CN105081681A - Machining method for helicopter fairing supporting piece - Google Patents
Machining method for helicopter fairing supporting piece Download PDFInfo
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- CN105081681A CN105081681A CN201410213423.1A CN201410213423A CN105081681A CN 105081681 A CN105081681 A CN 105081681A CN 201410213423 A CN201410213423 A CN 201410213423A CN 105081681 A CN105081681 A CN 105081681A
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Abstract
The invention relates to a machining method for a helicopter fairing supporting piece. The method includes the steps that firstly, preprocessing is conducted; secondly, a positioning clamp is installed at the clamping installation location 1, areas except for a middle pressure plate 2 and the clamping installation location 1 are subjected to rough turning, and the allowance is 1mm; thirdly, the middle pressure plate 2 is removed, four lateral clamping plates 4 are installed, a part 3 is fixed from the outer side, and the residual unprocessed areas in the first step are subjected to rough turning, finish turning and finish milling; fourthly, the part and the positioning clamp are connected through cooperation of a sunken hole machined in the second step and a corresponding threaded hole in the positioning clamp, the lateral clamping plates 4 are removed, the residual area of secondary finish turning is subjected to finish turning, and the residual portions, except for a lightening hole, of the part 3 are machined; and fifthly, an outer end pressure plate 5 is installed at the outer end face of the part 3, and the lightening hole in the outer end pressure plate 5 is subjected to rough milling and finish milling. The clamping purpose is reasonably achieved in machining, resources of tools and numerically-controlled machine tools are saved, cycling time is greatly shortened, and a good effect is achieved.
Description
Technical field
The invention belongs to field of machining, relate to a kind of processing method of Helicopter Dome support member.
Background technology
Radome fairing support member is the important component part of helicopter lift system, blank is forging part and accessory size comparatively large (diameter 600mm thickness 230mm), adopt many machine toolings in the past, because clamping difficulty causes processing, stable conditions is poor, so working (machining) efficiency is not high, and take lathe and frock resource is more.
Summary of the invention
The technical problem to be solved in the present invention: the problem that during processing of conventional helicopters radome fairing support member, clamping difficulty causes.
Technical scheme of the present invention: a kind of processing method of Helicopter Dome support member, comprises the following steps,
The first step, preprocessing, part 3 is tapered tubular structure, needs all to carry out turn-milling cutting to its surfaces externally and internally, and before clamping, first at three-axis machining center processing end face, milling location endoporus, bores a dowel hole;
Second step, positioning fixture is arranged on jig installation position 1, by intermediate press plate 2, part 3 is fixed clamping, ensure that blank outer surface and inner surface intermediate press plate more than 2 region can process, rough turn region except intermediate press plate 2 and jig installation position 1, stays 1mm surplus;
3rd step, lays down intermediate press plate 2, installs four side clamping plate 4, fixes from outside by part 3, remains unprocessed region in rough turn, finish turning, the finish-milling first step, comprises the sagging hole that 5 is next step finish turning front clamp;
4th step, part is connected with positioning fixture with the cooperation of respective screw hole on positioning fixture by the sagging hole processed by second step, lays down side clamping plate 4, the remaining area of finish turning second step finish turning, the residue position of processing parts 3 except lightening core;
5th step, installs outer end clamp plate 5 in part 3 outer face, to rough mill, finish-milling 5 place lightening core.
Beneficial effect of the present invention: rationally solve the clamping problem adding man-hour, has saved frock and Digit Control Machine Tool resource, and a large amount of turnaround time.
Accompanying drawing explanation
Fig. 1 is second step clamping schematic diagram of the present invention, and wherein, 1 is positioning fixture, and 2 is intermediate press plate, and 3 is part.
Fig. 2 is the present invention the 3rd step clamping schematic diagram, and wherein, 4 is side clamping plate, and 5 is hole of sinking.
Fig. 3 is the present invention the 4th step clamping schematic diagram, and wherein, 6 is outer end clamp plate, and 7 is lightening core.
