CN102990990B - Low-speed impacting tracing layer of composite material - Google Patents
Low-speed impacting tracing layer of composite material Download PDFInfo
- Publication number
- CN102990990B CN102990990B CN201210500633.XA CN201210500633A CN102990990B CN 102990990 B CN102990990 B CN 102990990B CN 201210500633 A CN201210500633 A CN 201210500633A CN 102990990 B CN102990990 B CN 102990990B
- Authority
- CN
- China
- Prior art keywords
- ceramic substrate
- composite
- impact
- ceramic
- composite material
- 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
Abstract
The invention relates to a low-speed impacting tracing layer of a composite material. The low-speed impacting tracing layer is a ceramic thin layer coated at a composite material surface (1) and is used for distinguishing corresponding impact damage regions, sizes of impact energies and impacting-after residual compression strength of the composite material according to state changes of the ceramic thin layer after being subjected to low-speed impacting; and the ceramic thin layer is not in a continuous state and is formed in a manner that single ceramic substrates (2) are spliced, the thicknesses of the ceramic substrates (2) are 0.1-0.5mm, the areas of the ceramic substrates (2) are 100-2500mm<2>, and intervals between adjacent ceramic substrates (2) are less than 0.2mm. The technical scheme of the invention is that the ceramic thin layer is coated at the composite material surface, and the corresponding impact damage regions, the sizes of the impact energies and the impacting-after residual compression strengths of the composite material are distinguished through the state changes of the ceramic thin layer after being subjected to the low-speed impacting.
Description
Technical field
The present invention is a kind of composite low velocity impact tracer layer, belongs to manufacture technology of composite material field.
Background technology
Because composite product quality is light, intensity is high, be therefore widely used at aerospace field.Wherein in airborne vehicle, composite is widely used in the structural member such as wing cover, fuselage, vertical fin, aileron of fighter plane and civil aircraft.Aircaft configuration will meet the requirement of structural intergrity usually, comprising static strength, rigidity, durability and damage tolerance requirements.But composite has sensitiveness to low velocity impact, namely when composite product is subject to low velocity impact, easily there is delamination in inside, there is layering on a large scale in composite inner, and compressive strength is when sharply declining, but outer surface may remain visual and can not examine, just because of composite in such cases can not the property examined, make material in application process, there is very large danger.Therefore, the internal injury situation how making material carry out evaluating material with surface damage state after low velocity impact becomes one of emphasis of composite application study.
Traditional composite impact damage is visual, and to examine technology be adopt to have dropping hammer of the hemispherical impactor head of 1 ~ 4in and carry out impact test at specimen surface, by the quality of dropping hammer with highly regulate impact energy.After composite is impacted, measure composite material surface pit depth after impacting, if pit depth is when being greater than 1.3mm after impacting, can accomplish visually can examine impact injury reluctantly.But when after most composite laminated plate impacts, pit depth does not reach this numerical value, impact energy has reached very high, there is severe delamination in composite inner, residual compressive strength significantly reduces, and composite can not reach the mechanical property requirements of product requirement.Be hit before damage lost efficacy at composite, visually can examine the compromise state that technology just can not detect composite effectively reluctantly.
Summary of the invention
The deficiency that the present invention exists for above-mentioned prior art just and design and provide a kind of composite low velocity impact tracer layer, its objective is at composite material surface coated ceramic thin layer, be subject to the change of the state after low velocity impact by this thin layers of ceramic, distinguish the size of composite respective impact affected area, impact energy and impact rear residual compressive strength.
The object of the invention is to be realized by following technical measures:
This composite low velocity impact tracer layer, is characterized in that: described low velocity impact tracer layer is
Refer to the thin layers of ceramic pasted at composite material surface (1), function is subject to the change of the state after low velocity impact by this thin layers of ceramic, distinguishes the size of composite respective impact affected area, impact energy and impact rear residual compressive strength;
This thin layers of ceramic is discontinuous form, thin layers of ceramic pieces together with layered ceramic substrate (2) to form, the thickness of ceramic substrate (2) is 0.1 ~ 0.5mm, and area is 100 ~ 2500mm2, and the gap between adjacent ceramic substrate (2) should be less than 0.2mm.
The shape of ceramic substrate (2) is square, rectangle, triangle, trapezoidal or hexagon.
When composite is subject to low velocity impact, the phenomenon such as the ceramic base sector-meeting on top layer comes off, crack in single ceramic substrate breakage, single ceramic substrate, these phenomenons are easily observed, the position that corresponding composite material surface is hit just can be judged by these phenomenons, and judge residual compressive strength after impact energy that composite respective surfaces stands, impact area, impact according to the degree of injury of ceramic substrate, reach the visual requirement examined technology and judge.So described low velocity impact tracer layer serves the effect of low velocity impact spike.
The fortifying fibre of described composite can be the shuffling body of glass fibre, carbon fiber, aramid fiber, basalt fibre, natural plant fibre or above-mentioned fiber, fabric structure can be one-way fabric, plain cloth, satin fabric, twills, without latitude cloth, non-woven fabrics or non-flexing fabric, the resin system of composite can be epoxy resin, bismaleimide resin, phenolic resins, benzoxazine colophony, and the moulding process of composite can be autoclave technique, RTM technique, VARI technique, RFI technique, pre-preg vacuum bag moulding process.Ceramic substrate adopts following material to prepare: aluminium oxide, zirconia, carborundum, barium titanate.
Accompanying drawing explanation
Fig. 1 is the shape and structure signal that ceramic substrate is covered on composite material surface
Detailed description of the invention
Below with reference to drawings and Examples, technical solution of the present invention is further described:
Shown in accompanying drawing 1,
Embodiment 1
Technical solution of the present invention is carried out according to the following steps:
(1) prepare ceramic substrate
Adopt alumina material to prepare ceramic substrate 2, the thickness of ceramic substrate 2 is 0.2mm, is of a size of 400mm
2;
(2) material prepreg laying
By T300/AG80 epoxy radicals carbon fiber prepreg according to [45/0/-45/90] 4s laying paving laminate, after paving, by ceramic substrate 2 paving in composite material surface 1, ceramic substrate 2 clearance control, in 0.2mm, after paving, encapsulates;
(3) composite material forming
According to 130 DEG C in autoclave, 30min->180 DEG C, 2h->200 DEG C, obtain the composite laminated plate with squamous surface tracer layer after the solidification of 2h technique.
The shape of above-mentioned ceramic substrate 2 is square, rectangle, triangle, trapezoidal or hexagon.
Then, carry out post-impact compression (CAI) test by SACMASRM 2-88 standard to composite, impact energy is 6.67J/mm, and after impact, the ceramic substrate 2 that laminate surface is hit comes off, and periphery ceramic substrate 2 destroys.The region that is hit conforms to the damage field of ceramic substrate 2, and affected area is easily observed, and reaches the visual requirement examined technology and judge.
Embodiment 2
Technical solution of the present invention is carried out according to the following steps:
(1) prepare ceramic substrate
Adopt zirconia material to prepare ceramic substrate 2, the thickness of ceramic substrate 2 is 0.3mm, is of a size of 800mm2;
(2) material prepreg laying
T700 unidirectional carbon fiber dimensional fabric is according to [45/0/-45/90]
3slaying paving laminate, after paving, beats vacuum bag heat-shaping.After sizing, by ceramic substrate 2 paving in composite material surface 1, substrate gap controls in 0.2mm, after paving, again plays vacuum bag sizing;
(3) composite material forming
Pre-setting is laid in RTM mold, injection bimaleimide resin.After injection, according to 130 DEG C, 2h->150 DEG C, 2h->180 DEG C, obtain the composite laminated plate with squamous surface tracer layer after the solidification of 2h->200 DEG C, 10h technique.
The shape of above-mentioned ceramic substrate 2 is square, rectangle, triangle, trapezoidal or hexagon.
Then, carry out post-impact compression (CAI) test by SACMA SRM 2-88 standard to composite, impact energy is 6.67J/mm, and after impact, incomplete after the ceramic substrate 2 that laminate surface is hit is damaged, periphery ceramic substrate 2 destroys.The region that is hit conforms to the damage field of ceramic substrate 2, and affected area is easily observed, and reaches the visual requirement examined technology and judge.
Embodiment 3
Technical solution of the present invention is carried out according to the following steps:
(1) prepare ceramic substrate
Adopt barium-titanate material to prepare ceramic substrate 2, the thickness of ceramic substrate 2 is 0.25mm, is of a size of 700mm
2;
(2) material prepreg laying
By glass fabric/AG80 epoxy radicals prepreg according to [45/0/-45/90] 4s laying paving laminate, after paving, by ceramic substrate 2 paving in composite material surface 1, ceramic substrate 2 clearance control, in 0.2mm, after paving, encapsulates;
(3) composite material forming
According to 130 DEG C in autoclave, 30min->180 DEG C, 2h->200 DEG C, obtain the composite laminated plate with squamous surface tracer layer after the solidification of 2h technique.
The shape of above-mentioned ceramic substrate 2 is square, rectangle, triangle, trapezoidal or hexagon.
Then, by SACMA SRM 2-88 standard, post-impact compression (CAI) test is carried out to composite, impact energy is 6.67J/mm, after impact, ceramic substrate 2 inside that is hit, laminate surface crack and with ceramic substrate 2 gap enlargement of periphery, periphery ceramic substrate 2 destroys.The region that is hit conforms to the damage field of ceramic substrate 2, and affected area is easily observed, and reaches the visual requirement examined technology and judge.
Embodiment 4
Technical solution of the present invention is carried out according to the following steps:
(1) prepare ceramic substrate
Adopt carbofrax material to prepare ceramic substrate 2, the thickness of ceramic substrate 2 is 0.4mm, is of a size of 2000mm
2;
(2) material prepreg laying
T800 unidirectional carbon fiber dimensional fabric is according to [45/0/-45/90]
3slaying paving laminate, after paving, beats vacuum bag heat-shaping.After sizing, by ceramic substrate 2 paving in composite material surface 1, substrate gap controls in 0.2mm, after paving, again plays vacuum bag sizing;
(3) composite material forming
Pre-setting is laid in VARI mould, injection bimaleimide resin.Injection benzoxazine colophony.After injection, according to 180 DEG C, after the solidification of 2h->200 DEG C, 2h technique, obtain the composite laminated plate with squamous surface tracer layer.
The shape of above-mentioned ceramic substrate 2 is square, rectangle, triangle, trapezoidal or hexagon.
Then, carry out post-impact compression (CAI) test by SACMA SRM 2-88 standard to composite, impact energy is 6.67J/mm, and after impact, incomplete after the ceramic substrate 2 that laminate surface is hit is damaged, periphery ceramic substrate 2 destroys.The region that is hit conforms to the damage field of ceramic substrate 2, and affected area is easily observed, and reaches the visual requirement examined technology and judge.
Embodiment 5
Technical solution of the present invention is carried out according to the following steps:
(1) prepare ceramic substrate
Adopt alumina material to prepare ceramic substrate 2, the thickness of ceramic substrate 2 is 0.3mm, is of a size of 1000mm
2;
(2) material prepreg laying
T300 carbon fiber plain cloth is according to [(45/-45)/(0/90)]
4slaying paving laminate, after paving, beats vacuum bag heat-shaping.After sizing, by ceramic substrate 2 paving in composite material surface 1, substrate gap controls in 0.2mm, after paving, again plays vacuum bag sizing;
(3) composite material forming
Be encapsulated in by pre-setting in RFI mould, resin system is epoxy resin.According to 180 DEG C in autoclave, after the solidification of 2h->200 DEG C, 2h skill, obtain the composite laminated plate with squamous surface tracer layer.
The shape of above-mentioned ceramic substrate 2 is square, rectangle, triangle, trapezoidal or hexagon.
Then, carry out post-impact compression (CAI) test by SACMA SRM 2-88 standard to composite, impact energy is 6.67J/mm, and after impact, the ceramic substrate 2 that laminate surface is hit cracks, and periphery ceramic substrate 2 destroys.The region that is hit conforms to the damage field of ceramic substrate 2, and affected area is easily observed, and reaches the visual requirement examined technology and judge.
Embodiment 6
Technical solution of the present invention is carried out according to the following steps:
(1) prepare ceramic substrate
Adopt zirconia material to prepare ceramic substrate 2, the thickness of ceramic substrate 2 is 0.25mm, is of a size of 500mm
2;
(2) material prepreg laying
By IM7/AG80 epoxy radicals carbon fiber prepreg according to [45/0/-45/90]
4slaying paving laminate, after paving, by ceramic substrate 2 paving in composite material surface 1, ceramic substrate 2 clearance control, in 0.2mm, after paving, encapsulates;
(3) composite material forming
Put by packaged prepreg in mold pressing frock, press pressurizes 1.0MPa, according to 130 DEG C, 30min->180 DEG C, 2h->200 DEG C, 2h technique is solidified, and the demoulding obtains the composite laminated plate with squamous surface tracer layer.
The shape of above-mentioned ceramic substrate 2 is square, rectangle, triangle, trapezoidal or hexagon.
Then, carry out post-impact compression (CAI) test by SACMA SRM 2-88 standard to composite, impact energy is 6.67J/mm, and after impact, the ceramic substrate 2 that laminate surface is hit cracks, and periphery ceramic substrate 2 destroys.The region that is hit conforms to the damage field of ceramic substrate 2, and affected area is easily observed, and reaches the visual requirement examined technology and judge.
Compared with prior art, the present invention examines visual object to change the composite layer ceramic substrate easily observed into state change from the composite material surface pit not easily observed, the phenomenons such as these states change main manifestations is that ceramic substrate comes off, crack in single ceramic substrate breakage, single ceramic substrate, these phenomenons are easily observed, and reach composite and are subject to impacting the rear visual requirement examined technology and judge.
Claims (2)
1. a composite low velocity impact tracer layer, is characterized in that: described low velocity impact tracer layer is
Refer to the thin layers of ceramic pasted at composite material surface (1), function is subject to the change of the state after low velocity impact by this thin layers of ceramic, distinguishes the size of composite respective impact affected area, impact energy and impact rear residual compressive strength;
This thin layers of ceramic is discontinuous form, and thin layers of ceramic pieces together with layered ceramic substrate (2) to form, and the thickness of ceramic substrate (2) is 0.1 ~ 0.5mm, and area is 100 ~ 2500mm
2, the gap between adjacent ceramic substrate (2) is less than 0.2mm.
2. composite low velocity impact tracer layer according to claim 1, is characterized in that: the shape of ceramic substrate (2) is square, rectangle, triangle, trapezoidal or hexagon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210500633.XA CN102990990B (en) | 2012-11-29 | 2012-11-29 | Low-speed impacting tracing layer of composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210500633.XA CN102990990B (en) | 2012-11-29 | 2012-11-29 | Low-speed impacting tracing layer of composite material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102990990A CN102990990A (en) | 2013-03-27 |
| CN102990990B true CN102990990B (en) | 2015-02-11 |
Family
ID=47920341
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210500633.XA Active CN102990990B (en) | 2012-11-29 | 2012-11-29 | Low-speed impacting tracing layer of composite material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102990990B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109676975A (en) * | 2018-12-26 | 2019-04-26 | 中国航空工业集团公司基础技术研究院 | The spatial distribution method of self-repair resin based composites based on vascular |
| CN110413804B (en) * | 2019-07-30 | 2021-09-07 | 沈阳航空航天大学 | Efficient visual detection method suitable for low-energy impact damage of composite material |
| CN113686702A (en) * | 2021-09-13 | 2021-11-23 | 东华大学 | Visual method for representing low-speed impact protection effect of flexible material |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101509856A (en) * | 2008-12-30 | 2009-08-19 | 南京理工大学 | Multifunction flexible composite material impact test apparatus |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008016066A1 (en) * | 2008-03-28 | 2009-10-01 | Airbus Deutschland Gmbh | sandwich panel |
-
2012
- 2012-11-29 CN CN201210500633.XA patent/CN102990990B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101509856A (en) * | 2008-12-30 | 2009-08-19 | 南京理工大学 | Multifunction flexible composite material impact test apparatus |
Non-Patent Citations (5)
| Title |
|---|
| Low-velocity impact response of non-woven hemp fibre reinforced unsaturated polyester composites: Influence of impactor geometry and impact velocity;H.N. Dhakal等;《Composite Structures》;20120930 * |
| Review of low-velocity impact properties of composite materials;M.O.W Richardson等;《Composites》;19960430 * |
| S-2/F46 复合材料低速冲击损伤及剩余弯曲性能;贺成红等;《材料工程》;20080630 * |
| 复合材料层压板低速冲击和准静态压痕损伤等效性的研究;闫丽等;《航空材料学报》;20110630 * |
| 平纹编织碳纤维增强碳化硅复合材料低速冲击特性及冲击后的压缩强度;程起有等;《硅酸盐学报》;20091130 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102990990A (en) | 2013-03-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Petrucci et al. | Impact and post-impact damage characterisation of hybrid composite laminates based on basalt fibres in combination with flax, hemp and glass fibres manufactured by vacuum infusion | |
| CA2888615C (en) | Surface engineering of thermoplastic materials and tooling | |
| CN102990990B (en) | Low-speed impacting tracing layer of composite material | |
| US10632716B2 (en) | Composite panels | |
| CN111497278B (en) | Preparation method of carbon fiber composite material with designable characteristic structure and product | |
| Butukuri et al. | Evaluation of skin-core adhesion bond of out-of-autoclave honeycomb sandwich structures | |
| CN103552255A (en) | Method for manufacturing composite material porosity detection comparison sample pieces | |
| CN104149228A (en) | Integrated forming die and method for glass fiber reinforced plastic antenna housing | |
| CN110877464A (en) | Standard hard patching method for rapid repair of aircraft composite materials | |
| CN105021434A (en) | Preparation method of high-temperature composite material sample | |
| AU2012338544A1 (en) | Protective material arrangement | |
| CN110466217A (en) | A kind of tencel metal laminate and preparation method thereof | |
| CN106769302A (en) | A kind of method for preparing composite material defect testpieces | |
| CN110549692A (en) | ultraviolet fluorescent tracing layer for displaying low-speed impact damage of composite material | |
| CN100551694C (en) | The honeycomb block that is used for the honeycomb sandwich composite moulding | |
| CN104816491B (en) | Preparation method for RTM preforms with angular structures | |
| Wang et al. | Improvement of composite drape forming quality by enhancing interply slip | |
| CN102673084A (en) | Production method for automobile engine compartment heat-insulating cushion | |
| CN106584701B (en) | Body of sewing enhances composite material steering engine backplate forming method | |
| CN202608205U (en) | Production equipment for continuous fiber reinforced thermoplastic honeycomb plate | |
| Lin et al. | Experimental study on forming quality of hat-shaped component based on combined mandrel pressurization method | |
| CN202895788U (en) | Continuous fiber-reinforced thermoplastic cellular sheet material | |
| Haris et al. | A comparative study of an aircraft radome closed mold through vacuum infusion technique | |
| Castanié et al. | Effect of release agent on process-induced deformation in autoclave curing of laminate composites | |
| KR20220127854A (en) | Automated Mechanical Forming of Composite Materials |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |