CN103978270B - Aircraft inserts ear formula hinge hole precise machining device and method for fine finishing - Google Patents
Aircraft inserts ear formula hinge hole precise machining device and method for fine finishing Download PDFInfo
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- CN103978270B CN103978270B CN201410193523.2A CN201410193523A CN103978270B CN 103978270 B CN103978270 B CN 103978270B CN 201410193523 A CN201410193523 A CN 201410193523A CN 103978270 B CN103978270 B CN 103978270B
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- hinge
- hole
- bushing plate
- connection head
- head bore
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Abstract
The present invention discloses a kind of aircraft and inserts ear formula hinge hole precise machining device, comprises supporting tool, knuckle joint positioning tool, cutter; 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 be fixed on support, bushing plate II, the controll block I be flexibly connected between bushing plate I and bushing plate II and with support, alignment pin I; Underneath hinges detent mechanism comprises the bushing plate III be cemented on support, bushing plate IV, the controll block II be flexibly connected between bushing plate III and bushing plate IV and with support, alignment pin II; Cutter is structure as a whole, and is once provided with front guide post from top to bottom, the first cutting edge, the second cutting edge and rear guide post; And utilize this aircraft to insert ear formula hinge hole precise machining device to carry out method for finishing manufactured, not only effectively ensure that the axiality in ear formula hinge hole inserted by aircraft, also improve working (machining) efficiency and the quality of pan.
Description
Technical field
Aircraft of the present invention inserts ear formula hinge hole precise machining device and method, is mainly used in the fine finishining of aircraft being inserted to ear formula hinge nipple orifice.
Background technology
At present, the extensive use in aerospace industry of ear formula hinge joint is inserted.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.For 15-5PH stainless steel, its hardness ratio is higher, for machining, more difficult, when being mainly reflected in drilling, cutting force is large, cutting temperature is high, the heat expansion in easily sticky cutter, bad chip breaking, hole, can cause the abrasive wear of drilling inefficiency, cutter serious, the problems such as hole quality cannot be ensured; And slotting ear formula hinge nipple orifice is required that axiality is higher, mainly in order to better coordinate with the knuckle joint on hatch door, make hatch door more level and smooth in the process of opening the door and close the door, thus increase the service life of knuckle joint.Er Shimen not only complex structure inserted by aircraft, 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 faced at present.
Summary of the invention
The of low quality of ear formula hinge hole existence is inserted in order to solve current aircraft, the problem of axiality cannot be reached, the invention provides a kind of aircraft and insert Er Shimen hinge hole precise machining device and method for fine finishing, the method increase the drilling efficiency of hinge hole, ensure the quality of hinge hole and the requirement to axiality.
For achieving the above object, the technical solution used in the present invention is:
Ear formula hinge hole precise machining device inserted by aircraft, 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 be fixed on support, bushing plate II, the controll block I be flexibly connected between bushing plate I and bushing plate II and with support and alignment pin I, bushing plate I and bushing plate II have through hole I and through hole II respectively, and alignment pin I matches with through hole I, through hole II; Underneath hinges detent mechanism comprises the bushing plate III be cemented on support, bushing plate IV, the controll block II be flexibly connected between bushing plate III and bushing plate IV and with support and alignment pin II, bushing plate III and bushing plate IV have through hole III and through hole IV respectively, and 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 provided with guide post before coordinating with through hole II and IV from top to bottom successively, the first cutting edge, the second cutting edge, the rear guide post coordinated 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 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 adopt 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 moved to doorway frame and fix, upper articulation joint location mechanism is coordinated with the upper hinge joint on the frame of doorway, slotting ear upper arm I and the slotting ear underarm I of upper hinge joint 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 on ear upper arm I and there is hinge-connection head bore I, insert on ear underarm I and have hinge-connection head bore II, alignment pin I is successively through through hole I, hinge-connection head bore I, hinge-connection head bore II and through hole II; Lower hinge joint location mechanism coordinates with the underneath hinges joint on the frame of doorway, slotting ear upper arm II and the slotting ear underarm II of underneath hinges joint 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 on ear upper arm II and there is hinge-connection head bore III, insert on ear underarm II and have hinge-connection head bore IV, alignment pin II is successively through through hole III, hinge-connection head bore III, hinge-connection head bore 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 slotting ear arm upper hinge nipple orifice;
C. ream, to dismantle alignment pin I and alignment pin II, guide post before cutter is penetrated through hole I, hinge-connection head bore I, hinge-connection head bore II and through hole II, start to cut with scissors hinge-connection head bore I and hinge-connection head bore II simultaneously, after the hinge-connection head bore I being hinged upper hinge joint and hinge-connection head bore II, cutter is pulled down, by extension rod, penetrate through hole I successively, hinge-connection head bore I, after hinge-connection head bore II and through hole II, mounting cutter on extension rod, again guide post before cutter is penetrated through hole III and hinge-connection head bore III, hinge-connection head bore IV and through hole IV, start to cut with scissors hinge-connection head bore III and hinge-connection head bore IV simultaneously.
Preferably, described step c, in reaming procedure, is coated with lubricating oil with hairbrush on cutter, and useless the cutting that fraising is derived is drained.
Preferably, described step c adopts auto-feed brill or the manual air drill of high-power to be connected with cutter to ream.
The present invention has following beneficial effect:
1, aircraft inserts ear formula hinge hole precise machining device by being provided with supporting tool, knuckle joint positioning tool and cutter, ensure that the axiality of slotting ear formula hinge nipple orifice, ensures crudy and the efficiency of hinge-connection head bore simultaneously.
2, the extension rod of cutter is set, solves the less difficult problem being difficult to carry out reaming operations in space that to ream on the frame of doorway.
3, the aperture due to hinge-connection head bore is different, therefore adopts stepped positioning pin box staged cutter, contributes to accurate location, accurately reams.
4, one utilizes aircraft to insert ear formula hinge 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; The hinge-connection head bore of knuckle joint positioning tool to doorway frame is adopted accurately to locate, adopt alignment pin to ensure X and the Y direction of knuckle joint simultaneously, controll block I and controll block II for ensureing the Z-direction of knuckle joint, to guarantee position degree and the axiality of doorway frame hinge-connection head bore.Ream 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, for leading when cutter ream, the machining accuracy of guarantee hinge-connection head bore.In reaming procedure, use hairbrush to be coated with lubricating oil on cutter, not only improve cutting-tool's used life, the scrap of deriving during fraising is drained simultaneously, avoid hinge-connection head bore inwall to scratch, improve quality and the precision in hole.
5, owing to carrying out the fraising work in knuckle joint hole on the frame of doorway, there is fraising space less, machined steel material difficulty is large, and aperture, whole hole is larger, therefore the boring bar tool auto-feed taking up room less is adopted 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.
Accompanying drawing explanation
Fig. 1 is that supporting tool structural representation in the precise machining device of ear formula hinge hole inserted by aircraft of the present invention.
Fig. 2 is that aircraft of the present invention is inserted knuckle joint positioning tool in the precise machining device of ear formula hinge hole and 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 ear formula hinge hole precise machining device cutter schematic diagram inserted by aircraft of the present invention.
Fig. 5 is that cutter fraising schematic diagram in the precise machining device of ear formula hinge hole inserted by aircraft of the present invention.
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-first cutting edge, 33-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-hinge-connection head bore I, 414-hinge-connection head bore II, 42-underneath hinges joint, 421-inserts ear upper arm II, 422-inserts ear underarm II, 423-hinge-connection head bore III, 424-hinge-connection head bore IV, 5-air drill.
Detailed description of the invention
As Figure 1-5, aircraft of the present invention is inserted ear formula hinge hole precise machining device and is comprised 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 be fixed on support 23, bushing plate II 212, the controll block I 213 be flexibly connected between bushing plate I 211 and bushing plate II 212 and with support 23 and alignment pin I 24, bushing plate I 211 and bushing plate II 212 have through hole I 214 and through hole II 215 respectively, and 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 be cemented on support 23, bushing plate IV 222, the controll block II 223 be flexibly connected between bushing plate III 221 and bushing plate IV 222 and with support 23 and alignment pin II 25, bushing plate III 221 and bushing plate IV 222 have through hole III 224 and through hole IV 225 respectively, and 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 provided with guide post 31, first cutting edge 32, second cutting edge 33 before coordinating with through hole II 215 and IV 225 from top to bottom successively, the rear guide post 34 coordinated with through hole I 214 and III 224; Described cutter 3 also comprises extension rod 35, and extension rod 35 and rear guide post 34 detachable are fastenedly connected, and the diameter of extension rod 35 is identical with the diameter of front guide post 31, and the diameter of described 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 aircraft to insert ear formula hinge 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 adopt 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 moved to doorway frame 4 and fix, 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 on ear upper arm I 411 and there is hinge-connection head bore I 413, insert on ear underarm I 421 and there is hinge-connection head bore II 414, alignment pin I 24 is successively through through hole I 214, hinge-connection head bore I 413, hinge-connection head bore 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 on ear upper arm II 421 and there is hinge-connection head bore III 423, insert on ear underarm II 422 and have hinge-connection head bore IV 424, alignment pin II 25 is successively through through hole III 224, hinge-connection head bore III 423, hinge-connection head bore IV 424 and through hole IV 225, alignment pin I 24 and alignment pin II 25 control the direction of upper and lower part knuckle joint 41,42 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 the direction of upper and lower part knuckle joint 41,42 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. ream, to dismantle alignment pin I 24 and alignment pin II 25, guide post 31 before cutter 3 is penetrated through hole I 214, hinge-connection head bore I 413, hinge-connection head bore II 414 and through hole II 215, start to cut with scissors hinge-connection head bore I 413 and hinge-connection head bore 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 hinge-connection head bore I 413 and hinge-connection head bore II 414.After the hinge-connection head bore I 413 being hinged upper hinge joint 41 and hinge-connection head bore II 414, cutter 3 is pulled down, by extension rod 35, penetrate through hole I 214 successively, hinge-connection head bore I 413, after hinge-connection head bore II 414 and through hole II 215, mounting cutter 3 on extension rod 35, again guide post 31 before cutter 3 is penetrated through hole III 224, hinge-connection head bore III 423, hinge-connection head bore IV 424 and through hole IV 225, start to cut with scissors hinge-connection head bore III 423 and hinge-connection head bore 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 hinge-connection head bore III 423 and hinge-connection head bore IV 424, ensure hinge-connection head bore III 423 simultaneously, hinge-connection head bore IV 424 and hinge-connection head bore I 413, the axiality of hinge-connection head bore II 414.
Preferably, step c, in reaming procedure, is coated with lubricating oil with hairbrush on cutter 3, and useless the cutting that fraising is derived is drained.
Preferably, step c adopts air drill 5 to ream for auto-feed brill or the manual air drill of high-power are connected with cutter 3.
Above embodiment is only 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 are in the essence and protection domain of the invention, and the various amendment make innovation and creation or equivalent replacement also drop in the protection domain of the invention.
Claims (7)
1. ear formula hinge hole precise machining device inserted by aircraft, 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 be fixed on support, bushing plate II, the controll block I be flexibly connected between bushing plate I and bushing plate II and with support, alignment pin I, bushing plate I and bushing plate II have through hole I and through hole II respectively, and alignment pin I matches with through hole I, through hole II; Underneath hinges detent mechanism comprises the bushing plate III be cemented on support, bushing plate IV, the controll block II be flexibly connected between bushing plate III and bushing plate IV and with support, alignment pin II, bushing plate III and bushing plate IV have through hole III and through hole IV respectively, and 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 provided with guide post before coordinating with through hole II and IV from top to bottom successively, the first cutting edge, the second cutting edge, the rear guide post coordinated 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.
2. ear formula hinge hole precise machining device inserted by aircraft according to claim 1, it is characterized in that, the diameter of the first cutting edge is less than the diameter of the second cutting edge.
3. ear formula hinge hole precise machining device inserted by aircraft according to claim 2, it is characterized in that, alignment pin I and alignment pin II are stepped positioning pin.
4. ear formula hinge hole precise machining device inserted by aircraft according to claim 2, it is characterized in that, cutter is staged cutter.
5. utilize the arbitrary described aircraft of claim 1-4 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 adopt 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 moved to doorway frame and fix, upper articulation joint location mechanism is coordinated with the upper hinge joint on the frame of doorway, slotting ear upper arm I and the slotting ear underarm I of upper hinge joint 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 on ear upper arm I and there is hinge-connection head bore I, insert on ear underarm I and have hinge-connection head bore II, alignment pin I is successively through through hole I, hinge-connection head bore I, hinge-connection head bore II and through hole II; Lower hinge joint location mechanism coordinates with the underneath hinges joint on the frame of doorway, slotting ear upper arm II and the slotting ear underarm II of underneath hinges joint 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 on ear upper arm II and there is hinge-connection head bore III, insert on ear underarm II and have hinge-connection head bore IV, alignment pin II is successively through through hole III, hinge-connection head bore III, hinge-connection head bore 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 slotting ear arm upper hinge nipple orifice;
C. ream, to dismantle alignment pin I and alignment pin II, guide post before cutter is penetrated through hole I, hinge-connection head bore I, hinge-connection head bore II and through hole II, start to cut with scissors hinge-connection head bore I and hinge-connection head bore II simultaneously, after the hinge-connection head bore I being hinged upper hinge joint and hinge-connection head bore II, cutter is pulled down, by extension rod, penetrate through hole I successively, hinge-connection head bore I, after hinge-connection head bore II and through hole II, mounting cutter on extension rod, again guide post before cutter is penetrated through hole III and hinge-connection head bore III, hinge-connection head bore IV and through hole IV, start to cut with scissors hinge-connection head bore III and hinge-connection head bore IV simultaneously.
6. method for fine finishing according to claim 5, is characterized in that, step c, in reaming procedure, is coated with lubricating oil with hairbrush on cutter, and is drained by the scrap that fraising is derived.
7. method for fine finishing according to claim 5, is characterized in that, step c adopts auto-feed brill or the manual air drill of high-power to be connected with cutter and reams.
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 |
Applications Claiming Priority (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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| Publication Number | Publication Date |
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| CN103978270A CN103978270A (en) | 2014-08-13 |
| CN103978270B true 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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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104308266B (en) * | 2014-10-09 | 2016-09-28 | 青岛玉兰祥商务服务有限公司 | The automatic reaming device of Multi-functional disk saw blade centre bore |
| 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 |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN100563914C (en) * | 2008-10-08 | 2009-12-02 | 沈阳飞机工业（集团）有限公司 | Eliminate the method for a pair of concentric circle holes alignment error with reaming mode |
| CN102728994B (en) * | 2012-06-06 | 2015-03-11 | 沈阳飞机工业（集团）有限公司 | Processing method for holes in multi-lug-plate parts with dense spaces |
| CN102699440B (en) * | 2012-06-21 | 2014-03-12 | 福建省标光阀门科技有限公司 | Tool and method for processing concentric axle holes on valve body of valve |
| CN102909433B (en) * | 2012-11-19 | 2014-11-26 | 中航成飞民用飞机有限责任公司 | Method for reaming on latch lock connectors of airplane cargo space |
| CN203197390U (en) * | 2013-04-17 | 2013-09-18 | 华电曹妃甸重工装备有限公司 | Large-distance coaxial shaft hole machining device |
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2014
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Granted publication date: 20160316 Termination date: 20200508 |