CN113955124A - Embedded inlet lip anti-icing heating assembly and manufacturing method thereof - Google Patents
Embedded inlet lip anti-icing heating assembly and manufacturing method thereof Download PDFInfo
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- CN113955124A CN113955124A CN202111311005.2A CN202111311005A CN113955124A CN 113955124 A CN113955124 A CN 113955124A CN 202111311005 A CN202111311005 A CN 202111311005A CN 113955124 A CN113955124 A CN 113955124A
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Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
Abstract
The invention relates to the technical field of electrothermal deicing of airplanes. In particular to an embedded anti-icing heating component for a lip of an air inlet and a manufacturing method thereof. Comprises a heating function unit (1), a temperature measurement function unit (2), an overcurrent protection unit (3) and an electric connection unit (4); the heating component of the invention adopts the integrated design of the heating element and the temperature measuring element, and has the composite functions of heating and temperature measuring. The heating element is designed in a sine curve shape, and has the advantages of good shape following performance with the composite material, easy deformation and fatigue resistance; the temperature measuring unit uses the silver nanowires as a temperature sensing material to prepare the flexible temperature measuring unit, the temperature of the whole heating surface can be measured, and the problems that the traditional point type platinum resistor or thermocouple is large in size and is easy to bulge on the surface and reduce in strength after being embedded into the composite material of the airplane can be avoided.
Description
Technical Field
The invention relates to the technical field of electrothermal deicing of airplanes. In particular to an embedded anti-icing heating component for a lip of an air inlet and a manufacturing method thereof.
Background
The shapes of the airplane lip and the air inlet are composite materials and are relatively complex hyperbolic structural curved surfaces, the airplane lip and the air inlet are slightly iced to reduce the flight performance of the airplane and threaten the flight safety of the airplane, the existing airplane anti-icing/deicing is mainly applied to typical parts such as wings, empennages, lips and the air inlet, and the electric heating anti-icing is mainly divided into two structural forms of surface mounting type electric heating anti-icing and embedded type electric heating anti-icing.
From the aspect of retrieving relevant data at home and abroad, the embedded heating technology is already applied to the parts with thicker thickness, such as the wings, the empennage, the rotor wings and the like of the airplane. However, an embedded heating anti-icing technical scheme of a thin-wall hyperbolic inlet lip is not available, and the scheme is mainly solved by a mounting scheme at present.
At present, the deicing technology of the composite material lip and the air inlet of the airplane mainly faces the following technical problems:
(1) the conventional heating element has poor conformal performance
Due to the special thin-wall double-curvature structure of the lip, the heating elements which are commonly used at present are electric heating pieces, resistance wires or metal nets, but the heating elements are independently paved with the composite material, the shape-following curing property is poor, the lamination is easy to occur, the laminating property is poor, the defects of poor glue, wrinkles and the like of the composite material are caused, and the structural strength of the composite material is greatly influenced.
(2) The limitation of the traditional point-type temperature measuring element results in great difficulty in temperature control
In order to prevent the aircraft composite skin from being overheated, a traditional point platinum resistor or thermocouple sensor is adopted for temperature monitoring in the heating part.
Because the traditional point platinum resistor or thermocouple has larger size, the traditional point platinum resistor or thermocouple is suitable for being installed outside a composite material, the difficulty in 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 of a certain point, and the problem of inaccurate measurement can occur if the number of sensors is small due to poor heat conductivity of the composite material, so that the point platinum resistor or thermocouple can be used locally
The temperature point is controlled, the measurement is inaccurate, the phenomenon of uneven heating can occur due to poor heat conductivity of the composite material, hot spots are easy to occur, the ice preventing and removing effect can not be achieved at some parts, and unnecessary energy waste is caused by over-temperature of some parts.
(3) The traditional overcurrent protection element has less on-off times and low reliability index
Traditional electric anti-icing heating overcurrent protection component adopts traditional metal contact structure, and along with "contact" break-make number of times increases, contact material can fatigue aging, has the risk of breaking off, and the material reliability is lower, unsatisfied novel anti-icing overcurrent protection technical requirement.
(4) The traditional electric connection element has small contact area and large lap resistance
The traditional electric connection element and the heating unit adopt a lap joint process, the resistance wire is easy to burn off along with the increase of current during the electrifying work, and the lap joint problem of the resistance wire in the arrangement and gluing process is mainly solved.
The traditional electric connecting element and the heating unit are welded by large-area manual lap joint tin soldering, and the bus bar is made of metal materials, so that the heat dissipation is fast, and the problems of high difficulty and low strength after welding exist in large-area manual welding.
The heating net adopted by the traditional airplane anti-icing is made of nickel complex alloy materials, the diameter of a resistance wire is large, the flexibility is poor, and a flexible heating functional unit suitable for a hyperbolic thin-wall configuration air inlet channel cannot be manufactured.
In view of the above, how to design a heating assembly suitable for a thin-wall hyperbolic lip structure, which can satisfy conditions such as heating, temperature measurement, overcurrent protection, electrical connection, etc. at the same time, is a technical problem to be solved urgently in the field of deicing prevention.
Disclosure of Invention
The invention aims to provide an anti-icing and deicing heating assembly with a hyperbolic-structure composite material lip and an air inlet channel and an anti-icing and deicing function.
The technical scheme of the invention is as follows: an embedded 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); a heating function unit (1), a temperature measurement function unit (2), an overcurrent protection unit (3) and an electric connection unit (4) are sequentially paved on the base body of the inlet lip of the airplane;
the heating function unit (1) mainly converts electric energy into heat energy, the temperature measurement function unit (2) mainly has a temperature measurement 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), each binding post (9) is arranged on one side of each bus bar (10) and connected by laser soldering, the solder is BAg3Pb silver-copper material, the power of the laser soldering is 75W, and the soldering 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 inlet lip substrate on the mould, covering a heating function unit (1) to a mark reticle needing heating and anti-icing according to a partition design by adopting a 3D printing process, and printing the heating function unit on the aircraft inlet lip substrate by adopting the 3D printing process; after printing, vacuumizing treatment is carried out, wherein the vacuum degree is 0.16 MPa-0.25 MPa, and the vacuum degree lasts for 20 minutes-30 minutes.
Step 2: the temperature measuring unit (2) is paved on the heating unit (1) by using J-189 adhesive; paving the layers at 45 degrees to the marked scribed lines; after being paved, the vacuum is pumped, the vacuum degree is 0.25MPa to 0.45MPa, and the vacuum lasts for 25 minutes to 35 minutes.
And step 3: the overcurrent protection unit (3) is paved on the temperature measurement unit (2) by using J-189 adhesive; after being paved, the vacuum is pumped, the vacuum degree is 0.25MPa to 0.45MPa, and the vacuum lasts for 25 minutes to 35 minutes.
And 4, step 4: the conducting wires of all the functional layers sequentially penetrate through the composite material layer through holes and are welded with the bus bars (9) of the electric connection units (4) after penetrating out, and then the bus bars (9) are welded and fixed with the binding posts (10); the electric connection unit (4) is arranged on the overcurrent protection unit (3) by using J-189 adhesive;
and 5: and (3) performing integral hot-press molding, pasting a vacuum bag after the 4 functional units are manufactured, and performing vacuum pumping and hot-press treatment, wherein the negative pressure is 0.35-0.85 MPa, the temperature is 120 ℃, and the hot-press treatment is performed for 45-60 minutes.
The subareas of the heating unit (1) are different in modes of anti-icing and deicing according to power densityAnd (4) carrying out customized design. According to different anti-icing power requirements, the heating unit (1) is made into different power densities, wherein the anti-icing mode power density is 3W/cm2The power density of the deicing mode is 2W/cm2The heating element is designed according to a sine curve shape by adopting a Sin (3x) function.
The preparation method of the heating unit (1) comprises the following steps: the preparation method comprises the steps of mixing 30% of carbon nano paper, 50% of graphite, 10% of paraffin and 10% of polyacrylate to prepare a conductive polymer (5), printing the conductive polymer on polyethylene fibers by adopting a 3D printing process, then soaking the conductive polymer in 9225-grade organic silicon rubber solution, and preparing a flexible heating unit by taking a cured rubber sleeve (6) as an insulating protective layer.
A preparation method of the temperature measuring functional unit (2). Firstly, 5g of pure copper powder is weighed and added into 100mL of dilute hydrochloric acid with the concentration of 5.9 percent for ultrasonic cleaning for 20min, and surface oxidation substances are removed. And then adding the copper powder after acid washing into a gelatin water solution with the mass fraction of 0.8%, and uniformly performing ultrasonic dispersion. Finally, 10ml of citric acid and 15g of Ag are weighed2SO4Adding the solution into 250mL of deionized water to prepare a silver citrate suspension, slowly pouring the silver citrate suspension into the copper source solution, and stirring the solution at room temperature until the color of the 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 terylene cloth (8) as a temperature sensing material by adopting an explosion spraying method, and manufacturing a temperature sensing area according to a spiral pattern in a shape of Chinese character 'hui'.
The preparation method of the overcurrent protection unit (3) comprises the following steps: firstly, adding 25g of single-walled carbon nanotube with the mass fraction of 25%, 15g of polydimethylsiloxane material and 35g of natural crystalline flake graphite into 100ml of acetone solution, uniformly mixing, then adding 30ml of mixed solution (4:1) of potassium permanganate oxidation and concentrated sulfuric acid at the temperature of 35 ℃, carrying out oxidation intercalation, and mixing the obtained organic mixture with deionized water to prepare 1.5mg/ml of colloidal solution. And finally, ultrasonically stripping the colloidal solution in an ultrasonic cleaning machine with the power of 150W and the frequency of 20kHz for 45min, stirring for 90min, filtering, drying, extracting and filtering to form 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 deicing 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 a special conductive polymer as an electric heating material, adopts an advanced 3D printing process, realizes the special design of multi-region variable power density, and has the advantages of good flexibility, bending resistance and good stability.
(3) The flexible temperature measuring unit is prepared by adopting the novel temperature measuring functional unit and using the silver nanowires as the temperature sensing material, the temperature of the whole heating surface can be measured, the measurement accuracy is high, and the resistance repeatability is good.
(4) The over-current protection unit of the invention uses the flexible carbon nano paper organic composite film, when the over-current or short circuit occurs in the anti-icing current state, the flexible over-current protection unit expands or contracts to perform power-off protection, and has the advantages of fatigue resistance and high service life times.
(5) The invention changes the traditional lap welding mode into laser spot welding, changes the point contact of the welding joint into surface contact, increases the welding strength and overcomes the defect of poor low temperature resistance of tin soldering.
The heating component of the invention adopts the integrated design of the heating element and the temperature measuring element, and has the composite functions of heating and temperature measuring. The heating element is designed in a special sine curve shape, and has the advantages of good shape following performance with the composite material, easy deformation and fatigue resistance; the temperature element adopts embedded technology, can measure the temperature of whole temperature field, and it is high to measure the accuracy.
Drawings
FIG. 1 is a schematic view of a heating assembly according to the present invention;
FIG. 2 is a schematic structural view of a heating function unit according to the present invention;
FIG. 3 is a sectional view of a heating function unit according to the present invention;
FIG. 4 is a schematic structural diagram of a temperature measurement functional unit according to the present invention;
FIG. 5 is a schematic structural 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 is further detailed in the following with reference to the attached drawings and embodiments:
referring to the attached drawings 1-6, an embedded 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);
a manufacturing method of an embedded inlet lip anti-icing heating assembly specifically comprises the following steps:
step 1: production of heating Unit (1)
The preparation method comprises the steps of mixing 30% of carbon nano paper, 50% of graphite, 10% of paraffin and 10% of polyacrylate to prepare a conductive polymer (5), printing the conductive polymer on polyethylene fibers by adopting a 3D printing process, then soaking the conductive polymer in 9225-grade organic silicon rubber solution, and preparing a flexible heating unit by taking a cured rubber sleeve (6) as an insulating protective layer.
According to different anti-icing power requirements, the heating unit (1) is made into different power densities, wherein the anti-icing mode power density is 3W/cm2The power density of the deicing mode is 2W/cm2The heating element is designed according to a sine curve shape by adopting a Sin (3x) function.
Step 2: mounting heating unit (1)
Preparing a mould, coating a release agent, fixing an aircraft inlet lip substrate on the mould, covering a heating function unit (1) to a mark reticle needing heating and anti-icing according to a partition design by adopting a 3D printing process, and printing the heating function unit on the aircraft inlet lip substrate by adopting the 3D printing process; after printing, vacuumizing treatment is carried out, wherein the vacuum degree is 0.16 MPa-0.25 MPa, and the vacuum degree lasts for 20 minutes-30 minutes.
And step 3: production temperature measuring 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 percent for ultrasonic cleaning for 20min, and removing surface oxidation substances. And then adding the copper powder after acid washing into a gelatin water solution with the mass fraction of 0.8%, and uniformly performing ultrasonic dispersion. Finally, 10ml of citric acid and 15g of Ag are weighed2SO4Adding the solution into 250mL of deionized water to prepare a silver citrate suspension, slowly pouring the silver citrate suspension into the copper source solution, and stirring the solution at room temperature until the color of the 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 fabric (8) as a temperature sensing material by adopting an explosion spraying method, and manufacturing a temperature sensing area according to a spiral pattern with the shape of Chinese character 'hui', wherein the pattern with the shape of Chinese character 'hui' has the advantages of wide temperature measuring range and high stability.
And 4, step 4: installation temperature measuring function unit (2)
The temperature measuring unit (2) is paved on the heating unit (1) by using J-189 adhesive; paving the layers at 45 degrees to the marked scribed lines; after being laid, the vacuum is pumped, and the vacuum degree is 0.25MPa
About 0.45MPa for 25-35 min.
And 5: make overcurrent protection unit (3)
Firstly, adding 25g of single-walled carbon nanotube with the mass fraction of 25%, 15g of polydimethylsiloxane material and 35g of natural crystalline flake graphite into 100ml of acetone solution, uniformly mixing, then adding 30ml of mixed solution (4:1) of potassium permanganate oxidation and concentrated sulfuric acid at the temperature of 35 ℃, carrying out oxidation intercalation, and mixing the obtained organic mixture with deionized water to prepare 1.5mg/ml of colloidal solution. And finally, ultrasonically stripping the colloidal solution in an ultrasonic cleaning machine with the power of 150W and the frequency of 20kHz for 45min, stirring for 90min, filtering, drying, extracting and filtering to form a composite organic composite membrane, and preparing the flexible overcurrent protection unit.
Step 6: mounting overcurrent protection unit (3)
The overcurrent protection unit (3) is paved on the temperature measurement unit (2) by using J-189 adhesive; after being paved, the vacuum is pumped, the vacuum degree is 0.25MPa to 0.45MPa, and the vacuum lasts for 25 minutes to 35 minutes.
And 7: mounting electric connection unit (4)
The conducting wires of all the functional layers sequentially penetrate through the composite material layer through holes and are welded with the bus bars (9) of the electric connection units (4) after penetrating out, and then the bus bars (9) are welded and fixed with the binding posts (10); the electric connection unit (4) is arranged on the overcurrent protection unit (3) by using J-189 adhesive;
and 8: integral hot press forming
After the 4 functional units are manufactured, pasting a vacuum bag, vacuumizing and hot-pressing, wherein the negative pressure is 0.35 MPa-0.85 MPa, the temperature is 120 ℃, and hot-pressing is carried out for 45 minutes-60 minutes.
Claims (9)
1. An embedded inlet lip anti-icing heating assembly is characterized by comprising a heating function unit (1), a temperature measurement function unit (2), an overcurrent protection unit (3) and an electric connection unit (4); a heating function unit (1), a temperature measurement function unit (2), an overcurrent protection unit (3) and an electric connection unit (4) are sequentially paved on the base body of the inlet lip of the airplane;
the heating function unit (1) mainly converts electric energy into heat energy, the temperature measurement function unit (2) mainly has a temperature measurement 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.
2. The embedded inlet lip anti-icing heating assembly of claim 1, wherein the electrical connection unit (4) is composed of 3 bus bars (9) and 3 binding posts (10), each binding post (9) is installed on one side of the bus bar (10) and connected by laser soldering.
3. The embedded inlet lip anti-icing heating assembly of claim 2, wherein 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.
4. The method for manufacturing the embedded inlet lip anti-icing heating assembly according to any one of claims 1 to 3, characterized by comprising the following steps:
step 1: preparing a mould, coating a release agent, fixing an aircraft inlet lip substrate on the mould, covering a heating function unit (1) to a mark reticle needing heating and anti-icing according to a partition design by adopting a 3D printing process, and printing the heating function unit on the aircraft inlet lip substrate by adopting the 3D printing process; after printing, carrying out vacuum pumping treatment, wherein the vacuum degree is 0.16-0.25 MPa, and the vacuum degree lasts for 20-30 minutes;
step 2: the temperature measuring unit (2) is paved on the heating unit (1) by using an adhesive; paving the layers at 45 degrees to the marked scribed lines; after paving, vacuumizing treatment is carried out, wherein the vacuum degree is 0.25MPa to 0.45MPa, and the vacuum degree lasts for 25 minutes to 35 minutes;
and step 3: the overcurrent protection unit (3) is paved on the temperature measurement unit (2) by using an adhesive; after paving, vacuumizing treatment is carried out, wherein the vacuum degree is 0.25MPa to 0.45MPa, and the vacuum degree lasts for 25 minutes to 35 minutes;
and 4, step 4: the conducting wires of all the functional layers sequentially penetrate through the composite material layer through holes and are welded with the bus bars (9) of the electric connection units (4) after penetrating out, and then the bus bars (9) are welded and fixed with the binding posts (10); the electric connection unit (4) is arranged on the overcurrent protection unit (3) by using an adhesive;
and 5: and (3) performing integral hot-press molding, pasting a vacuum bag after the 4 functional units are manufactured, and performing vacuum pumping and hot-press treatment, wherein the negative pressure is 0.35-0.85 MPa, the temperature is 120 ℃, and the hot-press treatment is performed for 45-60 minutes.
5. The method for manufacturing the embedded inlet lip anti-icing heating assembly according to claim 4, wherein the partitions of the heating unit (1) are custom-designed according to the power density and different modes of anti-icing and de-icing, and the heating unit (1) is manufactured with different power densities according to different anti-icing power requirements, wherein the power density of the anti-icing mode is 3W/cm2The power density of the deicing mode is 2W/cm2The heating element is designed according to a sine curve shape by adopting a Sin (3x) function.
6. The manufacturing method of the embedded inlet lip anti-icing heating assembly according to claim 4, characterized in that the manufacturing method of the heating unit (1) comprises the following steps: the preparation method comprises the steps of mixing 30% of carbon nano paper, 50% of graphite, 10% of paraffin and 10% of polyacrylate to prepare a conductive polymer (5), printing the conductive polymer on polyethylene fibers by adopting a 3D printing process, then soaking the conductive polymer in 9225-grade organic silicon rubber solution, and preparing a flexible heating unit by taking a cured rubber sleeve (6) as an insulating protective layer.
7. The manufacturing method of the embedded inlet lip anti-icing heating assembly according to claim 4, wherein the preparation method of the temperature measurement functional unit (2) comprises the steps of firstly weighing 5g of pure copper powder, adding the weighed 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 acid washing into a gelatin water solution with the mass fraction of 0.8%, and uniformly performing ultrasonic dispersion; finally, 10ml of citric acid and 15g of Ag are weighed2SO4Adding the solution into 250mL of deionized water to prepare silver citrate suspension, slowly pouring the silver citrate suspension into a copper source solution, and stirring the mixture at room temperature until the color of the 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 terylene cloth (8) as a temperature sensing material by adopting an explosion spraying method, and manufacturing a temperature sensing area according to a spiral pattern in a shape of Chinese character 'hui'.
8. The manufacturing method of the embedded inlet lip anti-icing heating assembly according to claim 4, characterized in that the preparation method of the overcurrent protection unit (3) comprises the following steps: firstly, adding 25g of single-walled carbon nanotube with the mass fraction of 25%, 15g of polydimethylsiloxane material and 35g of natural crystalline flake graphite into 100ml of acetone solution, uniformly mixing, then adding 30ml of mixed solution (4:1) of potassium permanganate oxidation and concentrated sulfuric acid at the temperature of 35 ℃, carrying out oxidation intercalation, and mixing the obtained organic mixture with deionized water to prepare 1.5mg/ml of colloidal solution; and finally, ultrasonically stripping the colloidal solution in an ultrasonic cleaning machine with the power of 150W and the frequency of 20kHz for 45min, stirring for 90min, filtering, drying, extracting and filtering to form a composite organic composite membrane, and preparing the flexible overcurrent protection unit.
9. The method for manufacturing the embedded inlet lip anti-icing heating assembly according to claim 4, wherein the adhesives adopted in the steps 2, 3 and 4 are J-189 adhesives.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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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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| CN113955124B (en) | 2024-02-13 |
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