CN106895740A - Composite material film protecgulum with rubber as matrix and preparation method thereof - Google Patents
Composite material film protecgulum with rubber as matrix and preparation method thereof Download PDFInfo
- Publication number
- CN106895740A CN106895740A CN201710039094.7A CN201710039094A CN106895740A CN 106895740 A CN106895740 A CN 106895740A CN 201710039094 A CN201710039094 A CN 201710039094A CN 106895740 A CN106895740 A CN 106895740A
- Authority
- CN
- China
- Prior art keywords
- lid
- protecgulum
- rubber
- layer
- matrix
- 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
-
- 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
-
- 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
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
- B29C70/224—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being a net
-
- 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
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
-
- 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
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Textile Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention provides a kind of composite material film protecgulum with rubber as matrix and preparation method thereof, the protecgulum includes cover frame, lid, pressing plate and sealing ring, the lid is embedded in cover frame, and the pressing plate is arranged at the inner side of lid, and the sealing ring is nested on the inwall of cover frame.The preparation method comprises the following steps：Lid is put into the cover frame for having applied polysulfide sealant, lid is fastened with pressing plate and is locked lid, cover frame, pressing plate by bridge screw, finally sealing ring is fitted into cover frame, obtain the composite material film protecgulum with rubber as matrix.The present invention has following beneficial effect：Composite material film lid is made using rubber matrix, light weight, structurally flexible is small with firing box impact after cracking, easily realizes that protecgulum does not fall off function；Bearing structure layer is molded using metal rigidity frame and braider, can strictly control fiber spacing, quantity and tension force, it is ensured that product carries pressure unanimously, and steady quality, production are efficiently quick.
Description
Technical field
The present invention relates to a kind of composite material film protecgulum with rubber as matrix and preparation method thereof, belong to guided missile, fire
Arrow firing box (cylinder) technical field.
Background technology
Protecgulum is firing box (cylinder) important component, can to guided missile, rocket storage life, use and maintenance and transmitting
Influence larger by property.With the fast development of lift-off technology, it is desirable to certain intensity and rigidity is stamped before firing box (cylinder), is had
Good air-tightness and ablation resistance etc..
In recent years, the protecgulum for being made using high molecular foam material and glass fiber reinforced plastics composite material at home, outer some weapons
It is applied in model firing box (cylinder), product is generally frangible class protecgulum.With the continuous improvement of MISSILE LAUNCHING requirement, firing box
(cylinder) protecgulum is not allow for that fragment flies out, lid cracking does not fall off after opening, it has also become the current new research direction of lift-off technology.
The content of the invention
The present invention proposes a kind of composite material film protecgulum of rubber matrix, with certain firm, intensity and good
Air-tightness, ablation resistance, split in emission process in pintongs, and lid does not fall off in emission process.
The present invention is achieved by the following technical solutions：
In a first aspect, the invention provides a kind of composite material film protecgulum with rubber as matrix, it includes cover frame, lid
Body, pressing plate and sealing ring, the lid are embedded in cover frame, and the pressing plate is arranged at the inner side of lid, and the sealing ring is nested
In on the inwall of cover frame.
Preferably, the lid is fixed by fixing screws with cover frame.
Preferably, it is additionally provided with sealing ring between the lid and cover frame.
Preferably, the inner surface of the lid is provided with the stress groove of X-shaped structure.
Preferably, the lid includes bearing bed, anti-dropout layer and resistance to ablation layer and two-layer base layer, described anti-
Stratum disjunction and bearing bed are folded between the base layer of the two-layer, and the resistance to ablation layer is disposed therein one layer of base layer
Outer surface.
Preferably, the preparation method of the lid is：
Prepare bearing structure layer；
After base material is processed into sheet material, lid inner side base material is plated on formpiston, bearing structure layer is positioned over formpiston
In, in formpiston lay resist delamination material, repave the external side base material of mulching, finally on the outside of lid the outer surface of base material be plated in it is resistance to
Ablation film；
The film of resistance to ablation is sticked in former inner surface；
Formpiston and former are carried out into matched moulds, it is ensured that die joint position fit, after carrying out hot-press vulcanization shaping, remove formpiston and
Former, takes out the lid of shaping, and profile to lid is repaired.
Preferably, the preparation method of the bearing structure layer is：
By aramid fiber by winding two-layer in braider rigid frame, it is ensured that aramid fiber is in 45 ° with the edge of rigid frame
Angle, and ensure that bottom and the winding angle on upper strata are mutually perpendicular to.
Second aspect, present invention also offers a kind of such as the preparation of the foregoing composite material film protecgulum with rubber as matrix
Method, it comprises the following steps：
Lid is put into the cover frame for having applied polysulfide sealant, lid is fastened with pressing plate and will be covered by bridge screw
, finally be fitted into sealing ring in cover frame by body, cover frame, pressing plate locking, before obtaining the composite material film with rubber as matrix
Lid.
Compared with prior art, the present invention has following beneficial effect：
1st, composite material film lid is made using rubber matrix, light weight, structurally flexible clashes into after cracking with firing box
Power is small, easily realizes that protecgulum does not fall off function；
2nd, bearing structure layer is molded using metal rigidity frame and braider, can strictly be controlled fiber spacing, quantity and be opened
Power, it is ensured that product carries pressure unanimously, steady quality, production are efficiently quick；
3rd, protecgulum does not fall off performance, solves the potential safety hazard that lid fragmentation is caused；
4th, lid uses high temperature vulcanized shaping, it is ensured that using reliable under product high and low temperature environment.
Brief description of the drawings
The detailed description made to non-limiting example with reference to the following drawings by reading, further feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is the sectional view of composite material film protecgulum of the invention；
Fig. 2 is side schematic diagram in middle cover body of the present invention；
Fig. 3 is the structural representation of the bearing bed of lid in the present invention；
Fig. 4 is the sectional view of lid in the present invention；
In figure：1st, cover frame；2nd, sealing ring；3rd, lid；4th, pressing plate；5th, fixing screws；6th, sealant layer；7th, stress groove；8、
Rigid frame；9th, aramid fiber；10th, base layer；11st, bearing bed；12nd, anti-dropout layer；13rd, resistance to ablation layer.
Specific embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that to the ordinary skill of this area
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
As shown in figures 1-4, a kind of composite material film protecgulum with rubber as matrix that the present invention is provided, it includes lid
Frame 1, sealing ring 2, lid 3, pressing plate 4, lid 3 are embedded in cover frame 1, and pressing plate 4 is arranged at the inner side of lid 3, and sealing ring 2 is nested
In on the inwall of cover frame 1.
Lid 3 is fixed by fixing screws 5 with cover frame 1.
Sealant layer 6 is additionally provided between lid 3 and cover frame 1.
The inner surface of lid 3 is provided with the stress groove 7 of X-shaped structure.
Lid 3 includes bearing bed 11, anti-dropout layer 12, resistance to ablation layer 13 and two-layer base layer 10, anti-dropout layer 12 and holds
Carrier layer 11 is folded between the base layer 10 of the two-layer, and resistance to ablation layer 13 is disposed therein one layer of appearance of base layer 10
Face.
The preparation method of the lid in the present invention is：
Prepare bearing structure layer；
After base material is processed into sheet material, lid inner side base material is plated on formpiston, bearing structure layer is positioned over formpiston
In, in formpiston lay resist delamination material, repave the external side base material of mulching, finally on the outside of lid the outer surface of base material be plated in it is resistance to
Ablation film；
The film of resistance to ablation is sticked in former inner surface；
Formpiston and former are carried out into matched moulds, it is ensured that die joint position fit, after carrying out hot-press vulcanization shaping, remove formpiston and
Former, takes out the lid of shaping, and profile to lid is repaired.
The preparation method of bearing structure layer is：
By aramid fiber by winding two-layer in braider rigid frame, it is ensured that aramid fiber is in 45 ° with the edge of rigid frame
Angle, and ensure that bottom and the winding angle on upper strata are mutually perpendicular to.
