A friction welding device for aviation thin-walled structural parts

Abstract

The present invention relates to the technical field of friction welding devices for aviation thin-walled structural parts, and specifically to a friction welding device for aviation thin-walled structural parts, comprising a base plate and a support frame above the base plate, and also comprising a suction cup, of which a plurality is provided. The friction welding device for aviation thin-walled structural parts places a cylindrical aviation thin-walled structural part on the top of a first auxiliary plate, and then drives a screw rod to rotate through a motor to drive a first drive plate and a second drive plate to rise and fall, so that the second transmission plate slides on the corresponding second auxiliary plate and the first auxiliary plate through the first transmission plate, and the extrusion plate on the top of the second transmission plate pushes the rubber blocks at both ends thereof to move, so that the rubber blocks push the cylindrical aviation thin-walled structural part so that its axis is the same as the axis of the first auxiliary plate, and the second transmission plate pushes a trigger rod while moving, and through the cooperation of a sliding groove and two sliding plates, the arc plate squeezes the outer wall of the aviation thin-walled structural part, thereby fixing it on the top of the first auxiliary plate.

Description

Technical Field

[0001] The invention relates to the technical field of friction welding of aviation thin-walled structural parts, in particular to a friction welding device for aviation thin-walled structural parts. Background Art

[0002] Friction welding of aviation thin-walled structural parts is a welding technology widely used in aviation manufacturing. It uses the heat generated by the friction of the contact surface of the workpiece as a heat source to make the workpiece produce plastic deformation under pressure for welding. Friction welding generates friction heat through the relative movement between the workpieces, so that the temperature of the contact surface and its surrounding area rises to a temperature range close to but generally lower than the melting point, thereby achieving welding under the action of top forging pressure. However, we have found in real life that before welding aviation thin-walled structural parts, the aviation thin-walled structural parts to be welded need to be fixed, and the existing fixing method is to clamp and fix the aviation thin-walled structural parts through traditional mechanical pressure plates. However, this method takes a long time to clamp, and the clamping reliability depends entirely on the attitude of the workers and the standardization of the work. The size and consistency of the clamping force cannot be guaranteed. For this reason, we propose a friction welding device for aviation thin-walled structural parts. Summary of the invention

[0003] A technical problem to be solved by the present application is: how to fix the thin-walled aviation structural parts to be welded and avoid the inconsistency of the clamping force, thereby reducing and avoiding the disadvantages caused by manual operation.

[0004] In order to solve the above technical problems, the present application provides a friction welding device for thin-walled aircraft structural parts, including a base plate and a support frame above the base plate, and also including

[0005] A plurality of suction cups are provided, and the plurality of suction cups are arranged above the support frame, and are used to absorb the aviation thin-walled structural parts to be welded;

[0006] A plurality of arc-shaped plates are provided, and the plurality of arc-shaped plates are arranged between the support frame and the plurality of suction cups, and are used for extruding aviation thin-walled structural parts;

[0007] The fixing mechanism is arranged above the supporting frame, and the movement of the plurality of arc plates and the plurality of suction cups is controlled by the fixing mechanism to drive the plurality of arc plates to extrude the aviation thin-walled structural parts, and control the plurality of suction cups to adsorb the aviation thin-walled structural parts.

[0008] In some embodiments, the fixing mechanism includes a driving member arranged on the support frame, and the driving member is used to provide power for the movement of the multiple curved plates and the multiple suction cups. An auxiliary member is arranged above the support frame, and the auxiliary member is used to assist the multiple suction cups and the multiple curved plates to fix the aviation thin-walled structural parts. A clamping assembly is arranged above the support frame, and the clamping assembly is used to clamp the aviation thin-walled structural parts.

[0009] In some embodiments, the driving member includes a motor arranged on the base plate, a screw is arranged at the output end of the motor, and the motor and the screw are both located at the axis of the support frame, a first driving plate is arranged on the screw, a second driving plate is arranged on the screw, and the first driving plate and the second driving plate are both threadedly connected to the screw, and the second driving plate is located above the first driving plate.

[0010] In some embodiments, the auxiliary component includes a first auxiliary plate arranged on the top of the support frame, multiple support plates are arranged on the top of the first auxiliary plate, and a second auxiliary plate is arranged on the top of the multiple support plates, the screw rod is arranged through the axis of the first auxiliary plate and the second auxiliary plate, the first drive plate is located between the first auxiliary plate and the second auxiliary plate, and the second drive plate is located above the second auxiliary plate.

