Fine machining device for hinge hole of plug-in type door of airplane

Abstract

The invention provides an aircraft plug-in type door hinge hole finish machining device, which relates to the technical field of aircraft structure design, and comprises a door frame bracket, a door hinge mounting bracket, a door hinge mounting bracket, a door hinge mounting bracket and a door hinge mounting bracket, and is characterized in that the door frame bracket is used for pre-mounting an aircraft door frame and mounting a door hinge on the aircraft door frame; the clamping assembly comprises a clamping connector, a driving assembly and at least two locking assemblies, the driving assembly is located on one side of the door frame support, the locking assemblies are installed at the power output end of the driving assembly, and the clamping connector sequentially penetrates through the locking assemblies to be movably connected with the power output end of the driving assembly; the reaming assembly is located on the side, away from the door frame support, of the driving assembly. The driving assembly drives the clamping connector to adaptively position and clamp the door hinge in the length direction, the width direction and the height direction. According to the finish machining device provided by the invention, the accuracy of the axial position of the hinge hole can be ensured, so that the matching degree between an aircraft door and an aircraft door frame after assembly is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft structure design, in particular to a precision machining device for aircraft ear-insertion type door hinge holes. Background Art

[0002] The ear-type door hinge joint is widely used in the aerospace industry. The hinge joint is the key point connecting the door and the fuselage, and bears the weight of the entire door.

[0003] The hinge holes of existing aircraft hinges cannot achieve precise axial processing according to the spatial orientation of the aircraft door frame during fine processing, resulting in the inability of the processed hinge holes to match the aircraft door for installation, or causing technical problems such as the inability of the aircraft door and the aircraft door frame to accurately match after installation. Summary of the invention

[0004] In view of the shortcomings of the prior art described above, an object of the present invention is to provide a device for fine-machining hinge holes of aircraft plug-in door, which is used to solve the problem that the hinge holes of aircraft hinges in the prior art cannot be precisely axially machined according to the spatial orientation of the aircraft door frame during fine machining, resulting in the inability to match the machined hinge holes with the aircraft door for installation, or the inability to precisely match the aircraft door with the aircraft door frame after installation.

[0005] To achieve the above-mentioned object and other related objects, the present invention provides a device for finishing the hole of an aircraft plug-in door hinge, comprising: a door frame bracket, the door frame bracket is used to pre-install the aircraft door frame and install the door hinge on the aircraft door frame; a clamping assembly, the clamping assembly comprises a clamping joint, a driving assembly and at least two locking assemblies, the driving assembly is located on one side of the door frame bracket, the locking assembly is installed at the power output end of the driving assembly, the clamping joint passes through each locking assembly in turn and is movably connected with the power output end of the driving assembly; and a reaming assembly, the reaming assembly is located on one side of the driving assembly away from the door frame bracket; wherein, after the driving assembly drives the clamping joint to adaptively position and clamp the door hinge in the length, width and height directions, the locking assembly locks the position of the clamping joint relative to the power output end of the driving assembly, and then the door hinge is removed from the aircraft door frame, and the driving assembly drives the door hinge clamped by the clamping joint to reach the working area of ​​the reaming assembly for fine reaming.

[0006] In one embodiment of the present invention, a plurality of bolt holes for mounting the aircraft door frame are provided on the door frame bracket.

[0007] In one embodiment of the present invention, the clamping joint includes an upper plug and a lower plug, the door hinge includes an upper hinge and a lower hinge, the upper plug corresponds to the upper hinge, and the lower plug corresponds to the lower hinge.

[0008] In one embodiment of the present invention, the clamping joint includes: a plug, a locking groove corresponding to the hinge head of the door hinge is provided on the plug, and the end of the plug is provided with chamfers in multiple directions corresponding to the door hinge; a joint rod, one end of the joint rod is connected to the plug, and one end of the joint rod is connected to a guide ball; and a guide seat, the guide seat is movably installed at the power output end of the drive assembly, a guide groove corresponding to the guide ball is opened on one side of the guide seat, and the guide ball sleeve is arranged in the guide groove.

[0009] In one embodiment of the present invention, the plug includes: a connector body; and a first locking power member, the first locking power member is installed on the outer wall of the connector body, and the power output end of the first locking power member extends through the connector body into the locking groove to lock the side wall of the hinge head in the locking groove.

[0010] In one embodiment of the present invention, the driving assembly includes: an upper support; a driving base, which is arranged below the upper support, and the power output end of the driving base is connected to the bottom of the upper support to drive the upper support to rotate; a pushing power member, which is installed on the top of the upper support; and a linkage support, which is installed at the power output end of the pushing power member, the clamping joint is movably connected to the middle part of the linkage support, and the locking assembly is connected to the outside of the linkage support.

[0011] In one embodiment of the present invention, the linkage support includes: a moving seat, an adjustment groove is provided on one side of the moving seat, one end of the clamping joint is movably arranged in the adjustment groove, and a first spring is provided in the adjustment groove, and one end of the clamping joint is connected to the inner wall of the adjustment groove through the first spring; a second locking power member, the second locking power member is installed on the other side of the moving seat, and the power output end of the second locking power member extends through the moving seat into the adjustment groove to lock the position of one end of the clamping joint in the adjustment groove; an insertion rod, one end of the insertion rod is connected to the moving seat; a sleeve, one end of the sleeve is connected to the power output end of the pushing power member, and the other end of the sleeve is provided with a slot, and the other end of the insertion rod is movably inserted in the slot; a second spring, the second spring is sleeved on the insertion rod, and one end of the second spring is connected to the moving seat, and the other end of the second spring is connected to the end of the sleeve; and an inductive locking assembly, the inductive locking assembly is installed on the sleeve, so that when the pushing power member drives the clamping joint to press the hinge head end surface of the door hinge, and the moving seat reaches a set position close to the end of the sleeve, the insertion rod is locked on the sleeve.

[0012] In one embodiment of the present invention, the inductive locking assembly includes: a pressure sensor, which is mounted on a sleeve, and a pressure sensing connector of the pressure sensor extends out of the end of the sleeve; and a third locking power member), which is mounted on the sleeve, and a power output end of the third locking power member extends through the side wall of the sleeve into the slot, so that when the pressure sensor collects a pressure signal, the side surface of the insertion rod in the slot is pressed by the third locking power member.

[0013] In one embodiment of the present invention, the locking assembly includes: a locking seat, in which a plurality of first hinge joints are arranged; a third spring, one end of the third spring is movably connected to the locking seat through the first hinge joint, and the other end of the third spring is connected to the second hinge joint; a first pressure rod, a second hinge joint of a part of the third spring is installed on the first pressure rod, and the first pressure rod is arranged on both sides of the clamping joint along the thickness direction of the hinge head of the door hinge; a second pressure rod, a second hinge joint of a part of the third spring is installed on the second pressure rod, the second pressure rod is arranged on one side of the first pressure rod, and the second pressure rod is arranged on both sides of the clamping joint along the length direction of the hinge head of the door hinge; a clamping frame plate, a group of clamping frame plates is arranged on one side of the first pressure rod, and the other group of clamping frame plates is arranged on one side of the second pressure rod; wherein a group of clamping frame plates includes two clamping frame plates arranged symmetrically; and a clamping power assembly, the clamping power assembly is installed on the locking seat, and the power output end of the clamping power assembly is connected to the clamping frame plate to simultaneously drive the two clamping frame plates to move toward each other, and clamp and lock the first pressure rod and the second pressure rod.

[0014] In one embodiment of the present invention, the clamping power assembly includes: a screw rod, a plurality of screw rods are rotatably mounted on a locking seat, and the screw rod threads pass through each clamping frame plate arranged along the length direction of the clamping joint; and a driving motor, the driving motor is mounted on the locking seat, and the power output end of the driving motor is connected to one end of the screw rod.

[0015] As described above, the aircraft plug-in door hinge hole finishing device of the present invention has the following beneficial effects: through the mutual cooperation among the driving component, the clamping joint and the door frame bracket, it can be realized that after the aircraft door frame and the door hinge are installed on the door frame bracket in sequence, the clamping joint can be driven by the driving component to realize that the clamping joint can be adaptively positioned along the length, width and height directions of the door hinge to ensure that the clamping joint can fully match the specific orientation of the door hinge after installation; and through the mutual cooperation among the driving component, the clamping joint and the locking component, it can be realized that after the position of the clamping joint is determined, the driving component and the locking component can clamp the door hinge. The specific position of the holding joint is locked, so that the clamping joint after the locking position carries the door hinge under the drive of the driving assembly to the working area where the reaming assembly is located, so as to realize the fine processing after the isolation between the door hinge and the aircraft door frame, thereby not only ensuring the accuracy of the axial position of the hinge hole of the door hinge when the door hinge is installed on the aircraft door frame, but also solving the problems of slight deformation and damage of the aircraft door frame due to vibration, pressure and the like caused by reaming directly on the aircraft door frame, and also solving the problems of damage and pollution to the aircraft door frame caused by metal scraps ejected to the aircraft door frame when reaming directly on the aircraft door frame. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram showing the overall structure of the finishing device of the present invention.

[0017] Figure 2 Shown is an enlarged schematic diagram of the structure of a clamping assembly provided by an embodiment of the present invention.

[0018] Figure 3 Shown is a schematic structural diagram of a clamping joint and a locking assembly provided in one embodiment of the present invention.

[0019] Figure 4 The display is provided by an embodiment of the present invention Figure 3 Schematic diagram of the structure after the middle locking component is cut open.

[0020] Figure 5 A diagram showing the structural coordination of a clamping joint and a locking assembly provided in one embodiment of the present invention is shown.

[0021] Figure 6 The display is provided by an embodiment of the present invention Figure 5 Enlarged schematic diagram at point A in the middle.

[0022] Figure 7 Shown is a schematic structural diagram of a linkage support provided in one embodiment of the present invention. DETAILED DESCRIPTION

[0023] See also Figure 1 The present invention provides a device for finishing a hole of an aircraft plug-in door hinge, comprising: a door frame bracket 1, the door frame bracket 1 is used for pre-installing an aircraft door frame and installing a door hinge 10 on the aircraft door frame; a clamping assembly 2, the clamping assembly 2 comprises a clamping joint 21, a driving assembly 22 and at least two locking assemblies 23, the driving assembly 22 is located at one side of the door frame bracket 1, the locking assembly 23 is installed at the power output end of the driving assembly 22, the clamping joint 21 sequentially passes through each locking assembly 23 and is movably connected with the power output end of the driving assembly 22; and a reaming assembly 3, the reaming assembly 3 is located at a side of the driving assembly 22 away from the door frame bracket 1; wherein, after the driving assembly 22 drives the clamping joint 21 to adaptively position and clamp the door hinge in the length, width and height directions, the locking assembly 23 locks the position of the clamping joint 21 relative to the power output end of the driving assembly 22, and then the door hinge 10 is removed from the aircraft door frame, and the door hinge 10 clamped by the clamping joint 21 driven by the driving assembly 22 reaches the working area of ​​the reaming assembly 3 for fine reaming.

[0024] It is not difficult to find from the above content that when the hinge hole of the aircraft plug-in hinge is finely processed after the pre-processing is completed, the aircraft door frame corresponding to the aircraft door can be first installed on the door frame bracket 1, and then the corresponding door hinge 10 can be installed on the corresponding edge side of the aircraft door frame. After the door hinge 10 is pre-installed on the aircraft door frame, the driving component 22 of the clamping component 2 can drive the clamping joint 21 to move to the door hinge 10. Through the driving action of the driving component 22, the clamping joint 21 can be adaptively positioned along the length direction, width direction and height direction of the door hinge 10. After the positioning of the clamping joint 21 is completed, the locking component 23 installed at the power output end of the driving component 22 will lock the position of the clamping joint 21 relative to the power output end of the driving component 22, and then the door hinge 10 is removed from the aircraft door frame. After the door hinge 10 is removed from the aircraft door frame, the driving assembly 22 will drive the clamping joint 21 and the door hinge 10 after the position is locked to move to the reaming assembly 3, so that the door hinge 10 can be subjected to secondary precision reaming processing after the corresponding position relationship with the aircraft door frame is determined by the reaming assembly 3, thereby not only ensuring the accuracy of the axial position of the hinge hole of the door hinge 10 when the door hinge 10 is installed on the aircraft door frame, but also solving the problem that the aircraft door frame will be slightly deformed and damaged due to vibration, pressure, etc. when the hole is directly reamed on the aircraft door frame, and solving the problem that the aircraft door frame is damaged and contaminated due to the ejection of metal scraps to the aircraft door frame when the hole is directly reamed on the aircraft door frame.

[0025] It is worth noting that when the reaming assembly 3 performs fine reaming on the delivered door hinge 10, the position of the drill bit of the reaming assembly 3 is pre-adjusted according to the position of the door frame bracket 1 and the position of the aircraft door frame positioned and installed on the door frame bracket 1.

[0026] like Figure 1 As shown, the door frame bracket 1 is provided with a plurality of bolt holes 11 for mounting the aircraft door frame. In this embodiment, through the bolt holes 11 opened on the door frame bracket 1, the aircraft door frame can be positioned and mounted on the door frame bracket 1 by bolts or other means as needed.

[0027] Preferably, the clamping joint 21 includes an upper plug and a lower plug, and the door hinge 10 includes an upper hinge and a lower hinge, the upper plug corresponds to the upper hinge, and the lower plug corresponds to the lower hinge.

[0028] See also Figure 2 , Figure 2 In one embodiment, the door hinge 10 comprises a hinge seat 101 and a hinge head 102. The door hinge 10 can be connected to an aircraft door frame via the hinge seat 101.

[0029] In this embodiment, after the upper hinge and the lower hinge are installed on the aircraft door frame, the upper plug and the lower plug can be respectively inserted into the upper hinge and the lower hinge to achieve simultaneous finishing of the upper hinge and the lower hinge.

[0030] like Figure 3 and Figure 5 As shown, the clamping joint 21 includes: a plug 211, a locking groove 2111 corresponding to the hinge head 102 of the door hinge 10 is provided on the plug 211, and the end of the plug 211 is provided with chamfers in multiple directions corresponding to the door hinge 10; a joint rod 212, one end of the joint rod 212 is connected to the plug 211, and one end of the joint rod 212 is connected to a guide ball 213; and a guide seat 214, the guide seat 214 is movably mounted on the power output end of the driving assembly 22, and a guide groove corresponding to the guide ball 213 is opened on one side of the guide seat 214, and the guide ball 213 is sleeved in the guide groove.

[0031] like Figure 5 As shown, the plug 211 includes: a connector body 2112; and a first locking power member 2113, the first locking power member 2113 is installed on the outer wall of the connector body 2112, and the power output end of the first locking power member 2113 extends through the connector body 2112 to the locking groove 2111 to lock the side wall of the hinge head 102 in the locking groove 2111.

[0032] In this embodiment, when the plug 211 is positioned and inserted into the door hinge 10, it is inserted into the two sides of the hinge head 102 through the locking grooves 2111 on the joint body 2112, and the side walls of the joint body 2112 are closely attached to the side walls of the hinge seat 101, so that the plug 211 can position the hinge in all directions. After the plug 211 has positioned the door hinge 10, the first locking power member 2113 drives its power output end so that its power output end is pressed against the surface of the hinge head 102 in the locking groove 2111, so that the door hinge 10 is locked on the joint body 2112 through the first locking power member 2113. The first locking power member 2113 can be a cylinder or a push rod motor.

[0033] like Figure 2 As shown, the driving assembly 22 includes: an upper support 221; a driving base 222, which is arranged below the upper support 221, and the power output end of the driving base 222 is connected to the bottom of the upper support 221 to drive the upper support 221 to rotate; a pushing power member 223, which is installed on the top of the upper support 221; and a linkage support 224, which is installed at the power output end of the pushing power member 223, the clamping joint 21 is movably connected to the middle part of the linkage support 224, and the locking assembly 23 is connected to the outer side of the linkage support 224.

[0034] In one embodiment of the present invention, when the driving assembly 22 drives the clamping joint 21 to move, the upper support 221 can be driven to rotate by driving the rotating base 222, so as to drive the clamping joint 21 and the door hinge 10 to rotate, so as to transport the door hinge 10 from the door frame bracket 1 to the reaming assembly 3 for reaming. Moreover, when the clamping joint 21 positions the door hinge 10, the pushing power member 223 will also push the clamping joint 21 to move toward the door hinge 10, so as to fully position the clamping joint 21 on the door hinge 10, and after the clamping joint 21 is fully positioned on the door hinge 10, the linkage support 224 will also complete self-locking, so as to realize that when the linkage support 224 is in a self-locking state, the pushing power member 223 and the clamping joint 21 and the door hinge 10 are driven to rotate by the rotating base 222. Among them, a servo motor is installed on the rotating base 222, and the rotating base 222 is connected to the upper support 221 through the power output end of the servo motor. The pushing power member 223 can be a cylinder or a push rod motor.

[0035] like Figure 3 and Figure 7 As shown, the linkage support 224 includes: a moving seat 2241, one side of the moving seat 2241 is provided with an adjustment groove 22411, one end of the clamping joint 21 is movably arranged in the adjustment groove 22411, and a first spring is provided in the adjustment groove 22411, and one end of the clamping joint 21 is connected to the inner wall of the adjustment groove 22411 through the first spring; a second locking power piece 2242, the second locking power piece 2242 is installed on the other side of the moving seat 2241, and the power output end of the second locking power piece 2242 passes through the moving seat 2241 and extends into the adjustment groove 22411 to lock the position of one end of the clamping joint 21 in the adjustment groove 22411; an insert rod 2243, one end of the insert rod 2243 is connected to the moving seat 2241; a sleeve 2244 , one end of the sleeve 2244 is connected to the power output end of the pushing power piece 223, and the other end of the sleeve 2244 is provided with a slot, and the other end of the insertion rod 2243 is movably inserted in the slot; a second spring 2245, the second spring 2245 is sleeved on the insertion rod 2243, and one end of the second spring 2245 is connected to the moving seat 2241, and the other end of the second spring 2245 is connected to the end of the sleeve 2244; and an inductive locking component 2246, the inductive locking component 2246 is installed on the sleeve 2244, so that when the pushing power piece 223 drives the clamping joint 21 to press the end surface of the hinge head 102 of the door hinge 10, and the moving seat 2241 reaches a set position close to the end of the sleeve 2244, the insertion rod 2243 is locked on the sleeve 2244.

[0036] In one embodiment of the present invention, when the linkage support 224 is connected to the power output end of the push power member 223 and the clamping joint 21 respectively, the end of the clamping joint 21 is movably connected through the adjustment groove 22411 provided in the movable seat 2241, so that the end of the clamping joint 21 can slide freely up and down and left and right in the adjustment groove 22411. In addition, in the adjustment groove 22411, the end of the clamping joint 21 is also connected to the inner wall of the adjustment groove 22411 through the first spring, so that when the end of the clamping joint 21 is in a free state, it can return to the middle of the adjustment groove 22411. Moreover, after the end of the clamping joint 21 is adaptively adjusted in the adjustment groove 22411, the second locking power member 2242 can pass through the side wall of the movable seat 2241 to reach the adjustment groove 22411, and contact with the end of the clamping joint 21, so as to lock the end of the clamping joint 21. The second locking power member 2242 can be a cylinder or a push rod motor. On the other side of the moving seat 2241, the plug rod 2243 is movably inserted into the sleeve 2244 connected to the power output end of the pushing power member 223, so that the pushing power member 223 generates a thrust, so that when the clamping joint 21 is pressed toward the end side surface of the hinge head 102, the second spring 2245 is in a compressed state, and when the induction locking component 2246 senses that the moving seat 2241 reaches the set position close to the end of the sleeve 2244, the plug rod 2243 will be controlled to be locked on the sleeve 2244.

[0037] Furthermore, the inductive locking assembly 2246 includes: a pressure sensor 22461, which is mounted on the sleeve 2244 and a pressure sensing connector 224611 of the pressure sensor 22461 extends out of the end of the sleeve 2244; and a third locking power member 22462, which is mounted on the sleeve 2244 and a power output end of the third locking power member 22462 extends through the side wall of the sleeve 2244 into the slot, so that when the pressure sensor 22461 collects a pressure signal, the side surface of the insertion rod 2243 in the slot is pressed by the third locking power member 22462.

[0038] In one embodiment of the present invention, when the movable seat 2241 moves toward one side of the sleeve 2244 and contacts the pressure sensor 22461 on the sleeve 2244, the power output end of the third locking power member 22462 is controlled by the controller to extend through the side wall of the sleeve 2244 into the slot, so as to achieve a pressing operation on the side surface of the insertion rod 2243 in the slot, so as to lock the relative positions of the insertion rod 2243 and the sleeve 2244.

[0039] like Figures 4 to 6As shown, the locking assembly 23 includes: a locking seat 231, in which a plurality of first hinge joints 2311 are arranged; a third spring 232, one end of the third spring 232 is movably connected to the locking seat 231 through the first hinge joint 2311, and the other end of the third spring 232 is connected to the second hinge joint 2321; a first pressure rod 233, on which the second hinge joint 2321 of a part of the third spring 232 is installed, and the first pressure rod 233 is arranged on both sides of the clamping joint 21 along the thickness direction of the hinge head 102 of the door hinge 10; a second pressure rod 234, on which the second hinge joint 2321 of a part of the third spring 232 is installed, and the second pressure rod 234 4 is arranged on one side of the first pressure rod 233, and the second pressure rod 234 is arranged on both sides of the clamping joint 21 along the length direction of the hinge head 102 of the door hinge 10; a clamping frame plate 235, one group of clamping frame plates 235 is arranged on one side of the first pressure rod 233, and the other group of clamping frame plates 235 is arranged on one side of the second pressure rod 234; wherein one group of clamping frame plates 235 includes two clamping frame plates 235 arranged symmetrically; and a clamping power assembly 236, the clamping power assembly 236 is installed on the locking seat 231, and the power output end of the clamping power assembly 236 is connected to the clamping frame plates 235, so as to simultaneously drive the two clamping frame plates 235 to move toward each other, and compress and lock the first pressure rod 233 and the second pressure rod 234.

[0040] In one embodiment of the present invention, when the locking assembly 23 locks the relative position of the clamping joint 21 and the driving assembly 22, after the clamping joint 21 adaptively completes the insertion and positioning of the door hinge 10, the end of the clamping joint 21 close to the power output end of the driving assembly 22 is also adaptively adjusted in space. At the same time, the first pressure rod 233 and the second pressure rod 234 are respectively under the elastic force of the third spring 232, and after the spatial position of the clamping joint 21 is adjusted, they can still be adaptively pressed on the circumferential side surface of the clamping joint 21. After the first pressure rod 233 and the second pressure rod 234 are pressed against the circumferential side surface of the clamping joint 21, the clamping frame plates 235 located on both sides of the first pressure rod 233 and the second pressure rod 234 can move toward each other through the power of the clamping power assembly 236, so that one side of the clamping frame plate 235 is pressed against one side of the first pressure rod 233, and one side of the other clamping frame plate 235 is pressed against one side of the second pressure rod 234. At the same time, the first pressure rod 233 and the second pressure rod 234 are also pressed and locked against each other, so as to realize the position locking of the clamping joint 21 after the orientation of the door hinge 10 is adaptively adjusted. Specifically, the first pressure rod 233 and the second pressure rod 234 can be arranged perpendicular to each other, and the surface cross section of the clamping joint 21 corresponding to the first pressure rod 233 and the second pressure rod 234 in contact with each other is rectangular.

[0041] like Figure 4As shown, the clamping power assembly 236 includes: a screw rod 2361, a plurality of screw rods 2361 are rotatably mounted on the locking seat 231, and the screw rods 2361 are threaded through each clamping frame plate 235 arranged along the length direction of the clamping joint 21; and a driving motor 2362, the driving motor 2362 is mounted on the locking seat 231, and the power output end of the driving motor 2362 is connected to one end of the screw rod 2361.

[0042] In one embodiment of the present invention, when the clamping power assembly 236 drives the clamping frame plates 235 to move toward each other, the drive motor 2362, which is preferably a servo motor, can drive the screw rod 2361 to rotate, thereby realizing the movement of the two clamping frame plates 235 arranged oppositely and threadedly connected with the screw rod 2361. The connection threads of the two clamping frame plates 235 arranged oppositely and the screw rod 2361 are mutually reverse threads.

[0043] See also Figure 1 ,exist Figure 1 In one embodiment, the reaming assembly 3 includes a reaming bracket 31, a driving device 32 slidably disposed on the reaming bracket 31, a drill rod 33 mounted on the power output end of the driving device 32, and a lifting power member 34 mounted on the reaming bracket 31 and having its power output end connected to the top of the driving device 32, so as to realize that the driving device 32 is driven to move up and down by the lifting power member 34, and the drilling rod 33 is driven to rotate by the driving device 32, so as to perform fine reaming on the door hinge 10. Among them, the lifting power member 34 can be a cylinder; the driving device 32 can include a driving motor and an adjusting mechanism. The drilling rod 33 can be driven to rotate by a driving motor which is preferably a servo motor, and the driving motor is mounted on the power output end of the adjusting mechanism, so as to realize adjusting the position of the driving motor by the adjusting mechanism, so as to adapt to the position fine adjustment when the aircraft door frame is finely reamed. The adjusting mechanism can be a combination of a ball screw and a servo motor, so as to be threadedly connected to the driving motor by the ball screw, so as to drive the driving motor to move and adjust the position. Since there are many forms of similar adjusting mechanisms, it is sufficient to adjust the position of the driving motor, which will not be described in detail here.

[0044] In summary, the present invention discloses an aircraft plug-in door hinge hole finishing device. Through the cooperation among the driving component 22, the clamping joint 21 and the door frame bracket 1, after the aircraft door frame and the door hinge 10 are sequentially installed on the door frame bracket 1, the clamping joint 21 can be driven by the driving component 22 to realize adaptive positioning of the clamping joint 21 along the length, width and height of the door hinge 10, so as to ensure that the clamping joint 21 can fully match the specific orientation of the door hinge 10 after installation; and through the cooperation among the driving component 22, the clamping joint 21 and the locking component 23, after the position of the clamping joint 21 is determined, the driving component 22 and the locking component 23 can be used to realize the precision machining of the aircraft plug-in door hinge hole. 3 can lock the specific position of the clamping joint 21, so that the clamping joint 21 after the locking position carries the door hinge 10 under the drive of the driving assembly 22 to reach the working area where the reaming assembly 3 is located, so as to achieve the fine processing after the door hinge 10 and the aircraft door frame are isolated, so as to not only ensure the accuracy of the axial position of the hinge hole of the door hinge 10 when the door hinge 10 is installed on the aircraft door frame, but also solve the problems that the aircraft door frame will be slightly deformed and damaged due to vibration, pressure and other effects when the aircraft door frame is directly reamed, and can also solve the problems that the aircraft door frame is damaged and polluted due to the ejection of metal scraps to the aircraft door frame when the aircraft door frame is directly reamed. Therefore, the present invention effectively overcomes various shortcomings in the prior art and has a high industrial utilization value.

[0045] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A device for fine machining of hinge holes for aircraft ear-insertion door, characterized in that: include: A door frame bracket (1), wherein the door frame bracket (1) is used to pre-install an aircraft door frame and to install a door hinge (10) on the aircraft door frame; A clamping assembly (2), the clamping assembly (2) comprising a clamping joint (21), a driving assembly (22) and at least two locking assemblies (23), the driving assembly (22) being located on one side of the door frame bracket (1), the locking assembly (23) being installed at the power output end of the driving assembly (22), the clamping joint (21) sequentially passing through each of the locking assemblies (23) to be movably connected to the power output end of the driving assembly (22); and a reaming assembly (3), the reaming assembly (3) being located on a side of the driving assembly (22) away from the door frame bracket (1); Wherein, after the driving component (22) drives the clamping joint (21) to adaptively position and clamp the door hinge in the length, width and height directions, the locking component (23) locks the position of the clamping joint (21) relative to the power output end of the driving component (22), and then the door hinge (10) is removed from the aircraft door frame, and the driving component (22) drives the door hinge (10) clamped by the clamping joint (21) to reach the working area of ​​the reaming component (3) for fine reaming.

2. The aircraft ear-insertion door hinge hole finishing device according to claim 1, characterized in that: The door frame bracket (1) is provided with a plurality of bolt holes (11) for mounting an aircraft door frame.

3. The aircraft ear-insertion door hinge hole finishing device according to claim 1, characterized in that: The clamping joint (21) comprises an upper plug and a lower plug, and the door hinge (10) comprises an upper hinge and a lower hinge, the upper plug corresponds to the upper hinge, and the lower plug corresponds to the lower hinge.

4. The aircraft ear-insertion door hinge hole finishing device according to claim 1, characterized in that: The clamping joint (21) comprises: A plug (211), wherein the plug (211) is provided with a locking groove (2111) corresponding to the hinge head (102) of the door hinge (10), and an end of the plug (211) is provided with chamfers in multiple directions corresponding to the door hinge (10); A joint rod (212), one end of which is connected to the plug (211), and one end of which is connected to a guide ball (213); and a guide seat (214), the guide seat (214) being movably mounted on the power output end of the drive assembly (22), a guide groove corresponding to the guide ball (213) being formed on one side of the guide seat (214), and the guide ball (213) being sleeved in the guide groove.

5. The aircraft ear-insertion door hinge hole finishing device according to claim 4, characterized in that: The plug (211) comprises: A joint body (2112); and a first locking power member (2113), wherein the first locking power member (2113) is mounted on an outer side wall of the joint body (2112), and a power output end of the first locking power member (2113) extends through the joint body (2112) into the locking groove (2111) to lock the side wall of the hinge head (102) in the locking groove (2111).

6. The aircraft ear-insertion door hinge hole finishing device according to claim 1, characterized in that: The driving assembly (22) comprises: Upper support (221); A driving and rotating base (222), wherein the driving and rotating base (222) is disposed below the upper support (221), and a power output end of the driving and rotating base (222) is connected to the bottom of the upper support (221) to drive the upper support (221) to rotate; A pushing power piece (223), the pushing power piece (223) is mounted on the top of the upper support (221); and a linkage support (224), the linkage support (224) is mounted on the power output end of the pushing power piece (223), the clamping joint (21) is movably connected to the middle of the linkage support (224), and the locking assembly (23) is connected to the outer side of the linkage support (224).

7. The aircraft ear-insertion door hinge hole finishing device according to claim 6, characterized in that: The linkage support (224) comprises: A movable seat (2241), wherein an adjusting groove (22411) is provided on one side of the movable seat (2241), one end of the clamping joint (21) is movably arranged in the adjusting groove (22411), and a first spring is provided in the adjusting groove (22411), and one end of the clamping joint (21) is connected to an inner wall of the adjusting groove (22411) via the first spring; a second locking power member (2242), the second locking power member (2242) being mounted on the other side of the movable seat (2241), and a power output end of the second locking power member (2242) extending through the movable seat (2241) into the adjusting slot (22411) to lock the position of one end of the clamping joint (21) in the adjusting slot (22411); An insertion rod (2243), one end of the insertion rod (2243) being connected to the movable seat (2241); A sleeve (2244), one end of the sleeve (2244) being connected to the power output end of the pushing power member (223), the other end of the sleeve (2244) being provided with a slot, and the other end of the insertion rod (2243) being movably inserted into the slot; a second spring (2245), wherein the second spring (2245) is sleeved on the insertion rod (2243), and one end of the second spring (2245) is connected to the movable seat (2241), and the other end of the second spring (2245) is connected to the end of the sleeve (2244); and an inductive locking component (2246), wherein the inductive locking component (2246) is installed on the sleeve (2244) so ​​as to lock the insertion rod (2243) on the sleeve (2244) when the pushing power member (223) drives the clamping joint (21) to press the end surface of the hinge head (102) of the door hinge (10) and the movable seat (2241) reaches a set position close to the end of the sleeve (2244).

8. The aircraft ear-insertion door hinge hole finishing device according to claim 7, characterized in that: The inductive locking assembly (2246) comprises: A pressure sensor (22461), wherein the pressure sensor (22461) is mounted on the sleeve (2244), and a pressure sensing connector (224611) of the pressure sensor (22461) extends out of the end of the sleeve (2244); and a third locking power member (22462), wherein the third locking power member (22462) is mounted on the sleeve (2244), and a power output end of the third locking power member (22462) extends through the side wall of the sleeve (2244) into the slot, so that when the pressure sensor (22461) collects a pressure signal, the side surface of the insertion rod (2243) in the slot is pressed by the third locking power member (22462).

9. The aircraft ear-insertion door hinge hole finishing device according to claim 1, characterized in that: The locking assembly (23) comprises: A locking seat (231), wherein a plurality of first hinge joints (2311) are provided in the locking seat (231); a third spring (232), one end of the third spring (232) being movably connected to the locking seat (231) via the first hinge joint (2311), and the other end of the third spring (232) being connected to the second hinge joint (2321); a first pressure rod (233), a second hinge joint (2321) of a portion of the third spring (232) being mounted on the first pressure rod (233), the first pressure rod (233) being arranged on both sides of the clamping joint (21) along the thickness direction of the hinge head (102) of the door hinge (10); a second pressure rod (234), a second hinge joint (2321) of a portion of the third spring (232) being mounted on the second pressure rod (234), the second pressure rod (234) being arranged on one side of the first pressure rod (233), and the second pressure rod (234) being arranged on both sides of the clamping joint (21) along the length direction of the hinge head (102) of the door hinge (10); A clamping frame plate (235), wherein one group of the clamping frame plates (235) is arranged on one side of the first pressure rod (233), and another group of the clamping frame plates (235) is arranged on one side of the second pressure rod (234); wherein one group of the clamping frame plates (235) comprises two symmetrically arranged clamping frame plates (235); and a clamping power assembly (236), wherein the clamping power assembly (236) is mounted on the locking seat (231), and a power output end of the clamping power assembly (236) is connected to the clamping frame plates (235) to simultaneously drive the two clamping frame plates (235) to move toward each other, thereby pressing and locking the first pressure rod (233) and the second pressure rod (234).

10. The aircraft ear-insertion door hinge hole finishing device according to claim 9, characterized in that: The clamping power assembly (236) comprises: A screw rod (2361), wherein a plurality of the screw rods (2361) are rotatably mounted on the locking seat (231), and the screw rods (2361) are threadedly passed through each of the clamping frame plates (235) arranged along the length direction of the clamping joint (21); and a driving motor (2362), wherein the driving motor (2362) is mounted on the locking seat (231), and a power output end of the driving motor (2362) is connected to one end of the screw rod (2361).

Images