CN115216611B - Stable heat treatment device for aircraft tail cover - Google Patents
Stable heat treatment device for aircraft tail cover Download PDFInfo
- Publication number
- CN115216611B CN115216611B CN202210712180.0A CN202210712180A CN115216611B CN 115216611 B CN115216611 B CN 115216611B CN 202210712180 A CN202210712180 A CN 202210712180A CN 115216611 B CN115216611 B CN 115216611B
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- Prior art keywords
- tail cover
- pressing
- block
- shaping
- aircraft tail
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- 238000010438 heat treatment Methods 0.000 title claims abstract description 38
- 238000003825 pressing Methods 0.000 claims abstract description 93
- 238000007493 shaping process Methods 0.000 claims description 44
- 238000005192 partition Methods 0.000 claims description 16
- 238000000034 method Methods 0.000 claims description 6
- 230000006641 stabilisation Effects 0.000 claims description 4
- 238000011105 stabilization Methods 0.000 claims description 4
- 230000000087 stabilizing effect Effects 0.000 claims description 4
- 230000000694 effects Effects 0.000 claims description 3
- 238000000926 separation method Methods 0.000 claims description 3
- 238000003466 welding Methods 0.000 abstract description 6
- 125000006850 spacer group Chemical group 0.000 abstract description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Butt Welding And Welding Of Specific Article (AREA)
- Heat Treatments In General, Especially Conveying And Cooling (AREA)
Abstract
The invention belongs to the technical field of heat treatment of parts, and relates to a stable heat treatment device for an aircraft tail cover. The invention utilizes the reference hole of the front end frame of the aircraft tail cover to position the aircraft tail cover and uses four sections of pressing plates to press the front end frame of the aircraft tail cover onto the bottom surface of the heat treatment clamp, thereby ensuring the flatness of the front end frame of the aircraft tail cover and enabling the front end frame of the aircraft tail cover to be connected with the rear aircraft body; supporting the aircraft tail cover to a theoretical pneumatic surface from inside to outside by using eight sections of inner supporting blocks at the upper bulkhead position in the aircraft tail cover; the annular spacer frame is positioned by a whole inner positioning ring behind the aircraft tail cover, the pneumatic appearance of the rear end of the aircraft tail cover is ensured, the middle beam of the connecting part of the aircraft tail cover and the tail cone and the rear saw tooth skin under the aircraft tail cover are positioned to the theoretical position from outside to inside by the movable clamping plate, the pneumatic appearance of the rear saw tooth skin under the middle beam and the aircraft tail cover is ensured, the welding precision of the aircraft tail cover is improved, and the integral pneumatic appearance of the aircraft tail cover is ensured.
Description
Technical Field
The invention belongs to the technical field of heat treatment of parts, and relates to a stable heat treatment device for an aircraft tail cover.
Background
The aircraft tail cover is an important structural member of the aircraft, plays a role in protecting an engine, and meets the pneumatic appearance requirement of the aircraft body. Because the engine has different types and structures, the engine tail cover has different structures, the engine tail cover is similar to a cylinder, the shape is more regular, the part size is large, the wall thickness of the sheet metal part is thicker, the whole rigidity is strong, the internal stress is large after welding, and the engine tail cover needs to be supported in the engine tail cover during stable heat treatment. The aircraft has large size, high precision and complex and irregular structure due to high aerodynamic shape requirement of high power. In order to meet the requirements of the whole aerodynamic performance of the aircraft and the engine, a middle beam and a rear saw-tooth skin under the tail cover are additionally arranged at two ends of the aircraft tail cover and are connected with tail cones, the middle beam and the rear saw-tooth skin under the tail cover are independently welded outside a cylinder of the tail cover, and the pneumatic appearance of the aircraft tail cover cannot be guaranteed because the joint surfaces between sheet metal parts with large welding areas are difficult to coordinate (deform after welding). The present invention has been made in view of the above technical background.
Disclosure of Invention
The purpose of the invention is that: and removing internal stress generated after the final assembly welding of the aircraft tail cover, and correcting the aerodynamic shape of the aircraft tail cover. The aircraft tail cover obtains the comprehensive performance required by design and the requirement of working in a high-temperature environment.
The technical scheme of the invention is as follows:
positioning the aircraft tail cover by utilizing a reference hole of the front end frame of the aircraft tail cover, and pressing the front end frame of the aircraft tail cover onto the bottom surface of the heat treatment clamp by utilizing four sections of pressing plates, so that the flatness of the front end frame of the aircraft tail cover is ensured, and the front end frame of the aircraft tail cover can be connected with the rear aircraft body; supporting the aircraft tail cover to a theoretical pneumatic surface from inside to outside by using eight sections of inner supporting blocks at the upper bulkhead position in the aircraft tail cover; the annular spacer frame is positioned by a whole inner positioning ring behind the aircraft tail cover, the pneumatic appearance of the rear end of the aircraft tail cover is ensured, the middle beam of the connecting part of the aircraft tail cover and the tail cone and the rear saw-tooth skin under the aircraft tail cover are positioned to the theoretical position from outside to inside by the movable clamping plate, and the pneumatic appearance of the middle beam and the rear saw-tooth skin under the aircraft tail cover is ensured.
The technical scheme of the invention is as follows:
the stable heat treatment device for the aircraft tail cover comprises a basic base platform, an inner supporting unit and an outer pressing unit.
The foundation base platform is formed by connecting a positioning plate, a bottom plate, a rib plate, a fixing upright post, a positioning sleeve, a supporting plate, a positioning ring, a compression stop block and a stop block through pins, bolts, nuts, eye bolts and part positioning pins.
The rib plates are uniformly distributed between the bottom plate and the part locating pins and welded into a frame structure to serve as a foundation, the fixed upright posts are uniformly distributed with the axis of the engine as a reference, the fixed upright posts are fixed on the locating plate through bolts and nuts, and then the supporting plate and the locating ring are arranged on the fixed upright posts according to the positions of the upper partition frame of the tail cover and the rear annular partition frame of the tail cover through locating sleeves; a stop block is arranged on the supporting plate according to the position of the rear tooth skin press shaping block under the tail cover; the eye screw is installed on the locating ring and used for lifting, and the part locating pin is installed according to the position of the locating pin hole on the locating plate.
The inner support unit comprises a movable frame pressing plate, a wedge shaft pin, a wedge, an inner support block, a guide block, a handle and a piece withdrawing plate.
The movable frame pressing plate consists of four uniform petals, is fixed on the positioning plate and is used for clamping the front end frame of the tail cover of the machine, wedge shaft pins are uniformly arranged in positioning holes on the positioning plate according to the inner edges of the pressing wedges of the movable frame pressing plate, and then the pressing plate and the pressing wedges are sequentially arranged on the wedge shaft pins. The wedge enables a pressing plate sleeved on the wedge shaft pin to press the front end frame of the tail cover below the movable frame pressing plate; the guide blocks are connected to the corresponding positions of the support plates through bolts, the inner support blocks are formed by eight uniform petals and are penetrated into the guide blocks, the upper partition frame in the tail cover is supported by the inner support blocks through wedge punching, the handles are pressed into holes on two sides of each inner support block, and the inner support blocks are retracted through the retraction plates, so that the die separation effect is achieved.
The outer pressing unit comprises a rear tooth skin pressing and shaping block under the tail cover, a rear tooth skin shaping pressing block on the tail cover and a shaping center sill pressing block, wherein the rear tooth skin pressing and shaping block under the tail cover, the rear tooth skin shaping pressing block on the tail cover and the shaping center sill pressing block are welded into a square frame structure through flat plates, the contact surface of the rear tooth skin pressing and shaping block with the saw tooth skin of the tail cover is a skin molded surface, the back surface and the bottom surface are planes, the rear tooth skin pressing and shaping block under the tail cover, the rear tooth skin shaping pressing block on the tail cover and the shaping center sill pressing block are positioned by movable positioning pins according to long round holes on a positioning plate, and the inclined wedges press the rear tooth skin pressing and shaping block under the tail cover, the rear tooth skin shaping pressing block on the tail cover and the shaping center sill pressing block to the tail cover through reaction force of the pressing stop blocks.
The application method of the aircraft tail cover stabilizing heat treatment device comprises the following steps:
the first step: and placing the welded tail cover on a basic base platform of the stable heat treatment device of the aircraft tail cover, and positioning the front end frame of the tail cover by using a part positioning pin.
And a second step of: after the tail cover is positioned, the movable frame pressing plate is used for shaping and pressing the front end frame of the tail cover, and then the inner supporting block is used for shaping and pressing the upper partition frame of the tail cover and the rear annular partition frame of the tail cover.
And a third step of: after the positioning and clamping of the tail cover inner type, the edge positions of the saw-tooth skin of the tail cover are shaped and compressed by the rear tooth skin shaping block below the tail cover, the rear tooth skin shaping pressing block on the tail cover and the shaping center sill pressing block respectively.
Fourth step: and (3) placing the stable heat treatment device of the aircraft tail cover and the aircraft tail cover into a vacuum furnace together for heat treatment.
Fifth step: after the stable heat treatment device of the aircraft tail cover and the tail cover are cooled, opening the internal and external shaping compacting components of the stable heat treatment device of the aircraft tail cover, and taking down the parts from the device to finish the stable heat treatment process of the aircraft tail cover.
The invention has the beneficial effects that:
the invention ensures the flatness of the front end frame of the tail cover by using the stable heat treatment device of the tail cover of the airplane, so that the tail cover can be better connected with the rear airplane body, the welding precision of the tail cover is improved, and the whole pneumatic appearance of the tail cover of the airplane is ensured.
Drawings
FIG. 1 is a schematic illustration of a part;
FIG. 2 is a perspective view of an aircraft tail hood stabilization heat treatment apparatus;
FIG. 3 is a side view of an aircraft tail hood stabilization heat treatment apparatus;
fig. 4 is a top view of an aircraft tail hood stabilization heat treatment apparatus.
A. Saw tooth skin of tail cover; B. a center sill; C. a front end frame of the tail cover; D. an upper partition frame in the tail cover; E. an annular bulkhead behind the tail cover; 01. a base platform; 02. an inner support unit; 03. an external pressure unit; 04. a positioning plate; 05. a bottom plate; 06. rib plates; 07. fixing the upright post; 08. a positioning sleeve; 09. a support plate; 10. a positioning ring; 11. a pin; 12. compressing the stop block; 13. a stop block; 14. a bolt; 15. a nut; 16. a suspension ring screw; 17. a movable frame pressing plate; 18. a pressing plate; 19. wedge shaft pin; 20. wedge; 21. an inner support block; 22. a guide block; 23. a handle; 24. a piece withdrawing plate; 25. the skin of the rear tooth below the tail cover is pressed and shaped; 26. forming and briquetting a rear tooth skin on a tail cover; 27. shaping a middle beam pressing block; 28. a movable positioning pin; 29. part locating pin.
Detailed Description
The present invention is described in further detail below with reference to the drawings to enable those skilled in the art to practice the invention by referring to the description.
Example 1:
the stable heat treatment device for the aircraft tail cover comprises a basic base platform 01, an inner support unit 02 and an outer pressure unit 03.
The foundation base platform 01 is formed by connecting a positioning plate 04, a bottom plate 05, a rib plate 06, a fixed upright column 07, a positioning sleeve 08, a supporting plate 09, a positioning ring 10, a compression stop block 12 and a stop block 13 through a pin 11, a bolt 14, a nut 15, a lifting ring screw 16 and a part positioning pin 29.
The rib plates 06 are uniformly distributed between the bottom plate 05 and the part positioning pins 29 and welded to form a frame structure as a basis, the fixed upright posts 07 are uniformly distributed with the axis of the engine as a reference, the fixed upright posts are fixed on the positioning plate 04 through bolts 14 and nuts 15, and then the supporting plate 09 and the positioning ring 10 are arranged on the fixed upright posts 07 according to the positions of an upper partition frame D in a tail cover and an annular partition frame E behind the tail cover through positioning sleeves 08; a stop block 13 is arranged on the supporting plate 09 according to the position of the rear tooth skin press shaping block 25 under the tail cover; the eye screw 16 is mounted on the surface of the positioning ring 10 for lifting, and the part positioning pin 29 is mounted according to the positioning pin hole position on the positioning plate 04.
The inner support unit 02 comprises a movable frame pressing plate 17, a pressing plate 18, a wedge shaft pin 19, a wedge 20, an inner support block 21, a guide block 22, a handle 23 and a piece withdrawing plate 24.
The movable frame pressing plate 17 consists of even four petals, the movable frame pressing plate 17 is fixed on the positioning plate 04 and used for clamping a front end frame C of a tail cover of the machine, the wedge shaft pins 19 are uniformly arranged in positioning holes on the positioning plate 04 according to the inner edges of the pressing wedges 20 of the movable frame pressing plate 17, and then the pressing plate 18 and the pressing wedges 20 are sequentially arranged on the wedge shaft pins 19. The wedge 20 enables the pressing plate 18 sleeved on the wedge shaft pin 19 to press the front end frame C of the tail cover below the movable frame pressing plate 17; the guide blocks 22 are connected to corresponding positions of the support plates 09 through bolts 14, the inner support blocks 21 are formed by uniform eight petals and are penetrated into the guide blocks 22, the inner support blocks 21 support the upper partition frame D in the tail cover through the wedge 20, the handles 23 are pressed into holes on two sides of each inner support block 21, and the retreating plates 24 are used for retreating the inner support blocks, so that the die separation effect is realized.
The outer pressing unit 03 comprises a rear tooth skin pressing and shaping block 25 under the tail cover, a rear tooth skin shaping pressing block 26 on the tail cover and a shaping center sill pressing block 27, wherein the rear tooth skin pressing and shaping block 25 under the tail cover, the rear tooth skin shaping pressing block 26 on the tail cover and the shaping center sill pressing block 27 are welded into a square frame structure through flat plates, the contact surface with the sawtooth skin A of the tail cover is a skin molded surface, the back surface and the bottom surface are planes, the rear tooth skin pressing and shaping block 25 under the tail cover, the rear tooth skin shaping pressing block 26 on the tail cover and the shaping center sill pressing block 27 are positioned by movable positioning pins 28 according to long round holes on a positioning plate 04, and the inclined wedges 20 press the rear tooth skin pressing and shaping block 25 under the tail cover, the rear tooth skin shaping pressing block 26 on the tail cover and the shaping center sill pressing block 27 onto the tail cover through reaction force with the pressing stop blocks 12.
Example 2:
the application method of the aircraft tail cover stabilizing heat treatment device comprises the following steps:
the first step: the welded tail cover is placed on a base platform 01 of an aircraft tail cover stabilizing heat treatment device, and a part positioning pin 29 is used for positioning a tail cover front end frame C.
And a second step of: after the tail cover is positioned, the movable frame pressing plate 17 is used for shaping and pressing the front end frame C of the tail cover, and then the inner supporting block 21 is used for shaping and pressing the upper partition frame D of the tail cover and the rear annular partition frame E of the tail cover.
And a third step of: after the positioning and clamping of the tail cover inner type, the edge positions of the tail cover sawtooth skin A are shaped and pressed by a tail cover lower rear tooth skin pressing shaping block 25, a tail cover upper rear tooth skin shaping pressing block 26 and a shaping center sill pressing block 27 respectively.
Fourth step: and (3) placing the stable heat treatment device of the aircraft tail cover and the aircraft tail cover into a vacuum furnace together for heat treatment.
Fifth step: after the stable heat treatment device of the aircraft tail cover and the tail cover are cooled, opening the internal and external shaping compacting components of the stable heat treatment device of the aircraft tail cover, and taking down the parts from the device to finish the stable heat treatment process of the aircraft tail cover.
Claims (3)
1. The stable heat treatment device for the aircraft tail cover is characterized by comprising a basic base platform (01), an inner supporting unit (02) and an outer pressing unit (03);
the foundation base platform (01) is formed by connecting a positioning plate (04), a bottom plate (05), a rib plate (06), a fixing upright post (07), a positioning sleeve (08), a supporting plate (09), a positioning ring (10), a pressing stop block (12) and a stop block (13) through a pin (11), a bolt (14), a nut (15), a lifting ring screw (16) and a part positioning pin (29);
the rib plates (06) are uniformly distributed in the middle of the bottom plate (05) and the part locating pins (29) to be welded into a frame structure to serve as a basis, the fixed upright posts (07) are uniformly distributed by taking the axis of the engine as a reference, and the supporting plates (09) and the locating rings (10) are arranged on the fixed upright posts (07) according to the positions of the upper partition frame (D) in the tail cover and the rear annular partition frame (E) of the tail cover by using locating sleeves (08); a stop block (13) is arranged on the supporting plate (09) according to the position of a rear tooth skin press shaping block (25) under the tail cover; the eye screw (16) is arranged on the positioning ring (10) for lifting, and the part positioning pin (29) is arranged according to the position of the positioning pin hole on the positioning plate (04);
the inner support unit (02) comprises a movable frame pressing plate (17), a pressing plate (18), a wedge shaft pin (19), a wedge (20), an inner support block (21), a guide block (22), a handle (23) and a piece withdrawing plate (24);
the movable frame pressing plate (17) consists of even four petals, the movable frame pressing plate (17) is fixed on the positioning plate (04) and is used for clamping a front end frame (C) of a tail cover of the machine, the inclined wedge shaft pins (19) are uniformly arranged in positioning holes on the positioning plate (04) according to the inner edges of the pressing inclined wedges (20) of the movable frame pressing plate (17), and then the pressing plate (18) and the pressing inclined wedges (20) are sequentially arranged on the inclined wedge shaft pins (19); the wedge (20) enables a pressing plate (18) sleeved on a wedge shaft pin (19) to press a front end frame (C) of the tail cover below the movable frame pressing plate (17); the guide blocks (22) are connected to corresponding positions of the support plates (09) through bolts (14), the inner support blocks (21) are formed by uniform eight petals and are penetrated into the guide blocks (22), the upper partition frame (D) in the tail cover is supported by the inner support blocks (21) through the diagonal wedges (20), the handles (23) are pressed into holes on two sides of each inner support block (21), and the back of each inner support block is enabled to be in a die separation effect through the back plate (24);
the outer pressing unit (03) comprises a rear tooth skin pressing and shaping block (25) below the tail cover, a rear tooth skin shaping pressing block (26) above the tail cover and a shaping center sill pressing block (27); the rear tooth skin shaping block (25) under the tail cover, the rear tooth skin shaping pressing block (26) on the tail cover and the shaping center sill pressing block (27) are welded into a square frame structure, the contact surface with the saw tooth skin (A) of the tail cover is a skin molded surface, the back surface and the bottom surface are planes, the rear tooth skin shaping block (25) under the tail cover, the rear tooth skin shaping pressing block (26) on the tail cover and the shaping center sill pressing block (27) are positioned by the movable positioning pin (28) according to a long round hole on the positioning plate (04), and the inclined wedge (20) presses the rear tooth skin shaping block (25) under the tail cover, the rear tooth skin shaping pressing block (26) on the tail cover and the shaping center sill pressing block (27) to the tail cover through the reaction force of the pressing stop block (12).
2. The aircraft tail cover stabilizing heat treatment device according to claim 1, wherein the fixing upright (07) is fixed on the positioning plate (04) through bolts (14) and nuts (15).
3. Method for using an aircraft tail cover stabilization heat treatment device according to claim 1 or 2, characterized by the following steps:
the first step: the welded tail cover is placed on a basic base platform (01) of an aircraft tail cover stable heat treatment device, and a part positioning pin (29) is used for positioning a tail cover front end frame (C);
and a second step of: after the tail cover is positioned, a movable frame pressing plate (17) is used for shaping and pressing a front end frame (C) of the tail cover, and then an inner supporting block (21) is used for shaping and pressing an upper partition frame (D) of the tail cover and a rear annular partition frame (E) of the tail cover;
and a third step of: after the positioning and clamping of the inner part of the tail cover, the edge position of the sawtooth skin (A) of the tail cover is shaped and pressed by a rear tooth skin shaping block (25) under the tail cover, a rear tooth skin shaping pressing block (26) on the tail cover and a shaping center sill pressing block (27) respectively;
fourth step: placing the stable heat treatment device of the aircraft tail cover and the aircraft tail cover into a vacuum furnace together for heat treatment;
fifth step: after the stable heat treatment device of the aircraft tail cover and the tail cover are cooled, opening the internal and external shaping compacting components of the stable heat treatment device of the aircraft tail cover, and taking down the parts from the device to finish the stable heat treatment process of the aircraft tail cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210712180.0A CN115216611B (en) | 2022-06-22 | 2022-06-22 | Stable heat treatment device for aircraft tail cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210712180.0A CN115216611B (en) | 2022-06-22 | 2022-06-22 | Stable heat treatment device for aircraft tail cover |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115216611A CN115216611A (en) | 2022-10-21 |
| CN115216611B true CN115216611B (en) | 2023-10-31 |
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ID=83607335
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210712180.0A Active CN115216611B (en) | 2022-06-22 | 2022-06-22 | Stable heat treatment device for aircraft tail cover |
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| CN (1) | CN115216611B (en) |
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| CN112410522A (en) * | 2020-11-19 | 2021-02-26 | 首都航天机械有限公司 | Quenching treatment clamp |
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| CN216401814U (en) * | 2021-11-15 | 2022-04-29 | 贵州弘安鑫晟航空科技有限责任公司 | Unmanned aerial vehicle tail cover assembly jig |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US10968497B2 (en) * | 2017-12-14 | 2021-04-06 | The Boeing Company | Tool for heating and quenching a structure |
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2022
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| CN106134323B (en) * | 2010-11-25 | 2014-05-28 | 北京卫星制造厂 | A kind of inner support external-compression type automatic welding of circumferential seams frock |
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| CN110295333A (en) * | 2019-08-07 | 2019-10-01 | 沈阳飞机工业（集团）有限公司 | A kind of stationary fixture of large size covering heat treatment |
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| Publication number | Publication date |
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| CN115216611A (en) | 2022-10-21 |
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