CN110814654A - Manufacturing method of aluminum-based composite movable ring of ultra-large helicopter - Google Patents
Manufacturing method of aluminum-based composite movable ring of ultra-large helicopter Download PDFInfo
- Publication number
- CN110814654A CN110814654A CN201911116148.0A CN201911116148A CN110814654A CN 110814654 A CN110814654 A CN 110814654A CN 201911116148 A CN201911116148 A CN 201911116148A CN 110814654 A CN110814654 A CN 110814654A
- Authority
- CN
- China
- Prior art keywords
- ultra
- aluminum
- manufacturing
- based composite
- machining
- 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.)
- Pending
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Milling Processes (AREA)
- Forging (AREA)
Abstract
The invention relates to the field of machining, in particular to a method for manufacturing an aluminum-based composite material moving ring of an ultra-large helicopter. The method comprises the following steps: step 1, clamping a part; step 2, scanning and registering; step 3, rough machining; step 4, flaw detection; step 5, artificial aging; step 6, semi-finishing; step 7, natural aging; step 8, fine machining; step 9, size detection; step 10, performing bench work; step 11, flaw detection; and step 12, chromic acid anodizing. The high-periodicity one-time cutting manufacturing of parts is realized, and the requirements of dimensional accuracy and form and position accuracy are met; the technology for controlling the deformation of the large-diameter hole system of the aluminum-based part is broken through, the product quality and the dimensional accuracy stability of the manufacturing process of the ultra-large helicopter moving part are improved through the technical scheme, and the flying safety stability of the helicopter moving part is effectively ensured.
Description
Technical Field
The invention relates to the field of machining, in particular to a method for manufacturing an aluminum-based composite material moving ring of an ultra-large helicopter.
Background
The manufacturing of high-cycle fatigue dynamic parts of ultra-large aluminum matrix composite materials is the first case in China, and the manufacturing process needs to be explored and summarized.
Disclosure of Invention
The purpose of the invention is as follows: a method for manufacturing an aluminum-based composite movable ring of an ultra-large helicopter is provided.
The technical scheme is as follows:
a manufacturing method of an aluminum-based composite material moving ring of an ultra-large helicopter comprises the following steps:
step 1, clamping a part;
step 2, scanning and registering;
step 3, rough machining;
step 4, flaw detection;
step 5, artificial aging;
step 6, semi-finishing;
step 7, natural aging;
step 8, fine machining;
step 9, size detection;
step 10, performing bench work;
step 11, flaw detection;
and step 12, chromic acid anodizing.
The step 1 specifically comprises the following steps: and connecting the threaded pin by using a non-processing area residual process table mode to fix and clamp the blank.
The step 2 specifically comprises the following steps: and establishing a digital model of the forge piece through a three-dimensional scanner, and carrying out digital through blank scribing, equal distribution of attitude adjustment allowance and offset rotation data transmission numerical control five-axis equipment to carry out reference hole surface machining.
The step 3 specifically comprises the following steps: and (3) aligning the rough datum according to the datum hole surface, and performing machining and milling by using a welded PCD polycrystalline diamond blade cutter to reserve a machining allowance of 3-4 mm.
The step 4 specifically comprises the following steps: capillary phenomenon is utilized by fluorescence penetration to detect the defect of penetrating fluid, and the penetrating fluid on the cleaned surface detects the defect of the part by capillary action of a developer.
The step 5 specifically comprises the following steps: placing the parts into a low-temperature furnace, wherein the temperature of the low-temperature furnace is as follows: 100-120 ℃, heat preservation time: 3-5 hours, cooling mode: and air cooling.
The step 6 specifically comprises the following steps: the method comprises the steps of machining the theoretical contour dimension of the PCD by using an integral alloy type PCD cutter to the final requirement, reserving 1-1.5 mm of machining allowance in a key dimension area, wherein the key dimension area is an area with the possibility of fatigue fracture.
