CN105806151B - A kind of adjustable deviation type adapter structure - Google Patents
A kind of adjustable deviation type adapter structure Download PDFInfo
- Publication number
- CN105806151B CN105806151B CN201610243305.4A CN201610243305A CN105806151B CN 105806151 B CN105806151 B CN 105806151B CN 201610243305 A CN201610243305 A CN 201610243305A CN 105806151 B CN105806151 B CN 105806151B
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- China
- Prior art keywords
- adapter
- metal shell
- guided missile
- built
- fitting
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- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A35/00—Accessories or details not otherwise provided for
-
- 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
Landscapes
- 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 adjustable deviation type adapter structure, including metal shell and adapter, adapter by it is close to thin uneven installation on metal shell, metal shell is split-type column construction, metal shell connects and composes launching tube, guided missile can be placed in launching tube, adapter profile matches with metal shell, for arc-shaped structure, adapter includes body and built-in fitting, bulk material is polyurethane foam, adapter circular arc inner surface sprays or bonding polytetrafluoroethylene (PTFE), built-in fitting material is metal, it is embedded in body forming process in the polyurethane foam of body, built-in fitting is connected by screw with metal shell, built-in fitting height is controlled by adjusting screw, and then adjust the gap value between adapter and guided missile.Adapter of the present invention is connected with launching tube, and after MISSILE LAUNCHING departs from launching tube, adapter does not leave launching tube with guided missile, realizes the separation function with guided missile, reusable.
Description
Technical field
The present invention relates to a kind of adjustable deviation type adapter structure, belongs to emission system regulation support structure designs neck
Domain.
Background technology
Adapter structure is the connection and support meanss between guided missile and launch canister, to storage of the guided missile in launching tube
Deposit, transport, loading and unloading and transmitting has an extremely important effect, adapter structure designing technique be emission system key technology it
One.
The vertical logical vertical concentric tube of heat emission requires can not there is ejecta in Missile Launching Process, therefore, it is necessary to using vibration damping
Cushion adapter (hereinafter referred to as " adapter "), i.e. adapter are fixed on launching tube inner cylinder internal face, unreal with Missile Motion
Now separate.In guided missile and launching tube storage, transportation, the effect of adapter is fixed, supported, balance guided missile；Work as guided missile
During in emission state, adapter mainly play the guiding role to guided missile.Adapter must have preferable damping property, and necessary
There is certain mechanical strength, moulded manufacturability is good, and easily embedding built-in fitting (adjusts barycenter, fastener, reinforcement in advance
Deng).Carry out the cushion blocking design and mechanics property analysis of adapter, from the material selection of cushion blocking, structure type, optimization design
Etc. carry out correlative study, the mechanical characteristic of cushion blocking is critical design element.
Existing adapter structure is the less high matching structure of adjustable range, to the dimension precision requirement of launching tube compared with
Height, which adds the processing cost of launching tube, and increase the installation difficulty of adapter.
The content of the invention
The technology of the present invention solves problem：For overcome the deficiencies in the prior art, there is provided a kind of adjustable deviation type adapter
Structure, makes not high in launching tube machining accuracy, in the case that dimensional discrepancy is larger, is adapted to by adjusting adapter own dimensions
Launching tube dimensional discrepancy.
The technical solution of the present invention：A kind of adjustable deviation type adapter structure, including metal shell and adapter,
Adapter by it is close to thin uneven installation on metal shell, metal shell is split-type column construction, metal shell connection structure
Into launching tube, guided missile can be placed in launching tube, and adapter profile matches with metal shell, be arc-shaped structure, adapter bag
Body and built-in fitting are included, bulk material is polyurethane foam, and adapter circular arc inner surface sprays or bonding polytetrafluoroethylene (PTFE), with
Reduce the frictional force between adapter and guided missile contact surface, built-in fitting material is metal, and this is embedded in body forming process
In the polyurethane foam of body, built-in fitting is connected by screw with metal shell, and built-in fitting height is controlled by adjusting screw, and then
Adjust the gap value between adapter and guided missile.
Built-in fitting height is controlled by adjusting screw, makes adapter and guided missile outer surface equidistant.
Coefficient of friction between adapter and guided missile contact surface is less than 0.1.
Metal shell machining accuracy -3mm~3mm, adaptor body thickness are 12mm~18mm.
Adapter stiffness K value scope is 1 × 106N/m~1.5 × 106N/m。
4 built-in fittings of center symmetric setting on each adapter, the radian between two built-in fittings is 17 °~19 °.
The radian of metal shell and adapter matches with missile diameter, and adapter radian is 30 °~32 °.
Adapter is corresponded to adapter and is distributed closeer end by close to thin non-uniform Distribution, nose of missile, and missile tail is corresponding suitable
End is relatively dredged in orchestration distribution.
Adapter after adjustment is equidistantly measured within 1mm with guided missile.
Adapter is axially distributed by close to thin uneven installation on metal shell, and along metal shell, adapter quantity
For 10, the frictional force between guided missile and adapter is set not hinder guided missile to pass in and out launching tube.
The present invention has the advantages that compared with prior art：
(1) it is original to go out an adapter structure complexity with guided missile, it can not reuse, adapter of the present invention is consolidated with launching tube
Even, after MISSILE LAUNCHING departs from launching tube, adapter does not leave launching tube with guided missile, realizes the separation function with guided missile, can weigh
It is multiple to use；
(2) the adjustable deviation type adapter structure of the present invention, is not high in launching tube machining accuracy, dimensional discrepancy is larger
In the case of propose a kind of can adapt to the structure of launching tube dimensional discrepancy by adjusting own dimensions.The structure is mountable to not
With the launching tube inwall of size, the gap adjustment amount between guided missile and launching tube is added, is meeting guided missile in launching tube
It is oriented to, supports outside the multiple functions such as fixed, vibration damping and transmitting separation, greatly reduces the machining accuracy of launching tube, effectively reduce
Product cost.
Brief description of the drawings
Fig. 1 is schematic structural view of the invention；
Fig. 2 is adapter structure plan of the present invention；
Fig. 3 is adapter embedded part structure schematic diagram of the present invention；
Fig. 4 is adapter structure stereogram of the present invention；
Fig. 5 is friction resistance curve of the adapter of the present invention to guided missile；
Fig. 6 is the stiffness curve of adapter of the present invention.
Embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
The present invention is larger for a kind of non-enclosed dimensional discrepancy of large thin-wall for being applied to the vertical heat emission of logical vertical concentric tube
Launching tube guided missile support adjustment structure, guided missile parks in launching tube, it is fixed with subtracting to play support in transportation to guided missile
Bestir oneself use；Guided missile is being loaded into launching tube, and in Missile Launching Process, guided missile is play the guiding role；MISSILE LAUNCHING departs from hair
After shooting cylinder, adapter must be separated voluntarily with guided missile；Structure of the present invention is mountable to various sizes of launching tube inwall, increases guided missile
Gap adjustment amount between launching tube, it is easy to operate, reduce machining accuracy and cost.Concrete structure is：
As shown in figure 1, including metal shell 4 and adapter, adapter by it is close to thin uneven installation in metal shell 4
On, and be axially distributed along metal shell 4, adapter quantity is 10, makes the frictional force between guided missile and adapter not hinder to lead
Snap into out launching tube.Nose of missile corresponds to adapter and is distributed closeer end, and missile tail corresponds to adapter distribution and relatively dredges end.Metal-back
Body 4 is split-type column construction, and 4 valve metal shells 4 connect and compose launching tube, and guided missile can be placed in launching tube, adapter profile
Match with metal shell 4, as shown in figure 4, being arc-shaped structure, adapter includes body 1 and built-in fitting 3, as shown in Fig. 2
The material of body 1 is polyurethane foam, the spraying of adapter circular arc inner surface or bonding polytetrafluoroethylene (PTFE), to reduce adapter with leading
Play the frictional force between contact surface, coefficient of friction therebetween need to be less than 0.1, and the material of built-in fitting 3 is metal, body 1 into
It is embedded in during type in the polyurethane foam of body 1, as shown in figure 3, built-in fitting 3 is connected with metal shell 4 by screw 2,
Built-in fitting height is controlled by adjusting screw 2, makes adapter and guided missile outer surface equidistant, so adjust adapter and guided missile it
Between gap value, adapter after adjustment and guided missile equidistantly amount within 1mm.
Metal shell machining accuracy -3mm~3mm of the present invention, adaptor body thickness need to adapt to the scope, can be designed
For 12mm~18mm, adapter range in stiffness is 1 × 106N/m~1.5 × 106N/m, adapter are too soft yielding, it is impossible to play
It is oriented to, support fixation, it is too hard then without effectiveness in vibration suppression.
4 built-in fittings of center symmetric setting on adapter of the invention each, radian between two built-in fittings for 17 °~
19°.The radian of metal shell 4 and adapter matches with missile diameter, and adapter radian is 30 °~32 °.
As shown in Fig. 5~6, pass through the adapter of Dynamics Simulation Analysis whole structural scheme of the present invention in use
Frictional force and rigidity value meet design requirement, and coefficient of friction is less than 0.1, and adapter stiffness K value ensures 1 × 106N/m~1.5
×106N/m。
The adjustable deviation type adapter structure of the present invention is mountable to various sizes of launching tube inwall, makes guided missile and hair
There is large range of gap adjustment amount between shooting cylinder, greatly reduce the machining accuracy of launching tube, effectively reduce cost, and
Guiding, support fixation, vibration damping and transmitting separation function of the guided missile in launching tube can be realized.The organization plan can be applicable
In various concentric tube emitting structurals.
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)
- A kind of 1. adjustable deviation type adapter structure, it is characterised in that including metal shell (4) and adapter, adapter by Close arrive dredges uneven installation on metal shell (4), and metal shell (4) is split-type column construction, and metal shell (4) connects structure Into launching tube, guided missile can be placed in launching tube, and adapter profile matches with metal shell (4), be arc-shaped structure, adapter Including body (1) and built-in fitting (3), body (1) material is polyurethane foam, and the spraying of adapter circular arc inner surface or bonding are poly- Tetrafluoroethene, to reduce the frictional force between adapter and guided missile contact surface, built-in fitting (3) material is metal, body (1) into It is embedded in during type in the polyurethane foam of body (1), built-in fitting (3) is connected with metal shell (4) by screw (2), is led to Screw (2) control built-in fitting height is overregulated, and then adjusts the gap value between adapter and guided missile.
- 2. a kind of adjustable deviation type adapter structure according to claim 1, it is characterised in that pass through adjusting screw (2) built-in fitting height is controlled, makes adapter and guided missile outer surface equidistant.
- 3. a kind of adjustable deviation type adapter structure according to claim 1, it is characterised in that adapter connects with guided missile Coefficient of friction between contacting surface is less than 0.1.
- A kind of 4. adjustable deviation type adapter structure according to claim 1, it is characterised in that metal shell processing essence Degree -3mm~3mm, adaptor body thickness are 12mm~18mm.
- A kind of 5. adjustable deviation type adapter structure according to claim 1, it is characterised in that adapter stiffness K value Scope is 1 × 106N/m~1.5 × 106N/m。
- 6. a kind of adjustable deviation type adapter structure according to claim 1, it is characterised in that on each adapter The heart is symmetrical arranged 4 built-in fittings, is 17 °~19 ° along the radian between the adjacent built-in fitting in two, radian direction.
- A kind of 7. adjustable deviation type adapter structure according to claim 1, it is characterised in that metal shell (4) and The radian of adapter matches with missile diameter, and adapter radian is 30 °~32 °.
- 8. a kind of adjustable deviation type adapter structure according to claim 1, it is characterised in that adapter is by close to thin Non-uniform Distribution, nose of missile correspond to adapter and are distributed closeer end, and missile tail corresponds to adapter distribution and relatively dredges end.
- A kind of 9. adjustable deviation type adapter structure according to claim 2, it is characterised in that the adapter after adjustment Equidistantly measured with guided missile within 1mm.
- A kind of 10. adjustable deviation type adapter structure according to claim 1, it is characterised in that adapter by it is close to Uneven installation is dredged on metal shell (4), and is axially distributed along metal shell (4), adapter quantity is 10, make guided missile with Frictional force between adapter does not hinder guided missile to pass in and out launching tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610243305.4A CN105806151B (en) | 2016-04-18 | 2016-04-18 | A kind of adjustable deviation type adapter structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610243305.4A CN105806151B (en) | 2016-04-18 | 2016-04-18 | A kind of adjustable deviation type adapter structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105806151A CN105806151A (en) | 2016-07-27 |
| CN105806151B true CN105806151B (en) | 2017-12-22 |
Family
ID=56457260
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610243305.4A Active CN105806151B (en) | 2016-04-18 | 2016-04-18 | A kind of adjustable deviation type adapter structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105806151B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516146A (en) * | 2016-11-02 | 2017-03-22 | 北京特种机械研究所 | Fixed adaptor type launch canister |
| CN110749233A (en) * | 2019-10-28 | 2020-02-04 | 上海机电工程研究所 | Honeycomb adapter and method of manufacture |
| CN112729007A (en) * | 2020-12-03 | 2021-04-30 | 上海复合材料科技有限公司 | Missile adapter, forming process method thereof and missile launching device |
| CN112729008B (en) * | 2020-12-08 | 2023-03-14 | 上海复合材料科技有限公司 | Gradient vibration-damping anti-adsorption adaptation layer, missile adapter and forming method thereof |
| CN113650225B (en) * | 2021-10-20 | 2022-01-21 | 北京玻钢院复合材料有限公司 | Polyurethane foam-PMI foam composite missile adapter and preparation method thereof |
| CN114646237B (en) * | 2022-04-15 | 2023-06-20 | 湖北三江航天万峰科技发展有限公司 | Detention adapter and contain its emitter case |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2940362A (en) * | 1956-06-22 | 1960-06-14 | Charles N Paxton | Missile launcher adapter |
| US3814837A (en) * | 1972-10-24 | 1974-06-04 | Us Army | Connector adapter device |
| US3883209A (en) * | 1973-06-29 | 1975-05-13 | Us Navy | Missile connector |
| CN201697539U (en) * | 2010-02-10 | 2011-01-05 | 中国船舶重工集团公司第七一三研究所 | Adapter |
-
2016
- 2016-04-18 CN CN201610243305.4A patent/CN105806151B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2940362A (en) * | 1956-06-22 | 1960-06-14 | Charles N Paxton | Missile launcher adapter |
| US3814837A (en) * | 1972-10-24 | 1974-06-04 | Us Army | Connector adapter device |
| US3883209A (en) * | 1973-06-29 | 1975-05-13 | Us Navy | Missile connector |
| CN201697539U (en) * | 2010-02-10 | 2011-01-05 | 中国船舶重工集团公司第七一三研究所 | Adapter |
Non-Patent Citations (1)
| Title |
|---|
| "适配器用硬质聚氨酯泡沫材料的研究";马天信;《航天制造技术》;20110825(第4期);第20-24页 * |
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| Publication number | Publication date |
|---|---|
| CN105806151A (en) | 2016-07-27 |
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