A rapid repair emergency repair kit and repair method for aircraft composite material structures

Abstract

The present invention discloses a rapid repair and emergency repair kit and a repair method for aircraft composite material structures in the technical field of aircraft composite material repair, which includes a toolbox. A detachable repair box and a solar panel are rotatably connected to the toolbox. Locking parts that are mutually locked and matched are provided on the same side wall of the toolbox and the repair box. A number of tool grooves are formed inside the toolbox, and repair tools are respectively placed in the tool grooves. A controller, a storage battery, and a vacuum pump are installed below the tool grooves. A cover plate is rotatably connected to the top of the repair box, and a heater is installed in the middle of the cover plate. The solar panel, the heater, and the vacuum pump are respectively electrically connected to the storage battery. Suction blocks are installed on both side walls in the width direction of the repair box, and the suction blocks are all communicated with the inside of the repair box. Suction pipes are communicated between the suction blocks and the vacuum pump. A circumferential fixed rubber is provided on the side wall at the bottom of the repair box, and an arc-shaped groove is provided at the bottom of the fixed rubber. The present invention can be used in bad weather, and has strong practicability and high applicability.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft composite material repair, and particularly to a rapid repair emergency repair kit and repair method for aircraft composite material structures. Background Art

[0002] With the development of science and technology, the application technology of composite materials has been continuously improved, and more and more advanced composite materials are applied to aircraft. Composite materials are widely used in aircraft structural components such as fuselage skins, aircraft wings, and stabilizer surfaces. Composite materials account for 60% of the total aircraft weight, and the volume ratio even exceeds 80%. Bonding repair is a common repair method for aircraft composite material structures. Generally, prepregs or wet layups are laid layer by layer, and then a heat patch instrument is used to control heating and curing with electric blankets, infrared lamps, hot air blowers, etc. Therefore, an emergency repair kit that can meet the requirements of composite material repair tools and environmental conditions is needed to ensure the repair quality of composite materials.

[0003] For example, in Chinese Patent, publication number: CN114851602A, the invention discloses a rapid repair emergency repair kit and repair method for aircraft composite material structures. The emergency repair kit includes repair patches, which are cured and formed by an autoclave device and are made in several specifications; a portable heater, which is filled with phase change energy storage materials and can generate heat spontaneously to solve the problem of power dependence; a portable vacuum device, which is directly connected to a vacuum pump through a vacuum nozzle, does not require sealant and can be reused; a special adhesive, which is a two-component non-mixed adhesive, including component A and component B; auxiliary tools, including a positioning identification plate, a gluing plate, and a limiting template; and auxiliary materials.

[0004] The method of this invention solves the problems of the dependence on power supply under existing curing conditions (such as the temperature required for curing) and the inconvenience of using tools such as vacuum bags by designing prefabricated patches, portable heating packs, portable vacuum devices, and simple auxiliary tools. However, this invention lacks equipment for creating a vacuum environment, and at the same time, the emergency repair kit has few carrying tools and cannot shield rain and snow when used in bad weather such as rain and snow, resulting in low applicability. Therefore, the present invention proposes a rapid repair emergency repair kit and repair method for aircraft composite material structures to solve the above-mentioned problems. Summary of the Invention

[0005] The present invention aims to provide a rapid repair emergency repair kit and repair method for aircraft composite material structures to solve the problem that the existing technical means have few carrying tools and cannot shield rain and snow when used in bad weather such as rain and snow, resulting in low applicability.

[0006] To achieve the above object, the basic solution of the present invention is as follows: A rapid repair and emergency repair kit for aircraft composite material structures, including a toolbox, a detachable repair box and a solar panel are rotatably connected to the toolbox, the solar panel is located between the toolbox and the repair box, and locking parts that are locked and matched with each other are provided on the same side wall of the toolbox and the repair box. A number of tool grooves are opened inside the toolbox, and repair tools are respectively placed in the tool grooves. The repair tools include aluminum foil tape, release cloth, isolation film, repair patch, positioning identification plate, glue spreading plate, equalizing plate and breathable felt. A controller, a storage battery and a vacuum pump are installed at the lower part of the tool groove. A cover plate is rotatably connected to the top of the repair box, and a heater is installed in the middle of the cover plate. The solar panel, the heater and the vacuum pump are respectively electrically connected to the storage battery. Suction blocks are installed on both side walls in the width direction of the repair box, and the suction blocks are all communicated with the inside of the repair box. A suction pipe is communicated between the suction block and the vacuum pump. A circumferential fixing rubber is provided on the side wall of the bottom of the repair box, and an arc-shaped groove is provided at the bottom of the fixing rubber.

[0007] Principle of the basic solution: For the rapid repair and emergency repair kit proposed by the present invention, the toolbox and the repair box are locked by the locking parts that are locked and matched with each other. During use, the locking parts are opened, and the repair box on the toolbox is removed through detachable connection. Through the arc-shaped groove at the bottom of the circumferential fixing rubber provided on the side wall of the bottom of the repair box, the four side walls of the repair box can be fixed to the place to be repaired through pressure. Opening the cover plate is convenient for cleaning. Through the storage battery and the vacuum pump installed in the toolbox, and the suction pipe connecting the vacuum pump and the inside of the repair box, the air in the repair box is pumped out, making the inside of the repair box a vacuum environment, which is convenient for heating and repair; the solar panel is used for power supply supplement. Through a number of tool grooves, the tools for repair can be placed in the tool grooves, and during the process of carrying and transporting, the side walls of the tool grooves protect and limit the tools.

[0008] The beneficial effects achieved are: (1) For the rapid repair and emergency repair kit for aircraft composite material structures proposed by the present invention, through the detachable and rotatable repair box installed on the toolbox, a part of the repair kit can be used as repair tools to cover the place to be repaired. While facilitating the extraction of the vacuum environment to accelerate the repair, it blocks the interference items in the external environment, such as rain and snow, ensuring portability while meeting the requirements of rapid and efficient on-site emergency repair, and can be used in bad weather, solving the problems of few tools carried by the existing repair kits and low practicability and applicability.

[0009] (2) The inside of the repair box is sucked through two suction pipes, so that the repair patch placed in the repair box can quickly be in a negative pressure state, and then the repair patch is pre-cured by the heater, thereby discharging the inevitable gas and moisture between the layers of materials during the production of the repair patch, improving the reliability of the repair patch.

[0010] Further, a handle is provided on the side wall of the toolbox.

[0011] The principle and beneficial effects of the basic solution are as follows: Through the handle provided on the side wall of the toolbox, it is convenient for the user to carry and transport, increasing the portability of the repair kit.

[0012] Further, a horizontal telescopic pull rod is installed at the bottom of the toolbox, and a holding rod is provided at one end of the telescopic pull rod.

[0013] The principle and beneficial effects of the basic solution are as follows: Through the horizontal telescopic pull rod installed at the bottom of the toolbox, it can be extended and retracted, facilitating the user to pull the repair kit.

[0014] Further, a number of universal wheels are installed on the side wall in the width direction of the toolbox.

[0015] The principle and beneficial effects of the basic solution are as follows: Through the installation of a number of universal wheels, when transporting the repair kit, it is convenient for the applicable personnel to pull the repair kit as easily as pulling a suitcase, increasing the transportation speed.

[0016] Further, tempered glass plates are installed on the side walls of the repair box.

[0017] The principle and beneficial effects of the basic solution are as follows: Through the tempered glass plates installed on the side walls of the repair box, it is convenient to observe the repair situation inside the repair box during the repair process, enabling the repair personnel to make adjustments according to the observed situation.

[0018] Further, a number of bumps are provided at the bottom of the toolbox.

[0019] The principle and beneficial effects of the basic solution are as follows: Through the number of bumps provided at the bottom of the toolbox, they can be used as support components when placing the toolbox, increasing the stability of the toolbox when placed.

[0020] A method for rapid repair of aircraft composite material structures specifically includes the following steps:

[0021] Step 1: Pull the emergency repair kit to the vicinity of the part to be repaired, place the emergency repair kit horizontally and flat, rotate the repair box and the solar panel to the appropriate positions, open the toolbox, and take out the measuring tools;

[0022] Step 2: Use the measuring tools to measure the damage type and shape parameters of the part to be repaired on the part to be repaired, and prepare the corresponding repair materials according to the measured data;

[0023] Step 3: Remove the repair box, cover the part to be repaired with the repair box, and fix the repair box on the part to be repaired by using the bottom fixing rubber;

[0024] Step 4: Open the repair box cover plate, and use the cleaning tool and the drying tool to clean and dry the part to be repaired respectively;

[0025] Step 5: Use an adhesive applicator to apply the adhesive on the area to be repaired and the repair patch, and place the repair patch into the repair box and position it on the area to be repaired.

[0026] Step 6: Successively stick a release cloth, an isolation film, a pressure equalizing plate, and a breather felt on the repair patch, close the cover plate, and rotate the connecting rod to make the fixing block press inward against the breather felt to prevent its position from shifting.

[0027] Step 7: Start the vacuum pump, use a double suction pipe to evacuate the inside of the repair box to a vacuum, start the heater, heat and cure the repair patch for one hour, and remove the auxiliary materials.

[0028] Step 8: Open the cover plate of the repair box, check the repaired area, and remove the excess adhesive.

[0029] Step 9: Remove the repair box and reinstall it on the toolbox, sand and clean the repaired area smoothly, stick an aluminum foil tape, and finally put the repair tools back into the toolbox.

[0030] Further, in Step 7, when starting the heater and the vacuum pump, rotate the solar panel on the toolbox to a position inclined 30 - 60 degrees to the toolbox.

[0031] The principle and beneficial effects of the basic solution are as follows: The rapid repair method for aircraft composite material structures proposed by the present invention can meet the requirements of rapid, efficient, and low environmental requirements for on-site emergency repair. When exposed to sunlight, the inclined solar panel on the toolbox converts solar energy into electrical energy to supplement the electrical energy of the battery; when it rains or snows, the solar panel provides shelter for the toolbox to prevent rain or snow from flowing into the toolbox.

[0032] Additional aspects and advantages of the present invention will be given in part in the following description, become apparent in part from the following description, or be learned through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a front view when the emergency repair kit of the embodiment of the present invention is opened.

[0034] Figure 2 It is a front view when the cover plate of the repair box of the embodiment of the present application is opened.

[0035] Figure 3 It is a schematic internal structure diagram of the repair box of the embodiment of the present application fixed on the repair part.

[0036] Figure 4 It is a front view of the emergency repair kit of the embodiment of the present application.

[0037] Figure 5 It is a rear view of the emergency repair kit of the embodiment of the present application.

[0038] Figure 6 This is the front view of the solar panel according to the embodiment of the present application.

[0039] Figure 7 This is the flowchart of the method according to the embodiment of the present application. Detailed implementation manners

[0040] The embodiments of the present invention will be described in detail below. Examples of the embodiments are shown in the accompanying drawings, where the same or similar reference numerals indicate the same or similar elements or elements with the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary only for explaining the present invention and should not be construed as limiting the present invention.

[0041] In the description of the present invention, it should be understood that the orientation or positional relationships indicated by the terms "longitudinal", "transverse", "vertical", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are based on the orientation or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

[0042] In the description of the present invention, unless otherwise specified and limited, it should be noted that the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it can be a mechanical connection or an electrical connection, or it can be the communication inside two elements. It can be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms can be understood according to specific situations.

[0043] The reference numerals in the accompanying drawings of the specification include: toolbox 1, repair box 2, solar panel 3, locking fastener 4, handle 5, telescopic pull rod 6, tool groove 7, universal wheel 8, suction pipe 9, suction block 10, cover plate 11, heater 12, fixed rubber 13, part to be repaired 14, repair area 15, repair patch 16, release cloth 17, isolation film 18, pressure equalizing plate 19, breathable felt 20, threaded hole 21, connecting rod 22, fixed block 23, convex block 24.

[0044] The following will be further described in detail through specific implementation manners.

[0045] Embodiment 1:

[0046] The embodiment is basically as shown in Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6Shown: A rapid repair emergency kit for aircraft composite structures, including a toolbox 1, a detachable repair box 2 and a solar panel 3 are rotatably connected to the toolbox 1. The solar panel 3 is located between the toolbox 1 and the repair box 2. On the same side wall of the toolbox 1 and the repair box 2, there are locking fasteners 4 that are locked and matched with each other. Inside the toolbox 1, several tool grooves 7 are opened. Repair tools are placed in the tool grooves respectively. The repair tools include aluminum foil tape, release cloth 17, isolation film 18, repair patch 16, positioning identification plate, glue application plate, equalizing plate 19 and breathable felt 20. A controller, a storage battery and a vacuum pump are installed at the lower part of the tool groove 7. A cover plate 11 is rotatably connected to the top of the repair box 2. A heater 12 is installed in the middle of the cover plate 11. The solar panel 3, the heater 12 and the vacuum pump are respectively electrically connected to the storage battery. Suction blocks 10 are installed on both side walls in the width direction of the repair box 2. The suction blocks 10 are all communicated with the inside of the repair box 2. Suction pipes 9 are connected between the suction blocks 10 and the vacuum pump. A circumferential fixed rubber 13 is provided on the side wall of the bottom of the repair box 2. An arc-shaped groove is provided at the bottom of the fixed rubber 13; A pull handle 5 is provided on the side wall of the toolbox 1; A horizontal telescopic pull rod 6 is installed at the bottom of the toolbox 1. A holding rod is provided at one end of the telescopic pull rod 6; A number of universal wheels 8 are installed on the side walls in the width direction of the toolbox 1; Tempered glass plates are installed on the side walls of the repair box 2; A number of bumps 24 are provided at the bottom of the toolbox 1.

[0047] The specific implementation process is as follows: For the rapid repair emergency kit proposed by the present invention, the toolbox 1 and the repair box 2 are locked by the locking fasteners 4 that are locked and matched with each other. When in use, the locking fasteners 4 are opened, and the repair box 2 on the toolbox 1 is removed through detachable connection. Through the arc-shaped groove at the bottom of the circumferential fixed rubber 13 provided on the side wall of the bottom of the repair box 2, the four side walls of the repair box 2 can be fixed to the place to be repaired 15 through pressure. The cover plate 11 is opened for convenient cleaning. Through the storage battery and the vacuum pump installed in the toolbox 1, and the suction pipe 9 connecting the vacuum pump and the inside of the repair box 2, the air inside the repair box 2 is pumped out, making the inside of the repair box 2 a vacuum environment, which is convenient for heating and repair; The solar panel 3 is used for power supply supplement. Through several tool grooves 7, the repair tools can be placed in the tool grooves. During the process of carrying and transporting, the side walls of the tool grooves protect and limit the tools.

[0048] Through the pull handle 5 provided on the side wall of the toolbox 1, it is convenient for the user to carry and transport, increasing the portability of the repair kit.

[0049] Through the horizontal telescopic pull rod 6 installed at the bottom of the toolbox 1, it can be extended and retracted, which is convenient for the user to pull the repair kit.

[0050] Through the installation of several universal wheels 8, it is convenient for the applicable personnel to pull the repair kit like pulling a suitcase during the transportation of the repair kit, increasing the transportation speed.

[0051] Through the toughened glass plate installed on the side wall of the repair box 2, it is convenient to observe the repair situation inside the repair box 2 during the repair process, enabling the repair personnel to make adjustments according to the observed situation.

[0052] Through a number of bumps 24 provided at the bottom of the tool box 1, it can be used as a support component when placing the tool box 1, increasing the stability of the tool box 1 when placed.

[0053] Embodiment 2:

[0054] A method for rapid repair of aircraft composite material structures, as shown in the appendix Figure 7 shown: The specific steps are as follows:

[0055] Step 1, Pull the emergency repair kit to near the part to be repaired 14, place the emergency repair kit horizontally and flat, rotate the repair box 2 and the solar panel 3 to appropriate positions, open the tool box 1, and take out the measuring tools;

[0056] Step 2, Use the measuring tools to measure the damage type and shape parameters of the part to be repaired 15 on the part to be repaired 14, and prepare the corresponding repair materials according to the measured data;

[0057] Step 3, Remove the repair box 2, cover the part to be repaired 15 with the repair box 2, and fix the repair box 2 on the part to be repaired 14 by using the bottom fixing rubber 13;

[0058] Step 4, Open the cover plate 11 of the repair box 2, and use the cleaning tool and the drying tool to clean and dry the part to be repaired 15 respectively;

[0059] Step 5, Apply the adhesive on the part to be repaired 15 and the repair patch 16 with the glue application plate, and place the repair patch 16 into the repair box 2 and place it on the part to be repaired 15;

[0060] Step 6, Stick the release cloth 17, the isolation film 18, the uniform pressure plate 19 and the breathable felt 20 on the repair patch 16 in sequence, close the cover plate 11, rotate the connecting rod 22, and let the fixing block 23 press inward against the breathable felt 20 to prevent its position from shifting;

[0061] Step 7, Start the vacuum pump, use the double suction pipe 9 to evacuate the inside of the repair box 2 to vacuum, start the heater 12, heat and cure the repair patch 16 for one hour, and remove the auxiliary materials; at the same time, rotate the solar panel 3 on the tool box 1 to a position inclined 30 - 60 degrees to the tool box 1;

[0062] Step 8, Open the cover plate 11 of the repair box 2, check the repair area, and remove the excess adhesive;

[0063] Step 9: Remove the repair box 2 and reinstall it on the toolbox 1. Polish and clean the repaired area, apply aluminum foil tape, and finally put the repair tools back into the toolbox 1.

[0064] The specific implementation process is as follows: The rapid repair method for aircraft composite material structures proposed by the present invention can meet the requirements of rapid, efficient, and low environmental requirements for on-site emergency repair. When irradiated by the sun, the solar panel 3 inclined on the toolbox 1 converts solar energy into electrical energy to supplement the electrical energy of the storage battery; when it rains or snows, the solar panel 3 provides shelter for the toolbox 1 to prevent rain or snow from flowing into the toolbox 1.

[0065] The above are only embodiments of the present invention. Common general knowledge such as specific structures and / or characteristics known in the solutions is not described in detail herein. It should be noted that for those skilled in the art, without departing from the structure of the present invention, several modifications and improvements can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the implementation effect of the present invention and the practicality of the patent. The protection scope required by this application should be based on the content of its claims, and the specific implementation manners described in the specification can be used to explain the content of the claims.

Claims

1. A rapid repair method for aircraft composite material structures, characterized in that: Specifically, it includes the following steps: Step 1: Pull the emergency repair kit to the vicinity of the part to be repaired, place the emergency repair kit horizontally and flat, rotate the repair box and the solar panel to appropriate positions, open the toolbox, and take out the measuring tool; Among them, the emergency repair kit includes a toolbox. The toolbox is rotatably connected with a detachable repair box and a solar panel. The solar panel is located between the toolbox and the repair box. There are locking fasteners on the same side wall of the toolbox and the repair box that are locked and matched with each other. There are several tool grooves opened inside the toolbox. Repair tools are respectively placed in the tool grooves. The repair tools include aluminum foil tape, release cloth, isolation film, repair patch, positioning identification board, glue application board, equalizing pressure plate, and breathable felt. A controller, a storage battery, and a vacuum pump are installed at the lower part of the tool groove. The top of the repair box is rotatably connected with a cover plate. A heater is installed in the middle of the cover plate. The solar panel, the heater, and the vacuum pump are respectively electrically connected to the storage battery. Suction blocks are installed on both side walls in the width direction of the repair box. The suction blocks are all communicated with the inside of the repair box. Suction pipes are connected between the suction blocks and the vacuum pump. A circumferential fixing rubber is provided on the side wall of the bottom of the repair box. An arc-shaped groove is provided at the bottom of the fixing rubber; A handle is provided on the side wall of the toolbox; A horizontal telescopic pull rod is installed at the bottom of the toolbox. A holding rod is provided at one end of the telescopic pull rod; Step 2: Use the measuring tool to measure the damage type and shape parameters of the part to be repaired on the part to be repaired, and prepare corresponding repair materials according to the measured data; Step 3: Remove the repair box, cover the part to be repaired with the repair box, and fix the repair box on the part to be repaired by using the bottom fixing rubber; Step 4: Open the cover plate of the repair box, and use the cleaning tool and the drying tool to clean and dry the part to be repaired respectively; Step 5: Use the glue application board to apply the adhesive on the part to be repaired and the repair patch, and put the repair patch into the repair box and place it on the part to be repaired; Step 6: Stick the release cloth, isolation film, equalizing pressure plate, and breathable felt on the repair patch in sequence, close the cover plate, rotate the connecting rod, and let the fixing block press inward against the breathable felt to prevent its position from shifting; Step 7: Start the vacuum pump, use the double suction pipe to evacuate the inside of the repair box to a vacuum, start the heater, heat and cure the repair patch for one hour, and remove the auxiliary materials; Step 9: Open the cover plate of the repair box, check the repaired part, and remove the excess adhesive; Step 10: Remove the repair box and install it back on the toolbox, polish and clean the repaired part, stick the aluminum foil tape, and finally put the repair tools back into the toolbox.

2. The rapid repair method for aircraft composite material structure according to claim 1, wherein: Several universal wheels are installed on the side wall in the width direction of the toolbox.

3. A rapid repair method for aircraft composite material structures according to claim 1, characterized in that: Tempered glass plates are installed on the side walls of the repair box.

4. A rapid repair method for aircraft composite material structures according to claim 1, characterized in that: Several convex blocks are provided at the bottom of the toolbox.

5. A rapid repair method for aircraft composite material structures according to claim 1, characterized in that: In Step 7, when starting the heater and the vacuum pump, rotate the solar panel on the toolbox to a position that is inclined 30 - 60 degrees to the toolbox.

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