CN103978270A - Fine machining device and fine machining method of airplane inserting lug type door hinge hole - Google Patents
Fine machining device and fine machining method of airplane inserting lug type door hinge hole Download PDFInfo
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- CN103978270A CN103978270A CN201410193523.2A CN201410193523A CN103978270A CN 103978270 A CN103978270 A CN 103978270A CN 201410193523 A CN201410193523 A CN 201410193523A CN 103978270 A CN103978270 A CN 103978270A
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Abstract
The invention discloses a fine machining device of an airplane inserting lug type door hinge hole. The fine machining device comprises a supporting tool, a hinge joint locating tool and a cutter, wherein the hinge joint locating tool is provided with a support, an upper hinge joint locating mechanism and a lower hinge joint locating mechanism, the upper hinge joint locating mechanism comprises a drill plate I, a drill plate II, a control block I and a locating pin I, the drill plate I and the drill plate II are fixedly connected to the support, and the control block I is positioned between the drill plate I and the drill plate II and is movably connected with the support; the lower hinge joint locating mechanism comprises a drill plate III, a drill plate IV, a control block II and a locating pin II, the drill plate III and the drill plate IV are fixedly connected to the support, and the control block II is positioned between the drill plate III and the drill plate IV and is movably connected with the support; the cutter is of an integrated structure and is sequentially provided with a front guiding rod, a first cutting edge, a second cutting edge and a rear guiding rod from top to bottom. The invention also discloses a fine machining method by utilizing the fine machining device of the airplane inserting lug type door hinge hole. According to the fine machining method disclosed by the invention, the coaxial degree of the airplane inserting lug type door hinge hole is ensured, and the machining efficiency and the machining quality of the airplane inserting lug type door hinge hole are increased.
Description
Technical field
Aircraft of the present invention is inserted ear formula hinge hole precise machining device and method, is mainly used in aircraft to insert the fine finishining of ear formula hinge nipple orifice.
Background technology
At present, insert the extensive use aspect aerospace industry of ear formula hinge joint.Because knuckle joint is the key point that hatch door is connected with fuselage, and bear the weight of whole hatch door, so knuckle joint generally all adopts high strength steel, stainless steel, titanium alloy etc materials manufacture.Taking 15-5PH stainless steel as example, its hardness ratio is higher, for machining, more difficult, while being mainly reflected in drilling, cutting force is large, cutting temperature is high, the easy heat expansion in sticky cutter, bad chip breaking, hole, can cause the abrasive wear of drilling inefficiency, cutter serious, cannot ensure the problems such as hole quality; And require axiality higher for slotting ear formula hinge nipple orifice, and be mainly in order better to coordinate with the knuckle joint on hatch door, make hatch door more level and smooth in the process of opening the door and closing the door, thereby increase the service life of knuckle joint.Aircraft is inserted not only complex structure of Er Shimen, and the space of carrying out hinge hole is also very narrow and small, therefore will ensure that the axiality between hinge hole is the very difficult technical problem facing at present.
Summary of the invention
Insert in order to solve current aircraft of low quality that ear formula hinge hole exists, cannot reach the problem of axiality, the invention provides a kind of aircraft and insert Er Shimen hinge hole precise machining device and method for fine finishing, the method has improved the drilling efficiency of hinge hole, ensures the quality of hinge hole and the requirement to axiality.
For achieving the above object, the technical solution used in the present invention is:
Aircraft is inserted ear formula hinge hole precise machining device, comprises supporting tool, knuckle joint positioning tool, cutter;
Described knuckle joint positioning tool has support, upper hinge joint location mechanism and underneath hinges joint location mechanism, upper hinge joint location mechanism comprises the bushing plate I that is fixed on support, bushing plate II, the controll block I and the alignment pin I that between bushing plate I and bushing plate II and with support, are flexibly connected, in bushing plate I and bushing plate II, have respectively through hole I and through hole II, alignment pin I matches with through hole I, through hole II; Underneath hinges detent mechanism comprises the bushing plate III that is cemented on support, bushing plate IV, the controll block II and the alignment pin II that between bushing plate III and bushing plate IV and with support, are flexibly connected, in bushing plate III and bushing plate IV, have respectively through hole III and through hole IV, alignment pin II matches with through hole III, through hole IV; Through hole II is identical with the aperture of through hole IV, and through hole I is identical with the aperture of through hole III;
Described cutter is structure as a whole, and is once provided with from top to bottom the front guide post coordinating with through hole II and IV, the first cutting edge, the second cutting edge, the rear guide post coordinating with through hole I and III.
Described cutter also comprises extension rod, and extension rod and rear guide post detachable are fastenedly connected, and the diameter of extension rod is identical with the diameter of front guide post.
The diameter of described the first cutting edge is less than the diameter of the second cutting edge.
Described alignment pin I and alignment pin II are stepped positioning pin.
Described cutter is staged cutter.
Utilize aircraft described above to insert ear formula hinge hole precise machining device and carry out a method for fine finishing, it is characterized in that:
A. first doorway frame and aircraft lower half shell are fixed, then adopted supporting tool to support doorway frame, then the upper half shell of aircraft is connected with the lower half shell of aircraft;
B. knuckle joint positioning tool is moved to doorway frame fixing, upper articulation joint location mechanism is coordinated with the upper hinge joint on the frame of doorway, the slotting ear upper arm I of upper hinge joint and slotting ear underarm I are placed between bushing plate I and bushing plate II, controll block I is between slotting ear upper arm I and slotting ear underarm I, insert in ear upper arm I and there is knuckle joint hole I, insert in ear underarm I and have knuckle joint hole II, alignment pin I is successively through through hole I, knuckle joint hole I, knuckle joint hole II and through hole II; Lower hinge joint location mechanism coordinates with the underneath hinges joint on the frame of doorway, the slotting ear upper arm II of underneath hinges joint and slotting ear underarm II are placed between bushing plate III and bushing plate IV, controll block II is between slotting ear upper arm II and slotting ear underarm II, insert in ear upper arm II and there is knuckle joint hole III, insert in ear underarm II and have knuckle joint hole IV, alignment pin II is successively through through hole III, knuckle joint hole III, knuckle joint hole IV and through hole IV; Controll block I coordinates with the lower surface of slotting ear upper arm I, and controll block II coordinates with the lower surface of slotting ear upper arm II, determines the accurate location of inserting ear arm upper hinge nipple orifice;
C. fraising, the alignment pin I of dismantling and alignment pin II, the front guide post of cutter is penetrated to through hole I, knuckle joint hole I, knuckle joint hole II and through hole II, start to cut with scissors knuckle joint hole I and knuckle joint hole II simultaneously, be hinged after the knuckle joint hole I and knuckle joint hole II of upper hinge joint, cutter is pulled down, by extension rod, penetrate successively through hole I, knuckle joint hole I, after knuckle joint hole II and through hole II, mounting cutter on extension rod, again the front guide post of cutter is penetrated to through hole III and knuckle joint hole III, knuckle joint hole IV and through hole IV, start to cut with scissors knuckle joint hole III and knuckle joint hole IV simultaneously.
Preferably, described step c, in fraising process, is coated with lubricating oil on cutter with hairbrush, and useless the cutting that fraising is derived drained.
Preferably, described step c adopts auto-feed brill or the manual air drill of high-power to be connected and to ream with cutter.
The present invention has following beneficial effect:
1, aircraft is inserted ear formula hinge hole precise machining device by being provided with supporting tool, and knuckle joint positioning tool and cutter have ensured the axiality of slotting ear formula hinge nipple orifice, ensure crudy and the efficiency in knuckle joint hole simultaneously.
2, the extension rod of cutter is set, has solved the less difficult problem that is difficult to ream operation in the space of reaming on the frame of doorway.
3, due to the aperture difference in knuckle joint hole, therefore adopt stepped positioning pin box staged cutter, contribute to accurate location, accurately fraising.
4, one utilizes the slotting ear formula hinge of aircraft hole precise machining device to carry out method for finishing manufactured, adopts supporting tool to support doorway frame and ensures that doorway frame is indeformable; Adopt knuckle joint positioning tool accurately to locate the knuckle joint hole of doorway frame, adopt alignment pin to ensure X and the Y direction of knuckle joint simultaneously, controll block I and controll block II are for ensureing the Z-direction of knuckle joint, to guarantee position degree and the axiality in frame knuckle joint hole, doorway.Fraising time, the front guide post of cutter and rear guide post are taken up in order of priority and are coordinated with bushing plate II, bushing plate IV and bushing plate I, bushing plate III, while fraising for cutter, lead, guarantee knuckle joint hole machining accuracy.In fraising process, use hairbrush on cutter, to be coated with lubricating oil, not only improve the service life of cutter, the scrap of deriving during simultaneously by fraising is drained, and avoids knuckle joint hole inwall to scratch, and improves quality and the precision in hole.
5, owing to carrying out the fraising work in knuckle joint hole on the frame of doorway, exist fraising space less, machined steel material difficulty is large, and whole hole aperture ratio is larger, therefore adopt the boring bar tool auto-feed that takes up room less to bore or the common manual air drill of high-power, select auto-feed to creep into row fraising, advantage is that the amount of feeding is constant, can ensure hole surface quality and aperture requirement; Select the manual air drill of common high-power, advantage is cheap, small volume.
Brief description of the drawings
Fig. 1 is that aircraft of the present invention is inserted supporting tool structural representation in the precise machining device of ear formula hinge hole.
Fig. 2 is that in the precise machining device of the slotting ear formula hinge of aircraft of the present invention hole, knuckle joint positioning tool is arranged on the structural representation on the frame of doorway.
Fig. 3 is the structural representation that position is confined on knuckle joint positioning tool and doorway.
Fig. 4 is that aircraft of the present invention is inserted ear formula hinge hole precise machining device cutter schematic diagram.
Fig. 5 is that aircraft of the present invention is plugged in cutter fraising schematic diagram in the precise machining device of ear formula hinge hole.
Wherein, 1-supporting tool, 2-knuckle joint positioning tool, 21-upper hinge joint location mechanism, 211-bushing plate I, 212-bushing plate II, 213-controll block I, 214-through hole I, 215-through hole II, 22-underneath hinges joint location mechanism, 221-bushing plate III, 222-bushing plate IV, 223-controll block II, 224-through hole III, 225-through hole IV, 23-support, 24-alignment pin I, 25-alignment pin II, 3-cutter, guide post before 31-, 32-the first cutting edge, 33-the second cutting edge, guide post after 34-, 35-extension rod, 4-doorway frame, 41-upper hinge joint, 411-inserts ear upper arm I, 412-inserts ear underarm I, 413-knuckle joint hole I, 414-knuckle joint hole II, 42-underneath hinges joint, 421-inserts ear upper arm II, 422-inserts ear underarm II, 423-knuckle joint hole III, 424-knuckle joint hole IV, 5-air drill.
Detailed description of the invention
As Figure 1-5, the slotting ear formula hinge of aircraft of the present invention hole precise machining device comprises supporting tool 1, knuckle joint positioning tool 2, cutter 3, doorway frame 4.Wherein supporting tool 1, for being supported to tram by doorway frame 4.Knuckle joint positioning tool 2 has support 23, upper hinge joint location mechanism 21 and underneath hinges joint location mechanism 22, upper hinge joint location mechanism 21 comprises the bushing plate I 211 that is fixed on support 23, bushing plate II 212, the controll block I 213 and the alignment pin I 24 that between bushing plate I 211 and bushing plate II 212 and with support 23, are flexibly connected, in bushing plate I 211 and bushing plate II 212, have respectively through hole I 214 and through hole II 215, alignment pin I 24 matches with through hole I 214, through hole II 215; Underneath hinges detent mechanism 22 comprises the bushing plate III 221 that is cemented on support 23, bushing plate IV 222, the controll block II 223 and the alignment pin II 25 that between bushing plate III 221 and bushing plate IV 222 and with support 23, are flexibly connected, in bushing plate III 221 and bushing plate IV 222, have respectively through hole III 224 and through hole IV 225, alignment pin II 25 matches with through hole III 224, through hole IV 225; Through hole II 215 is identical with the aperture of through hole IV 225, and through hole I 214 is identical with the aperture of through hole III 224.
Cutter 3 is structure as a whole, and is once provided with from top to bottom front guide post 31, the first cutting edge 32, the second cutting edges 33 that coordinate with through hole II 215 and IV 225, the rear guide post 34 coordinating with through hole I 214 and III 224; Described cutter 3 also comprises extension rod 35, and extension rod 35 is fastenedly connected with rear guide post 34 detachables, and the diameter of extension rod 35 is identical with the diameter of front guide post 31, and the diameter of described the first cutting edge 32 is less than the diameter of the second cutting edge 33.Preferably, alignment pin I 24 and alignment pin II 25 are stepped positioning pin; Cutter 3 is staged cutter.
One utilizes the slotting ear formula hinge of aircraft hole precise machining device to carry out method for fine finishing, it is characterized in that:
A. first doorway frame 4 and aircraft lower half shell are fixed, then adopted supporting tool 1 to support doorway frame 4, then the upper half shell of aircraft is connected with the lower half shell of aircraft;
B. knuckle joint positioning tool 2 is moved to doorway frame 4 fixing, upper articulation joint location mechanism 21 is coordinated with the upper hinge joint 41 on doorway frame 4, slotting ear upper arm I 411 and the slotting ear underarm I 412 of upper hinge joint 41 are placed between bushing plate I 211 and bushing plate II 212, controll block I 213 is between slotting ear upper arm I 411 and slotting ear underarm I 412, insert in ear upper arm I 411 and there is knuckle joint hole I 413, insert in ear underarm I 421 and there is knuckle joint hole II 414, alignment pin I 24 is successively through through hole I 214, knuckle joint hole I 413, knuckle joint hole II 414 and through hole II 215, lower hinge joint location mechanism 22 coordinates with the underneath hinges joint 42 on doorway frame 4, slotting ear upper arm II 421 and the slotting ear underarm II 422 of underneath hinges joint 42 are placed between bushing plate III 221 and bushing plate IV 222, controll block II 223 is between slotting ear upper arm II 421 and slotting ear underarm II 422, insert in ear upper arm II 421 and there is knuckle joint hole III 423, insert in ear underarm II 422 and have knuckle joint hole IV 424, alignment pin II 25 is successively through through hole III 224, knuckle joint hole III 423, knuckle joint hole IV 424 and through hole IV 225, alignment pin I 24 and alignment pin II 25 are controlled upper and lower part knuckle joint 41,42 direction of X-axis and Y-axis aboard.Controll block I 213 is fitted with the lower surface of slotting ear upper arm I 411, controll block II 223 is fitted with the lower surface of slotting ear upper arm II 421, control upper and lower part knuckle joint 41,42 direction of Z axis aboard, to determine the accurate location of the slotting ear arm upper hinge nipple orifice of upper and lower part knuckle joint 41,42;
C. fraising, the alignment pin I 24 of dismantling and alignment pin II 25, the front guide post 31 of cutter 3 is penetrated to through hole I 214, knuckle joint hole I 413, knuckle joint hole II 414 and through hole II 215, start to cut with scissors knuckle joint hole I 413 and knuckle joint hole II 414 simultaneously, the rear guide post 34 of cutter 3 coordinates with bushing plate I, front guide post 31 coordinates with bushing plate II, guarantees the axiality of knuckle joint hole I 413 and knuckle joint hole II 414.Be hinged after the knuckle joint hole I 413 and knuckle joint hole II 414 of upper hinge joint 41, cutter 3 is pulled down, by extension rod 35, penetrate successively through hole I 214, knuckle joint hole I 413, after knuckle joint hole II 414 and through hole II 215, mounting cutter 3 on extension rod 35, again the front guide post 31 of cutter 3 is penetrated to through hole III 224, knuckle joint hole III 423, knuckle joint hole IV 424 and through hole IV 225, start to cut with scissors knuckle joint hole III 423 and knuckle joint hole IV 424 simultaneously, the rear guide post 34 of cutter 3 coordinates with bushing plate III, extension rod 35 coordinates with bushing plate II 212, front guide post 31 coordinates with bushing plate IV 222, ensure the axiality of knuckle joint hole III 423 and knuckle joint hole IV 424, ensure knuckle joint hole III 423 simultaneously, knuckle joint hole IV 424 and knuckle joint hole I 413, the axiality of knuckle joint hole II 414.
Preferably, step c, in fraising process, is coated with lubricating oil with hairbrush on cutter 3, and useless the cutting that fraising is derived drained.
Preferably, step c adopts air drill 5 to be connected and to ream with cutter 3 for auto-feed brill or the manual air drill of high-power.
Above embodiment only, for the exemplary embodiment of the invention, is not used in restriction the invention, and the protection domain of the invention is defined by the claims.Those skilled in the art in the essence and protection domain of the invention, various amendments that innovation and creation are made or be equal in the protection domain that replacement also drops on the invention.
Claims (8)
1. aircraft is inserted ear formula hinge hole precise machining device, it is characterized in that, comprises supporting tool, knuckle joint positioning tool, cutter;
Described knuckle joint positioning tool has support, upper hinge joint location mechanism and underneath hinges joint location mechanism, upper hinge joint location mechanism comprises the bushing plate I that is fixed on support, bushing plate II, the controll block I, the alignment pin I that between bushing plate I and bushing plate II and with support, are flexibly connected, in bushing plate I and bushing plate II, have respectively through hole I and through hole II, alignment pin I matches with through hole I, through hole II; Underneath hinges detent mechanism comprises the bushing plate III that is cemented on support, bushing plate IV, the controll block II, the alignment pin II that between bushing plate III and bushing plate IV and with support, are flexibly connected, in bushing plate III and bushing plate IV, have respectively through hole III and through hole IV, alignment pin II matches with through hole III, through hole IV; Through hole II is identical with the aperture of through hole IV, and through hole I is identical with the aperture of through hole III;
Described cutter is structure as a whole, and is once provided with from top to bottom the front guide post coordinating with through hole II and IV, the first cutting edge, the second cutting edge, the rear guide post coordinating with through hole I and III.
2. aircraft according to claim 1 is inserted ear formula hinge hole precise machining device, it is characterized in that, described cutter also comprises extension rod, and extension rod and rear guide post detachable are fastenedly connected, and the diameter of extension rod is identical with the diameter of front guide post.
3. aircraft according to claim 1 is inserted ear formula hinge hole precise machining device, it is characterized in that, the diameter of the first cutting edge is less than the diameter of the second cutting edge.
4. aircraft according to claim 3 is inserted ear formula hinge hole precise machining device, it is characterized in that, alignment pin I and alignment pin II are stepped positioning pin.
5. aircraft according to claim 3 is inserted ear formula hinge hole precise machining device, it is characterized in that, cutter is staged cutter.
6. utilize the arbitrary described aircraft of claim 1-5 to insert ear formula hinge hole precise machining device and carry out a method for fine finishing, it is characterized in that:
A. first doorway frame and aircraft lower half shell are fixed, then adopted supporting tool to support doorway frame, then the upper half shell of aircraft is connected with the lower half shell of aircraft;
B. knuckle joint positioning tool is moved to doorway frame fixing, upper articulation joint location mechanism is coordinated with the upper hinge joint on the frame of doorway, the slotting ear upper arm I of upper hinge joint and slotting ear underarm I are placed between bushing plate I and bushing plate II, controll block I is between slotting ear upper arm I and slotting ear underarm I, insert in ear upper arm I and there is knuckle joint hole I, insert in ear underarm I and have knuckle joint hole II, alignment pin I is successively through through hole I, knuckle joint hole I, knuckle joint hole II and through hole II; Lower hinge joint location mechanism coordinates with the underneath hinges joint on the frame of doorway, the slotting ear upper arm II of underneath hinges joint and slotting ear underarm II are placed between bushing plate III and bushing plate IV, controll block II is between slotting ear upper arm II and slotting ear underarm II, insert in ear upper arm II and there is knuckle joint hole III, insert in ear underarm II and have knuckle joint hole IV, alignment pin II is successively through through hole III, knuckle joint hole III, knuckle joint hole IV and through hole IV; Controll block I coordinates with the lower surface of slotting ear upper arm I, and controll block II coordinates with the lower surface of slotting ear upper arm II, determines the accurate location of inserting ear arm upper hinge nipple orifice;
C. fraising, the alignment pin I of dismantling and alignment pin II, the front guide post of cutter is penetrated to through hole I, knuckle joint hole I, knuckle joint hole II and through hole II, start to cut with scissors knuckle joint hole I and knuckle joint hole II simultaneously, be hinged after the knuckle joint hole I and knuckle joint hole II of upper hinge joint, cutter is pulled down, by extension rod, penetrate successively through hole I, knuckle joint hole I, after knuckle joint hole II and through hole II, mounting cutter on extension rod, again the front guide post of cutter is penetrated to through hole III and knuckle joint hole III, knuckle joint hole IV and through hole IV, start to cut with scissors knuckle joint hole III and knuckle joint hole IV simultaneously.
7. method for fine finishing according to claim 6, is characterized in that, described step c, in fraising process, is coated with lubricating oil on cutter with hairbrush, and useless the cutting that fraising is derived drained.
8. method for fine finishing according to claim 6, is characterized in that, described step c adopts auto-feed brill or the manual air drill of high-power to be connected and to ream with cutter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410193523.2A CN103978270B (en) | 2014-05-08 | 2014-05-08 | Aircraft inserts ear formula hinge hole precise machining device and method for fine finishing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410193523.2A CN103978270B (en) | 2014-05-08 | 2014-05-08 | Aircraft inserts ear formula hinge hole precise machining device and method for fine finishing |
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| CN103978270A true CN103978270A (en) | 2014-08-13 |
| CN103978270B CN103978270B (en) | 2016-03-16 |
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| CN201410193523.2A Expired - Fee Related CN103978270B (en) | 2014-05-08 | 2014-05-08 | Aircraft inserts ear formula hinge hole precise machining device and method for fine finishing |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106001770A (en) * | 2014-10-09 | 2016-10-12 | 王和根 | Multifunctional automatic disc saw blade center hole reaming device |
| CN106141314A (en) * | 2014-10-09 | 2016-11-23 | 王和根 | A kind of have circular saw bit and automatically extract the reaming device with release function |
| CN113998139A (en) * | 2021-12-20 | 2022-02-01 | 浙江万丰飞机制造有限公司 | General aircraft elevator trailing edge hinge tool and using method |
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| US3352182A (en) * | 1964-02-29 | 1967-11-14 | Vernon G Norum | Valve guide reaming assembly |
| CA2144022A1 (en) * | 1995-03-06 | 1996-09-07 | Gary E. Samsom | Line bore tool |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106001770A (en) * | 2014-10-09 | 2016-10-12 | 王和根 | Multifunctional automatic disc saw blade center hole reaming device |
| CN106141314A (en) * | 2014-10-09 | 2016-11-23 | 王和根 | A kind of have circular saw bit and automatically extract the reaming device with release function |
| CN106141314B (en) * | 2014-10-09 | 2017-12-08 | 重庆丰银包装材料有限公司 | A kind of reaming device automatically extracted with circular saw bit with release function |
| CN113998139A (en) * | 2021-12-20 | 2022-02-01 | 浙江万丰飞机制造有限公司 | General aircraft elevator trailing edge hinge tool and using method |
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|---|---|
| CN103978270B (en) | 2016-03-16 |
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