CN105910492A - Winged missile vertical thermal emission inner-round outer-square concentric cylinder structure - Google Patents
Winged missile vertical thermal emission inner-round outer-square concentric cylinder structure Download PDFInfo
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- CN105910492A CN105910492A CN201610237423.4A CN201610237423A CN105910492A CN 105910492 A CN105910492 A CN 105910492A CN 201610237423 A CN201610237423 A CN 201610237423A CN 105910492 A CN105910492 A CN 105910492A
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- missile
- inner core
- urceolus
- barrel
- vertical thermal
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a winged missile vertical thermal emission inner-round outer-square concentric cylinder structure comprising an outer barrel, an inner barrel, reinforcing ribs, a diversion cone, stop piece support plates and a diversion plate; the inner barrel is a non-sealing barrel formed by four arc panels, wherein the non-sealing zone of the inner barrel forms a motion channel for the missile and missile wings; the outer barrel is a square barrel formed by splicing four square panels, wherein the outer barrel inner wall is fixed with the inner barrel, and a gas flow exhaust gap is arranged between the outer barrel and the inner barrel; the diversion cone is arranged on the inner side of the bottom of the outer barrel, and is a conical symmetry structure; a missile engine ejects the gas flow applied on the diversion cone, and the ejected gas flow is backflowed by the diversion cone so as to enter the gap between the outer barrel and the inner barrel, thus exhausting the gas flow. The outer barrel is designed into a square shape, thus improving the gas flow exhaust gap between the outer barrel and the inner barrel; compared with a concentric cylinder with an inner round barrel and an outer round barrel, the winged missile vertical thermal emission inner-round outer-square concentric cylinder structure can maximumly effectively improve gas flow exhaust space area, thus better adapting to large missile diameter missile concentric cylinder emission.
Description
Technical field
The present invention relates to a kind of aerodynamic missile vertical thermal and launch inner circle foreign side just as heart barrel structure, belong to MISSILE LAUNCHING technology
Field.
Background technology
Cartridge type discharger is applicable to carrier-borne VLS with one heart, uses the inner/outer tube of arranged concentric to lead as carrier-borne
The storage of bullet, transport, launch container.For the guided missile of heat emission, the high temperature produced during transmitting, high-speed fuel gas, through bottom
After guiding device deflection, upwards discharged by the annular space between two-layer cylinder, it is no longer necessary to the combustion gas that many pieces of guided missiles share
Tapping equipment.Traditional concentric tube structure is many to be made up of two concentric drums, and inner core is complete cylindrical structure, is suitable for little bullet
Footpath is launched with wingless missile, it is difficult to the concentric tube realizing big caliber aerodynamic missile is launched.
Summary of the invention
The technology of the present invention solves problem: for overcoming the deficiencies in the prior art, it is provided that a kind of aerodynamic missile vertical thermal is launched
Inner circle foreign side is just as heart barrel structure, to realize the transmitting of big caliber aerodynamic missile concentric tube vertical thermal.
The technical solution of the present invention:
A kind of aerodynamic missile vertical thermal launches inner circle foreign side just as heart barrel structure, including urceolus, inner core, reinforcement, water conservancy diversion
Cone, block gripper shoe and deflector, wherein inner core is formed non-enclosed cylinder by four arcs, and the non-close district of inner core is formed
Guided missile and the moving conduit of missile wing；Urceolus is formed square tube by four square plate splicings, and outer tube inner wall is fixing with inner core to be connected, outward
There is combustion gas stream row between cylinder and inner core and lead gap；
Urceolus bottom inside arranges deflection cone, and deflection cone is cone symmetrical structure, centrage and inner core dead in line；Lead
The combustion gas stream playing electromotor ejection acts on deflection cone, and backflowing through deflection cone is carried out in gap between entrance urceolus and inner core
Combustion gas stream row lead；
Inner core axial length is less than urceolus, and the row of the installing space and combustion gas stream that reserve deflection cone bottom inner core leads sky
Between, bottom inner core, underface connects deflector, for the combustion gas stream backflowed upwards through deflection cone is carried out water conservancy diversion；At inner core four
One block gripper shoe of each connection bottom individual missile wing moving conduit, to seal bottom missile wing moving conduit and to support guided missile, stops
Combustion gas stream enters inner core inner space.
All it is correspondingly arranged four row's connecting holes on each inner core, urceolus are axial, is connected by securing member.
