CN2926979Y - Easily-broken composite-film cap - Google Patents
Easily-broken composite-film cap Download PDFInfo
- Publication number
- CN2926979Y CN2926979Y CNU2006200730630U CN200620073063U CN2926979Y CN 2926979 Y CN2926979 Y CN 2926979Y CN U2006200730630 U CNU2006200730630 U CN U2006200730630U CN 200620073063 U CN200620073063 U CN 200620073063U CN 2926979 Y CN2926979 Y CN 2926979Y
- Authority
- CN
- China
- Prior art keywords
- layer
- membrane cover
- weak area
- film cover
- along
- 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.)
- Expired - Fee Related
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- 239000002131 composite material Substances 0.000 claims abstract description 12
- 239000011521 glass Substances 0.000 claims abstract description 9
- 238000007373 indentation Methods 0.000 claims description 16
- 239000004744 fabric Substances 0.000 claims description 15
- 239000005030 aluminium foil Substances 0.000 claims description 14
- 238000000034 method Methods 0.000 abstract description 11
- 239000003822 epoxy resin Substances 0.000 abstract description 9
- 229920000647 polyepoxide Polymers 0.000 abstract description 9
- 239000012528 membrane Substances 0.000 abstract description 8
- 239000000463 material Substances 0.000 abstract description 5
- 230000009471 action Effects 0.000 abstract description 3
- 238000004026 adhesive bonding Methods 0.000 abstract description 2
- 239000011888 foil Substances 0.000 abstract description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 abstract 1
- 229910052782 aluminium Inorganic materials 0.000 abstract 1
- 239000000835 fiber Substances 0.000 abstract 1
- 230000003014 reinforcing effect Effects 0.000 abstract 1
- 239000002759 woven fabric Substances 0.000 abstract 1
- 239000010408 film Substances 0.000 description 45
- 239000010410 layer Substances 0.000 description 35
- 238000012360 testing method Methods 0.000 description 14
- 239000003292 glue Substances 0.000 description 6
- 238000013461 design Methods 0.000 description 5
- 239000003365 glass fiber Substances 0.000 description 5
- 230000009172 bursting Effects 0.000 description 4
- 238000006748 scratching Methods 0.000 description 4
- 230000002393 scratching effect Effects 0.000 description 4
- 238000005336 cracking Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 description 2
- 238000004140 cleaning Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- 229920003023 plastic Polymers 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 229920000742 Cotton Polymers 0.000 description 1
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 1
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000013100 final test Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000005357 flat glass Substances 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 238000006062 fragmentation reaction Methods 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 210000004209 hair Anatomy 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 239000004816 latex Substances 0.000 description 1
- 229920000126 latex Polymers 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 229920006267 polyester film Polymers 0.000 description 1
- 238000012805 post-processing Methods 0.000 description 1
- 230000037452 priming Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000010409 thin film Substances 0.000 description 1
Images
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
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/077—Doors or covers for launching tubes
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Laminated Bodies (AREA)
Abstract
The utility model relates to an easily crushing composite material membrane cover and pertains to the technical field of missile launching. The materials for a basal body layer and an auxiliary layer of the membrane cover body are high-strength glass woven fabric and epoxy resin and are paved along the fiber orientations with angles of 0 degree and 90 degrees in a bid to prove the chance of crazing along preset directions. In terms of structure, the utility model mainly adopts a method combining central cross notching and high-strength threads or to say a method of applying central cross notching on the membrane cover first and then filling high-strength threads and gluing. Thus, membrane cover may, under the action of a warhead, have the other half of a weak area still being under stress under the pulling of the high-strength threads and further craze at the same time once one half of the weak area craze, thereby making four petals on the weak areas craze at the same time. Meanwhile, to lower the possibility that the membrane cover crazes along other directions, four pieces of reinforced sheets are arranged at two sides of a rip line in a bid to strengthen the two sides of the rip line. In a bid to satisfy the bearing requirement of the interior of the membrane cover, one layer of auxiliary layer is also be arranged on the weak area to play a reinforcing role. Additionally, the inner surface of the basal body layer is pasted with one piece of aluminum foil as a shielding layer.
Description
Technical field
Frangible composite canister cover of the present utility model belongs to the MISSILE LAUNCHING technical field.
Background technology
The design of MISSILE LAUNCHING lid is to influence guided missile to reflect one of key factor of ability fast.Therefore, when development missile storing firing box, the design of case lid is extremely important.Major requirement is to bear certain pressure reduction, and good seal performance is opened rapidly when launching a guided missile.For satisfying above-mentioned requirements, the normal in the past mechanical cap that adopts of MISSILE LAUNCHING case lid, blasting bolt is opened lid etc., but the shortcoming of the equal various degrees of these case lids is opened lid as machinery need open with hydraulic system, mechanism's complexity, not only increased the weight of case and delayed the operating time, the reaction of blast lid is opened rapidly than mechanical cap, but shoots and keep in repair more complicated again, and adopt the priming system transportation, store difficulty.
For improving MISSILE LAUNCHING efficient, satisfy the requirement that army fights fast, developed a kind of frangible membrane will lid abroad, referring to U.S. Pat Pat.4498368,1985, this kind film cover is the basic composition material with glass fabric and epoxy resin, on the layer of difference shop, scribe tear line and form weak area, film cover can be born certain well-distributed pressure and just can be made film cover with projected path eight lobe fragmentations under less concentrated force, is swift in response, and has improved MISSILE LAUNCHING efficient.But the woven cloth number of plies that this kind film cover is laid is more, and film cover is thicker, and different shops interlayer angle differs, prefabricated weak area complexity, and actual moulding difficulty is bigger; And influencing each other when reducing adjacent MISSILE LAUNCHING set up the frothed latex safeguard procedures at the film cover outer surface.Therefore, this film cover of introducing on the foreign patent can not directly be used.
Summary of the invention
The purpose of this utility model is to provide a kind of existing certain bearing capacity, can destroy at less concentrated force again, and fragment does not influence the composite material film lid of MISSILE LAUNCHING.
A kind of frangible composite canister cover, mainly by high strength glass fiber sheet with epoxy resin is compound and spread layer by 0 ° of machine direction, 90 ° forms as base layer, the base layer inner surface be pasted with aluminium foil as screen layer to be used for shielding electromagnetic wave, weak area is arranged on the base layer, it is characterized in that:
(1), the form of the weak area on the described base layer is the central cross indentation, and lay and gummed has high strength yarn along the indentation direction;
(2), also post four reinforced sheets that cross indentation both sides played humidification along central cross indentation both sides at the base layer outer surface;
(3), the weak area between base layer and screen layer also is equipped with one deck and can bears the glass cloth of internal pressure as auxiliary layer.
Adopt the method for above-mentioned central cross indentation+high strength yarn, be because when MISSILE LAUNCHING, because bullet can not cover the weak area center by point-device alignment thin film, therefore, after very easily causing half at first to ftracture, discharged the situation that causes second half to ftracture owing to load.Adopted the method for cross indentation+high strength yarn, can make film cover under the bullet effect, if half weak area cracking, second half weak area load still under the involving of high strength yarn causes second half also to ftracture simultaneously, thereby weak area position pintongs is ftractureed simultaneously.
Base layer selects for use high strength glass fiber sheet+epoxy resin as stock, in view of glass fabric has along machine direction, i.e. 0 ° and 90 ° of characteristics that direction is easy to tear so spread layer according to 0 °, 90 °, can improve the possibility of tearing along predetermined direction like this.
Adopting auxiliary layer, is because base layer is carved disconnectedly at the layer of cloth at weak area place, can make guided missile bursting power also can reduce greatly.But film cover also needs to satisfy inner bearing requirements simultaneously, and weak area still need have certain intensity, therefore increases layer of glass cloth as auxiliary layer at weakness zone.
Arrange reinforced sheet be because: although 0 °/90 ° woven cloth are difficult for tearing along other direction, but in process of the test, find under the uneven load effect, destroy track and may turn to other direction, as when 0 ° is torn, forwarding 90 ° of directions to, therefore for guaranteeing that film cover tears along machine direction, increase by four sheet glass cloth in the tear line both sides, make the enhancing of tear line both sides, thereby reduce the possibility that film cover is torn along other direction, guarantee that film cover tears along desired trajectory.
Film cover size in the said structure, the concrete number of plies of base layer, weak area size all need to adopt Finite Element Method to carry out whole and local design analysis according to actual engineering objective, obtain concrete film cover version.
Made certain film cover material object and carried out verification experimental verification according to above-mentioned design.The pressurising result of the test shows, the air pressure that the film cover of made fully can bearing certain pressure, and the film cover air-tightness is fully by resin content and resin+aluminium foil control, and air-tightness also can meet the demands; The guided missile burst testing is the result show, film cover is according to the form cracking of projected path with pintongs, guided missile goes out tin rear film lid fully can well be torn along flange circle periphery, and what do not influence guided missile normally goes out tube, and can be under less bursting load (about 80Kg) destruction.
Description of drawings
Fig. 1 is a frangible composite canister cover outer surface structure schematic diagram.
Fig. 2 is a frangible composite canister cover inner surface structure schematic diagram.
Fig. 3 is a frangible composite canister cover mould side view.
Fig. 4 is a frangible composite canister cover mould vertical view.
Fig. 5 is a film cover burst testing device schematic diagram.
Label title among Fig. 1: 1, base layer, 2, the central cross indentation, 3, reinforced sheet.
Label title among Fig. 2: 4, foil shielding layer, 5, high strength yarn, 6, auxiliary layer, 7, weak area.
Label title among Fig. 3: 8, film cover, 9, patrix, 10, counterdie, 11, bolt.
Label title among Fig. 5: 12, bullet, 13, load transducer, 14, pressurized strut.
The specific embodiment
In conjunction with Fig. 1, shown in Figure 2, the method for central cross indentation 2+ high strength yarn 5 is adopted in the design of the utility model frangible composite canister cover, engraves central cross indentation 2 promptly for film cover 8, fills out high strength yarn 5 and gummed.Like this, film cover 8 is under the bullet effect, if half weak area 7 crackings, second half weak area 7 load still under the involving of high strength yarn causes second half also to ftracture simultaneously.In order to reduce the possibility that film cover 8 is torn along other direction, guarantee that film cover 8 tears along desired trajectory, increase by four reinforced sheets 3 in the tear line both sides, make the tear line both sides strengthen.In order to satisfy the inner bearing requirements of film cover, weak area also increases by 6 booster actions of one deck auxiliary layer.In addition, the inner surface at base layer is pasted with aluminium foil as screen layer 4.
For selecting for use of material, the base layer material can be selected high strength glass fiber sheet for use, with epoxy resin as glueing material, in view of glass fabric has along machine direction, i.e. 0 ° and 90 ° of characteristics that direction is easy to tear, so spread layer according to 0 °, 90 °, can improve the possibility of tearing like this along predetermined direction.High strength yarn is selected the high-strength glass fibre that is dipped into gel state through epoxy resin prepolymer for use.Screen layer can be used aluminium foil.
Embodiment 1:
Present embodiment is the film cover manufacture craft.The film cover base layer adopts several layers 0.1 plain woven glass cloth and epoxy resin to be composited, and according to the described prefabricated weak area of technical scheme, and pastes aluminium foil to do shielding action at the film cover inner surface.
1, film cover base layer moulding process
1) cleaning mould, mould is as shown in Figure 3, Figure 4;
2) on counterdie and patrix, smear demoulding fat, on counterdie, smear the low temperature grease;
3) on counterdie, spread aluminium foil and prune by the profile of counterdie, with the cotton yarn that speckles with acetone that the cleaning oil pollution on the aluminium foil is clean and finish cross hairs, find out the position, center;
4) make reinforced sheet prepreg and place after 2 hours and to use on request;
5) reinforced sheet that preimpregnation is good sticks on the aluminium foil on request and uses the plastics doctor blade;
6) dispose glue on request;
7) be layered on ground floor cloth on the counterdie and scraped glue;
8) on counterdie, spread layer of cloth and scraped glue by same angle according to this;
9) cover polyester film, unnecessary glue and bubble are scraped with the plastics scraper;
10) upper mould cover is connected with cotter bolt and counterdie completing on the counterdie of cloth;
11) treat to carry out the demoulding after 24 hours film cover are solidified.
2, the concrete technology of the prefabricated cross indentation of film cover
1) film cover is scratched by cross with blade at the prefabricated indentation of the film cover of making place, the length of scratching is that starting point respectively is that 20mm is long with the cross center;
2) it is long the aluminium foil of film cover to be scratched again 20mm, the aluminium foil of scratching is dug and is noted aluminium foil not being torn, and is careful when scratching, and film cover is not scratched;
3) make high strength yarn prepreg and place and treated that high strength yarn used in 4 hours to gel state;
4) with alcohol the place of scratching is cleaned out, lay along direction of check, lay the second layer, the 3rd layer, the 4th layer high strength yarn with the method again after the ground floor high strength yarn lays with high strength yarn (being glass fiber);
5) spread upon epoxide-resin glue on the high strength yarn uniformly, and lay a fritter 0.1 plain woven glass cloth and strengthen, with the aluminium foil shop reposition of digging, cut the circular aluminium foil of an about 50mm radius, evenly be coated with and spread epoxide-resin glue, it is layered on cross indent locations place, and pressurization back curing behind the processing release paper is placed and after 24 hours processing release paper is removed on the pad.
The film cover of prefabricated cross indentation is placed baking oven, is post processing 3 hours under 50 ℃ the environment in temperature, takes out after cooling.
Embodiment 2:
Present embodiment is film cover pressurising, air seal test and burst testing detailed process:
1, pressurising, air seal test
As shown in Figure 5, on request film cover is installed on the test tube, opens air compressor, turn off air compressor after waiting to be added to 0.4MPa pressure, open intake valve pressurising slowly and examine the distortion and the sound of film cover, wait to be charged to and promptly open vent valve behind the certain pressure and lay down air pressure.
2, burst testing
The film cover that will satisfy the air seal test requirement on request is installed on the burst testing tube, as shown in Figure 5.Open the electric hydaulic car, treat to turn off the electric hydaulic car after pressure is charged to 12MPa pressure, open the mobile slowly bullet bogusware of inlet valve, observe the frictional force that shows on the electronic scale and frictional force is removed by the electronic scale zeroing, stop mobile bullet bogusware, connect displacement transducer and begin test, open the mobile slowly bullet bogusware of inlet valve, displacement note zero when bullet Contact Thin membrane cover, examine distortion and the sound and the video recording of film cover in the test, when bullet bursting film, write down maximum bursting load, continue mobile bullet bogusware, when bullet all tears film cover, write down maximum and tear load, withdrawal bullet bogusware, take a picture and record final test phenomenon, finish test.
Claims (1)
1, a kind of frangible composite canister cover mainly comprises by 0 ° of machine direction, 90 ° of base layers (1) of spreading layer, is pasted with aluminium foil as screen layer at base layer (1) inner surface, and weak area (7) is arranged on the base layer (1), it is characterized in that:
(1), the form of the weak area (7) on the described base layer (1) is central cross indentation (2), and lay and gummed has high strength yarn (5) along the indentation direction;
(2), also post four reinforced sheets (3) that cross indentation (2) both sides played humidification along central cross indentation (2) both sides at base layer (1) outer surface;
(3), the weak area (7) between base layer (1) and screen layer (4) also is equipped with one deck and can bears the glass cloth of internal pressure as auxiliary layer (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2006200730630U CN2926979Y (en) | 2006-04-30 | 2006-04-30 | Easily-broken composite-film cap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2006200730630U CN2926979Y (en) | 2006-04-30 | 2006-04-30 | Easily-broken composite-film cap |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2926979Y true CN2926979Y (en) | 2007-07-25 |
Family
ID=38281229
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2006200730630U Expired - Fee Related CN2926979Y (en) | 2006-04-30 | 2006-04-30 | Easily-broken composite-film cap |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2926979Y (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| WO2016144423A1 (en) * | 2015-03-12 | 2016-09-15 | Raytheon Company | Tube to bulkhead bonded joint design |
| TWI595909B (en) * | 2015-10-20 | 2017-08-21 | The 202Nd Arsenal Materiel Production Center | Bullet structure improved |
| CN109703062A (en) * | 2019-01-31 | 2019-05-03 | 上海材料研究所 | Using the method for vacuum assisted resin diffusion moulding process production firing box end cap |
| 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 |
| CN110953929A (en) * | 2019-11-12 | 2020-04-03 | 南京航空航天大学 | Breakable lid of carbon-fibre composite |
-
2006
- 2006-04-30 CN CNU2006200730630U patent/CN2926979Y/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN102313491B (en) * | 2011-08-02 | 2014-11-26 | 南京航空航天大学 | Integral bursting type composite material launching box cover and manufacturing method thereof |
| WO2016144423A1 (en) * | 2015-03-12 | 2016-09-15 | Raytheon Company | Tube to bulkhead bonded joint design |
| US10240896B2 (en) | 2015-03-12 | 2019-03-26 | Raytheon Company | Tube to bulkhead bonded joint design |
| TWI595909B (en) * | 2015-10-20 | 2017-08-21 | The 202Nd Arsenal Materiel Production Center | Bullet structure improved |
| CN109703062A (en) * | 2019-01-31 | 2019-05-03 | 上海材料研究所 | Using the method for vacuum assisted resin diffusion moulding process production firing box end cap |
| 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 |
| CN110953929A (en) * | 2019-11-12 | 2020-04-03 | 南京航空航天大学 | Breakable lid of carbon-fibre composite |
| CN110953929B (en) * | 2019-11-12 | 2022-04-08 | 南京航空航天大学 | Breakable lid of carbon-fibre composite |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |