An aircraft plug-in ear type door hinge hole finish machining device

Abstract

The present invention provides a fine machining device for the hinge holes of aircraft plug-in ear type door hinges, which relates to the technical field of aircraft structural design and includes: a door frame bracket for pre-installing an aircraft door frame and installing door hinges on the aircraft door frame; a clamping assembly including 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 assemblies are installed at the power output end of the driving assembly, and the clamping joint sequentially passes through each locking assembly and is movably connected to the power output end of the driving assembly; and a reaming assembly located on the side of the driving assembly away from the door frame bracket. Among them, the driving assembly drives the clamping joint to perform adaptive positioning and clamping on the door hinge in the length, width, and height directions. The fine machining device provided by the present invention can ensure the accuracy of the axial position of the hinge holes, thereby improving the matching degree after the assembly between the aircraft door and the aircraft door frame.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft structure design, and particularly to a fine machining device for the hinge holes of aircraft lug-type door hinges. Background Art

[0002] Lug-type door hinge joints are widely used in the aerospace industry. Since the hinge joint is the key point where the cabin door is connected to the fuselage and bears the weight of the entire cabin door.

[0003] During the fine machining of the hinge holes of existing aircraft hinges, accurate axial machining cannot be achieved according to the spatial orientation of the aircraft door frame, resulting in technical problems that the processed hinge holes cannot be matched and installed with the aircraft door, or the aircraft door and the aircraft door frame cannot be accurately matched after installation. Summary of the Invention

[0004] In view of the above-mentioned disadvantages of the prior art, the purpose of the present invention is to provide a fine machining device for the hinge holes of aircraft lug-type door hinges, which is used to solve the problem that during the fine machining of the hinge holes of aircraft hinges in the prior art, accurate axial machining cannot be achieved according to the spatial orientation of the aircraft door frame, resulting in the processed hinge holes not being able to be matched and installed with the aircraft door, or the aircraft door and the aircraft door frame not being able to be accurately matched after installation.

[0005] To achieve the above purpose and other related purposes, the present invention provides a fine machining device for the hinge holes of aircraft lug-type door hinges, including: a door frame support for pre-installing the aircraft door frame and installing the door hinge on the aircraft door frame; a clamping assembly including a clamping joint, 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 joint sequentially passes through each locking assembly and is movably connected to the power output end of the driving assembly; and a reaming assembly located on the side of the driving assembly away from the door frame support; wherein, after the driving assembly drives the clamping joint to perform adaptive positioning and clamping on the door hinge in the length, width, and height directions, the locking assemblies lock the position of the clamping joint relative to the power output end of the driving assembly, 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 an embodiment of the present invention, a plurality of bolt holes for installing the aircraft door frame are provided on the door frame support.

[0007] In an 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 an embodiment of the present invention, the clamping joint includes: a plug, on which a locking groove corresponding to the hinge head of the door hinge is provided, and chamfers in multiple directions corresponding to the door hinge are provided at the end of the plug; a joint rod, one end of the joint rod is connected to the plug, and a guide ball is connected to one end of the joint rod; and a guide seat, the guide seat is movably installed at the power output end of the driving assembly, a guide groove corresponding to the guide ball is provided on one side of the guide seat, and the guide ball is sleeved in the guide groove.

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

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

[0011] In an 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 arranged 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 passes through the moving seat and extends into the adjustment groove to lock the position of one end of the clamping joint in the adjustment groove; a plug rod, one end of the plug 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, a slot is provided at the other end of the sleeve, and the other end of the plug rod is movably inserted into the slot; a second spring, the second spring is sleeved on the plug 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 induction locking assembly, the induction locking assembly is installed on the sleeve to lock the plug rod on the sleeve when the pushing power member drives the clamping joint to press the end surface of the hinge head of the door hinge and the moving seat reaches a set position close to the end of the sleeve.

[0012] In an embodiment of the present invention, the induction locking assembly includes: a pressure sensor, the pressure sensor is installed on the sleeve, and the pressure sensing joint of the pressure sensor extends out of the end of the sleeve; and a third locking power member), the third locking power member) is installed on the sleeve, and the power output end of the third locking power member) passes through the side wall of the sleeve and extends into the slot to press the side surface of the plug rod in the slot through the third locking power member) when the pressure sensor collects a pressure signal.

[0013] In an embodiment of the present invention, the locking assembly includes: a locking seat, in which a plurality of first hinge joints are provided; 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 with a second hinge joint; a first pressure rod, the second hinge joints of a part of the third spring are 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, the second hinge joints of a part of the third spring are 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, one 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, one group of clamping frame plates includes two symmetrically arranged clamping frame plates; 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 with the clamping frame plate to simultaneously drive the two clamping frame plates to move towards each other to tightly press and lock the first pressure rod and the second pressure rod.

[0014] In an embodiment of the present invention, the clamping power assembly includes: a lead screw, a plurality of lead screws are rotatably installed on the locking seat, and the lead screws thread through each clamping frame plate arranged along the length direction of the clamping joint; and a driving motor, the driving motor is installed on the locking seat, and the power output end of the driving motor is connected with one end of the lead screw.

[0015] As described above, the fine machining device for the hinge hole of the aircraft ear-type door hinge of the present invention has the following beneficial effects: through the mutual cooperation among the driving assembly, the clamping joint and the door frame bracket, after the aircraft door frame and the door hinge are sequentially installed on the door frame bracket, by driving the clamping joint through the driving assembly, 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 completely match the specific orientation of the door hinge after installation; then, through the mutual cooperation among the driving assembly, the clamping joint and the locking assembly, after the position of the clamping joint is determined, the driving assembly and the locking assembly can lock the specific position of the clamping joint, so that the clamping joint carrying the door hinge can reach the working area where the hinge hole assembly is located under the drive of the driving assembly after the position is locked, so as to realize the fine machining after the isolation between the door hinge and the aircraft door frame, which can not only ensure 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 solve the problems that the aircraft door frame will also bear vibrations, pressures, etc. when directly reaming holes on the aircraft door frame, resulting in slight deformation, damage, etc. of the aircraft door frame, and can also solve the problems that metal chips are ejected onto the aircraft door frame when directly reaming holes on the aircraft door frame, resulting in damage and pollution of the aircraft door frame. 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 an aircraft plug-in door hinge hole, comprising: a door frame bracket 1, the door frame bracket 1 is used to pre-install an aircraft door frame and install 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 on 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 passes through each locking assembly 23 and the power output end of the driving assembly 22 in sequence Active connection; and a reaming assembly 3, which is located on 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 10 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 driving assembly 22 drives the door hinge 10 clamped by the clamping joint 21 to reach the working area of ​​the reaming assembly 3 for fine reaming.

[0024] It is not difficult to find from the above that when finishing the hinge holes after the preprocessing of the aircraft plug-in hinge, 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 respectively. 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 will be removed from the aircraft door frame. After the door hinge 10 is removed from the aircraft door frame, the driving component 22 will drive the clamped joint 21 and the door hinge 10 with the position locked to move to the reaming component 3, so that the reaming component 3 can perform secondary precise reaming processing on the door hinge 10 after determining the corresponding position relationship with the aircraft door frame. This can 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 also be subjected to vibrations, pressures, etc. when directly reaming on the aircraft door frame, resulting in slight deformation and damage of the aircraft door frame, and can also solve the problems that metal chips are ejected onto the aircraft door frame when directly reaming on the aircraft door frame, resulting in damage and pollution of the aircraft door frame.

[0025] It should be noted that when the reaming component 3 performs fine reaming on the conveyed door hinge 10, the position of the drill bit of the reaming component 3 has been 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] As Figure 1 shown, a plurality of bolt holes 11 for installing the aircraft door frame are provided on the door frame bracket 1. In this embodiment, through each bolt hole 11 opened on the door frame bracket 1, the aircraft door frame can be positioned and installed on the door frame bracket 1 by means of bolts as required.

[0027] Preferably, the clamping joint 21 includes an upper plug and a lower plug, 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] Please refer to Figure 2 , Figure 2 In an embodiment shown, the door hinge 10 includes a hinge seat 101 and a hinge head 102. The door hinge 10 can be connected to the aircraft door frame through the hinge seat 101.

[0029] In this embodiment, after both 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 finish machining of the upper hinge and the lower hinge.

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

[0031] As Figure 5 shown, the plug 211 includes: a joint body 2112; and a first locking power member 2113, the first locking power member 2113 is installed on the outer side wall of the joint body 2112, and the power output end of the first locking power member 2113 passes through the joint body 2112 and extends into 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 on both sides of the hinge head 102 through the locking groove 2111 on the joint body 2112, and the side wall of the joint body 2112 is closely attached to the side wall of the hinge seat 101, so as to realize the all-round positioning of the plug 211 on the hinge. And after the plug 211 finishes positioning the door hinge 10, through the driving action of the first locking power member 2113 on its power output end, its power output end is pressed against the surface of the hinge head 102 in the locking groove 2111, so as to realize locking the door hinge 10 on the joint body 2112 through the first locking power member 2113. Among them, the first locking power member 2113 can be one of a cylinder and a push rod motor.

[0033] As Figure 2 shown, the driving assembly 22 includes: an upper support 221; a driving base 222, the driving base 222 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, the pushing power member 223 is installed on the top of the upper support 221; and a linkage support 224, the linkage support 224 is installed at the power output end of the pushing power member 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 outside of the linkage support 224.

[0034] In an 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 rotating the base 222, so as to drive the clamping joint 21 and the door hinge 10 to rotate, and convey the door hinge 10 from the door frame bracket 1 to the hinge hole assembly 3 for hinge hole processing. 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 towards the door hinge 10, so as to fully position the clamping joint 21 on the door hinge 10. Moreover, after the clamping joint 21 is fully positioned on the door hinge 10, the linkage support 224 will complete self-locking, so as to drive the pushing power member 223, the clamping joint 21 and the door hinge 10 to rotate when the linkage support 224 is in the self-locked state. 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 one of a cylinder and a push rod motor.

[0035] As Figure 3 and Figure 7 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 arranged 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 member 2242, the second locking power member 2242 is installed on the other side of the moving seat 2241, and the power output end of the second locking power member 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; a plug rod 2243, one end of the plug 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 member 223, the other end of the sleeve 2244 is provided with a slot, and the other end of the plug rod 2243 is movably inserted into the slot; a second spring 2245, the second spring 2245 is sleeved on the plug 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 induction locking assembly 2246, the induction locking assembly 2246 is installed on the sleeve 2244 to lock the plug 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 moving seat 2241 reaches a set position close to the end of the sleeve 2244.

[0036] In an embodiment of the present invention, when the linkage support 224 is respectively connected to the power output end of the pushing power member 223 and the clamping joint 21, an adjustment groove 22411 is formed in its moving seat 2241 to achieve an active connection to the end of the clamping joint 21, so that the end of the clamping joint 21 can freely slide up, down, left, and right in the adjustment groove 22411. And 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 a 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 adaptively adjusts its position in the adjustment groove 22411, the second locking power member 2242 can pass through the side wall of the moving seat 2241 and reach the adjustment groove 22411, and contact the end of the clamping joint 21 to lock the end of the clamping joint 21. Among them, the second locking power member 2242 can be one of a cylinder and a push rod motor. On the other side of the moving seat 2241, the insertion rod 2243 is movably inserted into the sleeve 2244 connected to the power output end of the pushing power member 223, so that when the pushing power member 223 generates a thrust force to press the clamping joint 21 against the side surface of the hinge head 102 end, the second spring 2245 is in a compressed state, and when the induction locking assembly 2246 senses that the moving seat 2241 reaches the set position near the end of the sleeve 2244, it will control to lock the insertion rod 2243 on the sleeve 2244.

[0037] Further, the induction locking assembly 2246 includes: a pressure sensor 22461, the pressure sensor 22461 is installed on the sleeve 2244, and the pressure sensing joint 224611 of the pressure sensor 22461 extends out of the end of the sleeve 2244; and a third locking power member 22462, the third locking power member 22462 is installed on the sleeve 2244, and the power output end of the third locking power member 22462 passes through the side wall of the sleeve 2244 and extends 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 an embodiment of the present invention, when the moving seat 2241 moves toward the sleeve 2244 side and the moving seat 2241 contacts the pressure sensor 22461 on the sleeve 2244, at this time, the controller controls the power output end of the third locking power member 22462 to pass through the side wall of the sleeve 2244 and extend into the slot, so as to perform a pressing operation on the side surface of the insertion rod 2243 in the slot, so as to lock the relative position of the insertion rod 2243 and the sleeve 2244.

[0039] As Figures 4 to 6As shown, the locking component 23 includes: a locking seat 231, in which a plurality of first hinge joints 2311 are provided; 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 with a second hinge joint 2321; a first pressing rod 233, the second hinge joint 2321 of a part of the third spring 232 is installed on the first pressing rod 233, and the first pressing 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 pressing rod 234, the second hinge joint 2321 of a part of the third spring 232 is installed on the second pressing rod 234, the second pressing rod 234 is arranged on one side of the first pressing rod 233, and the second pressing 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, a set of clamping frame plates 235 is arranged on one side of the first pressing rod 233, and another set of clamping frame plates 235 is arranged on one side of the second pressing rod 234; wherein, a set of clamping frame plates 235 includes two symmetrically arranged clamping frame plates 235; 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 with the clamping frame plate 235 to simultaneously drive the two clamping frame plates 235 to move towards each other, so as to tightly press and lock the first pressing rod 233 and the second pressing rod 234.

[0040] In an embodiment of the present invention, when the locking component 23 locks the relative positions of the clamping joint 21 and the driving component 22, after the clamping joint 21 adaptively completes the insertion and positioning of the door hinge 10, one end of the clamping joint 21 close to the power output end of the driving component 22 also undergoes an adaptive spatial position adjustment. At the same time, under the elastic force of the third spring 232, after the spatial position of the clamping joint 21 is adjusted, the first pressing rod 233 and the second pressing rod 234 can still adaptively press against the circumferential side surface of the clamping joint 21. And after the first pressing rod 233 and the second pressing rod 234 are tightly attached to the circumferential side surface of the clamping joint 21, through the power action of the clamping power assembly 236, the clamping frame plates 235 located on both sides of the first pressing rod 233 and the second pressing rod 234 can move towards each other, so that one side of a clamping frame plate 235 presses against one side of the first pressing rod 233, and one side of another clamping frame plate 235 presses against one side of the second pressing rod 234. At the same time, the first pressing rod 233 and the second pressing rod 234 are also tightly pressed and locked with each other, so as to lock the position of the clamping joint 21 that has been adaptively adjusted following the orientation of the door hinge 10. Specifically, the first pressing rod 233 and the second pressing rod 234 can be perpendicularly arranged, and the cross-section of the surface of the clamping joint 21 corresponding to the contact with the first pressing rod 233 and the second pressing rod 234 is rectangular.

[0041] As Figure 4As shown, the clamping power assembly 236 includes: a lead screw 2361. A plurality of lead screws 2361 are rotatably installed on the locking seat 231, and the lead screws 2361 thread 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 installed on the locking seat 231, and the power output end of the driving motor 2362 is connected to one end of the lead screw 2361.

[0042] In an embodiment of the present invention, when the clamping power assembly 236 drives the clamping frame plates 235 to move towards each other, the driving motor 2362 preferably a servo motor can drive the lead screw 2361 to rotate, so as to realize the relative arrangement of the two clamping frame plates 235 threadedly connected to the lead screw 2361 to move towards each other. Among them, the connection threads of the two relatively arranged clamping frame plates 235 and the lead screw 2361 are reverse threads to each other.

[0043] Please refer to Figure 1 , in Figure 1 In an embodiment given, the reaming assembly 3 includes a reaming bracket 31, a driving device 32 slidably arranged on the reaming bracket 31, a drill rod 33 installed on the power output end of the driving device 32, and a lifting power member 34 installed on the reaming bracket 31 and having a power output end connected to the top of the driving device 32, so as to realize driving the driving device 32 to move up and down by the lifting power member 34, and driving the drill rod 33 to rotate by the driving device 32 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 driving motor preferably a servo motor can drive the drill rod 33 to rotate, and the driving motor is installed on the power output end of the adjusting mechanism, so as to realize adjusting the position of the driving motor by the adjusting mechanism to adapt to the position fine adjustment during the fine reaming of the aircraft door frame. The adjusting mechanism can be a connection combination of a ball screw and a servo motor, so as to drive the driving motor to move and adjust the position by threadedly connecting the ball screw to the driving motor. Since there are many implementation forms of similar adjusting mechanisms, as long as the position of the driving motor can be adjusted, it will not be elaborated here.

[0044] In summary, for the fine machining device for the hinge holes of the plug-in ear type door hinge of an aircraft disclosed in the present invention, through the mutual cooperation among the driving assembly 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, by driving the clamping joint 21 through the driving assembly 22, the clamping joint 21 can be adaptively positioned in each direction of the length, width, and height of the door hinge 10, so as to ensure that the clamping joint 21 can completely match the specific orientation of the door hinge 10 after installation; then, through the mutual cooperation among the driving assembly 22, the clamping joint 21, and the locking assembly 23, after the position of the clamping joint 21 is determined, the specific position of the clamping joint 21 can be locked through the driving assembly 22 and the locking assembly 23, so that the clamping joint 21 carrying the door hinge 10 after the position is locked can reach the working area where the reaming assembly 3 is located under the drive of the driving assembly 22, so as to realize the fine machining after the isolation between the door hinge 10 and the aircraft door frame. Therefore, not only can the accuracy of the axial position of the hinge hole of the door hinge 10 be ensured when the door hinge 10 is installed on the aircraft door frame, but also the problems that the aircraft door frame will be subjected to vibrations, pressures, etc. when directly reaming on the aircraft door frame, resulting in slight deformation, damage, etc. of the aircraft door frame can be solved, and the problems that metal chips are ejected onto the aircraft door frame when directly reaming on the aircraft door frame, resulting in damage and pollution of the aircraft door frame can be solved. Therefore, the present invention effectively overcomes various disadvantages in the prior art and has high industrial utilization value.

[0045] The above embodiments are only illustrative of the principles and effects of the present invention, and are not used to limit the present invention. Any person familiar with this technology can modify or change the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or changes completed by those with ordinary knowledge in the technical field without departing from the spirit and technical ideas disclosed by the present invention should 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 a 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 (10) 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; 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 the joint rod (212) being connected to the plug (211), and one end of the joint rod (212) being connected to a guide ball (213); and A guide seat (214) is movably mounted on the power output end of the drive assembly (22); a guide groove corresponding to the guide ball (213) is formed on one side of the guide seat (214); and the guide ball (213) is sleeved in the guide groove.

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 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).

5. The aircraft ear-insertion door hinge hole finishing device according to claim 1, characterized in that: The driving assembly (22) comprises: an 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).

6. The aircraft ear-insertion door hinge hole finishing device according to claim 5, 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).

7. The aircraft ear-insertion door hinge hole finishing device according to claim 6, 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).

8. 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).

9. The aircraft ear-insertion door hinge hole finishing device according to claim 8, 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).

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