Helicopter composite material repairing and curing method and device based on temperature compensation

Abstract

The invention provides a helicopter composite material repairing and curing method based on temperature compensation, and the method comprises the following steps: carrying out polishing treatment on a damaged area of a composite material component, preparing a composite material prepreg patch for repairing, and placing the composite material prepreg patch on the surface of the damaged area; the flexible pneumatic telescopic system is adjusted according to the surface shape of the composite material component, so that the flexible pneumatic adsorption system is adsorbed to the surface of the composite material component; the flexible pneumatic adsorption system is adjusted, so that the pressure in the vacuum bag meets the curing requirement; a curing temperature curve is input to the device, an adjustable infrared heating temperature compensation system and an infrared thermal imaging system are started, and curing is started; meanwhile, the invention further provides a helicopter composite material repairing and curing device based on temperature compensation.

Description

Technical Field

[0001] The present application belongs to the technical field of composite material adhesive curing and repair, and in particular, relates to a helicopter composite material repair and curing method and device based on temperature compensation. Background Art

[0002] Composite materials are increasingly used in the aerospace field because they have the characteristics of high specific strength, high specific modulus, good fatigue resistance, etc. In addition, composite materials also have the advantage of multifunctional integration, which can realize the integration of multiple functions in one material, such as electrical conductivity, thermal conductivity, impact resistance, etc.

[0003] However, composite materials may become damaged during use and need to be repaired. The wet dressing repair method is to apply liquid resin directly to the damaged area and then cure it by heating. The vacuum-assisted resin transfer molding repair method is to wrap the damaged area in a vacuum bag, transfer liquid resin to the damaged area by vacuum suction, and then cure it by heating.

[0004] However, due to the uneven temperature distribution during the heating process, different parts of the damaged area may experience different curing speeds and degrees of curing, which may cause deformation of the repaired composite material and affect the quality of the repair. Summary of the invention

[0005] Purpose of the invention: The present invention provides a method and device for rapid curing of helicopter composite repair based on temperature compensation. The device mainly includes an adjustable infrared heating temperature compensation system, an infrared thermal imaging system, a flexible pneumatic telescopic system, and a flexible pneumatic adsorption system. The device adopts an adjustable infrared heating temperature compensation system and utilizes a high-precision cylinder to achieve precise control of the three-dimensional shape of the infrared heating lamp array, and precise control of the distance between the infrared lamp and the surface of the composite component to be repaired. The real-time feedback infrared thermal imaging system is utilized to achieve precise control of the heating power of the infrared lamp. The difficult problems of difficult control of the curing temperature, low curing efficiency, and poor curing quality of composite materials during the adhesive repair process are solved, thereby achieving rapid curing repair of composite materials and improving the repair quality.

[0006] In a first aspect, the present application provides a helicopter composite repair and curing method based on temperature compensation, the method comprising the following steps:

[0007] Grinding the damaged area of ​​the composite component, preparing a composite prepreg patch for repair, and placing it on the surface of the damaged area;

[0008] The flexible pneumatic telescopic system is adjusted according to the surface shape of the composite material component so that the flexible pneumatic adsorption system is adsorbed on the surface of the composite material component;

[0009] Adjust the flexible pneumatic adsorption system so that the pressure inside the vacuum bag meets the curing requirements;

[0010] Input the curing temperature curve into the device, turn on the adjustable infrared heating temperature compensation system and infrared thermal imaging system, and start curing.

[0011] Preferably, the method further comprises:

[0012] When the curing process is finished, the adjustable infrared heating temperature compensation system, the flexible pneumatic adsorption system and the flexible pneumatic telescopic system are turned off in sequence.

[0013] Preferably, the method of sequentially closing the adjustable infrared heating temperature compensation system, the flexible pneumatic adsorption system and the flexible pneumatic telescopic system includes:

[0014] First, turn off the adjustable infrared heating temperature compensation system to stop heating;

[0015] Then the flexible pneumatic adsorption system is turned off to release the adsorption state;

[0016] Finally, the flexible pneumatic telescopic system is turned off to restore the system to its initial state.

[0017] Preferably, the method further comprises:

[0018] After the curing process is completed, check the curing effect of the composite component to ensure that it has achieved the expected strength and performance;

[0019] Carry out necessary post-processing on the cured components;

[0020] Finally, the entire curing process was completed and the repair work of the composite material components was successfully completed.

[0021] Preferably, the necessary post-processing includes finishing and grinding to ensure that the surface is smooth and free of defects.

[0022] In the second aspect, the present application also provides a helicopter composite repair and curing device based on temperature compensation, the device comprising an adjustable infrared heating temperature compensation system 1, an infrared thermal imaging system 2, a flexible pneumatic telescopic system 3, and a flexible pneumatic adsorption system 4;

[0023] Among them, the adjustable infrared heating temperature compensation system 1 is composed of adjustable infrared heating temperature compensation components 6 arranged in an array, which can be flexibly adjusted according to the shape and area of ​​the composite structure to be repaired to adapt to different situations;

[0024] The infrared thermal imaging system 2 is used to monitor the surface temperature of the material in the repair and curing process in real time, and provide real-time feedback to the adjustable infrared heating temperature compensation system 1 to achieve precise control of the curing temperature;

[0025] The flexible pneumatic telescopic system, which is composed of a pneumatic control device 31 and a pneumatic telescopic device 32, can achieve precise height control of the pneumatically controlled telescopic rod to adapt to composite structures of different shapes;

[0026] The flexible pneumatic adsorption system 4, composed of a flexible suction cup 41 and a vacuum bag 42, can realize the adsorption of the device on the surface of the composite material to be repaired, and apply pressure to the composite material prepreg patch 51 for repair through the vacuum bag during the curing process.

[0027] Preferably, the adjustable infrared heating temperature compensation component 6 includes an air pipe connector 11, a cylinder 12, a piston 13, a piston sealing ring 14, a cylinder housing 15 and an adjustable infrared heating lamp 16, which can achieve precise control of the height and heating power of the adjustable infrared heating lamp 16.

[0028] Preferably, the repair composite prepreg patch 51 is a carbon fiber / epoxy resin composite prepreg patch.

[0029] Beneficial technical effects of this application:

[0030] The present invention discloses a method and device for rapid curing of helicopter composite repair based on temperature compensation. The device mainly comprises an adjustable infrared heating temperature compensation system, an infrared thermal imaging system, a flexible pneumatic telescopic system and a flexible pneumatic adsorption system. The device adopts an adjustable infrared heating temperature compensation system and utilizes a high-precision cylinder to achieve precise control of the three-dimensional shape of an infrared heating lamp array, and precise control of the distance between the infrared lamp and the surface of a composite component to be repaired. The real-time feedback infrared thermal imaging system is utilized to achieve precise control of the heating power of the infrared lamp. The difficult problems of difficult control of the curing temperature, low curing efficiency and poor curing quality of composite materials during adhesive repair are solved, and rapid curing repair of composite materials is achieved, thereby improving the repair quality. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is an overall schematic diagram of a helicopter composite material repair and curing device based on temperature compensation provided by a specific embodiment of the present invention;

[0032] Figure 2 It is a partial schematic diagram of a helicopter composite material repair and curing device based on temperature compensation provided by a specific embodiment of the present invention;

[0033] Figure 3 It is a schematic diagram of an adjustable infrared heating temperature compensation component provided by a specific embodiment of the present invention;

[0034] Among them: 1-adjustable infrared heating temperature compensation system; 2-infrared thermal imaging system; 3-flexible pneumatic expansion and contraction system; 4-flexible pneumatic adsorption system; 5-helicopter skin composite structure to be repaired; 6-adjustable infrared heating temperature compensation component; 41-flexible suction cup; 42-vacuum bag; 31-air pressure control device; 32-pneumatic expansion and contraction device; 51-composite material prepreg patch for repair; 52-hole damage in helicopter skin structure; 11-trachea connector; 12-cylinder; 13-piston; 14-piston sealing ring; 15-cylinder housing; 16-adjustable infrared heating lamp. DETAILED DESCRIPTION

[0035] The method and device for rapid curing of helicopter composite material repair based on temperature compensation are mainly aimed at the deformation problem caused by uneven temperature distribution during the composite material repair process, especially during the curing process. This method and device can improve the repair efficiency and the surface quality after repair by accurately controlling the temperature distribution during the curing process.

[0036] Specifically, this method ensures uniform temperature distribution across the damaged area by monitoring temperature distribution in real time during the curing process and performing temperature compensation based on the monitoring results. The temperature compensation system can flexibly adjust the heating temperature and heating time according to different repair requirements to achieve the best curing effect. By precisely controlling the temperature distribution, deformation problems caused by uneven temperature can be avoided, thereby ensuring that the repaired composite material has good appearance and mechanical properties.

[0037] In addition, this method can also shorten the curing time, improve the repair efficiency and reduce the repair cost. In short, the method and device for rapid curing of helicopter composite material repair based on temperature compensation provide an efficient and reliable solution for the repair of composite materials.

[0038] See also Figure 1-Figure 3 The present application provides a device for rapid curing of helicopter composite repair based on temperature compensation, which includes an adjustable infrared heating temperature compensation system 1, an infrared thermal imaging system 2, a flexible pneumatic telescopic system 3, and a flexible pneumatic adsorption system 4.

[0039] The adjustable infrared heating temperature compensation system 1 includes adjustable infrared heating temperature compensation components 6 arranged in an array, which can be flexibly adjusted according to the shape and area of ​​the composite structure to be repaired to adapt to different situations.

[0040] Among them, the infrared thermal imaging system 2 can realize real-time monitoring of the surface temperature of the material during the repair and curing process, and provide real-time feedback to the adjustable infrared heating temperature compensation system 1 to achieve precise control of the curing temperature.

[0041] The flexible pneumatic telescopic system is composed of an air pressure control device 31 and a pneumatic telescopic device 32, which can realize precise control of the height of the pneumatically controlled telescopic rod to adapt to composite structures of different shapes.

[0042] The flexible pneumatic adsorption system 4 is composed of a flexible suction cup 41 and a vacuum bag 42, which can realize the adsorption of the device on the surface of the composite material to be repaired, and apply pressure to the composite material prepreg patch 51 for repair through the vacuum bag during the curing process;

[0043] Among them, the adjustable infrared heating temperature compensation component 6 mainly includes an air pipe connector 11, a cylinder 12, a piston 13, a piston sealing ring 14, a cylinder housing 15 and an adjustable infrared heating lamp 16, which can realize precise control of the height and heating power of the adjustable infrared heating lamp 66.

[0044] In other embodiments of the present application, a method for rapid curing of helicopter composite repair based on temperature compensation is provided, comprising the following steps:

[0045] (1) Grind the damaged area of ​​the composite component and prepare a composite prepreg patch for repair, and place it on the surface of the damaged area. First, use appropriate tools to grind the damaged area to ensure that the surface is smooth and free of impurities. Then, select a suitable composite prepreg patch and cut it according to the shape and size of the damaged area. Place the cut patch on the surface of the damaged area to ensure that it completely covers the damaged area and fits tightly with the surrounding materials.

[0046] (2) The flexible pneumatic telescopic system is adjusted according to the surface shape of the composite component so that the flexible pneumatic adsorption system can be adsorbed on the surface of the composite component. The flexible pneumatic telescopic system is highly adaptable and can be adjusted according to different surface shapes. By adjusting the various parts of the system, it can be closely fitted to the surface of the composite component, ensuring that the adsorption system can be stably adsorbed on the surface.

[0047] (3) Adjust the flexible pneumatic adsorption system so that the pressure inside the vacuum bag meets the curing requirements. The flexible pneumatic adsorption system adjusts the internal pressure so that the pressure inside the vacuum bag reaches the standard required for curing. By monitoring and adjusting various parameters of the system, ensure that the pressure inside the vacuum bag is always maintained within the appropriate range to meet the requirements of the curing process.

[0048] (4) Input the curing temperature curve into the device and start the adjustable infrared heating temperature compensation system and infrared thermal imaging system. According to the curing requirements of the composite material, set the appropriate temperature curve and input it into the curing device. Turn on the adjustable infrared heating temperature compensation system to ensure uniform temperature distribution during the curing process by adjusting the heating temperature. At the same time, turn on the infrared thermal imaging system to monitor the temperature changes during the curing process in real time to ensure that the temperature is controlled within the predetermined range.

[0049] (5) Start the curing process. After all preparations are completed, start the curing device and start the curing process. The curing process takes a certain amount of time. According to the characteristics of the composite material and the curing requirements, set an appropriate curing time. During the curing process, keep the environment stable to avoid the influence of external factors on the curing process.

[0050] (6) End the curing process and turn off the adjustable infrared heating temperature compensation system, the flexible pneumatic adsorption system and the flexible pneumatic telescopic system in turn. After the curing process is completed, turn off each system in turn to ensure the safe shutdown of the curing device. First, turn off the adjustable infrared heating temperature compensation system to stop heating. Then turn off the flexible pneumatic adsorption system to release the adsorption state. Finally, turn off the flexible pneumatic telescopic system to restore the system to its initial state.

[0051] (7) Complete the repair process. After the curing process is completed, check the curing effect of the composite component to ensure that it has achieved the expected strength and performance. Perform necessary post-processing on the cured component, such as trimming and polishing, to ensure that its surface is smooth and free of defects. Finally, the entire curing process is completed and the repair work of the composite component is successfully completed.

[0052] In other embodiments of the present application, the solutions provided by the present application are as follows:

[0053] (1) The damaged area of ​​the composite component is polished using sandpaper with a grit of P120, and then a carbon fiber / epoxy resin composite prepreg patch with a diameter of 50 mm is prepared for repair and placed on the surface of the damaged area;

[0054] (2) According to the curvature radius of the surface shape of the composite component being 100 mm, the flexible pneumatic telescopic system is adjusted so that the flexible pneumatic adsorption system can be adsorbed on the surface of the composite component;

[0055] (3) Adjust the flexible pneumatic adsorption system so that the pressure inside the vacuum bag reaches 0.85 MPa to meet the curing requirements;

[0056] (4) Input the curing temperature curve into the device. The curing temperature curve is: increase the temperature to 120°C, keep it at this temperature for 2 hours, then increase the temperature to 180°C, and keep it at this temperature for 4 hours.

[0057] (5) Turn on the adjustable infrared heating temperature compensation system and infrared thermal imaging system;

[0058] (6) Start the curing process and use the real-time feedback infrared thermal imaging system to achieve precise regulation of the infrared lamp heating power and accurately control the temperature of the curing process;

[0059] (7) End the curing process and turn off the adjustable infrared heating temperature compensation system, the flexible pneumatic adsorption system and the flexible pneumatic telescopic system in sequence;

[0060] (8) After the repair process is completed, the repaired structure is polished and the repaired composite material component should reach more than 85% of the raw material strength.

[0061] The present application solves the problems of difficult control of curing temperature, low curing efficiency and poor curing quality in the process of adhesive repair of composite materials, realizes rapid curing repair of composite materials and improves the repair quality. The technical means of the present invention are simple and easy to implement, and have outstanding substantial progress compared with the prior art.

[0062] The present invention discloses a method and device for rapid curing of helicopter composite repair based on temperature compensation. The device mainly comprises an adjustable infrared heating temperature compensation system, an infrared thermal imaging system, a flexible pneumatic telescopic system and a flexible pneumatic adsorption system. The device adopts an adjustable infrared heating temperature compensation system and utilizes a high-precision cylinder to achieve precise control of the three-dimensional shape of an infrared heating lamp array, and precise control of the distance between the infrared lamp and the surface of a composite component to be repaired. The real-time feedback infrared thermal imaging system is utilized to achieve precise control of the heating power of the infrared lamp. The difficult problems of difficult control of the curing temperature, low curing efficiency and poor curing quality of composite materials during adhesive repair are solved, and rapid curing repair of composite materials is achieved, thereby improving the repair quality.

Claims

1. A helicopter composite material repair and curing method based on temperature compensation, characterized in that: The method comprises the following steps: Grinding the damaged area of ​​the composite component, preparing a composite prepreg patch for repair, and placing it on the surface of the damaged area; The flexible pneumatic telescopic system is adjusted according to the surface shape of the composite material component so that the flexible pneumatic adsorption system is adsorbed on the surface of the composite material component; Adjust the flexible pneumatic adsorption system so that the pressure inside the vacuum bag meets the curing requirements; Input the curing temperature curve into the device, turn on the adjustable infrared heating temperature compensation system and infrared thermal imaging system, and start curing.

2. The method according to claim 1, characterized in that The method further comprises: When the curing process is finished, the adjustable infrared heating temperature compensation system, the flexible pneumatic adsorption system and the flexible pneumatic telescopic system are turned off in sequence.

3. The method according to claim 2, characterized in that The method of sequentially closing the adjustable infrared heating temperature compensation system, the flexible pneumatic adsorption system and the flexible pneumatic telescopic system includes: First, turn off the adjustable infrared heating temperature compensation system to stop heating; Then the flexible pneumatic adsorption system is turned off to release the adsorption state; Finally, the flexible pneumatic telescopic system is turned off to restore the system to its initial state.

4. The method according to claim 3, characterized in that The method further comprises: After the curing process is completed, check the curing effect of the composite component to ensure that it has achieved the expected strength and performance; Carry out necessary post-processing on the cured components; Finally, the entire curing process was completed and the repair work of the composite material components was successfully completed.

5. The method according to claim 4, characterized in that The necessary post-processing includes trimming and grinding to ensure that the surface is smooth and free of defects.

6. A helicopter composite material repair and curing device based on temperature compensation, characterized in that: The device comprises an adjustable infrared heating temperature compensation system (1), an infrared thermal imaging system (2), a flexible pneumatic telescopic system (3), and a flexible pneumatic adsorption system (4); The adjustable infrared heating temperature compensation system (1) is composed of adjustable infrared heating temperature compensation components (6) arranged in an array, and can be flexibly adjusted according to the shape and area of ​​the composite structure to be repaired to adapt to different situations; The infrared thermal imaging system (2) is used to monitor the surface temperature of the material in real time during the repair and curing process, and to provide real-time feedback to the adjustable infrared heating temperature compensation system (1) to achieve precise control of the curing temperature; The flexible pneumatic telescopic system is composed of a pneumatic control device (31) and a pneumatic telescopic device (32), and can realize precise control of the height of the pneumatically controlled telescopic rod to adapt to composite structures of different shapes; The flexible pneumatic adsorption system (4) is composed of a flexible suction cup (41) and a vacuum bag (42), which can realize adsorption of the device on the surface of the composite material to be repaired, and apply pressure to the composite material prepreg patch (51) for repair through the vacuum bag during the curing process.

7. The device according to claim 6, characterized in that The adjustable infrared heating temperature compensation component (6) comprises an air pipe connector (11), a cylinder (12), a piston (13), a piston sealing ring (14), a cylinder housing (15) and an adjustable infrared heating lamp (16), and can realize precise control of the height and heating power of the adjustable infrared heating lamp (16).

8. The device according to claim 6, characterized in that The repair composite material prepreg patch (51) is a carbon fiber / epoxy resin composite material prepreg patch.

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