Aircraft composite blade leading edge protection boot bonding device and use method thereof

Abstract

The present invention discloses a device for bonding composite blade leading edge protective boots for aircraft. The device comprises a frame base, an airbag assembly, a limiting mechanism, and a fixing strip; the airbag assembly and the limiting mechanism are both mounted on the frame base; the limiting mechanism comprises multiple limiting mechanisms, and the multiple limiting mechanisms are arranged at intervals; the fixing strip is located on the limiting mechanism and above the airbag assembly; the airbag assembly comprises a metal frame and a heat-resistant rubber airbag; a U-shaped groove is provided in the metal frame; and the heat-resistant rubber airbag is mounted on the inner wall of the U-shaped groove. The present invention has the advantages of significantly improving the one-time success rate of bonding protective boots, effectively reducing the consumption of high-priced aircraft equipment. The present invention also discloses a method for using the device for bonding composite blade leading edge protective boots for aircraft.

Description

Technical Field

[0001] The present invention relates to a bonding device for a composite material blade leading edge protection boot of an aircraft, and also relates to a method for using the bonding device for the composite material blade leading edge protection boot of an aircraft. Background Art

[0002] Composite materials are widely used in aviation, particularly in aircraft propulsion systems. The protective boot on the leading edge of composite blades is made of metal. It protects composite blades from wear and erosion, and disperses the force in the event of an impact to protect the main blade structure.

[0003] The replacement method for the blade's leading edge boot varies depending on the manufacturer. Each blade model requires its own tooling, and the corresponding operation is complex, resulting in low tooling utilization and inconvenient operation during actual maintenance. Replacing the blade's leading edge boot is typically done using a vacuum pump, which requires sophisticated equipment and can make minor leaks difficult to detect. Because the vacuum's pressure is limited, undetected leaks can further affect the bonding process, leading to bonding failure and rework, resulting in financial losses.

[0004] Therefore, it is necessary to develop a composite material blade leading edge protection boot bonding device for aircraft that can improve the one-time success rate of protection boot bonding. Summary of the Invention

[0005] The first purpose of the present invention is to provide a composite material blade leading edge protective boot bonding device for aircraft, which can be generally applicable to the bonding needs of most composite material blade leading edge protective boots, while using a lower-cost positive pressure system to reduce costs, and can accommodate general heating equipment, thereby improving equipment utilization and reducing the demand for tooling. The one-time success rate of protective boot bonding is significantly improved, effectively reducing the consumption of high-priced aircraft equipment (the bonding cost of a single product using the existing technology is approximately 1,000 yuan, and the probability of achieving qualification in one time is approximately 30%; the bonding cost of a single product after the improvement using the present invention is approximately 900 yuan, and the probability of achieving qualification in one time is approximately 90%).

[0006] A second object of the present invention is to provide a method for using a device for bonding composite blade leading edge boots of an aircraft.

[0007] In order to achieve the first object of the present invention, the technical solution of the present invention is as follows: a composite material blade leading edge protection boot bonding device for aircraft, characterized by comprising a frame base, an airbag assembly, a limiting mechanism and a fixing strip;

[0008] The airbag assembly and the limiting mechanism are both mounted on the frame base;

[0009] There are multiple limiting mechanisms, and the multiple limiting mechanisms are arranged at intervals;

[0010] The fixing strip is located on the limiting mechanism and above the airbag assembly;

[0011] The airbag assembly includes a metal frame and a temperature-resistant rubber airbag;

[0012] A U-shaped groove is arranged in the metal frame; and a heat-resistant rubber airbag is installed on the inner wall of the U-shaped groove.

[0013] In the above technical solution, casters are provided at the lower end of the frame base; and a braking device is provided on the casters.

[0014] In the above technical solution, the limiting mechanism includes a longitudinal limiting structure and a transverse limiting structure; the longitudinal limiting structure is installed on the frame base;

[0015] The transverse limiting structure is vertically mounted on two longitudinal limiting structures that are spaced apart;

[0016] The fixing strip is installed on the transverse limiting structure.

[0017] In the above technical solution, a fixing seat is provided at the upper end of the frame base; the metal frame is installed in the middle of the fixing seat;

[0018] Two longitudinal limiting structures arranged at intervals are respectively installed on both sides of the fixing seat.

[0019] In the above technical solution, the longitudinal limiting structure is a telescopic screw; the fixed end of the longitudinal limiting structure is installed on the side end of the fixing seat, and the telescopic end is connected to the transverse limiting structure.

[0020] In the above technical solution, the fixing bar has a U-shaped structure; the fixing bar is located directly above the U-shaped groove; and the fixing bar and the U-shaped groove are arranged opposite to each other.

[0021] In order to achieve the second object of the present invention, the technical solution of the present invention is: a method for using the composite material blade leading edge protection boot bonding device for aircraft, characterized in that it includes the following steps:

[0022] Step 1: Place the aircraft composite blade leading edge boot bonding equipment in the work area, fix the casters on the frame base, and remove the limit mechanism and fixing strips;

[0023] Step 2: Install the new blade leading edge boot on the propeller according to the blade maintenance technical requirements, seal the blade leading edge boot area with an isolation film, and then install a fixed heating device outside the isolation film.

[0024] Step 3: Install the encapsulated blade into the aircraft's composite blade leading edge boot bonding equipment, with the blade leading edge boot facing the airbag assembly and the blade trailing edge facing upward. The blade leading edge boot to be bonded is completely within the coverage area of ​​the airbag assembly.

[0025] Step 4: Install the fixing strip on the trailing edge of the propeller blade, and then use the limit mechanism to secure the trailing edge of the propeller blade. The propeller blade is securely in place when it cannot move up or down.

[0026] Step 5: Connect the compressed air source to the airbag assembly through the pressure control device and connect it to the controller of the heating device. Check to make sure the connection is secure.

[0027] Step 6: Based on bonding requirements, apply 300-400 kPa of air pressure to the airbag assembly to inflate the heat-resistant rubber airbag. This evenly transmits the extrusion force to the blade leading edge boot, ensuring a tight fit between the boot and the blade.

[0028] Step 7: Check the bonding equipment for the composite blade leading edge boots to see if there are any leaks. Confirm again that the blade leading edge boots are completely enclosed in the airbag assembly. Then, turn on the heating device and set the heating temperature and time according to the adhesive curing requirements.

[0029] Step 8: Check and confirm the airbag pressure and heating temperature every 15 minutes before the adhesive is completely cured to ensure that the pressure and temperature meet the requirements for the blade leading edge protection shoe connection;

[0030] Step 9: When the preset adhesive curing time is reached, first stop and disconnect the external control component of the heating device, then release the pressure in the airbag component to ambient pressure through the pressure control device, and finally disconnect the air source and pressure control device on the airbag component;

[0031] Step 10: Disassemble the limit mechanism, remove the fixing strip, and remove the propeller from the airbag assembly;

[0032] Step 11: Inspect the airbag assembly, clean any debris from the U-shaped groove of the metal frame, clean the aircraft's composite blade leading edge protection boot bonding equipment, and store the aircraft's composite blade leading edge protection boot bonding equipment as required.

[0033] The composite material in the present invention is glass fiber and carbon fiber.

[0034] The beneficial effects of the present invention are:

[0035] (1) The equipment described in the present invention is universally applicable to the bonding needs of most composite blade leading edge boots. It utilizes a lower-cost positive pressure system and can accommodate common heating equipment, thereby improving equipment utilization and reducing tooling requirements. Compared to traditional vacuum operation methods, the one-time success rate of boot bonding is significantly improved, effectively reducing the consumption of expensive aircraft equipment.

[0036] (2) The present invention can be applied to the repair needs of composite blade leading edge protective boots of various models of aircraft, and realize efficient replacement of protective boots. The equipment used in the present invention can adapt to the shape of most existing blades, and the compressed gas filling equipment can apply positive pressure to the blade, so that the protective boot of the leading edge of the blade to be installed can fit tightly with the blade. Compared with the vacuum method, the use of positive pressure compressed gas is easier to achieve the requirements for gas source equipment, and is more economical. At the same time, it can provide a greater force than vacuuming, and can effectively eliminate the "empty bag" generated on the bonding surface during the bonding process, thereby improving the efficiency of the bonding operation. The present invention can accurately control the bonding force and the curing temperature of the adhesive through the temperature and pressure control system matched with the equipment, effectively avoiding the unfavorable factors of the original operation method, improving the utilization rate of the tooling, and adapting to the replacement of protective boots on the leading edge of various models of blades. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 The figure is a schematic structural diagram of the bonding device for the composite material blade leading edge protection boot of the aircraft according to the present invention.

[0038] Figure 2 This is a schematic diagram of the main structure of the airbag assembly in the present invention.

[0039] exist Figure 2 In the figure, M stands for adhesive and N stands for binding.

[0040] In the figure, A-frame base, B-airbag assembly, C-limiting mechanism, D-fixing bar, 1-metal frame, 2-heat-resistant rubber airbag, 3-castor, 4-brake device, 5-U-shaped groove, 6-fixing seat, 7-longitudinal limiting structure, 8-lateral limiting structure, 9-paddle, 10-isolating membrane, 11-heating device. DETAILED DESCRIPTION

[0041] The following detailed description of the embodiments of the present invention is given in conjunction with the accompanying drawings, which do not limit the present invention but are merely examples. The description makes the advantages of the present invention clearer and easier to understand.

[0042] The present invention is based on a frame base with casters, on which an airbag assembly and a limiting mechanism are fixedly installed. The U-shaped groove of the metal frame can accommodate the blades, and the sac formed by the rubber membrane is used to accommodate compressed gas. The pressure of the compressed gas acts on the rubber membrane of the airbag to cause deformation, thereby generating an extrusion force on the blades installed thereon. Because the pressure of the compressed gas is uniform in the airbag, the area covered by the rubber membrane of the airbag can generate a uniform extrusion force. When bonding the blade protective boot, it is necessary to uniformly fit it tightly to the base shape of the composite blade. At the same time, during the pressurization process, the bubbles generated when the protective boot is installed can be effectively discharged during the process of gradually increasing pressure. The important basis for judging whether the bonding of the blade leading edge protective boot is qualified is how large the total empty area is under the protective boot. The ideal state is that there is no empty bag or the empty bag is extremely small and very few. After the propeller blade to be repaired is placed in the airbag assembly, the fixing strip and the frame-type limiting mechanism need to work together to ensure that the propeller blade is always within the working area of ​​the airbag assembly when the airbag assembly is inflated. The frame-type limiting mechanism can disperse the extrusion force transmitted from the protective strip, so that the trailing edge of the blade is evenly stressed, and cooperate with the fixing strip to further disperse the force on the trailing edge of the blade, thereby protecting the trailing edge of the blade from damage.

[0043] By counting the external dimensions and external distortion of helicopter rotor blades, helicopter tail rotor blades, and propeller blades made of various types of composite materials, and taking into account a certain degree of scalability, the designed airbag assembly can adapt to various types of blades; the frame-type limiting mechanism reserves sufficient adjustment range to meet the fixing needs of blades of various widths; the matching fixing strip can accommodate the twisted trailing edge of the blade and provide good protection.

[0044] The airbag assembly of the present invention has a reserved standard interface, which can be easily and quickly connected to universal air source equipment and control devices. The U-shaped groove space of the airbag assembly is sufficient. At the same time, the selected temperature-resistant rubber can meet the curing temperature requirements for the viscose, and allows standard heating control equipment to be installed together with the blades.

[0045] The current technology for the bonding repair of composite blade leading edge boots mainly relies on vacuuming and normal pressure fixing. The vacuum bonding method is suitable for small-scale repairs. After the length exceeds 500mm, the bonding defect rate and cost will increase. This is because as the size of the bonded part increases, the number of consumables for making vacuum bags will increase exponentially. In addition, due to the increase in vacuum area, the uniformity of pressure decreases, which will cause the shape of the protective boot after molding to not meet the requirements. In addition, the residual air in the bonding area after large-area glue coating cannot be effectively discharged, resulting in failure to pass the tapping inspection after bonding, and the inspection pass rate after bonding is less than 30%. In addition, the bonding area applicable to normal pressure fixing bonding is smaller than the bonding area of ​​the vacuum method, and its scope of application is very limited (it cannot be applied to composite material (such as glass fiber, carbon fiber) blade leading edge boots (bonding)), and its scope of use is limited. The present invention uses an airbag plus positive pressure method for bonding. The applied positive pressure is much greater than the pressure formed by evacuation, and the airbag can make the bonded protective boots evenly pressurized. The appearance quality after bonding is stable and high. In addition, the positive pressure can effectively squeeze out excess glue, and most of the air can be taken out at the same time as the excess glue. In this way, the inspection pass rate after bonding can reach more than 90%, and it has strong applicability (suitable for composite materials (such as glass fiber, carbon fiber, etc.) blade leading edge protective boots (bonding)).

[0046] Referring to the accompanying drawings, a composite material blade leading edge boot bonding device for an aircraft is characterized by comprising a frame base A, an airbag assembly B, a limiting mechanism C, and a fixing bar D. The frame base provides support for the entire device; the airbag assembly generates uniform pressing force during bonding of the composite material blade leading edge boot; the limiting mechanism and fixing bar securely secure the blade to prevent it from being squeezed out during bonding, and the fixing bar also provides protection; a reasonable and effective bonding operation procedure is formulated based on the characteristics of the bonding device to ensure that the bonding operation can be completed correctly;

[0047] The airbag assembly B and the limiting mechanism C are both installed on the frame base A;

[0048] There are multiple limiting mechanisms C, and the multiple limiting mechanisms C are arranged at intervals;

[0049] The fixing strip D is located on the limiting mechanism C and above the airbag assembly B;

[0050] The airbag assembly B includes a metal frame 1 and a heat-resistant rubber airbag 2;

[0051] A U-shaped groove 5 is provided in the metal frame 1; a heat-resistant rubber airbag 2 is installed on the inner wall of the U-shaped groove 5; the present invention realizes that the composite blade leading edge protection boot generates uniform pressing force when being bonded by the airbag assembly, the airbag assembly can accommodate the composite blade and the heating device, the airbag made of heat-resistant rubber can withstand high temperature during heating, the airbag pressure comes from compressed gas, the airbag can withstand up to 1.5 times the working pressure without failure, and can generate uniform deformation after inflation, and the uniform deformation generates uniform force, which acts evenly on the protection boot, so that the blade protection boot can fit closely with the base shape of the composite blade when being bonded.

[0052] Furthermore, a caster 3 is provided at the lower end of the frame base A; a brake device 4 is provided on the caster 3; the frame base provides support for the entire equipment and can bear the weight of various types of composite material blades. The casters of the frame base can make the frame base flexibly moved, and the brake device 4 limits the caster 3.

[0053] Furthermore, the limiting mechanism C includes a longitudinal limiting structure 7 and a transverse limiting structure 8; the longitudinal limiting structure 7 is mounted on the frame base A;

[0054] The transverse limiting structure 8 is vertically mounted on two longitudinal limiting structures 7 that are spaced apart;

[0055] The fixing strip D is mounted on the transverse limiting structure 8. The present invention forms a blade fixing device by the limiting mechanism and the fixing strip, so that the blade can be stable and immobile during the inflation of the airbag assembly, and at the same time can disperse the pressure on the blade and protect the trailing edge of the blade from damage.

[0056] Furthermore, a fixing seat 6 is provided at the upper end of the frame base A; the metal frame 1 is installed in the middle of the fixing seat 6;

[0057] Two longitudinal limiting structures 7 are spaced apart and installed on both sides of the fixing seat 6 respectively.

[0058] Furthermore, the longitudinal limiting structure 7 is a telescopic screw; the fixed end of the longitudinal limiting structure 7 is installed on the side end of the fixing seat 6, and the telescopic end is connected to the transverse limiting structure 8. The longitudinal limiting structure 7 can be telescopic to increase or decrease the size, thereby improving the utilization rate of the tooling and adapting to the replacement of protective boots on the leading edges of various models of blades.

[0059] Furthermore, the fixing bar D has a U-shaped structure; the fixing bar D is located directly above the U-shaped groove 5; the fixing bar D and the U-shaped groove 5 are arranged opposite to each other (ie, the opening direction of the fixing bar D is opposite to the opening direction of the U-shaped groove 5).

[0060] Referring to the accompanying drawings, it can be seen that the method for using the composite material blade leading edge protection boot bonding device for aircraft is characterized by comprising the following steps:

[0061] Step 1: Place the aircraft composite blade leading edge boot bonding equipment in the work area, fix the caster 3 on the frame base A, and remove the limit mechanism C and fixing bar D;

[0062] Step 2: Install a new blade leading edge boot onto the blade 9 according to the blade maintenance technical requirements, seal the blade leading edge boot area with an isolation film 10, and then install a fixed heating device 11 outside the isolation film 10;

[0063] Step 3: Install the encapsulated blade into the aircraft's composite blade leading edge boot bonding equipment, with the blade leading edge boot facing airbag assembly B and the blade trailing edge facing upward. The blade leading edge boot to be bonded must be completely within the coverage area of ​​airbag assembly B.

[0064] Step 4: Install fixing strip D on the trailing edge of the propeller blade, and then use limiter C to secure the trailing edge of the propeller blade. The propeller blade is securely in place when it cannot move up or down.

[0065] Step 5: Connect the compressed air or nitrogen source to the airbag assembly B through the pressure control device, and connect it to the controller of the heating device 11, and check to make sure the connection is stable;

[0066] Step 6: Based on bonding requirements, apply 300-400 kPa of air pressure to airbag assembly B to inflate the heat-resistant rubber airbag 2. This evenly transmits the extrusion force generated by the heat-resistant rubber airbag 2 to the blade leading edge boot, ensuring a tight fit between the boot and the blade.

[0067] Step 7: Check the bonding equipment of the composite blade leading edge boot of the aircraft for air leakage, confirm again that the blade leading edge boot is completely wrapped in the airbag assembly B, then turn on the external control component of the heating device 11, and set the heating temperature and heating time according to the adhesive curing requirements;

[0068] Step 8: Check and confirm the airbag pressure and heating temperature every 15 minutes before the adhesive is completely cured to ensure that the pressure and temperature meet the requirements for the blade leading edge protection shoe connection;

[0069] Step 9: When the preset adhesive curing time is reached, the external control component of the heating device 11 is first stopped and disconnected, and the pressure in the airbag component B is then released to ambient pressure through the pressure control device. Finally, the air source and pressure control device on the airbag component B are disconnected;

[0070] Step 10: Disassemble the limit mechanism C, remove the fixing strip D, and remove the propeller from the airbag assembly B;

[0071] Step 11: Check the airbag assembly B, clean the residue in the U-shaped groove 5 of the metal frame 1, clean the aircraft's composite blade leading edge protection boot bonding equipment, and store the aircraft's composite blade leading edge protection boot bonding equipment as required.

[0072] The bonding operation procedure formulated by the present invention based on the characteristics of the bonding equipment ensures that the bonding operation of the composite material blade leading edge protection boot of the aircraft can be correctly completed, thereby reducing blade damage and bonding defects.

[0073] Other parts not described belong to the prior art.

Claims

1. A method for using a bonding device for composite blade leading edge boots of aircraft, characterized by: The composite material blade leading edge protection boot bonding device for an aircraft comprises a frame base (A), an airbag assembly (B), a limiting mechanism (C) and a fixing strip (D); The airbag assembly (B) and the limiting mechanism (C) are both mounted on the frame base (A); The limiting mechanism (C) has multiple limiting mechanisms (C) arranged at intervals; The fixing strip (D) is located on the limiting mechanism (C) and above the airbag assembly (B); The airbag assembly (B) comprises a metal frame (1) and a heat-resistant rubber airbag (2); A U-shaped groove (5) is provided in the metal frame (1); a heat-resistant rubber airbag (2) is installed on the inner wall of the U-shaped groove (5); A caster (3) is provided at the lower end of the frame base (A); The limiting mechanism (C) includes a longitudinal limiting structure (7) and a transverse limiting structure (8); the longitudinal limiting structure (7) is installed on the frame base (A); The transverse limiting structure (8) is vertically mounted on two longitudinal limiting structures (7) spaced apart; the fixing strip (D) is mounted on the transverse limiting structure (8); A fixing seat (6) is provided at the upper end of the frame base (A); the metal frame (1) is installed in the middle of the fixing seat (6); The longitudinal limiting structure (7) is a telescopic screw; the fixed end of the longitudinal limiting structure (7) is installed on the side end of the fixed seat (6), and the telescopic end is connected to the transverse limiting structure (8); The fixing strip (D) is in a U-shaped structure; the fixing strip (D) is located directly above the U-shaped groove (5); the fixing strip (D) and the U-shaped groove (5) are arranged opposite to each other; The isolation film (10) encapsulates the blade leading edge protection boot area, and then a fixed heating device (11) is installed outside the isolation film (10); The blade leading edge boot faces the airbag assembly (B), and the blade trailing edge faces upward. The blade leading edge boot that needs to be bonded is entirely within the coverage area of ​​the airbag assembly (B). The isolation film (10) is located between the heating device (11) and the blade leading edge protection boot to be bonded, and the blade leading edge protection boot to be bonded is entirely within the coverage area of ​​the isolation film (10); The method of use comprises the following steps: Step 1: Place the aircraft composite blade leading edge protection boot bonding equipment in the work area, fix the caster (3) of the frame base (A), and remove the limit mechanism (C) and the fixing strip (D); Step 2: Install a new blade leading edge protection boot onto the blade (9) according to the blade maintenance technical requirements, encapsulate the blade leading edge protection boot area with an isolation film (10), and then install a fixed heating device (11) outside the isolation film (10); Step 3: Install the encapsulated blade into the aircraft's composite blade leading edge boot bonding equipment, with the blade leading edge boot facing the airbag assembly (B) and the blade trailing edge facing upward. The entire blade leading edge boot to be bonded is within the coverage area of ​​the airbag assembly (B). Step 4: Install the retaining bar (D) on the trailing edge of the propeller blade, and then secure the trailing edge of the propeller blade with the stopper (C). The propeller blade is securely in place when it cannot move up or down. Step 5: Connect the compressed air source to the airbag assembly (B) through the pressure control device and connect it to the controller of the heating device (11), and check to make sure the connection is stable; Step 6: According to the bonding requirements, input 300-400 kPa of air pressure into the airbag assembly (B) to inflate the heat-resistant rubber airbag (2) in the airbag assembly (B). At this time, the extrusion force generated by the heat-resistant rubber airbag (2) will be evenly transmitted to the blade leading edge protection boot, so that the leading edge protection boot and the blade can fit tightly together; Step 7: Check whether there is any leakage in the bonding equipment of the composite blade leading edge protection boot of the aircraft, confirm again that the blade leading edge protection boot is completely wrapped in the airbag component (B), and then turn on the external control component of the heating device (11), and set the heating temperature and heating time according to the adhesive curing requirements; Step 8: Check and confirm the airbag pressure and heating temperature every 15 minutes before the adhesive is completely cured to ensure that the pressure and temperature meet the requirements for the blade leading edge protection shoe connection; Step 9: When the preset adhesive curing time is reached, the external control component of the heating device (11) is first stopped and disconnected, and then the pressure in the airbag component (B) is released to the ambient pressure through the pressure control device, and finally the air source and pressure control device on the airbag component (B) are disconnected; Step 10: Disassemble the stopper (C), remove the fixing strip (D), and remove the propeller from the airbag assembly (B). Step 11: Check the airbag assembly (B), clean the residue in the U-shaped groove (5) of the metal frame (1), clean the aircraft's composite blade leading edge protection boot bonding equipment, and store the aircraft's composite blade leading edge protection boot bonding equipment as required.

2. The method for using the composite material blade leading edge boot bonding device for aircraft according to claim 1, characterized in that: A brake device (4) is provided on the caster (3).

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