CN112607048B - Temperature-adjustable solar composite material repairing device - Google Patents
Temperature-adjustable solar composite material repairing device Download PDFInfo
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- CN112607048B CN112607048B CN202011277195.6A CN202011277195A CN112607048B CN 112607048 B CN112607048 B CN 112607048B CN 202011277195 A CN202011277195 A CN 202011277195A CN 112607048 B CN112607048 B CN 112607048B
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- temperature
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
Abstract
The invention discloses a temperature-adjustable solar composite material repairing device, which belongs to the field of structure repairing and comprises a supporting structure, a plate-shell structure and a repairing area, wherein a vacuum bag is arranged at the upper end of the plate-shell structure, and in a space formed by the vacuum bag: a composite material repairing component is adhered to the upper end of the repairing area; the composite material repairing assembly comprises an adhesive film, a composite material patch is arranged at the upper end of the adhesive film, a plurality of thermocouples are arranged above the composite material patch, the thermocouples are connected with a temperature control system, and isolating films are arranged above the composite material patch and the thermocouples; and a solar heat absorption material film is adhered and covered on the isolating film, and a plurality of electrochromic films are adhered on the upper surface of the solar heat absorption material film. The invention utilizes the technology of combining the heating layer with the solar heat-absorbing material coating and the electrochromic film, so that the heating curing composite material and the like are coated with glue and cured, cracks are repaired or a patch is adhered to a damaged area, and the damage of equipment such as an airplane and the like is repaired more conveniently and rapidly.
Description
Technical Field
The invention relates to the field of structure repair, in particular to a heating process required in the process of repairing the surface structure of equipment such as an airplane and the like by adopting materials such as a composite material or a special adhesive and the like, and particularly relates to a temperature-adjustable solar composite material repairing device.
Background
Composite materials are used in large quantities for their excellent properties. For example, various aircraft, such as fighter and civil aircraft, incorporate an increasing amount of composite material into structures, such as skins, due to the good mechanical properties of the composite material. Further, machines such as automobiles and ships are beginning to use composite materials for structures such as housings.
The outer surface structure of equipment such as aircrafts, ships and automobiles is often damaged by cracks, peeling, gaps, dents, corrosion and the like. Most failure situations occur in metal plates, shells, etc. With the extensive use of composite materials, such damage also occurs to the structures made of the composite materials. The composite materials have been successfully glued as a new "connector" or patch directly to the damaged area (also known as the rework area) of the device surface.
And for smaller damages such as cracks, the adhesive bonding is directly carried out by adopting the heating curing composite material for adhesive coating. For larger lesions, the patch is typically bonded to the rework area with glue, wherein the glue is positioned at the bond line between the patch and the rework area. Typically, heat and pressure are applied to the patch, for example by means of a heated pad and a vacuum bag. A heating pad is used to raise the bond line to the appropriate glue curing temperature. A vacuum bag may be used to consolidate the debulked patch. During the curing process, the bond line may be maintained within a relatively narrow temperature range for a predetermined period of time in order to fully cure the adhesive. Furthermore, the entire area of the bonding line can be maintained within a temperature range that is substantially unchanged across the bonding line.
If the patch is large, a thermal survey of the rework area may be required before bonding the patch to the rework area. A thermal survey may be required to identify locations of non-uniform heating of the rework area by the heating pad. Because the rework area is mostly of a metal structure, the heat conduction performance is obviously different from that of the patch, and differential heating of the area near the bonding line can be caused, so that non-uniform heating can be caused. In this regard, the thermal survey may provide a means for identifying hot and cold spots within the rework area, either by adding temporary insulation to the composite structure or by adjusting the heating pad temperature until the temperature is within a desired range.
Conventional thermal surveying processes require the assembly of a surrogate patch that is a duplicate of a patch to be permanently bonded to a composite structure. In this regard, conventional surrogate patches are formed from the same type of composite material as the final patch and have the same number of plies as the final patch. Construction of conventional surrogate patches is a time consuming and labor intensive process that typically requires manual cutting of multiple composite plies, and where each composite ply has a unique size and shape for each rework area ply to be replaced. After a thermal survey, conventional surrogate patches are typically discarded after a single use.
