CN110484151A - 微沟槽减阻柔性薄膜及其制备方法 - Google Patents
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Abstract
本发明涉及一种微沟槽减阻柔性薄膜及制备方法,属于流体力学流动控制技术领域。微沟槽薄膜上表面加工有沿气流流动方向的三角形沟槽结构单元,下表面附有胶层,便于快速粘贴于飞行器表面。飞行器表面覆盖微沟槽薄膜后,在飞行器高速飞行时,可限制飞行器表面边界层底层空气的展向运动,改善飞行器近壁面的流场特性,有效降低壁面的摩擦阻力。微沟槽柔性薄膜的制备是通过滚轴热压成型的方法实现,在双滚轴热压机的模具轴表面加工出三角形沟槽结构,预处理热塑性聚氨酯(TPU)聚合物薄膜后,在TPU薄膜表面热压出微沟槽结构。本发明可用于解决飞行器飞行时受空气阻力影响较大的问题,具有工艺设备简单、经济实用、易于制造的优点。
Description
技术领域
本发明涉及一种微沟槽减阻柔性薄膜及其制备方法,属于流体力学流动控制技术。
背景技术
自然界中鲨鱼表皮的微小凸起遁甲结构,能有效降低鲨鱼在水中游动的阻力,受到大自然的启发,研究发现在物体表面合理设置一定尺度的沟槽结构,可有效减小物体表面的摩擦阻力。飞行器在空气中高速飞行,需要克服极大的空气阻力,飞行器所受阻力主要由表面摩擦阻力和压差阻力构成,其中摩擦阻力占较大部分,航空工业的发展和能源短缺及环境污染问题,对降低飞机的阻力研究变得尤为迫切。因此,减小飞行器在行进过程中与空气的摩擦阻力,有助于提高飞行器的航速和航程,还可有效节约能源消耗,降低碳排放。目前研究学者已对物体表面覆盖沟槽结构进行减阻的效果和机理进行了数值仿真和实验研究,美国3M公司曾研发一款沟槽贴膜,为研究机构提供不同规格的减阻贴膜,用于测试实验研究;欧洲空客公司在A320试验机上进行了沟槽结构的整机试飞验证,结果表明沟槽贴膜可节油1%~2%。
发明内容
本发明的目的是提供一种微沟槽减阻柔性薄膜及制备方法,可以高效率、大面积成型具有一定减阻效果的柔性薄膜。
本发明中微沟槽减阻柔性薄膜由上表面带有三角形微沟槽结构的TPU(热塑性聚氨酯)聚合物层、中间胶层和底层防粘纸组成。三角形沟槽结构在TPU聚合物层沿空气流动方向等间距均匀分布,沿流向以正弦函数型分布。
本发明微沟槽薄膜的制备方法包括以下步骤,首先根据飞行器的实际工况计算出微沟槽结构的实际尺寸;根据微沟槽结构的实际尺寸,使用高精度机床系统加工出表面有“V”型沟槽结构的空心铝制模具滚轴,并清洗后安装于双滚轮热压机上;预处理待加工的TPU聚合物薄膜;设置双滚轴热压机的工艺参数,在TPU聚合物薄膜表面热压出微沟槽结构。具体的技术方案如下:
一、确定微沟槽结构实际尺寸。根据飞行器实际工况,以沟槽高度h针对湍流摩擦速度uτ的无量纲数h+(υ为空气运动粘度)在12-15之间,确定沟槽结构的实际尺寸。以30m/s的来流速度为例,特征长度1m处,沟槽峰-峰间宽度s为0.2mm,微沟槽峰-谷间深度h为0.17mm,三角形沟槽的顶角α为60°,沟槽结构沿流向正弦函数分布的振幅为1mm,正弦函数的波长为20mm。
二、制造用于热压微沟槽结构的模具滚轴。根据微沟槽结构的实际尺寸,使用高精度机床加工制作用于热压TPU聚合物薄膜的微沟槽模具滚轴,使用无水乙醇清洗,烘干后涂覆脱模剂,并将加热棒穿过滚轴中心后安装于双滚轴热压机上。
三、预处理TPU聚合物薄膜。沟槽高度为0.2mm,裁剪厚度0.5mm的TPU薄膜以适合双滚轴热压机的入料尺寸,使用无水乙醇清洗表面去除污渍,晾干后均匀涂覆防粘剂。
四、在TPU聚合物薄膜表面热压成型微沟槽结构。设置双滚轮热压机的工作参数,模具滚轴温度设置为90~92℃,滚轴速度调为最低档3r/min,从入料口放入TPU聚合物薄膜,模具滚轴与TPU聚合物薄膜接触压力设定为83~85N,待模具滚轴达到设定温度后,开启滚轴转动,在TPU聚合物薄膜上热压出沟槽结构。
本发明微沟槽减阻柔性薄膜及其制备方法,制作沿流向曲形分布微沟槽结构薄膜,粘贴于飞行器表面后,可改善飞行器近壁面区域流场特性,限制边界层底层的空气的展向运动,降低飞行器在行进中的表面摩擦阻力,具有工艺设备简单、经济实用、易于制造的优点,适合于大规模生产,有良好的工程应用前景。
附图说明
为了更清楚地说明本申请实施例或现有技术中的技术方案,下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍,显而易见地,下面描述中的附图仅仅是本申请的实施例,对于本领域普通技术人员来讲,在不付出创造性劳动的前提下,还可以根据提供的附图获得其他的附图。
图1为微沟槽减阻柔性薄膜的组成示意图,其中1为TPU聚合物薄膜表层,2为胶层,3为防粘底纸。
图2为微沟槽减阻柔性薄膜表层三角形沟槽结构的示意图。
图3为双滚轴热压机用模具滚轴的结构示意图。
图4为双滚轴热压机工作示意图,4为模具滚轴,5为模具滚轴加热管,6为橡胶底轴,7为TPU聚合物薄膜。
具体实施方式
下面将结合本申请实施例中的附图,对本申请实施例中的技术方案进行清楚、完整地描述,显然,所描述的实施例仅仅是本申请一部分实施例,而不是全部的实施例。基于本申请中的实施例,本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例,都属于本申请保护的范围。
一、微沟槽减阻柔性薄膜由TPU聚合物薄膜表层、胶层和防粘底纸三部分组成,如图1所示,其中,TPU聚合物薄膜表层沿流向方向等间距均匀分布有三角形沟槽结构,根据飞行器实际工况,以30m/s的来流速度,特征长度取1m为例,确定微沟槽结构的实际尺寸。使沟槽高度h针对湍流摩擦速度uτ的无量纲数h+(υ为空气运动粘度)在12-15之间,则沟槽峰-峰间宽度s为0.2mm,微沟槽峰-谷间深度h为0.17mm,三角形沟槽的顶角α为60°,沟槽结构沿流向正弦函数分布的振幅为1mm,正弦函数的波长为20mm,如图2所示。
二、根据步骤一得到的微沟槽结构的实际尺寸,使用高精度机床加工制作用于热压TPU聚合物薄膜的微沟槽模具滚轴,使用无水乙醇清洗烘干,后涂覆脱模剂,并将加热棒穿过滚轴中心后安装于双滚轴热压机上,如图3所示。
三、沟槽高度确定为0.2mm,选择厚度为0.5mm的TPU薄膜裁剪以适合双滚轴热压机的入料尺寸,使用无水乙醇清洗表面去除污渍,晾干后均匀涂覆防粘剂。
四、设置双滚轮热压机的工作参数,模具滚轴温度设置为90~92℃,滚轴速度调为最低档3r/min,从入料口放入TPU聚合物薄膜,模具滚轴与TPU聚合物薄膜接触压力设定为83~85N,待模具滚轴达到设定温度后,开启滚轴转动,TPU聚合物薄膜进入滚轮热压区,在表面热压出微沟槽结构。
按照上述方法制备出的微沟槽减阻柔性薄膜,在风洞实验中,在30m/s的实验条件下,可实现8%以上的局部减阻效果。可根据飞行器的实际飞行工况,粘贴于飞行器表面,在不改变飞行器外形特征的前提下,三角形微沟槽结构可限制近壁面区域的空气展向运动,有效降低壁面摩擦力,改善飞行器飞行性能,达到减小整体飞行阻力、增加飞行器航程、降低排放的目的。
以上对本发明所提供的技术方案进行了详细介绍。本文中应用了具体个例对本发明的原理及实施方式进行了阐述,以上实施例的说明只是用于帮助理解本发明的方法及其核心思想。应当指出,对于本技术领域的普通技术人员来说,在不脱离本发明原理的前提下,还可以对本发明进行若干改进和修饰,这些改进和修饰也落入本发明权利要求的保护范围内。
Claims (4)
1.一种微沟槽减阻柔性薄膜,其特征在于,由表面带有三角形微沟槽结构的TPU聚合物层、中间胶层和底层防粘纸组成,所述的三角形微沟槽结构是在TPU聚合物层沿空气流动方向等间距均匀分布的三角形微结构,沿流向以正弦函数型分布,制备方法包括如下步骤:
一、根据飞行器实际工况,以微沟槽高度的无量纲数在12~15之间,计算出微沟槽结构的实际尺寸;
二、根据微沟槽结构的实际尺寸,使用高精度机床系统加工出表面具有V型沟槽结构的空心铝制模具滚轴,用于热压TPU聚合物薄膜;使用无水乙醇清洗步骤二中加工得到的模具滚轴,烘干后涂覆脱模剂,并将模具滚轴安装于双滚轮热压机上;
三、处理待加工的TPU聚合物薄膜,裁剪以适合双滚轮热压机滚轴尺寸,使用无水乙醇清洗表面,晾干后均匀涂上防粘剂;
四、在TPU聚合物薄膜表面热压出微沟槽结构,设置双滚轴热压机的工艺参数,包括模具轴温度、滚轴速度、滚轴压力,待模具滚轴达到设定温度后,开启滚轴转动,放入TPU聚合物薄膜,从而获得表面带有三角形微沟槽结构的TPU聚合物层。
2.根据权利要求1所述的微沟槽减阻柔性薄膜,其特征在于,所述的三角形微沟槽结构为:微沟槽的峰-峰间宽度s为0.1mm~0.8mm,微沟槽峰-谷间深度h为0.1mm-0.8mm,三角形沟槽的顶角α为60°,沟槽结构沿流向正弦函数分布的振幅为1mm,正弦函数的波长为20mm。
3.根据权利要求1所述的微沟槽减阻柔性薄膜,其特征在于,所述的TPU聚合物薄膜厚度为0.3mm~1mm。
4.根据权利要求1所述的微沟槽减阻柔性薄膜,其特征在于,所述的双滚轴热压机其模具轴温度为90~92℃的条件下,模具滚轴与TPU聚合物薄膜接触后压力设定为83~85N。
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US17/633,174 US20220315806A1 (en) | 2019-08-29 | 2020-08-18 | Micro-groove drag reduction flexible film and preparation method thereof |
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CN111737836A (zh) * | 2020-06-30 | 2020-10-02 | 扬州大学 | 一种动静腔流动微沟槽-超疏水耦合减阻设计方法 |
WO2021036858A1 (zh) * | 2019-08-29 | 2021-03-04 | 浙江大学 | 微沟槽减阻柔性薄膜及其制备方法 |
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US9352533B2 (en) * | 2009-01-29 | 2016-05-31 | The Boeing Company | Elastomeric riblets |
US8684310B2 (en) * | 2009-01-29 | 2014-04-01 | The Boeing Company | Rigid tipped riblets |
CN101758864B (zh) * | 2010-01-14 | 2011-11-09 | 浙江大学 | 具有气动减阻效应的仿生非光滑表面贴膜 |
US20110186685A1 (en) * | 2010-02-02 | 2011-08-04 | The Boeing Company | Thin-Film Composite Having Drag-Reducing Riblets and Method of Making the Same |
CN102673052B (zh) * | 2012-05-28 | 2014-10-15 | 哈尔滨工业大学 | 飞艇蒙皮用Al层涂覆型TPU薄膜减阻微沟槽的热压印制备方法 |
CN110484151A (zh) * | 2019-08-29 | 2019-11-22 | 浙江大学 | 微沟槽减阻柔性薄膜及其制备方法 |
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CN102672959A (zh) * | 2012-05-28 | 2012-09-19 | 哈尔滨工业大学 | 飞艇蒙皮用tpu薄膜减阻微沟槽的热压印制备方法 |
CN102689459A (zh) * | 2012-06-01 | 2012-09-26 | 清华大学 | 一种减阻降噪沟槽贴膜及其制备方法 |
CN109795673A (zh) * | 2019-01-24 | 2019-05-24 | 深圳大学 | 一种无人机旋翼表面微结构减阻膜及其制造方法 |
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WO2021036858A1 (zh) * | 2019-08-29 | 2021-03-04 | 浙江大学 | 微沟槽减阻柔性薄膜及其制备方法 |
CN111737836A (zh) * | 2020-06-30 | 2020-10-02 | 扬州大学 | 一种动静腔流动微沟槽-超疏水耦合减阻设计方法 |
CN111737836B (zh) * | 2020-06-30 | 2021-06-22 | 扬州大学 | 一种动静腔流动微沟槽-超疏水耦合减阻设计方法 |
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