CN104897002B - Modularity Common-frame vertical launch device - Google Patents

Modularity Common-frame vertical launch device Download PDF

Info

Publication number
CN104897002B
CN104897002B CN201510243905.6A CN201510243905A CN104897002B CN 104897002 B CN104897002 B CN 104897002B CN 201510243905 A CN201510243905 A CN 201510243905A CN 104897002 B CN104897002 B CN 104897002B
Authority
CN
China
Prior art keywords
frame
motor
transmitting tube
mozzle
valve
Prior art date
Application number
CN201510243905.6A
Other languages
Chinese (zh)
Other versions
CN104897002A (en
Inventor
祝凌云
应跃明
盛强观
Original Assignee
杭州航海仪器有限公司
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 杭州航海仪器有限公司 filed Critical 杭州航海仪器有限公司
Priority to CN201210437262.5A priority Critical patent/CN103808206B/en
Publication of CN104897002A publication Critical patent/CN104897002A/en
Application granted granted Critical
Publication of CN104897002B publication Critical patent/CN104897002B/en

Links

Abstract

The modularity Common-frame vertical launch device of a kind of shipborne weapon of the present invention.This device is spliced by multiple transmitter unit modules, including the mozzle fixed by launcher, air deflector, motor I and several transmitting tubes, air deflector is driven by motor I, and launcher is provided with mounting interface, and adjacent transmission unit module is connected by mounting interface is removable.The invention has the beneficial effects as follows: 1, possess the Common-frame vertical launch function of independently rotary transmitting tube module, modularized design, according to the on-demand configuration transmitter unit module of naval vessel installing space and bearing capacity, the manufacturing cycle can be shortened, it is simple to install and update;2, stealth is good, can omnidirectional emission half guided munition, adopt after vertical launching technology, the impact of naval vessel superstructure and other battle stations can not be subject to, give full play to firepower, expand firing area, target is implemented comprehensive attack;3, simple in construction, Operation and Maintenance easily, at the bottom of manufacturing expense, ship navigation stability is good.

Description

Modularity Common-frame vertical launch device

The patent application of the present invention is application number: 201210437262.5, denomination of invention: a kind of modularity Common-frame vertical launch device, 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 the modularity Common-frame vertical launch device of a kind of shipborne weapon.

Background technology

Carrier-borne VLS is a kind of missile release system being used on submarine and some water surface naval vessel, results from the emission system of ballistic missile the earliest, has the advantage such as high emissivity, big, the non-emissive blind area of bullet-loading capacity.Current carrier-borne Vertical Launch mode has been widely used in the naval equipment of countries in the world, starts guided missile vertical launching technology from strategic missile and reaches its maturity, and launching tower just develops towards the direction of versatility motility.Missile release system is generally divided into pop-up and heat emission two ways, 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 aerofluxus, the advantage of heat emission system is that efficiency is higher, it is possible to saves the volume and weight of emission system and reduces its maintenance cost.

Traditional guided missile launcher is made up of thousands of moving components, and arbitrary link breaks down and is likely to make 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, it is provided with motor 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, it is provided with fuel cell and high-energy battery, described fuel cell and high-energy battery be connected with the power end of motor respectively through switching controller.The moving component of the missile launcher that this patent provides integrates one complete combat gear of composition, but owing to composition component is more, dismounting is inconvenience extremely, maintenance trouble, quantity and the position of missile gear can not be arranged according to fight demand simultaneously, taking up room relatively big, it is inflexible to use, underaction.

Summary of the invention

The component that the present invention is primarily directed to existing for existing guided missile launcher is more, structure is complicated, the problem of relatively big, dismounting and the inconvenient maintenance, use underaction of taking up room, a kind of simple in construction is provided, the degree of modularity is high, take up room little, dismounting and easy to maintenance, can according to the modularity Common-frame vertical launch device of fight demand flexible arrangement.

The above-mentioned technical problem of the present invention is addressed mainly by following technical proposals: a kind of modularity Common-frame vertical launch device, it is spliced by multiple transmitter unit modules, transmitter unit module includes mozzle, air deflector, motor I and several transmitting tubes fixed by launcher, air deflector is driven by motor I, several transmitting tubes are coupled 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 uniformly laid in around mozzle, and four transmitting tubes couple with mozzle each through air deflector;nullDescribed air deflector includes diaphragm valve and baffle,Baffle is positioned at below transmitting tube,Diaphragm valve is between baffle and transmitting tube,Baffle is provided with four directed fluid inlet II,Four directed fluid inlet II connect 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 connects with mozzle,Diaphragm valve is additionally provided with four valve ports II,Valve port II and the position one_to_one corresponding of transmitting tube and connect with corresponding transmitting tube,Motor I have four and with valve port II one_to_one corresponding,Four valve ports II connect with the position one_to_one corresponding of four directed fluid inlet II and with corresponding directed fluid inlet II,Valve port II is provided with valve gap,Valve port II place is provided with " n " the shape position-limited edge that can hold valve gap traverse,Valve gap is provided with " V " shape breach,Motor I is connected to rocking bar,Rocking bar is hinged with the connecting rod being active in " V " shape breach,Connecting rod is connected with the center of valve gap.

Air deflector, mozzle and transmitting tube collectively constitute the transmitting inner core of this discharger, launch inner core to take out from launcher, this launching tower adopts modular construction, it is spliced by multiple transmitter unit modules, many group transmitting tubes share a mozzle, each transmitting tube unit can independently selected transmitting direction, ammunition spontaneous emission pipe launches away, the high-temperature fuel gas produced passes through air deflector, enter in mozzle and discharge, air deflector is driven by motor I, this module can carry out different assemblings according to mission requirements and naval vessel condition and change with suitable in different warship types, eliminate the filling of Shi Dan storehouse, deck launch required complex operations and control parts, 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 mozzles, each transmitting tube unit can independently selected transmitting direction, four groups of transmitting tubes are connected with mozzle each through air deflector.The program is additionally arranged diaphragm valve between baffle and transmitting tube, motor I drives rocking bar, rocking bar drivening rod, connecting rod drives valve gap to move in position-limited edge, the position-limited edge mobile limited location effect to valve gap, when valve gap moves to corresponding valve port II, this valve port II closes, gas extraction system is closed, when valve gap removes 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 passes through valve port II, enter in directed fluid inlet II, gas in directed fluid inlet II enters in mozzle again through valve port I, 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 vias, the position of valve port I and valve port II and five via 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; so as to cisco unity malfunction, thus in scheme two, add dust cap on diaphragm valve top; via on dust cap is used for connecting valve port and transmitting tube or mozzle, and dust cap can stop solid particle to enter diaphragm valve.

As preferably, described launcher includes frame and is arranged in the top board of frame, plate and base plate, top board, middle plate and base plate are connected to transmitting tube and the top of 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, being connected with mozzle, top board, middle plate and base plate are connected by support bar, and middle plate is provided with motor III and gear-box II, motor III electrically connects with gear-box II, and gear-box II is connected with transmitting tube.Top board, middle plate and base plate connect transmitting tube and mozzle, motor III driven gear case II, and the operation of motor III is converted into the rotary motion of transmitting tube by gear-box II, it is simple to complete the emission process of guided missile.

As preferably, the top of described frame is provided with cover, and one end of cover is hinged by rotating shaft and frame, and frame is provided with motor II, and motor II electrically connects with rotating shaft.For preventing foreign body from entering transmitting tube and mozzle, can arranging cover at frame top, cover is hinged with frame, and motor II drives cover to overturn, and can pass through motor II and control the opening and closing of cover.

As preferably, the described frame side of being frame, four sides of frame are equipped with mounting interface, and mounting interface includes the upper interface being located at frame upper end and the lower interface being located at frame lower end, being respectively connected with foundation bolt on upper interface and lower interface, adjacent transmission unit module is fixed by foundation bolt.Four sides of frame are equipped with mounting interface, thus can carry out different assemblings according to mission requirements and naval vessel condition and change with suitable in different warship types, and combined and instant is flexible;Adjacent transmission unit module is fixed by foundation bolt, and fixation is reliable, easy accessibility.

As preferably, described motor I is motor.Motor I is motor, and along with different transmitting tube sequential transmission guided missiles, motor I can turn an angle according to instruction, it is ensured that the opening of rotary inner core and directed fluid inlet I are connected.

Therefore, the invention has the beneficial effects as follows: 1, possess the Common-frame vertical launch function of independently rotary transmitting tube module, adopt modularized design, it is possible to according to the on-demand configuration transmitter unit module of naval vessel installing space and bearing capacity, shorten the manufacturing cycle, it is simple to install and update;2, stealth is good, can omnidirectional emission half guided munition, after adopting vertical launching technology, the impact of naval vessel superstructure and other battle stations can not be subject to, give full play to firepower, expand firing area, target is implemented comprehensive attack, and the dome-type spatial domain of 360 ° can be covered, in all orientation identical can emission probability, naval vessel operation respond, it may be achieved implement to attack to multiple target;3, simple in construction, Operation and Maintenance easily, at the bottom of manufacturing expense, ship navigation stability is good, the present invention is especially suitable for 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 single a kind of structural representation organizing transmitter unit module in the present invention;

Accompanying drawing 3 is a kind of structural representation launching inner core in the present invention;

Accompanying drawing 4 is the A-A sectional view in the accompanying drawing 3 of employing embodiment 1 structure;

Accompanying drawing 5 is the A-A sectional view in the accompanying drawing 3 of employing embodiment 2 structure;

Accompanying drawing 6 is a kind of structural representation of diversion seat in the present invention;

Accompanying drawing 7 is a kind of structural representation of diaphragm valve in the present invention;

Accompanying drawing 8 is a kind of structural representation of baffle in the present invention;

Accompanying drawing 9 is a kind of structural representation of dust cap in the present invention.

nullShown 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-diversion seat、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-baffle、451-directed fluid inlet II、46-dust cap、461-via、5-motor I、6-transmitting tube、7-mounting interface、The upper interface of 71-、72-lower interface.

Detailed description of the invention

By the examples below, and in conjunction with accompanying drawing, technical scheme is described in further detail.

Embodiment 1:

nullSuch as Figure of description 1、2、Shown in 3,A kind of modularity Common-frame vertical launch device,It is spliced by two groups of transmitter unit modules 1,Transmitter unit module 1 includes launcher 2、Mozzle 3、Air deflector 4、Motor I 5 and four transmitting tubes 6,Four transmitting tubes 6 are uniformly laid in around mozzle 3,Air deflector 4 is positioned at bottom transmitting tube 6 and mozzle 3,Four transmitting tubes 6 couple with mozzle 3 each through air deflector 4,Launcher 2 includes 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 transmitting tube 6 and the top of 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,It is connected with mozzle 3,Top board 22、Middle plate 23 and base plate 24 are connected by support bar 25,Middle plate 23 is provided with motor III 26 and gear-box II 27,Motor III 26 electrically connects 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 electrically connects with rotating shaft,Frame 21 side of being frame,Four sides of frame 21 are equipped with mounting interface 7,Mounting interface 7 includes 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 respectively connected with foundation bolt,Adjacent transmission unit module 1 is fixed by foundation bolt,Such as Figure of description 4、Shown in 6,Air deflector 4 includes diversion seat 41、Rotary inner core 42 and gear-box I 43,Diversion seat 41 is provided with connecting hole 411,Rotary inner core 42 be positioned at connecting hole 411 and with diversion seat 41 matched in clearance,Motor I 5 is motor,Motor I 5 is fixed on diversion seat 41 and electrically connects with gear-box I 43,Gear-box I 43 is connected with rotary inner core 42,Diversion seat 41 is provided with four directed fluid inlet I 412,Directed fluid inlet I 412 connects with the position one_to_one corresponding of transmitting tube 6 and with corresponding transmitting tube 6,Four directed fluid inlet I 412 are uniformly laid in around connecting hole 411 and connect 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 the bottom surface of directed fluid inlet I 412 and 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 connects with mozzle 3.

Cover is driven to open by motor II, arming in the transmitting tube of each transmitting tube module, the transmitting tube 360 ° rotation equipped with ammunition is driven by gear-box II by motor III, the orientation that selection to be launched, when after ammunition engine start, ammunition is promoted 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 diversion seat by gear-box I, select and connect the lower port of transmitting tube and the mozzle being in emission state, the air-flow guiding by circular arc camber, enter mozzle smoothly and discharge from discharger.

Air deflector, mozzle and transmitting tube collectively constitute the transmitting inner core of this discharger, as shown in Figure of description 3, it generally launches inner core, handling ammunition or maintenance process in can middle taking-up suitable for reading from launcher, can be taken off after opening cover launch inner core.The transmitting tube of this guided missile launcher is pipe, is equally applicable to square tube.

Embodiment 2:

nullSuch as Figure of description 1、Shown in 2,A kind of modularity Common-frame vertical launch device,It is spliced by two groups of transmitter unit modules 1,Transmitter unit module 1 includes launcher 2、Mozzle 3、Air deflector 4、Motor I 5 and four transmitting tubes 6,Four transmitting tubes 6 are uniformly laid in around mozzle 3,Air deflector 4 is positioned at bottom transmitting tube 6 and mozzle 3,Four transmitting tubes 6 couple with mozzle 3 each through air deflector 4,Launcher 2 includes 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 transmitting tube 6 and the top of 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,It is connected with mozzle 3,Top board 22、Middle plate 23 and base plate 24 are connected by support bar 25,Middle plate 23 is provided with motor III 26 and gear-box II 27,Motor III 26 electrically connects 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 electrically connects with rotating shaft,Frame 21 side of being frame,Four sides of frame 21 are equipped with mounting interface 7,Mounting interface 7 includes 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 respectively connected with foundation bolt,Adjacent transmission unit module 1 is fixed by foundation bolt,As shown in Figure of description 5,Air deflector 4 includes diaphragm valve 44 and baffle 45,Baffle 45 is positioned at below transmitting tube 6,Diaphragm valve 44 is between baffle 45 and transmitting tube 6,As shown in Figure of description 8,Baffle 45 is provided with four directed fluid inlet II 451,Four directed fluid inlet II 451 connect 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 connects with mozzle 3,Diaphragm valve 44 is additionally provided with four valve ports II 442,Valve port II 442 connects with the position one_to_one corresponding of transmitting tube 6 and with corresponding transmitting tube 6,Motor I 5 is motor,Motor I 5 have four and with valve port II 442 one_to_one corresponding,Four valve ports II 442 connect with the position one_to_one corresponding of four directed fluid inlet II 451 and 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 " the shape position-limited edge 445 that can hold valve gap 444 traverse,Valve gap 444 is provided with " V " shape breach 446,Motor I 5 is connected to rocking bar 447,Rocking bar 447 is hinged with the connecting rod 443 being active in " V " shape breach 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 vias 461,The position of valve port I 441 and valve port II 442 and five via 461 one_to_one corresponding.

Cover is driven to open by motor II, arming in the transmitting tube of each transmitting tube module, the transmitting tube 360 ° rotation equipped with ammunition is driven by gear-box II by motor III, the orientation that selection to be launched, when after ammunition engine start, ammunition is promoted to fly out from transmitting tube, the air-flow simultaneously produced enters air deflector from transmitting tube lower port, when adopting the 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, it may be achieved opens or closes, and by baffle connection transmitting tube and mozzle.Air-flow enters baffle, enters mozzle smoothly by the guide effect of circular arc camber and discharges from discharger.Now launch and complete with water conservancy diversion process, the transmitting of two schemes other each transmitting tube module equally applicable.

Air deflector, mozzle and transmitting tube collectively constitute the transmitting inner core of this discharger, as shown in Figure of description 3, it generally launches inner core, handling ammunition or maintenance process in can middle taking-up suitable for reading from launcher, can be taken off after opening cover 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, simple in construction, and reliability is high, and it has also generally used the isolation technique of redundancy, except warship power source is lost, being absent from the Single Point of Faliure of influential system fighting capacity, whole system is improved reliability for this and availability is all helpful.Additionally, in guided missile VLS, every piece of guided missile is encapsulated in respective storing and transporting box before transmission all the time, it is provided that effective environmental conservation and handling protection, substantially increase the reliability of guided missile.Storing and transporting box is loaded on below deck, has the protection of armoring hatchcover above, it is possible to avoid being subject to the destruction of enemy firepower.

This launching tower adopts modular construction, it is spliced by multiple transmitter unit modules, many group transmitting tubes share a mozzle, each transmitting tube unit can independently selected transmitting direction, ammunition spontaneous emission pipe launches away, the high-temperature fuel gas produced passes through air deflector, enter in mozzle and discharge, this module can carry out different assemblings according to mission requirements and naval vessel condition and change with suitable in different warship types, eliminate the filling of Shi Dan storehouse, deck launch required complex operations and control parts, 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 merely to illustrate the present invention rather than restriction the scope of the present invention.In addition, it is to be understood that after having read the content that the present invention lectures, the present invention can be made various changes or modifications by those skilled in the art, and these equivalent form of values fall within the application appended claims limited range equally.

Claims (6)

1. a modularity Common-frame vertical launch device, it is characterized in that, it is spliced by multiple transmitter unit modules (1), transmitter unit module (1) includes mozzle (3), air deflector (4), motor I (5) and several transmitting tubes (6) of being fixed by launcher (2), air deflector (4) is driven by motor I (5), several transmitting tubes (6) are coupled 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, and transmitting tube (6) has four, and four transmitting tubes (6) are uniformly laid in mozzle (3) around, and four transmitting tubes (6) couple with mozzle (3) each through air deflector (4);nullDescribed air deflector (4) includes diaphragm valve (44) and baffle (45),Baffle (45) is positioned at transmitting tube (6) lower section,Diaphragm valve (44) is positioned between baffle (45) and transmitting tube (6),Baffle (45) is provided with four directed fluid inlet II (451),Four directed fluid inlet II (451) connect 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 connects with mozzle (3),Diaphragm valve (44) is additionally provided with four valve ports II (442),Valve port II (442) and the position one_to_one corresponding of transmitting tube (6) and connect with corresponding transmitting tube (6),Motor I (5) have four and with valve port II (442) one_to_one corresponding,Four valve ports II (442) connect with the position one_to_one corresponding of four directed fluid inlet II (451) and 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 " the shape position-limited edge (445) that can hold valve gap (444) traverse,Valve gap (444) is provided with " V " shape breach (446),Motor I (5) is connected to rocking bar (447),Rocking bar (447) is hinged with the connecting rod (443) being active in " V " shape breach (446),Connecting rod (443) is connected with the center of valve gap (444).
2. modularity Common-frame vertical launch device 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 vias (461), the position of valve port I (441) and valve port II (442) and five via (461) one_to_one corresponding.
null3. modularity Common-frame vertical launch device according to claim 1 and 2,It is characterized in that,Described launcher (2) includes 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 transmitting tube (6) and the top of 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),It is connected with mozzle (3),Top board (22)、Middle plate (23) and base plate (24) are connected by support bar (25),Middle plate (23) is provided with motor III (26) and gear-box II (27),Motor III (26) electrically connects with gear-box II (27),Gear-box II (27) is connected with transmitting tube (6).
4. modularity Common-frame vertical launch device 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) is hinged by rotating shaft and frame (21), frame (21) is provided with motor II (29), and motor II (29) electrically connects with rotating shaft.
5. modularity Common-frame vertical launch device according to claim 4, 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) includes the upper interface (71) being located at frame (21) upper end and the lower interface (72) being located at frame (21) lower end, being respectively connected with foundation bolt on upper interface (71) and lower interface (72), adjacent transmission unit module (1) is fixed by foundation bolt.
6. modularity Common-frame vertical launch device according to claim 1 and 2, it is characterised in that described motor I (5) is motor.
CN201510243905.6A 2012-11-05 2012-11-05 Modularity Common-frame vertical launch device CN104897002B (en)

Priority Applications (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

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
CN201210437262.5A Division CN103808206B (en) 2012-11-05 2012-11-05 A kind of modularization Common-frame vertical launch device

Publications (2)

Publication Number Publication Date
CN104897002A CN104897002A (en) 2015-09-09
CN104897002B true CN104897002B (en) 2016-07-13

Family

ID=50705330

Family Applications (2)

Application Number Title Priority Date Filing Date
CN201510243905.6A CN104897002B (en) 2012-11-05 2012-11-05 Modularity Common-frame vertical launch device
CN201210437262.5A CN103808206B (en) 2012-11-05 2012-11-05 A kind of modularization Common-frame vertical launch device

Family Applications After (1)

Application Number Title Priority Date Filing Date
CN201210437262.5A CN103808206B (en) 2012-11-05 2012-11-05 A kind of modularization Common-frame vertical launch device

Country Status (1)

Country Link
CN (2) CN104897002B (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105423814B (en) * 2015-11-01 2017-10-24 宁波市鄞州发辉机械科技有限公司 A kind of multifunction missile emitter
CN105910492B (en) * 2016-04-15 2017-10-24 中国运载火箭技术研究院 A kind of vertical heat emission inner circle foreign side of aerodynamic missile is just as heart barrel structure
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
CN109353476A (en) * 2018-10-31 2019-02-19 沪东中华造船(集团)有限公司 A kind of carrier-borne Shell-feeding system installation method collecting ammunition transhipment, ammunition feed, filling and transmitting
CN110131076B (en) * 2019-04-23 2020-05-08 湖北三江航天江北机械工程有限公司 Modularized forming method of fluid director
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

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2715998B1 (en) * 1994-02-10 1996-04-26 Lacroix E Tous Artifices Multi-thrower system with pyrotechnic effect.
AT408690B (en) * 1996-06-20 2002-02-25 Dynamit Nobel Graz Gmbh Stealfire protection, especially grenade launchers
NO970621D0 (en) * 1996-09-17 1997-02-11 Forsvarets Forsknings Evolved means for ejection of röykhåndgranat
US5847307A (en) * 1997-06-24 1998-12-08 Northrop Grumman Corporation Missile launcher apparatus
FR2873197B1 (en) * 2004-07-13 2006-10-27 Mbda France Sa Launcher of missiles
US7350451B2 (en) * 2005-11-10 2008-04-01 Lockheed Martin Corporation Apparatus comprising an exhaust duct and anti-fratricide shield
CN201096482Y (en) * 2007-10-30 2008-08-06 姜春 Deep sea submarine missile launcher
CN201680764U (en) * 2010-05-28 2010-12-22 吴长明 Missile launching device
CN202141380U (en) * 2011-03-26 2012-02-08 赵文志 Automatic-aiming secondary-speedup matrix cannon
CN202903017U (en) * 2012-11-05 2013-04-24 杭州航海仪器有限公司 Modular common-frame vertical launching device

Also Published As

Publication number Publication date
CN104897002A (en) 2015-09-09
CN103808206A (en) 2014-05-21
CN103808206B (en) 2015-09-02

Similar Documents

Publication Publication Date Title
US8281697B2 (en) Method for launching naval mines
US7549365B2 (en) Electromagnetic missile launcher
US8051637B2 (en) Heat energy recapture and recycle and its new applications
JP2779287B2 (en) Method of forming modular solid fuel launch vehicle facility
US6833804B2 (en) Operation of a decoy against threats
KR101575720B1 (en) Weapon firing device of submarine
CN103922051B (en) Dangerous chemical the container datonation-inhibition equipment of lazy envelope and defence method
JP4058042B2 (en) Missile launcher cells with exhaust gas intake ducts and rows of these missile launcher cells
US9297626B2 (en) Aquatic vessel fiber optic network
CN104864774B (en) A kind of guided missile is from ejection firing device
CN1628053A (en) System and method for enhancing the payload capacity, carriage efficiency, and adaptive flexibility of external stores mounted on an aerial vehicle
CN1165740C (en) Decoy
CN106477047B (en) A kind of aerial howitzer launch craft
DK2609390T3 (en) Autonomous system for controlling ammunitionsgas
GB2025009A (en) Airborne weapons system
US8468924B2 (en) Stowable elevating trainable launcher (SETL)
CN105021089B (en) High initial speed projectile transmitting device and launching technique
CN101726219B (en) Multielement seeding combustion explosion type rainfall-increasing and anti-hail rocket
CN202828057U (en) Aircraft carrier capable of adjusting carried airplanes and submarines and warships manoeuvrably
RU2309358C2 (en) Armament platform moving by air
CN104554675A (en) Underwater dish vehicle
ES2398001A1 (en) Adaptable launching system
CN103868414B (en) Bottom deflation type caseless cartridge
CN101725432A (en) Jet engine of seaplane
CN103183132A (en) Power source unit body for ejecting, aircraft carrier gas and steam ejector and ejecting method

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant