CN105585727A - Surface treatment method of EPDM thermal insulation material - Google Patents
Surface treatment method of EPDM thermal insulation material Download PDFInfo
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- CN105585727A CN105585727A CN201410564809.7A CN201410564809A CN105585727A CN 105585727 A CN105585727 A CN 105585727A CN 201410564809 A CN201410564809 A CN 201410564809A CN 105585727 A CN105585727 A CN 105585727A
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Abstract
The invention provides a surface treatment method of an EPDM thermal insulation material. The method comprises the following steps: firstly polishing, cleaning and drying a vulcanized EPDM thermal insulation material, and cooling to 5-50 DEG C; and then uniformly coating or spraying the surface of the EPDM thermal insulation material with a surface treating agent, drying at 60-100 DEG C when a solvent is used and removing the solvent so as to form an isocyanato enriched layer. The above surface treating agent is composed of the following ingredients (by weight): 100 parts of isocyanate, 0-0.2 part of a curing catalyst, 0-10 parts of a plasticizer and 0-2000 parts of a solvent. Dosage of the surface treating agent is controlled according to mole number of isocyanato-NCO on unit projected area of the EPDM thermal insulation material, and the range is 0.1-0.6 mol/m<2>. The invention has the following beneficial effects: weak intensity layer of a near interface propellant can be eliminated, and interfacial bonding strength can be enhanced.
Description
Technical field
The present invention relates to heat-insulating material preconditioning technique field in solid propellant rocket, specifically relate to a kind of EPDM heat-insulating material surface treatment method.
Background technology
The interface bond quality of three kinds of storerooms of propellant/lining/heat insulation layer of solid propellant rocket motor charge directly affects the integrality of engine structure and the reliability of work, interface unsticking easily cause housing overheated, lose strong and cause power failure even to be disintegrated. It is reported have 1st/3rd in the solid propellant rocket of external test failure, because interface unsticking causes, wherein propellant/lining interface unsticking is again topmost failure mode.
Interfaces of solid propellant rocket motor charge is bonding, and to compare traditional bonding pattern more complicated, and in its bonding process, solid propellant and lining form by multicomponent slip curing reaction. In addition, for meeting the requirement of performance separately, in the macromolecule network skeleton of propellant, lining and heat insulation layer, contain the little molecules such as the moisture of bringing in several functions auxiliary agent and preparation process, between matrix network, coexist with combination or free mode, after motor charge, small-molecule substance free in each assembly material will move under the driving of chemical potential, the active component migration of particularly following in propellant and lining solidify reaction process, can cause curing system off-design, even cannot normally solidify, Bearing performance is that bonding interface lost efficacy.
Research shows, in the bonding system of fourth hydroxyl propellant/EPDM heat insulation layer, the formation mechanism of nearly interface propellant weak intensity layer is: curing agent isocyanate molecule is because moving to lining from propellant, and in heat insulation layer moisture etc. containing the little molecule of active hydrogen " pass through " lining to propellant migration and with nearly interface propellant in isocyano generation side reaction, all make curing agent isocyanates in the propellant of nearly interface by excess loss, and then cause the design load of its cure parameter lower than propellant body, fail to reach higher curing cross-linked degree, strength decreased, become weak intensity layer. motor charge, in curing molding process, is worked as interface zone, when the intensity that particularly nearly interface propellant is set up because of curing cross-linked can not be resisted the stress of its cure shrinkage generation, is prone to even unsticking of micro-crack.
Summary of the invention
The problem existing for solving prior art, the invention provides a kind of technique simple, can significantly improve interfaces of solid propellant rocket motor charge adhesive strength, ensure the complete EPDM heat-insulating material surface treatment method of charge constitution.
For realizing technique scheme, EPDM heat-insulating material surface treatment method provided by the present invention, its step comprises:
Step 1, by the EPDM heat-insulating material of sulfidization molding through polishing, clean and dry after, be cooled to 5 ~ 50 DEG C;
Step 2, surface conditioning agent is evenly brushed or is sprayed at EPDM heat-insulating material surface, while using solvent, at 60 ~ 100 DEG C, dry except desolventizing, form isocyano enriched layer, thereby improve solid propellant/lining/heat insulation layer interfacial adhesion.
Further, the composition of above-mentioned surface conditioning agent is made up of following component by weight ratio: isocyanates, 100 parts; Curing catalysts, 0 ~ 0.2 part; Plasticizer, 0 ~ 10 part; Solvent, 0 ~ 2000 part.
Further, the consumption of surface conditioning agent is pressed isocyano-NCO molal quantity control in EPDM heat-insulating material unit projected area, and its scope is 0.1mol/m2~0.6mol/m2。
Compared with prior art, advantage of the present invention comprises:
1. process of surface treatment is simple, easily implements;
2. can eliminate nearly interface propellant weak intensity layer, improve the adhesive strength of interfaces of solid propellant rocket motor charge.
Brief description of the drawings
Fig. 1 is the schematic flow sheet of a kind of EPDM heat-insulating material surface treatment method provided by the present invention.
Detailed description of the invention
Describe below in conjunction with brief description of the drawings use of the present invention. Referring to the accompanying drawing that the embodiment of the present invention is shown, the present invention below will be described in more detail. But the present invention can be with many multi-form realizations, and should not be construed as the restriction of the embodiment being subject in this proposition.
Embodiment 1
In advance dibutyl tin laurate and di-n-octyl sebacate are mixed with to solution by weight 5:95. At room temperature, respectively 100g modification six methine polyisocyanates, 1g dibutyl tin laurate-di-n-octyl sebacate solution, 1000g ethyl acetate are added in mixer, stir, make surface conditioning agent.
The EPDM heat-insulating material test specimen of sulfidization molding, after polishing, cleaning and dry, is cooled to 25 DEG C, and then by above-mentioned surface conditioning agent, by isocyano-NCO, the molal quantity in EPDM heat-insulating material unit projected area is 0.3mol/m2Consumption be evenly painted on EPDM heat-insulating material surface, then be placed at 80 DEG C and dry 1 hour except desolventizing, make fourth hydroxyl propellant/EPDM heat insulation layer powder charge bonding interface test specimen, recording propellant body tensile strength is 979kPa, associating pull-off strength is 941kPa, and the associating pull-off strength of more untreated test specimen has improved 478kPa.
Embodiment 2
At room temperature, respectively 100g modification six methine polyisocyanates, 500g ethyl acetate are added in mixer, stir, make surface conditioning agent.
The EPDM heat-insulating material test specimen of sulfidization molding, after polishing, cleaning and dry, is cooled to 25 DEG C, and then by above-mentioned surface conditioning agent, by isocyano-NCO, the molal quantity in EPDM heat-insulating material unit projected area is 0.5mol/m2Consumption be evenly painted on EPDM heat-insulating material surface, then be placed at 80 DEG C and dry 1 hour except desolventizing, make fourth hydroxyl propellant/EPDM heat insulation layer powder charge bonding interface test specimen, recording propellant body tensile strength is 977kPa, associating pull-off strength is 978kPa, and the associating pull-off strength of more untreated test specimen has improved 471kPa.
Embodiment 3
In advance ferric acetyl acetonade and dibutyl phthalate are mixed with to solution by weight 2:98. At room temperature, respectively 100g IPDI, 2g ferric acetyl acetonade-dibutyl phthalate solution are added in mixer, stir, make surface conditioning agent.
The EPDM heat-insulating material test specimen of sulfidization molding, after polishing, cleaning and dry, is cooled to 25 DEG C, and then by above-mentioned surface conditioning agent, by isocyano-NCO, the molal quantity in EPDM heat-insulating material unit projected area is 0.4mol/m2Consumption be evenly painted on EPDM heat-insulating material surface, make fourth hydroxyl propellant/EPDM heat insulation layer powder charge bonding interface test specimen, recording propellant body tensile strength is 979kPa, and associating pull-off strength is 951kPa, and the associating pull-off strength of more untreated test specimen has improved 488kPa.
Embodiment 4
Using IPDI directly as surface conditioning agent.
The EPDM heat-insulating material test specimen of sulfidization molding, after polishing, cleaning and dry, is cooled to 25 DEG C, and then by above-mentioned surface conditioning agent, by isocyano-NCO, the molal quantity in EPDM heat-insulating material unit projected area is 0.4mol/m2Consumption be evenly painted on EPDM heat-insulating material surface, make fourth hydroxyl propellant/EPDM heat insulation layer powder charge bonding interface test specimen, recording propellant body tensile strength is 945kPa, and associating pull-off strength is 976kPa, and the associating pull-off strength of more untreated test specimen has improved 499kPa.
Embodiment 5
In advance ferric acetyl acetonade and dibutyl phthalate are mixed with to solution by weight 2:98. At room temperature, respectively 100g toluene di-isocyanate(TDI), 2g ferric acetyl acetonade-dibutyl phthalate solution are added in mixer, stir, make surface conditioning agent.
The EPDM heat-insulating material test specimen of sulfidization molding, after polishing, cleaning and dry, is cooled to 25 DEG C, and then by above-mentioned surface conditioning agent, by isocyano-NCO, the molal quantity in EPDM heat-insulating material unit projected area is 0.45mol/m2Consumption be evenly painted on EPDM heat-insulating material surface, make fourth hydroxyl propellant/EPDM heat insulation layer powder charge bonding interface test specimen, recording propellant body tensile strength is 979kPa, and associating pull-off strength is 935kPa, and the associating pull-off strength of more untreated test specimen has improved 472kPa.
Although the present invention discloses as above, the present invention is not defined in this. Any those skilled in the art, without departing from the spirit and scope of the present invention, all can make various changes or modifications, and therefore protection scope of the present invention should be as the criterion with claim limited range.
Claims (8)
1. an EPDM heat-insulating material surface treatment method, is characterized in that, comprising:
Step 1, by the EPDM heat-insulating material of sulfidization molding through polishing, clean and dry after, be cooled to 5 ~ 50 DEG C;
Step 2, surface conditioning agent is evenly brushed or is sprayed at EPDM heat-insulating material surface, while using solvent, at 60 ~ 100 DEG C, dry except desolventizing, form isocyano enriched layer, thereby improve solid propellant/lining/heat insulation layer interfacial adhesion.
2. according to a kind of EPDM heat-insulating material surface treatment method claimed in claim 1, it is characterized in that, the composition of described surface conditioning agent is made up of following component by weight ratio: isocyanates, 100 parts; Curing catalysts, 0 ~ 0.2 part; Plasticizer, 0 ~ 10 part; Solvent, 0 ~ 2000 part.
3. according to a kind of EPDM heat-insulating material surface treatment method claimed in claim 2, it is characterized in that, described isocyanates is modification six methine polyisocyanates, toluene di-isocyanate(TDI), IPDI, 4, one in 4 '-methyl diphenylene diisocyanate, 4,4 '-dicyclohexyl methyl hydride diisocyanate, XDI, Methylcyclohexyl diisocyanate.
4. according to a kind of EPDM heat-insulating material surface treatment method claimed in claim 2, it is characterized in that, described curing catalysts is the one in dibutyl tin laurate, stannous octoate, isooctyl acid zinc, ferric acetyl acetonade, triphenyl bismuth series.
5. according to a kind of EPDM heat-insulating material surface treatment method claimed in claim 2, it is characterized in that, described plasticizer is dibutyl sebacate, the one in repefral, diethyl phthalate, dibutyl phthalate, diisobutyl phthalate, dioctyl phthalate, diisooctyl phthalate, dioctyl adipate, di-n-octyl sebacate.