The step 8 specifically comprises the following steps: the integral alloy type PCD cutter is adopted to carry out one-step forming processing of key size by driving, milling and boring, and the tolerance size requirement of the hole system is ensured.
The step 9 specifically comprises the following steps: and the three-coordinate measurement of the space and the theoretical contour dimension is finished, the tolerance dimension of the key hole system adopts the same material to the surface piece, and the constant temperature detection is carried out to ensure that the dimensional deformation coefficients of the key hole system are consistent.
The step 10 specifically comprises: and (3) clamping tapping threads, wherein the threads are manufactured by adopting a PCD coating screw tap to perform extrusion mode thread forming, and the requirement on the thread strength of the moving part is met.
Has the advantages that:
aiming at the structure of the ultra-large composite material forging, the invention innovatively adopts the process methods of main positioning of a reserved process table, maximum stress release, integral forming of key elements and the like, thereby ensuring the high-precision quality requirement; the PCD cutter with large length-diameter ratio is innovatively adopted, and the high-periodicity one-time cutting manufacturing of parts is realized by using the mode of combining the cutter parameter ratio and the polycrystal abrasion mechanism analysis, so that the requirements of dimensional precision and form and position precision are met; the technology for controlling the deformation of the large-diameter hole system of the aluminum-based part is broken through, the product quality and the dimensional accuracy stability of the manufacturing process of the ultra-large helicopter moving part are improved through the technical scheme, and the flying safety stability of the helicopter moving part is effectively ensured.
Drawings
FIG. 1 is a flow chart of the present invention.
Detailed Description
As shown in FIG. 1, a process for manufacturing an ultra-large aluminum-based rotating ring comprises the following steps:
A. the part clamping scheme is as follows: and connecting the threaded pin by using a non-processing area residual process table mode to fix and clamp the blank.
B. Tool design: the design comprises auxiliary support and a process table positioning connecting hole to meet the limitation of enough bearing and clamping force and freedom degree in the machining process, so that the workpiece is positioned stably, reliably and openly, and the feed area in the machining process is maximized
C, scanning and registering: and (3) establishing a digital model of the forge piece through a three-dimensional scanner, and carrying out digital through blank scribing, equal distribution of attitude adjustment allowance and offset rotation data transmission numerical control five-axis equipment to carry out reference hole surface machining (the reference hole straightening part determines X and Y references, and the reference surface is positioned to determine Z value reference).
The registration of the ultra-large forging meets the following requirements:
① fatigue area allowance distribution size precision is plus or minus 0.1 mm;
② distribution precision of machining allowance is +/-0.2 mm;
③ Scan line Filter Standard deviation 0.025mm.
D. Rough machining: and (3) aligning the rough datum according to the datum hole surface, and performing machining and milling by using a welded PCD polycrystalline diamond blade cutter to reserve a machining allowance of 3-4 mm. (roughing preferentially ensures maximum metal removal)
E. Flaw detection: capillary phenomenon is utilized by fluorescence penetration to detect the defect of penetrating fluid, and the penetrating fluid on the cleaned surface detects the defect of the part by capillary action of a developer.
F. Aging: putting the parts into a low-temperature furnace, wherein the temperature is as follows: 100-120 ℃, heat preservation time: 3-5 hours, cooling mode: air cooling (after machining, parts are often greatly deformed due to stress release, and in order to stabilize the size and reduce the influence of residual stress on the parts, a stabilizing treatment process can be adopted to eliminate the stress.)
G. Semi-finishing: the method comprises the steps of machining the theoretical contour dimension of the PCD by using an integral alloy type PCD cutter to the final requirement, reserving 1-1.5 mm of machining allowance in a key dimension area, wherein the key dimension area is an area with the possibility of fatigue fracture.
H. Natural aging: naturally standing for 72 hours, releasing residual stress after machining, and ensuring the key dimension stability of the part.
I. Finish machining: the integral alloy type PCD cutter is adopted to carry out one-step forming processing of key size by driving, milling and boring, and the tolerance size requirement of the hole system is ensured.
J. And (3) size detection: and the three-coordinate measurement of the space and the theoretical contour dimension is finished, the tolerance dimension of the key hole system adopts the same material to the surface piece, and the constant temperature detection is carried out to ensure that the dimensional deformation coefficients of the key hole system are consistent.
K. Performing bench work: and (3) clamping tapping threads, wherein the threads are manufactured by adopting a PCD coating screw tap to perform extrusion mode thread forming, and the requirement on the thread strength of the moving part is met.
L, flaw detection: secondary flaw detection, deep detection of part defects and guarantee of quality requirements of moving parts.
M. chromic acid anodizing: free chromic acid, hexavalent chromium, chloride and sulfate are adopted for treatment at 35-40 min.
And in the step of roughly milling the profile of the part, ensuring that the depth of a cutting layer is not greater than the height of the PCD polycrystalline diamond blade.
In the step of processing the part profile, the PCD blade is adopted for processing, and the reciprocating feeding can be adopted from top to bottom.
In the step of processing the key hole system of the part, the final forming mode of drilling before milling can be adopted as boring, a main shaft of a processing machine tool rotates, a long PCD boring cutter is adopted for one-time type processing, and the boring cutter feeding allowance is not more than 0.15 mm.
In the step of forming the part threads, the PCD coating screw tap is required to be formed in a tapping mode, and the requirement on thread strength is met.
In the step of rough machining and finish machining of the part, a rough machining complete positioning principle can be adopted to ensure stable clamping of the part, and finish machining can be carried out by a three-point process table positioning principle, so that a key size machining area has no clamping stress, the clamping size control requirement is ensured to be completely consistent with a natural mode requirement, and the deformation of the part is reduced to the minimum
Part size phi 1680 x 335
The ovality of the phi 600 inner hole size is not more than 0.03mm, and the verticality is not more than 0.05;
the position degree of each support arm hole is not more than 0.05 mm.
Claims (10)
1. A manufacturing method of an aluminum-based composite moving ring of an ultra-large helicopter is characterized by comprising the following steps:
step 1, clamping a part;
step 2, scanning and registering;
step 3, rough machining;
step 4, flaw detection;
step 5, artificial aging;
step 6, semi-finishing;
step 7, natural aging;
step 8, fine machining;
step 9, size detection;
step 10, performing bench work;
step 11, flaw detection;
and step 12, chromic acid anodizing.
2. The manufacturing method of the aluminum-based composite material moving ring of the ultra-large helicopter according to claim 1, characterized in that the step 1 specifically comprises: and connecting the threaded pin by using a non-processing area residual process table mode to fix and clamp the blank.
3. The manufacturing method of the aluminum-based composite material moving ring of the ultra-large helicopter according to claim 1, characterized in that the step 2 specifically comprises: and establishing a digital model of the forge piece through a three-dimensional scanner, and carrying out digital through blank scribing, equal distribution of attitude adjustment allowance and offset rotation data transmission numerical control five-axis equipment to carry out reference hole surface machining.
4. The manufacturing method of the aluminum-based composite material moving ring of the ultra-large helicopter according to claim 1, characterized in that the step 3 specifically comprises: and (3) aligning the rough datum according to the datum hole surface, and performing machining and milling by using a welded PCD polycrystalline diamond blade cutter to reserve a machining allowance of 3-4 mm.
5. The manufacturing method of the aluminum-based composite material moving ring of the ultra-large helicopter according to claim 1, characterized in that the step 4 specifically comprises: capillary phenomenon is utilized by fluorescence penetration to detect the defect of penetrating fluid, and the penetrating fluid on the cleaned surface detects the defect of the part by capillary action of a developer.
6. The manufacturing method of the aluminum-based composite material moving ring of the ultra-large helicopter according to claim 1, characterized in that the step 5 specifically comprises: placing the parts into a low-temperature furnace, wherein the temperature of the low-temperature furnace is as follows: 100-120 ℃, heat preservation time: 3-5 hours, cooling mode: and air cooling.
7. The manufacturing method of the aluminum-based composite material moving ring of the ultra-large helicopter according to claim 1, characterized in that the step 6 specifically comprises: the method comprises the steps of machining the theoretical contour dimension of the PCD by using an integral alloy type PCD cutter to the final requirement, reserving 1-1.5 mm of machining allowance in a key dimension area, wherein the key dimension area is an area with the possibility of fatigue fracture.
8. The manufacturing method of the aluminum-based composite material moving ring of the ultra-large helicopter according to claim 1, characterized in that the step 8 is specifically as follows: the integral alloy type PCD cutter is adopted to carry out one-step forming processing of key size by driving, milling and boring, and the tolerance size requirement of the hole system is ensured.
9. The manufacturing method of the aluminum-based composite material moving ring of the ultra-large helicopter according to claim 1, characterized in that the step 9 is specifically as follows: and the three-coordinate measurement of the space and the theoretical contour dimension is finished, the tolerance dimension of the key hole system adopts the same material to the surface piece, and the constant temperature detection is carried out to ensure that the dimensional deformation coefficients of the key hole system are consistent.
10. The manufacturing method of the aluminum-based composite material moving ring of the ultra-large helicopter according to claim 1, characterized in that the step 10 is specifically as follows: and (3) clamping tapping threads, wherein the threads are manufactured by adopting a PCD coating screw tap to perform extrusion mode thread forming, and the requirement on the thread strength of the moving part is met.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911116148.0A CN110814654A (en) | 2019-11-14 | 2019-11-14 | Manufacturing method of aluminum-based composite movable ring of ultra-large helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911116148.0A CN110814654A (en) | 2019-11-14 | 2019-11-14 | Manufacturing method of aluminum-based composite movable ring of ultra-large helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110814654A true CN110814654A (en) | 2020-02-21 |
Family
ID=69555324
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911116148.0A Pending CN110814654A (en) | 2019-11-14 | 2019-11-14 | Manufacturing method of aluminum-based composite movable ring of ultra-large helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110814654A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112247481A (en) * | 2020-09-22 | 2021-01-22 | 成都鑫三合机电新技术开发有限公司 | Machining method for aviation composite material parts |
| CN112276494A (en) * | 2020-10-28 | 2021-01-29 | 上海航天精密机械研究所 | Method for integrally processing and manufacturing weak-rigidity thin-wall ring frame suitable for spacecraft |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103737266A (en) * | 2013-12-31 | 2014-04-23 | 贵州遵义驰宇精密机电制造有限公司 | Machining method for rear shaft neck of aerial turbofan engine |
| CN104646961A (en) * | 2015-01-05 | 2015-05-27 | 上海应用技术学院 | Process method for improving manufacturing accuracy of aluminum-alloy open-type integral impeller |
| CN106002088A (en) * | 2016-05-24 | 2016-10-12 | 湖北三江航天红阳机电有限公司 | Manufacturing method for integral wing-body-fused cabin |
| CN107175465A (en) * | 2017-05-18 | 2017-09-19 | 济南重工股份有限公司 | The processing technology of typical large diameter thin wall part |
| EP3238865A1 (en) * | 2016-04-29 | 2017-11-01 | Oxford Performance Materials, Inc. | Additive manufacturing process with in situ inspection of metallic objects |
| CN108115357A (en) * | 2016-11-29 | 2018-06-05 | 沈阳格泰水电设备有限公司 | A kind of on-line machining method of blade of large-sized water turbine |
| CN108655669A (en) * | 2018-05-18 | 2018-10-16 | 陕西测易机电设备有限公司 | A kind of processing method of space flight and aviation thin-walled parts |
| CN110052713A (en) * | 2019-03-22 | 2019-07-26 | 江南大学 | Part increases and decreases material composite manufacturing technology |
-
2019
- 2019-11-14 CN CN201911116148.0A patent/CN110814654A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103737266A (en) * | 2013-12-31 | 2014-04-23 | 贵州遵义驰宇精密机电制造有限公司 | Machining method for rear shaft neck of aerial turbofan engine |
| CN104646961A (en) * | 2015-01-05 | 2015-05-27 | 上海应用技术学院 | Process method for improving manufacturing accuracy of aluminum-alloy open-type integral impeller |
| EP3238865A1 (en) * | 2016-04-29 | 2017-11-01 | Oxford Performance Materials, Inc. | Additive manufacturing process with in situ inspection of metallic objects |
| CN106002088A (en) * | 2016-05-24 | 2016-10-12 | 湖北三江航天红阳机电有限公司 | Manufacturing method for integral wing-body-fused cabin |
| CN108115357A (en) * | 2016-11-29 | 2018-06-05 | 沈阳格泰水电设备有限公司 | A kind of on-line machining method of blade of large-sized water turbine |
| CN107175465A (en) * | 2017-05-18 | 2017-09-19 | 济南重工股份有限公司 | The processing technology of typical large diameter thin wall part |
| CN108655669A (en) * | 2018-05-18 | 2018-10-16 | 陕西测易机电设备有限公司 | A kind of processing method of space flight and aviation thin-walled parts |
| CN110052713A (en) * | 2019-03-22 | 2019-07-26 | 江南大学 | Part increases and decreases material composite manufacturing technology |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112247481A (en) * | 2020-09-22 | 2021-01-22 | 成都鑫三合机电新技术开发有限公司 | Machining method for aviation composite material parts |
| CN112276494A (en) * | 2020-10-28 | 2021-01-29 | 上海航天精密机械研究所 | Method for integrally processing and manufacturing weak-rigidity thin-wall ring frame suitable for spacecraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102806443B (en) | Numerically-controlled processing method of nozzle housing piece | |
| CN104384825B (en) | Machining deformation control method of bushing thin-wall part | |
| CN110497162A (en) | A kind of processing method of aero-engine casing | |
| CN105033566B (en) | Suitable for the thin bottom product processing method of thin-walled of Digit Control Machine Tool | |
| CN107511642A (en) | A kind of numerical-control processing method of low rigid interrupted cut precision rotating class part | |
| CN101462178B (en) | Tool and method for processing half-speed machine crankshaft | |
| WO2023070921A1 (en) | Precision numerical control machining method for titanium alloy thin-walled lens barrel part | |
| CN110814654A (en) | Manufacturing method of aluminum-based composite movable ring of ultra-large helicopter | |
| CN104668916A (en) | Method for improving manufacturing precision of large-curvature curved-surface closed integral impeller made of aluminum alloy material | |
| CN104801935A (en) | Method for processing aircraft aluminum alloy special-shaped cabin | |
| CN116493882A (en) | Method for processing thin-wall retaining sleeve type part by using special tool | |
| CN108127341A (en) | A kind of processing technology of precision support bushing class part | |
| CN106312152A (en) | Method for machining thin-walled components | |
| CN103506816A (en) | Processing technique of planet carrier of coal cutter | |
| Pasko et al. | High speed machining (HSM)–the effective way of modern cutting | |
| CN114589464A (en) | Method for machining inner hole of high-precision long and thin cylindrical part | |
| CN104816160A (en) | Turning and drilling compound machine tool | |
| CN214291755U (en) | A frock clamp for numerical control lathe processing step hole | |
| CN102091818A (en) | Slotting and machining method of high-precision internal keyways | |
| CN110732853B (en) | Milling process method for propeller robot | |
| CN104841989A (en) | Machining method of H-shaped thin-wall parts | |
| CN108044307B (en) | Large high-strength alloy steel hook forging and machining method | |
| CN105522210A (en) | Machining method of taper key groove of end face of rotary shaft of large-scale steel rolling motor | |
| CN112548488B (en) | High-precision machining method for large-size annular groove | |
| CN110193702B (en) | Processing method of umbrella-shaped valve disc |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200221 |