CN105332982B - A kind of aircraft metal resistant cementing structure product weight losing method - Google Patents
A kind of aircraft metal resistant cementing structure product weight losing method Download PDFInfo
- Publication number
- CN105332982B CN105332982B CN201510845528.3A CN201510845528A CN105332982B CN 105332982 B CN105332982 B CN 105332982B CN 201510845528 A CN201510845528 A CN 201510845528A CN 105332982 B CN105332982 B CN 105332982B
- Authority
- CN
- China
- Prior art keywords
- weight
- glue
- structure product
- cementing structure
- metal resistant
- 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
Landscapes
- Adhesives Or Adhesive Processes (AREA)
Abstract
A kind of aircraft metal resistant cementing structure product weight losing method, belongs to weight research direction in preliminary design of aircraft field, for the Weight control of aircraft metal resistant cementing structure product, including：S1, chooses overweight metal resistant cementing structure product；S2, analyzes the weightening process of metal resistant cementing structure product described in S1；S3, chooses from the weightening process selected by S2 and is glued process as loss of weight process；S4, Theoretical Design control glue consumption, draw the weight range of glue consumption；S5, designs durable cementing structure product technique glue consumption loss of weight experiment.Aircraft metal resistant cementing structure product weight losing method provided by the invention realizes the purpose of aircraft metal bonding product loss of weight, so as to reduce the overall weight in the stage of design and producing of aircraft.
Description
Technical field
It is resistance in particular to a kind of aircraft metal the invention belongs to weight research direction in preliminary design of aircraft field
Long cementing structure product weight losing method.
Background technology
Metal bonding is exactly using adhesive and by the adhesion between viscous metal surface, and metal adherend is connected to become one
A entirety, and the method with certain mechanical property.In the past 30 years, all advanced aircrafts none do not employ cementing structure,
Metal bonding structure is as one of important feature form of airframe.It is now durable with the continuous development of technology, progress
Cementing structure is applied on the main force support structure of aircraft.It may be said that it is glued connection with mechanically connecting (rivet, be spirally connected)
Three big interconnection techniques of modern aircraft manufacture are listed as with welding.
In the development process for new model of marching toward, aircraft industry proposes the requirement precisely manufactured, and part weight
Technology stability is the direct examination key element for weighing the accuracy of manufacture, and is struggled always aircraft development to mitigate each gram weight
Forever continuous target, certain aircraft in development process because aircraft weight beyond design objective, it is necessary to carry out loss of weight work
Make, after analyzing overweight product, it is found that the weight fluctuation amplitude of metal bonding product is larger, overweight condition is serious, especially
On the premise of metallic article is not overweight, the part weight after splicing is the immediate cause for causing product overweight for it, it is therefore necessary to
Carry out loss of weight design studies.
The problem of present urgent need to resolve is how to design a kind of aircraft metal resistant cementing structure product weight losing method, with solution
Certainly in the prior art the defects of
The content of the invention
It is an object of the invention to solve above-mentioned deficiency of the prior art, there is provided a kind of aircraft metal of advantages of simple is resistance to
Long cementing structure product weight losing method.
The purpose of the present invention is achieved through the following technical solutions：A kind of aircraft metal resistant cementing structure product loss of weight side
Method, the Weight control for aircraft metal resistant cementing structure product, it is characterised in that include the following steps：
S1, chooses overweight metal resistant cementing structure product；
S2, analyzes the weightening process of metal resistant cementing structure product described in S1；
S3, chooses from the weightening process selected by S2 and is glued process as loss of weight process；
S4, Theoretical Design control glue consumption, draw the weight range of glue consumption；
S5, designs durable cementing structure product technique glue consumption loss of weight experiment, including：
S5-1, designs three groups of identical structural members, and weighs to structural member；
S5-2, glue spraying operation is carried out to structural member in S5-1, wherein, one group is the disposable glue spraying of whole face, and one group is whole face
Disposable glue spraying and carrying out inhales glue operation, and one group for the gradual glue spraying of branch point and carries out suction glue according to glue spraying order, and to glue spraying
Structural member after operation is weighed；
S5-3, structural member are glued fitting；
S5-4, is further handled structural member；
S5-5, weighs and draws experimental data；
The durable cementing structure part weight scope of control is drawn by S1-S5.
In such scheme preferably, it is resistance to for holding aircraft metal that the foundation for being glued process as loss of weight process is chosen in S3
The intensity of long cementing structure product.
In any of the above-described scheme preferably, the foundation of Theoretical Design control glue consumption includes glue-joint strength in S4.
