CN203479625U - Test piece for measuring type I breaking capacity of composite propellant/cladding layer bonding interface - Google Patents
Test piece for measuring type I breaking capacity of composite propellant/cladding layer bonding interface Download PDFInfo
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- CN203479625U CN203479625U CN201320566159.0U CN201320566159U CN203479625U CN 203479625 U CN203479625 U CN 203479625U CN 201320566159 U CN201320566159 U CN 201320566159U CN 203479625 U CN203479625 U CN 203479625U
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Abstract
The utility model discloses a test piece for measuring type I breaking capacity of a composite propellant/cladding layer bonding interface, wherein a composite propellant layer is bonded with the cladding layer through a bonding layer, and aligned to both ends, and one ends of the composite propellant layer and the cladding layer are not bonded, and provided with precracks; a grating is bonded in the middle positions of the side surfaces of the composite propellant layer, the bonding layer and the cladding layer; the initial graduation of the grating is opposite to the tip of each precrack; support beams are bonded to the corresponding surfaces of the bonding surfaces of the composite propellant layer and the cladding layer respectively; one ends of the support beams are aligned to the ends without precrack of the composite propellant layer, the bonding layer and the cladding layer; the support beam is longer than or as long as the composite propellant layer and the cladding layer; loading blocks are fixed on the support beams at the ends with the precracks of the composite propellant layer, the bonding layer and the cladding layer. According to the test piece, the support beams are adopted, so that the rigidity of the test piece is improved; the test piece is suitable for measuring the type I breaking capacity of a soft or flexible material combined component; the grating is adopted, so that the mesoscopic characteristics and the crack propagation situation of the tips of the cracks can be recorded in real time.
Description
Technical field
The utility model belongs to I type energy to failure and measures field, and particularly a kind of composite propellant/clad bonding interface I type energy to failure is measured test specimen.
Background technology
Composite propellant and clad are all the flexible materials with excellent resilience performance.About the energy to failure of soft material, measure, current relevant criterion both domestic and external is all by disbonded test, such as T-shapedly peeling off, 90 ° and 180 ° of disbonded tests etc.As standard BS EN ISO11339:2005.Adhesives----T-peel test for flexible-to-flexible bonded assemblies, with regard to specified in more detail the T-shaped peel test method of bonded assemblies of flexible material and flexible material. still, because propellant is particles filled compound substance, can will there is damage and failure in inside in propellant in disbonded test before bonding interface loses efficacy, thereby relevant disbonded test standard may be very not applicable.
And in the energy to failure of the very large material of the rigidity such as metal, pottery is measured, double cantilever beam sample is used comparatively extensive.This sample has two large advantages: Stable Crack Growth, can eliminate false effect; Can adopt beam theory to come reduced data to process.Standard BS ISO7991:2000.Determination of the mode I adhesive fracture energy GIc of structure adhesives using the double cantilever beam (DCB) and tapered double cantilever beam (TDCB) specimens, is just described the physical dimension of double cantilever beam sample and Processing for Data Analysis in Physics.But this sample and test method are not suitable for rigidity/from the very little material of anharmonic ratio, as composite propellant and clad.Because they are during as beam arm in sample, can there is deflection to a certain degree in end, impact experiment accuracy.
Summary of the invention
The purpose of this utility model is to provide a kind of test specimen that goes for composite propellant and clad bonding interface I type energy to failure mensuration.
The technical solution that realizes the utility model object is:
A kind of composite propellant/clad bonding interface I type energy to failure is measured test specimen, comprise loading blocks, brace summer, composite propellant layer, grating, adhered layer and clad, wherein, composite propellant layer and clad are bonding by adhesive linkage, justify align, one end is not bonding, leave precrack, push away the compound agent layer that enters, the centre position, side of adhered layer and clad is pasted with a grating, the initial scale of grating is corresponding with the tip of precrack, on the corresponding surface of composite propellant layer and clad bonding plane, be bonded with respectively brace summer, one end of brace summer and composite propellant layer, adhered layer and clad do not have one end alignment of precrack, the length of brace summer is more than or equal to composite propellant layer and clad, loading blocks is fixed on brace summer and is positioned at composite propellant layer, adhered layer and clad leave one end of precrack.
The utility model compared with prior art, its remarkable advantage:
(1) the utility model, owing to having adopted brace summer, has improved the rigidity of whole test specimen, and therefore, the I type energy to failure that is applicable to softness or flexible material coupling unit is measured, and can not damage material.
(2) dismounting is convenient in the utility model aluminium matter brace summer and loading blocks mechanism, can reuse.
(3) the utility model is owing to having adopted grating, and microscopy apparatus supports the use, and micro character and Crack Extension situation that can real time record crack tip, contribute to study its mechanism of fracture.
Below in conjunction with accompanying drawing, the utility model is described in further detail.
Accompanying drawing explanation
Fig. 1 is the structural representation of the utility model test specimen.
Embodiment
As shown in Figure 1:
A kind of composite propellant/clad of the utility model bonding interface I type energy to failure is measured test specimen, comprise loading blocks 1, brace summer 2, composite propellant layer 3, grating 4, adhered layer 5 and clad 6, wherein, composite propellant layer 3 and clad 6 are bonding by adhesive linkage 5, justify align, one end is not bonding, leave precrack, push away the compound agent layer 3 that enters, the centre position, side of adhered layer 5 and clad 6 is pasted with a grating 4, the initial scale of grating 4 is corresponding with the tip of precrack, on the corresponding surface of composite propellant layer 3 and clad 6 bonding planes, be bonded with respectively brace summer 2, one end of brace summer 2 and composite propellant layer 3, adhered layer 5 and clad 6 do not have one end alignment of precrack, the length of brace summer 2 is more than or equal to composite propellant layer 3 and clad 6, loading blocks 1 is fixed on brace summer 2 and is positioned at composite propellant layer 3, adhered layer 5 and clad 6 leave one end of precrack.
Brace summer 2 is aluminum support
In loading blocks 1, have the circular hole supporting with test machine clamping mechanism.
Loading blocks 1 and brace summer 2 are bolted.
Embodiment:
A kind of composite propellant/clad bonding interface I type energy to failure is measured test specimen, comprise loading blocks 1, aluminum brace summer, composite propellant layer 3, grating 4, adhered layer 5 and clad 6, wherein, composite propellant layer 3 and clad 6 are bonding by adhesive linkage 5, justify align, one end is not bonding, leave precrack, push away the compound agent layer 3 that enters, the centre position, side of adhered layer 5 and clad 6 is pasted with a grating 4, the initial scale of grating 4 is corresponding with the tip of precrack, on the corresponding surface of composite propellant layer 3 and clad 6 bonding planes, be bonded with respectively aluminum brace summer, one end of aluminum brace summer and composite propellant layer 3, adhered layer 5 and clad 6 do not have one end alignment of precrack, the length of aluminum brace summer is more than or equal to composite propellant layer 3 and clad 6, loading blocks 1 is fixed on aluminum brace summer and is positioned at composite propellant layer 3, adhered layer 5 and clad 6 leave one end of precrack, in loading blocks 1, have the circular hole supporting with test machine clamping mechanism.
When bonding composite propellant layer 3 and clad 6, in one end of adhesive linkage 5, place the crackle of the next prefabricated certain length of polytetrafluoroethylene film that one 0.2 ± 0.1mm is thick, after adhesive fixed line is complete, extract film out.
The assembling of aluminum brace summer: the loading blocks of making 1 and aluminum brace summer are carried out to removing surface, utilize 4 bolts to connect the two.Afterwards, correct upper and lower two-part repeatability and symmetry.The bonding plane of aluminum brace summer dries after by sand papering, acetone degrease, and the face bonding with clad will carry out surface treatment to improve bonding strength.
The combination of aluminum brace summer and composite propellant layer 3, clad 6: the aluminum brace summer of handling well and composite propellant layer 3 is bonding by modified acroleic acid adhesive, solidify and dry.Subsequently, the upper surface of clad 4 is carried out with before similarly after surface treatment, with corresponding bonding the solidifying of aluminum brace summer.
Bonding sample is evenly exerted pressure, process the adhesive that overflow side.After solidifying completely, side adheres to respectively grating 4 near adhesive linkage 5 places, can be used for experiment.
Experimentation is as follows: the sample of making is connected by straight pin with the clamping device in testing machine by the circular hole loading in 1, and circular hole place coating lubricating oil is to reduce friction; With relatively slow loading speed, carry out pretension again; Then optical microscope is placed on the platform moving freely, camera lens, over against this sample interface place, is brought into focus; Finally, testing machine is set to the loading mode of constant displacement speed, utilizes the supporting sensor record device load-displacement curve of experimental machine, and optical microscope is real-time follow-up and record crack tip situation also.
Adopt the load-displacement curve of sensor record in testing machine, and the length w of the crack tip crack process zone recording in the photo of interface, utilize following formula to calculate the I type energy to failure of sample:
P wherein
c, δ
cbe that peak of curve is put corresponding transverse and longitudinal coordinate figure, B is specimen width, and a is crack length, and F, N are correction terms, and F, N determine according to standard BS ISO7991:2000.
Claims (5)
1. composite propellant/clad bonding interface I type energy to failure is measured test specimen, it is characterized in that: comprise loading blocks (1), brace summer (2), composite propellant layer (3), grating (4), adhered layer (5) and clad (6), wherein, composite propellant layer (3) and clad (6) are bonding by adhesive linkage (5), justify align, one end is not bonding, leave precrack, push away the compound agent layer (3) that enters, the centre position, side of adhered layer (5) and clad (6) is pasted with a grating (4), the initial scale of grating (4) is corresponding with the tip of precrack, on the corresponding surface of composite propellant layer (3) and clad (6) bonding plane, be bonded with respectively brace summer (2), one end of brace summer (2) and composite propellant layer (3), adhered layer (5) and clad (6) do not have one end alignment of precrack, the length of brace summer (2) is more than or equal to composite propellant layer (3) and clad (6), loading blocks (1) is fixed on brace summer (2) and is positioned at composite propellant layer (3), adhered layer (5) and clad (6) leave one end of precrack.
2. a kind of propellant/clad bonding interface I type energy to failure according to claim 1 is measured test specimen, it is characterized in that: described brace summer (2) is aluminum brace summer.
3. a kind of propellant/clad bonding interface I type energy to failure according to claim 1 is measured test specimen, it is characterized in that: described loading blocks has the circular hole supporting with test machine clamping mechanism on (1).
4. a kind of propellant/clad bonding interface I type energy to failure according to claim 1 is measured test specimen, it is characterized in that: described loading blocks (1) and brace summer (2) are bolted.
5. a kind of propellant/clad bonding interface I type energy to failure according to claim 1 is measured test specimen, it is characterized in that: the thickness of described adhered layer (5) is 0.2 ± 0.1mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201320566159.0U CN203479625U (en) | 2013-09-12 | 2013-09-12 | Test piece for measuring type I breaking capacity of composite propellant/cladding layer bonding interface |
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| CN201320566159.0U CN203479625U (en) | 2013-09-12 | 2013-09-12 | Test piece for measuring type I breaking capacity of composite propellant/cladding layer bonding interface |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103454153A (en) * | 2013-09-12 | 2013-12-18 | 南京理工大学 | Test piece for determining I type fracture energy of compound propellant/coating layer bonding interface |
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2013
- 2013-09-12 CN CN201320566159.0U patent/CN203479625U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103454153A (en) * | 2013-09-12 | 2013-12-18 | 南京理工大学 | Test piece for determining I type fracture energy of compound propellant/coating layer bonding interface |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140312 Termination date: 20150912 |
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| EXPY | Termination of patent right or utility model |