A clamping device for processing of thin-walled aeronautical parts

Abstract

The application relates to the field of aerospace part machining technology, in particular to a clamping device for machining of an aviation thin-walled part, which comprises a supporting frame, a sliding groove is formed in the outer surface of the supporting frame, a second push rod is fixedly connected to the inner wall of the supporting frame, when the aviation thin-walled part is clamped and supported, when the stress part of the sliding frame is extruded by the extrusion plate, the extrusion plate pushes the sliding frame to slide along the first fixed shaft and compresses the first spring, the reaction force generated by the first spring acts on the two ends of the sliding frame and the push frame, thereby prompting the first elastic member to be elastically deformed, driving the two ends of the whole push frame to deflect, with the gradual adjustment of the deflection angle, the contact area between the outer surface of the push frame and the inner wall of the aviation thin-walled part is continuously expanded, the clamping force is prevented from being concentrated on limited contact points, so that the supporting effect on the inner wall of the aviation thin-walled part and the accuracy in the machining process can be improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aerospace part processing, in particular to a clamping device for processing of an aerospace thin-walled part. BACKGROUND

[0002] The aerospace thin-walled part is a key core component in aerospace equipment, which is widely used in key positions such as wing skin, engine casing, fuselage wall plate, and tail front edge due to its light and thin structure. This type of component mainly uses high-strength aluminum alloy, high-temperature-resistant titanium alloy, and advanced composite materials as the main raw material, which not only meets the stringent requirements of aerospace equipment for lightweight, but also guarantees the structural strength and stability of the component under complex conditions at high altitudes through material performance. It is an important basic component for realizing weight reduction and efficiency improvement of aerospace equipment and improving flight performance.

[0003] There are many clamping devices for processing of aerospace thin-walled parts in the prior art, for example:

[0004] Chinese patent publication No. CN117086667A discloses a clamping device for processing of an aerospace thin-walled part, which includes a base, an inner clamping block and an outer clamping block mounted above the base; the inner clamping block and the outer clamping block are clamped on the inner and outer sides of the thin-walled part, respectively; a boss is provided in the middle of the top of the base, and an extension rod is connected around the boss, the inner clamping block is slidingly connected with the extension rod; a rotating rod is provided below the outer clamping block, the rotating rod is inserted into one end of the outer clamping block, and a driving member is installed at the bottom of the rotating rod.

[0005] As can be seen, when clamping and fixing the thin-walled part of the engine shell in the field of aviation, the above-mentioned clamping device supports the thin-walled part from both the inner and outer sides at the same time through the inner clamping block and the outer clamping block to achieve clamping and fixing of the thin-walled part. However, the inner clamping block only relies on the spring to provide support force, and the clamping force is concentrated on a limited number of contact points, which may cause the thin-walled part to deform slightly during processing, resulting in springback after the workpiece is removed, and loss of shape accuracy. SUMMARY

[0006] The application provides a clamping device for processing an aviation thin-walled part, which comprises a support frame, a sliding groove is formed in the outer surface of the support frame, a second push rod is fixedly connected to the inner wall of the support frame, a first push rod is fixedly connected to the center of the support frame, a connecting block is fixedly connected to the output end of the first push rod, a pushing mechanism is arranged on the top of the support frame, and the output end of the second push rod is provided with a supporting mechanism.

[0007] To achieve the above object, the clamping device for processing the aviation thin-walled part comprises a support frame, a sliding groove is formed in the outer surface of the support frame, a second push rod is fixedly connected to the inner wall of the support frame, a first push rod is fixedly connected to the center of the support frame, a connecting block is fixedly connected to the output end of the first push rod, a pushing mechanism is arranged on the top of the support frame, and the output end of the second push rod is provided with a supporting mechanism.

[0008] The pushing mechanism comprises a pushing frame, a first sliding block is fixedly connected to the bottom of the pushing frame, the first sliding block is slidingly connected to the inner wall of the sliding groove, a first elastic member is fixedly connected to the inner wall of the pushing frame, a first fixed shaft is fixedly connected to the inner wall of the left and right ends of the pushing frame, a sliding frame is slidingly connected to the outer surface of the first fixed shaft, and a stress receiving portion is arranged on the outer surface of the sliding frame.

[0009] On the basis of the above, a first spring is fixedly connected to the outer surface of the side of the sliding frame close to the pushing frame, and the end of the first spring away from the sliding frame is fixedly connected to the pushing frame.

[0010] Meanwhile, a second sliding block is arranged outside the side of the stress receiving portion away from the pushing frame, a second fixed shaft is fixedly connected to the outer wall of the side of the second sliding block close to the pushing frame, the end of the second fixed shaft away from the second sliding block penetrates the stress receiving portion and is fixedly connected with a second spring, and the end of the second spring close to the second sliding block is fixedly connected to the stress receiving portion.

[0011] Based on the above, when clamping and supporting thin-walled aerospace parts, when the force-bearing part of the sliding frame is subjected to the extrusion pressure of the extrusion plate, the extrusion plate will push the sliding frame to slide along the first fixed axis and compress the first spring. The reaction force generated by the first spring acts on both ends of the sliding frame and the push frame, thereby causing the first elastic element to undergo elastic deformation, which in turn causes both ends of the entire push frame to deflect. As the deflection angle is gradually adjusted, the contact area between the outer surface of the push frame and the inner wall of the thin-walled aerospace part continues to expand, avoiding the clamping force from being concentrated on a limited number of contact points. This can improve the support effect on the inner wall of the thin-walled aerospace part and the accuracy of its processing.

[0012] In the above technical solution, a pressing plate is fixedly connected to the outer wall of the second sliding block near the force-bearing part, and a rotating rod is rotatably connected to the inner wall of the second sliding block away from the pressing plate via a rotating shaft. The end of the rotating rod away from the second sliding block is rotatably connected to the connecting block.

[0013] Based on the above, the support mechanism includes two clamping frames. The outer wall of the bottom clamping frame is fixedly connected to the second push rod. Notably, a motor is installed between the two clamping frames, and a lead screw is fixedly connected to the output end of the motor. The motor is fixedly connected to the bottom clamping frame. When supporting and clamping the outer surface of thin-walled aero-engine housing components of different heights, the motor drives the lead screw to push the upper clamping frame to slide, thereby adjusting the vertical distance between the upper and lower clamping frames to adapt to thin-walled aero-engine housing components of different heights. During the sliding of the upper clamping frame, a third fixed shaft fixedly connected to the bottom clamping frame can improve the stability of the upper clamping frame during sliding.

[0014] Furthermore, a third fixed shaft is fixedly connected to the outer wall of the bottom clamping frame near the motor, and the upper clamping frame is movably sleeved on the outer surface of the third fixed shaft.

[0015] Meanwhile, a second elastic element is fixedly connected to the outer surface of the clamping frame, and an air inlet pipe is fixedly connected to the outer wall of the clamping frame near the second elastic element. A weakening groove is formed on the outer surface of the clamping frame, and a connecting pipe is fixedly connected to the inner wall of the weakening groove. An air outlet is formed on the outer surface of the clamping frame away from the connecting pipe. The air inlet pipe is connected to the air outlet through the connecting pipe and is used to spray high-pressure gas from the air outlet. The air inlet pipe injects high-pressure gas into the connecting pipe. The connecting pipe, as an airflow transmission channel, can guide the high-pressure gas to the air outlet and make the high-pressure gas spray out from the air outlet. The sprayed high-pressure gas forms a continuous air curtain outside the bag. This air curtain can block the debris generated during the processing, thereby preventing the debris from contacting and damaging the outer surface of the bag.

[0016] Based on the above, an inlet pipe is fixedly connected to the outer wall of the clamping frame away from the air inlet pipe, and a bladder is fixedly connected to the inner wall of the clamping frame away from the second elastic element. The inlet pipe communicates with the inside of the bladder and is used to inject hydraulic oil into the bladder.

[0017] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0018] 1. In this clamping device for processing thin-walled aerospace parts, when clamping and supporting the thin-walled aerospace parts, when the force-bearing part of the sliding frame is subjected to the extrusion pressure of the extrusion plate, the extrusion plate will push the sliding frame to slide along the first fixed axis and compress the first spring. The reaction force generated by the first spring acts on both ends of the sliding frame and the push frame, thereby causing the first elastic element to undergo elastic deformation, causing both ends of the entire push frame to deflect. As the deflection angle is gradually adjusted, the contact area between the outer surface of the push frame and the inner wall of the thin-walled aerospace part continuously expands, avoiding the clamping force from being concentrated on a limited number of contact points, thereby improving the support effect on the inner wall of the thin-walled aerospace part and the accuracy of its processing.

[0019] 2. In this clamping device for machining thin-walled aerospace parts, when clamping the outer surface of a thin-walled aero-engine casing, hydraulic oil is injected into the bag through the inlet pipe. The bag expands under the action of hydraulic oil filling, so that its outer surface can fit tightly against the outer surface of the thin-walled aerospace part, thereby achieving adaptive clamping of the outer surface of thin-walled aerospace parts of different diameters. At the same time, high-pressure gas is injected into the connecting pipe through the air inlet pipe, so that the high-pressure gas is ejected from the air outlet. The ejected high-pressure gas forms a continuous air curtain outside the bag, thereby blocking the debris generated during the machining process. Therefore, it can prevent debris from contacting and damaging the outer surface of the bag. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of the present invention. Figure 1 ;

[0021] Figure 2 This is a schematic diagram of the overall structure of the present invention. Figure 2 ;

[0022] Figure 3 This is a schematic diagram of the support frame structure of the present invention;

[0023] Figure 4 This is a schematic diagram of the pushing mechanism structure of the present invention;

[0024] Figure 5 This is an exploded structural diagram of the jacking mechanism of the present invention;

[0025] Figure 6 This is a schematic diagram of the front structure of the support mechanism of the present invention;

[0026] Figure 7 This is a schematic diagram of the rear structure of the support mechanism of the present invention;

[0027] Figure 8 For the present invention Figure 2 A magnified structural diagram of A in the diagram.

[0028] The meanings of the labels in the diagram are as follows:

[0029] 1. Support frame; 2. Sliding groove; 3. First push rod; 4. Connecting block; 5. Second push rod; 6. Pushing mechanism; 601. Pushing frame; 602. First elastic element; 603. First sliding block; 604. Sliding frame; 605. First fixed shaft; 606. First spring; 607. Force-bearing part; 608. Second sliding block; 609. Second fixed shaft; 610. Second spring; 611. Extrusion plate; 612. Rotating rod; 7. Support mechanism; 701. Clamping frame; 702. Weakening groove; 703. Second elastic element; 704. Air inlet pipe; 705. Connecting pipe; 706. Air outlet; 707. Liquid inlet pipe; 708. Bag; 709. Third fixed shaft; 8. Motor; 9. Lead screw. Detailed Implementation

[0030] The technical solutions of this invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0031] When clamping and fixing thin-walled parts of engine casings in the aerospace field, the existing clamping device for machining thin-walled parts of aerospace (CN117086667A) supports the thin-walled parts from both the inside and outside of the thin-walled parts simultaneously through inner and outer clamping blocks to achieve clamping and fixing of the thin-walled parts. However, the inner clamping block only relies on springs to provide support force, and the clamping force is concentrated on a limited number of contact points. This may cause the thin-walled parts to undergo slight deformation during the machining process, resulting in springback after the workpiece is removed, and loss of shape accuracy.

[0032] Therefore, in view of the above-mentioned problems, the present invention discloses a clamping device for machining thin-walled aerospace parts, with reference to... Figures 1-3 As shown, a support frame 1 has a sliding groove 2 on its outer surface, a second push rod 5 is fixedly connected to the inner wall of the support frame 1, a first push rod 3 is fixedly connected to the center of the support frame 1, a connecting block 4 is fixedly connected to the output end of the first push rod 3, a pushing mechanism 6 is provided on the top of the support frame 1, and a support mechanism 7 is provided at the output end of the second push rod 5.

[0033] When it is necessary to support a thin-walled component from the inside, refer toFigures 4-5 , Figure 8 As shown, the jacking mechanism 6 includes a jacking frame 601. A first sliding block 603 is fixedly connected to the bottom of the jacking frame 601. The first sliding block 603 is slidably connected to the inner wall of the sliding groove 2. A first elastic element 602 is fixedly connected to the inner wall of the jacking frame 601. The first elastic element 602 is made of high carbon spring steel and is semi-arc in shape. A first fixed shaft 605 is fixedly connected to the inner walls of the left and right ends of the jacking frame 601. A sliding frame 604 is slidably connected to the outer surface of the first fixed shaft 605. A force-bearing part 607 is provided on the outer surface of the sliding frame 604. A first spring 606 is fixedly connected to the outer surface of the sliding frame 604 on the side close to the jacking frame 601. The end of the first spring 606 away from the sliding frame 604 is fixedly connected to the jacking frame 601.

[0034] When performing inner wall support and clamping operations on thin-walled engine housing parts of different diameters, the outer surface of the pusher 601 is difficult to fit with the inner wall of the thin-walled engine housing parts of different diameters. Therefore, the fit effect during the support and clamping process cannot be guaranteed. To address this, a second sliding block 608 is provided on the outer side of the force-bearing part 607 away from the pusher 601. A second fixed shaft 609 is fixedly connected to the outer wall of the second sliding block 608 near the pusher 601. The end of the second fixed shaft 609 away from the second sliding block 608 passes through the force-bearing part 607 and is fixedly connected to a second spring 610. The second spring 610 can limit the compressive force applied by the pusher 601 to the inner wall of the thin-walled part, effectively preventing the pusher 601 from excessively compressing the inner wall of the thin-walled part. The end of the second spring 610 near the second sliding block 608 is fixedly connected to the force-bearing part 607.

[0035] It is worth noting that a pressing plate 611 is fixedly connected to the outer wall of the second sliding block 608 near the force-bearing part 607, and a rotating rod 612 is rotatably connected to the inner wall of the second sliding block 608 away from the pressing plate 611 via a rotating shaft. The end of the rotating rod 612 away from the second sliding block 608 is rotatably connected to the connecting block 4. The first push rod 3 pulls the connecting block 4 downward, causing it to move towards the support frame 1. The rotating rod 612, which rotates with the inner wall of the connecting block 4, will apply a horizontal thrust to the second sliding block 608 as the connecting block 4 moves, pushing the second sliding block 608 towards the sliding frame 604 and generating a pressing effect.

[0036] When the force-bearing part 607 on the sliding frame 604 is subjected to the squeezing force of the squeezing plate 611, the squeezing plate 611 pushes the sliding frame 604 to slide along the first fixed shaft 605 and compresses the first spring 606. The reaction force of the first spring 606 acts on the sliding frame 604 and the pusher frame 601, thereby causing the first elastic element 602 to undergo elastic deformation, which in turn causes the two ends of the entire pusher frame 601 to deflect. As the deflection angle is gradually adjusted, the contact area between the outer surface of the pusher frame 601 and the inner wall of the aerospace thin-walled part increases continuously, and finally the contact area between the two is effectively increased, thereby improving the support operation of the inner wall of the aerospace thin-walled part.

[0037] When it is necessary to support a thin-walled component from the outside, refer to Figures 6-7 As shown, the support mechanism 7 includes two clamping frames 701. The outer wall of the bottom clamping frame 701 is fixedly connected to the second push rod 5.

[0038] A motor 8 is installed between the two clamping frames 701. A lead screw 9 is fixedly connected to the output end of the motor 8. The motor 8 is fixedly connected to the bottom clamping frame 701. The motor 8 adjusts the vertical distance between the upper clamping frame 701 and the bottom clamping frame 701 by driving the lead screw 9. A third fixed shaft 709 is fixedly connected to the outer wall of the bottom clamping frame 701 near the motor 8. The upper clamping frame 701 is movably sleeved on the outer surface of the third fixed shaft 709. When supporting and clamping thin-walled parts of the aero-engine housing of different heights, the motor 8 pushes the upper clamping frame 701 to slide by driving the lead screw 9, thereby adjusting the vertical distance between the upper and lower clamping frames 701 to adapt to thin-walled parts of the aero-engine housing of different heights. During the sliding of the upper clamping frame 701, the third fixed shaft 709 fixedly connected to the bottom clamping frame 701 can improve the stability of the upper clamping frame 701 during sliding.

[0039] A liquid inlet pipe 707 is fixedly connected to the outer wall of the clamping frame 701 away from the air inlet pipe 704. A bag 708 is fixedly connected to the inner wall of the clamping frame 701 away from the second elastic element 703. The bag 708 adopts a three-layer composite structure design. Its inner layer is a fluororubber sealing layer, which plays a sealing and protective role; the middle layer is a fiber braided reinforcement layer, which is used to improve the structural strength and tensile strength of the bag 708; the outer layer is a polyurethane wear-resistant outer layer covering the fiber braided reinforcement layer. The hydraulic inlet pipe 707 is connected to the inside of the bag 708 to inject hydraulic oil into the bag 708. When it is necessary to clamp the outer surface of the thin-walled part of the aircraft engine housing, hydraulic oil is injected into the bag 708 through the hydraulic inlet pipe 707. The bag 708 expands under the action of hydraulic oil filling, and its outer surface can fit tightly with the outer surface of the aircraft thin-walled part, thereby realizing the adaptive clamping of the outer surface of aircraft thin-walled parts of different diameters.

[0040] A second elastic element 703 is fixedly connected to the outer surface of the clamping frame 701. The second elastic element 703 is made of high-carbon spring steel and has a semi-arc shape. During the processing of thin-walled aerospace parts, the debris generated during processing may scratch the outer surface of the pouch 708. Once the outer surface of the pouch 708 is damaged, its sealing performance will be affected, which may lead to the risk of hydraulic oil leakage inside the pouch 708. For this reason, an air inlet pipe 704 is fixedly connected to the outer wall of the clamping frame 701 near the second elastic element 703. A weakening groove 702 is formed on the outer surface of the clamping frame 701, and the inner wall of the weakening groove 702 is fixedly connected to... The clamping frame 701 has a connecting pipe 705 and an air outlet 706 on the outer surface of the side away from the connecting pipe 705. The air inlet pipe 704 is connected to the air outlet 706 through the connecting pipe 705 and is used to spray high-pressure gas from the air outlet 706. The air inlet pipe 704 injects high-pressure gas into the connecting pipe 705. The connecting pipe 705 serves as an airflow transmission channel, which can guide the high-pressure gas to the air outlet 706 and make the high-pressure gas spray out from the air outlet 706. The sprayed high-pressure gas forms a continuous air curtain outside the bag 708. This air curtain can block the debris generated during the processing, thereby preventing the debris from contacting and damaging the outer surface of the bag 708.

[0041] The foregoing has shown and described 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 to the above embodiments. The embodiments and descriptions in the specification are merely preferred examples and are not intended to limit the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A clamping device for machining thin-walled aerospace parts, comprising a support frame, wherein a sliding groove is formed on the outer surface of the support frame, a second push rod is fixedly connected to the inner wall of the support frame, a first push rod is fixedly connected to the center of the support frame, and a connecting block is fixedly connected to the output end of the first push rod, characterized in that: The top of the support frame is provided with a pushing mechanism, and the output end of the second push rod is provided with a support mechanism; The pushing mechanism includes: A pusher frame, wherein a first sliding block is fixedly connected to the bottom of the pusher frame, the first sliding block is slidably connected to the inner wall of the sliding groove, a first elastic element is fixedly connected to the inner wall of the pusher frame, a first fixed shaft is fixedly connected to the inner walls of the left and right ends of the pusher frame, a sliding frame is slidably connected to the outer surface of the first fixed shaft, and a force-bearing part is provided on the outer surface of the sliding frame; A first spring is fixedly connected to the outer surface of the sliding frame near the push frame, and the end of the first spring away from the sliding frame is fixedly connected to the push frame. A second sliding block is provided on the outer side of the force-bearing part away from the push frame. A second fixed shaft is fixedly connected to the outer wall of the second sliding block near the push frame. The end of the second fixed shaft away from the second sliding block passes through the force-bearing part and is fixedly connected to a second spring. The end of the second spring near the second sliding block is fixedly connected to the force-bearing part. A pressing plate is fixedly connected to the outer wall of the second sliding block near the force-bearing part. A rotating rod is rotatably connected to the inner wall of the second sliding block away from the pressing plate via a rotating shaft. The end of the rotating rod away from the second sliding block is rotatably connected to the connecting block.

2. The clamping device for machining thin-walled aerospace parts according to claim 1, characterized in that: The support mechanism includes two clamping frames, one of which is located at the bottom. The outer wall of the clamping frame is fixedly connected to the second push rod.

3. The clamping device for machining thin-walled aerospace parts according to claim 2, characterized in that: A motor is provided between the two clamping frames. A lead screw is fixedly connected to the output end of the motor. The motor is fixedly connected to the bottom clamping frame. The motor adjusts the vertical distance between the upper clamping frame and the bottom clamping frame by driving the lead screw.

4. The clamping device for machining thin-walled aerospace parts according to claim 3, characterized in that: A third fixed shaft is fixedly connected to the outer wall of the bottom clamping frame near the motor, and the upper clamping frame is movably sleeved on the outer surface of the third fixed shaft.

5. The clamping device for machining thin-walled aerospace parts according to claim 4, characterized in that: A second elastic element is fixedly connected to the outer surface of the clamping frame, and an air inlet pipe is fixedly connected to the outer wall of the clamping frame near the second elastic element.

6. The clamping device for machining thin-walled aerospace parts according to claim 5, characterized in that: The outer surface of the clamping frame is provided with a weakening groove, and a connecting pipe is fixedly connected to the inner wall of the weakening groove. An air outlet is provided on the outer surface of the clamping frame away from the connecting pipe. The air inlet pipe is connected to the air outlet through the connecting pipe and is used to spray high-pressure gas from the air outlet.

7. The clamping device for machining thin-walled aerospace parts according to claim 6, characterized in that: A liquid inlet pipe is fixedly connected to the outer wall of the clamping frame away from the air inlet pipe, and a bladder is fixedly connected to the inner wall of the clamping frame away from the second elastic element. The liquid inlet pipe communicates with the inside of the bladder and is used to inject hydraulic oil into the bladder.

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