CN106218896B - Aircraft reinforces drip tray and preparation method thereof - Google Patents
Aircraft reinforces drip tray and preparation method thereof Download PDFInfo
- Publication number
- CN106218896B CN106218896B CN201610692011.XA CN201610692011A CN106218896B CN 106218896 B CN106218896 B CN 106218896B CN 201610692011 A CN201610692011 A CN 201610692011A CN 106218896 B CN106218896 B CN 106218896B
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- drip tray
- water receiving
- disk body
- aircraft
- reinforces
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- 238000002360 preparation method Methods 0.000 title claims abstract description 26
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 62
- 239000004744 fabric Substances 0.000 claims abstract description 36
- 239000011521 glass Substances 0.000 claims abstract description 36
- 239000003822 epoxy resin Substances 0.000 claims abstract description 21
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 21
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 20
- 229920006335 epoxy glue Polymers 0.000 claims abstract description 19
- 239000004033 plastic Substances 0.000 claims abstract description 15
- 229920003023 plastic Polymers 0.000 claims abstract description 15
- 238000000034 method Methods 0.000 claims abstract description 12
- 238000005498 polishing Methods 0.000 claims abstract description 10
- 239000003292 glue Substances 0.000 claims abstract description 9
- 230000002787 reinforcement Effects 0.000 claims abstract description 6
- 239000000853 adhesive Substances 0.000 claims abstract description 3
- 230000001070 adhesive effect Effects 0.000 claims abstract description 3
- 244000137852 Petrea volubilis Species 0.000 claims description 19
- 238000000465 moulding Methods 0.000 claims description 15
- 238000001035 drying Methods 0.000 claims description 11
- 230000008595 infiltration Effects 0.000 claims description 7
- 238000001764 infiltration Methods 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 7
- 230000003014 reinforcing effect Effects 0.000 claims description 7
- 238000005728 strengthening Methods 0.000 claims description 7
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 6
- 239000002245 particle Substances 0.000 claims description 6
- 238000007596 consolidation process Methods 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 4
- 238000005520 cutting process Methods 0.000 claims description 4
- 230000007547 defect Effects 0.000 claims description 4
- 238000013461 design Methods 0.000 claims description 4
- 238000012856 packing Methods 0.000 claims description 4
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 2
- 238000010422 painting Methods 0.000 claims 1
- 239000000203 mixture Substances 0.000 abstract description 3
- 238000005452 bending Methods 0.000 description 5
- 239000002994 raw material Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000000052 comparative effect Effects 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- ZKSPHENWXBWOPM-UHFFFAOYSA-N 2-methylprop-2-enoic acid oxochromium Chemical compound CC(=C)C(=O)O.O=[Cr] ZKSPHENWXBWOPM-UHFFFAOYSA-N 0.000 description 1
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 239000004593 Epoxy Substances 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 239000010426 asphalt Substances 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 235000013361 beverage Nutrition 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005538 encapsulation Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 210000004602 germ cell Anatomy 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
- 238000009736 wetting Methods 0.000 description 1
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D22/00—Producing hollow articles
- B29D22/003—Containers for packaging, storing or transporting, e.g. bottles, jars, cans, barrels, tanks
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K7/00—Use of ingredients characterised by shape
- C08K7/02—Fibres or whiskers
- C08K7/04—Fibres or whiskers inorganic
- C08K7/14—Glass
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L63/00—Compositions of epoxy resins; Compositions of derivatives of epoxy resins
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Medicinal Chemistry (AREA)
- Polymers & Plastics (AREA)
- Organic Chemistry (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a kind of aircrafts to reinforce drip tray and preparation method thereof, including water receiving disk body and fixing device, water receiving disk body includes one piece of horizontally disposed bottom plate and polylith sketch plate, and forward and backward, left three directions of bottom plate are connected with sketch plate inner end, and sketch plate outer end is upturned；Fixing device includes being set to a pair of of lifting lug of water receiving disk body left end and is set to a pair of projections of water receiving disk body right end, and water receiving disk body is fixedly connected by fixing device with electronic compartment.The method that aircraft reinforces drip tray is prepared, drip tray is prepared using plastic uptake technique is vacuumized, is 100 according to epoxy resin and curing agent weight proportion:14~100:18 prepare epoxy glue, and the region surface that needed reinforcement using epoxy glue to drip tray is pre-processed, and glass fabric is taped against glue bearing areas, mix polishing water receiving panel surface after adhesive curing.The aircraft prepared with the method, which reinforces drip tray, has the characteristics that intensity is high, wearability is strong, at low cost.
