CN103913098A - Multi-petal composite material launching box cover and preparation method thereof - Google Patents
Multi-petal composite material launching box cover and preparation method thereof Download PDFInfo
- Publication number
- CN103913098A CN103913098A CN201410089075.1A CN201410089075A CN103913098A CN 103913098 A CN103913098 A CN 103913098A CN 201410089075 A CN201410089075 A CN 201410089075A CN 103913098 A CN103913098 A CN 103913098A
- Authority
- CN
- China
- Prior art keywords
- sidepiece
- sub
- disengagement zone
- lid
- gai
- 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
Landscapes
- Closures For Containers (AREA)
Abstract
The invention relates to a multi-petal composite material launching box cover and a preparation method thereof and belongs to the technical field of missile launching. The multi-petal composite material launching box cover sequentially comprises a frame (1), a side sub-cover (5) and a top sub-cover (6). The side sub-cover (5) is connected with the frame (1) through a thrown body separating area (2), the top sub-cover (6) is connected with the side sub-cover (5) through a top sub-cover separating area (4), the side sub-cover (5) is evenly divided into 4-8 side sub-cover units in the circumference, and the side sub-cover units are connected through side sub-cover unit separating areas (3). Under the effect of missile launching tail flow, the launching box cover is broken into a plurality of sub-covers to fly away from a launching box, and accordingly missile launching is not influenced. The problem that a thrown object of the fragile cover is high in mass is solved, and the threat to surrounding devices and workers caused by the thrown object is effectively reduced.
Description
Art
The present invention relates to a kind of multi-clove type composite material launching box cover and preparation method thereof, belong to MISSILE LAUNCHING technical field.
Background technology
The design of MISSILE LAUNCHING case lid is to affect guided missile to reflect fast one of key factor of ability.Therefore in the time of development missile storage firing box, the design of case lid is extremely important.Case lid is mainly to bear certain pressure reduction, and good seal performance can be opened rapidly in the time launching a guided missile.For meeting above-mentioned requirements, MISSILE LAUNCHING case lid used adopts mechanical cap, and blasting bolt open cap etc. (refers to US Pat.3970006,1976; US Pat.4333381,1982), but the shortcoming of the equal various degrees of these case lids, opening lid as machinery need to open by hydraulic system, and mechanism's complexity has not only increased the weight of firing box and wasted time, blast lid is opened and is reacted rapid compared with mechanical cap, but again shoot and keep in repair more complicated, and adopt priming system transport, storage difficulty.
For improving MISSILE LAUNCHING efficiency, meet the requirement that army fights fast, develop a kind of composite penetration film case lid (referring to US Pat.4498368,1985) abroad.This kind of case lid can bear certain well-distributed pressure and under less concentrated force, just can make case lid to subscribe track fragmentation, is swift in response, and improved MISSILE LAUNCHING efficiency.But this kind of composite material launching box cover need destroy under the effect of guided missile end, case lid will inevitably produce certain adverse effect to the guided missile warhead of contact with it.Domestic a kind of integral impacting type composite canister cover (referring to CN1844839A, 2006), the gas shock film cover of utilizing the front engine of MISSILE LAUNCHING to produce, film cover is destroyed with desired trajectory entirety, can not have a negative impact to MISSILE LAUNCHING.But this film cover entirety is dished out after destroying, weight is larger, and emitter surrounding devices is constituted a threat to, and therefore practical application has certain limitation.
Summary of the invention
The object of the present invention is to provide that a kind of simple in structure, bearing capacity is strong, the multi-clove type composite material launching box cover of good stability and preparation method thereof, solved the above-mentioned case lid large problem of weight of dishing out.
A kind of multi-clove type composite material launching box cover of the present invention, is characterized in that: comprise successively framework, sidepiece lid and top Zi Gai; Between sidepiece lid and framework, be connected by the body Disengagement zone of dishing out; Between top son lid and sidepiece lid, be connected by Zi Gai Disengagement zone, top; The sub-cover rim of sidepiece is circumferentially divided into 4-8 the sub-cap unit of sidepiece, between the sub-cap unit of sidepiece, is connected by the sub-cap unit of sidepiece Disengagement zone; Above-mentioned sidepiece lid, top son lid have formed the body of dishing out jointly; The body of dishing out adopts ladder ply sequence to form by complex fabric cloth; The above-mentioned body Disengagement zone of dishing out, sidepiece cap unit Disengagement zone and Zi Gai Disengagement zone, top have formed lid subregion jointly; Lid Disengagement zone all adopts V-type groove structure filling AB glue outer overlap joint bonding fiber cloth, and wherein V-type open slot is towards launching box cover inner side.
The multi-clove type composite material launching box cover of the present invention development,, can bear certain interior pressure and not destroy, the pressure in guard box during in sealing state at MISSILE LAUNCHING case; In the time that guided missile is lighted a fire, launching box cover is subject to guided missile wake flow percussion, and first the Disengagement zone that design strength is lower is destroyed, and causes sidepiece lid and top son lid depart from framework and fly out by planned course; Due to ejecta journey multi-petal shape formula, therefore unit mass is less, can effectively reduce the threat to surrounding devices and personnel; When MISSILE LAUNCHING is gone up to the air around, guided missile wake effect, in dome-shaped cover external surface, can be born larger external pressure according to Topological Interlocking principle and not destroy.
A kind of multi-clove type composite material launching box cover of the present invention, it is characterized in that: the above-mentioned body of dishing out adopts with downstairs ply sequence: basal layer [(0/90) (± 45) (0/90) (± 45) (0/90)], overlay [45/0/90/-45].
The multi-clove type composite material launching box cover of the present invention's development, adopts ladder ply sequence, effectively in increasing structural strength, alleviate construction weight, and preparation method is simple.
A kind of multi-clove type composite material launching box cover of the present invention, is characterized in that: the V-type groove of above-mentioned Disengagement zone is 45 degree.
The multi-clove type composite material launching box cover Disengagement zone V-type groove of the present invention's development is 45 degree, and Disengagement zone is subject to direct stress and shear stress effect in the time destroying, and 45 degree V-type grooves can effectively increase the bearing capacity of structure, have good sealing simultaneously.
The preparation method of a kind of multi-clove type composite material launching box cover of the present invention, is characterized in that comprising following process:
Step 1, utilize mould by the framework of launching box cover, Disengagement zone and the integral prefabricated moulding of the body of dishing out;
Step 2, cut at default the body Disengagement zone of dishing out, sidepiece cap unit Disengagement zone and Zi Gai Disengagement zone, top place, make framework, the sub-cap unit of sidepiece, top son lid separated from one another;
Step 3, in the sub-cap unit of sidepiece, get V-type chamfering along edge on the inner edge of edge and framework in the son lid of, top;
Step 4, use AB glue are by amalgamation between sub-each sidepiece cap unit and top son lid; In the V-type groove forming in mosaic, inject AB glue; After AB glue solidifies completely, be glued to mosaic with glass fibre cloth, and glass fibre cloth covers overlapping edges with the adjacent sub-cap unit of sidepiece or top and glues together, prepare the body of dishing out;
Step 5, with AB glue will dish out body and framework amalgamation; In forming V-type groove, mosaic injects AB glue; After AB glue solidifies completely, be glued to mosaic with glass fibre cloth, and glass fibre cloth glues together with the overlapping edges of dish out body and framework;
Step 6, by the lid of above-mentioned preparation in baking oven constant temperature process after take out;
Step 7, polishing lid inner surface also spray screen layer.
The multi-clove type composite material launching box cover of the present invention's development, it is simple that preparation method has technique, and the composite material launching box cover of other version is made and had directive function.
Brief description of the drawings
Fig. 1 is the multi-clove type composite material launching box cover plan structure schematic diagram in the embodiment of the present invention 1;
Fig. 2 is the multi-clove type composite material launching box cover side-looking structural representation in the embodiment of the present invention 1;
Fig. 3 is the multi-clove type composite material launching box cover broken section structural representation in the embodiment of the present invention 1;
Fig. 4 is the multi-clove type composite material launching box cover plan structure schematic diagram in the embodiment of the present invention 2;
In figure, be numbered: 1, framework, 2, the body Disengagement zone of dishing out, 3, the sub-cap unit of sidepiece Disengagement zone, 4, Zi Gai Disengagement zone, top, 5, sidepiece lid, 6, top Zi Gai, 7, V-type chamfered region, 8, fiber cloth.
Detailed description of the invention
Below in conjunction with accompanying drawing, by embodiment, the present invention is elaborated:
Embodiment 1
As shown in Figure 1: a kind of multi-clove type composite material launching box cover, taking high strength glass fiber sheet and epoxy resin as material of main part, adopts ladder ply sequence to design and produce.Particularly, a kind of multi-clove type composite material launching box cover of the present invention comprises 1, framework, and described framework 1 is circular; 2, the body Disengagement zone of dishing out, described in the body Disengagement zone 2 of dishing out be positioned at framework 1 and the sub-cap unit of sidepiece junction, adopt 45 ° of V-type groove structures, the inner AB glue of filling, 2 layers of glass fibre cloth are posted in outside; 3, sidepiece Zi Gai Disengagement zone, 2 use same structures, between the sub-cap unit of sidepiece, are adopted with the body Disengagement zone of dishing out in described sidepiece Zi Gai Disengagement zone 3; 4, Zi Gai Disengagement zone, top, Zi Gai Disengagement zone, described top 4 is positioned at top son lid 6 and the sub-cap unit of sidepiece 5 junctions, and body Disengagement zone 2 adopts same structure with dishing out; 5, the sub-cap unit of sidepiece, the sub-cap unit of described sidepiece (5) forms for the body formed rear cutting of dishing out, totally 4 lobes; 6, top Zi Gai, described top son lid 6 is identical with sidepiece lid 5 production methods, totally 1 lobe.
Launching box cover manufacture craft
There is case lid making and be divided into 5 steps: 1, framework, Disengagement zone and the integral prefabricated moulding of the body of dishing out; 2, Disengagement zone is set; 3, connection and the body lid of fixedly dishing out; 4, connection and fixed frame, Disengagement zone and the body of dishing out; 5, screen layer is set.
1, framework, Disengagement zone and the integral prefabricated moulding of the body of dishing out
1) cleaning punch, smears one deck low temperature grease at mould upper surface, cuts out polyester plastics paper and sticks on mould by punch shape;
2) preparation epoxy resin adhesive liquid;
3) cut out woven glass fabric by dimensional requirement some;
4) if 5 layers of glass fabric are laid on mould by 0/90/ ± 45/0 direction and have scraped glue;
5) 4 layers of circular glass fiber cloth of cutting out are in advance laid on to grinding tool center and have scraped glue by 45/0/90/-45 direction;
6) if 5 layers of glass fabric are laid on mould by 90/ ± 45/0/90 direction and have scraped glue;
7) launching box cover and mold integral are put into vacuum bag and carried out vacuum and inhale glue, after 24 hours, solidify.
2, Disengagement zone is set
1) the prefabricated launching box cover entirety after solidifying is separated with mould;
2) Disengagement zone height is set, and prefabricated case lid is dished out to body and framework apart out with cutting off machine by top;
3) position, Zi Gai Disengagement zone is set, and the body cutting machine of dishing out is divided into top son lid and sidepiece lid;
4) angle that arranges of sander is 45 °, in the interior edge on the clockwise limit of sidepiece lid, top cover on the inner edge of edge and framework along getting a V-type chamfering;
3, connection and the body lid of fixedly dishing out
1) each the body of dishing out son lid is reapposed by the position before cutting and separating, and fix with a small amount of AB glue each several part;
2) the body upset of dishing out after fixing, configuration AB glue, injects AB glue in prefabricated V-type chamfering;
3) after AB glue solidifies completely, glass fibre cloth center line is alignd with the body lid splicing line of dishing out, on fiber cloth, brush glue, cover Disengagement zone, and the each sub-interior surface of the body of dishing out overlaps, overlapping the number of plies is 2 layers;
4, connection and fixed frame, Disengagement zone and the body of dishing out
1) by dish out body and framework, the position before by cutting and separating reapposes, and fixes with a small amount of AB glue each several part;
2) after AB glue solidifies completely, upper edge, framework inner side is close to in one side of glass fibre cloth, on fiber cloth, brush glue, cover Disengagement zone, and framework and the body of dishing out are overlapped at inner surface, the overlap joint number of plies is 2 layers;
3) launching box cover after curing molding is placed in baking oven, constant temperature takes out after processing;
5, screen layer is set
1) lid inner surface is smooth with sand papering;
2) the copper silver mixed paint modulating in advance is evenly sprayed on to lid inner surface, after parching, completes the manufacturing process of launching box cover.
Embodiment 2
As shown in Figure 4: a kind of multi-clove type composite material launching box cover, taking high strength glass fiber sheet and epoxy resin as material of main part, adopts ladder ply sequence to design and produce.Particularly, a kind of multi-clove type composite material launching box cover of the present invention comprises 1, framework, and described framework is circular; 2, the body Disengagement zone of dishing out; 3, sidepiece Zi Gai Disengagement zone; 4, Zi Gai Disengagement zone, top; 5, sidepiece lid, the sub-cap unit of described sidepiece forms for the body formed rear cutting of dishing out, totally 8 lobes; 6, top Zi Gai, described top son lid is identical with the sub-cap unit production method of sidepiece, totally 1 lobe.This embodiment adopts in the time that the quality of launching box cover is excessive, alleviates ejecta unit mass in the mode that increases the sub-cap unit quantity of sidepiece.Therefore, the large problem of launching box cover ejecta quality when this multi-clove type launching box cover can solve MISSILE LAUNCHING effectively, reduces the threat to surrounding devices and personnel.
Claims (4)
1. a multi-clove type composite material launching box cover, is characterized in that:
Comprise successively framework (1), sidepiece lid (5) and top Zi Gai (6); Between sidepiece lid (5) and framework (1), be connected by the body Disengagement zone (2) of dishing out; Between top Zi Gai (6) and sidepiece lid (5), be connected by Zi Gai Disengagement zone, top (4); Sidepiece lid (5), along being circumferentially divided into 4-8 the sub-cap unit of sidepiece, is connected by the sub-cap unit of sidepiece Disengagement zone (3) between the sub-cap unit of sidepiece;
Above-mentioned sidepiece lid (5), top Zi Gai (6) have formed the body of dishing out jointly; The body of dishing out adopts ladder ply sequence to form by complex fabric cloth;
The above-mentioned body Disengagement zone (2) of dishing out, the sub-cap unit of sidepiece Disengagement zone (3) and Zi Gai Disengagement zone, top (4) have formed lid subregion jointly; Lid Disengagement zone all adopts V-type groove structure filling AB glue outer overlap joint bonding fiber cloth (8), and wherein V-type open slot is towards launching box cover inner side.
2. multi-clove type composite material launching box cover according to claim 1, it is characterized in that: the above-mentioned body of dishing out adopts with downstairs ply sequence: basal layer [(0/90) (± 45) (0/90) (± 45) (0/90)], overlay [45/0/90/-45].
3. multi-clove type composite material launching box cover according to claim 1, is characterized in that: the V-type groove of above-mentioned Disengagement zone is 45 degree.
4. the preparation method of multi-clove type composite material launching box cover according to claim 1, is characterized in that comprising following process:
Step 1, utilize mould by the framework of launching box cover, Disengagement zone and the integral prefabricated moulding of the body of dishing out;
Step 2, locate to cut in default the body Disengagement zone (2) of dishing out, the sub-cap unit of sidepiece Disengagement zone (3) and Zi Gai Disengagement zone, top (4), make framework (1), the sub-cap unit of sidepiece, top Zi Gai (6) separated from one another;
Step 3, in the sub-cap unit of sidepiece, get V-type chamfering along edge on the inner edge of edge and framework (1) in, top Zi Gai (6);
Step 4, use AB glue are by amalgamation between sub-each sidepiece cap unit and top Zi Gai (6); In the V-type groove forming in mosaic, inject AB glue; After AB glue solidifies completely, be glued to mosaic with glass fibre cloth, and glass fibre cloth and the adjacent sub-cap unit of sidepiece or top Zi Gai (6) overlapping edges glue together, prepare the body of dishing out;
Step 5, with AB glue will dish out body and framework (1) amalgamation; In forming V-type groove, mosaic injects AB glue; After AB glue solidifies completely, be glued to mosaic with glass fibre cloth, and glass fibre cloth glues together with the overlapping edges of dish out body and framework (1);
Step 6, by the lid of above-mentioned preparation in baking oven constant temperature process after take out;
Step 7, polishing lid inner surface also spray screen layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410089075.1A CN103913098A (en) | 2014-03-12 | 2014-03-12 | Multi-petal composite material launching box cover and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410089075.1A CN103913098A (en) | 2014-03-12 | 2014-03-12 | Multi-petal composite material launching box cover and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103913098A true CN103913098A (en) | 2014-07-09 |
Family
ID=51038967
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410089075.1A Pending CN103913098A (en) | 2014-03-12 | 2014-03-12 | Multi-petal composite material launching box cover and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103913098A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104864773A (en) * | 2015-05-08 | 2015-08-26 | 南京航空航天大学 | Composite material frangible cover enabling direction-pinpointed ejection and manufacturing method thereof |
| CN104913692A (en) * | 2015-06-30 | 2015-09-16 | 湖北三江航天万峰科技发展有限公司 | Fragile cap |
| CN105043166A (en) * | 2015-07-20 | 2015-11-11 | 北京理工大学 | Low-impact overall ejection type launching canister front cover |
| TWI595909B (en) * | 2015-10-20 | 2017-08-21 | The 202Nd Arsenal Materiel Production Center | Bullet structure improved |
| CN109202437A (en) * | 2018-09-03 | 2019-01-15 | 郑州郑飞机电技术有限责任公司 | A kind of molding assembly method of composite material body storage box |
| CN110697066A (en) * | 2019-10-10 | 2020-01-17 | 北京特种机械研究所 | Fragile cover with mooring, buffering and ablation-proof functions |
| CN111322909A (en) * | 2020-03-03 | 2020-06-23 | 南京航空航天大学 | Integrally-broken-type frangible cover with stepped cutting plane and preparation method thereof |
| CN111575875A (en) * | 2020-04-23 | 2020-08-25 | 南京航空航天大学 | Fragile cap is with three-dimensional machine weaving prefabricated part that contains weak area |
| 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 |
| CN115479501A (en) * | 2022-09-06 | 2022-12-16 | 上海交通大学 | Multi-flap resin-based composite material fragile protective cover and preparation method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11183090A (en) * | 1997-12-24 | 1999-07-06 | Mitsubishi Electric Corp | Firing apparatus for missile |
| CN1844839A (en) * | 2006-04-30 | 2006-10-11 | 南京航空航天大学 | Integral impacting type composite canister cover |
| CN1844840A (en) * | 2006-04-30 | 2006-10-11 | 南京航空航天大学 | Frangible composite canister cover |
| CN201653274U (en) * | 2010-03-25 | 2010-11-24 | 中国兵器工业第五九研究所 | Easy-breaking through cover of tube/box type projectile weapon |
| CN102313491A (en) * | 2011-08-02 | 2012-01-11 | 南京航空航天大学 | Integral bursting type composite material launching box cover and manufacturing method thereof |
| CN103542773A (en) * | 2013-11-04 | 2014-01-29 | 上海燕兴科技实业有限公司 | Fragile rear cover of launching cylinder of weapon system |
-
2014
- 2014-03-12 CN CN201410089075.1A patent/CN103913098A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11183090A (en) * | 1997-12-24 | 1999-07-06 | Mitsubishi Electric Corp | Firing apparatus for missile |
| CN1844839A (en) * | 2006-04-30 | 2006-10-11 | 南京航空航天大学 | Integral impacting type composite canister cover |
| CN1844840A (en) * | 2006-04-30 | 2006-10-11 | 南京航空航天大学 | Frangible composite canister cover |
| CN201653274U (en) * | 2010-03-25 | 2010-11-24 | 中国兵器工业第五九研究所 | Easy-breaking through cover of tube/box type projectile weapon |
| CN102313491A (en) * | 2011-08-02 | 2012-01-11 | 南京航空航天大学 | Integral bursting type composite material launching box cover and manufacturing method thereof |
| CN103542773A (en) * | 2013-11-04 | 2014-01-29 | 上海燕兴科技实业有限公司 | Fragile rear cover of launching cylinder of weapon system |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104864773A (en) * | 2015-05-08 | 2015-08-26 | 南京航空航天大学 | Composite material frangible cover enabling direction-pinpointed ejection and manufacturing method thereof |
| CN104864773B (en) * | 2015-05-08 | 2016-08-24 | 南京航空航天大学 | Orient composite Fragile cap and preparation method thereof of dishing out |
| CN104913692A (en) * | 2015-06-30 | 2015-09-16 | 湖北三江航天万峰科技发展有限公司 | Fragile cap |
| CN105043166A (en) * | 2015-07-20 | 2015-11-11 | 北京理工大学 | Low-impact overall ejection type launching canister front cover |
| TWI595909B (en) * | 2015-10-20 | 2017-08-21 | The 202Nd Arsenal Materiel Production Center | Bullet structure improved |
| CN109202437B (en) * | 2018-09-03 | 2019-11-12 | 郑州郑飞机电技术有限责任公司 | A kind of molding assembly method of composite material body storage box |
| CN109202437A (en) * | 2018-09-03 | 2019-01-15 | 郑州郑飞机电技术有限责任公司 | A kind of molding assembly method of composite material body storage box |
| CN110697066A (en) * | 2019-10-10 | 2020-01-17 | 北京特种机械研究所 | Fragile cover with mooring, buffering and ablation-proof functions |
| CN111322909A (en) * | 2020-03-03 | 2020-06-23 | 南京航空航天大学 | Integrally-broken-type frangible cover with stepped cutting plane and preparation method thereof |
| CN111575875A (en) * | 2020-04-23 | 2020-08-25 | 南京航空航天大学 | Fragile cap is with three-dimensional machine weaving prefabricated part that contains weak area |
| 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 |
| CN115479501A (en) * | 2022-09-06 | 2022-12-16 | 上海交通大学 | Multi-flap resin-based composite material fragile protective cover and preparation method thereof |
| CN115479501B (en) * | 2022-09-06 | 2024-03-26 | 上海交通大学 | Multi-flap type resin matrix composite fragile protective cover and preparation method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103913098A (en) | Multi-petal composite material launching box cover and preparation method thereof | |
| CN107738457A (en) | A kind of integrated forming technique of unmanned aerial vehicle body | |
| CN1844839B (en) | Integral impacting type composite canister cover | |
| US10118348B2 (en) | Aircraft component with closed box structure | |
| JP4236661B2 (en) | Method and apparatus for manufacturing a helicopter rotor fairing and fairings obtained thereby | |
| CN104864773B (en) | Orient composite Fragile cap and preparation method thereof of dishing out | |
| US10792891B2 (en) | Polymer matrix-ceramic matrix hybrid composites for high thermal applications | |
| CN106515045B (en) | Composite material joint skirt automatic placement molding method | |
| KR950007642B1 (en) | Ballistic helmet body | |
| CN111002646A (en) | Electromagnetic shielding interlayer composite material frangible cover and preparation method thereof | |
| CN105690790B (en) | Composite material blade integral formation method and device used for wind power generation | |
| CN109849368A (en) | A kind of composite material tape cone section Varying-thickness revolution attachment structure processing method | |
| CN104908975B (en) | Aircraft fore-body and internal waverider-derived hypersonic inlet integrated design method | |
| US9506349B2 (en) | Wind turbine component comprising radar-absorbing material | |
| US20170254212A1 (en) | A guide vane made of composite material for a gas turbine engine, and it's method of fabrication | |
| KR100831309B1 (en) | Method for reinforcement manufacturing a composite sabot applying band/hoop lamination | |
| CN105690821A (en) | Wet winding forming method for fiber-reinforced resin matrix composite sandwich pipe | |
| CN106584881B (en) | Full carbon fiber structural of a kind of hollow out hat shape rice word reinforcement and preparation method thereof | |
| CN104768735B (en) | Cylinder-like shell and the manufacture method of cylinder-like shell | |
| CN111322909B (en) | Integrally-broken-type frangible cover with stepped cutting plane and preparation method thereof | |
| CN109204851A (en) | Oiltank structure and its manufacturing method | |
| CN105751530A (en) | Blade manufacturing method | |
| CN110481058A (en) | Inside it is embedded in the winding intracorporal lightweight cable hood forming method of shell | |
| CN109849370A (en) | The processing method of connection structure between a kind of rocket/missile propulsive plant grade | |
| CN204730751U (en) | Orientation is dished out composite Fragile cap |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140709 |