CN113955124B - Embedded air inlet lip anti-icing heating assembly and manufacturing method - Google Patents
Embedded air inlet lip anti-icing heating assembly and manufacturing method Download PDFInfo
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- CN113955124B CN113955124B CN202111311005.2A CN202111311005A CN113955124B CN 113955124 B CN113955124 B CN 113955124B CN 202111311005 A CN202111311005 A CN 202111311005A CN 113955124 B CN113955124 B CN 113955124B
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- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 claims abstract description 11
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- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 6
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- QUTYHQJYVDNJJA-UHFFFAOYSA-K trisilver;2-hydroxypropane-1,2,3-tricarboxylate Chemical compound [Ag+].[Ag+].[Ag+].[O-]C(=O)CC(O)(CC([O-])=O)C([O-])=O QUTYHQJYVDNJJA-UHFFFAOYSA-K 0.000 claims description 4
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- NEIHULKJZQTQKJ-UHFFFAOYSA-N [Cu].[Ag] Chemical compound [Cu].[Ag] NEIHULKJZQTQKJ-UHFFFAOYSA-N 0.000 claims description 2
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- 229910000679 solder Inorganic materials 0.000 claims 1
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 abstract description 12
- 229910052697 platinum Inorganic materials 0.000 abstract description 6
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
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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
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Surface Heating Bodies (AREA)
Abstract
The invention relates to the technical field of electrothermal deicing of aircraft. In particular to an embedded type inlet lip anti-icing heating component and a manufacturing method thereof. Comprises a heating functional unit (1), a temperature measuring functional unit (2), an overcurrent protection unit (3) and an electric connection unit (4); the heating component adopts the integrated design of the heating element and the temperature measuring element, and has the composite functions of heating and temperature measurement. The heating element adopts a sinusoidal shape design, and has the advantages of good shape following with the composite material, easy deformation and fatigue resistance; the temperature measuring unit uses silver nanowires as temperature sensing materials to prepare the flexible temperature measuring unit, so that the temperature of the whole heating surface can be measured, and the problems that the traditional point platinum resistor or thermocouple is large in size, and the surface is easy to bulge and strength is reduced after the traditional point platinum resistor or thermocouple is embedded into the aircraft composite material can be avoided.
Description
Technical Field
The invention relates to the technical field of electrothermal deicing of aircraft. In particular to an embedded type inlet lip anti-icing heating component and a manufacturing method thereof.
Background
The appearance of the aircraft lip and the air inlet is a composite material and is a complex hyperbolic structural curved surface, the aircraft lip and the air inlet are slightly frozen, the flight performance of the aircraft is reduced, the flight safety of the aircraft is threatened, the aircraft anti-icing/deicing is mainly applied to typical parts such as wings, tail wings, lips and air inlets at present, and the electric heating anti-icing is mainly divided into two structural forms of surface mounted electric heating anti-icing and embedded electric heating anti-icing.
From the aspect of searching relevant data at home and abroad, the embedded heating technology has been applied to the parts with thicker thickness of common curved surfaces such as wings, tail wings and rotor wings of an airplane. However, no embedded heating anti-icing technical scheme for the thin-wall hyperbolic air inlet lip is found, and the problem is solved by adopting a mounting scheme at present.
The deicing technology of the lip and the air inlet channel of the aircraft composite material mainly faces the following technical problems:
(1) The conventional heating element has poor following performance
Because of the special thin-wall double-curvature structure of the lips, the heating elements commonly used at present are electric heating plates, resistance wires or metal nets, but the heating elements are independently paved with the composite material, have poor shape-following curability, are easy to laminate and have poor laminating property, so that the composite material has defects of poor glue, wrinkles and the like, and the structural strength of the composite material is greatly influenced.
(2) The limitation of the traditional point type temperature measuring element leads to great difficulty in temperature control
In order to prevent the composite material skin of the aircraft from being over-heated, a traditional point platinum resistor or thermocouple sensor is adopted in the heating component for temperature monitoring.
Because the traditional point platinum resistor or thermocouple has larger size, the traditional point platinum resistor or thermocouple is suitable for being arranged outside the composite material, the difficulty of embedding the composite material is higher, and the surface of the aircraft skin is easy to bulge and the strength is reduced.
The traditional point platinum resistor or thermocouple can only measure the temperature at a certain point, and because the composite material has poor heat conductivity, if the number of sensors is small, the problem of inaccurate measurement can occur, thus the temperature can be locally measured
The temperature points are controlled, measurement is inaccurate, the phenomenon of uneven heating can occur due to poor thermal conductivity of the composite material, hot spots are easy to occur, some parts cannot achieve the effect of preventing and removing ice, and unnecessary energy waste is caused by over-temperature of some parts.
(3) The traditional overcurrent protection element has the advantages of less on-off times and low reliability index
The traditional electric anti-icing heating overcurrent protection element adopts a traditional metal contact structure, and as the number of times of switching on and off of a contact is increased, a contact material is fatigued and aged, the risk of breakage exists, the reliability of the material is lower, and the requirement of a novel anti-icing overcurrent protection technology is not met.
(4) The traditional electric connecting element has small contact area and large lap resistance
A lap joint process is adopted between the traditional electric connecting element and the heating unit, and along with the current increase during the electrifying operation, the resistance wire is easy to burn out, and mainly the problem of easy lap joint of the resistance wire in the arrangement and cementing process is solved.
The traditional electric connecting element and the heating unit are subjected to large-area manual lap soldering, and as the bus bar is made of metal materials, the heat dissipation is faster, and the problems of high difficulty and low strength after the large-area manual soldering exist.
The heating net adopted by the traditional aircraft anti-icing is made of nickel complex gold material, the diameter of the resistance wire is large, the flexibility is poor, and the flexible heating functional unit suitable for the hyperbolic thin-wall configuration air inlet channel can not be manufactured.
In view of the above, how to design a heating assembly suitable for a thin-wall hyperbolic lip structure, and meet the conditions of heating, temperature measurement, overcurrent protection, electrical connection and the like at the same time, is an urgent technical problem to be solved in the field of ice prevention and removal.
Disclosure of Invention
The invention aims to provide an ice prevention and removal heating assembly with hyperbolic composite material lips and air inlets having ice prevention and removal functions.
The technical scheme of the invention is as follows: an embedded inlet lip anti-icing heating assembly comprises a heating functional unit (1), a temperature measuring functional unit (2), an overcurrent protection unit (3) and an electric connection unit (4); a heating functional unit (1), a temperature measuring functional unit (2), an overcurrent protection unit (3) and an electric connection unit (4) are sequentially paved on a lip substrate of an air inlet of the aircraft;
the heating functional unit (1) mainly converts electric energy into heat energy, the temperature measuring functional unit (2) mainly has a temperature measuring function, the overcurrent protection unit (3) mainly has a short-circuit protection function, and the electric connection unit (4) mainly has a signal transmission function.
The electric connection unit (4) consists of 3 bus bars (9) and 3 binding posts (10), wherein each binding post (9) is arranged on one side of each bus bar (10) and is connected by adopting laser brazing, the welding flux is BAg3Pb silver copper material, the power of the laser welding is 75W, and the welding current is 3.5A.
The manufacturing method of the embedded inlet lip anti-icing heating assembly comprises the following steps:
step 1: preparing a mould, coating a release agent, fixing an aircraft air inlet lip substrate on the mould, covering a heating functional unit (1) to a mark line position needing to be heated for anti-icing according to a partition design by adopting a 3D printing process, and printing on the aircraft air inlet lip substrate by adopting the 3D printing process; after printing, vacuumizing, wherein the vacuum degree is 0.16-0.25 MPa, and the duration is 20-30 minutes.
Step 2: the temperature measuring unit (2) is paved on the heating unit (1) by using J-189 adhesive; laying the marked lines according to the 45-degree layering; and (3) carrying out vacuumizing treatment after paving, wherein the vacuum degree is 0.25-0.45 MPa, and the duration is 25-35 minutes.
Step 3: the J-189 adhesive is used for paving the overcurrent protection unit (3) on the temperature measurement unit (2); and (3) carrying out vacuumizing treatment after paving, wherein the vacuum degree is 0.25-0.45 MPa, and the duration is 25-35 minutes.
Step 4: the wires of each functional layer sequentially pass through the through holes of the composite material layer and are welded with the bus bar (9) of the electric connection unit (4) after passing out, and then the bus bar (9) and the binding post (10) are welded and fixed; mounting the electrical connection unit (4) on the overcurrent protection unit (3) using a J-189 adhesive;
step 5: and (3) integrally hot-pressing and forming, namely pasting a vacuum bag after the 4 functional units are manufactured, vacuumizing, hot-pressing, carrying out negative pressure 0.35-0.85 MPa, and hot-pressing at 120 ℃ for 45-60 minutes.
The subareas of the heating unit (1) are custom designed according to different modes of power density and ice prevention and deicing. According to different anti-icing power requirements, the heating unit (1) is manufactured with different power densities, wherein the anti-icing mode power density is 3W/cm 2 Deicing mode power density of 2W/cm 2 The heating element is designed in a sinusoidal shape using a Sin (3 x) function.
The preparation method of the heating unit (1) comprises the following steps: the method comprises the steps of mixing 30% of carbon nano paper, 50% of graphite, 10% of paraffin and 10% of polyacrylate, preparing a conductive polymer (5), printing on polyethylene fibers by a 3D printing process, then dipping the polyethylene fibers in 9225-grade organosilicon rubber solution, and preparing the flexible heating unit by taking the cured rubber sleeve (6) as an insulating protective layer.
The preparation method of the temperature measurement functional unit (2). Firstly, weighing 5g of pure copper powder, adding the pure copper powder into 100mL of dilute hydrochloric acid with the concentration of 5.9%, and carrying out ultrasonic cleaning for 20min to remove surface oxidation substances. Then adding the copper powder after pickling into gelatin water-soluble with the mass fraction of 0.8 percentAnd uniformly dispersing the liquid by ultrasonic waves. Finally, 10ml of citric acid and 15g of Ag are weighed 2 SO 4 After adding into 250mL deionized water to prepare silver citrate suspension, slowly pouring the suspension into copper source solution, and stirring at room temperature until the solution color becomes dark green.
And spraying silver nanowires (7) with the width of 40nm and the length-width ratio of more than 200 on the polyester cloth (8) by adopting an explosion spraying method to obtain 95% silver particles as a temperature sensing material, and manufacturing a temperature sensing area according to a spiral pattern in a shape of a Chinese character 'Hui'.
The preparation method of the overcurrent protection unit (3) comprises the following steps: firstly, 25g of single-wall carbon nano tube with mass fraction of 25%, 15g of polydimethylsiloxane material and 35g of natural crystalline flake graphite are added with 100ml of acetone solution to be uniformly mixed, then 30ml of mixed solution of potassium permanganate oxidation and concentrated sulfuric acid (4:1) is added under the environment of 35 ℃ to perform oxidation intercalation, and the obtained organic mixture is mixed with deionized water to prepare 1.5mg/ml of colloid solution. And finally, ultrasonically peeling the colloid solution for 45min in an ultrasonic cleaner with the wave of 150W and 20kHz, stirring for 90min, filtering, drying, extracting and filtering to obtain a composite organic composite membrane, and preparing the flexible overcurrent protection unit. The invention has the advantages and beneficial effects that:
(1) The novel three-dimensional variable curvature ice prevention and removal heating unit is adopted, so that the flexibility is good, the power density can be specially designed according to the lip of an airplane, the compatibility with a composite material is good, the heating is uniform, and the stability is good.
(2) The novel heating functional unit adopts the special conductive polymer as the electrothermal material, and adopts the advanced 3D printing process, thereby realizing the special design of multi-region variable power density and having the advantages of good flexibility, bending resistance and good stability.
(3) According to the invention, the novel temperature measurement functional unit is used for preparing the flexible temperature measurement unit by using the silver nanowire as the temperature sensing material, so that the temperature of the whole heating surface can be measured, the measurement accuracy is high, and the resistance repeatability is good.
(4) The overcurrent protection unit uses the flexible carbon nano paper organic composite film, and when overcurrent or short circuit occurs in an anti-icing current state, the flexible overcurrent protection unit expands or contracts to perform power-off protection, and has the advantages of fatigue resistance and high service life.
(5) The invention changes the traditional lap welding mode into laser spot welding, changes the point contact into the surface contact, increases the welding strength, and overcomes the defect of poor low temperature resistance of soldering.
The heating component adopts the integrated design of the heating element and the temperature measuring element, and has the composite functions of heating and temperature measurement. The heating element is designed in a special sinusoidal shape, and has the advantages of good shape following with the composite material, easy deformation and fatigue resistance; the temperature element adopts an embedded process, so that the temperature of the whole temperature field can be measured, and the measurement accuracy is high.
Drawings
FIG. 1 is a schematic view of a heating assembly according to the present invention;
FIG. 2 is a schematic diagram of a heating unit according to the present invention;
FIG. 3 is a schematic diagram of a heating functional unit of the present invention;
FIG. 4 is a schematic diagram of a temperature measurement functional unit according to the present invention;
FIG. 5 is a schematic diagram of an overcurrent protection unit according to the present invention;
fig. 6 is a schematic structural diagram of an electrical connection unit according to the present invention.
Detailed Description
The novel technical scheme of the invention will be further described in detail with reference to the accompanying drawings and examples:
referring to the drawings 1-6, an embedded type inlet lip anti-icing heating assembly comprises a heating function unit (1), a temperature measurement function unit (2), an overcurrent protection unit (3) and an electric connection unit (4);
the manufacturing method of the embedded inlet lip anti-icing heating assembly comprises the following specific implementation steps:
step 1: heating unit (1)
The method comprises the steps of mixing 30% of carbon nano paper, 50% of graphite, 10% of paraffin and 10% of polyacrylate, preparing a conductive polymer (5), printing on polyethylene fibers by a 3D printing process, then dipping the polyethylene fibers in 9225-grade organosilicon rubber solution, and preparing the flexible heating unit by taking the cured rubber sleeve (6) as an insulating protective layer.
According to different anti-icing power requirements, the heating unit (1) is manufactured with different power densities, wherein the anti-icing mode power density is 3W/cm 2 Deicing mode power density of 2W/cm 2 The heating element is designed in a sinusoidal shape using a Sin (3 x) function.
Step 2: heating unit (1)
Preparing a mould, coating a release agent, fixing an aircraft air inlet lip substrate on the mould, covering a heating functional unit (1) to a mark line position needing to be heated for anti-icing according to a partition design by adopting a 3D printing process, and printing on the aircraft air inlet lip substrate by adopting the 3D printing process; after printing, vacuumizing, wherein the vacuum degree is 0.16-0.25 MPa, and the duration is 20-30 minutes.
Step 3: temperature measurement functional unit (2)
Firstly, weighing 5g of pure copper powder, adding the pure copper powder into 100mL of dilute hydrochloric acid with the concentration of 5.9%, and carrying out ultrasonic cleaning for 20min to remove surface oxidation substances. Then adding the copper powder after pickling into gelatin aqueous solution with mass fraction of 0.8%, and uniformly dispersing by ultrasonic. Finally, 10ml of citric acid and 15g of Ag are weighed 2 SO 4 After adding into 250mL deionized water to prepare silver citrate suspension, slowly pouring the suspension into copper source solution, and stirring at room temperature until the solution color becomes dark green.
And spraying silver nanowires (7) with the width of 40nm and the length-width ratio of more than 200 on the polyester cloth (8) by adopting an explosion spraying method to obtain 95% silver particles as a temperature sensing material, and manufacturing a temperature sensing area according to a spiral pattern in a shape of Chinese character 'Hui', wherein the pattern in the shape of Chinese character 'Hui' has the advantages of wide temperature measuring range and high stability.
Step 4: temperature measurement functional unit (2)
The temperature measuring unit (2) is paved on the heating unit (1) by using J-189 adhesive; laying the marked lines according to the 45-degree layering; after paving, vacuumizing, wherein the vacuum degree is 0.25MPa
0.45MPa for 25-35 min.
Step 5: manufacturing overcurrent protection unit (3)
Firstly, 25g of single-wall carbon nano tube with mass fraction of 25%, 15g of polydimethylsiloxane material and 35g of natural crystalline flake graphite are added with 100ml of acetone solution to be uniformly mixed, then 30ml of mixed solution of potassium permanganate oxidation and concentrated sulfuric acid (4:1) is added under the environment of 35 ℃ to perform oxidation intercalation, and the obtained organic mixture is mixed with deionized water to prepare 1.5mg/ml of colloid solution. And finally, ultrasonically peeling the colloid solution for 45min in an ultrasonic cleaner with the wave of 150W and 20kHz, stirring for 90min, filtering, drying, extracting and filtering to obtain a composite organic composite membrane, and preparing the flexible overcurrent protection unit.
Step 6: overcurrent protection unit (3)
The J-189 adhesive is used for paving the overcurrent protection unit (3) on the temperature measurement unit (2); and (3) carrying out vacuumizing treatment after paving, wherein the vacuum degree is 0.25-0.45 MPa, and the duration is 25-35 minutes.
Step 7: mounting electric connection unit (4)
The wires of each functional layer sequentially pass through the through holes of the composite material layer and are welded with the bus bar (9) of the electric connection unit (4) after passing out, and then the bus bar (9) and the binding post (10) are welded and fixed; mounting the electrical connection unit (4) on the overcurrent protection unit (3) using a J-189 adhesive;
step 8: integral hot press molding
After the 4 functional units are manufactured, pasting a vacuum bag, vacuumizing, performing hot pressing treatment, and performing hot pressing for 45-60 minutes at the temperature of 120 ℃ under the negative pressure of 0.35-0.85 MPa.
Claims (6)
1. The manufacturing method of the embedded type inlet lip anti-icing heating assembly is characterized in that the embedded type inlet lip anti-icing heating assembly comprises a heating function unit (1), a temperature measuring function unit (2), an overcurrent protection unit (3) and an electric connection unit (4); a heating functional unit (1), a temperature measuring functional unit (2), an overcurrent protection unit (3) and an electric connection unit (4) are sequentially paved on a lip substrate of an air inlet of the aircraft;
the electric connection unit (4) consists of 3 bus bars (9) and 3 binding posts (10), wherein each binding post (10) is arranged on one side of each bus bar (9) and is connected by adopting laser brazing; the solder of the laser brazing is BAg3Pb silver copper material, the power of the laser brazing is 75W, and the welding current is 3.5A;
the manufacturing method of the embedded inlet lip anti-icing heating assembly comprises the following steps:
step 1: preparing a mould, coating a release agent, fixing an aircraft air inlet lip substrate on the mould, covering a heating functional unit (1) to a mark line position needing heating and anti-icing according to partition design, and printing on the aircraft air inlet lip substrate by adopting a 3D printing process; after printing, vacuumizing, wherein the vacuum degree is 0.16-0.25 MPa, and the duration is 20-30 minutes;
step 2: the temperature measuring unit (2) is paved on the heating functional unit (1) by using an adhesive; laying the marked lines according to the 45-degree layering; vacuum pumping treatment is carried out after paving, wherein the vacuum degree is 0.25-0.45 MPa, and the duration is 25-35 minutes;
step 3: the overcurrent protection unit (3) is paved on the temperature measurement functional unit (2) by using an adhesive; vacuum pumping treatment is carried out after paving, wherein the vacuum degree is 0.25-0.45 MPa, and the duration is 25-35 minutes;
step 4: the wires of each functional layer sequentially pass through the through holes of the composite material layer and are welded with the bus bar (9) of the electric connection unit (4) after passing out, and then the bus bar (9) and the binding post (10) are welded and fixed; the electric connection unit (4) is arranged on the overcurrent protection unit (3) by using an adhesive;
step 5: and (3) integrally hot-pressing and forming, namely pasting a vacuum bag after the 4 functional units are manufactured, vacuumizing, hot-pressing, carrying out negative pressure 0.35-0.85 MPa, and hot-pressing at 120 ℃ for 45-60 minutes.
2. The embedded inlet lip anti-icing of claim 1The manufacturing method of the heating component is characterized in that the subareas of the heating functional units (1) are custom designed according to the power density and different modes of anti-icing and deicing, and the heating functional units (1) manufacture different power densities according to different anti-icing power requirements, wherein the power density of the anti-icing mode is 3W/cm 2 Deicing mode power density of 2W/cm 2 The heating element is designed in a sinusoidal shape using a Sin (3 x) function.
3. The method for manufacturing the embedded inlet lip anti-icing heating assembly according to claim 1, wherein the manufacturing method of the heating functional unit (1) comprises the following steps: the method comprises the steps of mixing 30% of carbon nano paper, 50% of graphite, 10% of paraffin and 10% of polyacrylate, preparing a conductive polymer (5), printing on polyethylene fibers by a 3D printing process, then dipping the polyethylene fibers in 9225-grade organosilicon rubber solution, and preparing the flexible heating unit by taking the cured rubber sleeve (6) as an insulating protective layer.
4. The method for manufacturing the embedded inlet lip anti-icing heating assembly according to claim 1, wherein the method for manufacturing the temperature measurement functional unit (2) is characterized in that firstly, 5g of pure copper powder is weighed and added into 100mL of dilute hydrochloric acid with the concentration of 5.9% for ultrasonic cleaning for 20min, and surface oxidation substances are removed; then adding the copper powder after pickling into gelatin aqueous solution with mass fraction of 0.8%, and uniformly dispersing by ultrasonic; finally, 10ml of citric acid and 15g of Ag are weighed 2 SO 4 Adding the copper source solution into 250mL of deionized water to prepare silver citrate suspension, slowly pouring the silver citrate suspension into the copper source solution, and stirring the copper source solution at room temperature until the color of the copper source solution becomes dark green; and spraying silver nanowires (7) with the width of 40nm and the length-width ratio of more than 200 on the polyester cloth (8) by adopting an explosion spraying method to obtain 95% silver particles as a temperature sensing material, and manufacturing a temperature sensing area according to a spiral pattern in a shape of a Chinese character 'Hui'.
5. The method for manufacturing the embedded inlet lip anti-icing heating assembly according to claim 1, wherein the method for manufacturing the overcurrent protection unit (3) comprises the following steps: firstly, uniformly mixing 25g of single-wall carbon nano tube with mass fraction of 25%, 15g of polydimethylsiloxane material and 35g of natural crystalline flake graphite, adding 100ml of acetone solution, then adding 30ml of mixed solution of potassium permanganate and concentrated sulfuric acid at 35 ℃ in a mixing ratio of 4:1, performing oxidation intercalation, and mixing the obtained organic mixture with deionized water to prepare 1.5mg/ml of colloid solution; and finally, ultrasonically peeling the colloid solution for 45min in an ultrasonic cleaner with the wave of 150W and 20kHz, stirring for 90min, filtering, drying, extracting and filtering to obtain a composite organic composite membrane, and preparing the flexible overcurrent protection unit.
6. The method for manufacturing the embedded air inlet lip anti-icing heating assembly according to claim 1, wherein the adhesives adopted in the steps 2, 3 and 4 are J-189 adhesives.
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| CN115599144A (en) * | 2022-12-12 | 2023-01-13 | 中国空气动力研究与发展中心低速空气动力研究所（Cn） | Dynamic temperature feedback electric heating anti-icing method and device for air inlet passage |
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| FR2887518A1 (en) * | 2005-06-22 | 2006-12-29 | Airbus France Sas | Jet aircraft engine nacelle has air intake de-icing and anti-icing system created by resistive heating elements embedded in electrical insulating material |
| CN203146115U (en) * | 2013-03-29 | 2013-08-21 | 成都飞机设计研究所 | Electric heating anti-icing system of engine lip |
| CN103826971A (en) * | 2011-09-28 | 2014-05-28 | 埃尔塞乐公司 | Lip unit for an electrically deiced turbojet engine nacelle |
| CN108843523A (en) * | 2018-06-21 | 2018-11-20 | 株洲时代新材料科技股份有限公司 | A kind of wind power turbine machine blade and its manufacturing method with deicing function |
| CN112537047A (en) * | 2020-11-17 | 2021-03-23 | 西安飞机工业（集团）有限责任公司 | Forming and assembling method for composite material reflector |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100199629A1 (en) * | 2005-06-22 | 2010-08-12 | Airbus France | Systeme d'anti givrage et de degivrage de nacelle de moteur d'aeronef a tapis resistif |
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|---|---|---|---|---|
| FR2887518A1 (en) * | 2005-06-22 | 2006-12-29 | Airbus France Sas | Jet aircraft engine nacelle has air intake de-icing and anti-icing system created by resistive heating elements embedded in electrical insulating material |
| CN103826971A (en) * | 2011-09-28 | 2014-05-28 | 埃尔塞乐公司 | Lip unit for an electrically deiced turbojet engine nacelle |
| CN203146115U (en) * | 2013-03-29 | 2013-08-21 | 成都飞机设计研究所 | Electric heating anti-icing system of engine lip |
| CN108843523A (en) * | 2018-06-21 | 2018-11-20 | 株洲时代新材料科技股份有限公司 | A kind of wind power turbine machine blade and its manufacturing method with deicing function |
| CN112537047A (en) * | 2020-11-17 | 2021-03-23 | 西安飞机工业（集团）有限责任公司 | Forming and assembling method for composite material reflector |
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