CN110696440B - 基于多孔泡沫的高速飞行器超限热防护柔性蒙皮及其方法 - Google Patents
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Abstract
本发明公开了一种基于多孔泡沫的高速飞行器超限热防护柔性蒙皮及其制备方法,柔性蒙皮从外至内依次包括表层发汗热防护微结构层、中层柔性多孔泡沫层和底层柔性进液衬底层;表层发汗热防护微结构层通过中层柔性多孔泡沫层与底层柔性进液衬底层连通。本发明柔性蒙皮具有全柔性结构,能够用于高速飞行器实现超越柔性材料耐温极限的热防护(超限热防护),使现有高速飞行器实现可变形飞行,同时具有较大流阻,能够克服重力、移动和反转带来发汗的不均匀性问题。
Description
技术领域
本发明属于热防护和柔性电子器件领域,特别涉及一种基于多孔泡沫的高速飞行器超限热防护柔性蒙皮及其方法。
背景技术
现有柔性蒙皮无法实现超高温环境下的应用。其原因在于柔性可延展的高分子基底材料最高耐受温度不超过400摄氏度。高温会导致柔性基底材料的分子链断裂,表面碳化,使基底材料失去延展性,无法实现柔性蒙皮所必须的可拉升延展的技术需求。而现有的发汗冷去技术大多使用金属材料等刚性材料作为基底,无法实现可延展可拉伸的项目需求。
目前,应用于柔性蒙皮和发汗冷却热防护的主要研究有:现有技术1(名称:一种变形飞机的柔性蒙皮,授权公告号CN207389526U,公开日:2018.5.22)公开了橡胶类柔性蒙皮或纤维增强型复合橡胶材料制备的柔性蒙皮,包括柔性弹簧骨架和超弹性硅橡胶薄片,但该蒙皮非全柔性,自由度下降,且无法承受高温,只能在低空低速飞行器上使用。(2)刚性材料基底热防护技术,如现有技术2(名称:基于梯度多孔材料的高超声速飞行器前缘热防护方法,公开号CN108423154A,公开日:2018.8.21)采用耐高温材料制备出具有梯度孔隙率的多孔前缘,注入冷却工质进行热防护,但该技术采用了刚性金属材料基底,无法形变,不可适用于可变体柔性蒙皮。(3)现有技术3(名称:超限热防护与生存状态感知的高速飞行器柔性蒙皮,公开号CN109823508A,公开日:2019.5.31)采用贯通的微孔道,冷却液通过微孔道直接流出到表面渗出孔,整个蒙皮管道的流阻很小,导致冷却液压力很小,且难以人为增加,这使得重力、蒙皮的移动和反转等因素都会对表面冷却液渗出均匀性造成影响,导致各个冷却剂溢出孔的流量不均匀,降低热防护效果。
综上所述,现有的柔性蒙皮只能用于400℃以下的非超高温环境,在超高温环境下如何实现柔性蒙皮柔性材料的存活是其面临的关键问题。而现有的热防护手段都是基于刚性基底材料,无法实现柔性蒙皮可拉伸延展的需求。因此,发明能够在高温等极端环境下具有柔性可延展的蒙皮是实现柔性蒙皮在超高温下应用的关键和瓶颈问题。
发明内容
为解决上述技术问题,本发明提供一种基于多孔泡沫的高速飞行器超限热防护柔性蒙皮,具有全柔性结构,能够用于高速飞行器实现超越柔性材料耐温极限的热防护(超限热防护),使现有高速飞行器实现可变形飞行;同时发汗结构具有较大流阻,降低重力、蒙皮移动和反转等因素的影响,液体冷却剂渗出均匀稳定,提高热防护效果,解决了现有柔性蒙皮因其无法承受超高温只能用于低温环境的问题。
本发明的另一目的是,提供一种基于多孔泡沫的高速飞行器超限热防护柔性蒙皮的制备方法。
本发明所采用的技术方案是,一种基于多孔泡沫的高速飞行器超限热防护柔性蒙皮,从外至内依次包括表层发汗热防护微结构层、中层柔性多孔泡沫层和底层柔性进液衬底层;表层发汗热防护微结构层通过中层柔性多孔泡沫层与底层柔性进液衬底层连通。
进一步的,所述表层发汗热防护微结构层的层内均匀设置有贯通的冷却剂溢出孔,中层柔性多孔泡沫层的上表面与冷却剂溢出孔相通。
进一步的,所述中层柔性多孔泡沫层为内部孔相互交错连通的开孔泡沫,中层柔性多孔泡沫层内部的孔隙率高于表层发汗热防护微结构层,中层柔性多孔泡沫层内部孔直径小于冷却剂溢出孔的直径。
进一步的,所述底层柔性进液衬底层的层内设有贯通的冷却剂进液孔,冷却剂进液孔的直径不小于冷却剂溢出孔的直径,中层柔性多孔泡沫层的下表面与冷却剂进液孔相通。
进一步的,所述冷却剂溢出孔的的孔径为0.1mm-30mm,间距为2.5mm-40mm。
进一步的,所述表层发汗热防护微结构层、中层柔性多孔泡沫层、底层柔性进液衬底层的厚度比为0.5:1:0.5至1:1:1,均采用材质相同的柔性聚合物制得。
