CN105437537A - Assembling method for airfoil total composite transonic flutter model - Google Patents
Assembling method for airfoil total composite transonic flutter model Download PDFInfo
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- CN105437537A CN105437537A CN201510897501.9A CN201510897501A CN105437537A CN 105437537 A CN105437537 A CN 105437537A CN 201510897501 A CN201510897501 A CN 201510897501A CN 105437537 A CN105437537 A CN 105437537A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
- B29C65/52—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the way of applying the adhesive
- B29C65/54—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the way of applying the adhesive between pre-assembled parts
- B29C65/544—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the way of applying the adhesive between pre-assembled parts by suction
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to an assembling method for an airfoil total composite transonic flutter model. An auxiliary laser structural piece positioning system and a simple limiting block assembly are utilized, accurate positioning assembling of composite components of the total composite model is achieved, the deformation of the model in the hot press forming process is effectively controlled, the manufacturing period is shortened, the product quality is guaranteed, and the manufacturing cost is reduced. By means of a skin metal die overall pressing technology, a skin metal die is utilized, and the surface quality of products in the forming process is effectively guaranteed. The technology problem that in the original model manufacturing process, the surface quality is hard to guarantee in the composite skin hot press tank secondary glue joint forming technology is solved.
Description
Technical field
The invention belongs to flutter model design and manufaction field in technical field of aerospace, relate to the assembly method that a kind of aerofoil answers material transonic flutter model entirely.
Background technology
The buffet characteristic of aircraft components and full machine depends on its factor such as geometric shape and natural vibration characteristic.Will in wind tunnel test the buffet characteristic of accurate simulation, research aircraft parts and even full machine, first must design and produce can the test model of its natural vibration characteristic of accurate simulation.
Transonic flutter model in wind tunnel has that stand under load is large, frequency is high and intensity high and difficult point compared to low-speed flutter test model, therefore in order to reduce the overweight ratio of model, and even design, produce not overweight test model, with the requirement making it meet each similar proportion chi completely, transonic flutter test model need adopt the high composite of specific strength, specific stiffness to design, and manufactures in conjunction with a series of new technology and new technology.
The multiple material component manufacture of current aircraft, assembling all need design, produce a large amount of high-quality moulds, cost is high, the cycle is long, for this kind of single-piece of flutter test model or several products, it is no longer applicable that conventional multiple material component manufactures mounting technology, a large amount of wastes of resource can be caused, new manufacture, mounting technology need be sought.In addition, at the multiple material covering Bonding Process of existing flutter test model, be that test model and covering are inserted in vacuum bag, by vacuumizing, covering is exerted pressure, finally complete splicing, this mode may cause the slippage in covering Bonding Process, and model surface such as to subside at the quality problems.
The present invention utilizes laser assisted structural member navigation system and simple and easy limited block component, achieve the accurate orientation assemble of each multiple material component of full material model again, effectively control the deflection of model in hot-forming process, shorten the manufacturing cycle, ensure that product quality, reduce manufacturing cost; Covering metal die entirety exerts pressure technology by utilizing covering metal die, effectively ensure that the surface quality in formed product process, to solve in mould manufacturing process in the past surface quality in multiple material covering autoclave second bonding moulding process and be comparatively difficult to ensure the technological difficulties of card.
Summary of the invention
The object of the invention is:
In order to solve in the past entirely again material transonic flutter model precision in assembling and Bonding Process be difficult to ensure, cost is higher, and surface quality is difficult to the problems such as guarantee, proposes the assembly method that a kind of aerofoil answers material transonic flutter model entirely.
Technical scheme of the present invention is:
Aerofoil answers an assembly method for material transonic flutter model entirely, comprises the steps:
The first step, the each component of model carries out pre-assembled by after the independent curing molding of designing requirement, utilize laser assisted navigation system (1) to carry out component projection on the metal skin mould (2) with one-sided multiple material covering (8), complete the accurate location to each component rigging position;
Second step, after having located, glued membrane is laid at multiple material component assembly surface to be assembled, recycling aluminium alloy or multiple material connect gusset plate and are fixed by each component link position, position location must be contrasted in whole pre-assembled process, formation model skeleton (4) after each component pre-connection completes, each geometrical boundary of aerofoil utilizes metal spacing block (5,6,7) carry out spacing to model skeleton (4), to prevent under hot pressing environment component generation integral slipping in glued membrane solidification process;
3rd step, by opposite side with multiple material covering covering metal die (3) with carry out involutory for preassembled side covering die (2), vacuum bag (9) is utilized to load at mould involutory limit place, pre glued joint is carried out to model skeleton (4) and covering (8), checks assembly quality;
4th step, after checking out assembly quality, carry out formal solidification by cement, because covering die and model skeleton (4) external surface are fitted completely, in solidification by cement process, mould carries out entirety exert pressure to model skeleton (4) the bearing beam frame system of contact and covering (8), completes and glueds joint and final assembling process.
The advantage that this method has and beneficial effect:
The present invention mainly has the following advantages:
Present invention achieves accurate location during the full assembling of each component of material flutter model again, effectively control the deflection of model in hot-forming process, ensure that the design performance of model; The simple and direct practicality of this design invention technical method, owing to making full use of resource, only needs design, manufactures upper and lower covering die, shorten the manufacturing cycle, significantly reduce manufacturing cost.By ground resonance test and wind tunnel test, demonstrate and utilize the assembling of this assembly system, shaping full material model dynamics again simulation accurately, there is higher model practical value.。
Accompanying drawing explanation
Fig. 1 is the schematic diagram of parts of the present invention, and wherein, 1 is laser assisted navigation system, and 2,3 is metal skin moulds, and 4 is model skeletons, and 5,6,7 is metal spacing blocks, and 8 is coverings.
Fig. 2 is the inventive method pre-assembled model skeleton schematic diagram.
Fig. 3 is that the inventive method glueds joint schematic diagram, and wherein, 9 is vacuum bags.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is elaborated.
The first step, the each component of model carries out pre-assembled by after the independent curing molding of designing requirement, utilize laser assisted navigation system (1) to carry out component projection on the metal skin mould (2) with one-sided multiple material covering (8), complete the accurate location to each component rigging position;
Second step, as shown in Figure 2, after having located, glued membrane is laid at multiple material component assembly surface to be assembled, recycling aluminium alloy or multiple material connect gusset plate and are fixed by each component link position, position location must be contrasted in whole pre-assembled process, formation model skeleton (4) after each component pre-connection completes, each geometrical boundary of aerofoil utilizes metal spacing block (5,6,7) carry out spacing to model skeleton (4), to prevent under hot pressing environment component generation integral slipping in glued membrane solidification process;
3rd step, as shown in Figure 3, by opposite side with multiple material covering covering metal die (3) with carry out involutory for preassembled side covering die (2), vacuum bag (9) is utilized to load at mould involutory limit place, pre glued joint is carried out to model skeleton (4) and covering (8), checks assembly quality;
4th step, after checking out assembly quality, carry out formal solidification by cement, because covering die and model skeleton (4) external surface are fitted completely, in solidification by cement process, mould carries out entirety exert pressure to model skeleton (4) the bearing beam frame system of contact and covering (8), completes and glueds joint and final assembling process.
Claims (1)
1. aerofoil answers an assembly method for material transonic flutter model entirely, comprises the steps:
The first step, the each component of model carries out pre-assembled by after the independent curing molding of designing requirement, utilize laser assisted navigation system (1) to carry out component projection on the metal skin mould (2) with one-sided multiple material covering (8), complete the accurate location to each component rigging position;
Second step, after having located, glued membrane is laid at multiple material component assembly surface to be assembled, recycling aluminium alloy or multiple material connect gusset plate and are fixed by each component link position, position location must be contrasted in whole pre-assembled process, formation model skeleton (4) after each component pre-connection completes, each geometrical boundary of aerofoil utilizes metal spacing block (5,6,7) carry out spacing to model skeleton (4), to prevent under hot pressing environment component generation integral slipping in glued membrane solidification process;
3rd step, by opposite side with multiple material covering covering metal die (3) with carry out involutory for preassembled side covering die (2), vacuum bag (9) is utilized to load at mould involutory limit place, pre glued joint is carried out to model skeleton (4) and covering (8), checks assembly quality;
4th step, after checking out assembly quality, carry out formal solidification by cement, because covering die and model skeleton (4) external surface are fitted completely, in solidification by cement process, mould carries out entirety exert pressure to model skeleton (4) the bearing beam frame system of contact and covering (8), completes and glueds joint and final assembling process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510897501.9A CN105437537A (en) | 2015-12-08 | 2015-12-08 | Assembling method for airfoil total composite transonic flutter model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510897501.9A CN105437537A (en) | 2015-12-08 | 2015-12-08 | Assembling method for airfoil total composite transonic flutter model |
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| CN105437537A true CN105437537A (en) | 2016-03-30 |
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| CN201510897501.9A Pending CN105437537A (en) | 2015-12-08 | 2015-12-08 | Assembling method for airfoil total composite transonic flutter model |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107160717A (en) * | 2017-06-22 | 2017-09-15 | 中国航空工业集团公司基础技术研究院 | A kind of preparation method of composite material skin structure mechanical processing technique line |
| CN107283137A (en) * | 2016-04-12 | 2017-10-24 | 哈尔滨飞机工业集团有限责任公司 | A kind of moulding technique of structural adhesive bonding part |
| CN107297910A (en) * | 2017-06-22 | 2017-10-27 | 中国航空工业集团公司基础技术研究院 | The method that composite material skin structure mechanical processing technique line is prepared using technique cover plate |
| CN109605019A (en) * | 2018-11-30 | 2019-04-12 | 上海航天精密机械研究所 | Carrier rocket empennage glue riveting assembly technique |
| CN110091519A (en) * | 2018-01-29 | 2019-08-06 | 李璐璐 | A kind of splicing mold |
| CN110159623A (en) * | 2018-02-15 | 2019-08-23 | 卡本卡车拖车有限责任公司 | Load guide device and the method for bonding load guide device |
| CN116878340A (en) * | 2023-09-07 | 2023-10-13 | 北京爱思达航天科技有限公司 | Large-bearing light composite material flying wing and preparation method thereof |
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| CN102114706A (en) * | 2010-12-29 | 2011-07-06 | 江西昌河航空工业有限公司 | Method for forming frame, stringer and covering of composite material component through integrated co-curing |
| CN102909866A (en) * | 2012-10-24 | 2013-02-06 | 中国航空工业集团公司北京航空材料研究院 | Method for forming control of long joist axial line of composite material stiffened wall panel |
| CN103342167A (en) * | 2013-05-18 | 2013-10-09 | 大连理工大学 | Method for making scaled composite material wing model |
| EP2728172A1 (en) * | 2012-11-01 | 2014-05-07 | General Electric Company | Rotor blade mold assembly and method for forming rotor blade |
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2015
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Patent Citations (4)
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| CN102114706A (en) * | 2010-12-29 | 2011-07-06 | 江西昌河航空工业有限公司 | Method for forming frame, stringer and covering of composite material component through integrated co-curing |
| CN102909866A (en) * | 2012-10-24 | 2013-02-06 | 中国航空工业集团公司北京航空材料研究院 | Method for forming control of long joist axial line of composite material stiffened wall panel |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107283137A (en) * | 2016-04-12 | 2017-10-24 | 哈尔滨飞机工业集团有限责任公司 | A kind of moulding technique of structural adhesive bonding part |
| CN107160717A (en) * | 2017-06-22 | 2017-09-15 | 中国航空工业集团公司基础技术研究院 | A kind of preparation method of composite material skin structure mechanical processing technique line |
| CN107297910A (en) * | 2017-06-22 | 2017-10-27 | 中国航空工业集团公司基础技术研究院 | The method that composite material skin structure mechanical processing technique line is prepared using technique cover plate |
| CN107160717B (en) * | 2017-06-22 | 2019-03-19 | 中国航空工业集团公司基础技术研究院 | A kind of preparation method of composite material skin structure mechanical processing technique line |
| CN107297910B (en) * | 2017-06-22 | 2019-03-19 | 中国航空工业集团公司基础技术研究院 | Utilize the method for technique cover board preparation composite material skin structure mechanical processing technique line |
| CN110091519A (en) * | 2018-01-29 | 2019-08-06 | 李璐璐 | A kind of splicing mold |
| CN110091519B (en) * | 2018-01-29 | 2024-05-07 | 李璐璐 | Cementing mold |
| CN110159623A (en) * | 2018-02-15 | 2019-08-23 | 卡本卡车拖车有限责任公司 | Load guide device and the method for bonding load guide device |
| CN109605019A (en) * | 2018-11-30 | 2019-04-12 | 上海航天精密机械研究所 | Carrier rocket empennage glue riveting assembly technique |
| CN116878340A (en) * | 2023-09-07 | 2023-10-13 | 北京爱思达航天科技有限公司 | Large-bearing light composite material flying wing and preparation method thereof |
| CN116878340B (en) * | 2023-09-07 | 2023-12-29 | 北京爱思达航天科技有限公司 | Large-bearing light composite material flying wing and preparation method thereof |
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