In any of the above-described scheme preferably, durable cementing structure product technique glue consumption loss of weight experiment is to having a competition in S5
Test.
In any of the above-described scheme preferably, the suction glue operation used tool is suction gummed paper.
The beneficial effect of aircraft metal resistant cementing structure product weight losing method provided by the present invention is, realizes winged
The purpose of machine metal bonding product loss of weight.This technology is implemented in related model, it was demonstrated that is reasonable.The technology can be with
Promoted the use of in Aeronautics and Astronautics field, while also establish solid foundation for follow-up relation technological researching, there are wide military affairs
Using with civil aircraft application prospect.
Brief description of the drawings
Fig. 1 is the flow of a preferred embodiment of aircraft metal resistant cementing structure product weight losing method according to the invention
Schematic diagram；
Fig. 2 is the knot of the embodiment illustrated in fig. 1 of aircraft metal resistant cementing structure product weight losing method according to the invention
The schematic diagram of component cementation interface layer.
Reference numeral：
1- adherends, 2- anodization layers, 3- primer layers, 4- glued membranes.
Embodiment
In order to better understand according to the aircraft metal resistant cementing structure product weight losing method of the present invention program, tie below
Attached drawing is closed to be further elaborated a preferred embodiment of the aircraft metal resistant cementing structure product weight losing method of the present invention
It is bright.
As Figure 1-Figure 2, aircraft metal resistant cementing structure product weight losing method provided by the invention, for aircraft gold
Belong to the Weight control of durable cementing structure product, include the following steps：
S1, chooses overweight metal resistant cementing structure product；
S2, analyzes the weightening process of metal resistant cementing structure product described in S1；
S3, chooses from the weightening process selected by S2 and is glued process as loss of weight process；
S4, Theoretical Design control glue consumption, draw the weight range of glue consumption；
S5, designs durable cementing structure product technique glue consumption loss of weight experiment；
The durable cementing structure part weight scope of control is drawn by S1-S5.
In the process step for the aircraft metal resistant cementing structure product weight losing method that the invention described above provides, chosen in S3
It is to keep the intensity of aircraft metal resistant cementing structure product to be glued process as the foundation of loss of weight process；Theoretical Design control in S4
The foundation of glue consumption processed includes glue-joint strength；Durable cementing structure product technique glue consumption loss of weight experiment is contrast test in S5.
Durable cementing structure product technique glue consumption loss of weight experiment includes the following steps in S5：S5-1, three groups of design are identical
Structural member, and weigh to structural member；S5-2, in S5-1 structural member carry out glue spraying operation, and to glue spraying operate after
Structural member is weighed；S5-3, structural member are glued fitting；S5-4, is further handled structural member；S5-5, weighs and draws experiment
Data.
The glue spraying that three groups of structural members carry out is operated in S5-2 and is respectively：One group is the disposable glue spraying of whole face；One group is whole
The disposable glue spraying in face and carry out inhale glue operation；One group is divided gradual glue spraying for branch and carries out suction glue according to glue spraying order.Wherein, on
Involved suction glue operation used tool is suction gummed paper in stating.
Among above-mentioned steps, inhale glue material and be used in pre-suction glue or curing process, can quantify and suction out Excess resin in blank,
And there is certain air permeability energy.Inhale glue material and have and inhale rubber mat, glass cloth etc., inhale glue material unit area resin absorption with material and
It is different.Common rubber mat of inhaling inhales material trademark：AIRWEAVE.S；Individual layer inhales glue weight：150~200 (g/m2)。
During specific use, aircraft metal resistant cementing structure product weight losing method provided by the invention is applied
In the design production process of the metal bonding product of aircraft.
First, the weight configuration personnel in Conceptual Aircraft Design Process propose according to the overall weight loss of weight demand of aircraft
The weight of glue consumption needed for metal bonding product is ± the 2.5% of part weight.Metal bonding product on above-mentioned aircraft
Totally 8, all overweight, maximum overweight amplitude reaches 12%, and minimum overweight amplitude reaches 4%.
Secondly, it is designed analysis to being glued product splicing interface.Be glued product by adhesive and adherend surface by
Adhesive attraction is formed.A complicated boundary layer is formed between adherend surface and adhesive, is illustrated in figure 2 splicing boundary layer
Schematic diagram.Boundary layer is by adherend 1 and its superficial layer (such as anodization layer 2), adsorption layer (such as empty gas and water, impurity), close quilt
The primer layer 3 and glued membrane 4 of the anodization layer 2 of viscous thing 1 form.
Again, it is glued design and combines wetting qualities requirement.Adhesive to the good moistening on adherend surface be to be formed it is excellent
The necessary condition of product.Adhesive is when the expansion of adherend surface wettability reaches balance：
γ S=γ SL+ γ L cos θ (1-1)
In formula：γ S --- adherend surface energy；
γ L --- liquid adhesive surface tension；
γ SL --- interfacial tension between adherend and liquid adhesive；
θ --- contact angle.
Found out by formula (1-1), to obtain good interface, it is necessary to reach it is following some：
A) 4/ primer layer of glued membrane, 3/ anodization layer will reach good compatibility；
B) contact angle θ≤0；
C) adherend 1 should have high surface energy.High surface energy helps to reduce the contact between glued membrane 4 and adherend 1
Angle, improves wet performance of the adhesive to adherend 1.
Increase pre-suction glue process.On the premise of meeting that being glued product is glued the design wetting qualities requirement at interface, carry out
Loss of weight technological work, increases pre-suction glue process after glued membrane is applied, and the splicing design for proving to meet product by test of many times will
Ask, and significantly reduce the weight of product.
Aircraft metal bonding product weight loss effect is analyzed
The present invention proposes aircraft metal resistant cementing structure product weight losing method, and specifically describes metal bonding product
Loss of weight technological process, aircraft metal-to-metal adhesive is realized using aircraft metal resistant cementing structure product weight losing method proposed by the present invention
Connect the purpose of product loss of weight.This technology is implemented in the design production process of the metal bonding product of above-mentioned aircraft, and
Learn that aircraft metal resistant cementing structure product weight losing method provided by the invention is reasonable according to final data.This hair
The aircraft metal resistant cementing structure product weight losing method of bright offer can be promoted the use of in Aeronautics and Astronautics field, while after being also
Continuous relation technological researching establishes solid foundation, has wide Military Application and civil aircraft application prospect.
Do above in association with aircraft metal resistant cementing structure product weight losing method specific embodiment of the invention and retouched in detail
State, but be not limitation of the present invention, every technical spirit according to the present invention is to made for any of the above embodiments any simple
Modification belongs to the technical scope of the present invention, it is also necessary to explanation, aircraft metal resistant cementing structure system according to the invention
The category of part weight losing method technical solution includes any combination between each part mentioned above.
Claims (5)
1. a kind of aircraft metal resistant cementing structure product weight losing method, the weight for aircraft metal resistant cementing structure product
Control, it is characterised in that include the following steps：
S1, chooses overweight metal resistant cementing structure product；
S2, analyzes the weightening process of metal resistant cementing structure product described in S1；
S3, chooses from the weightening process selected by S2 and is glued process as loss of weight process；
S4, Theoretical Design control glue consumption, draw the weight range of glue consumption；
S5, designs durable cementing structure product technique glue consumption loss of weight experiment, including：
S5-1, designs three groups of identical structural members, and weighs to structural member；
S5-2, glue spraying operation is carried out to structural member in S5-1, wherein, one group be the disposable glue spraying of whole face, one group be whole face once
Property glue spraying and carry out inhaling glue operation, one group carries out suction glue for branch's point gradual glue spraying and according to glue spraying order, and glue spraying is operated
Structural member afterwards is weighed；
S5-3, structural member are glued fitting；
S5-4, is further handled structural member；
S5-5, weighs and draws experimental data；
The durable cementing structure part weight scope of control is drawn by S1-S5.
2. aircraft metal resistant cementing structure product weight losing method as claimed in claim 1, it is characterised in that glue is chosen in S3
It is to keep the intensity of aircraft metal resistant cementing structure product that process, which is connect, as the foundation of loss of weight process.
3. aircraft metal resistant cementing structure product weight losing method as claimed in claim 1, it is characterised in that theory is set in S4
The foundation of meter control glue consumption includes glue-joint strength.
4. aircraft metal resistant cementing structure product weight losing method as claimed in claim 1, it is characterised in that durable glue in S5
It is contrast test to connect the experiment of structural fabrication technique glue consumption loss of weight.
5. aircraft metal resistant cementing structure product weight losing method as claimed in claim 1, it is characterised in that the suction glue behaviour
Make used tool to inhale gummed paper.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510845528.3A CN105332982B (en) | 2015-11-26 | 2015-11-26 | A kind of aircraft metal resistant cementing structure product weight losing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510845528.3A CN105332982B (en) | 2015-11-26 | 2015-11-26 | A kind of aircraft metal resistant cementing structure product weight losing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105332982A CN105332982A (en) | 2016-02-17 |
| CN105332982B true CN105332982B (en) | 2018-04-13 |
Family
ID=55283701
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510845528.3A Active CN105332982B (en) | 2015-11-26 | 2015-11-26 | A kind of aircraft metal resistant cementing structure product weight losing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105332982B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3780969A (en) * | 1971-03-02 | 1973-12-25 | Ver Flugtechnische Werke | Wing case for air foils |
| CN101687287A (en) * | 2007-05-31 | 2010-03-31 | 空中客车控股有限公司 | Method for producing a composite skin in the field of aeronautics and astronautics |
| CN101891015A (en) * | 2010-07-20 | 2010-11-24 | 中国航空工业集团公司西安飞机设计研究所 | Skin plate weight reducing method |
| CA2765140A1 (en) * | 2009-06-11 | 2010-12-16 | Saab Ab | An aircraft structure with structural parts connected by a nanostructure and a method for making said aircraft structure |
| US7988809B2 (en) * | 2004-09-01 | 2011-08-02 | Hexcel Corporation | Aircraft floor and interior panels using edge coated honeycomb |
| CN102712164A (en) * | 2010-01-20 | 2012-10-03 | 赫克塞尔合成有限公司 | Sandwich panels for aerospace structural application |
| CN103661918A (en) * | 2012-08-28 | 2014-03-26 | 波音公司 | Bonded composite aircraft wing |
-
2015
- 2015-11-26 CN CN201510845528.3A patent/CN105332982B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3780969A (en) * | 1971-03-02 | 1973-12-25 | Ver Flugtechnische Werke | Wing case for air foils |
| US7988809B2 (en) * | 2004-09-01 | 2011-08-02 | Hexcel Corporation | Aircraft floor and interior panels using edge coated honeycomb |
| CN101687287A (en) * | 2007-05-31 | 2010-03-31 | 空中客车控股有限公司 | Method for producing a composite skin in the field of aeronautics and astronautics |
| CA2765140A1 (en) * | 2009-06-11 | 2010-12-16 | Saab Ab | An aircraft structure with structural parts connected by a nanostructure and a method for making said aircraft structure |
| CN102712164A (en) * | 2010-01-20 | 2012-10-03 | 赫克塞尔合成有限公司 | Sandwich panels for aerospace structural application |
| CN101891015A (en) * | 2010-07-20 | 2010-11-24 | 中国航空工业集团公司西安飞机设计研究所 | Skin plate weight reducing method |
| CN103661918A (en) * | 2012-08-28 | 2014-03-26 | 波音公司 | Bonded composite aircraft wing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105332982A (en) | 2016-02-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Chermoshentseva et al. | The behavior of delaminations in composite materials-experimental results | |
| CN104441631B (en) | A kind of easy-abrasion silicone rubber ring and metal-to-metal adhesive fitting manufacture method | |
| WO2010057502A2 (en) | Wind turbine blade comprising particle-reinforced bonding material | |
| US20110297315A1 (en) | Method for producing resin-based composite | |
| JP2014065482A (en) | Bonded composite aircraft wing | |
| EP2669186A3 (en) | Bonded composite airfoil and fabrication method | |
| US20080048359A1 (en) | Manufacturing method for trumpet spar and other curved objects | |
| Gulasik et al. | Delamination-debond behaviour of composite T-joints in wind turbine blades | |
| CN105332982B (en) | A kind of aircraft metal resistant cementing structure product weight losing method | |
| CN109514887A (en) | Acoustic damping structures | |
| CN108363828B (en) | Modeling method of variable-stiffness composite material | |
| CN107116849A (en) | A kind of embedded suction ripple comb core, its preparation method and implantation frock | |
| Adkins et al. | End effects in scarf joints | |
| CN202244075U (en) | Frame and wallboard connecting structure | |
| CN211546394U (en) | Gridding adhesive tape | |
| Kumar et al. | Modeling and experimental evaluation of geometrically graded multi-material single-lap joints | |
| CN204391284U (en) | One inserts type Wave suction composite material structure | |
| Selahi | Non-linear analysis of adhesive joints in composite structures | |
| CN207825479U (en) | The attachment erection structure on composite products surface | |
| CN112303079A (en) | Convenient large-size thermal protection member profile matching degree trial assembly detection method | |
| CN108749163A (en) | A kind of preparation method of Pneumatic flexible element with variable rigidity | |
| CN113246339B (en) | Carbon fiber reinforced prepreg material and method for forming coated missile wing by using same | |
| Norton et al. | Pressure distribution over thick airfoils-model tests | |
| Ungureanu et al. | Shear structural response of adhesive joints for FRP composites | |
| Han et al. | Multiscale analysis of the correlation of processing parameters on viscidity of composites fabricated by automated fiber placement |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |