CN112173160B - Forming process of unmanned aerial vehicle wing and clamping tool thereof - Google Patents
Forming process of unmanned aerial vehicle wing and clamping tool thereof Download PDFInfo
- Publication number
- CN112173160B CN112173160B CN201910588800.2A CN201910588800A CN112173160B CN 112173160 B CN112173160 B CN 112173160B CN 201910588800 A CN201910588800 A CN 201910588800A CN 112173160 B CN112173160 B CN 112173160B
- Authority
- CN
- China
- Prior art keywords
- wing
- clamping tool
- tool
- processing
- 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.)
- Active
Links
Images
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q2703/00—Work clamping
- B23Q2703/02—Work clamping means
- B23Q2703/10—Devices for clamping workpieces of a particular form or made from a particular material
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Jigs For Machine Tools (AREA)
Abstract
The invention discloses a forming process of an unmanned aerial vehicle wing and a tail wing and a clamping tool thereof, wherein the wing chord of the wing is used as a datum line for carrying out surface division and sectional type processing on the wing, the processing of the wing can be accurately completed by adopting a three-axis CNC (computer numerical control) in a surface division and sectional processing mode, the processing cost is saved, and meanwhile, the problem of deformation caused by uneven stress of the wing due to too thin wing in the processing process can be avoided by combining the sectional type processing method completed by the clamping tool.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle manufacturing, in particular to a forming process of an unmanned aerial vehicle wing and a clamping tool thereof.
Background
The wing is one of important parts of the unmanned aerial vehicle system, and has the main function of generating lifting force so as to support the aircraft to fly in the air and also plays a certain role in stabilizing and manipulating; the aerodynamic characteristics of the unmanned aerial vehicle are directly affected by the wing parameter design of the unmanned aerial vehicle; in the existing wing manufacturing process, a CNC numerical control machine tool is adopted for machining or injection molding of a mold, wherein in order to ensure the precision of wing machining, a five-axis CNC numerical control machine tool is generally adopted, and the cost of a craftsman is high, but in the prior art, a fixture is required to clamp the wing by adopting a three-axis CNC numerical control machine tool, and because the wing is an airfoil with radian on two sides, the CNC numerical control machine tool cannot clamp the wing well; and only clamp wing length direction's one end or both ends when using CNC digit control machine tool clamping, but because of current unmanned aerial vehicle wing thickness is less than 6mm, the condition that the wing warp appears easily in case when processing longer wing.
Disclosure of Invention
The invention aims to provide a forming process and a clamping tool for an unmanned aerial vehicle wing, and aims to solve the problems of high processing cost and easy deformation in processing in the background technology.
In order to achieve the above purpose, the invention provides a forming process of an unmanned aerial vehicle wing, which takes the chord of the wing as a datum line to carry out surface and sectional processing on the wing, and comprises the following steps:
s1: preparing a workpiece blank for manufacturing the wing;
s2: machining one surface of a workpiece blank at a high speed by adopting a triaxial CNC (computer numerical control) linkage, and machining one airfoil surface of the airfoil;
s3: turning over the workpiece blank to the other surface, and equally dividing the workpiece blank into a plurality of processing sections;
s4: fixing a processing section by using a clamping tool, and then processing the processing section sequentially by adopting three-axis CNC numerical control linkage;
s5: finishing the treatment of the processing section, and fixing the adjacent processing sections by using a clamping tool for processing;
s6: and (5) circularly executing the steps S4 and S5 until the wing is molded.
Preferably, the specific method for fixing the wing by the clamping tool comprises the following steps: the first clamping tool is fixed at a position which is finished in machining and is adjacent to a machining section to be machined, and the second clamping tool is fixed at a position which is unprocessed and is adjacent to the machining section to be machined.
