CN115626289A - Aircraft tank electrostatic protection structure - Google Patents
Aircraft tank electrostatic protection structure Download PDFInfo
- Publication number
- CN115626289A CN115626289A CN202211377813.3A CN202211377813A CN115626289A CN 115626289 A CN115626289 A CN 115626289A CN 202211377813 A CN202211377813 A CN 202211377813A CN 115626289 A CN115626289 A CN 115626289A
- Authority
- CN
- China
- Prior art keywords
- net layer
- layer
- copper
- aluminum
- fuel tank
- 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
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 69
- 229910052802 copper Inorganic materials 0.000 claims abstract description 69
- 239000010949 copper Substances 0.000 claims abstract description 69
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 61
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 61
- 239000002828 fuel tank Substances 0.000 claims abstract description 31
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 22
- 239000004917 carbon fiber Substances 0.000 claims abstract description 22
- 239000002131 composite material Substances 0.000 claims abstract description 22
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 22
- 238000000034 method Methods 0.000 claims abstract description 11
- 239000000945 filler Substances 0.000 claims abstract description 4
- 239000002313 adhesive film Substances 0.000 claims description 16
- 238000006056 electrooxidation reaction Methods 0.000 claims description 5
- 208000025274 Lightning injury Diseases 0.000 claims description 4
- 230000002265 prevention Effects 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 9
- 239000000446 fuel Substances 0.000 abstract description 8
- 238000009795 derivation Methods 0.000 abstract description 3
- 239000010410 layer Substances 0.000 description 103
- 238000013461 design Methods 0.000 description 15
- 230000003068 static effect Effects 0.000 description 14
- 230000005611 electricity Effects 0.000 description 9
- 238000005516 engineering process Methods 0.000 description 4
- 239000003292 glue Substances 0.000 description 4
- 238000011161 development Methods 0.000 description 2
- 229920000642 polymer Polymers 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011247 coating layer Substances 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
Images
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
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses an aircraft fuel tank electrostatic protection structure, which comprises a rubber film layer, an aluminum net layer, a copper net layer and a carbon fiber one-way belt, wherein the rubber film layer, the aluminum net layer, the copper net layer and the carbon fiber one-way belt are sequentially paved and adhered from bottom to top according to a general composite material paving and adhering process, the aluminum net layer comprises a first aluminum net layer and a second aluminum net layer, the first aluminum net layer is installed on a fuel filler cover of a fuel tank, the copper net layer comprises a first copper net layer and a second copper net layer, the first copper net layer and the second copper net layer are respectively connected with the first aluminum net layer and the second aluminum net layer, the first copper net layer and the second copper net layer are connected through the carbon fiber one-way belt, the second aluminum net layer is connected with a zero potential point part of the aircraft, and an electric path for electrostatic derivation is formed between the fuel tank and the zero potential point part of the aircraft. The invention has the advantages of improving the electrostatic protection efficiency and the production efficiency of the oil tank, reducing external lap joint components, reducing the manufacturing cost and the like.
Description
Technical Field
The invention belongs to the technical field of airplanes, and particularly relates to an electrostatic protection structure for an airplane fuel tank.
Background
For composite material structures on airplanes, particularly airplane fuel tanks, due to the characteristics of high resistance and low thermal conductivity, and the use temperature of a base material of a polymer-based composite material is low (generally not more than 80 ℃), the polymer-based composite material structure is extremely sensitive to high voltage, large current, large coulomb (continuous large current), sparks and the like caused by lightning strike, and the structure is easily damaged by the lightning strike to cause disastrous results. In addition, in the service process of the airplane, a large amount of static electricity is easily generated inside the composite material integral fuel tank, particularly, during the maneuvering flight, the fuel and the inner wall of the composite material integral fuel tank or other internal fuel system components generate violent friction, impact, splash and the like, and in the oiling and other use processes of the airplane, the fuel in the wing fuel tank is always in a vibration state and the fuel per se can be stirred. Because the composite material is an electrical poor conductor, the static leakage speed is low, and if the static protection design of the composite material structure is not proper, a large amount of static accumulation is easily caused. When the static electricity is accumulated to a certain degree and sensitive conditions (such as the tips of components of a fuel system) for triggering the static electricity discharge exist in the fuel tank, the static electricity discharge triggers discharge sparks to ignite mixed gas of fuel steam and air, and further disastrous accidents such as fuel tank explosion or fire are caused.
For safety and risk considerations, the airworthiness regulations for normal, utility, special and commuting aircraft (CCAR 23R 3) items 23.867 and 23.954 specify the lightning protection design requirements for aircraft airframe structures and fuel systems, broadly divided into lightning direct effect protection design and electrostatic protection design requirements. For the fuel tank with the composite material integral structure, the fuel tank is generally considered to be arranged in an area with low probability of lightning strike adhesion, namely a lightning strike 3 area during the overall layout stage of the structure. Although the probability of a lightning strike directly attaching to a component arranged in the lightning strike 3 region is low, the component in the lightning strike 3 region still needs to have the capability of conducting a large current. The electrostatic protection design of the fuel tank with the integral composite structure generally considers two aspects, namely, measures are taken to reduce the generation of static electricity and measures are taken to accelerate the dissipation of the static electricity. The traditional oil tank antistatic protection method mainly comprises the steps of applying flame to spray an aluminum layer on the inner wall of the oil tank, spraying an antistatic coating layer and hanging a metal net in the oil tank. The traditional method has the problems of poor electrostatic protection efficiency, high implementation cost and increased airplane weight due to the need of externally overlapping more parts, high process difficulty, complex operation, long production period and the like.
Disclosure of Invention
The invention aims to solve the problems in the background art, and provides an aircraft fuel tank electrostatic protection structure which can improve the electrostatic protection efficiency and the production efficiency of a fuel tank, reduce external lap joint components and reduce the manufacturing cost.
In order to achieve the purpose, the invention provides an aircraft fuel tank electrostatic protection structure, which comprises an adhesive film layer, an aluminum net layer, a copper net layer and a carbon fiber unidirectional tape, wherein the adhesive film layer, the aluminum net layer, the copper net layer and the carbon fiber unidirectional tape are sequentially paved from bottom to top according to a general composite paving technology, the aluminum net layer comprises a first aluminum net layer and a second aluminum net layer, the first aluminum net layer is installed on a fuel tank oil filling port cover, the copper net layer comprises a first copper net layer and a second copper net layer, the first copper net layer and the second copper net layer are respectively connected with the first aluminum net layer and the second aluminum net layer, the first copper net layer and the second copper net layer are connected through the carbon fiber unidirectional tape, and the second aluminum net layer is connected with a zero potential point part of an aircraft, so that an electric path for electrostatic derivation is formed between the fuel tank and the zero potential point part of the aircraft.
Preferably, the edges of the left side and the right side of the adhesive film layer are respectively 18.5-19.5 mm wider than the edges of the left side and the right side of the copper mesh layer.
Preferably, the edges of the left side and the right side of the adhesive film layer are respectively 19.05mm wider than the edges of the left side and the right side of the copper mesh layer.
Preferably, the first copper mesh layer and the second copper mesh layer are both square.
Preferably, the first copper mesh layer and the second copper mesh layer each have a size of 50.80mm × 50.80mm.
Preferably, the aluminium mesh layer is laid according to the requirements of a main lightning current conduction path in a lightning stroke zone.
Preferably, the carbon fiber unidirectional tape is laid according to the requirements of an electrostatic conduction path.
Preferably, the copper mesh layer is laid according to lightning current lap joint requirements and electrochemical corrosion prevention requirements.
Preferably, the adhesive film layer, the aluminum net layer, the copper net layer and the carbon fiber unidirectional tape are sequentially paved from bottom to top according to the paving process of the universal composite material and then cured according to the curing requirement of the universal composite material.
Preferably, the curing temperature is kept uniform when the adhesive film layer, the aluminum mesh layer, the copper mesh layer and the carbon fiber unidirectional tape are cured.
The invention has the beneficial effects that:
1. by adopting the integrated forming technology, the integral electrostatic protection efficiency, the production efficiency and the surface processing quality of the oil tank are improved, the antistatic inspection efficiency of the oil tank is effectively improved, the development progress of a general airplane is accelerated, and the development cost is reduced.
2. The oil tank filler cap is utilized and protected, and the static protection/conduction laying layer is only arranged on the local part of the oil tank, so that a large number of external lap joint components are avoided, the purchase cost is effectively reduced, and the weight of the airplane is reduced.
3. Special manufacturing equipment is not needed, only conventional blanking equipment or simple cutting tools are needed, and manufacturing cost is greatly saved.
4. All the electrostatic lapping technologies are based on the paving layer design, so that when the design requirement changes, only the paving layer size needs to be updated, the design, the paving mold, the process parameters and the like do not need to be changed greatly, and the design change cost is greatly reduced.
The features and advantages of the present invention will be described in detail by embodiments in conjunction with the accompanying drawings.
Drawings
Fig. 1 is a schematic view of an installation structure of an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of an embodiment of the present invention.
Fig. 3 is a schematic view of a state of the tile according to an embodiment of the present invention.
In the figure: 1-an adhesive film layer, 2-an aluminum mesh layer, 3-a copper mesh layer, 4-a carbon fiber unidirectional tape, 5-a paving mould, 21-a second aluminum mesh layer, 22-a first aluminum mesh layer, 31-a second copper mesh layer and 32-a first copper mesh layer.
Detailed Description
Referring to fig. 1, 2 and 3, the present embodiment provides an aircraft fuel tank static electricity protection structure, including a glue film layer 1, an aluminum mesh layer 2, a copper mesh layer 3 and a carbon fiber unidirectional tape 4 which are sequentially laid according to a general composite material laying process from bottom to top, the aluminum mesh layer 2 includes a first aluminum mesh layer 22 and a second aluminum mesh layer 21, the first aluminum mesh layer 22 is mounted on a fuel tank filler cap, the copper mesh layer 3 includes a first copper mesh layer 32 and a second copper mesh layer 31, the first copper mesh layer 32 and the second copper mesh layer 31 are respectively connected with the first aluminum mesh layer 22 and the second aluminum mesh layer 21, the first copper mesh layer 32 and the second copper mesh layer 31 are connected by the carbon fiber unidirectional tape 4, the second aluminum mesh layer 21 is connected with a zero potential point part of an aircraft, so that an electric path for static electricity derivation is formed between the fuel tank and the zero potential point part of the aircraft, when the aluminum mesh layer is laid according to the general composite material laying process, the glue film layer 1 is determined according to design, it is ensured that a molded surface of the solidified aluminum mesh layer 2, the aluminum mesh layer 2 is smooth, the aluminum mesh layer 2 is formed, the first aluminum mesh layer 3 is extended to the first aluminum mesh layer 22, the aluminum mesh layer 22, and the aluminum mesh layer 22 are extended to the first aluminum mesh layer 31, and the second aluminum mesh layer 31, and the aluminum mesh layer 31 are extended to realize static electricity is extended along with the first aluminum mesh layer.
The edges of the left side and the right side of the adhesive film layer 1 are respectively 18.5-19.5 mm wider than the edges of the left side and the right side of the copper mesh layer 3, preferably, the edges of the left side and the right side of the adhesive film layer 1 are respectively 18.5-19.5 mm wider than the edges of the left side and the right side of the copper mesh layer 3, and the copper mesh layer is prevented from being exposed outside.
The first copper mesh layer 32 and the second copper mesh layer 31 are both square, and the first copper mesh layer 32 and the second copper mesh layer 31 are both 50.80mm × 50.80mm in size.
The aluminum net layer 2 is laid according to the requirement of a main lightning current conduction path in a lightning stroke area.
The carbon fiber unidirectional tape 4 is laid according to the electrostatic conduction path requirement.
The copper net layer 3 is laid according to lightning current lapping requirements and electrochemical corrosion prevention requirements, and electrochemical corrosion of the copper net layer 3 is avoided.
The adhesive film layer 1, the aluminum net layer 2, the copper net layer 3 and the carbon fiber unidirectional tape 4 are sequentially paved and pasted from bottom to top according to the paving and pasting technology of the general composite material and then are solidified according to the solidification requirement of the general composite material.
The curing temperature of the adhesive film layer 1, the aluminum net layer 2, the copper net layer 3 and the carbon fiber unidirectional tape 4 is kept consistent when curing.
The manufacturing process of the electrostatic protection structure of the aircraft fuel tank comprises the following steps:
step one, finishing the layout design of 2 layers of an aluminum net according to the requirement of a main lightning current conduction path in a lightning stroke area;
step two, finishing the laying layout design of the carbon fiber unidirectional tape 4 according to the requirement of the static conduction path;
step three, finishing the layout design of the copper mesh layer 3 according to the lightning current lapping requirement and the electrochemical corrosion prevention requirement;
fourthly, finishing the layout design of the glue film layer 1 according to the layer design of the copper mesh layer 3;
step five, carrying out surface treatment on the paving mould 5 according to the paving requirement of the universal composite material;
paving and pasting a glue film layer 1, an aluminum net layer 2, a copper net layer 3 and a carbon fiber unidirectional tape 4 in sequence according to the paving and pasting requirements of the universal composite material;
and step seven, finishing integral curing molding of the parts according to the curing requirement of the universal composite material.
The above embodiments are illustrative of the present invention, and are not intended to limit the present invention, and any simple modifications of the present invention are within the scope of the present invention.
Claims (10)
1. The utility model provides an aircraft tank electrostatic protection structure which characterized in that: the aluminum net layer comprises a first aluminum net layer and a second aluminum net layer, the first aluminum net layer is installed on an oil tank oil filler cover, the copper net layer comprises a first copper net layer and a second copper net layer, the first copper net layer and the second copper net layer are respectively connected with the first aluminum net layer and the second aluminum net layer, the first copper net layer and the second copper net layer are connected through the carbon fiber unidirectional tape, the second aluminum net layer is connected with a zero potential point part of an airplane, and an electric path for electrostatic conduction is formed between the oil tank and the zero potential point part of the airplane.
2. An aircraft fuel tank electrostatic protection arrangement as claimed in claim 1, wherein: the edges of the left side and the right side of the adhesive film layer are respectively 18.5-19.5 mm wider than the edges of the left side and the right side of the copper mesh layer.
3. An aircraft fuel tank electrostatic protection arrangement as claimed in claim 2, wherein: the edges of the left side and the right side of the adhesive film layer are respectively 19.05mm wider than the edges of the left side and the right side of the copper mesh layer.
4. An aircraft fuel tank electrostatic protection arrangement as claimed in claim 1, wherein: the first copper mesh layer and the second copper mesh layer are both square.
5. An aircraft fuel tank electrostatic protection arrangement as claimed in claim 1 or 4, wherein: the sizes of the first copper mesh layer and the second copper mesh layer are 50.80mm multiplied by 50.80mm.
6. An aircraft fuel tank electrostatic protection arrangement as claimed in claim 1, wherein: and the aluminum net layer is laid according to the requirement of a main lightning current conduction path in a lightning stroke area.
7. An aircraft fuel tank electrostatic protection arrangement as claimed in claim 1, wherein: and the carbon fiber unidirectional belt is laid according to the requirements of the electrostatic conduction path.
8. An aircraft fuel tank electrostatic protection arrangement as claimed in claim 1, wherein: and the copper net layer is laid according to the lightning current lap joint requirement and the electrochemical corrosion prevention requirement.
9. An aircraft fuel tank electrostatic protection arrangement as claimed in claim 1, wherein: the adhesive film layer, the aluminum net layer, the copper net layer and the carbon fiber unidirectional tape are sequentially paved and adhered from bottom to top according to the paving and adhering process of the universal composite material and then are cured according to the curing requirement of the universal composite material.
10. An aircraft fuel tank electrostatic protection arrangement as claimed in claim 9, wherein: and the curing temperature of the adhesive film layer, the aluminum net layer, the copper net layer and the carbon fiber unidirectional tape is kept consistent when the adhesive film layer, the aluminum net layer, the copper net layer and the carbon fiber unidirectional tape are cured.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211377813.3A CN115626289A (en) | 2022-11-04 | 2022-11-04 | Aircraft tank electrostatic protection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211377813.3A CN115626289A (en) | 2022-11-04 | 2022-11-04 | Aircraft tank electrostatic protection structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115626289A true CN115626289A (en) | 2023-01-20 |
Family
ID=84908335
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211377813.3A Pending CN115626289A (en) | 2022-11-04 | 2022-11-04 | Aircraft tank electrostatic protection structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115626289A (en) |
-
2022
- 2022-11-04 CN CN202211377813.3A patent/CN115626289A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7969706B2 (en) | Lightning protection system for aircraft composite structure | |
| JP6338843B2 (en) | Method and apparatus for lightning protection of composite structures | |
| US7898785B2 (en) | Lightning protection system for an aircraft composite structure | |
| EP1068130B1 (en) | Adhesively bonded joints in carbon fibre composite structures | |
| CN109291575B (en) | Surface protection type conductive composite material and preparation method thereof | |
| JP6849375B2 (en) | Conductive corner filler system and method | |
| CN110744833B (en) | Carbon nano tube film/composite material forming method and lightning protection structure manufactured by same | |
| US8986816B2 (en) | Decorative decal system for an aircraft | |
| JP2009531863A (en) | Lightning protection system for composite structures | |
| CN112009694B (en) | Preparation method of electric heating anti-icing coating for three-dimensional complex curved surface | |
| US20170129616A1 (en) | Method for installing a de-icing system on an aircraft, involving the application of layers of material in the solid and/or fluid state | |
| EP2781452B1 (en) | Electromagnetic energy surface protection | |
| US20160368613A1 (en) | Aircraft structure with solar energy capture capacity | |
| EP3000736A1 (en) | Method for mitigating edge glow and resulting composite structure | |
| CN115626289A (en) | Aircraft tank electrostatic protection structure | |
| CN202783773U (en) | Lightning stroke-proof composite material wing box for airplane | |
| JP2012006528A (en) | Laminar composite for machine body structures of aircraft and machine body structure of aircraft | |
| CN102843790A (en) | Electrical heater and fabricating method thereof, and vehicle | |
| CN211376212U (en) | Lightning protection structure | |
| US10875624B2 (en) | Carbon flocked tape | |
| EP2800694B1 (en) | Electric charge dissipation system for aircraft | |
| CN104218333B (en) | A kind of carbon fibre composite aircraft equipotential structure | |
| CN113212812B (en) | Self-dropping type lightning protection diversion strip of solid rocket | |
| US11459468B2 (en) | Conductive doped-epoxy hybrid surfacing film | |
| CN109326443A (en) | A kind of new-energy automobile quick charging system thin film capacitor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |