CN103865259A - 一种航空航天用增强增韧尼龙扎带及其制备方法 - Google Patents
一种航空航天用增强增韧尼龙扎带及其制备方法 Download PDFInfo
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Abstract
本发明公开了一种航空航天用增强增韧尼龙扎带,其原料按重量份包括:PA66 43-47份,PA6 13-17份,玻璃纤维28-32份,增韧剂8-12份,马来酸酐0.4-0.5份,过氧化二异丙苯0.07-0.1份,抗氧剂0.1-0.3份,阻交联剂1-1.5份,润滑剂1.5-2份,偶联剂KH-570 0.13-0.17份。本发明还公开了一种航空航天用增强增韧尼龙扎带的制备方法。本发明中,上述航空航天用增强增韧尼龙扎带冲击强度高,韧性、刚性好,耐热性能优异。
Description
技术领域
本发明涉及尼龙扎带技术领域,尤其涉及一种航空航天用增强增韧尼龙扎带及其制备方法。
背景技术
尼龙66疲劳强度和钢性较高,耐热性较好,摩擦系数低,耐磨性好,尼龙66主要用于汽车、机械工业、电子电器、精密仪器等领域。大约有88%的尼龙66通过注射成型加工成各种制件,约12%的尼龙66则通过挤出、吹塑等成型加工成相应的制品。在上世纪70-80年代,我国大面积工业生产和社会日常使用涉及到的绑扎用途需求都采用诸如麻绳、棉线及草绳等等就地取材的生产产出辅料手工或机器制成,效率极低,应用领域极窄,劳动操作强度较大。随后,由于沿海省份和地区加强外贸互动交流,尼龙扎带作为一种新奇的塑料制品渐然渗入国内,在得到实际的常规化应用后,继而在航空航天、园林工艺、农业生产、建筑施工、广告施工等相关设计到固定器物、绑扎紧固的场所,尼龙扎带作为最具代表性的首选替代产品逐步的淘汰掉了传统绑扎绳索的应用。尼龙66具有干态和低温冲击强度低、吸水后易变形,其饱和水可达到3%以上,缺口冲击强度低,在一定程度影响制件的尺寸稳定性,使其使用受到了一定的限制,因此需要对其进行改性,如何制备一种冲击强度高,韧性、刚性好,耐热性能优异的尼龙扎带成为目前需要解决的技术问题。
发明内容
本发明提出了一种航空航天用增强增韧尼龙扎带及其制备方法,所述航空航天用增强增韧尼龙扎带的冲击强度高,韧性、刚性好,耐热性能优异。
本发明提出的一种航空航天用增强增韧尼龙扎带,其原料按重量份包括:
在具体实施方式中,上述PA66的重量份可以为43、44、46、46.3、46.5、46.8、47份,PA6的重量份可以为13、14、14.2、14.4、14.9、15、16、17份,GF的重量份可以为28、29、29.5、29.6、30、31.3、32份,增韧剂的重量份可以为8、8.4、8.9、9.5、10、11、12份,MAH的重量份可以为0.3、0.35、0.4、0.42、0.44、0.45、0.47、0.5份,DCP的重量份可以为0.07、0.08、0.085、0.09、0.1份,抗氧剂的重量份可以为0.1、0.15、0.16、0.18、0.2、0.25、0.28、0.3份,阻交联剂的重量份可以为1、1.1、1.2、1.23、1.3、1.35、1.4、1.5份,偶联剂KH-570的重量份可以为0.13、0.15、0.16、0.17份。
优选地,所述增韧剂为聚乙烯PE、线型低密度聚乙烯LLDPE、三元乙丙橡胶EPDM或乙烯-辛烯共聚物POE。
优选地,所述增韧剂为PE。
优选地,所述GF在原料中的重量百分比为30%。
优选地,所述抗氧剂为抗氧剂1098和/或抗氧剂168。
优选地,所述抗氧剂1098与抗氧剂168的重量比为1:1。
优选地,所述阻交联剂为二甲基甲酰胺、二甲基乙酰胺、己内酰胺、二甲亚砜一种或多种组成。
优选地,上述航空航天用增强增韧尼龙扎带的原料按重量份包括:
本发明还公开了一种航空航天用增强增韧尼龙扎带的制备方法,包括如下步骤:
S1、首先按配比称取增韧剂、阻交联剂放入开炼机中,然后按配比加入MAH、DCP及抗氧剂进行混炼,成片,粉碎得到接枝物;
S2、按配比称取PA66、PA6及S1得到的接枝物置于同向双螺杆挤出机中,然后向其中加入GF、偶联剂KH-570分散共混均匀得到共混物,其中螺杆转速为38-43rpm,挤出温度为230-270℃;
S3、将S2得到的共混物进行造粒,干燥,注塑成型得到航空航天用增强增韧尼龙扎带,其中注塑温度为255-280℃,注射压力为80-90MPa。
优选地,在S2中,螺杆转速为39-42rpm,挤出温度为250-255℃;在S3中,注塑温度为255、265或280℃,注射压力为85-88MPa。
本发明中,尼龙66与增韧剂配合使用,并使用MAH接枝来改进两者的相容性,通过合理控制三者配比,并添加适量的抗氧剂,尼龙66与增韧剂的相容性好,且增韧效果显著,热变形温度较高,耐热性能优异,尼龙扎带的拉伸强度及弯曲强度也显著增强,使用PE作为增韧剂并与MAH进行接枝改性,制备的接枝物可明显增强上述尼龙扎带的韧性及刚性,缺口冲击强度大大增强,通过使用GF作为填充剂,可显著增强上述尼龙扎带的拉伸强度、弯曲强度,力学性能大幅度提高,配合使用偶联剂KH-570可增强尼龙66与GF的界面结合度,提高GF的使用效果;本发明中,上述航空航天用增强增韧尼龙扎带冲击强度高,韧性、刚性好,耐热性能优异。
附图说明
图1为本发明提出的一种航空航天用增强增韧尼龙扎带的制备工艺流程图。具体实施方式
如图1所示,图1为本发明提出的一种航空航天用增强增韧尼龙扎带的制备工艺流程图。
本发明提出的一种航空航天用增强增韧尼龙扎带,其原料按重量份包括:
参照图1,上述航空航天用增强增韧尼龙扎带的制备方法,包括如下步骤:
S1、首先按配比称取增韧剂、阻交联剂放入开炼机中,然后按配比加入MAH、DCP及抗氧剂进行混炼,成片,粉碎得到接枝物;
S2、按配比称取PA66、PA6及S1得到的接枝物置于同向双螺杆挤出机中,然后向其中加入GF、偶联剂KH-570分散共混均匀得到共混物,其中螺杆转速为38-43rpm,挤出温度为230-270℃;
S3、将S2得到的共混物进行造粒,干燥,注塑成型得到航空航天用增强增韧尼龙扎带,其中注塑温度为255-280℃,注射压力为80-90MPa。
实施例1
一种航空航天用增强增韧尼龙扎带,其原料按重量份包括:
本实施例中,上述航空航天用增强增韧尼龙扎带的制备方法包括如下步骤:
S1、首先按配比称取PE、二甲亚砜放入开炼机中,然后按配比加入MAH、DCP及抗氧剂1098进行混炼,成片,粉碎得到接枝物;
S2、按配比称取PA66、PA6及S1得到的接枝物置于同向双螺杆挤出机中,然后向其中加入GF、偶联剂KH-570分散共混均匀得到共混物,其中螺杆转速为38rpm,挤出温度为260℃;
S3、将S2得到的共混物进行造粒,干燥,注塑成型得到航空航天用增强增韧尼龙扎带,其中注塑温度为255℃,注射压力为80MPa。
实施例2
一种航空航天用增强增韧尼龙扎带,其原料按重量份包括:
本实施例中,上述航空航天用增强增韧尼龙扎带的制备方法包括如下步骤:
S1、首先按配比称取POE、二甲基乙酰胺放入开炼机中,然后按配比加入MAH、DCP及抗氧剂168进行混炼,成片,粉碎得到接枝物;
S2、按配比称取PA66、PA6及S1得到的接枝物置于同向双螺杆挤出机中,然后向其中加入GF、偶联剂KH-570分散共混均匀得到共混物,其中螺杆转速为43rpm,挤出温度为270℃;
S3、将S2得到的共混物进行造粒,干燥,注塑成型得到航空航天用增强增韧尼龙扎带,其中注塑温度为265℃,注射压力为85MPa。
实施例3
一种航空航天用增强增韧尼龙扎带,其原料按重量份包括:
本实施例中,上述航空航天用增强增韧尼龙扎带的制备方法包括如下步骤:
S1、首先按配比称取EPDM、二甲基甲酰胺放入开炼机中,然后按配比加入MAH、DCP及抗氧剂1098进行混炼,成片,粉碎得到接枝物;
S2、按配比称取PA66、PA6及S1得到的接枝物置于同向双螺杆挤出机中,然后向其中加入GF、偶联剂KH-570分散共混均匀得到共混物,其中螺杆转速为40rpm,挤出温度为250℃;
S3、将S2得到的共混物进行造粒,干燥,注塑成型得到航空航天用增强增韧尼龙扎带,其中注塑温度为280℃,注射压力为90MPa。
实施例4
一种航空航天用增强增韧尼龙扎带,其原料按重量份包括:
本实施例中,上述航空航天用增强增韧尼龙扎带的制备方法包括如下步骤:
S1、首先按配比称取LLDPE、己内酰胺放入开炼机中,然后按配比加入MAH、DCP及抗氧剂1098进行混炼,成片,粉碎得到接枝物;
S2、按配比称取PA66、PA6及S1得到的接枝物置于同向双螺杆挤出机中,然后向其中加入GF、偶联剂KH-570分散共混均匀得到共混物,其中螺杆转速为42rpm,挤出温度为240℃;
S3、将S2得到的共混物进行造粒,干燥,注塑成型得到航空航天用增强增韧尼龙扎带,其中注塑温度为265℃,注射压力为86MPa。
实施例5
一种航空航天用增强增韧尼龙扎带,其原料按重量份包括:
本实施例中,上述航空航天用增强增韧尼龙扎带的制备方法包括如下步骤:
S1、首先按配比称取PE、二甲亚砜放入开炼机中,然后按配比加入MAH、DCP及抗氧剂1098与抗氧剂168进行混炼,成片,粉碎得到接枝物;
S2、按配比称取PA66、PA6及S1得到的接枝物置于同向双螺杆挤出机中,然后向其中加入GF、偶联剂KH-570分散共混均匀得到共混物,其中螺杆转速为40rpm,挤出温度为255℃;
S3、将S2得到的共混物进行造粒,干燥,注塑成型得到航空航天用增强增韧尼龙扎带,其中注塑温度为265℃,注射压力为87MPa。
在实施例1-5中,尼龙66与增韧剂配合使用,并使用MAH接枝来改进两者的相容性,通过合理控制三者配比,并添加适量的抗氧剂,尼龙66与增韧剂的相容性好,且增韧效果显著,热变形温度较高,耐热性能优异,尼龙扎带的拉伸强度及弯曲强度也显著增强,使用PE作为增韧剂并与MAH进行接枝改性,制备的接枝物可明显增强上述尼龙扎带的韧性及刚性,缺口冲击强度大大增强,通过使用GF作为填充剂,可显著增强上述尼龙扎带的拉伸强度、弯曲强度,力学性能大幅度提高,配合使用偶联剂KH-570可增强尼龙66与GF的界面结合度,提高GF的使用效果。
本发明中,上述航空航天用增强增韧尼龙扎带冲击强度高,韧性、刚性好,耐热性能优异。
以上所述,仅为本发明较佳的具体实施方式,但本发明的保护范围并不局限于此,任何熟悉本技术领域的技术人员在本发明揭露的技术范围内,根据本发明的技术方案及其发明构思加以等同替换或改变,都应涵盖在本发明的保护范围之内。
Claims (10)
2.根据权利要求1所述的航空航天用增强增韧尼龙扎带,其特征在于,所述增韧剂为聚乙烯PE、线型低密度聚乙烯LLDPE、三元乙丙橡胶EPDM或者乙烯-辛烯共聚物POE。
3.根据权利要求2所述的航空航天用增强增韧尼龙扎带,其特征在于,所述增韧剂为PE。
4.根据权利要求3所述的航空航天用增强增韧尼龙扎带,其特征在于,所述GF在原料中的重量百分比为30%。
5.根据权利要求1所述的航空航天用增强增韧尼龙扎带,其特征在于,所述抗氧剂为抗氧剂1098和/或抗氧剂168。
6.根据权利要求5所述的航空航天用增强增韧尼龙扎带,其特征在于,所述抗氧剂1098与抗氧剂168的重量比为1:1。
7.根据权利要求1所述的航空航天用增强增韧尼龙扎带,其特征在于,所述阻交联剂为二甲基甲酰胺、二甲基乙酰胺、己内酰胺、二甲亚砜一种或多种组成。
9.一种根据权利要求1-8中任一项所述的航空航天用增强增韧尼龙扎带的制备方法,其特征在于,包括如下步骤:
S1、首先按配比称取增韧剂、阻交联剂放入开炼机中,然后按配比加入MAH、DCP及抗氧剂进行混炼,成片,粉碎得到接枝物;
S2、按配比称取PA66、PA6及S1得到的接枝物置于同向双螺杆挤出机中,然后向其中加入GF、偶联剂KH-570分散共混均匀得到共混物,其中螺杆转速为38-43rpm,挤出温度为230-270℃;
S3、将S2得到的共混物进行造粒,干燥,注塑成型得到航空航天用增强增韧尼龙扎带,其中注塑温度为255-280℃,注射压力为80-90MPa。
10.根据权利要求9所述的的航空航天用增强增韧尼龙扎带的制备方法,其特征在于,在S2中,螺杆转速为39-42rpm,挤出温度为250-255℃;在S3中,注塑温度为255、265或280℃,注射压力为85-88MPa。
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