CN106225576A - A kind of bulletproof armour for Helicopter Seat and manufacture method thereof - Google Patents
A kind of bulletproof armour for Helicopter Seat and manufacture method thereof Download PDFInfo
- Publication number
- CN106225576A CN106225576A CN201610849664.4A CN201610849664A CN106225576A CN 106225576 A CN106225576 A CN 106225576A CN 201610849664 A CN201610849664 A CN 201610849664A CN 106225576 A CN106225576 A CN 106225576A
- Authority
- CN
- China
- Prior art keywords
- armour
- plate
- carbon fiber
- bulletproof
- intermediate plate
- 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
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 15
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 45
- 239000004917 carbon fiber Substances 0.000 claims abstract description 45
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 44
- 239000000853 adhesive Substances 0.000 claims abstract description 30
- 230000001070 adhesive effect Effects 0.000 claims abstract description 30
- 229910052580 B4C Inorganic materials 0.000 claims abstract description 27
- INAHAJYZKVIDIZ-UHFFFAOYSA-N boron carbide Chemical compound B12B3B4C32B41 INAHAJYZKVIDIZ-UHFFFAOYSA-N 0.000 claims abstract description 26
- 239000000919 ceramic Substances 0.000 claims abstract description 25
- 239000004705 High-molecular-weight polyethylene Substances 0.000 claims abstract description 24
- 239000003292 glue Substances 0.000 claims abstract description 23
- 239000003822 epoxy resin Substances 0.000 claims abstract description 21
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 21
- 239000004744 fabric Substances 0.000 claims abstract description 19
- 238000004026 adhesive bonding Methods 0.000 claims abstract description 14
- 238000005253 cladding Methods 0.000 claims abstract description 11
- 238000002360 preparation method Methods 0.000 claims abstract description 6
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 30
- 239000003795 chemical substances by application Substances 0.000 claims description 23
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 20
- 229910052593 corundum Inorganic materials 0.000 claims description 10
- 239000010431 corundum Substances 0.000 claims description 10
- 235000016768 molybdenum Nutrition 0.000 claims description 10
- 238000005498 polishing Methods 0.000 claims description 10
- 239000004576 sand Substances 0.000 claims description 10
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 8
- 229910052796 boron Inorganic materials 0.000 claims description 8
- 230000008859 change Effects 0.000 claims description 7
- 239000004593 Epoxy Substances 0.000 claims description 6
- 239000004698 Polyethylene Substances 0.000 claims description 6
- -1 polyethylene Polymers 0.000 claims description 6
- 229920000573 polyethylene Polymers 0.000 claims description 6
- 150000001412 amines Chemical class 0.000 claims description 5
- 238000010276 construction Methods 0.000 claims description 5
- 239000011521 glass Substances 0.000 claims description 5
- 238000003756 stirring Methods 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- 229910052799 carbon Inorganic materials 0.000 claims description 4
- 238000006073 displacement reaction Methods 0.000 claims description 4
- 229920005989 resin Polymers 0.000 claims description 4
- 239000011347 resin Substances 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims 1
- 229920002554 vinyl polymer Polymers 0.000 claims 1
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000004140 cleaning Methods 0.000 abstract 1
- 238000007789 sealing Methods 0.000 abstract 1
- 239000000463 material Substances 0.000 description 6
- 238000003763 carbonization Methods 0.000 description 4
- 230000015556 catabolic process Effects 0.000 description 3
- 229920002521 macromolecule Polymers 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- 238000005303 weighing Methods 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 2
- 239000011230 binding agent Substances 0.000 description 2
- 230000002829 reductive effect Effects 0.000 description 2
- 238000003556 assay Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000686 essence Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000002427 irreversible effect Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000036961 partial effect Effects 0.000 description 1
- 229910052573 porcelain Inorganic materials 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
- F41H5/00—Armour; Armour plates
- F41H5/02—Plate construction
- F41H5/04—Plate construction composed of more than one layer
- F41H5/0414—Layered armour containing ceramic material
- F41H5/0428—Ceramic layers in combination with additional layers made of fibres, fabrics or plastics
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Laminated Bodies (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Ceramic Products (AREA)
Abstract
The invention discloses a kind of bulletproof armour for Helicopter Seat and manufacture method thereof, bulletproof armour includes being constituted by by boron carbide ceramics splice plate, carbon fiber intermediate plate and the High molecular weight polyethylene plate of epoxide-resin glue successively fixing bonding, and the outside cladding of armour is bonded with brocade silk sail silk fabric layer；Manufacture method includes polish plate, cleaning adhesive surface, preparation adhesive glue, the gluing that carries out plate, vacuum sealing and hot setting.Beneficial effects of the present invention: bulletproof armour of the present invention can reduce density and the volume of Helicopter Seat bulletproof armour on the basis of ensureing Helicopter Seat ballistic requirements.
Description
Technical field
The present invention relates to bulletproof armour technical field, it particularly relates to a kind of bulletproof armour for Helicopter Seat
And manufacture method.
Background technology
Being applied to the bulletproof armour of Helicopter Seat at present, its performance exists for preventing 12.7mm bore armor-piercing incendiary
At 1000m, Firing Velocity is the armor-piercing incendiary of 488m/s, and its shooting performance is relatively low, it is impossible to the hit velocity that Defence Standard specifies
The most breakdown for the armor-piercing incendiary shooting of 488m/s, its weight is the heaviest simultaneously, and armour thickness is big (about 28mm), identical anti-
Mask amasss lower weight and is unfavorable for that greatly (empty weight is the finger being of great value for helicopter for the load-carrying of helicopter and mobility
Mark), Protective armor is plate simultaneously, it is impossible to accomplish abnormally-structured, space Appropriate application is existed the biggest defect (due to
Helicopter inner space is less, and the bulk design of equipment is particularly important).
Number of patent application is that the Chinese patent application of 201480023646.X discloses a kind of ballistic resistant armor articles, specifically public
Open: its comprise at least one towards the ground floor of projectile and at least one second layer, at least one second layer described is neighbouring
At least one ground floor described towards object to be protected, wherein under ballistic event, at least one ground floor described can
Experience hits the irreversible transition caused.Though above-mentioned patent application can improve the barrier propterty of bulletproof armour, but does not accounts for
The density of bulletproof armour and volume.
Summary of the invention
It is an object of the invention to propose a kind of bulletproof armour for Helicopter Seat and manufacture method thereof, it is possible to protecting
Density and the volume of Helicopter Seat bulletproof armour is reduced on the basis of card Helicopter Seat ballistic requirements.
For realizing above-mentioned technical purpose, the technical scheme is that and be achieved in that:
A kind of bulletproof armour for Helicopter Seat, including armour, described armour is depended on by by epoxide-resin glue
The boron carbide ceramics splice plate of secondary fixing bonding, carbon fiber intermediate plate and High molecular weight polyethylene plate are constituted, described armour
Outside cladding is bonded with brocade silk sail silk fabric layer.
Further, the thickness of described boron carbide ceramics splice plate is 11mm, and the thickness of described carbon fiber intermediate plate is 3-
5mm, the thickness of described High molecular weight polyethylene plate is 9-10mm.
Further, described boron carbide ceramics splice plate is that T font intersection fissure of displacement splicing construction is arranged.
Further, described armour is made up of middle flat board and the curved bend folding part being wholely set with flat board two ends.
The manufacture method of a kind of bulletproof armour for Helicopter Seat as above, comprises the following steps:
1) using the adhesive surface of the corundum sand papering carbon fiber intermediate plate of 60 molybdenums, the polishing time is 5-6 minute；
2) use acetone to clean the adhesive surface of carbon fiber intermediate plate, use alcohol washes High molecular weight polyethylene plate and carbonization
The adhesive surface of boron pottery splice plate；
3) preparation epoxy resin glue caking agent: weigh the modified epoxy of 50 ± 4g and the modified amine solidification of 10 ± 1g
Agent is poured in beaker and is mixed, and stirs 1 minute with Glass rod；
4) until step 2) in adhesive surface on acetone clean after carbon fiber and ethanol is evaporated completely, be 25 ± 5 DEG C in temperature,
The epoxy resin glue caking agent of 20 ± 2g is weighed respectively by carbon fiber intermediate plate and height under the working environment of relative humidity≤65%
Molecular weight polyethylene plate and carbon fiber intermediate plate and boron carbide ceramics splice plate are glued, epoxy resin to be got rid of in gluing procedures
The bubble of glue caking agent, make between carbon fiber intermediate plate and High molecular weight polyethylene plate and carbon fiber intermediate plate and boron carbide pottery
Fit between porcelain splice plate smooth, justified margin；
5) armour vacuum good for gluing is sealed；
6) armour of vacuum good seal is stored 100 minutes in the couveuse of 80 DEG C；
7) using the lateral surface of the corundum sand papering armour of 60 molybdenums, the polishing time is 5-6 minute；
8) lateral surface of alcohol washes armour is used；
9), after the ethanol until armour lateral surface is evaporated completely, XY-401 adhesive is used brocade silk sail silk fabric layer cladding to be glued at
The lateral surface of armour；
10) armour that cladding is bonded with brocade silk sail silk fabric layer stores 100 minutes in the couveuse of 60 DEG C.
Further, the thickness of described boron carbide ceramics splice plate is 11mm, and the thickness of described carbon fiber intermediate plate is 3-
5mm, the thickness of described High molecular weight polyethylene plate is 9-10mm.
Further, described boron carbide ceramics splice plate is that T font intersection splicing construction is arranged.
Further, the polyurethane-modified resin of High molecular weight polyethylene plate employing is suppressed under the pressure of 20Mpa and is formed.
Beneficial effects of the present invention: bulletproof armour of the present invention can subtract on the basis of ensureing Helicopter Seat ballistic requirements
The density of little Helicopter Seat bulletproof armour and volume.
Accompanying drawing explanation
Fig. 1 is the partial cross sectional views of the bulletproof armour for Helicopter Seat described according to embodiments of the present invention；
Fig. 2 is the side view of armour described according to embodiments of the present invention；
Fig. 3 is the part-structure schematic diagram of boron carbide ceramics splice plate described according to embodiments of the present invention.
Shown in figure:
1-boron carbide ceramics splice plate；2-carbon fiber intermediate plate；3-High molecular weight polyethylene plate；4-brocade silk sail silk fabric layer；5-
Flat board；6-curved bend folding part.
Detailed description of the invention
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
Ground describes, it is clear that described embodiment is only a part of embodiment of the present invention rather than whole embodiments.Based on this
Embodiment in invention, the every other embodiment that those of ordinary skill in the art are obtained, broadly fall into the model of present invention protection
Enclose.
As shown in Figure 1-2, according to a kind of bulletproof armour for Helicopter Seat described in embodiments of the invention, including
Armour, described armour is by by the epoxide-resin glue successively boron carbide ceramics splice plate 1 of fixing bonding, carbon fiber intermediate plate
2 and High molecular weight polyethylene plate 3 constitute, the outside of described armour cladding is bonded with brocade silk sail silk fabric layer 4.
Time specifically used, using boron carbide ceramics splice plate 1 as out surface, bullet is beaten on boron carbide ceramics splice plate 1
Form reverse taper holes, it is possible to farthest destroying the impulsive force of bullet, High molecular weight polyethylene plate 3, as backboard, passes through plasticity
Deformation absorbs the last energy of bullet, reaches the effect making bulletproof armour of the present invention the most breakdown.It addition, be coated with outside armour
The bright and beautiful silk sail silk fabric layer 4 of bonding can not only further improve the impact capacity of boron carbide ceramics splice plate 1, and is prevented from
The fragment hit down by bullet on armour produces and splashes.
In the above-described embodiments, the thickness of described boron carbide ceramics splice plate 1 is preferably 11mm, described carbon fiber intermediate plate
The thickness of 2 is preferably 3-5mm, and the thickness of described High molecular weight polyethylene plate 3 is preferably 9-10mm.Above-mentioned arrange on the one hand in order to
Bulletproof armour of the present invention is made to disclosure satisfy that under the armor-piercing incendiary that hit velocity is 488m/s and bore is 12.7mm hits
The most breakdown, on the other hand in order to account for the inner space in helicopter cabin less.
In the above-described embodiments, as it is shown on figure 3, described boron carbide ceramics splice plate 1 intersects fissure of displacement splicing construction in T font
Arrange.For the boron carbide ceramics splice plate 1 of identical protection volume, T font is used to intersect fissure of displacement structure than cross-shaped configuration
Intensity can have greatly improved.
In the above-described embodiments, in order to reduce this in the case of guarantee bulletproof armour barrier propterty does not reduces further
Interior of aircraft space is taken by bright bulletproof armour, and described armour is wholely set by middle flat board 5 with flat board 5 two ends
Curved bend folding part 6 is constituted.
The invention also discloses the manufacture method of the above-mentioned bulletproof armour for Helicopter Seat:
Embodiment 1
Described manufacture method comprises the following steps:
1) using the adhesive surface of the corundum sand papering carbon fiber intermediate plate 2 of 60 molybdenums, the polishing time is 5 minutes；
2) use acetone to clean the adhesive surface of carbon fiber intermediate plate 2, use alcohol washes High molecular weight polyethylene plate 3 and carbon
Change the adhesive surface of boron pottery splice plate 1；
3) preparation epoxy resin glue caking agent: the modified amine curing agent of the modified epoxy and 11g that weigh 54g is poured into
Mixing in beaker, and stir 1 minute with Glass rod, the epoxy resin glue caking agent prepared need to use in 40 minutes
Complete；
4) until step 2) in adhesive surface on acetone clean after carbon fiber and ethanol is evaporated completely, be 20 DEG C in temperature, phase
To weighing the epoxy resin glue caking agent of 18g under the working environment of humidity≤65% respectively by carbon fiber intermediate plate 2 and macromolecule
Weight polyethylene board 3 and carbon fiber intermediate plate 2 and boron carbide ceramics splice plate 1 are glued, epoxy resin to be got rid of in gluing procedures
The bubble of glue caking agent, makes between carbon fiber intermediate plate 2 and High molecular weight polyethylene plate 3 and carbon fiber intermediate plate 2 and carbonization
Fit between boron pottery splice plate 1 smooth, justified margin；
5) armour vacuum good for gluing is sealed；
6) armour of vacuum good seal is stored 100 minutes in the couveuse of 80 DEG C solidify；
7) using the lateral surface of the corundum sand papering armour of 60 molybdenums, the polishing time is 5 minutes；
8) lateral surface of alcohol washes armour is used；
9), after the ethanol until armour lateral surface is evaporated completely, use XY-401 adhesive that brocade silk sail silk fabric layer 4 is coated with gluing
Lateral surface in armour；
10) cladding is bonded with brocade silk sail silk fabric layer 4 armour stores 100 minutes in the couveuse of 60 DEG C carry out consolidate
Change.
Embodiment 2
Described manufacture method comprises the following steps:
1) using the adhesive surface of the corundum sand papering carbon fiber intermediate plate 2 of 60 molybdenums, the polishing time is 6 minutes；
2) use acetone to clean the adhesive surface of carbon fiber intermediate plate 2, use alcohol washes High molecular weight polyethylene plate 3 and carbon
Change the adhesive surface of boron pottery splice plate 1；
3) preparation epoxy resin glue caking agent: the modified amine curing agent of the modified epoxy and 11g that weigh 54g is poured into
Mixing in beaker, and stir 1 minute with Glass rod, the epoxy resin glue caking agent prepared need to use in 40 minutes
Complete；
4) until step 2) in adhesive surface on acetone clean after carbon fiber and ethanol is evaporated completely, be 30 DEG C in temperature, phase
To weighing the epoxy resin glue caking agent of 22g under the working environment of humidity≤65% respectively by carbon fiber intermediate plate 2 and macromolecule
Weight polyethylene board 3 and carbon fiber intermediate plate 2 and boron carbide ceramics splice plate 1 are glued, epoxy resin to be got rid of in gluing procedures
The bubble of glue caking agent, makes between carbon fiber intermediate plate 2 and High molecular weight polyethylene plate 3 and carbon fiber intermediate plate 2 and carbonization
Fit between boron pottery splice plate 1 smooth, justified margin；
5) armour vacuum good for gluing is sealed；
6) armour of vacuum good seal is stored 100 minutes in the couveuse of 80 DEG C solidify；
7) using the lateral surface of the corundum sand papering armour of 60 molybdenums, the polishing time is 6 minutes；
8) lateral surface of alcohol washes armour is used；
9), after the ethanol until armour lateral surface is evaporated completely, use XY-401 adhesive that brocade silk sail silk fabric layer 4 is coated with gluing
Lateral surface in armour；
10) cladding is bonded with brocade silk sail silk fabric layer 4 armour stores 100 minutes in the couveuse of 60 DEG C carry out consolidate
Change.
Embodiment 3
Described manufacture method comprises the following steps:
1) using the adhesive surface of the corundum sand papering carbon fiber intermediate plate 2 of 60 molybdenums, the polishing time is 5 minutes；
2) use acetone to clean the adhesive surface of carbon fiber intermediate plate 2, use alcohol washes High molecular weight polyethylene plate 3 and carbon
Change the adhesive surface of boron pottery splice plate 1；
3) preparation epoxy resin glue caking agent: the modified amine curing agent of the modified epoxy and 10g that weigh 50g is poured into
Mixing in beaker, and stir 1 minute with Glass rod, the epoxy resin glue caking agent prepared need to use in 40 minutes
Complete；
4) until step 2) in adhesive surface on acetone clean after carbon fiber and ethanol is evaporated completely, be 25 DEG C in temperature, phase
To weighing the epoxy resin glue caking agent of 20g under the working environment of humidity≤65% respectively by carbon fiber intermediate plate 2 and macromolecule
Weight polyethylene board 3 and carbon fiber intermediate plate 2 and boron carbide ceramics splice plate 1 are glued, epoxy resin to be got rid of in gluing procedures
The bubble of glue caking agent, makes between carbon fiber intermediate plate 2 and High molecular weight polyethylene plate 3 and carbon fiber intermediate plate 2 and carbonization
Fit between boron pottery splice plate 1 smooth, justified margin；
5) armour vacuum good for gluing is sealed；
6) armour of vacuum good seal is stored 100 minutes in the couveuse of 80 DEG C solidify；
7) using the lateral surface of the corundum sand papering armour of 60 molybdenums, the polishing time is 6 minutes；
8) lateral surface of alcohol washes armour is used；
9), after the ethanol until armour lateral surface is evaporated completely, use XY-401 adhesive that brocade silk sail silk fabric layer 4 is coated with gluing
Lateral surface in armour；
10) cladding is bonded with brocade silk sail silk fabric layer 4 armour stores 100 minutes in the couveuse of 60 DEG C carry out consolidate
Change.
In terms of weight, first improve largely on material property proportion, reach single material on ballistic performance
Lifting 1/3, furthermore, using high-strength adhesive and high intensity crack arrest layer material (the high intensity crack arrest layer that the present invention selects
Material is brocade silk sail silk fabric layer 4) selections upper overall ballistic performance lifting 1/4, thus on the basis of guarantee bulletproof armour performance, subtract
The light weight of bulletproof armour.
At vpg connection, take full advantage of bending strength and the elasticity of ceramic wafer so that the bulletproof armour of the present invention can
Make the most abnormally-structured.
Binding agent, crack arrest layer material and conventional binding agent, the Data Comparison situation of crack arrest layer material that the present invention selects
As shown in table 1-table 4.
Table 1 conventional brocade silk plain weave silk fabric performance criteria value
Table 2 present invention uses brocade silk sail silk fabric layer performance criteria value
Bonded adhesives performance indications commonly used by table 3
| Inspection project | Examination requirements | Assay |
| Room temperature shear strength MPa | ≥25.0 | 33.7 |
| 100 DEG C of shear strengths MPa | ≥12.0 | 13.1 |
| 90 ° of board-to-board peel strengths N/cm | ≥20.0 | 47.5 |
Table 4 present invention uses bonded adhesives performance indications
Form it addition, High molecular weight polyethylene plate 3 uses polyurethane-modified resin to suppress under the pressure of 20Mpa, make
Polyethylene fibre intensity, modular ratio routine improve 50%.The performance of the High molecular weight polyethylene plate 3 that the present invention uses detects such as
Shown in table 5.
Table 5 V50Ballistic limit detection log
In sum, by means of the technique scheme of the present invention, bulletproof armour of the present invention can go straight up to support in guarantee
Density and the volume of Helicopter Seat bulletproof armour is reduced on the basis of chair ballistic requirements.
The foregoing is only presently preferred embodiments of the present invention, not in order to limit the present invention, all essences in the present invention
Within god and principle, any modification, equivalent substitution and improvement etc. made, should be included within the scope of the present invention.
Claims (8)
1. for a bulletproof armour for Helicopter Seat, including armour, it is characterised in that described armour is by passing through epoxy
Boron carbide ceramics splice plate (1), carbon fiber intermediate plate (2) and the High molecular weight polyethylene plate (3) of resin glue fixing bonding successively
Constituting, the outside cladding of described armour is bonded with brocade silk sail silk fabric layer (4).
Bulletproof armour for Helicopter Seat the most according to claim 1, it is characterised in that described boron carbide ceramics is spelled
The thickness of fishplate bar (1) is 11mm, and the thickness of described carbon fiber intermediate plate (2) is 3-5mm, described High molecular weight polyethylene plate (3)
Thickness be 9-10mm.
Bulletproof armour for Helicopter Seat the most according to claim 2, it is characterised in that described boron carbide ceramics is spelled
Fishplate bar (1) intersect in T font fissure of displacement splicing construction arrange.
Bulletproof armour for Helicopter Seat the most according to claim 1, it is characterised in that described armour is by centre
Flat board (5) and the curved bend folding part (6) being wholely set with flat board (5) two ends constitute.
5. the manufacture method of the bulletproof armour being used for Helicopter Seat as claimed in claim 1, it is characterised in that include
Following steps:
1) using the adhesive surface of corundum sand papering carbon fiber intermediate plate (2) of 60 molybdenums, the polishing time is 5-6 minute；
2) use acetone to clean the adhesive surface of carbon fiber intermediate plate (2), use alcohol washes High molecular weight polyethylene plate (3) and carbon
Change the adhesive surface of boron pottery splice plate (1)；
3) preparation epoxy resin glue caking agent: the modified amine curing agent of the modified epoxy and 10 ± 1g that weigh 50 ± 4g falls
Enter in beaker and mix, and stir 1 minute with Glass rod；
4) until step 2) in adhesive surface on acetone clean after carbon fiber and ethanol is evaporated completely, be 25 ± 5 DEG C in temperature, relatively
The epoxy resin glue caking agent of 20 ± 2g is weighed respectively by carbon fiber intermediate plate (2) and high score under the working environment of humidity≤65%
Sub-weight polyethylene board (3) and carbon fiber intermediate plate (2) and boron carbide ceramics splice plate (1) are glued, to get rid of in gluing procedures
The bubble of epoxy resin glue caking agent, makes between carbon fiber intermediate plate (2) and High molecular weight polyethylene plate (3) and in carbon fiber
Between fit between plate (2) and boron carbide ceramics splice plate (1) smooth, justified margin；
5) armour vacuum good for gluing is sealed；
6) armour of vacuum good seal is stored 100 minutes in the couveuse of 80 DEG C；
7) using the lateral surface of the corundum sand papering armour of 60 molybdenums, the polishing time is 5-6 minute；
8) lateral surface of alcohol washes armour is used；
9), after the ethanol until armour lateral surface is evaporated completely, XY-401 adhesive is used brocade silk sail silk fabric layer (4) cladding to be glued at
The lateral surface of armour；
10) armour that cladding is bonded with brocade silk sail silk fabric layer (4) stores 100 minutes in the couveuse of 60 DEG C.
The manufacture method of the bulletproof armour of Helicopter Seat the most according to claim 5, it is characterised in that described boron carbide
The thickness of pottery splice plate (1) is 11mm, and the thickness of described carbon fiber intermediate plate (2) is 3-5mm, described High molecular weight polyethylene
The thickness of plate (3) is 9-10mm.
The manufacture method of the bulletproof armour of Helicopter Seat the most according to claim 5, it is characterised in that described boron carbide
Pottery splice plate (1) intersects in T font splicing construction setting.
The manufacture method of the bulletproof armour of Helicopter Seat the most according to claim 7, it is characterised in that high-molecular-weight poly
Vinyl plate (3) uses polyurethane-modified resin to suppress under the pressure of 20Mpa and forms.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610849664.4A CN106225576A (en) | 2016-09-23 | 2016-09-23 | A kind of bulletproof armour for Helicopter Seat and manufacture method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610849664.4A CN106225576A (en) | 2016-09-23 | 2016-09-23 | A kind of bulletproof armour for Helicopter Seat and manufacture method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106225576A true CN106225576A (en) | 2016-12-14 |
Family
ID=58076480
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610849664.4A Pending CN106225576A (en) | 2016-09-23 | 2016-09-23 | A kind of bulletproof armour for Helicopter Seat and manufacture method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106225576A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114234721A (en) * | 2021-12-29 | 2022-03-25 | 咸宁海威复合材料制品有限公司 | Fireproof, heat-insulating and flame-retardant ultrahigh molecular weight polyethylene bulletproof plate and manufacturing method thereof |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3581620A (en) * | 1967-08-29 | 1971-06-01 | Norton Co | Armored seat for aircraft and the like |
| EP0293786A2 (en) * | 1987-06-04 | 1988-12-07 | Norton Company | Composite armored seat |
| US5164536A (en) * | 1989-11-24 | 1992-11-17 | Societe Europeenne De Propulsion | Composite armored seat, and method of manufacture |
| US6073884A (en) * | 1997-05-13 | 2000-06-13 | Eurocopter | Anticrash armor-plated modular seat |
| CN2406216Y (en) * | 1999-09-03 | 2000-11-15 | 北京航空航天大学 | Advanced composite-material anti-bullet board |
| CN2573990Y (en) * | 2002-09-25 | 2003-09-17 | 北京航空航天大学 | Bulletproof bearing composite armour plate |
| CN2577229Y (en) * | 2002-09-26 | 2003-10-01 | 北京航空航天大学 | Composite-material efficient high-strength force-bearing bulletproof board |
| US20040066082A1 (en) * | 2002-10-02 | 2004-04-08 | Mears Jeffrey A. | Armor system with monolithic ceramic shell |
| CN105659796B (en) * | 2005-09-02 | 2010-01-13 | 北京玻钢院复合材料有限公司 | Lightweight armor battlebus gun turret and preparation method thereof |
| CN202770328U (en) * | 2012-01-11 | 2013-03-06 | 陈照峰 | A composite-structure bulletproof material board |
| CN104154819A (en) * | 2013-05-14 | 2014-11-19 | 北京同益中特种纤维技术开发有限公司 | Polyethylene composite bulletproof helmet |
| CN206095047U (en) * | 2016-09-23 | 2017-04-12 | 北京安达维尔航空设备有限公司 | A bulletproof armour for helicopter seat |
-
2016
- 2016-09-23 CN CN201610849664.4A patent/CN106225576A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3581620A (en) * | 1967-08-29 | 1971-06-01 | Norton Co | Armored seat for aircraft and the like |
| EP0293786A2 (en) * | 1987-06-04 | 1988-12-07 | Norton Company | Composite armored seat |
| US5164536A (en) * | 1989-11-24 | 1992-11-17 | Societe Europeenne De Propulsion | Composite armored seat, and method of manufacture |
| US6073884A (en) * | 1997-05-13 | 2000-06-13 | Eurocopter | Anticrash armor-plated modular seat |
| CN2406216Y (en) * | 1999-09-03 | 2000-11-15 | 北京航空航天大学 | Advanced composite-material anti-bullet board |
| CN2573990Y (en) * | 2002-09-25 | 2003-09-17 | 北京航空航天大学 | Bulletproof bearing composite armour plate |
| CN2577229Y (en) * | 2002-09-26 | 2003-10-01 | 北京航空航天大学 | Composite-material efficient high-strength force-bearing bulletproof board |
| US20040066082A1 (en) * | 2002-10-02 | 2004-04-08 | Mears Jeffrey A. | Armor system with monolithic ceramic shell |
| CN105659796B (en) * | 2005-09-02 | 2010-01-13 | 北京玻钢院复合材料有限公司 | Lightweight armor battlebus gun turret and preparation method thereof |
| CN202770328U (en) * | 2012-01-11 | 2013-03-06 | 陈照峰 | A composite-structure bulletproof material board |
| CN104154819A (en) * | 2013-05-14 | 2014-11-19 | 北京同益中特种纤维技术开发有限公司 | Polyethylene composite bulletproof helmet |
| CN206095047U (en) * | 2016-09-23 | 2017-04-12 | 北京安达维尔航空设备有限公司 | A bulletproof armour for helicopter seat |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114234721A (en) * | 2021-12-29 | 2022-03-25 | 咸宁海威复合材料制品有限公司 | Fireproof, heat-insulating and flame-retardant ultrahigh molecular weight polyethylene bulletproof plate and manufacturing method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Bunsell et al. | Hybrid carbon and glass fibre composites | |
| ES2208605T3 (en) | COMPOSITE MATERIAL FOR SHIELDS. | |
| Matchen | Applications of ceramics in armor products | |
| US3380406A (en) | Composite design for transparent armour | |
| US4232069A (en) | Impact resistant composite structure | |
| RU2529466C2 (en) | Composite materials and their application | |
| US9162426B2 (en) | Transparent armor systems, methods for making and methods for using | |
| Rhodes | Impact fracture of composite sandwich structures | |
| CN112848554A (en) | High-toughness fiber-reinforced foamed aluminum gradient anti-explosion composite structure | |
| CN105088536A (en) | Preparation method of anti-sinking material in body armor | |
| CN104329991A (en) | Light composite sandwich bullet-resisting structure containing rectangular pyramid dot matrix structure | |
| CN106225576A (en) | A kind of bulletproof armour for Helicopter Seat and manufacture method thereof | |
| DK178289B1 (en) | Light weight composite armor with structural strength | |
| US20160025460A1 (en) | Armor System with Multi-Hit Capacity and Method of Manufacture | |
| CN2573990Y (en) | Bulletproof bearing composite armour plate | |
| CN206095047U (en) | A bulletproof armour for helicopter seat | |
| Horsfall et al. | Structural ballistic armour for transport aircraft | |
| CN114812276B (en) | High-constraint bionic structural armor resistant to multiple bullets and preparation method thereof | |
| US20150159316A1 (en) | Self-healing material | |
| CN114750469A (en) | Anti-elastic composite material containing negative Poisson's ratio ceramic structure and preparation method | |
| CN104501658A (en) | Complete plate type bulletproof inserting plate | |
| US3440132A (en) | Ceramic plastic composite material for radomes | |
| CN114872390A (en) | Ceramic/fiber reinforced composite protective armor structure | |
| CN114434917A (en) | Penetration-resistant material and preparation method and application thereof | |
| CN208633265U (en) | A kind of composite material |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| 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: 20161214 |