In the aviation field, the composite material is applied to repair, so that the flight performance of a large number of airplanes is recovered, the service life is prolonged, and very remarkable economic benefit is obtained. But conventional heating methods also expose some problems. The thermal survey process takes a significant amount of time and wastes one patch. Such patches are hand-made and the manufacturing process also consumes a significant amount of time. Splitting the thermal survey and heating into two processes also results in repeated heating, which can easily damage the structure.
The heating mat adopting electric heating needs an external power supply with larger electric quantity, thereby being difficult to realize the outfield restoration of the active aircraft. It is difficult to carry large storage batteries and electric heating equipment when other equipment such as automobiles, ships and the like works outdoors.
Disclosure of Invention
Aiming at the problems in the prior art, based on the composite material repairing technology, in a vacuum bag, a heating layer with a solar heat-absorbing material coating is utilized, and meanwhile, an electrochromic film is adopted to carry out semi-active control to keep the temperature of each area within a reasonable range, so that the heating curing composite material and the like are coated with glue and cured, cracks are repaired or a patch is adhered to a damaged area, and therefore damages of equipment such as an airplane and the like are repaired more conveniently and quickly.
The invention is realized by the following steps:
a temperature-adjustable solar composite material repairing device comprises a supporting structure, a plate-shell structure and a damaged part, namely a repairing area, wherein the plate-shell structure is arranged at the upper end of the supporting structure; in the space formed by the vacuum bag: and a composite material repairing component is adhered to the upper end of the repairing area.
The composite material repairing assembly comprises an adhesive film, a composite material patch is arranged at the upper end of the adhesive film, a plurality of thermocouples are arranged above the composite material patch, the thermocouples are connected with a temperature control system, and isolating films are arranged above the composite material patch and the thermocouples; a solar heat absorption material film is adhered and covered on the isolating film, and a plurality of electrochromic films are adhered on the upper surface of the solar heat absorption material film; in the method adopted by the patent, the size and the thickness of the solar heat absorbing material film and which solar heat absorbing material and coating method are adopted can be determined according to the actual situation. The coating can be selected from conventional electroplating coatings such as 1, black chromium coating, black cobalt coating and the like. 2. An electrochemical surface conversion coating. Such as aluminum anodized coatings, CuO conversion coatings, steel anodized coatings, and the like. 3. Preparing an absorption coating by vacuum plating and magnetron sputtering technology. 4. A paint type coating. And the like. Or selecting new materials such as non-traditional graphene and the like. Substrates can be divided into hard and flexible materials. When repairing on some planes and regular curved surfaces, hard materials such as metal (such as aluminum plates), glass, graphene, carbon fibers and the like can be adopted as substrates. When the complex curved surface is repaired, flexible materials such as tinfoil paper, rubber and other high polymer flexible materials can be adopted. When the repairing operation is carried out and the repairing operation is carried out, the solar heat absorption material film covers the composite material repairing sheet. If it is considered that the composite patch or other bonding adhesive material will be exposed to the solar heat absorbing film when melted, a barrier layer may be applied between the patch and the film. The insulating layer should have good thermal conductivity.
The repairing device is placed under the sunlight, and the solar heat absorption material film converts solar energy into heat energy, so that the temperature of the composite material patch is continuously increased; and monitoring the temperature in real time by adopting a thermocouple and feeding the temperature back to a temperature control system, adjusting the voltage of the electrochromic film to adjust the temperature, heating according to a preset curve, and finally taking down the vacuum bag and the assembly to finish the repair process.
The electrochromic material, i.e., the electrochromic film, can change light transmittance according to a change in voltage. The flexible electrochromic material is cut into 50-100 square centimeters (other areas can be adopted according to actual conditions), and the anode and the cathode of each flexible electrochromic film are connected with a power supply and a controller. The power supply and the controller can be made small and handy due to the small amount of electricity required. The controller has a control program edited in advance. The thermocouple attached to the surface of the composite material and each flexible electrochromic film at the corresponding position form a semi-active control system, when the temperature of the thermocouple at a certain position is too high or is heated too fast to cause uneven heating, a signal is transmitted to the controller, and the controller changes the voltage on the corresponding flexible electrochromic film to darken the color and reduce the light transmittance, so that the obtained heat is reduced.
Furthermore, a sealing rubber ring is arranged between the vacuum bag and the repair area and is completely sealed through the sealing rubber ring.
Furthermore, the positions of the thermocouples correspond to the positions of the electrochromic films up and down, and the installation positions of the thermocouples correspond to the middle position of each piece of electrochromic film.
Furthermore, an air bag is arranged above the vacuum bag, and plays a role in heat preservation by utilizing the air bag.
Further, the lower surface of the solar heat absorption material film can be provided with a breathable felt. The air-permeable felt can be attached below the solar heat absorption material film or can be eliminated.
Furthermore, the thermocouple is connected with a temperature control system outside the structure; the temperature control system is connected with the electrochromic film by using an electric wire.
The beneficial effects of the invention and the prior art are as follows:
the traditional composite material repairing method is heated by a resistance wire in a vacuum bag, and consumes a large amount of electricity, so that the method cannot be used in an external field. In many situations, such as field warfare areas, aircraft carriers, it is possible that our aircraft may not be able to enter and exit the hangar as quickly as possible, and some areas may not have a service hangar. The problem of too many ground lines is also caused by leading the power supply from the hangar to the vicinity of the plane parked at an outfield in many times, which easily causes a potential safety hazard, not to mention the problem of unstable voltage or power failure in remote areas. The film made of solar heat-absorbing material can perfectly solve the problem. The solar energy is sufficient in sunshine in regions such as oceans, deserts, middle east, plateaus and the like, and the short plate of the traditional power-dependent restoration method can be compensated by the solar energy. 7, 3.2019, American researchers newly develop a novel aerogel material with high cost performance, and the aerogel material can be used for a solar heat collector to improve the heat collection efficiency and keep the temperature at 220 ℃. This temperature far exceeds the maximum temperature of 120 ℃ for unidirectional carbon fiber prepregs. Illustrating that curing of the composite using solar heat absorbing materials is feasible.
In addition, when the repair area is large, there may be a case where the temperature is different from place to place. At the position where the skin is contacted with the beam, the heat conduction is more, so that the temperature at the position is easy to be lower, the control is difficult by using a resistance wire heating method, and the problems of complex circuit and the like are easily caused by rearranging the resistance wires for different patch shapes. And the light transmittance is adjusted by adopting the electrochromic film, so that the temperature of each part can be adjusted. The patch has good adaptability to patches with different shapes. The electric quantity and the voltage required by the electrochromic film are very small, and the requirement can be met only by a very small power supply.
The repairing device of the invention adopts solar energy as direct energy for curing the adhesive, so that the repairing process can be carried out in an external field without carrying a huge power supply or an external power supply. The patent also provides a temperature-adjustable method based on the flexible electrochromic film, so that the thermal surveying step can be omitted, the requirement of uniform heating near the bonding line is met, and the problem that the temperature is difficult to control in the electrical heating process during large-area repair is avoided. Traditional electrical heating has the drawback such as equipment complicacy and dependence power, and this patent adopts solar energy heat-absorbing material film to become thermal energy heating combined material patch with solar energy to electrochromic film regulation temperature.
The invention takes the flexible plastic film material as the basis to realize the phenomenon that the optical properties (reflectivity, transmissivity, absorptivity and the like) of the flexible plastic film material generate stable and reversible color depth change under the action of an external electric field. The electric quantity adopted by the technology is very small, in addition, the solar energy absorption coating has great influence on the technical and economic performance of solar energy utilization, and various coatings adopted by the invention can achieve good effect.
Drawings
FIG. 1 is a schematic diagram of an embodiment of a cross-sectional view of a temperature-adjustable solar composite repair device according to the present invention;
FIG. 2 is a top view of an electrochromic film structure and a diagram of a circuit system;
FIG. 3 is a schematic cross-sectional view of an example of a temperature-adjustable solar composite repair apparatus according to the present invention;
in the figure, 1-support structure, 2-plate shell structure, 3-repair area (damaged part on the skin), 4-vacuum bag, 5-sealing rubber ring, 6-adhesive film, 7-composite material patch, 8-thermocouple, 9-isolation film, 10-solar heat absorption material film, 11-electrochromic film, 12-air permeable felt, 13-composite material repair component, 14-air bag, 15-temperature control system and 16-electric wire.
Detailed Description
In order to make the objects, technical solutions and effects of the present invention more clear, the present invention is further described in detail by the following examples. It should be noted that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Fig. 1 and 3 are schematic cross-sectional views of a film coated with a solar heat absorbing material and a vacuum bag assembly using a flexible electrochromic film for temperature control according to the present invention. The composite material repairing component 13 adopts the solar heat absorption material film 10 and the electrochromic film 11 to replace the traditional resistance wire heating pad. The specific operation is as follows:
firstly, the position of the repair area 3 is accurately found, and a proper composite material gluing method is selected according to damage conditions such as fracture, corrosion, pot holes and the like. And adhering a composite material repairing component 13 to the repairing area 3, wherein the composite material repairing component 13 is composed of an adhesive film 6, a composite material patch 7, a thermocouple 8 (wiring is not marked) and an isolating film 9. Firstly, the composite material patch 7 is stuck on the repair area 3 by the glue film 6, the thermocouple 8 is stuck above the composite material patch 7, and the thermocouple 8 transmits the temperature of the composite material patch 7 to the temperature controller. The number of thermocouples 8 installed is determined according to the area of the composite patch 7. In the embodiment, one piece of the electrochromic film is arranged at 50-100 square centimeters, and the installation position of each thermocouple corresponds to the middle position of each electrochromic film 11 as much as possible. The isolation film 9 covers the thermocouple 8 and the composite material patch 7, and the isolation film 9 can prevent the composite material patch 7 from being adhered to the solar heat absorption material film 10 when melting, and plays a role in transferring heat. The solar heat absorbing material film 10 is covered on the isolating film 9 by common glue.
The electrochromic film 11 is adhered to the surface of the solar heat absorption material film 10 by using common colorless glue. The number and size of the electrochromic films 11 are determined according to the size of the solar heat absorbing material film 10. 50-100 square centimeters can be used as the area of one electrochromic film 11. In this example, 9 electrochromic films 11 of the same size were used, as shown in fig. 2.
The airfelt 12 can be attached below the solar heat absorbing material film 10 or can be eliminated. The sealing rubber ring 5 on the vacuum bag 4 is attached to the periphery, and then the whole structure is compacted by using a vacuum pump to pump air. The vacuum bag 4 is provided with an air bag 14 which is blown by a nozzle. The bladder 14 may serve as a thermal insulator.
After the patch is installed, the patch is placed in the sun, and the solar heat absorption material film converts solar energy into heat energy, so that the temperature of the composite patch 7 is continuously increased. The temperature is monitored in real time by adopting a thermocouple and fed back to the temperature control system 15, if the temperature displayed by the thermocouple at a certain position is high and the safety temperature standard is adopted, the voltage of the electrochromic film 11 at the certain position is adjusted to change the electrochromic film into dark color, the light transmittance of the sun is reduced, and the electrochromic film is heated according to a preset curve. The safety temperature standard can be adjusted according to the curing temperature of different materials. If the composite patch 7 is required to be uniformly heated in practical situations and the temperature rise curves are as uniform as possible, more heat may be conducted at the location of the support structure 1, resulting in the occurrence of cold spots. The controller 15 is required to adjust the transmittance of the electrochromic film 11 to make the temperatures of the respective portions close. In one embodiment, the curing process is carried out by heating to 120 ℃ and holding for a period of time before cooling to room temperature, as required for curing the resin in the prepreg. Finally, the vacuum bag and the assembly are taken down to complete the repair process.
If the time is urgent (such as a wartime situation), the solar heat absorbing material film 10 can be placed in the sun to be exposed to the sun to a certain temperature in advance and then installed in a vacuum bag when needed.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that modifications can be made by those skilled in the art without departing from the principle of the present invention, and these modifications should also be construed as the protection scope of the present invention.
Claims (7)
1. A temperature-adjustable solar composite material repairing device comprises a supporting structure (1), a plate-shell structure (2) arranged at the upper end of the supporting structure (1), and a damaged part, namely a repairing area (3), existing on the plate-shell structure (2), and is characterized in that a vacuum bag (4) is arranged at the upper end of the plate-shell structure (2), and the vacuum bag (4) completely covers the repairing area (3);
in the space formed by the vacuum bag (4): a composite material repairing component (13) is adhered to the upper end of the repairing area (3);
the composite material repairing assembly (13) comprises an adhesive film (6), a composite material patch (7) is arranged at the upper end of the adhesive film (6), a plurality of thermocouples (8) are arranged above the composite material patch (7), the thermocouples (8) are connected with a temperature control system (15), and isolating films (9) are arranged above the composite material patch (7) and the thermocouples (8); a solar heat absorbing material film (10) is adhered and covered on the isolating film (9), and a plurality of electrochromic films (11) are adhered on the upper surface of the solar heat absorbing material film (10); the repairing device is placed under the sunlight, the solar heat absorbing material film (10) converts solar energy into heat energy, and the temperature of the composite material patch (7) is continuously increased; a thermocouple (8) is adopted to monitor the temperature in real time and feed the temperature back to a temperature control system (15), then the voltage of the electrochromic film (11) is adjusted to adjust the temperature, heating is carried out according to a preset curve, and finally the vacuum bag and the assembly are taken down to complete the repairing process;
the adhesive film (6) adheres the composite material patch (7) to the repair area (3), a thermocouple (8) is adhered above the composite material patch (7), and the thermocouple (8) transmits the temperature of the composite material patch (7) to a temperature controller in time; the installation number of the thermocouples (8) is set according to the area of the composite material patch (7); after the patch is installed, the patch is placed in the sun, and the solar heat absorption material film converts solar energy into heat energy, so that the temperature of the composite material patch (7) is continuously increased; the temperature is monitored in real time by adopting a thermocouple and fed back to a temperature control system (15), if the temperature displayed by the thermocouple at a certain position is higher than the safety temperature standard, the voltage of the electrochromic film (11) at the position is adjusted to change the electrochromic film into dark color, the light transmittance of the sun is reduced, and the electrochromic film is heated according to a preset curve.
2. The solar composite repair device with the adjustable temperature according to claim 1, wherein a sealing rubber ring (5) is arranged between the vacuum bag (4) and the repair area (3), and is completely sealed through the sealing rubber ring (5).
3. The temperature-adjustable solar composite material repairing device according to claim 1, wherein the positions of the thermocouples (8) are up and down corresponding to the positions of the electrochromic films (11), and the installation positions of the thermocouples (8) correspond to the middle position of each electrochromic film (11).
4. The solar composite repair device with the adjustable temperature according to claim 1, wherein an air bag (14) is arranged above the vacuum bag (4), and the air bag (14) is used for heat preservation.
5. The solar composite repair device with adjustable temperature according to claim 1, wherein the lower surface of the solar heat absorbing material film (10) is further provided with an air-permeable felt (12).
6. The solar composite repair device with adjustable temperature according to claim 1, characterized in that said thermocouple (8) is connected to a temperature control system (15) outside the structure; the temperature control system (15) is connected with the electrochromic film (11) by using an electric wire.
7. The temperature-adjustable solar composite material repairing device according to claim 1, wherein the coating of the solar heat absorbing material film (10) is selected from a black chromium coating, a black cobalt coating, an aluminum anodic oxidation coating, a CuO conversion coating, a steel anodic oxidation coating, a vacuum coating, a magnetron sputtering technology, and an absorption coating, a paint type coating, or graphene.
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| US10160163B2 (en) * | 2011-08-11 | 2018-12-25 | The Boeing Company | Heating system for composite rework of aircraft |
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