Detailed description of the invention
Below in conjunction with Figure of description, installation of the present invention and working method are described.
The first step, as shown in Figure 1, part 3 is tapered tubular structure, need all to carry out turn-milling cutting to its surfaces externally and internally, clamping, fixes clamping by positioning fixture and intermediate press plate 2 by part 3, ensures that blank outer surface and inner surface intermediate press plate more than 2 region can process, rough turn region except intermediate press plate 2 and positioning fixture installation site 1, stays 1mm surplus;
Second step, installs four side clamping plate 4, lays down intermediate press plate 2, fix from outside by part 3, as shown in Figure 2, remains unprocessed region in rough turn, finish turning, the finish-milling first step, comprises the sagging hole that 5 is next step finish turning front clamp;
3rd step, part, by screw tightening corresponding screwed hole on positioning fixture, is connected with positioning fixture, lays down four side clamping plate 4, the remaining area of finish turning second step finish turning, the residue position of processing parts 3 except lightening core by the sagging hole processed by second step;
4th step, as shown in Figure 3, installs outer end clamp plate 5 in part 3 outer face, to rough mill, finish-milling 5 place lightening core.
Claims (1)
1. a processing method for Helicopter Dome support member, comprises the following steps,
The first step, preprocessing, part (3) is tapered tubular structure, needs all to carry out turn-milling cutting to its surfaces externally and internally, and before clamping, first at three-axis machining center processing end face, milling location endoporus, bores a dowel hole;
Second step, positioning fixture is arranged on jig installation position (1), by intermediate press plate (2) by fixing for part (3) clamping, ensure that blank outer surface and inner surface intermediate press plate (2) above region can process, rough turn region except intermediate press plate (2) and jig installation position (1), stays 1mm surplus;
3rd step, lay down intermediate press plate (2), four side clamping plate (4) are installed, fix from outside by part (3), remain unprocessed region in rough turn, finish turning, the finish-milling first step, comprise the sagging hole that 5 is next step finish turning front clamp;
4th step, part is connected with positioning fixture with the cooperation of respective screw hole on positioning fixture by the sagging hole processed by second step, lay down side clamping plate (4), the remaining area of finish turning second step finish turning, the residue position of processing parts (3) except lightening core;
5th step, installs outer end clamp plate (5) in part (3) outer face, to rough mill, finish-milling 5 place lightening core.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410213423.1A CN105081681B (en) | 2014-05-20 | 2014-05-20 | A kind of processing method of Helicopter Dome support member |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410213423.1A CN105081681B (en) | 2014-05-20 | 2014-05-20 | A kind of processing method of Helicopter Dome support member |
Publications (2)
| Publication Number | Publication Date |
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| CN105081681A true CN105081681A (en) | 2015-11-25 |
| CN105081681B CN105081681B (en) | 2017-07-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410213423.1A Active CN105081681B (en) | 2014-05-20 | 2014-05-20 | A kind of processing method of Helicopter Dome support member |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105619145A (en) * | 2015-12-28 | 2016-06-01 | 哈尔滨工业大学 | Clamping device and method used for precise machining of outer surface of shape-preserving fairing |
| CN105643303A (en) * | 2016-04-12 | 2016-06-08 | 哈尔滨工业大学 | Clamping device for precisely machining inner surface of conformal optical cowling |
| CN106825614A (en) * | 2017-03-07 | 2017-06-13 | 中航湖南通用航空发动机有限公司 | A kind of aero-compressor hubcap profile surface processing method |
| CN107817568A (en) * | 2017-11-10 | 2018-03-20 | 哈尔滨工业大学 | The clamping device and clamping method of big L/D ratio aspherical optical element concave surface processing |
| CN110281047A (en) * | 2019-05-30 | 2019-09-27 | 武汉船用机械有限责任公司 | The processing tool and processing method of the pod of full-rotating rudder paddle |
| CN113070649A (en) * | 2021-05-17 | 2021-07-06 | 哈尔滨汽轮机厂有限责任公司 | Method for processing air inlet fairing of heavy gas turbine compressor |
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| US20080001036A1 (en) * | 2005-05-20 | 2008-01-03 | The Boeing Company | Aerospace vehicle fairing systems and associated methods |
| CN102161150A (en) * | 2011-05-19 | 2011-08-24 | 宁波市鄞州勇耀缝制机械有限公司 | Manufacturing process of external shuttle of rotating shuttle |
| CN102271998A (en) * | 2008-12-29 | 2011-12-07 | 空客运营有限公司 | Fairing system for an aircraft horizontal stabiliser and method for installing said system |
| CN103302611A (en) * | 2013-05-23 | 2013-09-18 | 亚洲新能源（中国）有限公司 | Fairing locating and supporting tool |
| CN103706809A (en) * | 2013-12-14 | 2014-04-09 | 山西江淮重工有限责任公司 | Machining fixture for large thin-wall conical barrel and machining process thereof |
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2014
- 2014-05-20 CN CN201410213423.1A patent/CN105081681B/en active Active
Patent Citations (5)
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| US20080001036A1 (en) * | 2005-05-20 | 2008-01-03 | The Boeing Company | Aerospace vehicle fairing systems and associated methods |
| CN102271998A (en) * | 2008-12-29 | 2011-12-07 | 空客运营有限公司 | Fairing system for an aircraft horizontal stabiliser and method for installing said system |
| CN102161150A (en) * | 2011-05-19 | 2011-08-24 | 宁波市鄞州勇耀缝制机械有限公司 | Manufacturing process of external shuttle of rotating shuttle |
| CN103302611A (en) * | 2013-05-23 | 2013-09-18 | 亚洲新能源（中国）有限公司 | Fairing locating and supporting tool |
| CN103706809A (en) * | 2013-12-14 | 2014-04-09 | 山西江淮重工有限责任公司 | Machining fixture for large thin-wall conical barrel and machining process thereof |
Non-Patent Citations (1)
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| 杨海涛: "某型涡轮风扇发动机风扇转子整流罩的车加工", 《现代零部件》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105619145A (en) * | 2015-12-28 | 2016-06-01 | 哈尔滨工业大学 | Clamping device and method used for precise machining of outer surface of shape-preserving fairing |
| CN105619145B (en) * | 2015-12-28 | 2017-11-03 | 哈尔滨工业大学 | For the precision machined clamping device in conformal dome outer surface and clamping method |
| CN105643303A (en) * | 2016-04-12 | 2016-06-08 | 哈尔滨工业大学 | Clamping device for precisely machining inner surface of conformal optical cowling |
| CN105643303B (en) * | 2016-04-12 | 2018-02-02 | 哈尔滨工业大学 | One kind is used for the conformal precision machined clamping device of optical rectification cover inner surface |
| CN106825614A (en) * | 2017-03-07 | 2017-06-13 | 中航湖南通用航空发动机有限公司 | A kind of aero-compressor hubcap profile surface processing method |
| CN106825614B (en) * | 2017-03-07 | 2019-04-02 | 中航湖南通用航空发动机有限公司 | A kind of aero-compressor hubcap profile surface processing method |
| CN107817568A (en) * | 2017-11-10 | 2018-03-20 | 哈尔滨工业大学 | The clamping device and clamping method of big L/D ratio aspherical optical element concave surface processing |
| CN110281047A (en) * | 2019-05-30 | 2019-09-27 | 武汉船用机械有限责任公司 | The processing tool and processing method of the pod of full-rotating rudder paddle |
| CN113070649A (en) * | 2021-05-17 | 2021-07-06 | 哈尔滨汽轮机厂有限责任公司 | Method for processing air inlet fairing of heavy gas turbine compressor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105081681B (en) | 2017-07-28 |
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