The clamping tool for the unmanned aerial vehicle wing molding comprises a first clamping tool and a second clamping tool, wherein the first clamping tool is fixed on a machined machining section, the first clamping tool comprises an upper clamp and a lower clamp, and wing grooves which are communicated with wing surfaces of corresponding wings are respectively formed in the end surfaces of the upper clamp and the lower clamp corresponding to the machining section; the second clamping tool is fixed on an unprocessed processing section and comprises an upper tool and a lower tool, wherein a notch corresponding to the airfoil surface is formed in the lower tool.
Preferably, the upper fixture and the lower fixture and the upper fixture and the lower fixture are connected and fixed through adjusting bolts.
Compared with the prior art, the invention has the beneficial effects that: through the split and sectional machining mode, the machining of the wing with the thinner thickness can be accurately finished by using the triaxial CNC numerical control, so that the machining cost is saved, and meanwhile, the problem of deformation caused by uneven stress of the wing due to too thin wing in the machining process can be avoided by combining the sectional machining method finished by the clamping tool.
Drawings
FIG. 1 is a chord explanatory diagram of a wing;
FIG. 2 is a process flow diagram of the present invention;
fig. 3 is a schematic structural diagram of the clamping tool of the present invention.
In the figure: 1. the first clamping tool, 1-1 part of an upper clamp, 1-2 parts of a lower clamp, 1-3 parts of a wing groove, 2 parts of a second clamping tool, 2-1 parts of an upper tool, 2-2 parts of a lower tool, 2-3 parts of a notch
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1, the airfoil of the wing has a series of lines inscribing the center of circles, also called camber lines, the front end point of which is called the leading edge, the rear end point is called the trailing edge, and the lines between the leading edge and the trailing edge are called chords or geometric chords.
Referring to fig. 2-3, the present invention provides a technical solution: the forming process of the unmanned aerial vehicle wing and the empennage takes the chord of the wing as a datum line to carry out surface division and sectional processing on the wing, and comprises the following steps:
s1: preparing a workpiece blank for manufacturing the wing, wherein the workpiece blank is an aluminum alloy 7075 plate with the thickness of 5mm and is mainly used for processing the wing with the thickness of thin, the minimum thickness can reach 0.5mm, a wing with the length of 220mm and the width of 50mm is processed, and the length of 230mm, the thickness of 5mm and the width of 60mm of the workpiece blank are taken;
s2: fixing two ends of a workpiece blank, and then adopting three-axis CNC (computer numerical control) linkage to process one surface of the workpiece blank at high speed, and firstly processing one airfoil surface of the airfoil;
s3: turning over the workpiece blank to the other surface, and equally dividing the workpiece blank into a plurality of processing sections;
s4: fixing a processing section by using a clamping tool, and then processing the processing section sequentially by adopting three-axis CNC numerical control linkage;
s5: finishing the treatment of the processing section, and fixing the adjacent processing sections by using a clamping tool for processing;
s6: and (5) circularly executing the steps S4 and S5 until the wing is molded.
The specific method for fixing the wing by the clamping tool comprises the following steps: the first clamping tool is fixed at a position which is finished in a machining mode and is adjacent to a machining section to be machined, the second clamping tool is fixed at a position which is unprocessed and is adjacent to the machining section to be machined, and the two ends of the fixed machining section are shortened to shorten the machining length of the wing, so that the situation that the machine tool only fixes the two ends of the wing because the length of the wing is overlong, and the middle section of the wing is too thin to deform under stress is avoided;
meanwhile, the processing section of the head end and the processing section of the tail end only need one clamping tool, namely the processing section of the head end is fixed at the adjacent and unprocessed processing section by using a second clamping tool; the processing section of tail end uses first clamping frock to fix in adjacent and processed processing section department.
The clamping tool for forming the wings and the tail wings of the unmanned aerial vehicle consists of a first clamping tool 1 and a second clamping tool 2, wherein the first clamping tool 1 is fixed on a machined machining section, the first clamping tool 1 comprises an upper clamp 1-1 and a lower clamp 1-2, wing grooves 1-3 which are communicated with wing surfaces of the corresponding wings are respectively formed in the end surfaces of the upper clamp 1-1 and the lower clamp 1-2, and the wing grooves 1-3 are adapted to the wing surfaces at the fixed machining section; the second clamping tool 2 is fixed on an unprocessed processing section, the second clamping tool 2 comprises an upper tool 2-1 and a lower tool 2-2, wherein a notch 2-3 corresponding to an airfoil is formed in the lower tool 2-2, the notch 2-3 is adapted to the airfoil at the fixed processing section, and meanwhile, the upper clamp 1-1 and the lower clamp 1-2 and the upper tool 2-1 and the lower tool 2-2 are connected and fixed through adjusting bolts, so that the effect of clamping and fixing a workpiece blank is achieved.
Although the present invention has been described with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements and changes may be made without departing from the spirit and principles of the present invention.
Claims (3)
1. The forming process of the unmanned aerial vehicle wing is characterized by taking the chord of the wing as a datum line to carry out surface division and sectional processing on the wing, and comprises the following steps of:
s1: preparing a workpiece blank for manufacturing the wing;
s2: machining one surface of a workpiece blank at a high speed by adopting a triaxial CNC (computer numerical control) linkage, and machining one airfoil surface of the airfoil;
s3: turning over the workpiece blank to the other surface, and equally dividing the workpiece blank into a plurality of processing sections;
s4: fixing a processing section by using a clamping tool, and then processing the processing section sequentially by adopting three-axis CNC numerical control linkage;
s5: finishing the treatment of the processing section, and fixing the adjacent processing sections by using a clamping tool for processing;
s6: s4, S5 steps are circularly executed until the wing is formed;
the machining device comprises a first clamping tool, a second clamping tool, a first clamping tool and a second clamping tool, wherein the first clamping tool is fixed at a position which is finished in machining and is adjacent to a machining section to be machined; and
when the wing head end is machined, the second clamping tool is used for fixing the wing head end at an adjacent machining section which is not machined; and when the tail end of the wing is machined, the first clamping tool is used for fixing the tail end of the wing at the adjacent machined machining section.
2. The clamping tool for forming the unmanned aerial vehicle wing is characterized by comprising a first clamping tool (1) and a second clamping tool (2), wherein the first clamping tool (1) is fixed on a machined machining section, the first clamping tool (1) comprises an upper clamp (1-1) and a lower clamp (1-2), and wing grooves (1-3) which are communicated with wing surfaces of the corresponding wing are respectively formed in the end surfaces of the upper clamp (1-1) and the lower clamp (1-2) corresponding to the machining section; the second clamping tool (2) is fixed on an unprocessed processing section, the second clamping tool (2) comprises an upper tool (2-1) and a lower tool (2-2), and a notch (2-3) corresponding to the airfoil surface is formed in the lower tool (2-2).
3. The unmanned aerial vehicle wing forming clamping tool according to claim 2, wherein the upper clamp (1-1) and the lower clamp (1-2) and the upper tool (2-1) and the lower tool (2-2) are connected and fixed through adjusting bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910588800.2A CN112173160B (en) | 2019-07-02 | 2019-07-02 | Forming process of unmanned aerial vehicle wing and clamping tool thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910588800.2A CN112173160B (en) | 2019-07-02 | 2019-07-02 | Forming process of unmanned aerial vehicle wing and clamping tool thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112173160A CN112173160A (en) | 2021-01-05 |
| CN112173160B true CN112173160B (en) | 2023-05-26 |
Family
ID=73914984
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910588800.2A Active CN112173160B (en) | 2019-07-02 | 2019-07-02 | Forming process of unmanned aerial vehicle wing and clamping tool thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112173160B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112722318B (en) * | 2021-01-18 | 2023-06-23 | 成都纵横鹏飞科技有限公司 | Unmanned aerial vehicle assembly debugging rack |
| CN113001125A (en) * | 2021-03-19 | 2021-06-22 | 沈阳万事达机械有限公司 | Process flow of empennage framework |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4316059B2 (en) * | 1999-08-06 | 2009-08-19 | 富士重工業株式会社 | Manufacturing method of composite wing |
| CN103639655B (en) * | 2013-11-28 | 2016-08-17 | 江西洪都航空工业集团有限责任公司 | A kind of manufacturing process of high-curvature full-profile thin-wall part |
| CN108248824B (en) * | 2017-12-29 | 2021-12-21 | 南京航空航天大学 | Wing surface leading edge structure of micro unmanned aerial vehicle, forming die and preparation method of wing surface leading edge structure |
| CN108583931B (en) * | 2018-05-21 | 2020-11-03 | 沈观清 | Advanced manufacturing process for small and medium-sized unmanned aerial vehicle |
| CN109514200B (en) * | 2018-12-06 | 2020-07-31 | 上海无线电设备研究所 | Method for manufacturing nonlinear arc-shaped empennage |
-
2019
- 2019-07-02 CN CN201910588800.2A patent/CN112173160B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN112173160A (en) | 2021-01-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112173160B (en) | Forming process of unmanned aerial vehicle wing and clamping tool thereof | |
| US4256555A (en) | Electro-chemical-machining of aerofoil blades | |
| CN102862035B (en) | Method for symmetrically and precisely cutting and machining thin-wall blade by regions and special clamp thereof | |
| CN104476118A (en) | Manufacturing method of airplane chemical milling skin three-dimensional chemical milling sample plate | |
| CN110605538B (en) | Anti-side bending method in long beam part machining process | |
| CN107984179A (en) | A kind of quick method for preparing double installing plate blades | |
| CN105290712A (en) | Machining method of curved surface part | |
| CN104482892B (en) | Spatial special casts the datum tool method of nacelle | |
| CN112276490B (en) | Method for processing large-scale cast stainless steel wing cabin fusion cabin section | |
| CN103577635A (en) | Fitting method of blade surface data | |
| CN106041233A (en) | Square throttling hole linear cutting positioning tool of ultrahigh-precision servo valve sleeve and method thereof | |
| CN104625571A (en) | Age-hardening aluminum alloy cutting method | |
| CN108788208B (en) | Boring method for machining intersection angle box hole system | |
| CN104400475B (en) | A kind of positioning and clamping instrument and method | |
| CN110449648B (en) | Cutter and method for machining eccentric shaft clearance groove | |
| CN115533134A (en) | Method for processing flange edge of large thin-wall part | |
| CN108655417A (en) | A method of using accurate symmetrical layered circulation turning complex thin-wall component type face | |
| CN106516152A (en) | Technological method for finish machining of docking surface of vertical tail and fuselage of aircraft | |
| CN111037367B (en) | Finish machining alignment method for high-precision thin-walled workpiece | |
| CN112371846B (en) | Multifunctional skin stretch-forming die and stretch-forming method | |
| CN101569975B (en) | Method for changing die shape | |
| CN110899782B (en) | Machining method for self-adaptive milling of external surface of split case | |
| CN209095021U (en) | A kind of CNC finishing thin-wall part inner cavity special fixture | |
| CN106837710A (en) | A kind of wind wheel blade web turnup structure and its manufacture craft | |
| CN205996594U (en) | A kind of frock for processing model aircraft multistage rudder face part |
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 | ||
| CB02 | Change of applicant information |
Address after: 315000 room 412, floor 4, building 2, Lane 218, Qingyi Road, high tech Zone, Ningbo, Zhejiang Province Applicant after: Ningbo Yutu Aviation Technology Co.,Ltd. Address before: 315700 1st floor, building 4, No. 367, Buzheng East Road, Wangchun Industrial Park, Ningbo City, Zhejiang Province Applicant before: Ningbo Haishu Yutu Aviation Technology Co.,Ltd. |
|
| CB02 | Change of applicant information | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |