CN102248383A - Process for machining connecting structure in integral thin-wall closed cavity - Google Patents
Process for machining connecting structure in integral thin-wall closed cavity Download PDFInfo
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- CN102248383A CN102248383A CN2011102033133A CN201110203313A CN102248383A CN 102248383 A CN102248383 A CN 102248383A CN 2011102033133 A CN2011102033133 A CN 2011102033133A CN 201110203313 A CN201110203313 A CN 201110203313A CN 102248383 A CN102248383 A CN 102248383A
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Abstract
The invention relates to a process for machining a connecting structure in an integral thin-wall closed cavity. The process comprises the following steps of: 1) machining a joint; 2) preparing in the earlier stage; 3) performing superplastic forming; 4) performing diffused connection; and 5) removing allowance. By the process, a cutting process is saved, the pollution generated in the cutting process is avoided, a repair process is saved, the labor intensity is reduced greatly, and the work efficiency is improved greatly while the integral constructing quality is improved.
Description
Technical field
The present invention relates to a kind of processing technology of thin-walled integrally closed die cavity interconnect structure, this technology is applicable to that thin-walled integral structure component and machine add the syndeton of part.
Background technology
In the Aerospace Products, adopt the thin-walled integrated structure of lightweight, high-strength material in a large number, when satisfying higher intensity, rigidity requirement, lighter quality is arranged also, superplastic forming/diffusion syndeton is exactly typical case's representative.When this kind structure member and other parts especially machine add parts and are connected, traditional process is to adopt superplastic forming/diffusion connecting process shaping near closed hollow ring part, then part is cut, die cavity is exposed, machine is added structure put into die cavity, adopt modes such as welding, bolt to link together.There is following shortcoming in this process: 1. complex technical process, and near closed hollow ring structure cuts difficulty needs cutting tool or clamping tooling, and kerf quality is poor, and otch finishing process amount is big; 2. die cavity inside is subject to pollutions such as cutting fluid, cutting when cutting, and needs follow-up cleaning; 3. cavity structure and street corner repair difficulty, the repair workload is big, and fit quality is bad; 4. the center of gravity of every product differs bigger, is difficult to guarantee designing requirement.
Summary of the invention
The technical problem to be solved in the present invention provides a kind of processing technology of thin-walled integrally closed die cavity interconnect structure, this technology has not only reduced cutting action, avoided the pollution in the cutting process, and removed the repair operation, greatly reduce labour intensity, when the unitary construction quality improved, operating efficiency also improved greatly.
For overcoming the above problems, concrete technical scheme of the present invention is as follows: a kind of processing technology of thin-walled integrally closed die cavity interconnect structure may further comprise the steps:
1) joint processing:, joint is divided into two according to joint design and process characteristic;
2) early-stage preparations:
2.1) plate cutting: need four sheet materials altogether, and press the blanking of figure paper size, monolateral high-volume 50 ± 0.25mm is as margin of operation;
2.2) the location line: for guaranteeing accurate positioning between which floor model material, on plate, reserve locator tabs, rule on plate according to model and indicate non-diffusion zone;
2.3) mill air channel: the gas circuit position on plate, milling pore groove, width are 3～4mm, the degree of depth is 40%～50% of a sheet thickness, the deburring of polishing after the milling;
2.4) pickling: the processing plate is placed in the descaling bath, and the surface acid-washing oil removing is to guarantee panel surface cleaning, free from admixture and oxide skin;
2.5) separant coating: the non-diffusion zone that marks on plate applies interleaving agent, and applies interleaving agent at pore groove and gas channels place;
2.6) the vent line preparation: the length of design vent line can be placed on platform central authorities with part and be advisable;
2.7) adopt the argon arc welding manner to weld around the plate and pipeline, after finishing, welding checks the air-tightness of pipeline and cavity;
3) superplastic forming:
3.1) the dress mould: cleaning die surface, and, be convenient to molding at the outer surface and the die surface separant coating of blank, mould is put furnace chamber middle position with superplastic forming equipment, underlay insulation asbestic blanket is put into mould with outer plate, accurate positioning on the mould;
3.2) heat up: be warming up to and be shaped temperature requiredly, in the process that heats up, fill the protective gas argon gas and protect;
3.3) be shaped:
3.3.1) feed inert gas at the lamina rara externa materials and parts, outer plate and mould are fitted;
3.3.2) the cooling molding: below 500 ℃ part is taken out;
4) diffusion connects:
4.1) two joints and the internal layer plate that will process, outer plate is located mutually, and tab order is followed successively by from top to bottom: lamina rara externa upper strata, joint, two of inner platings, joint and lamina rara externa lower floor, utilize resistance spot welding with plate and joint welding location;
4.2) each laminate material spreads with joint and be connected, and between final every laminate material, joint diffusion effect takes place all, closely is connected to form integral body mutually, obtains the integrally closed cavity structure that inside has reinforcement;
5) remove surplus: modes such as the employing machine adds, laser cutting are removed process allowance, obtain final design of part.
The processing technology of this thin-walled integrally closed die cavity interconnect structure adopts said method, can directly directly place it in by the method for superplastic forming working joint, save a large amount of operations that produce because of the placement joint, thereby under the prerequisite of ensuring the quality of products, improved production efficiency.
Description of drawings
Fig. 1 is the design of part schematic diagram among the embodiment.
Fig. 2 is the structural representation in mould before the inherent superplastic forming of thin-walled integrally closed die cavity.
Fig. 3 is the structural representation of outer superplastic forming.
Fig. 4 is the structural representation of internal layer superplastic forming.
Wherein, 1, machine adds joint; 2, thin-walled cavity structure; 3, mould; 4, lamina rara externa upper strata; 5, inner plating upper strata; 6, inner plating upper strata; 7, inner plating lower floor.
The specific embodiment
As shown in Figure 1, certain guided missile rudder and body syndeton, rudder is the whole superplastic forming syndeton of near closed hollow ring, and adds joint by machine and be connected with the body skeleton.May further comprise the steps:
1) joint processing:, joint is divided into two according to joint design and process characteristic;
2) early-stage preparations:
2.1) plate cutting: as shown in Figure 2, need four sheet materials altogether, and press the blanking of figure paper size, monolateral high-volume 50 ± 0.25mm is as margin of operation;
2.2) the location line: for guaranteeing accurate positioning between which floor model material, on plate, reserve locator tabs, rule on plate according to model and indicate non-diffusion zone;
2.3) mill air channel: the gas circuit position on plate, milling pore groove, width are 3～4mm, the degree of depth is 40%～50% of a sheet thickness, the deburring of polishing after the milling;
2.4) pickling: the processing plate is placed in the descaling bath, and the surface acid-washing oil removing is to guarantee panel surface cleaning, free from admixture and oxide skin;
2.5) separant coating: the non-diffusion zone that marks on plate applies interleaving agent, and applies interleaving agent at pore groove and gas channels place;
2.6) the vent line preparation: the length of design vent line can be placed on platform central authorities with part and be advisable;
2.7) adopt the argon arc welding manner to weld around the plate and pipeline, after finishing, welding checks the air-tightness of pipeline and cavity;
3) superplastic forming:
3.1) the dress mould: cleaning die surface, and, be convenient to molding at the outer surface and the die surface separant coating of blank, mould is put furnace chamber middle position with superplastic forming equipment, underlay insulation asbestic blanket is put into mould with outer plate, accurate positioning on the mould;
3.2) heat up: be warming up to and be shaped temperature requiredly, in the process that heats up, fill the protective gas argon gas and protect;
3.3) be shaped:
3.3.1) feed inert gas at the lamina rara externa materials and parts, outer plate and mould are fitted;
3.3.2) the cooling molding: below 500 ℃ part is taken out;
4) diffusion connects:
4.1) as shown in Figure 3, with two joints and the internal layer plate that processes, outer plate is located mutually, and tab order is followed successively by from top to bottom: lamina rara externa upper strata, joint, two of inner platings, joint and lamina rara externa lower floor, utilize resistance spot welding with plate and joint welding location;
4.2) each laminate material spreads with joint and be connected, and between final every laminate material, joint diffusion effect takes place all, closely is connected to form integral body mutually, obtains the integrally closed cavity structure that inside has reinforcement, as shown in Figure 4;
5) remove surplus: modes such as the employing machine adds, laser cutting are removed process allowance, obtain final design of part.
Claims (1)
1. the processing technology of a thin-walled integrally closed die cavity interconnect structure is characterized in that may further comprise the steps:
1) joint processing:, joint is divided into two according to joint design and process characteristic;
2) early-stage preparations:
2.1) plate cutting: need four sheet materials altogether, and press the blanking of figure paper size, monolateral high-volume 50 ± 0.25mm is as margin of operation;
2.2) the location line: for guaranteeing accurate positioning between which floor model material, on plate, reserve locator tabs, rule on plate according to model and indicate non-diffusion zone;
2.3) mill air channel: the gas circuit position on plate, milling pore groove, width are 3～4mm, the degree of depth is 40%～50% of a sheet thickness, the deburring of polishing after the milling;
2.4) pickling: the processing plate is placed in the descaling bath, and the surface acid-washing oil removing is to guarantee panel surface cleaning, free from admixture and oxide skin;
2.5) separant coating: the non-diffusion zone that marks on plate applies interleaving agent, and applies interleaving agent at pore groove and gas channels place;
2.6) the vent line preparation: the length of design vent line can be placed on platform central authorities with part and be advisable;
2.7) adopt the argon arc welding manner to weld around the plate and pipeline, after finishing, welding checks the air-tightness of pipeline and cavity;
3) superplastic forming:
3.1) the dress mould: cleaning die surface, and, be convenient to molding at the outer surface and the die surface separant coating of blank, mould is put furnace chamber middle position with superplastic forming equipment, underlay insulation asbestic blanket is put into mould with outer plate, accurate positioning on the mould;
3.2) heat up: be warming up to and be shaped temperature requiredly, in the process that heats up, fill the protective gas argon gas and protect;
3.3) be shaped:
3.3.1) feed inert gas at the lamina rara externa materials and parts, outer plate and mould are fitted;
3.3.2) the cooling molding: below 500 ℃ part is taken out;
4) diffusion connects:
4.1) two joints and the internal layer plate that will process, outer plate is located mutually, and tab order is followed successively by from top to bottom: lamina rara externa upper strata, joint, two of inner platings, joint and lamina rara externa lower floor, utilize resistance spot welding with plate and joint welding location;
4.2) each laminate material spreads with joint and be connected, and between final every laminate material, joint diffusion effect takes place all, closely is connected to form integral body mutually, obtains the integrally closed cavity structure that inside has reinforcement;
5) remove surplus: modes such as the employing machine adds, laser cutting are removed process allowance, obtain final design of part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN 201110203313 CN102248383B (en) | 2011-07-20 | 2011-07-20 | Process for machining connecting structure in integral thin-wall closed cavity |
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| CN 201110203313 CN102248383B (en) | 2011-07-20 | 2011-07-20 | Process for machining connecting structure in integral thin-wall closed cavity |
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| CN102248383B CN102248383B (en) | 2013-04-10 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103008998A (en) * | 2012-12-14 | 2013-04-03 | 中国航空工业集团公司北京航空制造工程研究所 | Superplastic forming (SPF)/diffusion bonding (DB) forming method of titanium alloy cylindrical three-layer structure |
| CN103424091A (en) * | 2013-07-10 | 2013-12-04 | 温州华聚科技有限公司 | Ultra-thin pneumatic measuring head and processing method thereof |
| CN104259774A (en) * | 2014-09-09 | 2015-01-07 | 黄河科技学院 | Plane wing titanium alloy thin-wall web efficient numerical control machining technology |
| CN106181226A (en) * | 2015-04-29 | 2016-12-07 | 哈尔滨建成集团有限公司 | A kind of aspect is than the processing method of thin plate porous part |
| CN106363375A (en) * | 2016-08-26 | 2017-02-01 | 北京普惠三航科技有限公司 | Method for manufacturing grid rudder |
| CN108161205A (en) * | 2017-12-06 | 2018-06-15 | 北京星航机电装备有限公司 | A kind of wing rudder class part electron beam welding SPF Technology |
| CN109158842A (en) * | 2018-10-31 | 2019-01-08 | 北京普惠三航科技有限公司 | The processing technology of aerofoil is reinforced in a kind of titanium alloy lightweight |
| CN109175917A (en) * | 2018-10-31 | 2019-01-11 | 北京普惠三航科技有限公司 | The manufacturing method of aerofoil is reinforced in a kind of titanium alloy lightweight |
| CN109955041A (en) * | 2019-03-28 | 2019-07-02 | 中国航空制造技术研究院 | Titanium alloy hollow structure without molding Preparation Method |
| CN112643101A (en) * | 2020-12-11 | 2021-04-13 | 上海无线电设备研究所 | Processing method of weak-rigidity thin-wall hollow structural part |
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| EP1108922A2 (en) * | 1999-12-18 | 2001-06-20 | Bayerische Motoren Werke Aktiengesellschaft | Method of and apparatus for controlling a continuously variable automatic transmission |
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| CN101704178A (en) * | 2009-10-29 | 2010-05-12 | 西北锆管有限责任公司 | Method for processing thin-walled tube of zirconium alloy specially used by nuclear reactor |
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2011
- 2011-07-20 CN CN 201110203313 patent/CN102248383B/en not_active Expired - Fee Related
Patent Citations (3)
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| EP1108922A2 (en) * | 1999-12-18 | 2001-06-20 | Bayerische Motoren Werke Aktiengesellschaft | Method of and apparatus for controlling a continuously variable automatic transmission |
| CN101579804A (en) * | 2009-06-04 | 2009-11-18 | 航天材料及工艺研究所 | Integral forming method of large size thin-walled titanium alloy cylindrical part without welding line |
| CN101704178A (en) * | 2009-10-29 | 2010-05-12 | 西北锆管有限责任公司 | Method for processing thin-walled tube of zirconium alloy specially used by nuclear reactor |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103008998A (en) * | 2012-12-14 | 2013-04-03 | 中国航空工业集团公司北京航空制造工程研究所 | Superplastic forming (SPF)/diffusion bonding (DB) forming method of titanium alloy cylindrical three-layer structure |
| CN103008998B (en) * | 2012-12-14 | 2015-05-27 | 中国航空工业集团公司北京航空制造工程研究所 | Superplastic forming (SPF)/diffusion bonding (DB) forming method of titanium alloy cylindrical three-layer structure |
| CN103424091A (en) * | 2013-07-10 | 2013-12-04 | 温州华聚科技有限公司 | Ultra-thin pneumatic measuring head and processing method thereof |
| CN104259774A (en) * | 2014-09-09 | 2015-01-07 | 黄河科技学院 | Plane wing titanium alloy thin-wall web efficient numerical control machining technology |
| CN106181226A (en) * | 2015-04-29 | 2016-12-07 | 哈尔滨建成集团有限公司 | A kind of aspect is than the processing method of thin plate porous part |
| CN106363375A (en) * | 2016-08-26 | 2017-02-01 | 北京普惠三航科技有限公司 | Method for manufacturing grid rudder |
| CN108161205A (en) * | 2017-12-06 | 2018-06-15 | 北京星航机电装备有限公司 | A kind of wing rudder class part electron beam welding SPF Technology |
| CN108161205B (en) * | 2017-12-06 | 2020-05-26 | 北京星航机电装备有限公司 | Electron beam welding superplastic forming process for wing rudder parts |
| CN109158842A (en) * | 2018-10-31 | 2019-01-08 | 北京普惠三航科技有限公司 | The processing technology of aerofoil is reinforced in a kind of titanium alloy lightweight |
| CN109175917A (en) * | 2018-10-31 | 2019-01-11 | 北京普惠三航科技有限公司 | The manufacturing method of aerofoil is reinforced in a kind of titanium alloy lightweight |
| CN109955041A (en) * | 2019-03-28 | 2019-07-02 | 中国航空制造技术研究院 | Titanium alloy hollow structure without molding Preparation Method |
| CN112643101A (en) * | 2020-12-11 | 2021-04-13 | 上海无线电设备研究所 | Processing method of weak-rigidity thin-wall hollow structural part |
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| CN102248383B (en) | 2013-04-10 |
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