[0011] In some embodiments, the clamping assembly includes transmission parts respectively arranged on the outside of the first auxiliary plate and the second auxiliary plate, which are used to transmit power for the movement of the multiple curved plates and the multiple suction cups. A plurality of extrusion parts are arranged above the first auxiliary plate, and the multiple extrusion parts are used to control the aviation thin-walled structural parts and the first auxiliary plate to be located at the same axis. A plurality of pneumatic parts are arranged on the first auxiliary plate, and the multiple pneumatic parts are used to control the movement of the corresponding curved plates respectively, so that the multiple curved plates are driven to extrude the outer walls of the aviation thin-walled structural parts respectively. A plurality of adsorption parts are arranged above the second auxiliary plate, and the multiple adsorption parts are used to control the movement of the corresponding suction cups, so that the multiple suction cups are driven to adsorb the inner walls of the aviation thin-walled structural parts.

[0012] In some embodiments, the transmission member includes a plurality of first transmission plates respectively rotatably arranged on the outside of the first drive plate and the second drive plate through a rotating shaft, a second transmission plate is rotatably arranged at one end of the plurality of first transmission plates away from the first drive plate and the second drive plate through a rotating shaft, a plurality of limiting grooves are opened in the first auxiliary plate and the second auxiliary plate, and a plurality of second transmission plates are respectively slidably arranged in the first auxiliary plate and the second auxiliary plate through corresponding limiting grooves.

[0013] In some embodiments, the extrusion member includes an extrusion plate disposed on the top of the second transmission plate, and rubber blocks are disposed at both ends of the extrusion plate.

[0014] In some embodiments, the pneumatic part includes a pneumatic plate arranged on the first auxiliary plate, a sliding groove is opened in the pneumatic plate, two sliding plates are slidably arranged in the sliding groove, and the two sliding plates are respectively located at both ends of the pneumatic plate, and one of the two sliding plates located at the bottom is provided with a trigger rod used in conjunction with the second transmission plate on its side close to the first auxiliary plate, and limit rods are provided on both sides of the trigger rod, one end of the two limit rods is arranged on adjacent sliding plates, and the other end thereof is slidably arranged in the first auxiliary plate, an auxiliary frame is provided on the first auxiliary plate, and a plurality of push rods are slidably arranged in the auxiliary frame, one end of the plurality of push rods is arranged on adjacent sliding plates, and the other end thereof is arranged on the outside of the corresponding arc-shaped plates, and a return spring is provided on the outside of the plurality of push rods, one end of the plurality of return springs is arranged on adjacent sliding plates, and the other end thereof is arranged on the outside of the auxiliary frame.

[0015] In some embodiments, the adsorption component includes a fixed plate arranged on the top of the second transmission plate, a rotating rod is rotatably arranged in the fixed plate, a gear is arranged on the outside of the rotating rod, and the gear is located in the fixed plate, a rubber pad 1 is arranged on the side of the fixed plate away from the second transmission plate, a plate 1 is slidably arranged in the fixed plate, a plurality of tooth grooves are provided on the plate 1 for cooperating with the gear, an extrusion spring is arranged in the fixed plate, one end of the extrusion spring is arranged in the fixed plate, and the other end of the extrusion spring is arranged at one end of the plate 1, and a rubber pad 2 is arranged at the end of the plate 1 away from the extrusion spring, rotating plates are arranged at both ends of the rotating rod, control plates are arranged on the top of the two rotating plates, rubber plates are arranged on the top of the two control plates, multiple suction cups are arranged on corresponding rotating plates, and micro air pumps for cooperating with the multiple suction cups are arranged at the bottom of the two rotating plates.

[0016] In some embodiments, a plurality of grooves are formed on the top of each of the plurality of rubber plates.

[0017] The present invention has at least the following beneficial effects:

[0018] When in use, a cylindrical aviation thin-walled structural part is placed on the top of the first auxiliary plate, and then the screw is driven to rotate by a motor to drive the first drive plate and the second drive plate to rise and fall, so that the second transmission plate slides on the corresponding second auxiliary plate and the first auxiliary plate through the first transmission plate. At this time, the extrusion plate on the top of the second transmission plate will push the rubber blocks at both ends to move, so that the rubber blocks push the cylindrical aviation thin-walled structural part so that its axis is the same as the axis of the first auxiliary plate. While moving, the second transmission plate will push the trigger rod, and through the cooperation of the sliding groove and the two sliding plates, the arc plate will squeeze the outer wall of the aviation thin-walled structural part, thereby fixing it on the top of the first auxiliary plate. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0020] Figure 2 For the present invention Figure 1 Another structural diagram;

[0021] Figure 3 It is a schematic diagram of the structure of the driving part of the present invention;

[0022] Figure 4 It is a partial structural schematic diagram of the clamping assembly of the present invention;

[0023] Figure 5 It is a schematic diagram of the auxiliary component structure of the present invention;

[0024] Figure 6 It is a side cross-sectional schematic diagram of the first auxiliary plate structure of the present invention;

[0025] Figure 7 It is a schematic diagram of the explosion of the pneumatic component structure of the present invention;

[0026] Figure 8 It is a partial structural schematic diagram of the adsorption member of the present invention;

[0027] Fig. 9 It is a side cross-sectional schematic diagram of the fixing plate structure of the present invention;

[0028] Fig.10 This is a structural diagram of Example 2 of the present invention.

[0029] In the figure: 1, bottom plate; 2, support frame; 3, suction cup; 4, arc plate; 5, fixing mechanism; 6, driving member; 61, motor; 62, screw; 63, first driving plate; 64, second driving plate; 7, auxiliary member; 71, first auxiliary plate; 72, support plate; 73, second auxiliary plate; 8, clamping assembly; 9, transmission member; 91, first transmission plate; 92, second transmission plate; 93, limit groove; 10, extrusion member; 101, extrusion plate; 102, rubber block; 11, pneumatic member; 111, pneumatic Moving plate; 112, sliding groove; 113, sliding plate; 114, trigger rod; 115, limit rod; 116, auxiliary frame; 117, push rod; 118, reset spring; 12, adsorption member; 121, fixed plate; 122, rotating rod; 123, gear; 124, rubber pad 1; 125, plate 1; 126, tooth groove; 127, squeeze spring; 128, rubber pad 2; 129, rotating plate; 1210, control plate; 1211, rubber plate; 1212, micro air pump; 13, groove. DETAILED DESCRIPTION

[0030] 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.

[0031] Embodiment 1

[0032] See also Figure 1-9 The present invention provides a technical solution: a friction welding device for aviation thin-walled structural parts, comprising a base plate 1 and a support frame 2 above the base plate 1, and also comprising

[0033] Suction cups 3, which are provided in plurality and are all arranged above the support frame 2, for adsorbing aviation thin-walled structural parts to be welded;

[0034] A plurality of arc-shaped plates 4 are provided, and the plurality of arc-shaped plates 4 are all provided between the support frame 2 and the plurality of suction cups 3, and are used for extruding aviation thin-walled structural parts;

[0035] The fixing mechanism 5 is arranged above the support frame 2, and is used to control the movement of the plurality of curved plates 4 and the plurality of suction cups 3, so as to drive the plurality of curved plates 4 to extrude the aviation thin-walled structural parts, and control the plurality of suction cups 3 to adsorb the aviation thin-walled structural parts.

[0036] The fixing mechanism 5 includes a driving member 6 arranged on the support frame 2, and the driving member 6 is used to provide power for the movement of the multiple curved plates 4 and the multiple suction cups 3. An auxiliary member 7 is arranged above the support frame 2, and the auxiliary member 7 is used to assist the multiple suction cups 3 and the multiple curved plates 4 to fix the aviation thin-walled structural parts. A clamping assembly 8 is arranged above the support frame 2, and the clamping assembly 8 is used to clamp the aviation thin-walled structural parts.

[0037] The driving member 6 includes a motor 61 arranged on the base plate 1, a screw 62 is arranged at the output end of the motor 61, and the motor 61 and the screw 62 are both located at the axis of the support frame 2, a first driving plate 63 is arranged on the screw 62, and a second driving plate 64 is arranged on the screw 62, and the first driving plate 63 and the second driving plate 64 are both threadedly connected with the screw 62, and the second driving plate 64 is located above the first driving plate 63. When the motor 61 starts to work, the motor 61 will drive the screw 62 at its output end to rotate. When the screw 62 starts to rotate, the first driving plate 63 and the second driving plate 64 threadedly connected with the screw 62 will rotate together with the screw 62. Since the first driving plate 63 and the second driving plate 64 are rotatably connected to the first transmission plate 91 through the rotating shaft, the first driving plate 63 and the second driving plate 64 are driven by the screw 62 to perform lifting movement, and their function is to provide power for the movement of multiple arc plates 4 and multiple suction cups 3.

[0038] The auxiliary component 7 includes a first auxiliary plate 71 arranged on the top of the support frame 2, a plurality of support plates 72 are arranged on the top of the first auxiliary plate 71, a second auxiliary plate 73 is arranged on the top of the plurality of support plates 72, a screw 62 is arranged through the first auxiliary plate 71 and the second auxiliary plate 73 at the axis center, the first drive plate 63 is located between the first auxiliary plate 71 and the second auxiliary plate 73, the second drive plate 64 is located above the second auxiliary plate 73, the first auxiliary plate 71 and the second auxiliary plate 73 function to provide movement tracks for the plurality of suction cups 3 and the plurality of arc plates 4 respectively, and the first auxiliary plate 71 is mainly used to support the bottom of the cylindrical aviation thin-walled structural member, and the support plate 72 functions to support the second auxiliary plate 73 by using the first auxiliary plate 71 as a base.

[0039] The clamping assembly 8 includes transmission parts 9 respectively arranged on the outside of the first auxiliary plate 71 and the second auxiliary plate 73, which are used to transmit power for the movement of multiple curved plates 4 and multiple suction cups 3. Multiple extrusion parts 10 are arranged above the first auxiliary plate 71, and the multiple extrusion parts 10 are used to control the aviation thin-walled structural parts and the first auxiliary plate 71 to be located at the same axis. Multiple pneumatic parts 11 are arranged on the first auxiliary plate 71, and the multiple pneumatic parts 11 are used to control the movement of the corresponding curved plates 4 respectively, so that the multiple curved plates 4 are driven to extrude the outer walls of the aviation thin-walled structural parts respectively. Multiple adsorption parts 12 are arranged above the second auxiliary plate 73, and the multiple adsorption parts 12 are used to control the movement of the corresponding suction cups 3, so that the multiple suction cups 3 are driven to adsorb the inner walls of the aviation thin-walled structural parts.

[0040] The transmission member 9 includes a plurality of first transmission plates 91 respectively rotatably arranged on the outer sides of the first drive plate 63 and the second drive plate 64 through a rotating shaft, and a second transmission plate 92 is rotatably arranged on one end of the plurality of first transmission plates 91 away from the first drive plate 63 and the second drive plate 64 through a rotating shaft, and a plurality of limiting grooves 93 are provided in the first auxiliary plate 71 and the second auxiliary plate 73, and a plurality of second transmission plates 92 are respectively slidably arranged in the first auxiliary plate 71 and the second auxiliary plate 73 through corresponding limiting grooves 93. When the first drive plate 63 and the second drive plate 64 descend, the first drive plate 63 and the second drive plate 64 will drive the plurality of first transmission plates 91 on the outer sides thereof to move downward. When the first transmission plate 91 follows the second When the first driving plate 63 and the second driving plate 64 move downward, since the first transmission plate 91 is rotatably connected to the first driving plate 63 and the second driving plate 64 through the rotating shaft, and the first transmission plate 91 is rotatably connected to the second transmission plate 92 through the rotating shaft, the first transmission plate 91 pushes the second transmission plate 92 under the action of the first driving plate 63 and the second driving plate 64, and the second transmission plate 92 is slidably arranged in the limiting groove 93, and then the multiple second transmission plates 92 are respectively slid in the corresponding limiting grooves 93 opened in the first auxiliary plate 71 and the second auxiliary plate 73 under the action of the multiple first transmission plates 91, and their function is to transmit power for the movement of the multiple suction cups 3 and the multiple arc plates 4.

[0041] The extrusion member 10 includes an extrusion plate 101 arranged on the top of the second transmission plate 92, and rubber blocks 102 are arranged at both ends of the extrusion plate 101. When the multiple second transmission plates 92 located on the top of the first auxiliary plate 71 slide in the corresponding limiting grooves 93, the second transmission plate 92 will drive the extrusion plate 101 on its top to move together. When the extrusion plate 101 moves, the extrusion plate 101 will drive the rubber blocks 102 at both ends to move together, so that the two rubber blocks 102 squeeze the inner wall of the aviation thin-walled structural member and push the aviation thin-walled structural member so that the axis of the aviation thin-walled structural member is located at the same place as the axis of the first auxiliary plate 71. Its function is to be able to cooperate with the extrusion of the multiple rubber blocks 102 through the movement of the multiple extrusion plates 101, so that the axis of the aviation thin-walled structural member will not deviate from the axis of the first auxiliary plate 71, thereby avoiding position displacement when fixing the aviation thin-walled structural member, thereby causing unstable fixing.

[0042] The pneumatic member 11 includes a pneumatic plate 111 disposed on the first auxiliary plate 71, a sliding groove 112 is provided in the pneumatic plate 111, two sliding plates 113 are slidably provided in the sliding groove 112, and the two sliding plates 113 are respectively located at both ends of the pneumatic plate 111, and one of the two sliding plates 113 located at the bottom is provided with a trigger rod 114 used in conjunction with the second transmission plate 92 on its side close to the first auxiliary plate 71, and limit rods 115 are provided on both sides of the trigger rod 114, one end of the two limit rods 115 is provided on the adjacent sliding plate 113, and the other end thereof is slidably provided on the first auxiliary plate 71, an auxiliary frame 116 is provided on the first auxiliary plate 71, and a plurality of push rods 117 are slidably provided in the auxiliary frame 116, one end of each of the plurality of push rods 117 is provided on the adjacent sliding plate 113, and the other end thereof is provided on the outer side of the corresponding arc-shaped plate 4, and a return spring 118 is provided on the outer side of each of the plurality of push rods 117, one end of each of the plurality of return springs 118 is provided on the adjacent sliding plate 113, and the other end thereof is provided on the outer side of the auxiliary frame 116, and when the second transmission plate 92 at the top of the first auxiliary plate 71 moves to contact with the corresponding trigger rod 114, the plurality of second transmission plates 92 will be slowed down. The trigger rod 114 is slowly pushed to the corresponding trigger rod 114. When the trigger rod 114 is pushed, the trigger rod 114 will push the sliding plate 113 at one end thereof. Under the action of the sliding groove 112, the sliding plate 113 at one end of the trigger rod 114 will squeeze the gas to the other sliding plate 113, so that a sliding plate 113 close to the push rod 117 moves, and then the sliding plate 113 located above pushes the push rod 117, so that the push rod 117 pushes the arc plate 4 at one end thereof. When the arc plate 4 moves, the arc plate 4 will squeeze the outer wall of the aviation thin-walled structural member. Under the action of multiple rubber blocks 102, the aviation thin-walled structural member will be compressed. The bottom of the thin-walled structural part is fixed on the first auxiliary plate 71. The limiting rod 115 slidably arranged in the first auxiliary plate 71 can limit the position of the trigger rod 114 when the second transmission plate 92 pushes the trigger rod 114, so as to avoid the movement angle of the trigger rod 114 from being offset. The reset spring 118 arranged on the outside of the push rod 117 can control the two sliding plates 113 to reset after the second transmission plate 92 releases the squeezing of the trigger rod 114. Its function is to enable the arc plate 4 to move through the mutual squeezing of the two sliding plates 113, so as to squeeze and fix the outer wall of the aviation thin-walled structural part.

[0043] The adsorption member 12 includes a fixed plate 121 arranged on the top of the second transmission plate 92, a rotating rod 122 is rotatably arranged in the fixed plate 121, a gear 123 is arranged on the outer side of the rotating rod 122, and the gear 123 is located in the fixed plate 121, a rubber pad 124 is arranged on the side of the fixed plate 121 away from the second transmission plate 92, a plate 125 is slidably arranged in the fixed plate 121, a plurality of tooth grooves 126 used in conjunction with the gear 123 are opened on the plate 125, an extrusion spring 127 is arranged in the fixed plate 121, one end of the extrusion spring 127 is arranged in the fixed plate 121, and the other end of the extrusion spring 127 is arranged at one end of the plate 125, a rubber pad 2 128 is arranged on the end of the plate 125 away from the extrusion spring 127, and the two ends of the rotating rod 122 are provided with a plurality of tooth grooves 126 used in conjunction with the gear 123. The two ends are provided with rotating plates 129, the tops of the two rotating plates 129 are provided with control plates 1210, the tops of the two control plates 1210 are provided with rubber plates 1211, a plurality of suction cups 3 are provided on the corresponding rotating plates 129, and the bottoms of the two rotating plates 129 are provided with micro air pumps 1212 used in conjunction with the plurality of suction cups 3. When the second transmission plate 92 on the second auxiliary plate 73 slides in the limiting groove 93 in the second auxiliary plate 73, the second transmission plate 92 will drive the fixed plate 121 on its top to move together. When the plate 125 sliding in the fixed plate 121 follows the fixed plate 121 to move and bear against the inner wall of the cylindrical aviation thin-walled structure, the rubber pad 124 at one end of the plate 125 can prevent the plate 125 from contacting the cylindrical aviation thin-walled structure. The thin-walled inner wall produces rigid contact, and then the second transmission plate 92 will continue to push the fixed plate 121, and at this time the plate 125 will slide in the fixed plate 121. When the plate 125 slides in the fixed plate 121, the plate 125 will make the gear 123 used in conjunction with it rotate through the multiple tooth grooves 126 on its top. When the gear 123 rotates, the rotating rod 122 set at the axis of the gear 123 will rotate with the gear 123. When the rotating rod 122 rotates, the rotating rod 122 will drive the rotating plates 129 at both ends to rotate, so that the two rotating plates 129 drive the suction cup 3 on the top thereof to move, so that the suction cup 3 is adsorbed on the inner wall of the conical aviation thin-walled structure. At this time, the rubber pad 121 set on one side of the fixed plate 121 28 is fitted with the inner wall of the cylindrical aviation thin-walled structural part, so that the top of the cylindrical aviation thin-walled structural part is fixed, and then the micro air pump 1212 starts to work, so that the air in the suction cup 3 is sucked out, and then the suction cup 3 is tightly adsorbed on the inner wall of the conical aviation thin-walled structural part. When the rotating plate 129 drives the suction cup 3 to move, the control board 1210 arranged on the top thereof will move together with the rotating plate 129, and the rubber plate 1211 on the top of the control board 1210 will be pressed against the inner wall of the conical aviation thin-walled structural part. As the micro air pump 1212 works, the conical aviation thin-walled structural part is firmly fixed. Its function is to firmly fix the conical aviation thin-walled structural part on the top of the cylindrical aviation thin-walled structural part, which is convenient for subsequent friction welding.

[0044] When in use, the staff first places the cylindrical aviation thin-walled structural part on the top of the first auxiliary plate 71, and then puts the conical aviation thin-walled structural part on the top of the cylindrical aviation thin-walled plate. At this time, turn on the motor 61. When the motor 61 starts to work, the motor 61 will drive the screw 62 at its output end to rotate. When the screw 62 starts to rotate, the first drive plate 63 and the second drive plate 64 are rotatably connected to the first transmission plate 91 through the rotating shaft, so that the first drive plate 63 and the second drive plate 64 are driven by the screw 62 to perform lifting and lowering movements. When the first drive plate 63 and the second drive plate 64 descend, the first drive plate 63 and the second drive plate 64 will drive multiple first transmission plates 91 on their outer sides to move downward. When the first transmission plate 91 follows the second drive plate 63, the second drive plate 64 will move downward. When the first driving plate 63 and the second driving plate 64 move downward, since the first transmission plate 91 is rotatably connected with the first driving plate 63 and the second driving plate 64 through the rotating shaft, and the first transmission plate 91 is rotatably connected with the second transmission plate 92 through the rotating shaft, the first transmission plate 91 pushes the second transmission plate 92 under the action of the first driving plate 63 and the second driving plate 64. Since the second transmission plate 92 is slidably arranged in the limiting groove 93, the plurality of second transmission plates 92 are respectively slid in the limiting grooves 93 provided in the corresponding first auxiliary plate 71 and the second auxiliary plate 73 under the action of the plurality of first transmission plates 91. When the plurality of second transmission plates 92 located at the top of the first auxiliary plate 71 slide in the corresponding limiting grooves 93, the second transmission plates 92 will The extrusion plate 101 at the top thereof is driven to move together. When the extrusion plate 101 moves, the extrusion plate 101 drives the rubber blocks 102 at both ends thereof to move together, so that the two rubber blocks 102 squeeze the inner wall of the aviation thin-walled structural member and push the aviation thin-walled structural member, so that the axis of the aviation thin-walled structural member is located at the same place as the axis of the first auxiliary plate 71. When the second transmission plate 92 at the top of the first auxiliary plate 71 moves to contact with the corresponding trigger rod 114, the plurality of second transmission plates 92 will slowly push the corresponding trigger rod 114. When the trigger rod 114 is pushed, the trigger rod 114 will push the sliding plate 113 at one end thereof. Under the action of the sliding groove 112, the sliding plate 113 at one end of the trigger rod 114 will squeeze the gas to the other The sliding plate 113 moves a sliding plate 113 close to the push rod 117, thereby causing the sliding plate 113 located above to push the push rod 117, so that the push rod 117 pushes the arc plate 4 at one end thereof. When the arc plate 4 moves, the arc plate 4 will squeeze the outer wall of the aviation thin-walled structural component. Under the action of multiple rubber blocks 102, the bottom of the aviation thin-walled structural component is fixed on the first auxiliary plate 71. The limiting rod 115 slidingly arranged in the first auxiliary plate 71 can limit the position of the trigger rod 114 when the second transmission plate 92 pushes the trigger rod 114, so as to avoid the movement angle of the trigger rod 114 from being offset. The return spring 118 arranged on the outer side of the push rod 117 can release the squeezing of the trigger rod 114 by the second transmission plate 92.Control the two sliding plates 113 to reset;

[0045] When the second transmission plate 92 on the second auxiliary plate 73 slides in the limiting groove 93 in the second auxiliary plate 73, the second transmission plate 92 will drive the fixed plate 121 on its top to move together, and when the plate 125 sliding in the fixed plate 121 follows the movement of the fixed plate 121 and presses against the inner wall of the cylindrical aviation thin-walled structure, the rubber pad 2 128 at one end of the plate 125 can prevent the plate 125 from having a rigid contact with the inner wall of the cylindrical aviation thin-walled structure, and then, the second transmission plate 92 will continue to push the fixed plate 121, at this time, the plate 125 will slide in the fixed plate 121, when the plate 125 slides in the fixed plate 121, the plate 125 will make the gear 123 used in conjunction with it rotate through the multiple tooth grooves 126 on its top, and when the gear 123 rotates, the rotating rod 122 set at the axis of the gear 123 will rotate with the gear 123, and when the rotating rod 122 rotates When the rotating plate 129 moves, the rotating rod 122 will drive the rotating plates 129 at both ends to rotate, so that the two rotating plates 129 drive the suction cups 3 on the top to move, so that the suction cups 3 are adsorbed on the inner wall of the conical aviation thin-walled structure. At this time, the rubber pad 124 arranged on one side of the fixed plate 121 fits with the inner wall of the cylindrical aviation thin-walled structure, so that the top of the cylindrical aviation thin-walled structure is fixed, and then the micro air pump 1212 starts to work, so that the air in the suction cup 3 is extracted, and then the suction cup 3 is tightly adsorbed on the inner wall of the conical aviation thin-walled structure. When the rotating plate 129 drives the suction cup 3 to move, the control board 1210 arranged on the top thereof will move with the rotating plate 129, and the rubber plate 1211 on the top of the control board 1210 is pressed against the inner wall of the conical aviation thin-walled structure. With the operation of the micro air pump 1212, the conical aviation thin-walled structure is firmly fixed.

[0046] Embodiment 2

[0047] See also Fig.10 , the present invention provides a technical solution:

[0048] Different from Example 1, multiple grooves 13 are opened on the top of the multiple rubber plates 1211. The grooves 13 on the rubber plates 1211 can increase the friction between the rubber plates 1211 and the inner wall of the conical aviation thin-walled structural component, so that the conical aviation thin-walled structural component will not rotate or other deflection movements occur, ensuring stability during the welding process.

[0049] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0050] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A friction welding device for aviation thin-walled structural parts, comprising a base plate (1) and a support frame (2) above the base plate (1), characterized in that: Also includes A plurality of suction cups (3) are provided, and the plurality of suction cups (3) are all arranged above the support frame (2) and are used to absorb the aviation thin-walled structural parts to be welded; A plurality of arc-shaped plates (4) are provided, and the plurality of arc-shaped plates (4) are all provided between the support frame (2) and the plurality of suction cups (3), and are used for extruding aviation thin-walled structural parts; A fixing mechanism (5) is arranged above the support frame (2), and the fixing mechanism (5) is used to control the movement of the plurality of curved plates (4) and the plurality of suction cups (3), so as to drive the plurality of curved plates (4) to extrude the aviation thin-walled structural parts, and control the plurality of suction cups (3) to adsorb the aviation thin-walled structural parts; The fixing mechanism (5) comprises a driving member (6) arranged on the support frame (2), and the driving member (6) is used to provide power for the movement of the plurality of curved plates (4) and the plurality of suction cups (3); an auxiliary member (7) is arranged above the support frame (2), and the auxiliary member (7) is used to assist the plurality of suction cups (3) and the plurality of curved plates (4) in fixing the aviation thin-walled structural member; a clamping assembly (8) is arranged above the support frame (2), and the clamping assembly (8) is used to clamp the aviation thin-walled structural member; The driving member (6) comprises a motor (61) arranged on the bottom plate (1), a screw rod (62) being arranged at an output end of the motor (61), and the motor (61) and the screw rod (62) are both located at the axis of the support frame (2), a first driving plate (63) is arranged on the screw rod (62), a second driving plate (64) is arranged on the screw rod (62), and the first driving plate (63) and the second driving plate (64) are both threadedly connected to the screw rod (62), and the second driving plate (64) is located above the first driving plate (63); The auxiliary component (7) comprises a first auxiliary plate (71) arranged on the top of the support frame (2); a plurality of support plates (72) are arranged on the top of the first auxiliary plate (71); a second auxiliary plate (73) is arranged on the top of the plurality of support plates (72); the screw rod (62) is arranged through the first auxiliary plate (71) and the second auxiliary plate (73) at the axis center; the first drive plate (63) is located between the first auxiliary plate (71) and the second auxiliary plate (73); and the second drive plate (64) is located above the second auxiliary plate (73); The clamping assembly (8) comprises transmission members (9) respectively arranged on the outside of the first auxiliary plate (71) and the second auxiliary plate (73), and used for transmitting power for the movement of the plurality of arc-shaped plates (4) and the plurality of suction cups (3); a plurality of extrusion members (10) are arranged above the first auxiliary plate (71), and the plurality of extrusion members (10) are used to control the aviation thin-walled structural member and the first auxiliary plate (71) to be located at the same axis; a plurality of pneumatic members (11) are arranged on the first auxiliary plate (71), and the plurality of pneumatic members (11) are used to control the movement of the corresponding arc-shaped plates (4), so that the plurality of arc-shaped plates (4) are respectively pressed against the outer wall of the aviation thin-walled structural member; a plurality of adsorption members (12) are arranged above the second auxiliary plate (73), and the plurality of adsorption members (12) are used to control the movement of the corresponding suction cups (3), so that the plurality of suction cups (3) are respectively adsorbed against the inner wall of the aviation thin-walled structural member; The transmission member (9) comprises a plurality of first transmission plates (91) which are respectively rotatably arranged on the outer sides of the first drive plate (63) and the second drive plate (64) via a rotating shaft, and a second transmission plate (92) is rotatably arranged at one end of the plurality of first transmission plates (91) away from the first drive plate (63) and the second drive plate (64) via a rotating shaft, and a plurality of limiting grooves (93) are respectively provided in the first auxiliary plate (71) and the second auxiliary plate (73), and the plurality of second transmission plates (92) are respectively slidably arranged in the first auxiliary plate (71) and the second auxiliary plate (73) via corresponding limiting grooves (93); The extrusion member (10) comprises an extrusion plate (101) arranged on the top of the second transmission plate (92), and rubber blocks (102) are arranged at both ends of the extrusion plate (101); The pneumatic member (11) comprises a pneumatic plate (111) arranged on the first auxiliary plate (71), a sliding groove (112) being provided in the pneumatic plate (111), two sliding plates (113) being slidably provided in the sliding groove (112), and the two sliding plates (113) being respectively located at two ends of the pneumatic plate (111), and a trigger rod (114) for use with the second transmission plate (92) being provided on a side of the lower one of the two sliding plates (113) close to the first auxiliary plate (71), and limit rods (115) being provided on both sides of the trigger rod (114), and the two limit rods (115) One end of the push rods (117) is arranged on an adjacent sliding plate (113), and the other end of the push rods (117) is slidably arranged in a first auxiliary plate (71); an auxiliary frame (116) is arranged on the first auxiliary plate (71); a plurality of push rods (117) are slidably arranged in the auxiliary frame (116); one end of each of the push rods (117) is arranged on an adjacent sliding plate (113), and the other end of each of the push rods (117) is arranged on the outside of a corresponding arc-shaped plate (4); a return spring (118) is arranged on the outside of each of the push rods (117); one end of each of the return springs (118) is arranged on an adjacent sliding plate (113), and the other end of each of the return springs (118) is arranged on the outside of the auxiliary frame (116).

2. The friction welding device for aviation thin-walled structural parts according to claim 1, characterized in that: The adsorption member (12) comprises a fixed plate (121) arranged on the top of the second transmission plate (92); a rotating rod (122) is rotatably arranged in the fixed plate (121); a gear (123) is arranged on the outside of the rotating rod (122), and the gear (123) is located in the fixed plate (121); a rubber pad (124) is arranged on the side of the fixed plate (121) away from the second transmission plate (92); a plate (125) is slidably arranged in the fixed plate (121); a plurality of tooth grooves (126) are provided on the plate (125) for use with the gear (123); a compression spring (127) is arranged in the fixed plate (121); One end of the extrusion spring (127) is arranged in the fixed plate (121), and the other end thereof is arranged at one end of the plate one (125); a rubber pad two (128) is arranged at one end of the plate one (125) away from the extrusion spring (127); rotating plates (129) are arranged at both ends of the rotating rod (122); control plates (1210) are arranged at the top of the two rotating plates (129); rubber plates (1211) are arranged at the top of the two control plates (1210); the plurality of suction cups (3) are arranged on corresponding rotating plates (129); and micro air pumps (1212) used in conjunction with the plurality of suction cups (3) are arranged at the bottom of the two rotating plates (129).

3. The friction welding device for aviation thin-walled structural parts according to claim 2, characterized in that: A plurality of grooves (13) are formed on the tops of the plurality of rubber plates (1211).

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