CN105910492B - A kind of vertical heat emission inner circle foreign side of aerodynamic missile is just as heart barrel structure - Google Patents
A kind of vertical heat emission inner circle foreign side of aerodynamic missile is just as heart barrel structure Download PDFInfo
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- CN105910492B CN105910492B CN201610237423.4A CN201610237423A CN105910492B CN 105910492 B CN105910492 B CN 105910492B CN 201610237423 A CN201610237423 A CN 201610237423A CN 105910492 B CN105910492 B CN 105910492B
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- inner cylinder
- missile
- outer barrel
- deflection cone
- heat emission
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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 kind of vertical heat emission inner circle foreign side of aerodynamic missile just as heart barrel structure, including outer barrel, inner cylinder, reinforcement, deflection cone, block supporting plate and deflector, wherein inner cylinder constitutes non-enclosed cylinder by four arcs, and the non-close area of inner cylinder forms the moving conduit of guided missile and missile wing；Outer barrel constitutes square tube by four square plate splicings, and outer tube inner wall is fixedly connected with inner cylinder, there is combustion gas stream row between outer barrel and inner cylinder and leads gap；Outer barrel bottom inside sets deflection cone, and deflection cone is conical symmetrical structure；The combustion gas stream that missile propulsive plant sprays is acted on deflection cone, and being backflowed by deflection cone between entrance outer barrel and inner cylinder, progress combustion gas stream row leads in gap.Outer barrel is designed as square by the present invention, improves between outer barrel and inner cylinder combustion gas stream row and leads gap, relative to it is inside and outside be cylindrical structure concentric tube, jet exhaust spatial area is effectively improved as far as possible, big caliber guided missile concentric tube transmitting has been better adapted to.
Description
Technical field
The present invention relates to a kind of vertical heat emission inner circle foreign side of aerodynamic missile just as heart barrel structure, belong to MISSILE LAUNCHING technology
Field.
Background technology
Concentric cartridge type emitter is applied to carrier-borne VLS, is led using the inner/outer tube of arranged concentric as carrier-borne
The storage of bullet, transport, transmitting container.For the guided missile of heat emission, the high temperature produced during transmitting, high-speed fuel gas, by bottom
After guiding device deflection, discharged upwards by the annular space between two layers of cylinder, it is no longer necessary to the shared combustion gas of many pieces of guided missiles
Tapping equipment.Traditional concentric barrel structure is made up of two concentric drums more, and inner cylinder is complete cylindrical structure, is suitable for small bullet
Launch with wingless missile in footpath, it is difficult to realize the concentric tube transmitting of big caliber aerodynamic missile.
The content of the invention
The technology of the present invention solves problem：To overcome the deficiencies in the prior art, there is provided a kind of vertical heat emission of aerodynamic missile
Inner circle foreign side is just as heart barrel structure, to realize the vertical heat emission of big caliber aerodynamic missile concentric tube.
The technical solution of the present invention：
A kind of vertical heat emission inner circle foreign side of aerodynamic missile is just as heart barrel structure, including outer barrel, inner cylinder, reinforcement, water conservancy diversion
Cone, block supporting plate and deflector, wherein inner cylinder constitute non-enclosed cylinder by four arcs, and the non-close area of inner cylinder is formed
The moving conduit of guided missile and missile wing；Outer barrel constitutes square tube by four square plate splicings, and outer tube inner wall is fixedly connected with inner cylinder, outside
There is combustion gas stream row between cylinder and inner cylinder and lead gap；
Outer barrel bottom inside sets deflection cone, and deflection cone is conical symmetrical structure, and center line is overlapped with inner cylinder axis；Lead
The combustion gas stream for playing engine ejection is acted on deflection cone, is backflowed and is carried out into gap between outer barrel and inner cylinder by deflection cone
Combustion gas stream row leads；
Inner cylinder axial length is less than outer barrel, and the installing space of deflection cone is reserved in inner cylinder bottom and the row of combustion gas stream leads sky
Between, connection deflector immediately below inner cylinder bottom, for carrying out water conservancy diversion to the combustion gas stream for backflowing upward by deflection cone；In inner cylinder four
Individual missile wing moving conduit bottom respectively connects a block supporting plate, to seal missile wing moving conduit bottom and support guided missile, prevents
Combustion gas stream enters inner cylinder inner space.
Four row's connecting holes are correspondingly arranged on each inner cylinder, outer barrel axial direction, are connected by fastener.
Deflection cone cone angle is 19 °~22 °, cone angle two bottom sides are arc structure.
Guided missile and missile wing are not interfered with inner cylinder.
Thermal protective coating is sprayed in outer tube inner wall, inner tank theca, deflection cone outer surface, makes outer barrel, inner cylinder and deflection cone temperature
Rise and be respectively less than 10 DEG C.
Adapter is set in inner cylinder inwall, coordinated with guided missile gap, for gap to be adjusted.
The row that inner cylinder and outer barrel are surrounded leads the area in gap for S, its second flow with missile propulsive plantBetween ratio close
It is to be
Connection reinforcement plate in the middle part of every piece of arc outer surface of inner cylinder, reinforcing plate is connected with outer barrel.
Thermal protective coating is TR-42B.
Outer drum outer wall is circumferentially evenly arranged with reinforcement.
The present invention has the advantages that compared with prior art：
(1) outer barrel is designed as square by the present invention, improves between outer barrel and inner cylinder combustion gas stream row and leads gap, relative to interior
Outer is the concentric tube of cylindrical structure, and jet exhaust spatial area is effectively improved as far as possible, big caliber guided missile has been better adapted to
Concentric tube is launched；
(2) traditional closed inner tube structure, because guided missile and missile wing are integrally placed in closed inner cylinder, which limit
The diameter of guided missile, and the present invention uses non-enclosed inner tube structure, missile wing is not take up inner cylinder 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 bulks constraint, can realize big
Caliber (diameter is more than Φ 500mm) vertical heat emission of aerodynamic missile concentric tube, is divided into multiple parts, reduction life by outer barrel and inner cylinder
Difficulty of processing is produced, cost is effectively reduced.
Brief description of the drawings
Fig. 1 is schematic structural view of the invention；
Fig. 2 is sectional view of the present invention；
Fig. 3 is shaft side figure of the invention；
Fig. 4 is deflection cone structural representation of the present invention.
Embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
Compared to existing concentric barrel structure, the invention proposes that a kind of outer barrel is square tube, and inner cylinder is non-enclosed cylinder
Concentric barrel structure, meets general Common-frame vertical launch system 850mm × 850mm bulks constraint, can realize that big caliber is (straight
Footpath is more than Φ 500mm) there is the vertical heat emission of the not folded guided missile concentric tube of the wing, and engine gas is led from row when realizing transmitting, is made
Protection bullet surface in Missile Launching Process is obtained not washed away by high-temperature fuel gas.
Concrete structure is as shown in Fig. 1~2, including outer barrel 1, inner cylinder 2, reinforcement 3, deflection cone 4, bolt 5, block supporting plate
6th, deflector 7, wherein inner cylinder 2 constitute non-enclosed cylinder by four arcs, and inner cylinder 2 is connected in the middle part of every piece of arc outer surface
Reinforcing plate, reinforcing plate is connected with outer barrel 1；The non-close area of inner cylinder 2 forms the moving conduit of guided missile and missile wing, as shown in figure 3, really
Protect guided missile and missile wing is not interfered with inner cylinder 2；Outer barrel 1 constitutes square tube by four square plate splicings, and the outer wall of outer barrel 1 is circumferential
Be evenly arranged with reinforcement 3, the inwall of outer barrel 1 is fixedly connected with inner cylinder 2, exist between outer barrel 1 and inner cylinder 2 combustion gas stream row lead between
Gap, the area that row leads gap is S, its second flow with missile propulsive plantBetween proportionate relationship be
Four row's connecting holes are correspondingly arranged on each inner cylinder 2, the axial direction of outer barrel 1, are connected by bolt 5；
The bottom inside of outer barrel 1 sets deflection cone 4, deflection cone 4 be conical symmetrical structure, concrete structure as shown in figure 4, in
Heart line is overlapped with inner cylinder axis, and the cone angle of deflection cone 4 is 19 °~22 °, cone angle two bottom sides arc radius 130mm, top fillet half
Footpath 5mm, height 730mm, apart from inner cylinder distance from bottom 270mm；The combustion gas stream that missile propulsive plant sprays is acted on deflection cone 4,
Being backflowed by deflection cone 4 between entrance outer barrel 4 and inner cylinder 4, progress combustion gas stream row leads in gap；
The axial length of inner cylinder 2 is less than outer barrel 1, reserves the installing space of deflection cone 4 in the bottom of inner cylinder 2 and the row of combustion gas stream leads
Connection deflector 7 immediately below space, the bottom of inner cylinder 2, for carrying out water conservancy diversion to the combustion gas stream for backflowing upward by deflection cone 4；
2 four missile wing moving conduit bottoms of inner cylinder respectively connect a block supporting plate 6, are led with sealing missile wing moving conduit bottom and supporting
Bullet, prevents combustion gas stream from entering the inner space of inner cylinder 2.
Adapter is set in the inwall of inner cylinder 2, coordinated with guided missile gap, for gap to be adjusted.The inwall of outer barrel 1,
The outer wall of inner cylinder 2, the outer surface of deflection cone 4 spray thermal protective coating, and TR-42B may be selected in thermal protective coating, make outer barrel 1, inner cylinder 2 and lead
The temperature rise of flow cone 4 is respectively less than 10 DEG C
When concentric tube of the present invention carries out general assembly, the bottom of four inner cylinders 2 and deflector 7 and four blocks are supported first
Plate 6 is welded, and connects outer barrel 1 and inner cylinder 2 secondly by bolt 5, reinforcement 3 then is welded on into the outer surface of outer barrel 1, will finally be led
Flow cone 4 is welded with the bottom of outer barrel 1.
Emission process：Guided missile is inserted after inner cylinder 2, is supported by block supporting plate 6, in emission process, and engine jet pipe sprays
High-temperature fuel gas flow through after the water conservancy diversion of deflection cone 4 in reverse direction flow, by the use of the annular gaps between the inner cylinder 2 of outer barrel 1 be used as row pathway
Discharge upwards.Block supporting plate 6 is used to support guided missile, while sealing missile wing channel bottom, prevents combustion gas stream during transmitting from entering interior
Cylinder inner space.Deflector 7 is used to carry out water conservancy diversion, the anti-bottom of stop block supporting plate 6 to the combustion gas for backflowing upward by deflection cone 4
Local pressure is too high, is also beneficial to combustion gas and smoothly enters row's pathway.Reinforcement 3 is welded on the outer wall of outer barrel 1, strong to improve
Degree, reduces the outer barrel deformation that emission process mesohigh combustion gas is caused.
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. a kind of vertical heat emission inner circle foreign side of aerodynamic missile is just as heart barrel structure, it is characterised in that including outer barrel (1), inner cylinder
(2), reinforcement (3), deflection cone (4), block supporting plate (6) and deflector (7), wherein inner cylinder (2) are made up of four arcs
Non-enclosed cylinder, the non-close area of inner cylinder (2) forms the moving conduit of guided missile and missile wing；Outer barrel (1) is spelled by four square plates
Composition square tube is connect, outer barrel (1) inwall is fixedly connected with inner cylinder (2), there is combustion gas stream row between outer barrel (1) and inner cylinder (2) and lead
Gap；
Outer barrel (1) bottom inside sets deflection cone (4), and deflection cone (4) is conical symmetrical structure, center line and inner cylinder axis weight
Close；The combustion gas stream that missile propulsive plant sprays is acted on deflection cone (4), is backflowed by deflection cone (4) into outer barrel (1) and inner cylinder
(2) combustion gas stream row is carried out between in gap to lead；
Inner cylinder (2) axial length is less than outer barrel (1), reserves in inner cylinder (2) bottom the installing space and combustion gas stream of deflection cone (4)
Connection deflector (7) immediately below guide space, inner cylinder (2) bottom is arranged, is flowed into for upward combustion gas of being backflowed to process deflection cone (4)
Row water conservancy diversion；A block supporting plate (6) is respectively connected in (2) four missile wing moving conduit bottoms of inner cylinder, it is logical to seal missile wing motion
Road bottom simultaneously supports guided missile, prevents combustion gas stream from entering inner cylinder (2) inner space.
2. a kind of vertical heat emission inner circle foreign side of aerodynamic missile according to claim 1 is just as heart barrel structure, its feature exists
In being correspondingly arranged four row's connecting holes on each inner cylinder (2), outer barrel (1) axial direction, connected by fastener.
3. a kind of vertical heat emission inner circle foreign side of aerodynamic missile according to claim 1 is just as heart barrel structure, its feature exists
In, deflection cone (4) cone angle be 19 °~22 °, cone angle two bottom sides be arc structure.
4. a kind of vertical heat emission inner circle foreign side of aerodynamic missile according to claim 1 is just as heart barrel structure, its feature exists
In guided missile and missile wing are not interfered with inner cylinder (2).
5. a kind of vertical heat emission inner circle foreign side of aerodynamic missile according to claim 1 is just as heart barrel structure, its feature exists
In spraying thermal protective coating in outer barrel (1) inwall, inner cylinder (2) outer wall, deflection cone (4) outer surface, make outer barrel (1), inner cylinder (2)
And deflection cone (4) temperature rise is respectively less than 10 DEG C.
6. a kind of vertical heat emission inner circle foreign side of aerodynamic missile according to claim 1 is just as heart barrel structure, its feature exists
In, inner cylinder (2) inwall set adapter, with guided missile gap coordinate, for gap to be adjusted.
7. a kind of vertical heat emission inner circle foreign side of aerodynamic missile according to claim 1 is just as heart barrel structure, its feature exists
The row surrounded in, inner cylinder (2) and outer barrel (1) leads the area in gap for S, its second flow with missile propulsive plantBetween ratio
Relation is
8. a kind of vertical heat emission inner circle foreign side of aerodynamic missile according to claim 1 is just as heart barrel structure, its feature exists
In connection reinforcement plate in the middle part of every piece of arc outer surface of inner cylinder (2), reinforcing plate is connected with outer barrel (1).
9. a kind of vertical heat emission inner circle foreign side of aerodynamic missile according to claim 5 is just as heart barrel structure, its feature exists
In thermal protective coating is TR-42B.
10. a kind of vertical heat emission inner circle foreign side of aerodynamic missile according to claim 1 is just as heart barrel structure, its feature exists
In outer barrel (1) outer wall is circumferentially 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 |
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| 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 |
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| Publication Number | Publication Date |
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| CN105910492A CN105910492A (en) | 2016-08-31 |
| CN105910492B true CN105910492B (en) | 2017-10-24 |
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| 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 |
| 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 |
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| FR2127109A5 (en) * | 1971-02-24 | 1972-10-13 | France Etat | |
| US8534177B2 (en) * | 2010-03-01 | 2013-09-17 | Lockheed Martin Corporation | System and method for shock isolation in a launch system |
| CN104897002B (en) * | 2012-11-05 | 2016-07-13 | 杭州航海仪器有限公司 | Modularity Common-frame vertical launch device |
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