CN114473380A - Numerical control machining method for aviation integral frame part - Google Patents
Numerical control machining method for aviation integral frame part Download PDFInfo
- Publication number
- CN114473380A CN114473380A CN202210061940.6A CN202210061940A CN114473380A CN 114473380 A CN114473380 A CN 114473380A CN 202210061940 A CN202210061940 A CN 202210061940A CN 114473380 A CN114473380 A CN 114473380A
- Authority
- CN
- China
- Prior art keywords
- hole
- tool
- blank
- numerical control
- heightening
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
Abstract
The invention relates to the field of aviation part processing, in particular to a numerical control processing method of an aviation integral frame part, which comprises the step of fixing a rough processing blank on a hole tool through a plurality of heightening tools, wherein the top of each heightening tool is fixed with the rough processing blank through a bolt, the bottom of each heightening tool is fixed with the hole tool through a bolt, the rough processing blank is subjected to numerical control finish processing in a main shaft swing angle mode under one-time clamping of the heightening tools, and at least the appearance characteristic, the hole characteristic and the single-side inner-shaped groove cavity characteristic of the part are formed. The clamping time is shortened, the surface quality of the formed part is better, the polishing time of the pliers is shortened, the part forming precision is improved, smooth assembly of the whole machine in the later period is ensured, meanwhile, the heightening tool is simple in structure, the heightening tools can be adjusted adaptively according to the structural characteristics of the whole frame part, the adjustment is easier, the clamping efficiency is higher, the time and the cost for preparing the special tool are reduced, and the part processing efficiency is improved.
Description
Technical Field
The invention relates to the field of aviation part machining, in particular to a numerical control machining method for an aviation integral frame part.
Background
In recent years, with the rapid development of the design and manufacture industry of airplanes, the market demand is increased year by year, and the processing quality and efficiency of large and complex integral frame parts which are used as the most important parts of the airframe and play a vital role in the assembly precision of the airframe directly influence the delivery of airplanes.
The traditional processing mode of the existing large-scale complex integral frame part generally has two types of modes: firstly, a mode of machining two surfaces and milling an angle head is adopted, the method easily causes that a cutter connecting step is formed on the appearance, the machining precision is not high enough, the quality of parts is directly influenced, even the subsequent assembly is carried out, and the machining period and the cost are increased; and secondly, a reverse drawing tool is adopted for processing, the internal clamping problem of the large-scale complex integral frame part cannot be reasonably solved, and the clamping position of the tool on a machine tool workbench cannot be determined, so that the difficulty in adjusting the part and the tool during clamping is large.
Therefore, a technical scheme is needed at present to solve the technical problems that in the existing aircraft manufacturing, clamping of large complex integral frame parts is difficult, machining precision is low, and part quality, machining period and cost are affected.
Disclosure of Invention
The invention aims to: aiming at the problems in the background technology, a numerical control machining method for an aviation integral frame part is provided.
In order to achieve the purpose, the invention adopts the technical scheme that:
a numerical control machining method for an aviation integral frame part comprises the step of fixing a rough machining blank on a hole tool through a plurality of heightening tools, wherein the top of each heightening tool is fixed with the rough machining blank through a bolt, the bottom of each heightening tool is fixed with the hole tool through a bolt, the rough machining blank is subjected to numerical control finish machining in a main shaft swing angle mode under one-time clamping of the heightening tools, and at least the appearance characteristic, the hole characteristic and the single-side inner-shaped groove cavity characteristic of a formed part are achieved.
The numerical control machining method of the aviation integral frame part is suitable for machining the integral frame part with a continuous curved surface and a precise hole structure distributed on the curved surface, increases the Z-direction distance of the part relative to a hole tool by adopting the heightening tool to be matched with the hole tool, is convenient to assemble, reduces the clamping adjusting time, can finish machining all high-precision position characteristics on a single surface to a theoretical size under one-time clamping of the part, finishes the shape by one-time machining, is not easy to generate a cutter receiving step, ensures the surface quality of the formed part to be better, reduces the clamp repairing and polishing time, improves the forming precision of the part, ensures the smooth later-stage complete machine assembly, improves the machining efficiency and the machining quality, has simple structure, and can carry out adaptive position adjustment according to the structural characteristics of the integral frame part, the adjustment is easier, the clamping efficiency is higher, the time and the cost for preparing the special tool are reduced, the part processing efficiency is favorably improved, and the part processing cost is reduced.