A kind of preparation method of such as foregoing composite material film protecgulum with rubber as matrix, comprises the following steps：
First, lid is made：
1st, bearing structure formable layer
Aramid fiber is fastened in rigid frame by braider, and fiber winds with frame side in 45° angle, and fiber tension leads to
Overtension controller is adjusted, and easily splits position fiber tension less than other positions, and maximum fiber tension should be less than 70 pounds.Firm
Property frame on, fiber winds upper and lower two-layer, and bilaminar fiber is in 90 ° of intersections.The fiber spacing and Tensity size of braiding will according to carrying
Seek design.
2nd, composite molding
Step 1, the prefabricated 1~2mm raw material sheet material of rubber (rubber, the rubber of resistance to ablation) base material.By lid inner rubber base material
It is plated on formpiston, then the rigid frame after braided fiber is positioned in mould by frock；Steel wire is laid in lid root
Or aramid fabric, it is fixed with frame with aramid fiber；It is plated in lid outer rubber base material；It is last to be spread in cover outer surface
Apply the film of resistance to ablation.Rubber substrate and anti-dropout material are plated in quantity foundation and require design；
Step 2, stick the film of resistance to ablation layer in former inner surface, the film stock thickness of resistance to ablation layer is according to requiring design；
Step 3, the shaping of lid hot-press vulcanization, fit die joint position during matched moulds, and overfall has rubber glue to flow out, and presses
Vulcanization system vulcanizes；
Step 4, dismounting yin, yang mould, carry out lid contouring.
2nd, protecgulum assembling
Lid is put into the cover frame for having applied polysulfide sealant, lid is fastened with pressing plate and will be covered by bridge screw
Body, cover frame, pressing plate locking, then sealing ring is fitted into cover frame.
Specific embodiment of the invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can within the scope of the claims make various deformations or amendments, this not shadow
Sound substance of the invention.
Claims (8)
1. a kind of composite material film protecgulum with rubber as matrix, it is characterised in that including cover frame, lid, pressing plate and sealing
Circle, the lid is embedded in cover frame, and the pressing plate is arranged at the inner side of lid, and the sealing ring is nested in the inwall of cover frame
On.
2. the composite material film protecgulum with rubber as matrix as claimed in claim 1, it is characterised in that the lid passes through
Fixing screws are fixed with cover frame.
3. the composite material film protecgulum with rubber as matrix as claimed in claim 1, it is characterised in that the lid and lid
Sealing ring is additionally provided between frame.
4. the composite material film protecgulum with rubber as matrix as claimed in claim 1, it is characterised in that the lid it is interior
Surface is provided with the stress groove of X-shaped structure.
5. the composite material film protecgulum with rubber as matrix as described in any one in Claims 1 to 4, its feature exists
In the lid includes bearing bed, anti-dropout layer and resistance to ablation layer and two-layer base layer, and the anti-dropout layer and bearing bed are pressed from both sides
It is located between the base layer of the two-layer, the resistance to ablation layer is disposed therein one layer of outer surface of base layer.
6. composite material film protecgulum with rubber as matrix as described in claim 5, it is characterised in that the lid
Preparation method is：
Prepare bearing structure layer；
After base material is processed into sheet material, lid inner side base material is plated on formpiston, bearing structure layer is positioned in formpiston,
Resist delamination material is laid in formpiston, the external side base material of mulching is repaved, finally the outer surface of base material is plated in resistance to ablation on the outside of lid
Film；
The film of resistance to ablation is sticked in former inner surface；
Formpiston and former are carried out into matched moulds, it is ensured that die joint position is fitted, after carrying out hot-press vulcanization shaping, remove formpiston and the moon
Mould, takes out the lid of shaping, and profile to lid is repaired.
7. composite material film protecgulum with rubber as matrix as described in claim 6, it is characterised in that the carrying knot
Structure layer preparation method be：
By aramid fiber by winding two-layer in braider rigid frame, it is ensured that aramid fiber is in 45° angle with the edge of rigid frame, and
Ensure that bottom and the winding angle on upper strata are mutually perpendicular to.
8. a kind of preparation method of composite material film protecgulum with rubber as matrix as claimed in claim 1, it is characterised in that
Comprise the following steps：
Lid is put into the cover frame for having applied polysulfide sealant, with pressing plate by lid fasten and by bridge screw by lid, lid
, finally be fitted into sealing ring in cover frame by frame, pressing plate locking, obtains the composite material film protecgulum with rubber as matrix.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710039094.7A CN106895740A (en) | 2017-01-19 | 2017-01-19 | Composite material film protecgulum with rubber as matrix and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710039094.7A CN106895740A (en) | 2017-01-19 | 2017-01-19 | Composite material film protecgulum with rubber as matrix and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106895740A true CN106895740A (en) | 2017-06-27 |
Family
ID=59197991
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710039094.7A Pending CN106895740A (en) | 2017-01-19 | 2017-01-19 | Composite material film protecgulum with rubber as matrix and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106895740A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107932817A (en) * | 2017-11-29 | 2018-04-20 | 上海航天设备制造总厂 | A kind of bursting epoxy foam plastics Fragile cap and preparation method thereof |
| 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 |
| CN113091506A (en) * | 2021-03-22 | 2021-07-09 | 上海机电工程研究所 | Film front cover suitable for burst-type launch canister |
| CN115014125A (en) * | 2022-06-17 | 2022-09-06 | 北京新风航天装备有限公司 | Breakable thin film cover made of carbon fiber composite material and broken according to preset path |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006096326A1 (en) * | 2005-03-04 | 2006-09-14 | Lockheed Martin Corporation | Article comprising a missile canister cover |
| CN1844840A (en) * | 2006-04-30 | 2006-10-11 | 南京航空航天大学 | Frangible composite canister cover |
| CN1844839A (en) * | 2006-04-30 | 2006-10-11 | 南京航空航天大学 | Integral impacting type composite canister cover |
| CN103017616A (en) * | 2011-09-27 | 2013-04-03 | 上海机电工程研究所 | Composite easily-cracking front cover opened in one side and making method of composite easily-cracking front cover |
| CN203595451U (en) * | 2013-11-04 | 2014-05-14 | 上海燕兴科技实业有限公司 | Launch canister fragile rear cover of weapon system |
-
2017
- 2017-01-19 CN CN201710039094.7A patent/CN106895740A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006096326A1 (en) * | 2005-03-04 | 2006-09-14 | Lockheed Martin Corporation | Article comprising a missile canister cover |
| CN1844840A (en) * | 2006-04-30 | 2006-10-11 | 南京航空航天大学 | Frangible composite canister cover |
| CN1844839A (en) * | 2006-04-30 | 2006-10-11 | 南京航空航天大学 | Integral impacting type composite canister cover |
| CN103017616A (en) * | 2011-09-27 | 2013-04-03 | 上海机电工程研究所 | Composite easily-cracking front cover opened in one side and making method of composite easily-cracking front cover |
| CN203595451U (en) * | 2013-11-04 | 2014-05-14 | 上海燕兴科技实业有限公司 | Launch canister fragile rear cover of weapon system |
Non-Patent Citations (1)
| Title |
|---|
| 刘锋等: "复合柔性盖有限元建模及设计变量影响分析", 《强度与环境》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107932817A (en) * | 2017-11-29 | 2018-04-20 | 上海航天设备制造总厂 | A kind of bursting epoxy foam plastics Fragile cap and preparation method thereof |
| 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 |
| CN113091506A (en) * | 2021-03-22 | 2021-07-09 | 上海机电工程研究所 | Film front cover suitable for burst-type launch canister |
| CN113091506B (en) * | 2021-03-22 | 2022-11-11 | 上海机电工程研究所 | Film front cover suitable for burst-type launch canister |
| CN115014125A (en) * | 2022-06-17 | 2022-09-06 | 北京新风航天装备有限公司 | Breakable thin film cover made of carbon fiber composite material and broken according to preset path |
| CN115014125B (en) * | 2022-06-17 | 2023-07-04 | 北京新风航天装备有限公司 | Broken carbon fiber composite fragile film cover according to preset path |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170627 |