Deflection cone cone angle is 19 °～22 °, cone angle two bottom sides is arc structure.
Guided missile and missile wing do not interfere with inner core.
All spray thermal protective coating at outer tube inner wall, inner tank theca, deflection cone outer surface, make urceolus, inner core and deflection cone temperature
Rise and be respectively less than 10 DEG C.
Adapter is set at inner core inwall, with guided missile matched in clearance, is used for gap is adjusted.
It is S that the row that inner core and urceolus surround leads the area in gap, itself and the second flow of missile propulsive plantBetween ratio close
System is
Connection reinforcement plate in the middle part of inner core every piece arc outer surface, reinforcing plate is connected with urceolus.
Thermal protective coating is TR-42B.
Outer drum outer wall circumference is evenly arranged with reinforcement.
The present invention compared with prior art has the advantages that
(1) urceolus is designed as square by the present invention, improves combustion gas stream row between urceolus and inner core and leads gap, relative to interior
It is outward the concentric tube of cylindrical structure, is effectively improved jet exhaust spatial area as far as possible, better adapt to big caliber guided missile
Concentric tube is launched；
(2) traditional closed inner tube structure, owing to guided missile and missile wing are integrally placed in closed inner core, which limit
The diameter of guided missile, and the present invention uses non-enclosed inner tube structure, missile wing to be not take up inner core space, has better adapted to big caliber
Aerodynamic missile concentric tube is launched；
(3) present invention meets general Common-frame vertical launch system 850mm × 850mm bulk constraint, it is possible to realize big
Caliber (diameter is more than Φ 500mm) aerodynamic missile concentric tube vertical thermal is launched, and urceolus and inner core are divided into multiple part, reduces raw
Produce difficulty of processing, effectively reduce cost.
Accompanying drawing explanation
Fig. 1 is present configuration schematic diagram；
Fig. 2 is sectional view of the present invention；
Fig. 3 is the shaft side figure of the present invention；
Fig. 4 is deflection cone structural representation of the present invention.
Detailed description of the invention
The present invention is described in further detail below in conjunction with the accompanying drawings.
Compared to existing concentric tube structure, it is square tube that this invention proposes a kind of urceolus, and inner core is non-enclosed cylinder
Concentric tube structure, meets general Common-frame vertical launch system 850mm × 850mm bulk constraint, it is possible to realize big caliber (straight
Footpath is more than Φ 500mm) there is the wing not folded guided missile concentric tube vertical thermal to launch, and when realizing launching, engine gas is led from row, makes
Obtain protection bullet surface in Missile Launching Process not washed away by high-temperature fuel gas.
Concrete structure is as shown in Fig. 1～2, including urceolus 1, inner core 2, reinforcement 3, deflection cone 4, bolt 5, block gripper shoe
6, deflector 7, wherein inner core 2 is formed non-enclosed cylinder by four arcs, connects in the middle part of every piece of arc outer surface of inner core 2
Reinforcing plate, reinforcing plate is connected with urceolus 1；The non-close district of inner core 2 forms the moving conduit of guided missile and missile wing, as it is shown on figure 3, really
Protect guided missile and missile wing does not interferes with inner core 2；Urceolus 1 is formed square tube, urceolus 1 outer wall circumference by four square plate splicings
Being evenly arranged with reinforcement 3, urceolus 1 inwall is fixing with inner core 2 to be connected, exists between combustion gas stream arranges and lead between urceolus 1 and inner core 2
Gap, it is S that row leads the area in gap, itself and the second flow of missile propulsive plantBetween proportionate relationship be
All it is correspondingly arranged four row's connecting holes on each inner core 2, urceolus 1 are axial, is connected by bolt 5；
Urceolus 1 bottom inside arranges deflection cone 4, deflection cone 4 be cone symmetrical structure, concrete structure as shown in Figure 4, in
Heart line and inner core dead in line, deflection cone 4 cone angle is 19 °～22 °, cone angle two bottom sides arc radius 130mm, top fillet half
Footpath 5mm, highly 730mm, distance inner core distance from bottom 270mm；The combustion gas stream of missile propulsive plant ejection acts on deflection cone 4,
Backflow through deflection cone 4 and gap carries out between entrance urceolus 4 and inner core 4 combustion gas stream row lead；
Inner core 2 axial length is less than urceolus 1, and the row of the installing space and combustion gas stream that reserve deflection cone 4 bottom inner core 2 leads
Space, bottom inner core 2, underface connects deflector 7, for the combustion gas stream backflowed upwards through deflection cone 4 is carried out water conservancy diversion；?
One block gripper shoe 6 of each connection bottom 2 four missile wing moving conduits of inner core, leads to seal bottom missile wing moving conduit and to support
Bullet, stops combustion gas stream to enter inner core 2 inner space.
Adapter is set at inner core 2 inwall, with guided missile matched in clearance, is used for gap is adjusted.Urceolus 1 inwall,
Inner core 2 outer wall, deflection cone 4 outer surface all spray thermal protective coating, and thermal protective coating may select TR-42B, make urceolus 1, inner core 2 and lead
Flow cone 4 temperature rise is respectively less than 10 DEG C
When concentric tube of the present invention carries out general assembly, first the bottom of four inner cores 2 is supported with deflector 7 and four blocks
Plate 6 welds, and connects urceolus 1 and inner core 2 secondly by bolt 5, reinforcement 3 is then welded on urceolus 1 outer surface, finally will lead
Flow cone 4 welds bottom urceolus 1.
Emission process: after inner core 2 inserted by guided missile, is supported by block gripper shoe 6, and in emission process, engine jet pipe sprays
High-temperature fuel gas flow through after deflection cone 4 water conservancy diversion in reverse direction flow, utilize the annular gaps between urceolus 1 inner core 2 as row's pathway
Upwards discharge.Block gripper shoe 6 is used for supporting guided missile, seals missile wing channel bottom simultaneously, stops combustion gas stream when launching to enter interior
Cylinder inner space.Deflector 7 is for carrying out water conservancy diversion, bottom anti-stop block gripper shoe 6 to through deflection cone 4 combustion gas upwards of backflowing
Local pressure is too high, is also beneficial to the combustion gas row's of entrance pathway smoothly.Reinforcement 3 is welded on urceolus 1 outer wall, strong in order to improve
Degree, reduces the urceolus deformation that emission process mesohigh combustion gas causes.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (10)
1. an aerodynamic missile vertical thermal launches inner circle foreign side just as heart barrel structure, it is characterised in that include urceolus (1), inner core
(2), reinforcement (3), deflection cone (4), block gripper shoe (6) and deflector (7), wherein inner core (2) is made up of four arcs
Non-enclosed cylinder, the non-close district of inner core (2) forms the moving conduit of guided missile and missile wing；Urceolus (1) is spelled by four square plates
Connecing composition square tube, urceolus (1) inwall is fixing with inner core (2) to be connected, and there is combustion gas stream row and lead between urceolus (1) and inner core (2)
Gap；
Urceolus (1) bottom inside arranges deflection cone (4), and deflection cone (4) is cone symmetrical structure, centrage and inner core axis weight
Close；The combustion gas stream of missile propulsive plant ejection acts on deflection cone (4), and backflowing through deflection cone (4) enters urceolus (1) and inner core
(2) gap carries out between combustion gas stream row lead；
Inner core (2) axial length is less than urceolus (1), reserves installing space and the combustion gas stream of deflection cone (4) in inner core (2) bottom
Row's guide space, inner core (2) connects deflector (7) immediately below bottom, for flowing to the combustion gas backflowed upwards through deflection cone (4)
Row water conservancy diversion；One block gripper shoe (6) of each connection bottom (2) four missile wing moving conduits of inner core, logical to seal missile wing motion
Bottom road and support guided missile, combustion gas stream is stoped to enter inner core (2) inner space.
A kind of aerodynamic missile vertical thermal the most according to claim 1 launches inner circle foreign side just as heart barrel structure, and its feature exists
In, each inner core (2), urceolus (1) axially on be all correspondingly arranged four row's connecting holes, connected by securing member.
A kind of aerodynamic missile vertical thermal the most according to claim 1 launches inner circle foreign side just as heart barrel structure, and its feature exists
In, deflection cone (4) cone angle be 19 °～22 °, cone angle two bottom sides be arc structure.
A kind of aerodynamic missile vertical thermal the most according to claim 1 launches inner circle foreign side just as heart barrel structure, and its feature exists
In, guided missile and missile wing do not interfere with inner core (2).
A kind of aerodynamic missile vertical thermal the most according to claim 1 launches inner circle foreign side just as heart barrel structure, and its feature exists
In, all spray thermal protective coating at urceolus (1) inwall, inner core (2) outer wall, deflection cone (4) outer surface, make urceolus (1), inner core (2)
And deflection cone (4) temperature rise is respectively less than 10 DEG C.
A kind of aerodynamic missile vertical thermal the most according to claim 1 launches inner circle foreign side just as heart barrel structure, and its feature exists
In, adapter is set at inner core (2) inwall, with guided missile matched in clearance, is used for gap is adjusted.
A kind of aerodynamic missile vertical thermal the most according to claim 1 launches inner circle foreign side just as heart barrel structure, and its feature exists
In, it is S that the row that inner core (2) and urceolus (1) surround leads the area in gap, itself and the second flow of missile propulsive plantBetween ratio
Relation is
A kind of aerodynamic missile vertical thermal the most according to claim 1 launches inner circle foreign side just as heart barrel structure, and its feature exists
In, connection reinforcement plate in the middle part of every piece of arc outer surface of inner core (2), reinforcing plate is connected with urceolus (1).
A kind of aerodynamic missile vertical thermal the most according to claim 5 launches inner circle foreign side just as heart barrel structure, and its feature exists
In, thermal protective coating is TR-42B.
A kind of aerodynamic missile vertical thermal the most according to claim 1 launches inner circle foreign side just as heart barrel structure, and its feature exists
In, urceolus (1) outer wall circumference is evenly arranged with reinforcement (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610237423.4A CN105910492B (en) | 2016-04-15 | 2016-04-15 | A kind of vertical heat emission inner circle foreign side of aerodynamic missile is just as heart barrel structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610237423.4A CN105910492B (en) | 2016-04-15 | 2016-04-15 | A kind of vertical heat emission inner circle foreign side of aerodynamic missile is just as heart barrel structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105910492A true CN105910492A (en) | 2016-08-31 |
| CN105910492B CN105910492B (en) | 2017-10-24 |
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|---|---|---|---|
| CN201610237423.4A Active CN105910492B (en) | 2016-04-15 | 2016-04-15 | A kind of vertical heat emission inner circle foreign side of aerodynamic missile is just as heart barrel structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106288952A (en) * | 2016-08-18 | 2017-01-04 | 成都航天万欣科技有限公司 | Launching tube W shape arc and moulding process thereof |
| CN106516146A (en) * | 2016-11-02 | 2017-03-22 | 北京特种机械研究所 | Fixed adaptor type launch canister |
| CN110595276A (en) * | 2019-09-17 | 2019-12-20 | 上海机电工程研究所 | Gas flow self-discharging structure suitable for missile launcher |
Citations (3)
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|---|---|---|---|---|
| GB1338872A (en) * | 1971-02-24 | 1973-11-28 | France Etat Defense | Container for the storage and launching of a missile |
| WO2011152903A2 (en) * | 2010-03-01 | 2011-12-08 | Lockheed Martin Corporation | System and method for shock isolation in a launch system |
| CN103808206A (en) * | 2012-11-05 | 2014-05-21 | 杭州航海仪器有限公司 | Modularization support-sharing vertical launch device |
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Patent Citations (4)
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| GB1338872A (en) * | 1971-02-24 | 1973-11-28 | France Etat Defense | Container for the storage and launching of a missile |
| WO2011152903A2 (en) * | 2010-03-01 | 2011-12-08 | Lockheed Martin Corporation | System and method for shock isolation in a launch system |
| WO2011152903A3 (en) * | 2010-03-01 | 2012-01-26 | Lockheed Martin Corporation | System and method for shock isolation in a launch system |
| CN103808206A (en) * | 2012-11-05 | 2014-05-21 | 杭州航海仪器有限公司 | Modularization support-sharing vertical launch device |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106288952A (en) * | 2016-08-18 | 2017-01-04 | 成都航天万欣科技有限公司 | Launching tube W shape arc and moulding process thereof |
| CN106288952B (en) * | 2016-08-18 | 2017-11-10 | 成都航天万欣科技有限公司 | Launching tube W shapes arc and its moulding process |
| CN106516146A (en) * | 2016-11-02 | 2017-03-22 | 北京特种机械研究所 | Fixed adaptor type launch canister |
| CN110595276A (en) * | 2019-09-17 | 2019-12-20 | 上海机电工程研究所 | Gas flow self-discharging structure suitable for missile launcher |
| CN110595276B (en) * | 2019-09-17 | 2021-11-09 | 上海机电工程研究所 | Gas flow self-discharging structure suitable for missile launcher |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105910492B (en) | 2017-10-24 |
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