CN107718605A - One kind transmitting box body and preparation method thereof, firing box and preparation method thereof - Google Patents
One kind transmitting box body and preparation method thereof, firing box and preparation method thereof Download PDFInfo
- Publication number
- CN107718605A CN107718605A CN201711136564.8A CN201711136564A CN107718605A CN 107718605 A CN107718605 A CN 107718605A CN 201711136564 A CN201711136564 A CN 201711136564A CN 107718605 A CN107718605 A CN 107718605A
- Authority
- CN
- China
- Prior art keywords
- preparation
- fibrous layer
- metal alloy
- box body
- winding
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/681—Component parts, details or accessories; Auxiliary operations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
- B29B11/06—Making preforms by moulding the material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/70—Completely encapsulating inserts
-
- 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
Abstract
The invention provides one kind transmitting box body and preparation method thereof, firing box and preparation method thereof, it is related to emitter technical field, the transmitting box body preparation method can reduce technology difficulty and production cost.A kind of preparation method for launching box body, methods described include：The drawing of metal alloy blank is formed by metal alloy inner bag using drawing process；Thermal insulation layer is formed in the outside of the metal alloy inner bag；Fibrous layer is formed in the outside of the thermal insulation layer using winding process；The fibrous layer is post-processed, to form transmitting box body.The present invention is applied to the preparation of transmitting box body, firing box.
Description
Technical field
The present invention relates to emitter technical field, more particularly to a kind of transmitting box body and preparation method thereof, firing box
And preparation method thereof.
Background technology
Firing box is mainly used in the storage, transport and transmitting of guided missile, in various roadbeds and carrier-borne sophisticated missile armament systems
In be widely used.Firing box generally comprises：The parts such as casing, case lid, finder.
Existing transmitting box body is formed using Metal Material Welding, and complex process, production cost are high, it is difficult to meet the military
Requirement for low cost.
The content of the invention
Embodiments of the invention provide a kind of preparation method, preparation method of firing box for launching box body, the firing box
Casing preparation method can reduce technology difficulty and production cost.
To reach above-mentioned purpose, embodiments of the invention adopt the following technical scheme that：
On the one hand, there is provided a kind of preparation method for launching box body, methods described include：
The drawing of metal alloy blank is formed by metal alloy inner bag using drawing process；
Thermal insulation layer is formed in the outside of the metal alloy inner bag；
Fibrous layer is formed in the outside of the thermal insulation layer using winding process；
The fibrous layer is post-processed, to form transmitting box body.
Optionally, it is described to be included using winding process in the outside of thermal insulation layer formation fibrous layer：
By fiber yarn sheet to be wound respectively according to the first winding angle and the second winding angle in the outer of the metal alloy inner bag
Side carries out the first winding and the second winding.
Optionally, the scope of first winding angle is 85 ° -90 °, and the number of plies of first winding is 1 layer -5 layers；
The scope of second winding angle is 40 ° -50 °, and the number of plies of second winding is 80 layers -90 layers.
Optionally, it is described to be included metal alloy blank drawing formation metal alloy inner bag using drawing process：
To metal alloy blank machine-shaping, to form the first forming part and the second forming part；
First forming part and second forming part are welded；
Drawing is carried out to first forming part after welding and second forming part, to form metal alloy inner bag.
Optionally, after being post-processed to the fibrous layer, methods described also includes：
Preventing laser layer is formed in the outside of the fibrous layer.
Optionally, it is described post processing is carried out to the fibrous layer to include：
Curing process is carried out to the fibrous layer.
Optionally, it is described that fibrous layer progress curing process is included：
Within the t1 periods, the fibrous layer is heated, its temperature is raised to T2 from T1；
It is T2 to keep temperature of the fibrous layer within the t2 periods；
Within the t3 periods, the fibrous layer is heated, its temperature is raised to T3 from T2；
It is T3 to keep temperature of the fibrous layer within the t3 periods；
Wherein, the t1 periods, the t2 periods and the t3 periods are the continuous period successively.
On the other hand, there is provided a kind of preparation method of firing box, the preparation method include：Hair described in any of the above-described
Penetrate the preparation method of box body.
Another further aspect, there is provided one kind transmitting box body, the transmitting box body is using the firing box described in any of the above-described
The preparation method of casing is formed.
Another aspect, there is provided a kind of firing box, the firing box are formed using the preparation method of firing box described above.
The embodiment provides a kind of preparation method, preparation method of firing box for launching box body, the transmitting
The preparation method of box body includes：The drawing of metal alloy blank is formed by metal alloy inner bag using drawing process；Closed in metal
The outside of golden inner bag forms thermal insulation layer；Fibrous layer is formed in the outside of thermal insulation layer using winding process；Locate after being carried out to fibrous layer
Reason, to form transmitting box body.This method forms metal alloy inner bag using drawing process, while forms fibre using winding process
Layer is tieed up, compared to prior art, the production time is saved, reduces complex procedures and production cost.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the required accompanying drawing used in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can be with
Other accompanying drawings are obtained according to these accompanying drawings.
Fig. 1 is a kind of schematic flow sheet one of preparation method for launching box body provided in an embodiment of the present invention；
Fig. 2 is the schematic flow sheet of the specific steps that S101 includes in Fig. 1；
Fig. 3 is a kind of schematic flow sheet two of preparation method for launching box body provided in an embodiment of the present invention；
Fig. 4 is a kind of schematic flow sheet three of preparation method for launching box body provided in an embodiment of the present invention；
Fig. 5 is a kind of stereogram for launching box body provided in an embodiment of the present invention；
Fig. 6 is schematic cross-sections of the Fig. 5 along a-b directions；
Fig. 7 is a kind of structural representation for launching box body provided in an embodiment of the present invention；
Fig. 8 is the structural representation of another transmitting box body provided in an embodiment of the present invention；
Fig. 9 is another structural representation for launching box body provided in an embodiment of the present invention.
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, rather than whole embodiments.It is based on
Embodiment in the present invention, those of ordinary skill in the art are obtained every other under the premise of creative work is not made
Embodiment, belong to the scope of protection of the invention.
Embodiment one
The embodiment provides a kind of preparation method for launching box body, with reference to shown in figure 1, this method includes：
S101, using drawing process by the drawing of metal alloy blank formed metal alloy inner bag.
Here, the specific material of metal alloy blank does not limit, and it can be the gold such as magnesium alloy, titanium alloy, aluminium alloy
Belong to alloy；In view of reducing cost, preferably aluminium alloy.
Here, also it is not specifically limited for the number of drawing, can be depending on actual conditions.In view of improving drawing
Precision and quality, it is preferred to use multiple drawing.Example, once thick cold-drawn can be first used, is then pulled out again using a cold sperm.
It should be noted that before the drawing of metal alloy blank is formed into metal alloy inner bag using drawing process, also
Pickling processes can be carried out to metal alloy blank, to wash the oxide skin of metal alloy blank surface off, reduce friction, reduction is pulled out
Power processed, so as to prevent in drawing produce road plan the defects of.In addition, metal alloy blank drawing is formed using drawing process
After metal alloy inner bag, metal alloy inner bag can also be heat-treated, to reduce the degree of deformation, improve product essence
Degree.Heat treatment can be solution treatment, Ageing Treatment and annealing etc..
Here, also do not limited for the shape of metal alloy inner bag, can be according to the transmitting box body for being actually subjected to production
Shape depending on.Example, the shape of the metal alloy inner bag can be cylinder（Shown in Fig. 5）Or long square tube, certainly, metal
The shape of alloy inner bag can also be other shapes, no longer illustrate one by one here.
S102, metal alloy inner bag outside formed thermal insulation layer.
Here, also do not limited for the specific forming method of thermal insulation layer.In addition, do not done for the specific material of thermal insulation layer
Limit, at least need to meet heat-insulated requirement.
It should be noted that in subsequent technique, fibrous layer can be formed in the outside of thermal insulation layer.Launch using firing box
During guided missile, amount of heat can be produced.And the performance of fibrous layer is affected by temperature bigger, exceed certain value in temperature（Such as：
100℃）When, the performance of fibrous layer and life-span can have a greatly reduced quality.Therefore, set between metal alloy inner bag and fibrous layer heat-insulated
Layer can ensure the temperature of fibrous layer within its temperature in use.Meanwhile during storing with transport missile, be advantageous to protect
The temperature in firing box is held in prescribed limit.
S103, using winding process thermal insulation layer outside formed fibrous layer.
Here, winding process can be wet-winding craft either dry method winding process, with specific reference to actual conditions
It is fixed.The particular type of fibrous layer does not limit, it is contemplated that performance and technological problemses, preferably PE fibrous layers, PE fibrous layers refer to surpass
High molecular weight polyethylene fiber layer.
S104, fibrous layer is post-processed, to form transmitting box body.
Here, post processing can be including curing process etc., to ensure to launch the performance of box body.
The embodiment provides a kind of preparation method for launching box body, the preparation method bag of the transmitting box body
Include：The drawing of metal alloy blank is formed by metal alloy inner bag using drawing process；Metal alloy inner bag outside formed every
Thermosphere；Fibrous layer is formed in the outside of thermal insulation layer using winding process；Fibrous layer is post-processed, to form firing box case
Body.This method forms metal alloy inner bag using drawing process, while forms fibrous layer using winding process, compared to existing skill
Art, the production time is saved, reduce complex procedures and production cost；Meanwhile the transmitting box body formed by this method
With light weight, ballistic performance is good, intensity is big the characteristics of.
Optionally, S103, using winding process thermal insulation layer outside formed fibrous layer include：
Fiber yarn sheet to be wound is entered according to the first winding angle and the second winding angle on the outside of metal alloy inner bag respectively
Row first is wound and the second winding.It can obtain winding fibrous layer uniform, of good performance by above-mentioned winding method.
Optionally, the scope of above-mentioned first winding angle is 85 ° -90 °, such as：It can be 86 °, 88 ° etc.；Above-mentioned first
The number of plies of winding is 1 layer -5 layers, such as：It can be 2 layers, 4 layers etc..The scope of above-mentioned second winding angle is 40 ° -50 °, example
Such as：It can be 42 °, 44 °, 48 ° etc.；The number of plies of second winding is 80 layers -90 layers, such as：It can be 84 layers, 86 layers, 88 layers etc..
It should be noted that in order to improve the intensity of winding and quality, can be to silvalin to be wound before being wound
Piece carries out dipping process, while controls fiber gel content within the specific limits.If gel content is too high, the transmitting box body of formation
Intensity can reduce；If gel content is too low, the increase of the transmitting box body space of formation, it can cause to launch the air-tightness of box body, resistance to
Ageing properties and shear strength decline.Therefore, it is necessary to strictly control the gel content of fiber, ensure that whole winding process is front and rear and contain glue
Amount is uniform.Optionally, gel content should be controlled in 17%-25%, and preferably gel content is 20%.
Further, since fiber is all to use fiber size for reinforcemeent, storage is improper also to adsorb substantial amounts of moisture.Fiber surface
These free moistures influence the bonding of resin matrix and fiber, while cause stress corrosion, the defects of making micro-crack is further
Extension, so that product strength and ageing-resistant performance decline.Therefore, after dipping process is carried out to silvalin piece to be wound, and
Before coiling, drying and processing can also be carried out to silvalin piece to be wound.Fiber drying parameter can be according to fiber moisture content
Depending on spindle size, in general, 24h can be dried at 60 DEG C -80 DEG C.
Optionally, in order to reduce drawing difficulty while improve operability, with reference to shown in figure 2, S101, using drawing process
Metal alloy blank drawing formation metal alloy inner bag is included：
S201, to metal alloy blank machine-shaping, to form the first forming part and the second forming part.Here, for the first one-tenth
The shape of type portion and the second forming part does not limit.
S202, the first forming part and the second forming part welded.
S203, drawing is carried out to the first forming part after welding and the second forming part, to form metal alloy inner bag.
Optionally, with reference to shown in figure 3, in S104, fibrous layer is post-processed after, this method also includes：S105,
The outside of fibrous layer forms preventing laser layer.Here do not limited for the specific material of preventing laser layer.Formed by the above method
The structure of casing may be referred to shown in figure, the casing has the characteristics of shellproof, preventing laser, anti-electromagnetism.
Optionally, above-mentioned preventing laser layer is titanium dioxide vanadium layers.Titanium dioxide vanadium layers can effectively prevent laser, while to fiber
Layer plays a part of isolating sunshine heat.
Optionally, above-mentioned S104, post processing carried out to fibrous layer include：Curing process is carried out to fibrous layer, to ensure to send out
Penetrate the performance of box body.
Optionally, it is above-mentioned that fibrous layer progress curing process is included in order to improve solidification effect：
Within the t1 periods, fibrous layer is heated, its temperature is raised to T2 from T1.
It is T2 to keep temperature of the fibrous layer within the t2 periods.
Within the t3 periods, fibrous layer is heated, its temperature is raised to T3 from T2.
It is T3 to keep temperature of the fibrous layer within the t3 periods；Wherein, t1 periods, t2 periods and t3 periods be according to
The secondary continuous period.
It should be noted that t1, t2, t3, T1, T2, T3 concrete numerical value can determine according to actual conditions.Example,
T1 scope can be 25min-35min, and t2 scope can be 55min-65min, and t3 scope can be 170min-
190min, T1 temperature are initial temperature, generally normal temperature；T2 scope can be 55 DEG C -65 DEG C, and T3 scope can be
120℃-130℃。
Optionally, with reference to shown in figure 4, the drawing of metal alloy blank is formed into metal alloy in S101, using drawing process
After inner bag and S102, metal alloy inner bag outside formed thermal insulation layer before, this method also includes：
S106, metal alloy inner bag outside formed tack coat.
So, thermal insulation layer and metal alloy inner bag are fixed together by tack coat.Here, tack coat can be epoxy
Glue-line or polyurethane glue-line.
Optionally, above-mentioned thermal insulation layer is polyurethane foam.Polyurethane foam, which can mitigate in Missile Launching Process, to be produced
Influence of the raw high temp jet to fibrous layer, so as to improve the performance of transmitting box body.
Embodiment two
The embodiment provides a kind of preparation method of firing box, this method includes：Any one that embodiment one provides
Transmitting box body preparation method.This method forms metal alloy inner bag using drawing process, while uses winding process shape
Into fibrous layer, compared to prior art, the production time is saved, reduces complex procedures and production cost.
Embodiment three
The embodiment provides one kind to launch box body, any one that the transmitting box body is provided using embodiment one
The preparation method of transmitting box body is formed.With reference to shown in figure 5 and Fig. 6, the structure of the transmitting box body 10 can be included：From interior
Metal alloy inner bag 1, thermal insulation layer 2 and the fibrous layer 3 outwards set gradually；With reference to shown in figure 6, the structure of the transmitting box body is also
Can include：Metal alloy inner bag 1, thermal insulation layer 2, fibrous layer 3 and the preventing laser layer 4 set gradually from inside to outside；With reference to figure 7
It is shown, the structure of the transmitting box body can also be including：The metal alloy inner bag 1 that sets gradually from inside to outside, tack coat 5,
Thermal insulation layer 2 and fibrous layer 3；With reference to shown in figure 8, the structure of the transmitting box body can also be including：Set gradually from inside to outside
Metal alloy inner bag 1, tack coat 5, thermal insulation layer 2, fibrous layer 3 and preventing laser layer 4.Here, fibrous layer 3 can be PE fibers
Layer.
The transmitting box body formed by this method has the characteristics of light weight, ballistic performance are good, intensity is big.
Example IV
A kind of preparation method of the firing box provided the embodiment provides firing box, the firing box using embodiment two
Formed.The firing box formed by this method has the characteristics of light weight, ballistic performance are good, intensity is big.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, change or replacement can be readily occurred in, should all be contained
Cover within protection scope of the present invention.Therefore, protection scope of the present invention should be based on the protection scope of the described claims.
Claims (10)
1. a kind of preparation method for launching box body, it is characterised in that methods described includes：
The drawing of metal alloy blank is formed by metal alloy inner bag using drawing process；
Thermal insulation layer is formed in the outside of the metal alloy inner bag；
Fibrous layer is formed in the outside of the thermal insulation layer using winding process；
The fibrous layer is post-processed, to form transmitting box body.
2. preparation method according to claim 1, it is characterised in that it is described using winding process in the outer of the thermal insulation layer
Side, which forms fibrous layer, to be included：
By fiber yarn sheet to be wound respectively according to the first winding angle and the second winding angle in the outer of the metal alloy inner bag
Side carries out the first winding and the second winding.
3. preparation method according to claim 2, it is characterised in that the scope of first winding angle is 85 ° -90 °,
The number of plies of first winding is 1 layer -5 layers；
The scope of second winding angle is 40 ° -50 °, and the number of plies of second winding is 80 layers -90 layers.
4. preparation method according to claim 1, it is characterised in that described to be drawn metal alloy blank using drawing process
Pull out and to form metal alloy inner bag and include：
To metal alloy blank machine-shaping, to form the first forming part and the second forming part；
First forming part and second forming part are welded；
Drawing is carried out to first forming part after welding and second forming part, to form metal alloy inner bag.
5. preparation method according to claim 1, it is characterised in that after being post-processed to the fibrous layer, institute
Stating method also includes：
Preventing laser layer is formed in the outside of the fibrous layer.
6. preparation method according to claim 1, it is characterised in that described post processing is carried out to the fibrous layer to include：
Curing process is carried out to the fibrous layer.
7. preparation method according to claim 6, it is characterised in that described that curing process bag is carried out to the fibrous layer
Include：
Within the t1 periods, the fibrous layer is heated, its temperature is raised to T2 from T1；
It is T2 to keep temperature of the fibrous layer within the t2 periods；
Within the t3 periods, the fibrous layer is heated, its temperature is raised to T3 from T2；
It is T3 to keep temperature of the fibrous layer within the t3 periods；
Wherein, the t1 periods, the t2 periods and the t3 periods are the continuous period successively.
A kind of 8. preparation method of firing box, it is characterised in that including：Transmitting box body described in claim any one of 1-7
Preparation method.
9. one kind transmitting box body, it is characterised in that using the preparation side of the transmitting box body described in claim any one of 1-7
Method is formed.
10. a kind of firing box, it is characterised in that formed using the preparation method of the firing box described in claim 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711136564.8A CN107718605A (en) | 2017-11-16 | 2017-11-16 | One kind transmitting box body and preparation method thereof, firing box and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711136564.8A CN107718605A (en) | 2017-11-16 | 2017-11-16 | One kind transmitting box body and preparation method thereof, firing box and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107718605A true CN107718605A (en) | 2018-02-23 |
Family
ID=61216107
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711136564.8A Pending CN107718605A (en) | 2017-11-16 | 2017-11-16 | One kind transmitting box body and preparation method thereof, firing box and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107718605A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109323622A (en) * | 2018-11-26 | 2019-02-12 | 中国科学院长春光学精密机械与物理研究所 | A kind of launching tube |
| CN111912292A (en) * | 2020-07-31 | 2020-11-10 | 西安方元明科技股份有限公司 | Bulletproof and composite structure integrated launch canister and preparation method thereof |
| CN111997987A (en) * | 2020-07-20 | 2020-11-27 | 西安方元明科技股份有限公司 | Helicopter missile-tail-prevention transmission shaft and manufacturing method thereof |
Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4944210A (en) * | 1988-08-08 | 1990-07-31 | Hughes Aircraft Company | Missile launcher |
| US5000990A (en) * | 1985-08-22 | 1991-03-19 | The Budd Company | One piece molded composite part and method of manufacture |
| JP2000266243A (en) * | 1999-03-15 | 2000-09-26 | Babcock Hitachi Kk | High-temperature heat insulating pipe and its manufacture |
| CN101417524A (en) * | 2008-10-17 | 2009-04-29 | 哈尔滨工业大学 | Manufacture method of carbon fiber metal composite laminated plate |
| CN101532595A (en) * | 2009-04-13 | 2009-09-16 | 天津鹏翎胶管股份有限公司 | Special-shaped fuel hose wound by 5-layer tetrafluoroethylene (TFE) resin films and preparation method thereof |
| CN101578469A (en) * | 2007-01-31 | 2009-11-11 | 高级投资股份公司 | Metal/polymer laminate ducting and method of making same |
| CN101828230A (en) * | 2007-08-21 | 2010-09-08 | 约翰·D·布拉什公司 | Bucket-style fire resistant enclosure and manufacture method thereof |
| US20110056363A1 (en) * | 2008-04-30 | 2011-03-10 | Saab Ab | Weapon with im-characteristics |
| WO2013058863A2 (en) * | 2011-08-04 | 2013-04-25 | Polywad, Inc. | Recoil attenuated payload launcher system |
| CN103538269A (en) * | 2013-10-15 | 2014-01-29 | 中国船舶重工集团公司第七一〇研究所 | High temperature-resistant impact-resistant composite material housing, and molding method thereof |
| US20150175278A1 (en) * | 2009-09-25 | 2015-06-25 | Quicklaunch, Inc. | Gas gun launcher |
| CN204459508U (en) * | 2015-03-02 | 2015-07-08 | 新疆中石油管业工程有限公司 | A kind of continuous lod thermosetting resin composite pipe with two angle wound structure |
| CN105034402A (en) * | 2015-05-22 | 2015-11-11 | 上海复合材料科技有限公司 | Moulding method of missile launcher cylinder body |
| CN106182816A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion is wound around composite molding laser curing and prepares composite material hollow section bar |
| CN205991741U (en) * | 2016-06-17 | 2017-03-01 | 浙江鑫宙竹基复合材料科技有限公司 | Launch canister cylinder |
| CN106839874A (en) * | 2017-04-14 | 2017-06-13 | 北京特种机械研究所 | One kind can high efficiency temperature controlled composite cylinder |
| CN107314707A (en) * | 2017-08-15 | 2017-11-03 | 精功（绍兴）复合材料有限公司 | Composite material missile launching canister and preparation method thereof |
-
2017
- 2017-11-16 CN CN201711136564.8A patent/CN107718605A/en active Pending
Patent Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5000990A (en) * | 1985-08-22 | 1991-03-19 | The Budd Company | One piece molded composite part and method of manufacture |
| US4944210A (en) * | 1988-08-08 | 1990-07-31 | Hughes Aircraft Company | Missile launcher |
| JP2000266243A (en) * | 1999-03-15 | 2000-09-26 | Babcock Hitachi Kk | High-temperature heat insulating pipe and its manufacture |
| CN101578469A (en) * | 2007-01-31 | 2009-11-11 | 高级投资股份公司 | Metal/polymer laminate ducting and method of making same |
| CN101828230A (en) * | 2007-08-21 | 2010-09-08 | 约翰·D·布拉什公司 | Bucket-style fire resistant enclosure and manufacture method thereof |
| US20110056363A1 (en) * | 2008-04-30 | 2011-03-10 | Saab Ab | Weapon with im-characteristics |
| CN101417524A (en) * | 2008-10-17 | 2009-04-29 | 哈尔滨工业大学 | Manufacture method of carbon fiber metal composite laminated plate |
| CN101532595A (en) * | 2009-04-13 | 2009-09-16 | 天津鹏翎胶管股份有限公司 | Special-shaped fuel hose wound by 5-layer tetrafluoroethylene (TFE) resin films and preparation method thereof |
| US20150175278A1 (en) * | 2009-09-25 | 2015-06-25 | Quicklaunch, Inc. | Gas gun launcher |
| WO2013058863A2 (en) * | 2011-08-04 | 2013-04-25 | Polywad, Inc. | Recoil attenuated payload launcher system |
| CN103538269A (en) * | 2013-10-15 | 2014-01-29 | 中国船舶重工集团公司第七一〇研究所 | High temperature-resistant impact-resistant composite material housing, and molding method thereof |
| CN204459508U (en) * | 2015-03-02 | 2015-07-08 | 新疆中石油管业工程有限公司 | A kind of continuous lod thermosetting resin composite pipe with two angle wound structure |
| CN105034402A (en) * | 2015-05-22 | 2015-11-11 | 上海复合材料科技有限公司 | Moulding method of missile launcher cylinder body |
| CN205991741U (en) * | 2016-06-17 | 2017-03-01 | 浙江鑫宙竹基复合材料科技有限公司 | Launch canister cylinder |
| CN106182816A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion is wound around composite molding laser curing and prepares composite material hollow section bar |
| CN106839874A (en) * | 2017-04-14 | 2017-06-13 | 北京特种机械研究所 | One kind can high efficiency temperature controlled composite cylinder |
| CN107314707A (en) * | 2017-08-15 | 2017-11-03 | 精功（绍兴）复合材料有限公司 | Composite material missile launching canister and preparation method thereof |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109323622A (en) * | 2018-11-26 | 2019-02-12 | 中国科学院长春光学精密机械与物理研究所 | A kind of launching tube |
| CN111997987A (en) * | 2020-07-20 | 2020-11-27 | 西安方元明科技股份有限公司 | Helicopter missile-tail-prevention transmission shaft and manufacturing method thereof |
| CN111912292A (en) * | 2020-07-31 | 2020-11-10 | 西安方元明科技股份有限公司 | Bulletproof and composite structure integrated launch canister and preparation method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107718605A (en) | One kind transmitting box body and preparation method thereof, firing box and preparation method thereof | |
| CN106217915B (en) | The manufacturing method of tank | |
| CN104768734B (en) | Cylinder-like shell and the manufacture method of cylinder-like shell | |
| US20090314899A1 (en) | Structural element of an aircraft | |
| US10974469B2 (en) | Method for manufacturing a semifinished product or a part made of metal and fiber composite | |
| CN103603949A (en) | Metal liner pressure container made of basalt fibers serving as reinforcing materials and preparation method of metal liner pressure container | |
| CN109400194A (en) | The compound composite antenna housing of W-waveband fiber reinforced ceramic-base and preparation method | |
| US9889491B2 (en) | Method for producing a seamless pressure vessel for storing hydrogen | |
| CN105584056B (en) | Composite revolving body Combined impact structure and its preparation facilities and method | |
| US9895852B2 (en) | Method for producing a composite body | |
| CN207609489U (en) | The all- composite engine jet pipe of Z-direction enhancing | |
| CN106795576B (en) | Method for the steel spring for producing cold forming | |
| EP2675732B1 (en) | Belted toroid pressure vessel and method for making the same | |
| CN103770432A (en) | Production process of composite metal plastic belt | |
| JP2013542315A (en) | Method of hot forming coated metal parts and molded parts | |
| US4685241A (en) | Graphite fiber fishing rod | |
| CN105150639B (en) | A kind of novel ballistic plate and preparation method thereof | |
| CN106756684B (en) | GH4049 spheroid aluminizing methods | |
| CN107254568A (en) | The offline production method of high-carbon steel wire rod | |
| FI130072B (en) | Pipe-shaped product with ballistic protection | |
| CN106876015A (en) | A kind of half-hard state winding wire and its processing technology | |
| RU2634446C2 (en) | Method for forming thick-walled shell structures based on polymeric composite materials | |
| CN110217646A (en) | The method for reducing carbon fiber winding process abrasion loss | |
| CN206532620U (en) | A kind of half-hard state winding wire | |
| JP3913805B2 (en) | Golf club shaft manufacturing method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180223 |
|
| WD01 | Invention patent application deemed withdrawn after publication |