CN109420923A - A kind of undercarriage bearing hole method for fine finishing - Google Patents

A kind of undercarriage bearing hole method for fine finishing Download PDF

Info

Publication number
CN109420923A
CN109420923A CN201710735748.XA CN201710735748A CN109420923A CN 109420923 A CN109420923 A CN 109420923A CN 201710735748 A CN201710735748 A CN 201710735748A CN 109420923 A CN109420923 A CN 109420923A
Authority
CN
China
Prior art keywords
bearing hole
lose
undercarriage
processing
undercarriage bearing
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
Application number
CN201710735748.XA
Other languages
Chinese (zh)
Inventor
廖勇
王亮
李晓青
田俊
卢晓红
蔡永军
李连浩
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AVIC Guizhou Aircraft Co Ltd
Original Assignee
AVIC Guizhou Aircraft Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by AVIC Guizhou Aircraft Co Ltd filed Critical AVIC Guizhou Aircraft Co Ltd
Priority to CN201710735748.XA priority Critical patent/CN109420923A/en
Publication of CN109420923A publication Critical patent/CN109420923A/en
Pending legal-status Critical Current

Links

Classifications

    • 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
    • B23Q3/18—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for positioning only
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23B—TURNING; BORING
    • B23B41/00—Boring or drilling machines or devices specially adapted for particular work; Accessories specially adapted therefor
    • 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

Abstract

A kind of undercarriage bearing hole method for fine finishing, including finding out physical location of the undercarriage bearing hole under aircraft axes using laser tracker measurement, the theoretical coordinate value of bearing hole is run on numerically-controlled machine tool again, lathe is moved at undercarriage bearing hole, dual output processing head is installed on machine tool chief axis, the size that lose-lose is lifted one's head mutually is coordinated with undercarriage bearing hole, can satisfy the requirement of processing space；With again the knife bar of process tool, Cutting tool installation manner in the left side that lose-lose is lifted one's head, left side undercarriage bearing hole is processed；After the processing of left side, processing nut arbor, cutter are changed the outfit in the right side that lose-lose is lifted one's head, processing right side undercarriage bearing hole.The undercarriage bearing hole method for fine finishing can preferably improve machining accuracy, reduce labor intensity, improve processing work efficiency.Also, easy to operate, labor intensity is small, and processing quality is high, can completely disengage traditional drilling jig tool, realizes Flexible Manufacture.

Description

A kind of undercarriage bearing hole method for fine finishing
Technical field
The present invention relates to undercarriage bearing hole processing technique fields, more particularly to a kind of undercarriage bearing hole Method for fine finishing.
Background technique
For undercarriage bearing hole for installing undercarriage, bearing hole or so concentricity, requirement on machining accuracy are high； It is main at present to be processed using traditional tooling drill jig, first carry out reaming, then finally reamed, guaranteed by drill jig it is left, The concentricity of right side processing, such processing method need a large amount of drilling jig tool, further reduce processing space, and operation is tired Difficulty, large labor intensity, working efficiency is low, and processing quality is poor.
Summary of the invention
In order to solve the above technical problems, the present invention provides the precision that one kind had not only guaranteed undercarriage bearing hole machined, but also energy Labor intensity is effectively reduced, improves processing work efficiency, realizes the undercarriage bearing hole method for fine finishing of Flexible Manufacture.
A kind of undercarriage bearing hole method for fine finishing, comprising the following steps: (1) found out using laser tracker measurement Physical location of the undercarriage bearing hole in aircraft axes；(2) theoretical coordinate value (front and back numerical value and the height of frame bearing hole will be fallen Numerical value) it inputs in lathe, it allows lathe to move to and falls at frame bearing hole theoretical position；(3) knife bar, Cutting tool installation manner are lifted one's head a left side in lose-lose Side, processing left side undercarriage bearing hole；(4) by left side knife bar, cutter change the outfit to lose-lose lift one's head right side, processing right side undercarriage axis Bearing bore；(5) knife bar, cutter are removed, completes manufacturing procedure.
It is had the beneficial effect that by what the technological means present invention obtained, which can It is preferable to improve machining accuracy, labor intensity is reduced, processing work efficiency is improved.Also, easy to operate, labor intensity is small, adds Working medium amount is high, can completely disengage traditional drilling jig tool, realizes Flexible Manufacture.
Specific embodiment
Principles and features of the present invention are described below in conjunction with example, example is served only for explaining invention, not For limiting the scope of the invention.
A kind of undercarriage bearing hole method for fine finishing, comprising the following steps: (1) found out using laser tracker measurement Physical location of the undercarriage bearing hole in aircraft axes；(2) theoretical coordinate value (front and back numerical value and the height of frame bearing hole will be fallen Numerical value) it inputs in lathe, it allows lathe to move to and falls at frame bearing hole theoretical position；(3) knife bar, Cutting tool installation manner are lifted one's head a left side in lose-lose Side, processing left side undercarriage bearing hole；(4) by left side knife bar, cutter change the outfit to lose-lose lift one's head right side, processing right side undercarriage axis Bearing bore；(5) knife bar, cutter are removed, completes manufacturing procedure.It is walked first by lathe and determines hole location in conjunction with laser tracker The front-rear position and high and low position of processing determine the origin of hole location processing, are positioned by lathe and laser tracker, positioning accuracy It is far longer than the positioning accuracy of tooling drill jig, positioning accuracy can reach 0.1mm, and positioning accuracy is high；Since lose-lose is lifted one's head and is processed Knife bar precision-fit, the concentricity of cutter right and left mutually changing reach 0.01mm, are on the other hand processed by way of bore hole, essence Degree reaches 0.01mm, can greatly improve machining accuracy.
Above-mentioned technical proposal only embodies the optimal technical scheme of technical solution of the present invention, those skilled in the art The principle of the present invention is embodied to some variations that some of them part may be made, belongs to the scope of protection of the present invention it It is interior.

Claims (1)

1. a kind of undercarriage bearing hole method for fine finishing, it is characterised in that: the described method comprises the following steps:
(1) undercarriage bearing hole is found out in the physical location of aircraft axes using laser tracker measurement；
(2) by numerical value before and after the theoretical coordinate of undercarriage bearing hole and high degree input lathe, lathe is allowed to move to undercarriage axis At bearing bore theoretical position；
(3) by knife bar, Cutting tool installation manner on the left of lose-lose is lifted one's head, processing left side undercarriage bearing hole；
(4) by left side knife bar, cutter change the outfit to lose-lose lift one's head right side, processing right side undercarriage bearing hole；
(5) knife bar, cutter are removed, completes manufacturing procedure.
CN201710735748.XA 2017-08-24 2017-08-24 A kind of undercarriage bearing hole method for fine finishing Pending CN109420923A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201710735748.XA CN109420923A (en) 2017-08-24 2017-08-24 A kind of undercarriage bearing hole method for fine finishing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710735748.XA CN109420923A (en) 2017-08-24 2017-08-24 A kind of undercarriage bearing hole method for fine finishing

Publications (1)

Publication Number Publication Date
CN109420923A true CN109420923A (en) 2019-03-05

Family

ID=65499347

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201710735748.XA Pending CN109420923A (en) 2017-08-24 2017-08-24 A kind of undercarriage bearing hole method for fine finishing

Country Status (1)

Country Link
CN (1) CN109420923A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112937906A (en) * 2019-12-10 2021-06-11 中航贵州飞机有限责任公司 Training plane wing and fuselage large-space combined intersection hole position fault compensation method

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102416581A (en) * 2011-08-30 2012-04-18 北京航空航天大学 Hybrid measurement positioning method of part to be assembled in flexible assembly of airplane components
CN103279140A (en) * 2013-05-29 2013-09-04 成都飞机工业（集团）有限责任公司 Pose adjusting system and adjusting method of out-of-plane component connector intersection hole fine machining
CN103722207A (en) * 2013-12-23 2014-04-16 沈阳飞机工业（集团）有限公司 Automatic hole forming equipment and hole forming method for composite airfoil components
CN103991555A (en) * 2014-03-25 2014-08-20 浙江大学 Automatic measuring method for digitalized airplane assembly
CN104440384A (en) * 2014-10-15 2015-03-25 中航飞机股份有限公司西安飞机分公司 Method for building workpiece numerical control machining coordinate system
CN104759945A (en) * 2015-03-25 2015-07-08 西北工业大学 Mobile hole-making robot standard alignment method based on high precision industrial camera
CN105678023A (en) * 2016-02-24 2016-06-15 浙江大学 Movement parameter identification method of horizontal automatic drilling and riveting machine of aircraft panel
CN105716525A (en) * 2016-03-30 2016-06-29 西北工业大学 Robot end effector coordinate system calibration method based on laser tracker
CN106542113A (en) * 2016-11-02 2017-03-29 浙江大学 A kind of horizontal automatic drill riveter space relative pose error compensating method of aircraft target ship

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102416581A (en) * 2011-08-30 2012-04-18 北京航空航天大学 Hybrid measurement positioning method of part to be assembled in flexible assembly of airplane components
CN103279140A (en) * 2013-05-29 2013-09-04 成都飞机工业（集团）有限责任公司 Pose adjusting system and adjusting method of out-of-plane component connector intersection hole fine machining
CN103722207A (en) * 2013-12-23 2014-04-16 沈阳飞机工业（集团）有限公司 Automatic hole forming equipment and hole forming method for composite airfoil components
CN103991555A (en) * 2014-03-25 2014-08-20 浙江大学 Automatic measuring method for digitalized airplane assembly
CN104440384A (en) * 2014-10-15 2015-03-25 中航飞机股份有限公司西安飞机分公司 Method for building workpiece numerical control machining coordinate system
CN104759945A (en) * 2015-03-25 2015-07-08 西北工业大学 Mobile hole-making robot standard alignment method based on high precision industrial camera
CN105678023A (en) * 2016-02-24 2016-06-15 浙江大学 Movement parameter identification method of horizontal automatic drilling and riveting machine of aircraft panel
CN105716525A (en) * 2016-03-30 2016-06-29 西北工业大学 Robot end effector coordinate system calibration method based on laser tracker
CN106542113A (en) * 2016-11-02 2017-03-29 浙江大学 A kind of horizontal automatic drill riveter space relative pose error compensating method of aircraft target ship

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112937906A (en) * 2019-12-10 2021-06-11 中航贵州飞机有限责任公司 Training plane wing and fuselage large-space combined intersection hole position fault compensation method

Similar Documents

Publication Publication Date Title
CN104259774B (en) Plane wing titanium alloy thin-wall web efficient numerical control machining technology
CN104597838B (en) A kind of deep narrow slot turning processing method of high temperature alloy integral wheel annular
CN102999011A (en) High-temperature alloy thin-wall case numerical-control lathing method
CN104001958A (en) Machining method for deep hole reducing inner cavity
CN204036079U (en) Aircraft wing titanium alloy thin wall web HECNCM special fixture
CN103962807B (en) A kind of method of ram Flexible Manufacture
CN105290475A (en) Method for milling titanium alloy fan blade profiles
CN106312152A (en) Method for machining thin-walled components
CN204075839U (en) A kind of double-deck multiple-cutting-edge wire rod quality equipment for cutter positioning
CN109420923A (en) A kind of undercarriage bearing hole method for fine finishing
CN102699630B (en) Numerically controlled processing method for thin-walled part with open lateral groove end
CN104772604A (en) Processing method of steam nozzle on steam injection coverplate of steam turbine
CN103586517A (en) Narrow deep cavity numerical control milling method of integral impeller
CN204182942U (en) A kind of cutter processing drum barrel ultra-deep inner chamber
CN105522340A (en) Main valve hole machining method for water press distributor valve body
RU2498883C1 (en) Method of making compressor blade
CN105479099A (en) Improved technology for machining deep groove parts by numerically-controlled lathe
CN203030946U (en) Multifunctional tool clamp special for numerically controlled lathe
CN203649485U (en) Arc forming drill
CN203235981U (en) Multi-station compound cutter for machine tool
CN207448037U (en) A kind of testpieces for testing Machine-settings
CN204338945U (en) A kind of novel lathe
CN204135343U (en) A kind of for the assembled tool from plate front in locomotive buffer unit
CN205032744U (en) Knife rest structure for processing watch clamping plate by numerical control lathe
CN205183843U (en) Eccentric double -end drilling machine

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

Application publication date: 20190305

RJ01 Rejection of invention patent application after publication