As a preferred scheme of the invention, the rough machining blank is a blank prepared by rough milling a raw material blank and reserving finish milling allowance according to the shape and the structure of the part.
As a preferable scheme of the invention, the blank member is reserved with an internal boss at the part lightening hole. The inside boss is used for laminating with the bed hedgehopping frock, provides the mounted position for being connected of blank and bed hedgehopping frock, avoids the part to carry out the position atress deformation that is connected with the bed hedgehopping frock, influences the shaping precision of part.
According to the preferable scheme of the invention, the blank is reserved with an external boss on the part appearance. The external boss can increase the strength of the outer frame of the whole frame part, so that the part is less deformed in the machining process, and the appearance precision of the manufactured part is higher.
As a preferable scheme of the invention, the heightening tool comprises a frame body and a reinforcing rib, wherein the reinforcing rib and the frame body are integrally formed, the reinforcing rib is positioned in the frame body, a bushing mounting hole is formed in the top of the frame body, and a pressing through hole is formed in the bottom of the frame body. The bed hedgehopping frock simple structure of this structure, it is better to the bearing strength of part, can maintain the overall stability of part in the course of the parts machining.
As a preferable aspect of the present invention, the reinforcing rib includes a lateral reinforcing rib, a peripheral edge of the lateral reinforcing rib is connected to an inner wall of the frame body, and the lateral reinforcing rib is provided with a weight removal hole.
As a preferable scheme of the present invention, the reinforcing rib further includes a vertical reinforcing rib provided on the horizontal reinforcing rib, upper and lower end surfaces of the vertical reinforcing rib are connected to an inner wall of the frame body, and the vertical reinforcing rib is perpendicular to the horizontal reinforcing rib.
As a preferable scheme of the invention, the method specifically comprises the following steps: s1: processing a fixing hole: preparing a through hole as a fixing hole in advance at a position on the raw material blank corresponding to the part lightening hole; s2: roughly milling a first surface: according to the shape and the structure of the part, a finish machining milling allowance is reserved, a first surface of a raw material blank is roughly milled, an inner boss is reserved at a lightening hole, an outer boss is reserved on the appearance, and the fixing hole is positioned on the inner boss; s3: roughly milling a second surface: turning and clamping, removing an external boss, reserving a finish machining milling allowance, and roughly milling the other side of the raw material blank to obtain a blank piece; s4: arranging a tool: according to the shape and the structure of the part, fixed padding tools are distributed on the pore tool, and the padding tools can be at least supported on an outer frame structure and a partial groove cavity structure of the part; s5: clamping a blank piece: connecting and fixing the blank piece on the padding tool by penetrating a bolt through a fixing hole on the inner boss; s6: finish milling a first surface: finely milling the appearance characteristics, the hole characteristics and the single-side inner cavity characteristics of the machined part to theoretical sizes; s7: finish milling a second surface: turning and clamping, and finish milling the characteristics of the suspended web and the inner cavity of the other side; s8: repairing pliers: and (5) polishing, removing the inner boss and forming the integral frame part. According to the method, all high-precision parts and assembly holes of the part are machined in the one-time clamping state of S6, the surface quality is high, the position precision of the hole and the groove cavity is high, the part forming precision is improved, meanwhile, the clamping is convenient, the machining is efficient, the part forming time is reduced, the time and the cost for preparing and purchasing special tools are saved, and the part preparing cost is reduced.
As a preferred aspect of the present invention, in S6, the hole features at least include a tab profile, a finishing hole and a fitting hole; in S7, the flying web is processed in a direction of increasing rigidity strength.
In a preferable mode of the invention, in S6 and S7, a cutter with the length-diameter ratio of not more than 3:1 is adopted, the cutting depth is not more than 5mm, and the cutting width is not more than 2mm, and finish milling is carried out on a bridge machine tool.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. the heightening tool is matched with the hole tool, so that the Z-direction distance of the part relative to the hole tool is increased, all high-precision part characteristics of a single surface can be processed to reach the theoretical size under one-time clamping of the part, the surface quality of the formed part is better, the position precision of a hole cavity is higher, the forming precision of the part is improved, the clamp repairing and polishing time is reduced, and the smooth assembly of the whole machine at the later stage is ensured;
2. the elevating tools have simple structures, the plurality of elevating tools can perform adaptive position adjustment according to the structural characteristics of the integral frame part, the adjustment is easy, the clamping efficiency is high, and the part processing efficiency is improved;
3. the time and cost for preparing and purchasing special tools are saved, and the preparation cost of parts is reduced.
Drawings
FIG. 1 is a schematic flow chart of a numerical control machining method of an aviation integral frame part in embodiment 1;
FIG. 2 is a front view of the raising tool in example 1;
FIG. 3 is an isometric view of the step-up tool of example 1;
FIG. 4 is a top view of the step-up fixture and the aperture fixture of example 1 after they are connected;
FIG. 5 is a schematic structural view of the part described in example 1;
FIG. 6 is a schematic diagram of the structure of the tab of the part described in example 1;
FIG. 7 is a schematic structural view of the raw material ingot described in example 1;
FIG. 8 is a front view of the part in the clamped state as described in embodiment 1;
FIG. 9 is a plan view of the parts in the clamped state as described in embodiment 1;
fig. 10 is an axial view of the part in the clamped state as described in embodiment 1.
Icon:
1-heightening tool, 11-frame body, 12-reinforcing rib, 121-transverse reinforcing rib, 122-vertical reinforcing rib, 13-bushing mounting hole, 14-pressing through hole, 15-weight removing hole, 2-pore tool, 3-part, 31-outer frame structure, 32-groove cavity structure, 33-assembling hole, 34-lug, 35-lug hole, 36-special-shaped lightening hole, 37-web plate, 4-raw material blank, 41-material frame and 42-connecting plate.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Example 1
As shown in fig. 1 to 10, the present embodiment takes a certain integral frame part in the field of aviation as an example, and provides a numerical control machining method for an integral frame part in aviation:
as shown in fig. 5-6, the component 3 is a large complex double-sided integral frame component, the maximum size of the external shape of the component 3 is 3800mm × 1500mm, and includes an integral outer frame structure 31 and a plurality of slot cavity structures 32 arranged in the outer frame structure 31, both inner and outer surfaces of the outer frame structure 31 are provided with arc surfaces, a plurality of Φ 3 ± 0.1mm assembly holes 33 are arranged around the outer frame structure 31, two ends of the outer frame structure 31 in the length direction are provided with tab 34 structures perpendicular to each other, each tab 34 is provided with a tab hole 35, the transverse tab hole 35 is Φ 28H8mm, the vertical tab hole 35 is Φ 22H8mm, the thickness of the tab 34 is 12H11mm, a part of the slot cavities are provided with through irregular lightening holes 36, a part of the slot cavities are provided with webs 37 having a thickness of 2mm, before the integral frame component 3 is prepared, a padding tool 1 and a hole tool 2 are prepared, the padding tool 1 is machined to integrally form a frame body 11 and a reinforcing rib 12, four bushing mounting holes 13 are arranged at the top of the frame body 11, at least two pressing through holes 14 are arranged at the bottom of the frame body, and the distance between the pressing through holes 14 is matched with the hole position arrangement distance of the hole position tool 2.
Specifically, bed hedgehopping frock 1 in this embodiment is stainless steel material structure, square frame 11 has, frame 11 seals through horizontal strengthening rib 121 in one side, middle part perpendicular to horizontal strengthening rib 121 sets up vertical strengthening rib 122 in the frame 11, the symmetry sets up heavy hole 15 on the horizontal strengthening rib 121 of vertical strengthening rib 122 both sides, alleviate 1 weight of bed hedgehopping frock and consumptive material, reduce the preparation cost, hole frock 2 in this embodiment is the general frock of equidistant array arrangement screw hole, screw hole array distance is selected for 50mm or 100mm according to actual conditions.
Specifically, as shown in fig. 2 to fig. 3, the heightening tool 1 in the embodiment has a size of 196mm × 150mm and a height of 300mm, and is subjected to strength check under a condition of applying a load of 400N through simulation, so as to meet the use requirement.
Specifically, as shown in fig. 7, the raw material blank 4 of the integral frame component in this embodiment is a plate material that is machined to reserve the machining allowance of the external shape, the material frame 41 is reserved outside the raw material blank 4, the raw material blank is connected to the material frame 41 through a plurality of connecting plates 42, and the raw material blank 4, the connecting plates 42, and the material frame 41 are kept as an integral structural member.
Specifically, the numerical control machining method of the integral frame part 3 is used for machining on a bridge type machine tool, and comprises the following steps:
s1: processing a fixing hole: through holes are prepared in advance on the raw material blank 4 corresponding to the positions of the part lightening holes to serve as fixing holes, and the fixing holes are matched with the bushing mounting holes 13 on the top of the heightening tool 1.
S2: roughly milling a first surface: according to the shape and the structure of the part 3, a first surface of a raw material blank 4 is roughly milled, the allowance of the appearance, the inner groove cavity and the web 37 is reserved for at least 3mm, an inner boss is reserved at a lightening hole according to the position of a fixing hole, the fixing hole is positioned on the inner boss, a connecting plate 42 connecting the raw material blank 4 and a material frame 41 is processed, the thickness of the connecting plate 42 is reserved to be 3-6mm, the connecting state of the connecting plate and the material frame 41 is kept, and the connecting plate is formed into an outer boss.
S3: roughly milling a second surface: and turning and clamping, removing an external boss, roughly milling the other side of the raw material blank 4, reserving at least 3mm of appearance allowance, and respectively keeping at least 5mm of allowances at the positions of the internal groove cavity and the web 37 to obtain a blank piece.
Specifically, in S2 and S3, two sections of rough milling along the thickness middle dividing line are performed on the raw material blank 4, appropriate finish milling allowances are respectively reserved in the two rough milling processes, the allowances are overlapped, a blank meeting the finish milling allowances is provided for the subsequent finish machining, and the finish machining efficiency and the finish machining quality are improved.
Further comprising S4: arranging a tool: according to 3 shapes and structures of part, through the bolt, distribute fixed a plurality of bed hedgehopping frocks 1 on hole frock 2, the position of bed hedgehopping frock 1 is arranged by process design and is confirmed, make bed hedgehopping frock 1 can support at least on the frame structure 31 and the partial slot chamber structure 32 of part 3, ensure the stability of part 3 in the course of working, this bed hedgehopping frock 1 clamping is convenient, the processing is high-efficient, the part shaping time has been reduced, and preparation has been removed from, the time and the cost of purchasing special frock, the part preparation cost has been reduced.
Preferably, the method further comprises the step of S5: clamping a blank piece: and the blank piece is connected and fixed on the heightening tool 1 by a bolt penetrating through a fixing hole on the inner boss.
Preferably, the method further comprises the step of S6: finish milling a first surface: and (3) finely milling the appearance characteristics, the hole characteristics and the single-side inner cavity characteristics of the machined part 3 to theoretical sizes.
Specifically, in S6, the overall shape of the part 3 is first machined to the theoretical size, so that the shape is formed by one-time clamping, a tool receiving step is not easily formed, then the swing angle of the spindle head is adjusted, the outlines of the lugs 34 at the two ends, the lug holes 35, and the assembly holes 33 arranged around the shape are machined, so that the hole site precision of each hole is high, all the internal cavity features of the first surface are machined to the theoretical size, all the high-precision parts and the assembly holes 33 of the part 3 are completed by one-time clamping, the surface quality is high, the hole and cavity position precision is high, and the forming precision of the part 3 is improved.
Preferably, the method further comprises the step of S7: finish milling a second surface: and turning over and clamping, and finish milling the suspended web 37 and the characteristics of the inner cavity of the other side.
Specifically, in S7, the semi-finished product of turn-over clamping S6 processing, carry out the clamping of part 3 with same clamping point position in S6, carry out interior type slot cavity processing to the second face, wherein, to the slot cavity region that has web 37 in suspension, from the web 37 in suspension of processing near by the strong point from far away from web 37 in suspension, make the processing direction along web 37 in suspension rigidity weak point to the processing of stronger department, ensure the processingquality and the stability in the course of working of web 37 in suspension, wherein web 37 in suspension is web 37 department that no inside boss sets up, no support, the full suspension state.
Preferably, the method further comprises the step of S8: repairing with pliers: and (5) polishing, removing the inner boss and forming the integral frame part 3.
According to the numerical control machining method for the aviation integral frame part, a phi 12mm cutter is selected, the distance between a cutter point and the end face of a cutter sleeve is smaller than or equal to 50mm, the rotating speed S =20000r/min of a machine tool, the feeding F =3000mm/min, the cutting depth Ap =5mm, the cutting width Ae =2mm, and the Z-direction distance of the part 3 relative to the hole tool 2 is increased through the matching of the heightening tool 1 and the hole tool 2.
The numerical control machining method for the aviation integral frame part has the advantages of improving machining quality: the part 3 can be processed to complete all high-precision position characteristics on a single surface to a theoretical size under one-time clamping, the shape is processed at one time, the outer frame structure 31 is not easy to generate a cutter connecting step, so that the surface quality of the formed part 3 is better, the position precision of a hole is higher, the time for repairing and polishing the cutter is reduced, the forming precision of the part 3 is improved, the smooth assembly of the whole machine in the later period is ensured, the processing efficiency and the processing quality are improved, and the hole position precision of the hole on the curved surface shape manufactured by the method is improved by more than 30 percent compared with the hole position precision processed by an angle head through practice; has the advantages of high processing efficiency: the special tool does not need to be prepared in the machining process of the part 3, the time for preparing the special tool is reduced, the heightening tool 1 is simple in structure, the plurality of heightening tools 1 can be adaptively adjusted in position according to the structural characteristics of the whole frame part 3, the adjustment is easy, the clamping efficiency is high, and the cutter installation time and the manual intervention time caused by the use of angle head milling are reduced; has the advantages of reduced processing cost: the purchase cost of the angle head is eliminated, the universality and the flexibility of the heightening tool are better, and the cost for preparing the special tool is reduced.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. The numerical control machining method of the aviation integral frame part is characterized by comprising the step of fixing a rough machining blank on a hole tool (2) through a plurality of heightening tools (1), wherein the top of each heightening tool (1) is fixed with the rough machining blank through a bolt, the bottom of each heightening tool is fixed with the hole tool (2) through a bolt, the rough machining blank is subjected to numerical control finish machining in a spindle swing angle mode under one-time clamping of the heightening tools (1), and at least the appearance characteristic, the hole characteristic and the single-side inner-shaped groove cavity characteristic of a formed part (3) are formed.
2. The numerical control machining method of the aviation integral frame part as recited in claim 1, characterized in that the rough machining blank is a blank obtained by rough milling a raw material blank (4) and reserving a finish milling allowance according to the shape and structure of the part.
3. The numerical control machining method of the aviation integral frame part as claimed in claim 2, characterized in that an internal boss is reserved on the blank at the lightening hole of the part (3).
4. The numerical control machining method of the aviation integral frame part as claimed in claim 3, characterized in that an external boss is reserved on the external shape of the part (3) of the blank.
5. The numerical control machining method for aviation integral frame parts according to claim 1, characterized in that the bed-up tooling (2) comprises a frame body (11) and a reinforcing rib (12), wherein the reinforcing rib (12) and the frame body (11) are integrally formed, the reinforcing rib (12) is located in the frame body (11), a bushing mounting hole (13) is formed in the top of the frame body (11), and a pressing through hole (14) is formed in the bottom of the frame body.
6. The numerical control machining method for the integral aviation frame part as claimed in claim 5, wherein the reinforcing ribs (12) comprise transverse reinforcing ribs (121), the peripheral edges of the transverse reinforcing ribs (121) are connected with the inner wall of the frame body (11), and the transverse reinforcing ribs (121) are provided with the weight removing holes (15).
7. The numerical control machining method of the integral aviation frame part as claimed in claim 6, wherein the reinforcing ribs (12) further comprise vertical reinforcing ribs (122) arranged on the transverse reinforcing ribs (121), the upper and lower end faces of the vertical reinforcing ribs (122) are connected with the inner wall of the frame body (11), and the vertical reinforcing ribs (122) are perpendicular to the transverse reinforcing ribs (121).
8. The numerical control machining method of the integral aviation frame part as claimed in any one of claims 1 to 7, characterized by comprising the following steps:
s1: processing a fixing hole: preparing a through hole as a fixing hole in advance at a position corresponding to the lightening hole of the part (3) on the raw material blank (4);
s2: roughly milling a first surface: reserving finish machining milling allowance according to the shape and the structure of the part (3), roughly milling a first surface of a raw material blank (4), reserving an inner boss at a lightening hole, reserving an outer boss on the appearance, and positioning a fixing hole on the inner boss;
s3: roughly milling a second surface: turning and clamping, removing an external boss, reserving a finish machining milling allowance, and roughly milling the other side of the raw material blank (4) to obtain a blank piece;
s4: arranging a tool: according to the shape and the structure of the part (3), a fixed padding tool (1) is distributed on the pore tool (2), and the padding tool (1) can be at least supported on an outer frame structure (31) and a partial groove cavity structure (32) of the part (3);
s5: clamping a blank piece: the blank piece is fixedly connected to the heightening tool (2) through a bolt penetrating through a fixing hole in the inner boss;
s6: finish milling a first surface: finish milling the appearance characteristic, the hole characteristic and the single-side inner cavity characteristic of the machined part (3) to the theoretical size;
s7: finish milling a second surface: turning and clamping, and finish milling the characteristics of the suspended web and the inner cavity of the other side;
s8: repairing pliers: and (5) polishing, removing the inner boss and forming the integral frame part.
9. A numerical control machining method for an integral frame component for aviation as claimed in claim 8, wherein in S6, said hole features at least include tab profile, finishing hole and assembly hole; in S7, the flying web is processed in a direction of increasing rigidity strength.
10. The numerical control machining method for the aviation integral frame part as claimed in claim 9, wherein in S6 and S7, finish milling is carried out on a bridge machine tool by using a cutter with a length-diameter ratio of not more than 3:1 and parameters of not more than 5mm in cutting depth and not more than 2mm in cutting width.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210061940.6A CN114473380B (en) | 2022-01-19 | 2022-01-19 | Numerical control machining method for aviation integral frame part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210061940.6A CN114473380B (en) | 2022-01-19 | 2022-01-19 | Numerical control machining method for aviation integral frame part |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114473380A true CN114473380A (en) | 2022-05-13 |
| CN114473380B CN114473380B (en) | 2023-05-05 |
Family
ID=81473208
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210061940.6A Active CN114473380B (en) | 2022-01-19 | 2022-01-19 | Numerical control machining method for aviation integral frame part |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114473380B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3166160U (en) * | 2010-10-27 | 2011-02-24 | パナソニック株式会社 | Fixing jig and processing device for workpiece |
| CN102729071A (en) * | 2012-07-23 | 2012-10-17 | 杭州和泰机电工业有限公司 | Automatic clamping tool for chain plate processing |
| US20130040743A1 (en) * | 2010-02-12 | 2013-02-14 | Simon Kind | Method of Forming Anchors |
| CN210099509U (en) * | 2019-05-31 | 2020-02-21 | 四川省嘉绮瑞航空装备有限公司 | Milling tool suitable for airplane parts |
| CN210255284U (en) * | 2019-08-06 | 2020-04-07 | 江西华林金建科技有限公司 | Four-axis rotating tool clamp |
| CN212946691U (en) * | 2020-07-20 | 2021-04-13 | 吴友泉 | Lateral quick pneumatic tool |
| CN213380381U (en) * | 2020-10-13 | 2021-06-08 | 南昌新宝路航空科技有限公司 | Integrative general frock of location clamping of standard multiple distance |
| CN214559259U (en) * | 2021-06-04 | 2021-11-02 | 成都爱乐达航空制造股份有限公司 | CNC general adaptation bed hedgehopping anchor clamps |
-
2022
- 2022-01-19 CN CN202210061940.6A patent/CN114473380B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130040743A1 (en) * | 2010-02-12 | 2013-02-14 | Simon Kind | Method of Forming Anchors |
| JP3166160U (en) * | 2010-10-27 | 2011-02-24 | パナソニック株式会社 | Fixing jig and processing device for workpiece |
| CN102729071A (en) * | 2012-07-23 | 2012-10-17 | 杭州和泰机电工业有限公司 | Automatic clamping tool for chain plate processing |
| CN210099509U (en) * | 2019-05-31 | 2020-02-21 | 四川省嘉绮瑞航空装备有限公司 | Milling tool suitable for airplane parts |
| CN210255284U (en) * | 2019-08-06 | 2020-04-07 | 江西华林金建科技有限公司 | Four-axis rotating tool clamp |
| CN212946691U (en) * | 2020-07-20 | 2021-04-13 | 吴友泉 | Lateral quick pneumatic tool |
| CN213380381U (en) * | 2020-10-13 | 2021-06-08 | 南昌新宝路航空科技有限公司 | Integrative general frock of location clamping of standard multiple distance |
| CN214559259U (en) * | 2021-06-04 | 2021-11-02 | 成都爱乐达航空制造股份有限公司 | CNC general adaptation bed hedgehopping anchor clamps |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114473380B (en) | 2023-05-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107717342B (en) | Special-shaped depth blind hole antenna house processing method | |
| CN104259774A (en) | Plane wing titanium alloy thin-wall web efficient numerical control machining technology | |
| CN102489720B (en) | Process for controlling machining deformation of L-shaped aluminum alloy thin-wall end frames | |
| CN102303226A (en) | Method for controlling distortion of large-sized integral structural member in numerical control machining | |
| CN204036079U (en) | Aircraft wing titanium alloy thin wall web HECNCM special fixture | |
| CN107695628B (en) | Processing method for deformed bracket part made of aluminum alloy material | |
| CN114473380A (en) | Numerical control machining method for aviation integral frame part | |
| CN102922232B (en) | Machining process for non-standard clamp components | |
| CN109732279B (en) | Processing method of massage chair turbine box | |
| CN208743592U (en) | Decorative pattern spline rolls seat | |
| CN108202213B (en) | Numerical control machining method for cutting blanks in set | |
| CN114799779B (en) | Numerical control machining method and tool for beam die forging with A-shaped aluminum alloy integral structure | |
| CN101992223A (en) | Processing method of porous round bar die | |
| CN202317754U (en) | Processing tool for stainless-steel sheet parts | |
| CN105057992A (en) | Low-rigidity turbine blade milling clamp and use method thereof | |
| CN114029708B (en) | Processing technology of diffuser air flow channel and digital milling clamp | |
| CN112935707A (en) | Machining method for airplane support type parts | |
| CN114603375B (en) | Machining tool and machining process for thin-wall plate parts | |
| CN109571024A (en) | A kind of medium block parts processing tooling and method | |
| CN112958846B (en) | Forming method for semi-closed complex deep inner cavity of sealing disc | |
| CN204997383U (en) | A frock for processing of horizontal machining center former | |
| CN216138167U (en) | Special automatic centering jig for hub of machining center | |
| CN214557713U (en) | Automatic rotation mechanism of power head | |
| CN114178785B (en) | Method for processing brim-shaped curved wall plate part | |
| CN219293366U (en) | Outer circle milling grooving fixing tool for goods shelf emergency stop rod |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |