CN105092636A - Composite material part tool heat distribution experiment method - Google Patents
Composite material part tool heat distribution experiment method Download PDFInfo
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- CN105092636A CN105092636A CN201410188545.XA CN201410188545A CN105092636A CN 105092636 A CN105092636 A CN 105092636A CN 201410188545 A CN201410188545 A CN 201410188545A CN 105092636 A CN105092636 A CN 105092636A
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Abstract
The invention belongs to the technical field of composite material manufacturing, and especially relates to a composite material part tool heat distribution experiment method. By stimulating the whole process of part solidification, and the obtained data is analyzed so as to obtain all parameters of part solidification during the massive production process, wherein the parameters comprise the tool number, the tool positions, the used solidification equipment, the thermocouple number, the thermocouple positions, and solidification curve parameter.
Description
Technical field
The invention belongs to manufacture technology of composite material field, particularly relate to composite material parts frock heat distribution experimental technique.
Background technology
Existing in-plant composite material parts frock was the little of heat distribution before manufactured parts, even if it is also only the position determining leading and delayed thermopair that some frock has done heat distribution, and often ignores the adjustment of heating rate and the related request of subsequent production in cure parameter.But after some production requirement frock heat distribution success, the series-produced production model of part is just consistent with the scheme of heat distribution, and content comprises: the equipment of frock quantity, putting position, use, the quantity of thermopair and position and cure profile.
The content of invention
The object of invention
By the overall process of simulation part solidification, utilize the data analysis obtained, thus draw whole parameters that part solidifies when criticizing production, comprising: the parameter of frock quantity and putting position, the curing apparatus of use, the quantity of thermopair and position and cure profile.
The technical scheme of invention
Composite material parts frock heat distribution experimental technique, this method comprises the following steps:
Step one, before frock heat distribution experiment, according to difference of giving leaching material and design of part form used during forming parts, first cure profile will be analyzed by we, and formulates the standard of corresponding cure parameter.The solidification temperature of what present aeronautical product was commonly used give leaching material is divided into two kinds: 125 DEG C and 180 DEG C.For parameter analysis we be divided into 3 stages:
65 is 0.5 to 3.5 DEG C/min to (thermostat temperature-20 DEG C) heating rate scope;
(thermostat temperature-20 DEG C) are 0.2 to 3.5 DEG C/min to thermostat temperature heating rate scope;
The speed of cooling is not higher than 5 DEG C/min.
Step 2: at frock upper berth heat release galvanic couple
During lay, thermopair will cover whole frock to greatest extent, and then with two-layer airfelt cover heating galvanic couple, is also fixed in frock with high temperature gummed tape by airfelt; Finally, vacuum bag is pasted according to part production.If the thermocouple location of heat distribution scheme is at the back side of frock, only need covers two-layer airfelt just passable, then not need production to paste vacuum bag, as long as reinforce with high temperature gummed tape.
Step 3: frock is placed in autoclave:
The frock that frock material, version and volume are more or less the same be placed at same autoclave, frock putting position in autoclave will be convenient to the flowing of air-flow in autoclave to greatest extent; When frock quantity can not allow autoclave full load, the close hot-press tank mouth that try one's best.
Step 4: solidification frock being carried out heat distribution, utilizes thermopair to gather the data of solidification process heat distribution simultaneously:
Step 5: the collection of data and analysis:
Solidify complete, the data of heat distribution are derived from curing apparatus, curing data and the thermocouple location of deriving are number corresponding, our heating rate when can converse solidification of the data that application gathers, and the requirement contrasting step 1 judges that whether the heating rate of this secondary data is qualified; In addition, can also judge whether the temperature of constant temperature time and the solidification of solidifying meets the requirements.
The effect of invention
Test by this frock heat distribution result determined, determine the uncertain factor in the process of part solidification by data from many aspects, reduce the risk factor in the manufacture process of composite material parts.
Accompanying drawing explanation
Fig. 1 is embodiment thermopair lay schematic diagram.
Fig. 2 is that embodiment strengthens putty bar scheme of installation, and wherein 1 is thermopair, and 2 is putty bar, and 3 for strengthening putty bar.
Embodiment
Below for the frock of certain engine blower cover, the present invention is described in further detail.
Composite material parts frock heat distribution experimental technique, this method comprises the following steps:
Step one, before frock heat distribution experiment, according to difference of giving leaching material and design of part form used during forming parts, first cure profile will be analyzed by we, and formulates the standard of corresponding cure parameter.
Engine blower cover is honeycomb sandwich construction, the leaching material that gives used is expected for high temperature gives leaching, cure profile constant temperature is divided into two stage: 110-120 DEG C constant temperature 60 minutes (based on delayed thermopair), 172-182 DEG C of constant temperature 120 minutes (based on delayed thermopair); According to the characteristic of this curve, parameter is set to following 5 stages by us:
65 DEG C to 90 DEG C heating rate scopes are 0.5 to 3.5 DEG C/min;
90 DEG C to 110 DEG C heating rate scopes are 0.2 to 3.5 DEG C/min
120 DEG C to 152 DEG C heating rate scopes are 0.5 to 3.5 DEG C/min;
152 DEG C to 172 DEG C heating rate scopes are 0.2 to 3.5 DEG C/min
The speed of cooling is not higher than 5 DEG C/min.
Step 2: at frock upper berth heat release galvanic couple
During lay, thermopair will cover whole frock to greatest extent, the frock that curvature is large, and peak, the minimum point of frock all will have, like this, and the temperature rate's change drawing frock everywhere in temperature-rise period that just can be more detailed.Instantiation is shown in Fig. 1.
First, with high temperature gummed tape, thermopair is fixed on assigned position according to schema location; And then cover by the airfelt of two-layer 75*75 (mm), airfelt is also fixed in frock with high temperature gummed tape; Finally, vacuum bag is pasted according to part production.Fig. 2 is shown in process for the even vacuum bag of built-in thermoelectric, finally covers one deck putty bar again at bottom putty bar over, so just can reduce the vacuum leak caused by thermopair to greatest extent.
Step 3: frock is placed in autoclave:
Frock is placed in autoclave, because this part has with stove test piece, so the flowing of air-flow in autoclave will be convenient to greatest extent with stove test piece putting position in autoclave during frock heat distribution; When frock quantity can not allow frock also will solidify together, its processing mode is consistent with product frock, and only place 3 thermopairs, paired linea angulata is placed.Be placed on (away from equipment mouth) after part tooling with the frock of stove test piece during solidification, the height with stove test piece frock is consistent with the height of part tooling.
Step 4: solidification frock being carried out heat distribution, utilizes thermopair to gather the data of solidification process heat distribution simultaneously:
Step 5: the collection of data and analysis:
Solidifying complete, the data of heat distribution derived from curing apparatus, is the form of .xls by the form of data by .txt format conversion.Derive data be with autoclave channel number one to one, by the autoclave passage number data corresponding with thermocouple location number of process collection in early stage, derived data is become curing data and thermocouple location number corresponding data, just directly can reflect the particular location of frock during such analysis, the gauge outfit of form is in table 1.
In form, data are arranged, according to the Data classification requirement of step one, respectively different pieces of information is identified, the node of heating rate and the node of constant temperature will have differentiation, and are found out by the timing node of correspondence, fill in above gauge outfit, use is calculated, in table 2 after being convenient to.
Utilization is linked at another one form and calculates heating rate, account form: the 6th minute heating rate=(the 6th minute temperature-1 minute temperature)/5, by that analogy, both can draw intensification and the rate of temperature fall of overall process.
Mark the node of time according to above-mentioned intensification and constant temperature, make mark in the corresponding position of heating rate, and according to the segmentation of cure profile, find out each stage minimum and maximum rate value respectively, and colour code is carried out, in table 3 to the data do not conformed to.
Foundation previous calculations result fills in form below, just can judge that whether this test findings is qualified, in table 4 more intuitively.
Claims (1)
1. composite material parts frock heat distribution experimental technique, it is characterized in that, this method comprises the following steps:
Step one, before frock heat distribution experiment, according to difference of giving leaching material and design of part form used during forming parts, first cure profile will be analyzed by we, and formulates the standard of corresponding cure parameter; The solidification temperature of what present aeronautical product was commonly used give leaching material is divided into two kinds: 125 DEG C and 180 DEG C; For parameter analysis we be divided into 3 stages:
65 is 0.5 to 3.5 DEG C/min to (thermostat temperature-20 DEG C) heating rate scope;
(thermostat temperature-20 DEG C) are 0.2 to 3.5 DEG C/min to thermostat temperature heating rate scope;
The speed of cooling is not higher than 5 DEG C/min;
Step 2: at frock upper berth heat release galvanic couple
During lay, thermopair will cover whole frock to greatest extent, and then with two-layer airfelt cover heating galvanic couple, is also fixed in frock with high temperature gummed tape by airfelt; Finally, vacuum bag is pasted according to part production; If the thermocouple location of heat distribution scheme is at the back side of frock, only need covers two-layer airfelt just passable, then not need production to paste vacuum bag, as long as reinforce with high temperature gummed tape;
Step 3: frock is placed in autoclave:
The frock that frock material, version and volume are more or less the same be placed at same autoclave, frock putting position in autoclave will be convenient to the flowing of air-flow in autoclave to greatest extent; When frock quantity can not allow autoclave full load, the close hot-press tank mouth that try one's best;
Step 4: solidification frock being carried out heat distribution, utilizes thermopair to gather the data of solidification process heat distribution simultaneously:
Step 5: the collection of data and analysis:
Solidify complete, the data of heat distribution are derived from curing apparatus, curing data and the thermocouple location of deriving are number corresponding, our heating rate when can converse solidification of the data that application gathers, and the requirement contrasting step 1 judges that whether the heating rate of this secondary data is qualified; In addition, can also judge whether the temperature of constant temperature time and the solidification of solidifying meets the requirements.
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Cited By (5)
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| CN108943530A (en) * | 2018-07-12 | 2018-12-07 | 安徽佳力奇碳纤维科技股份公司 | A kind of composite molding more than one piece is into solidification of hot-press tank temperature difference control method |
| CN109355605A (en) * | 2018-12-10 | 2019-02-19 | 昆山市超群金属制品有限公司 | A kind of manufacturing method of aluminium bar homogenization |
| CN113203489A (en) * | 2021-03-31 | 2021-08-03 | 成都飞机工业（集团）有限责任公司 | Method for installing thermocouple on back of tool |
| CN113298204A (en) * | 2021-04-30 | 2021-08-24 | 成都飞机工业（集团）有限责任公司 | Correlation method of data in composite material manufacturing process |
| CN113733600A (en) * | 2021-07-30 | 2021-12-03 | 昌河飞机工业（集团）有限责任公司 | Method for improving air tightness of autoclave molding thermocouple |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108943530A (en) * | 2018-07-12 | 2018-12-07 | 安徽佳力奇碳纤维科技股份公司 | A kind of composite molding more than one piece is into solidification of hot-press tank temperature difference control method |
| CN109355605A (en) * | 2018-12-10 | 2019-02-19 | 昆山市超群金属制品有限公司 | A kind of manufacturing method of aluminium bar homogenization |
| CN113203489A (en) * | 2021-03-31 | 2021-08-03 | 成都飞机工业（集团）有限责任公司 | Method for installing thermocouple on back of tool |
| CN113298204A (en) * | 2021-04-30 | 2021-08-24 | 成都飞机工业（集团）有限责任公司 | Correlation method of data in composite material manufacturing process |
| CN113298204B (en) * | 2021-04-30 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Correlation method of data in composite material manufacturing process |
| CN113733600A (en) * | 2021-07-30 | 2021-12-03 | 昌河飞机工业（集团）有限责任公司 | Method for improving air tightness of autoclave molding thermocouple |
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