Description
Technical field
The present invention relates to a kind of drip trays and preparation method thereof, and in particular to a kind of aircraft reinforces drip tray and its preparation side
Method belongs to airplane component technical field.
Background technology
Coffee or beverage are often trickled down on the deck of aircraft passenger compartment, the deck lower part of aircraft passenger compartment be equipped with electronic compartment,
Landing gear compartment, cargo hold etc., electronic compartment are the places for placing the electronic equipments such as airborne computer, radar.Floor level is to separate visitor
Cabin and the interface of cargo hold, equipment compartment, since floor is using the splicing form of upper and lower fiber panel folder honeycomb core, and floor is by polylith
Plank riveting splicing composition, between have gap presence；Inserts on floor is installed, passes through inserts, screw and support construction
Connection, there is also gaps between screw and hole；Airplane floor in some regions, such as service area can not avoid will be by each germline
Road under the overall leadership passes through, and also has gap presence；Above-mentioned gap can undoubtedly do corresponding encapsulation process, but in the process of long-time service
In, by shake, the composite factors such as the aging of sealing element are influenced, still will appear small leakage, and this subtle leakage
Be difficult to be found in routine inspection, the cargo hold, general equipment compartment for main cabin lower part also almost without influence, but for
Very important for electronic compartment, the promising completion required various air environments of aerial mission of installation, main in electronic compartment
The presence or absence of want line telecommunication, navigation equipment, automatic flight control system, integrated display, airborne radar, airborne computer etc.；
The work of radar can be interfered if any infiltration phenomenon, the safety of aircraft certainly will be influenced.
Easily there is drainage in the pipeline of usual aircraft corridor or washing room, therefore corresponding position is special at the top of electronic compartment
It is not that drip tray is commonly installed above airborne radar, is destroyed to avoid radar electric device by liquid is penetrated into.Past is old
The drip tray lower end prominence of formula is easy to wear, fracture, and service life is shorter, and durability is poor, and the cost is relatively high.According to the country
Airline reacts, and drip tray maintenance capacity is big, need to spend a large amount of expenses every year to repair or replace drip tray.
Invention content
It is an object of the present invention to provide a kind of intensity is high, wearability is good, service life is long, aircraft at low cost reinforces water receiving
Disk.
The preparation method of drip tray is reinforced another object of the present invention is to provide a kind of aircraft.
The purpose of the present invention is what is be achieved through the following technical solutions：
A kind of aircraft reinforces drip tray, including water receiving disk body and fixing device, it is characterised in that：Water receiving disk body is integrated knot
Structure, including one piece of horizontally disposed bottom plate and polylith sketch plate, forward and backward, left three directions of bottom plate are connected with sketch plate inner end,
Sketch plate outer end is upturned；Fixing device includes being set to a pair of of lifting lug of water receiving disk body left end and is set to the water receiving disk body right side
The a pair of projections at end, water receiving disk body are fixedly connected by fixing device with electronic compartment.
Further, above-mentioned aircraft reinforces drip tray, go forward positioned at water receiving disk body, afterwards, outside the sketch plate in left three directions
End is equipped with upward dash side；If thering is water droplet to fall on electronics ceiling board, can be dropped on water receiving disk body, due to water receiving
Forward and backward on disk body, left three directions are equipped with dash side, and water can only be discharged by the outlet at the upper right end of water receiving disk body, convenient for receiving
Collection processing.Lifting lug is equipped with connecting hole A, can the left end of water receiving disk body be connected to electronics ceiling board by connecting hole A
On axis pin；Boss is equipped with connecting hole B, prevents putting rubber sheet gasket, cushion block on boss top, screw sequentially passes through connecting hole B, rubber
The right end of water receiving disk body is connected in the screw hole of electronics ceiling board by gasket and cushion block.
Further, above-mentioned aircraft reinforces drip tray, on water receiving disk body, the dash side on the left side and lifting lug and boss
Outer surface is equipped with strengthening layer, improves the intensity of fixing device, and then improve the durability and service life of drip tray.Described
Connecting hole B is slot hole, convenient to be connected with the top plate of electronic compartment.
A kind of aircraft reinforces the preparation method of drip tray, drip tray is prepared using plastic uptake technique is vacuumized, according to asphalt mixtures modified by epoxy resin
Fat is 100 with curing agent weight proportion:14~100:18 prepare epoxy glue, are needed reinforcement using epoxy glue to drip tray region table
Face is pre-processed, and glass fabric is taped against glue bearing areas, mixes polishing water receiving panel surface after adhesive curing.
The aircraft reinforces drip tray preparation method, includes the following steps：
（1）Blanking：According to design requirement by plate cutting into several equal portions rectangular slabs；
（2）It is dry：The horizontal or vertical interval of rectangular slab is put into drying in oven, drying temperature is 150 ± 2 DEG C, dry
Time is 8 ~ 12 hours；
（3）Plastics sucking moulding：Packing Machine is opened, mold is heated to 160 ± 5 DEG C, the rectangular slab of drying is put into mold frame
It is fixed on frame, material temperature is heated to 270 DEG C ± 20 DEG C, using vacuumizing plastics sucking moulding；
（4）Cooling demoulding：Cooled down using compressed air, the blank of plastics sucking moulding is removed from mold；
（5）Sand paper is polished：It is polished surface with sand paper, then cleaned with acetone or absolute ethyl alcohol；
（6）It is prepared by epoxy glue：Epoxy resin and curing agent are mixed and stirred for 15 ~ 20 minutes, epoxy resin and curing agent
Weight proportion is 100:14~100:18；
（7）Consolidation process：A. one layer of glue is applied to the region that needs reinforcement on draughty workbench, applied in the same direction
Brush, is allowed to uniform；B. the placed glass cloth on tablet brushes the epoxy glue prepared, epoxy glue is made thoroughly to be impregnated with glass fabric,
It hangs 30 ~ 40 minutes；C. the glass fabric after infiltration is taped against glue bearing areas, squeezes out the bubble in glass fabric, work as thickness
When spending inadequate, the glass fabric of one layer of infiltration can be also repaved according to above-mentioned laying step；
（8）Monolithic finish：It is lacked by the method for local heating to remove the pit of material surface, corrugation, tilting and ripple
It falls into, the water receiving disc thickness after finishing should be greater than 0.8 mm, and local heating temperature is 200 DEG C ± 20 DEG C；
（9）Reinforcing area is modified：When side and bubbly defect has occurred in glass fabric, by the region openings of damage
Epoxy glue is injected, makes curing；
（10）Engraving molding：Drip tray blank is carved by the requirement of drawing size, flash removed is removed with sand paper polishing.
The aircraft reinforces the preparation method of drip tray, and gap is 30 ~ 50 cm between dry every layer of plank.
The aircraft reinforces the preparation method of drip tray, and epoxy resin is EE 1067；Curing agent is Loctite productions
HD3561。
The aircraft reinforces the preparation method of drip tray, and the particle size range of sand paper is 80 ~ 150 mesh.
The aircraft reinforces the preparation method of drip tray, glass fabric A-1100, A-1100S, Volan, BMS9-
3rd, Type H, Type H-2, Type H-3, Classes 3, Classes 4 or Classes 7.
The aircraft reinforces the preparation method of drip tray, plank ULTEM1613.
The beneficial effects of the invention are as follows：
Due to the water receiving disk body of the present invention goes forward, afterwards, left three directions be equipped with dash side, water can only pass through water receiving disk body
The outlet discharge of upper right end, is handled convenient for collection.On water receiving disk body, the dash side on the left side and the outer surface of lifting lug and boss set
There is strengthening layer, improve the intensity of fixing device, and then improve the durability and service life of drip tray.
The present invention also fully utilizes the characteristic of epoxy resin, curing agent and glass fabric, and glass fabric is by tightly
Be affixed to the easily damaged position of water receiving tray fixing device, glass fabric by epoxy resin complete wetting, uniform close by ring
Oxygen resin wraps up, and forms the interface combined closely.Glass fabric has the effect of activeness and quietness, glass fabric reinforced epoxy
Resin is a kind of lightweight, high-strength composite material, has high tensile strength, bending strength and high impact flexibility, has simultaneously
Standby good wearability and fatigue performance set glass fabric reinforced epoxy in the outer surface of the fixing device of water receiving disk body
Resin strengthening layer improves the durability and service life of drip tray.The preparation method of drip tray of the present invention connects to solve aircraft
Water pond is easy to wear, breakage problem has opened up new field, and the aircraft prepared, which reinforces drip tray, has high intensity, high-wearing feature.
Description of the drawings
Structure diagram of the attached drawing for the present invention.
In Fig. 1：1- connecting holes A, 2- lifting lug, 3- dash sides, 4- connecting holes B, 5- boss, 6- strengthening layers, 7- bottom plates, 8- examinations
Sketch plate.
Specific embodiment
To make the objectives, technical solutions, and advantages of the present invention more comprehensible, the present invention is made with reference to embodiment
Further details of explanation.
Embodiment 1：
Referring to Fig. 1, a kind of aircraft reinforces drip tray, and including water receiving disk body and fixing device, water receiving disk body is structure as a whole,
Including one piece of horizontally disposed bottom plate 7 and polylith sketch plate 8, forward and backward, left three directions and the 8 inner end phase of sketch plate of bottom plate 7
Even, 8 outer end of sketch plate is upturned；Go forward positioned at water receiving disk body, afterwards, 8 outer end of sketch plate in left three directions be equipped with it is upward
Dash side 3；If thering is water droplet to fall on electronics ceiling board, can be dropped on water receiving disk body, due to water receiving disk body goes forward,
Afterwards, left three directions are equipped with dash side 3, and water can only be discharged by the outlet at the upper right end of water receiving disk body, are handled convenient for collection.
Fixing device includes being set to a pair of of lifting lug 2 of water receiving disk body left end and is set to a pair of convex of water receiving disk body right end
Platform 5, water receiving disk body are fixedly connected by fixing device with electronic compartment.Lifting lug 2 is equipped with connecting hole A1, can by connecting hole A1
The left end of water receiving disk body is connected on the axis pin of electronics ceiling board；Boss 5 is equipped with connecting hole B4, prevents on 5 top of boss
Rubber sheet gasket, cushion block are put, screw sequentially passes through connecting hole B4, rubber sheet gasket and cushion block, and the right end of water receiving disk body is connected to electricity
In the screw hole of sub- ceiling board.
On water receiving disk body, the dash side on the left side 3 and the outer surface of lifting lug 2 and boss 5 be equipped with strengthening layer 6, improve solid
Determine the intensity of device, and then improve the durability and service life of drip tray.The connecting hole B4 is slot hole, convenience and electronics
The top plate in cabin is connected.
Embodiment 2：
The aircraft of above-described embodiment reinforces the preparation method of drip tray, and the selection of raw material and proportioning are respectively：
The proportioning of reinforcing area epoxy resin and curing agent is 100:14, the dosage of glass fabric is homalographic water receiving
Disk is reinforced the area at place, uses sand paper polishing water receiving panel surface.The epoxy resin is EE 1067；Curing agent is HD
3561；The particle size range of the sand paper is 80 ~ 100 mesh.Glass fabric is A-1100.
The aircraft reinforces drip tray preparation method, includes the following steps：
（1）Blanking：According to design requirement by plate cutting into several equal portions rectangular slabs；
（2）It is dry：The horizontal or vertical interval of rectangular slab is put into drying in oven, drying temperature is 150 ± 2 DEG C, dry
Time is 8 ~ 12 hours；
（3）Plastics sucking moulding：Packing Machine is opened, mold is heated to 160 ± 5 DEG C, the rectangular slab of drying is put into mold frame
It is fixed on frame, material temperature is heated to 270 DEG C ± 50 DEG C, using vacuumizing plastics sucking moulding；
（4）Cooling demoulding：Cooled down using compressed air, the blank of plastics sucking moulding is removed from mold；
（5）Sand paper is polished：It is polished surface with sand paper, surface is in rough surface, increases roughness, then with acetone or absolute ethyl alcohol
Cleaning；
（6）It is prepared by epoxy glue：Epoxy resin and curing agent are mixed and stirred for 15 ~ 20 minutes, epoxy resin and curing agent
Weight proportion is 100:14~100:18, epoxy glue was used in 100 minutes；
（7）Consolidation process：A. one layer of glue is applied to the region that needs reinforcement on draughty workbench, applied in the same direction
Brush, is allowed to uniform；B. the placed glass cloth on tablet brushes the epoxy glue prepared, epoxy glue is made thoroughly to be impregnated with glass fabric,
It hangs 30 ~ 40 minutes；C. the glass fabric after infiltration is taped against glue bearing areas, squeezes out the bubble in glass fabric, work as thickness
When spending inadequate, the glass fabric of one layer of infiltration can be also repaved according to above-mentioned laying step；
（8）Monolithic finish：It is lacked by the method for local heating to remove the pit of material surface, corrugation, tilting and ripple
It falls into, the water receiving disc thickness after finishing should be greater than 0.8 mm, and local heating temperature is 200 DEG C ± 50 DEG C, can be filed and polished off with shaping
Small protrusion；
（9）Reinforcing area is modified：When side and bubbly defect has occurred in glass fabric, by the region openings of damage
Epoxy glue is injected, makes curing, applies 3 ~ 5 Mpa of pressure, enhances the intensity after its curing；
（10）Engraving molding：Drip tray blank is carved by the requirement of drawing size, flash removed is removed with sand paper polishing.
Embodiment 3：
The selection of its raw material and proportioning are respectively：
The proportioning of reinforcing area epoxy resin and curing agent is 100:16, the dosage of glass fabric is homalographic water receiving
Disk is reinforced the area at place, uses sand paper polishing water receiving panel surface.The epoxy resin is EE 1067；Curing agent is HD3561；
The particle size range of the sand paper is 80 ~ 100 mesh.Glass fabric is A-1100S.
Preparation method is the same as embodiment 2.
Embodiment 4：
The selection of its raw material and proportioning are respectively：
The proportioning of reinforcing area epoxy resin and curing agent is 100:18, the dosage of glass fabric is homalographic water receiving
Disk is reinforced the area at place, uses sand paper polishing water receiving panel surface.The epoxy resin is EE- 1067；Curing agent is
HD3561；The particle size range of the sand paper is 80 ~ 100 mesh.Glass fabric is BMS9-3.
Preparation method is the same as embodiment 2.
Embodiment 5：
The selection of its raw material and proportioning are respectively：
The proportioning of reinforcing area epoxy resin and curing agent is 100:15, the dosage of glass fabric is homalographic water receiving
Disk is reinforced the area at place, uses sand paper polishing water receiving panel surface.The epoxy resin is EE 1067；Curing agent is HD3561；
The particle size range of the sand paper is 80 ~ 100 mesh.Glass fabric is Type H.
Preparation method is the same as embodiment 2.
Comparative example：
The preparation method of existing drip tray：
（1）Blanking：According to design requirement by plate cutting into several equal portions rectangular slabs；
（2）It is dry：The horizontal or vertical interval of rectangular slab is put into oven dry；
（3）Plastics sucking moulding：Packing Machine is opened, mold is heated to 150 ± 5 DEG C, the rectangular slab of drying is put into mold frame
It is fixed on frame, material temperature is heated to 250 DEG C ± 50 DEG C, using vacuumizing plastics sucking moulding；
（4）Cooling demoulding：Room temperature cools down, and the blank of plastics sucking moulding is removed from mold；
The bending strength of drip tray that above-mentioned existing preparation method obtains is used as 71.72 MPa.
1 drip tray bending strength of table
| Embodiment | Bending strength（Execution standard ASTM D6109） |
| Embodiment 2 | 86.72 MPa |
| Embodiment 3 | 93.31 MPa |
| Embodiment 4 | 88.74 MPa |
| Embodiment 5 | 85.30 MPa |
| Comparative example | 71.72 MPa |
The difference of the drip tray that the preparation method of drip tray of the present invention is prepared and existing drip tray：
| Bending strength | Wearability | Tensile resistance | |
| Aircraft reinforces drip tray | It is high | It is high | By force |
| Existing drip tray | Generally | Generally | It is weak |
The consolidation effect for comparing different embodiments finds that the effect of embodiment 3 is best.
Above-mentioned specific embodiment is only the specific case of the present invention, is not that the invention has other forms of limitations,
Any person skilled in the art is changed or is modified as equivalent variations possibly also with the technology contents of the disclosure above
Equivalent implementations.But under the premise of every principle without departing from the technology of the present invention, technical spirit according to the present invention is to more than
Any simple modification, equivalent variations and the remodeling that embodiment is made should all fall into the scope of patent protection of the present invention.
Claims (8)
1. a kind of aircraft reinforces drip tray, including water receiving disk body and fixing device, it is characterised in that：Water receiving disk body is integrated knot
Structure, including one piece of horizontally disposed bottom plate and polylith sketch plate, forward and backward, left three directions of bottom plate are connected with sketch plate inner end,
Sketch plate outer end is upturned；Fixing device includes being set to a pair of of lifting lug of water receiving disk body left end and is set to the water receiving disk body right side
The a pair of projections at end, water receiving disk body are fixedly connected by fixing device with electronic compartment；
Drip tray is prepared by vacuumizing plastic uptake technique, is 100 according to epoxy resin and curing agent weight proportion:14~100:18
Epoxy glue is prepared, the region surface that needed reinforcement using epoxy glue to drip tray is pre-processed, and glass fabric is taped against painting
Glue region mixes polishing water receiving panel surface after adhesive curing, forms strengthening layer；Go forward positioned at water receiving disk body, afterwards, left three directions
Sketch plate outer end is equipped with upward dash side.
2. aircraft according to claim 1 reinforces drip tray, it is characterised in that：Lifting lug is equipped with connecting hole A, is set on boss
There is connecting hole B；The connecting hole B is slot hole.
3. aircraft according to claim 2 reinforces drip tray, it is characterised in that：On water receiving disk body, the dash side on the left side with
And the outer surface of lifting lug and boss is equipped with strengthening layer.
4. prepare the method that the aircraft in claims 1 to 3 described in any claim reinforces drip tray, it is characterised in that：Packet
Include following steps：
（1）Blanking：According to design requirement by plate cutting into several equal portions rectangular slabs；
（2）It is dry：The horizontal or vertical interval of rectangular slab is put into drying in oven, drying temperature is 150 ± 2 DEG C, drying time
It is 8~12 hours；
（3）Plastics sucking moulding：Packing Machine is opened, mold is heated to 160 ± 5 DEG C, the rectangular slab of drying is put on mold frame
It is fixed, material temperature is heated to 270 DEG C ± 20 DEG C, using vacuumizing plastics sucking moulding；
（4）Cooling demoulding：Cooled down using compressed air, the blank of plastics sucking moulding is removed from mold；
（5）Sand paper is polished：It is polished surface with sand paper, then cleaned with acetone or absolute ethyl alcohol；
（6）It is prepared by epoxy glue：Epoxy resin and curing agent are mixed and stirred for 15~20 minutes, epoxy resin and curing agent weight
Match is 100:14~100:18；
（7）Consolidation process：A. one layer of glue is applied to the region that needs reinforcement on draughty workbench, brushed in the same direction,
It is allowed to uniform；B. the placed glass cloth on tablet brushes the epoxy glue prepared, epoxy glue is made thoroughly to be impregnated with glass fabric, dries in the air
It puts 30~40 minutes；C. the glass fabric after infiltration is taped against glue bearing areas, squeezes out the bubble in glass fabric, work as thickness
When inadequate, the glass fabric of one layer of infiltration can be also repaved according to above-mentioned laying step；
（8）Monolithic finish：The pit of material surface, corrugation, tilting and uniformity defect are removed by the method for local heating, repaiied
Water receiving disc thickness after whole should be greater than 0.8 mm, and local heating temperature is 200 DEG C ± 20 DEG C；
（9）Reinforcing area is modified：When side and bubbly defect has occurred in glass fabric, the region openings of damage are injected
Epoxy glue makes curing；
（10）Engraving molding：Drip tray blank is carved by the requirement of drawing size, flash removed is removed with sand paper polishing.
5. aircraft as claimed in claim 4 reinforces the preparation method of drip tray, it is characterised in that：Gap between dry every layer of plank
For 30~50 cm.
6. aircraft reinforces the preparation method of drip tray as described in claim 4 or 5, it is characterised in that：Curing agent is given birth to for Loctite
The HD3561 of production.
7. aircraft as claimed in claim 4 reinforces the preparation method of drip tray, it is characterised in that：The particle size range of sand paper for 80~
150 mesh.
8. aircraft reinforces the preparation method of drip tray as described in claim 4 or 5, it is characterised in that:Plank is
ULTEM1613。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610692011.XA CN106218896B (en) | 2016-08-22 | 2016-08-22 | Aircraft reinforces drip tray and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610692011.XA CN106218896B (en) | 2016-08-22 | 2016-08-22 | Aircraft reinforces drip tray and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106218896A CN106218896A (en) | 2016-12-14 |
| CN106218896B true CN106218896B (en) | 2018-06-29 |
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| CN112095817A (en) * | 2017-01-11 | 2020-12-18 | 唐嘉诚 | Emergency treatment method for water seepage of waterproof layer of toilet |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101955666A (en) * | 2010-09-30 | 2011-01-26 | 长安大学 | Preparation method of glass fiber enhanced thermosetting resin matrix composite material |
| CN202470698U (en) * | 2012-01-10 | 2012-10-03 | 杭州华锦特种纸有限公司 | Condensed water inhibition tank |
| CN104271667A (en) * | 2012-04-27 | 2015-01-07 | 陶氏环球技术有限责任公司 | Curable epoxy resin compositions and composites made therefrom |
| CN205931270U (en) * | 2016-08-22 | 2017-02-08 | 山东翔宇航空技术服务有限责任公司 | Water collector is consolidated to aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| KR200161981Y1 (en) * | 1997-08-30 | 1999-12-01 | 윤종용 | Defrosting pan for a refrigerator |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101955666A (en) * | 2010-09-30 | 2011-01-26 | 长安大学 | Preparation method of glass fiber enhanced thermosetting resin matrix composite material |
| CN202470698U (en) * | 2012-01-10 | 2012-10-03 | 杭州华锦特种纸有限公司 | Condensed water inhibition tank |
| CN104271667A (en) * | 2012-04-27 | 2015-01-07 | 陶氏环球技术有限责任公司 | Curable epoxy resin compositions and composites made therefrom |
| CN205931270U (en) * | 2016-08-22 | 2017-02-08 | 山东翔宇航空技术服务有限责任公司 | Water collector is consolidated to aircraft |
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Denomination of invention: Aircraft reinforced water tray and its preparation method Effective date of registration: 20220929 Granted publication date: 20180629 Pledgee: Bank of Beijing Co.,Ltd. Jinan Branch Pledgor: SHANDONG XIANGYU AVIATION TECHNOLOGY SERVICE CO.,LTD. Registration number: Y2022370000126 |