CN202848023U - Repairable cabin cover - Google Patents
Repairable cabin cover Download PDFInfo
- Publication number
- CN202848023U CN202848023U CN 201220372978 CN201220372978U CN202848023U CN 202848023 U CN202848023 U CN 202848023U CN 201220372978 CN201220372978 CN 201220372978 CN 201220372978 U CN201220372978 U CN 201220372978U CN 202848023 U CN202848023 U CN 202848023U
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- CN
- China
- Prior art keywords
- cabin cover
- outside face
- repairing
- allosome
- engine room
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- 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.)
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Abstract
The utility model belongs to the technical field of repairing of a composite material, and discloses a repairable cabin cover. A repairing area is arranged on a shell of the repairable cabin cover; the repairing area comprises a damaged area and a variant component which is arranged on the outer surface of the repairing area and is mechanically connected with the shell of the repairable cabin cover; the shape of the variant component is matched with the shape of the outer surface of the damaged area; and resin and a glass fiber composite material layer cover the outer surface of the repairing area. With the adoption of the repairable cabin cover provided by the utility model, the damaged area on the shell of the repairable cabin cover can be repaired; and the repaired repairable cabin cover has enough strength, rigidity and using properties.
Description
Technical field
The utility model relates to the composite repair technical field, but particularly relates to a kind of repairing cabin cover.
Background technology
High-performance composite materials begin to have obtained very large development since aircraft and the application of all kinds of framing member at the beginning of 1970's, and the simultaneously damage of composite structure and repairing have also caused widely to be paid attention to.Composite materials property requires high, and operating cycles is long, and the formed product cost is higher, therefore fracture is appearred in its product and waits the product method for repairing and mending relevant with its mechanical property to require relatively high.
The engine room cover that is used on aircraft and the aerogenerator is exactly a kind of glass fiber reinforced plastics composite material product, glass-felt plastic itself has light weight, high-intensity characteristics, performance is better than steel, but it is low that its shortcoming is exactly modulus of elasticity, the damage that its impact causes is very responsive, fracture damage appears in product easily, and it is extremely important therefore to study the restorative procedure that can recover the engine room cover integraty.At present still lack effective, simple and economical reparation means and recover as far as possible to repair the original structural strength of product, rigidity and in-use performance.
The utility model content
The technical matters that (one) will solve
But the utility model syllabus provide a kind of repairing cabin cover, in order to solve the reparation problem after engine room cover is damaged.
(2) technical scheme
In order to solve the problems of the technologies described above, but the utility model provides a kind of repairing cabin cover, has restoring area on the housing of described engine room cover, described restoring area comprise damage field and be arranged on the described damage field outside face and with the allosome member of engine room cover housing mechanical connection, and the outside face of the shape of described allosome member and described damage field mates;
Be coated with resin and glass fiber compound material layer on the outside face of described restoring area;
Wherein, the height of described damage field outside face is less than the height of damage field outside face not.
But aforesaid repairing cabin cover, preferably, the intensity of described allosome construction material is greater than the intensity of engine room cover case material
But aforesaid repairing cabin cover, preferably, described allosome member and engine room cover housing are realized mechanical connection by resin and glass fibre.
But aforesaid repairing cabin cover, preferably, the outside face of described damage field has the trapezium structure that increase highly successively mind-set periphery therefrom.
But aforesaid repairing cabin cover, preferably, described resin is epoxy resin or unsaturated polyester (UP); Described glass fibre is the alkali-free woven roving.
But aforesaid repairing cabin cover preferably, also is filled with on the outside face of described resin and glass fiber compound material layer be used to the weighting material of filling and leading up described resin and glass fiber compound material layer outside face.
But aforesaid repairing cabin cover, preferably, described weighting material is putty.
But aforesaid repairing cabin cover, preferably, the material of described allosome member is titanium alloy, aluminum alloy or corrosion-resistant steel.
But aforesaid repairing cabin cover, preferably, the thickness of described allosome member is 1/4 of engine room cover thickness of shell.
But aforesaid repairing cabin cover, preferably, the thickness of described damage field is 1/2 of engine room cover thickness of shell.
(3) beneficial effect
But repairing cabin cover provided by the utility model is by the allosome member at the setting of damage field outside face and engine room cover housing mechanical connection, and on the outside face of restoring area covering resin and glass fiber compound material layer, so that solidifying with the allosome member with the glass fiber compound material layer, resin is connected, realization is to the reparation of failure area on the engine room cover housing, and the engine room cover after the reparation possesses enough intensity, rigidity and in-use performance.
Description of drawings
Fig. 1 is the structural representation of cabin cover of wind power generator;
But Fig. 2 is the partial schematic diagram of repairing cabin cover in the present embodiment;
Wherein, a: engine room cover housing; 1: flange; 2: restoring area; 3: failure area; 4: the allosome member; 5: resin and glass fiber compound material layer; 6: weighting material.
The specific embodiment
Below in conjunction with drawings and Examples, the specific embodiment of the present utility model is described in further detail.Following examples are used for explanation the utility model, but are not used for limiting scope of the present utility model.
The utility model is by providing the reparation problem after but a kind of repairing cabin cover solves the cover damage of composite material cabin, and recover as far as possible to repair the original structural strength of product, rigidity and in-use performance, illustrate as an example of cabin cover of wind power generator example in the present embodiment.
Figure 1 shows that the structural representation of cabin cover of wind power generator.As shown in Figure 1, the outside face of cabin cover of wind power generator housing a is not smooth, level and smooth structure, the connection structure that is connected with other parts (such as propeller hub cover, pylon etc.) in addition above it, such as flange, as shown in Figure 2, specify the reparation of composite material cabin cover in the present embodiment when damage occurring near the flange 1.
But Figure 2 shows that the partial schematic diagram of repairing cabin cover in the present embodiment.Be convenient and describe that the top of following content in Fig. 2 is the inside of engine room cover housing a, the below is the outside of engine room cover housing a.
As shown in Figure 2, but has restoring area 2 on the housing a of repairing cabin cover in the present embodiment, restoring area 2 comprises that damage field 3(is the upper part that damage occurs of engine room cover housing a) and be arranged on damage field 3 outside faces and with the allosome member 4 of engine room cover housing a mechanical connection, and the outside face of the shape of allosome member 4 and damage field 3 coupling, fit tightly with damage field 3 with realization allosome member 4, but the mechanical property of enhancing repairing cabin cover; And on the outside face of restoring area 2 covering resin and glass fiber compound material layer 5.
Wherein, the height of damage field 3 outside faces is less than the height of damage field not (being the part that occurs damage on the engine room cover housing a) outside face, realization allosome member 4 is imbedded on the outside face of damage field 3, with covering resin on the outside face of restoring area 2 and glass fiber compound material layer 5.And the intensity of preferred allosome member 4 materials can be titanium alloy, aluminum alloy or corrosion-resistant steel greater than the intensity of engine room cover housing a material, but with the intensity of further enhancing repairing cabin cover.
The felt that can consist of by glass-fiber-fabric and the glass fibre of impregnated with resin in the present embodiment covers and pastes on the outside face of restoring area 2, be implemented in covering resin and glass fiber compound material layer 5 on the outside face of restoring area 2, it is consistent with the height of damage field outside face not to fill the outside face height of restoring area 2, and so that resin realizes that with glass fiber compound material layer 5 and allosome member 4 curing is connected (technologic cure time is 24 hours), thereby satisfy the demand to restoring area 2 intensity, rigidity and mechanical property.Wherein, resin can be epoxy resin or unsaturated polyester (UP), and glass fibre can be the alkali-free woven roving.
Simultaneously, because resin has flowing power, can flow between allosome member 4 and the engine room cover housing a, utilize the solidification of resin and glass fibre can realize the mechanical connection of allosome member 4 and engine room cover housing a.Certain allosome member 4 and mode of engine room cover housing a mechanical connection of realizing also has a lot, is not limited to the mechanical connection of realizing allosome member 4 and engine room cover housing a in the present embodiment by the solidification of resin and glass fibre, do not repeat them here.
The height of realizing damage field 3 outside faces has a variety of less than the mode of the height of damage field outside face not, can be by the polish outside face of damage field 3 of angle grinding machine in the present embodiment, preferred polishing thickness is 1/2 of engine room cover thickness of shell, and the polishing area is 1.5 times of damaged area.Can also make the outside face of damage field 3 have the trapezium structure that increase highly successively mind-set periphery therefrom by polishing, the thickness of namely polishing is outward trapezoidal from injury region and successively decreases successively, so that damage field 3 outside faces keep certain roughness, it is firm to realize more fitting when allosome member 4 is imbedded on damage field 3 outside faces.
Before damage field 3 outside faces are imbedded allosome member 4, need with acetone scrub buffed surface, the particle that prevents from polishing affect the applying degree of allosome member 4 and damage field 3 outside faces.
After damage field 3 outside faces are imbedded allosome member 4, if allosome member 4 has the appreciiable slit with damage field 3 outside faces, can fill with glass fibre, repair.
Resin are connected with the glass fiber compound material layer with allosome member 4 realize solidifying be connected after, the outside face of restoring area 2 can have burr, can be coated with again one deck resin thereon in the present embodiment, so that the smoothness of restoring area 2 outside faces is consistent with the inside face smoothness of the not failure area of engine room cover housing a.And whether crackle is arranged on the inspection gel coat, and if crackle is arranged, can polish with 60 order sand paper, then clean up with acetone.
For the outside face of damage field 3 is more smooth attractive in appearance, can also fill the weighting material 6 that is used for filling and leading up resin and glass fiber compound material layer 5 outside face at the outside face of resin and glass fiber compound material layer 5.Weighting material 6 can be selected putty in the present embodiment, after putty solidifies, with 60 purpose sand paperings surface.Can be coated with again the last layer resin at last, make restoring area 3 outside faces more smooth, if find that gel coat has crackle, polish with 1200 order sand paper.
Construction temperature among the utility model embodiment is 5 ~ 40 ℃.
As can be seen from the above embodiments, but repairing cabin cover provided by the utility model is by the allosome member at the setting of damage field outside face and engine room cover housing mechanical connection, and on the outside face of restoring area covering resin and glass fiber compound material layer, so that solidifying with the allosome member with the glass fiber compound material layer, resin is connected, realization is to the reparation of failure area on the engine room cover housing, and the engine room cover after the reparation possesses enough intensity, rigidity and in-use performance.
But the Barcol hardness of repairing cabin cover reaches more than 35 in the present embodiment, test method according to GB/T1447-2005 detects sample, and breaking elongation is greater than 2.05%, and tensile strength is greater than 276MPa, stretching epistasis modulus has kept the premium properties of former engine room cover greater than 18.8Gpa.
The above only is preferred implementation of the present utility model; should be understood that; for those skilled in the art; under the prerequisite that does not break away from the utility model know-why; can also make some improvement and replacement, these improvement and replacement also should be considered as protection domain of the present utility model.
Claims (10)
1. but repairing cabin cover, it is characterized in that, has restoring area on the housing of described engine room cover, described restoring area comprise damage field and be arranged on the described damage field outside face and with the allosome member of engine room cover housing mechanical connection, and the outside face of the shape of described allosome member and described damage field mates;
Be coated with resin and glass fiber compound material layer on the outside face of described restoring area;
Wherein, the height of described damage field outside face is less than the height of damage field outside face not.
2. but repairing cabin cover according to claim 1 is characterized in that, the intensity of described allosome construction material is greater than the intensity of engine room cover case material.
3. but repairing cabin cover according to claim 1 is characterized in that, described allosome member and engine room cover housing are realized mechanical connection by resin and glass fibre.
4. but repairing cabin cover according to claim 1 is characterized in that, the outside face of described damage field has the trapezium structure that increase highly successively mind-set periphery therefrom.
5. but repairing cabin cover according to claim 1 is characterized in that, described resin is epoxy resin or unsaturated polyester (UP); Described glass fibre is the alkali-free woven roving.
6. but repairing cabin cover according to claim 1 is characterized in that, also is filled with on the outside face of described resin and glass fiber compound material layer be used to the weighting material of filling and leading up described resin and glass fiber compound material layer outside face.
7. but repairing cabin cover according to claim 6 is characterized in that, described weighting material is putty.
8. but repairing cabin cover according to claim 1 is characterized in that, the material of described allosome member is titanium alloy, aluminum alloy or corrosion-resistant steel.
9. but repairing cabin cover according to claim 8 is characterized in that, the thickness of described allosome member is 1/4 of engine room cover thickness of shell.
10. but repairing cabin cover according to claim 1 is characterized in that, the thickness of described damage field is 1/2 of engine room cover thickness of shell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220372978 CN202848023U (en) | 2012-07-30 | 2012-07-30 | Repairable cabin cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220372978 CN202848023U (en) | 2012-07-30 | 2012-07-30 | Repairable cabin cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202848023U true CN202848023U (en) | 2013-04-03 |
Family
ID=47979247
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220372978 Expired - Fee Related CN202848023U (en) | 2012-07-30 | 2012-07-30 | Repairable cabin cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202848023U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105881888A (en) * | 2016-04-07 | 2016-08-24 | 山东英特力新材料有限公司 | Method for mounting equipment on composite material sandwich panel |
| CN105881931A (en) * | 2016-04-07 | 2016-08-24 | 山东英特力新材料有限公司 | Complementation method for hole of large sandwich-structure composite cabin |
| CN105904747A (en) * | 2016-04-13 | 2016-08-31 | 山东英特力新材料有限公司 | Repairing method of large composite material shelter |
-
2012
- 2012-07-30 CN CN 201220372978 patent/CN202848023U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105881888A (en) * | 2016-04-07 | 2016-08-24 | 山东英特力新材料有限公司 | Method for mounting equipment on composite material sandwich panel |
| CN105881931A (en) * | 2016-04-07 | 2016-08-24 | 山东英特力新材料有限公司 | Complementation method for hole of large sandwich-structure composite cabin |
| CN105881931B (en) * | 2016-04-07 | 2018-03-16 | 山东英特力新材料有限公司 | A kind of complementing method in large-scale sandwich structure composite material nacelle aperture |
| CN105904747A (en) * | 2016-04-13 | 2016-08-31 | 山东英特力新材料有限公司 | Repairing method of large composite material shelter |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130403 Termination date: 20150730 |
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| EXPY | Termination of patent right or utility model |