Aircraft part stretch bending machining process and equipment
By designing adjustable clamping components, the problem of insufficient clamping adaptability of aircraft parts bending processing equipment in the prior art is solved, and tight clamping and high-precision machining of parts of different shapes is achieved.
Patent Information
- Application Number
- CN202510022413.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-07
- Publication Date
- 2025-03-14
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
The clamping adaptability of existing aircraft parts bending processing equipment is insufficient, making it difficult to adapt to aircraft parts of different sizes and complex shapes, resulting in machining accuracy and safety issues.
A clamping assembly including positioning members and model parts is designed. The positioning members are equipped with multiple model parts. The model parts can adjust the internal structure of the positioning members in real time according to changes in the shape of the part to achieve tight clamping of parts of different shapes.
It improves the positioning accuracy of aircraft parts before bending processing, reduces processing errors, enhances the equipment's compatibility with aircraft parts of different shapes, and ensures efficient and high-precision bending processing.
Smart Images
Figure CN119608995A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of aviation aircraft sheet metal parts processing, in particular to a stretch bending processing technology and equipment for aircraft parts. Background Art
[0002] With the continuous advancement of aviation technology, the performance requirements of aircraft are increasing. Modern aircraft need to have higher flight speeds, longer ranges and greater carrying capacity. This requires aircraft parts to have higher precision and more complex shapes to meet the requirements of aerodynamics and structural strength. Stretch-bending equipment came into being to manufacture aircraft parts with complex shapes and extremely high precision requirements, such as the leading edge, trailing edge, and fuselage frame of the wing. For example, the wing shape of an advanced fighter jet has a complex contour curve in order to achieve better stealth performance and high lift characteristics. Traditional processing methods are difficult to meet the requirements. Stretch-bending equipment can accurately process parts into shapes that meet the design.
[0003] At present, aircraft parts stretching and bending processing equipment usually needs to apply tension to the parts through a stretching system to put the parts in a stretched state. The bending mold in the bending system is driven by a rotary drive mechanism to rotate at a set speed and angle, so that the parts fit the mold contour under the action of tension to achieve bending deformation. At the same time, the fixture system is positioned according to the geometric features of the parts and firmly fixes the parts through multi-point clamping with adjustable clamping force. Each system works together under the coordination of the control system to accurately complete the stretching and bending processing of aircraft parts.
[0004] During the stretch and bending process of aircraft parts, when faced with aircraft parts of different sizes, the clamping adaptability of the equipment is insufficient; traditional clamping devices are often designed based on a specific part size range and lack sufficient flexibility; for example, for some smaller and more complex aircraft connectors, the existing clamping components are not convenient for accurately positioning and fixing the parts, resulting in easy displacement of the parts during the stretch and bending process, which in turn affects the processing accuracy; for larger aircraft frame parts, the clamping device may not be able to provide uniform and stable clamping force, causing the parts to be subjected to excessive local force during the force-bearing process, with the risk of deformation or even damage.
[0005] In view of this, we propose a stretch-bending process and equipment for aircraft parts. Summary of the invention
[0006] The purpose of the present invention is to provide a stretch bending process and equipment for aircraft parts to solve the problems raised in the above background technology.
[0007] To achieve the above-mentioned object, one of the objects of the present invention is to provide an aircraft parts bending processing equipment, comprising a bracket, wherein a rotating block is provided near both ends of the bracket, and the ends of the rotating block are fixedly connected to a base, a bending component is provided on the top of the bracket, and a clamping component is provided on the top of the base;
[0008] The clamping assembly includes a positioning member and a model member, wherein two positioning members are symmetrically arranged on the top of two bases, a plurality of model members are arranged inside the positioning member, and an aircraft part is arranged between the two model members;
[0009] The positioning member is used to drive multiple model parts to approach the two ends of the aircraft part. The model parts are used to form a shape consistent with the end shape of the aircraft part inside the positioning member. The positioning member and the model parts are used to clamp and fix aircraft parts of different shapes.
[0010] As a further improvement of the present technical solution, the positioning member includes a cylinder, which is fixedly connected to the top of the base, the end of the cylinder piston rod is fixedly connected to a mold, the inside of the mold is fixedly connected to a support plate, and a plurality of model parts are arranged between the mold and the inside of the support plate.
[0011] As a further improvement of the technical solution, the model part includes a sleeve, an elastic part is fixedly connected to the inner wall of the sleeve near the end, and the other end of the elastic part is fixedly connected to the outer wall of the support plate.
[0012] As a further improvement of the technical solution, the end of the inner wall of the sleeve is fixedly connected to a support rod, the support rod is movably connected to the inside of the support plate, the elastic member is wrapped around the outer wall of the support rod, and the other end of the support rod passing through the support plate is fixedly connected to a blocking block.
[0013] As a further improvement of the technical solution, the sleeve is made of sponge material, and the sleeve is movably connected between the support plate and the inside of the mold.
[0014] As a further improvement of the present technical solution, the bending assembly includes a slide rail, which is fixedly connected to the top of the bracket. A pillar is fixedly connected to the top of the slide rail near the center. A dual-axis motor is provided on the top of the pillar, and the output shafts of the dual-axis motor on the top of the pillar are fixedly connected with screws.
[0015] As a further improvement of the technical solution, the outer wall of the screw is threadedly connected to a support block, the bottom of the support block is fixedly connected to a slider, the slider is slidably connected to the outer wall of the slide rail, and the outer wall of the slider is cylindrical.
[0016] The second object of the present invention is to provide a process for operating an aircraft parts stretch bending processing device including any one of the above, comprising the following method steps:
[0017] S1. Parts preparation: Before the bending process, the aircraft parts are fully inspected and impurities such as oil, dust and oxide layer on the surface of the parts are removed;
[0018] S2. Positioning and clamping: according to the shape and size of the parts, multiple model parts are formed into matching shapes inside the positioning parts, and the positioning parts are used to drive multiple model parts to clamp and fix the parts;
[0019] S3, Bending positioning: By adjusting the length of the bending component, the bending position is determined according to the material, shape and bending requirements of the part;
[0020] S4, bending: starting the rotary drive mechanism to drive the rotating block to rotate inside the bracket, so that the rotating block drives the base to rotate, and the parts between the two bases are bent;
[0021] S5. Post-forming processing: After stretching and bending, use precision measuring equipment such as a three-coordinate measuring machine to check the dimensional accuracy of the parts, and check whether there are scratches, wear, deformation and other quality problems on the surface of the parts.
[0022] Compared with the prior art, the present invention has the following beneficial effects:
[0023] 1. In the aircraft parts bending process and equipment, the parts are placed in a specific area between two positioning parts. At this time, the model parts equipped inside the positioning parts can instantly receive the pressure applied by the shape of the parts. When the parts contact the model parts, due to the irregularity and diversity of the shapes of the parts, the model parts will change the internal structural area of the positioning parts according to the force distribution of the contact points and the change information of the part contour;
[0024] 2. In the aircraft parts stretch-bending processing technology and equipment, the internal space of the positioning piece is appropriately expanded at the raised part of the part to avoid excessive squeezing of the part; while in the recessed or narrow area of the part, the positioning piece is precisely contracted to ensure a tight fit; in this way, no matter whether the part has a smooth arc contour or has sharp turns and complex concave-convex structures, it can be completely and tightly clamped and fit inside the positioning piece; this high adaptability not only greatly improves the positioning accuracy of the parts before stretch-bending processing, reduces the processing errors caused by inaccurate positioning, but also significantly improves the compatibility of the equipment with aircraft parts of different shapes, effectively shortens the processing preparation time, and lays the foundation for the efficient and high-precision stretch-bending processing of aircraft parts. BRIEF DESCRIPTION OF THE DRAWINGS
[0025] Figure 1 It is a schematic diagram of the overall structure of the present invention;
[0026] Figure 2It is a schematic diagram of the bending state structure of the present invention;
[0027] Figure 3 It is a schematic diagram of the structure of the clamping assembly of the present invention;
[0028] Figure 4 It is a schematic diagram of the positioning member structure of the present invention;
[0029] Figure 5 It is a schematic diagram of the internal structure of the clamp box of the present invention;
[0030] Figure 6 It is a schematic diagram of the structure of the model of the present invention;
[0031] Figure 7 It is a schematic diagram of the structure of the bending component of the present invention.
[0032] The meaning of each number in the figure is:
[0033] 1. bracket; 11. base; 110. rotating block;
[0034] 12. bending assembly; 120. slide rail; 121. pillar; 122. slider; 123. screw rod; 124. support block;
[0035] 13. Clamping assembly; 130. Positioning member; 1300. Support plate; 1301. Cylinder; 1302. Mould; 131. Model member; 1310. Sleeve; 1311. Support rod; 1312. Elastic member; 1313. Block. DETAILED DESCRIPTION
[0036] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.
[0037] Example 1: Please refer to Figure 1-Figure 7 As shown, the purpose of this embodiment is to provide an aircraft parts bending processing equipment, including a bracket 1, a rotating block 110 is provided near both ends of the bracket 1, the ends of the rotating block 110 are fixedly connected to a base 11, a bending component 12 is provided on the top of the bracket 1, and a clamping component 13 is provided on the top of the base 11;
[0038] The clamping assembly 13 includes a positioning member 130 and a model member 131. The two positioning members 130 are symmetrically arranged on the top of the two bases 11. A plurality of model members 131 are arranged inside the positioning member 130. An aircraft part is arranged between the two model members 131.
[0039] The positioning member 130 is used to drive multiple model members 131 to approach the two ends of the aircraft part. The model members 131 are used to form a shape consistent with the end shape of the aircraft part inside the positioning member 130. The positioning member 130 and the model members 131 are used to clamp and fix aircraft parts of different shapes.
[0040] The improvement of this embodiment is that: in the key process of the aircraft part bending process, the parts are placed in specific areas inside the two positioning members 130; when the model member 131 provided inside the positioning member 130 contacts the parts, the model member 131 can immediately sense the pressure exerted by the shape of the parts; in view of the complex and varied shapes of the parts, the contours may be smooth arcs, or have sharp turns, or be covered with complex concave and convex structures, the model member 131 can quickly drive the internal structure of the positioning member 130 to make adaptive adjustments based on the force distribution details of the contact points and the dynamic change data of the contours, and accurately change the internal space area;
[0041] Furthermore, when encountering a part with a protrusion, the internal space of the positioning member 130 will be appropriately extended and expanded to wrap the protruding part of the part, effectively avoiding the risk of damage to the part caused by excessive extrusion; and when facing a recessed or narrow area of the part, the positioning member 130 will shrink its internal space to fit tightly with the recessed and narrow parts of the part; no matter how complex and diverse the shape of the part is, it can be perfectly and firmly clamped inside the positioning member 130, greatly improving the positioning accuracy of the part before the bending process, and effectively reducing the processing error caused by positioning deviation; expanding the adaptation scope of the equipment to various shapes of aircraft parts, and comprehensively improving the versatility of the equipment.
[0042] First, the specific structure of the positioning member 130 is disclosed. The positioning member 130 includes a cylinder 1301, which is fixedly connected to the top of the base 11. The end of the piston rod of the cylinder 1301 is fixedly connected to a mold 1302. The inside of the mold 1302 is fixedly connected to a support plate 1300. A plurality of model parts 131 are arranged between the mold 1302 and the inside of the support plate 1300.
[0043] See also Figure 3 and Figure 4 As shown, when the aircraft part is placed on the top of the bracket and located between the two molds 1302, the mold 1302 is pushed toward the two ends of the aircraft part by the piston rod of the cylinder 1301. When the end of the aircraft part enters the mold 1302, the model part 131 inside the mold 1302 is pushed to slide and shrink inside the support plate 1300 along with the shape of the aircraft part. Thus, according to the changes of the multiple model parts 131, the shape of the inside of the mold 1302 is changed, so that the mold 1302 matches the shape of the aircraft part, and it is convenient for aircraft parts of various shapes to be clamped between the two molds 1302.
[0044] Next, the specific structure of the model part 131 is disclosed. The model part 131 includes a sleeve 1310. An elastic member 1312 is fixedly connected to the inner wall of the sleeve 1310 near the end. The other end of the elastic member 1312 is fixedly connected to the outer wall of the support plate 1300. A support rod 1311 is fixedly connected to the end of the inner wall of the sleeve 1310. The support rod 1311 is movably connected to the inside of the support plate 1300. The elastic member 1312 is wound around the outer wall of the support rod 1311. The other end of the support rod 1311 passing through the support plate 1300 is fixedly connected to a blocking block 1313.
[0045] See also Figure 5 and Figure 6 As shown, when the aircraft part enters the mold 1302, as the cylinder 1301 drives the mold 1302 to continuously move toward the end of the aircraft part, the aircraft part applies pressure to the multiple sleeves 1310 inside the mold 1302; the multiple sleeves 1310 adaptably move inside the support plate 1300 according to the shape of the end of the aircraft part, and the movement of the sleeves 1310 drives the support rods 1311 to move inside the support plate 1300, and the support rods 1311 provide stability support for the movement of the sleeves 1310, and at the same time, under the movement of the sleeves 1310, the elastic member 1311 between the sleeves 1310 and the support plate 1300 is compressed; and the mold 13 The sleeves 1310 that are not in contact with the aircraft parts in the mold 1302 remain stationary, so that the multiple sleeves 1310 form corresponding shapes inside the mold 1302 along with the shape of the aircraft parts, which can more completely clamp and wrap the ends of the aircraft parts, so that they fit tightly with various parts of the ends of the aircraft parts; this tight fit not only greatly improves the stability and reliability of clamping, effectively prevents the aircraft parts from displacement, shaking or loosening during the subsequent stretch-bending process, but also ensures that the stretch-bending force can act evenly and accurately on various parts of the parts, thus laying a solid foundation for obtaining high-precision, high-quality stretch-bending parts;
[0046] When the stretching and bending work is completed, the mold 1302 is moved by the piston rod of the cylinder 1301, and the mold 1302 is moved out from the end of the aircraft part, so that the sleeve 1310 in the compressed state is affected by the rebound force of the elastic member 1312, driving the support rod 1311 to move inside the support plate 1300, and the sleeve 1310 is reset and rebounded to the end of the mold 1302. The moving distance of the support rod 1312 is limited by the block 1313, and the parallel position between the multiple support rods 1311 and the sleeve 1310 is maintained, so that when the next aircraft part is clamped, it can adapt to aircraft parts of other shapes.
[0047] The sleeve 1310 is made of sponge material, and is movably connected between the support plate 1300 and the inside of the mold 1302. According to the properties of the sponge material, its working principle is known to those skilled in the art. The sponge material has a complex and rich pore structure, and these pores are intertwined and connected to form a unique microscopic space system. When the aircraft parts are introduced into the sleeve 1310 assisted by the sponge material, the initial contact moment triggers a series of subtle interactions.
[0048] In terms of pressure transmission, due to the pore structure of the sponge, when the clamping force is applied to the sponge, the pressure is not directly and rigidly transmitted to the aircraft parts as on rigid materials; on the contrary, the pores of the sponge are like countless tiny buffer chambers, and the external force first acts on the solid skeleton of the sponge. These skeletons undergo elastic deformation when subjected to force, and partially store the energy as elastic potential energy; at the same time, the pressure will compress the air in the pores, and the air molecules will collide and rub against each other in a small space, thereby converting part of the energy into heat energy and dissipating it; this multi-form energy conversion and dispersion mechanism effectively reduces the pressure intensity and impact transmitted to the aircraft parts; for example, for some thin-walled aircraft parts or parts with extremely high surface precision requirements, this buffering effect can prevent indentations and depressions on the surface of the parts or damage to the internal microstructure of the material due to excessive clamping force at the moment;
[0049] In the shape adaptation process, the softness and plasticity of the sponge play a key role; the shapes of aircraft parts are often complex and diverse, and may have various curvature changes, edges and corners, and concave and convex structures; the sponge, with its own soft texture, can deform accordingly according to the contour characteristics of the parts when it contacts the parts; in the convex parts of the parts, the sponge will be squeezed and extended to the surroundings to fill the surrounding space; in the concave parts, the sponge will sink into them to a certain extent and fit the shape of the parts tightly; this process is not disordered, but is achieved under the synergistic effect of the skeleton and pore structure inside the sponge; the connection method between the skeletons and the distribution law of the pores enable the sponge to maintain a certain integrity and stability during the deformation process, thereby continuously and stably providing support and wrapping for the parts; this adaptive shape characteristic ensures that the parts are always in a uniform and stable clamping state during the entire stretching and bending process, and there will be no problems such as local uneven force, looseness or displacement due to the mismatch between the clamping part and the part shape, which effectively guarantees the accuracy and quality of the stretching and bending process;
[0050] Furthermore, the sponge material also has good damping properties. During the stretching and bending process, if there is external vibration or slight shaking caused by equipment operation, the sponge can effectively absorb and dissipate the vibration energy. The internal pore structure and the viscoelasticity of the material itself make the energy of the vibration wave continuously converted and consumed when it propagates inside the sponge. Just like in a maze full of resistance, the energy of the vibration wave is gradually weakened, making it difficult to have a substantial impact on aircraft parts. This damping effect further enhances the protection of aircraft parts, allowing parts to complete the stretching and bending process in a relatively stable and quiet environment, reducing the risk of processing errors and part fatigue damage caused by vibration, and providing a solid and reliable technical guarantee for the high-quality manufacturing of aircraft parts.
[0051] Finally, the specific structure of the bending assembly 12 is disclosed. The bending assembly 12 includes a slide rail 120, which is fixedly connected to the top of the bracket 1. A pillar 121 is fixedly connected to the top of the slide rail 120 near the center. A dual-axis motor is provided on the top of the pillar 121. The output shafts of the dual-axis motors on the top of the pillar 121 are fixedly connected to a screw 123. A support block 124 is threadedly connected to the outer wall of the screw 123. A slider 122 is fixedly connected to the bottom of the support block 124. The slider 122 is slidably connected to the outer wall of the slide rail 120. The outer wall of the slider 122 is cylindrical.
[0052] See also Figure 7 As shown, the output shaft of the double-headed motor drives the two screw rods 123 to rotate simultaneously, and the position of the support block 124 on the screw rod 123 is adjusted. By adjusting the distance between the two support blocks 124, the slider 122 is driven to move on the outer wall of the slide rail 120. According to the bending distance and position of the required aircraft parts, the distance between the two sliders 122 is adjusted;
[0053] When facing different types of aircraft parts, due to their respective design requirements and structural characteristics, the required bending distances and positions are significantly different; for example, when manufacturing curved components of aircraft fuselage frames, a larger bending radius and a specific bending starting position are required, and these requirements can be easily met by adjusting the spacing of the sliders 122; and when processing some small curved parts of aircraft engine intake ducts, a smaller bending spacing and more precise position control are required, and this device can also achieve this accurately;
[0054] Furthermore, due to the ingenious design of the cylindrical outer wall of the slider 122, during the stretching and bending process of the aircraft parts, when the aircraft parts are gradually deformed under the action of the stretching and bending force, their surfaces can achieve a tight and natural fit with the outer wall of the slider 122; since the cylindrical surface has the characteristic of continuous and uniform curvature change, the aircraft parts will gradually form a curved arc along the curved shape of the outer wall of the slider 122 during the fitting process. This fitting method enables the stretching and bending force of the aircraft parts during the stretching and bending process to be evenly dispersed on the contact surface between the parts and the slider 122, effectively avoiding the occurrence of stress concentration, and ensuring that the parts obtain a precise bending shape while the internal organizational structure remains intact and the mechanical properties are not damaged.
[0055] Embodiment 2: This embodiment is based on the content provided in Embodiment 1, and aims to provide a process for a bending processing equipment for aircraft parts, and the specific steps are as follows:
[0056] Step 1: Parts inspection: Before the bending process, the aircraft parts need to be fully inspected, including checking the dimensional accuracy of the parts to ensure that their length, width, thickness and other dimensions meet the design requirements to avoid affecting the forming quality after bending due to dimensional deviation.
[0057] Step 2: Clean parts: Remove impurities such as oil, dust and oxide layer on the surface of parts. Avoid these impurities affecting the friction between parts and fixtures during bending, or leaving scratches on the surface of parts. Use organic solvents to clean parts. For metal parts with oxide layer, use pickling or mechanical grinding to remove the oxide layer.
[0058] Step 3: Positioning and clamping: The aircraft part is placed on the top of the bracket 1, between the two molds 1302, and the mold 1302 is pushed toward the two ends of the aircraft part by the piston rod of the cylinder 1301; when the aircraft part enters the mold 1302, the cylinder 1301 drives the mold 1302 to move toward the end of the aircraft part, so that the aircraft part applies pressure to the multiple sleeves 1310 inside the mold 1302;
[0059] Step 4: Clamping operation: Multiple sleeves 1310 are adaptively moved inside the support plate 1300 according to the shape of the end of the aircraft part. The movement of the sleeves 1310 drives the support rods 1311 to move inside the support plate 1300. The support rods 1311 provide stability support for the movement of the sleeves 1310. At the same time, under the movement of the sleeves 1310, the elastic member 1311 between the sleeves 1310 and the support plate 1300 is compressed; while the sleeves 1310 in the mold 1302 that do not contact the aircraft part remain stationary, so that the multiple sleeves 1310 are moved in accordance with the shape of the aircraft part. The mold 1302 has a corresponding shape formed inside, which is convenient for various shapes of aircraft parts to be clamped and wrapped more completely between the two molds 1302, so that the ends of the aircraft parts can be tightly fitted with various parts of the ends of the aircraft parts; this tight fit not only greatly improves the stability and reliability of clamping, effectively prevents the aircraft parts from displacement, shaking or loosening during the subsequent stretch-bending process, but also ensures that the stretch-bending force can be evenly and accurately applied to various parts of the parts, thus laying a solid foundation for obtaining high-precision, high-quality stretch-bending parts;
[0060] Step 5, adjusting the arc distance: the two screw rods 123 are driven to rotate simultaneously by the output shaft of the double-headed motor, and the position of the support block 124 on the screw rod 123 is adjusted. By adjusting the distance between the two support blocks 124, the slider 122 is driven to move on the outer wall of the slide rail 120, and the spacing between the two sliders 122 is adjusted according to the bending distance and position of the required aircraft parts; when facing different types of aircraft parts, due to their respective design requirements and structural characteristics, the required bending distance and position are significantly different; for example, when manufacturing the bending components of the aircraft fuselage frame, a larger bending radius and a specific bending starting position are required, and these requirements can be easily met by adjusting the spacing of the sliders 122; and when processing some small bending parts of the aircraft engine intake duct, a smaller bending spacing and more precise position control are required, and the device can also achieve this accurately;
[0061] Step 6, bending processing: the rotating block 110 is driven to rotate by the rotary drive mechanism, so that the clamping assembly 13 on the base 11 rotates synchronously, so that the aircraft parts between the clamping assembly 13 are gradually bent around the outer wall of the slider 122 on the bracket 1; through the exquisite design of the outer wall of the slider 122 being cylindrical, when the aircraft parts are gradually deformed under the action of the bending force, their surface can be closely and naturally fitted with the outer wall of the slider 122; because the cylindrical surface has a continuous and uniform curvature change characteristic, the aircraft parts will gradually form a curved arc along the curved shape of the outer wall of the slider 122 during the fitting process. This fitting method enables the bending force of the aircraft parts during the bending process to be evenly dispersed on the contact surface between the parts and the slider 122, effectively avoiding the occurrence of stress concentration, and ensuring that the parts obtain a precise bending shape while the internal organizational structure remains intact and the mechanical properties are not damaged;
[0062] Step 7, demoulding of parts: after the bending work is completed, the mold 1302 is driven to move by the piston rod of the cylinder 1301, and the mold 1302 is moved out from the end of the aircraft part, so that the sleeve 1310 in the compressed state is subjected to the rebound force of the elastic member 1312, driving the support rod 1311 to move inside the support plate 1300, and the sleeve 1310 is reset and rebounded to the end of the mold 1302. The moving distance of the support rod 1312 is limited by the block 1313, and the parallel position between the plurality of support rods 1311 and the sleeve 1310 is maintained, so that when the next aircraft part is clamped, it can adapt to aircraft parts of other shapes;
[0063] Step 8. Post-forming processing: After stretching and bending, use precision measuring equipment such as a three-coordinate measuring machine to check the dimensional accuracy of the parts; measure the parts' overall dimensions, radius of curvature, angles and other parameters, and compare them with the design drawings; check whether the parts have scratches, wear, deformation and other quality problems on the surface. For parts with slight scratches on the surface, polishing, grinding and other methods can be used to repair them; if there is local deformation on the surface of the parts, it can be handled by pressure correction and other methods; at the same time, surface anti-corrosion treatment is performed according to the use environment and requirements of the parts.
[0064] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. The above embodiments and descriptions are only preferred examples of the present invention and are not intended to limit the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.
Claims
1. An aircraft parts bending processing equipment, comprising a bracket (1), characterized in that: The bracket (1) is provided with a rotating block (110) near both ends thereof, the ends of the rotating block (110) are fixedly connected to a base (11), the top of the bracket (1) is provided with a bending component (12), and the top of the base (11) is provided with a clamping component (13); The clamping assembly (13) comprises a positioning member (130) and a model member (131), wherein the two positioning members (130) are symmetrically arranged on the top of the two bases (11), a plurality of model members (131) are arranged inside the positioning member (130), and an aircraft part is arranged between the two model members (131); The positioning member (130) is used to drive a plurality of model members (131) to approach two ends of an aircraft part; the model members (131) are used to form a shape consistent with the shape of the end of the aircraft part inside the positioning member (130); the positioning member (130) and the model members (131) are used to clamp and fix aircraft parts of different shapes.
2. The aircraft parts stretch bending processing equipment according to claim 1, characterized in that: The positioning member (130) comprises a cylinder (1301), wherein the cylinder (1301) is fixedly connected to the top of the base (11), the end of the piston rod of the cylinder (1301) is fixedly connected to a mold (1302), the interior of the mold (1302) is fixedly connected to a support plate (1300), and a plurality of model members (131) are arranged between the mold (1302) and the interior of the support plate (1300).
3. The aircraft parts bending equipment according to claim 2, characterized in that: The model part (131) comprises a sleeve (1310), an elastic part (1312) is fixedly connected to the inner wall of the sleeve (1310) near the end, and the other end of the elastic part (1312) is fixedly connected to the outer wall of the support plate (1300).
4. The aircraft parts stretch bending equipment according to claim 3, characterized in that: The end of the inner wall of the sleeve (1310) is fixedly connected to a support rod (1311), and the support rod (1311) is movably connected to the inside of the support plate (1300). The elastic member (1312) is wound around the outer wall of the support rod (1311), and the other end of the support rod (1311) passing through the support plate (1300) is fixedly connected to a blocking block (1313).
5. The aircraft parts stretch bending equipment according to claim 3, characterized in that: The sleeve (1310) is made of sponge material, and the sleeve (1310) is movably connected between the support plate (1300) and the inside of the mold (1302).
6. The aircraft parts stretch bending processing equipment according to claim 1, characterized in that: The bending assembly (12) comprises a slide rail (120), the slide rail (120) is fixedly connected to the top of the bracket (1), a support (121) is fixedly connected to the top of the slide rail (120) near the center, a dual-axis motor is provided at the top of the support (121), and the output shafts of the dual-axis motors at the top of the support (121) are fixedly connected to screws (123).
7. The aircraft parts stretch bending equipment according to claim 6, characterized in that: The outer wall of the screw rod (123) is threadedly connected to a support block (124), the bottom of the support block (124) is fixedly connected to a slider (122), the slider (122) is slidably connected to the outer wall of the slide rail (120), and the outer wall of the slider (122) is cylindrical.
8. A process for operating the aircraft parts stretch bending equipment as claimed in claim 1, characterized in that: The method comprises the following steps: S1. Parts preparation: Before the bending process, the aircraft parts are fully inspected and impurities on the surface of the parts are removed; S2, positioning and clamping: according to the shape and size of the part, the plurality of model parts (131) are formed into a matching shape inside the positioning part (130), and the positioning part (130) is used to drive the plurality of model parts (131) to clamp and fix the part; S3, bending positioning: by adjusting the length of the bending assembly (12), the position to be bent is determined according to the material, shape and bending requirements of the part; S4, bending: starting the rotary drive mechanism to drive the rotating block (110) to rotate inside the bracket (1), so that the rotating block (110) drives the base (11) to rotate, and the parts between the two bases (11) are bent; S5. Post-forming processing: After stretching and bending, use precision measuring equipment such as a three-coordinate measuring machine to check the dimensional accuracy of the parts and check the surface quality of the parts.