6. according to a kind of EPDM heat-insulating material surface treatment method claimed in claim 2, it is characterized in that, described solvent is any one in ethyl acetate, acetone, carrene, oxolane, cyclohexane.
7. according to a kind of EPDM heat-insulating material surface treatment method described in claim 1 or 2, it is characterized in that, the consumption of described surface conditioning agent is pressed isocyano-NCO molal quantity control in EPDM heat-insulating material unit projected area, and its scope is 0.1mol/m2~0.6mol/m2。
8. according to any one EPDM heat-insulating material surface treatment method described in claim 2～7, it is characterized in that, the preparation process of described surface conditioning agent is as follows:
Step 1, curing catalysts and plasticizer are mixed with to solution by weight;
Step 2, at room temperature, adds the solution of isocyanates, curing catalysts and plasticizer, solvent in mixer successively by weight ratio, stirs, and makes surface conditioning agent.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410564809.7A CN105585727A (en) | 2014-10-22 | 2014-10-22 | Surface treatment method of EPDM thermal insulation material |
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| CN201410564809.7A CN105585727A (en) | 2014-10-22 | 2014-10-22 | Surface treatment method of EPDM thermal insulation material |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110596301A (en) * | 2019-10-14 | 2019-12-20 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
| CN113122178A (en) * | 2021-04-20 | 2021-07-16 | 上海航天化工应用研究所 | Adhesive and method suitable for interface bonding of glass fiber reinforced plastic heat-insulating material and hydroxyl-terminated propellant |
| CN114371122A (en) * | 2021-12-13 | 2022-04-19 | 湖北三江航天江河化工科技有限公司 | Method for improving interface bonding performance of IPDI (isophorone diisocyanate) type butylated hydroxytoluene propellant and lining |
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| CN103670798A (en) * | 2013-10-17 | 2014-03-26 | 湖北航天化学技术研究所 | Method for improving interface adhesive performance of NEPE propellant and lining |
| CN103694923A (en) * | 2013-12-11 | 2014-04-02 | 湖北航天化学技术研究所 | Method for improving interface adhesive property of HTPB (hydroxyterminated polybutadiene) liner and NEPE (Nitrate Ester Plasticized Polyether) high-energy propellant |
| CN103711609A (en) * | 2013-12-11 | 2014-04-09 | 湖北航天化学技术研究所 | Method for improving interface bonding performance of EPDM (ethylene prophlenediene monomer) heat insulating layer, HTPB (hydroxyl-terminated polybutadiene) lining and NEPE (nitrate ester plasticized polyether propellant) |
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2014
- 2014-10-22 CN CN201410564809.7A patent/CN105585727A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103670798A (en) * | 2013-10-17 | 2014-03-26 | 湖北航天化学技术研究所 | Method for improving interface adhesive performance of NEPE propellant and lining |
| CN103694923A (en) * | 2013-12-11 | 2014-04-02 | 湖北航天化学技术研究所 | Method for improving interface adhesive property of HTPB (hydroxyterminated polybutadiene) liner and NEPE (Nitrate Ester Plasticized Polyether) high-energy propellant |
| CN103711609A (en) * | 2013-12-11 | 2014-04-09 | 湖北航天化学技术研究所 | Method for improving interface bonding performance of EPDM (ethylene prophlenediene monomer) heat insulating layer, HTPB (hydroxyl-terminated polybutadiene) lining and NEPE (nitrate ester plasticized polyether propellant) |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110596301A (en) * | 2019-10-14 | 2019-12-20 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
| CN113122178A (en) * | 2021-04-20 | 2021-07-16 | 上海航天化工应用研究所 | Adhesive and method suitable for interface bonding of glass fiber reinforced plastic heat-insulating material and hydroxyl-terminated propellant |
| CN114371122A (en) * | 2021-12-13 | 2022-04-19 | 湖北三江航天江河化工科技有限公司 | Method for improving interface bonding performance of IPDI (isophorone diisocyanate) type butylated hydroxytoluene propellant and lining |
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