provided with motor III and gear-box II, the motor III is electrically connected with the gear-box II, and the gear-box II is connected with transmitting tube.Top board, middle plate are connected transmitting tube and mozzle with base plate, motor III driven gear case II, and the gear-box II is converted into rotatablely moving of transmitting tube with the operation of motor III, is convenient to finish the emission process of guided missile.
As preferably, the top of described frame is provided with cover, and an end of cover is hinged by rotating shaft and frame, and frame is provided with the motor II, and the motor II is electrically connected with rotating shaft.For preventing that foreign matter from entering transmitting tube and mozzle, can cover be set at frame top, cover and frame are hinged, and the motor II drives the cover upset, can be by the switching of motor II control cover.
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 of being located at the frame upper end and the lower interface of being located at the frame lower end, all be connected with foundation bolt on upper interface and the lower interface, the adjacent transmission unit module is fixed by foundation bolt.Four sides of frame are equipped with mounting interface, thereby can carry out different assemblings and change to be applicable to different warship types according to mission requirements and naval vessel condition, and combined and instant is flexible; The adjacent transmission unit module is fixed by foundation bolt, and fixation is reliable, easy accessibility.
As preferably, the bottom surface of described water conservancy diversion entrance I is circular arc camber, and the bottom surface of rotary inner core is circular arc camber, the bottom surface of water conservancy diversion entrance I and the bottom surface of rotary inner core seamlessly transits and the two surrounds a semicircle cavity.The bottom surface of water conservancy diversion entrance I and rotary inner core is circular arc camber, and seamlessly transits, and is conducive to high-temperature fuel gas and enters mozzle along circular arc camber.
As preferably, described motor I is stepper motor.The motor I is stepper motor, and along with different transmitting tube sequential transmission guided missiles, the motor I can turn an angle according to instruction, guarantees opening and the connection of water conservancy diversion entrance I of rotary inner core.
Therefore, the beneficial effects of the utility model are: 1, possess the common frame Vertical Launch function of independently rotary transmitting tube module, adopt modularized design, can dispose as required the transmitter unit module according to naval vessel installing space and bearing capacity, shorten the manufacturing cycle, be convenient to install and upgrade; 2, stealth is good, can comprehensive emission half guided munition, after adopting the Vertical Launch technology, can not be subjected to the impact of naval vessel superstructure and other battle stations, give full play to firepower, enlarge the firing area, target is implemented comprehensive attack, and can cover 360 ° dome-type spatial domain, but identical emission probability on all orientation, operation respond in naval vessel can realize multiple target is implemented to attack; 3, simple in structure, Operation and Maintenance easily, at the bottom of the manufacturing expense, the ship navigation stability is good, the utility model is specially adapted to the Vertical Launch of middle-size and small-size ammunition.
Description of drawings
Accompanying drawing 1 is a kind of structural representation that the utility model 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 utility model;
Accompanying drawing 3 is a kind of structural representations of emission inner core in the utility model;
Accompanying drawing 4 is the A-A cutaway views that adopt in the accompanying drawing 3 of embodiment 1 structure;
Accompanying drawing 5 is the A-A cutaway views that adopt in the accompanying drawing 3 of embodiment 2 structures;
Accompanying drawing 6 is a kind of structural representations of the first baffle in the utility model;
Accompanying drawing 7 is a kind of structural representations of diaphragm valve in the utility model;
Accompanying drawing 8 is a kind of structural representations of the second baffle in the utility model;
Accompanying drawing 9 is a kind of structural representations of dust cap in the utility model.
Shown in the figure: 1-transmitter unit module, the 2-launcher, the 21-frame, the 22-top board, plate among the 23-, the 24-base plate, the 25-support bar, 26-motor III, 27-gear-box II, the 28-cover, 29-motor II, the 3-mozzle, the 4-air deflector, 41-the first baffle, the 411-connecting hole, 412-water conservancy diversion entrance I, the 42-rotary inner core, the 421-opening, 43-gear-box I, the 44-diaphragm valve, 441-valve port I, 442-valve port II, the 443-connecting rod, the 444-valve gap, the 445-position-limited edge, the 446-breach, the 447-rocking bar, 45-the second baffle, 451-water conservancy diversion entrance II, the 46-dust cap, the 461-via hole, 5-motor I, the 6-transmitting tube, the 7-mounting interface, the upper interface of 71-, the 72-lower interface.
The specific embodiment
Below by embodiment, and by reference to the accompanying drawings, the technical solution of the utility model is described in further detail.
Embodiment 1:
Such as Figure of description 1,2, shown in 3, a kind of modularization is the frame launching tower altogether, 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 evenly are laid in around the mozzle 3, air deflector 4 is positioned at transmitting tube 6 and mozzle 3 bottoms, four transmitting tubes 6 all connect 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 base plate 24 connect transmitting tubes 6 and mozzle 3 and with transmitting tube 6 be matched in clearance, be connected with mozzle 3, top board 22, middle plate 23 is connected with base plate by support bar 25 connections, 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 is hinged by rotating shaft and frame 21, frame 21 is provided with motor II 29, motor II 29 is electrically connected with rotating shaft, frame 21 side's of being framves, four sides of frame 21 are equipped with mounting interface 7, mounting interface 7 comprises the upper interface 71 of being located at frame 21 upper ends and is located at the lower interface 72 of frame 21 lower ends, all be connected with foundation bolt on upper interface 71 and the lower interface 72, adjacent transmission unit module 1 is fixed by foundation bolt, such 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, the 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 is fixed on the first baffle 41 and with gear-box I 43 and is electrically connected, gear-box I 43 is connected with rotary inner core 42, the first baffle 41 is provided with four water conservancy diversion entrance I 412, the position of water conservancy diversion entrance I 412 and transmitting tube 6 is corresponding and be communicated with corresponding transmitting tube 6 one by one, four water conservancy diversion entrance I 412 evenly are laid in around the connecting hole 411 and with connecting hole 411 and are communicated with, rotary inner core 42 is provided with the pipe of opening 421 for the side, the in the same size of opening 421 and water conservancy diversion entrance I 412, the bottom surface of water conservancy diversion entrance I 412 is circular arc camber, the bottom surface of rotary inner core 42 is circular arc camber, the bottom surface of water conservancy diversion entrance the I 412 and bottom surface of rotary inner core 42 seamlessly transits 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.
Driving cover by the motor II opens, arming in the transmitting tube of each transmitting tube module, drive 360 ° of rotations of transmitting tube that ammunition is housed by the gear-box I by the motor III, the orientation that selection will be launched, behind the ammunition engine start, promoting ammunition flies out from transmitting tube, produced simultaneously air-flow enters air deflector from the transmitting tube lower port, when adopting one of air deflector scheme, the motor I drives rotary inner core by the gear-box I and rotates in the first baffle, select and be communicated with the lower port of the transmitting tube and the mozzle that are in emission state, air-flow is by the guiding of circular arc camber, enters smoothly mozzle and discharges from emitter.
Air deflector, mozzle and transmitting tube form the emission inner core of this emitter jointly, shown in Figure of description 3, it is whole to be the emission inner core, can middle taking-up suitable for reading from launcher in loading and unloading ammunition or maintenance process, and open and desirablely behind the cover go out to launch inner core.The transmitting tube of this guided missile launcher is pipe, is equally applicable to square tube.
Embodiment 2:
Such as Figure of description 1, shown in 2, a kind of modularization is the frame launching tower altogether, 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 evenly are laid in around the mozzle 3, air deflector 4 is positioned at transmitting tube 6 and mozzle 3 bottoms, four transmitting tubes 6 all connect 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 base plate 24 connect transmitting tubes 6 and mozzle 3 and with transmitting tube 6 be matched in clearance, be connected with mozzle 3, top board 22, middle plate 23 is connected with base plate by support bar 25 connections, 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 is hinged by rotating shaft and frame 21, frame 21 is provided with motor II 29, motor II 29 is electrically connected with rotating shaft, frame 21 side's of being framves, four sides of frame 21 are equipped with mounting interface 7, mounting interface 7 comprises the upper interface 71 of being located at frame 21 upper ends and is located at the lower interface 72 of frame 21 lower ends, all be connected with foundation bolt on upper interface 71 and the lower interface 72, adjacent transmission unit module 1 is fixed by foundation bolt, shown in Figure of description 5, air deflector 4 comprises diaphragm valve 44 and the second baffle 45, the second baffle 45 is positioned at transmitting tube 6 belows, diaphragm valve 44 is between the second baffle 45 and transmitting tube 6, shown in Figure of description 8, the second baffle 45 is provided with four water conservancy diversion entrance II 451, four water conservancy diversion entrance II 451 connections also are "X" shape distribution, the bottom surface of four water conservancy diversion entrance II 451 is circular arc camber and is connected smoothly, 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, also be provided with four valve port II 442 on the diaphragm valve 44, the position of valve port II 442 and transmitting tube 6 is corresponding and be communicated with corresponding transmitting tube 6 one by one, motor I 5 is stepper motor, motor I 5 has four and corresponding one by one with valve port II 442, the position of four valve port II 442 and four water conservancy diversion entrance II 451 is corresponding and be communicated with corresponding water conservancy diversion entrance II 451 one by one, valve port II 442 is provided with valve gap 444, valve port II 442 places are provided with and can hold " n " shape position-limited edge 445 that valve gap 444 passes, 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 that is active in " V " v notch v 446, connecting rod 443 is connected with the center of valve gap 444, 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, and the position of valve port I 441 and valve port II 442 is corresponding one by one with five via holes 461.
Driving cover by the motor II opens, arming in the transmitting tube of each transmitting tube module, drive 360 ° of rotations of transmitting tube that ammunition is housed by the gear-box I by the motor III, the orientation that selection will be launched, behind the ammunition engine start, promoting ammunition flies out from transmitting tube, produced simultaneously air-flow enters air deflector from the transmitting tube lower port, when adopt the air deflector scheme two the time, the motor I drives by connecting rod valve gap is opened and closed, the valve port II can realize opening or closure by the effect of four groups of valve members of diaphragm valve, and is communicated with transmitting tube and mozzle by the second baffle.Air-flow enters the second baffle, and the guide effect by circular arc camber enters smoothly mozzle and discharges from emitter.This moment, emission was finished with the water conservancy diversion process, the emission of applicable equally other each transmitting tube module of two schemes.
Air deflector, mozzle and transmitting tube form the emission inner core of this emitter jointly, shown in Figure of description 3, it is whole to be the emission inner core, can middle taking-up suitable for reading from launcher in loading and unloading ammunition or maintenance process, and open and desirablely behind the cover go out to launch inner core.The transmitting tube of this guided missile launcher is pipe, is equally applicable to square tube.
The guided missile VLS adopts modularized design, and is simple in structure, and reliability is high, and it has also generally used the isolation technique of redundancy, except the forfeiture of warship power source, there is not the Single Point of Faliure that affects system's fighting capacity, whole system is improved reliability for this and availability is all helpful.In addition, in the guided missile VLS, every piece of guided missile is encapsulated in before emission in separately the storing and transporting box all the time, and effective environmental protection and loading and unloading protection are provided, and has greatly improved the reliability of guided missile.Storing and transporting box is loaded on below the deck, and the above has the protection of armoring hatchcover, can avoid being subjected to the destruction of enemy firepower.
This launching tower adopts modular construction, be spliced by a plurality of transmitter unit modules, many group transmitting tubes share a mozzle, transmit direction can independently be selected in each transmitting tube unit, ammunition spontaneous emission pipe launches away, the high-temperature fuel gas that produces passes through air deflector, enter in the mozzle and discharge, this module can be carried out different assemblings and change to be applicable to different warship types according to mission requirements and naval vessel condition, save required complex operations and the control assembly of formula bullet storehouse, deck filling emission, improved the reliability of system, reduced the maintenance work amount, reduced naval vessels and taken up room, the generalization of guided missile launcher has realized the altogether frame emission of multiple guided missile.
Should be understood that this embodiment only is used for explanation the utility model and is not used in the scope of the present utility model that limits.Should be understood that in addition those skilled in the art can make various changes or modifications the utility model after the content of having read the utility model instruction, these equivalent form of values fall within the application's appended claims limited range equally.
Claims (10)
1. a modularization is total to the frame launching tower, it is characterized in that, it is spliced by a plurality of transmitter unit modules (1), transmitter unit module (1) comprises by launcher (2) fixing mozzle (3), air deflector (4), motor I (5) and several transmitting tubes (6), air deflector (4) is driven by motor I (5), several transmitting tubes (6) connect with mozzle (3) by air deflector (4), launcher (2) is provided with mounting interface (7), and adjacent transmission unit module (1) is by removable being connected of mounting interface (7).
2. a kind of modularization according to claim 1 is total to the frame launching tower, it is characterized in that, described air deflector (4) is positioned at transmitting tube (6) and mozzle (3) bottom, transmitting tube (6) has four, four transmitting tubes (6) evenly are laid in mozzle (3) on every side, and four transmitting tubes (6) all connect with mozzle (3) by air deflector (4).
3. a kind of modularization according to claim 2 is total to the frame launching tower, it is characterized in that, described air deflector (4) comprises the first baffle (41), rotary inner core (42) and gear-box I (43), the 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 fixed on the first baffle (41) and upward and with gear-box I (43) is electrically connected, gear-box I (43) is connected with rotary inner core (42), the first baffle (41) is provided with four water conservancy diversion entrance I (412), the position of water conservancy diversion entrance I (412) and transmitting tube (6) is corresponding and be communicated with corresponding transmitting tube (6) one by one, four water conservancy diversion entrance I (412) evenly are laid in connecting hole (411) on every side and are communicated with connecting hole (411), rotary inner core (42) is provided with the pipe of opening (421) for the side, the in the same size of opening (421) and water conservancy diversion entrance I (412), rotary inner core (42) is corresponding with the position of mozzle (3) and be communicated with mozzle (3).
4. a kind of modularization according to claim 2 is total to the frame launching tower, it is characterized in that, described air deflector (4) comprises diaphragm valve (44) and the second baffle (45), the second baffle (45) is positioned at transmitting tube (6) below, diaphragm valve (44) is positioned between the second baffle (45) and the transmitting tube (6), the second baffle (45) is provided with four water conservancy diversion entrance II (451), four water conservancy diversion entrance II (451) are communicated with and are "X" shape distribution, the bottom surface of four water conservancy diversion entrance 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), also be provided with four valve port II (442) on the diaphragm valve (44), the position of valve port II (442) and transmitting tube (6) is corresponding and be communicated with corresponding transmitting tube (6) one by one, motor I (5) has four and corresponding one by one with valve port II (442), the position of four valve port II (442) and four water conservancy diversion entrance II (451) is corresponding and be communicated with corresponding water conservancy diversion entrance II (451) one by one, valve port II (442) is provided with valve gap (444), valve port II (442) is located to be provided with and can be held " n " shape position-limited edge (445) that valve gap (444) passes, 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) that is active in " V " v notch v (446), and connecting rod (443) is connected with the center of valve gap (444).
5. a kind of modularization according to claim 4 is total to the frame launching tower, 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 the diaphragm valve (44), dust cap (46) is provided with five via holes (461), and the position of valve port I (441) and valve port II (442) is corresponding one by one with five via holes (461).
6. according to claim 1 and 2 or 3 or 4 or 5 described a kind of modularizations frame launching tower altogether, 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) connect transmitting tube (6) and with transmitting tube (6) be matched in clearance, be connected with mozzle (3), top board (22), middle plate (23) is connected 24 with base plate) connect by support bar (25), 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), and gear-box II (27) is connected with transmitting tube (6).
7. a kind of modularization according to claim 6 is total to the frame launching tower, it is characterized in that, the top of described frame (21) is provided with cover (28), one end of cover (28) is hinged by rotating shaft and frame (21), frame (21) is provided with motor II (29), and motor II (29) is electrically connected with rotating shaft.
8. a kind of modularization according to claim 7 is total to the frame launching tower, it is characterized in that, described 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) of being located at frame (21) upper end and the lower interface (72) of being located at frame (21) lower end, all be connected with foundation bolt on upper interface (71) and the lower interface (72), adjacent transmission unit module (1) is fixed by foundation bolt.
9. a kind of modularization according to claim 3 is total to the frame launching tower, it is characterized in that, the bottom surface of described water conservancy diversion entrance I (412) is circular arc camber, the bottom surface of rotary inner core (42) is circular arc camber, and the bottom surface of the bottom surface of water conservancy diversion entrance I (412) and rotary inner core (42) seamlessly transits and the two surrounds a semicircle cavity.
10. according to claim 1 and 2 or 3 or 4 or 5 or 9 described a kind of modularizations frame launching tower altogether, it is characterized in that described motor I (5) is stepper motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220578458 CN202903017U (en) | 2012-11-05 | 2012-11-05 | Modular common-frame vertical launching device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220578458 CN202903017U (en) | 2012-11-05 | 2012-11-05 | Modular common-frame vertical launching device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202903017U true CN202903017U (en) | 2013-04-24 |
Family
ID=48123677
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220578458 Withdrawn - After Issue CN202903017U (en) | 2012-11-05 | 2012-11-05 | Modular common-frame vertical launching device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202903017U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103808206A (en) * | 2012-11-05 | 2014-05-21 | 杭州航海仪器有限公司 | Modularization support-sharing vertical launch device |
| CN109747860A (en) * | 2019-03-08 | 2019-05-14 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of grid rudder wing suitable for canister launch mixes aerodynamic arrangement and design method |
| 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 |
-
2012
- 2012-11-05 CN CN 201220578458 patent/CN202903017U/en not_active Withdrawn - After Issue
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103808206A (en) * | 2012-11-05 | 2014-05-21 | 杭州航海仪器有限公司 | Modularization support-sharing vertical launch device |
| CN103808206B (en) * | 2012-11-05 | 2015-09-02 | 杭州航海仪器有限公司 | A kind of modularization Common-frame vertical launch device |
| CN104897002A (en) * | 2012-11-05 | 2015-09-09 | 杭州航海仪器有限公司 | Modular common-frame launch device |
| CN109747860A (en) * | 2019-03-08 | 2019-05-14 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of grid rudder wing suitable for canister launch mixes aerodynamic arrangement and design method |
| CN109747860B (en) * | 2019-03-08 | 2021-01-15 | 中国空气动力研究与发展中心计算空气动力研究所 | Grid rudder wing hybrid aerodynamic layout and design method suitable for box type launching |
| 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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103808206B (en) | A kind of modularization Common-frame vertical launch device | |
| US8468924B2 (en) | Stowable elevating trainable launcher (SETL) | |
| CN202903017U (en) | Modular common-frame vertical launching device | |
| CN109519280B (en) | Turboprop direct-injection hybrid multistage-power underwater high-speed propeller and control method | |
| CN103968714A (en) | Defending bomb device hung in air | |
| RU2531421C1 (en) | Universal combat module | |
| GB2472478A (en) | Launcher with multiple barrels | |
| CN105241314B (en) | Novel multifunctional military combat tank | |
| CN110108161B (en) | Missile launching device | |
| CN219277811U (en) | Can section of thick bamboo penetrate foldable unmanned aerial vehicle | |
| RU94325U1 (en) | UNIVERSAL MODULAR ROCKET WEAPON COMPLEX | |
| CN115655010A (en) | Single-vehicle integrated short-range air defense missile weapon system | |
| CN206235241U (en) | A kind of aerial howitzer launch craft | |
| CN212902890U (en) | Tank flat high dual-purpose high-speed weapon system | |
| CN201081604Y (en) | Front-loaded caseless ammunition rotary firing chamber | |
| CN102806984A (en) | Separation type defensive armor for naval vessel and ship | |
| RU2287764C1 (en) | Articulated fighting vehicle | |
| CN202609063U (en) | Unmanned submarine | |
| CN219798106U (en) | Series smoke screen transmitting device | |
| CN113959256B (en) | Protective missile launching box and remote control weapon station | |
| RU2238509C1 (en) | Articulated fighting vehicle | |
| CN219277812U (en) | Can section of thick bamboo shoot horizontal folding unmanned aerial vehicle | |
| KR102129776B1 (en) | Launching apparatus for weapon using electromagnet | |
| Liu et al. | Analysis of the Development Direction of Small-medium Caliber Artillery | |
| RU2612037C2 (en) | Reconnaissance and fire weapon system of tank armament |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20130424 Effective date of abandoning: 20150902 |
|
| RGAV | Abandon patent right to avoid regrant |