进一步的,所述表层发汗热防护微结构层、中层柔性多孔泡沫层和底层柔性进液衬底层采用聚二甲基硅氧烷或Ecoflex硅橡胶。
一种基于多孔泡沫的高速飞行器超限热防护柔性蒙皮的制备方法,具体按照以下步骤进行:
S1,分别制备与表层发汗热防护微结构层、中层柔性多孔泡沫层、底层柔性进液衬底层的结构相对应的糖模;
S2,将中层柔性多孔泡沫层对应的糖模与壳体模具组合,形成糖模组;
S3,向糖模组内浇注已经添加固化剂但尚未固化的聚二甲基硅氧烷或Ecoflex硅橡胶;
S4,真空环境下,18-25℃下固化40-50小时或者40-90℃下固化3-10小时;
S5,40-60℃水浴加热融化糖模,糖模沿相互交错连通的孔流出;
S6,用水和酒精冲洗以去除残留的糖模颗粒和未固化的高分子基团,在50-60℃下烘干,得到中层柔性多孔泡沫层;
S7,将表层发汗热防护微结构层对应的糖模置于中层柔性多孔泡沫层的上表面,糖模与壳体模具组合形成糖模组;重复步骤S3-S5;
S8,将底层柔性进液衬底层对应的糖模置于中层柔性多孔泡沫层的另一表面,糖模与壳体模具组合形成糖模组;重复步骤S3-S5;
S9,用水和酒精冲洗以去除残留的糖模颗粒和未固化的高分子基团,在50-60℃下烘干,得到基于多孔泡沫的高速飞行器超限热防护柔性蒙皮。
进一步的,所述步骤S1中的糖模通过局部加热融化糖颗粒,使糖颗粒按照固定的形状粘合在一起制备而成。
进一步的,所述步骤S1中糖模采用3d打印制成,加工精度为0.016毫米,最小壁厚为0.1mm。
本发明的有益效果是:
本发明在柔性材料中制作微孔道并注入冷却工质以模仿人体皮肤的发汗冷却效应,将外界温度降低到柔性材料耐受的温度范围内实现主动热防护;本发明的柔性蒙皮材质采用包括但不限于聚二甲基硅氧烷、Ecoflex硅橡胶等柔性聚合物材料,具有全柔性结构,延展拉伸效果良好,且能够适应超高温环境。
本发明考虑到流动阻力配置的重要性,提高冷却剂溢出孔的流量均匀性和稳定性;表层发汗热防护微结构层通过中层柔性多孔泡沫层与底层柔性进液衬底层连通,利用多孔结构使得液体冷却剂充满中层柔性多孔泡沫层,增大液体冷却剂进入表层发汗热防护微结构层的流阻,提高冷却剂经表层发汗热防护微结构层渗出的均匀性和稳定性,而且极大降低了重力、蒙皮的移动和反转等因素对表面冷却液渗出均匀性的影响,提高热防护效果;作为柔性材料在超高温情况下超限热防护的基础性关键问题,本发明的柔性蒙皮可广泛应用于高超声速飞行器、可往返航天器、空天飞机和返回式卫星等恶劣热环境中,具有重要的科研意义和应用价值。
附图说明
为了更清楚地说明本发明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发明的一些实施例,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,还可以根据这些附图获得其他的附图。
图1是本发明基于多孔泡沫的高速飞行器超限热防护柔性蒙皮的结构示意图。
图2是本发明的分层结构拆分立体图。
图3是本发明制备方法流程图。
图中,1.表层发汗热防护微结构层,11.冷却剂溢出孔,2.中层柔性多孔泡沫层,3.底层柔性进液衬底层,31.冷却剂进液孔。
具体实施方式
下面将结合本发明实施例中的附图,对本发明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发明一部分实施例,而不是全部的实施例。基于本发明中的实施例,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,都属于本发明保护的范围。
如图1-2所示,基于多孔泡沫的高速飞行器超限热防护柔性蒙皮,包括表层发汗热防护微结构层1、中层柔性多孔泡沫层2、底层柔性进液衬底层3;表层发汗热防护微结构层1的层内均匀设置有贯通状的冷却剂溢出孔11;主要作用是保证柔性蒙皮表面发汗的均匀性,避免蒙皮局部烧毁,保证热防护效果,也可以设置成其他形式;底层柔性进液衬底层3层内有贯通状的冷却剂进液孔31,冷却剂进液孔31的孔径不小于冷却剂溢出孔11的孔径,主要作用是将冷却液送至柔性蒙皮中,数量≥1个。中层柔性多孔泡沫层2的上表面与冷却剂溢出孔11相通,中层柔性多孔泡沫层2的下表面与冷却剂进液孔31相通,中层柔性多孔泡沫层2为内部孔相互交错连通的开孔泡沫。
表层发汗热防护微结构层1、中层柔性多孔泡沫层2、底层柔性进液衬底层3的厚度比为0.5:1:0.5至1:1:1,表层发汗热防护微结构层1、中层柔性多孔泡沫层2和底层柔性进液衬底层3的材质是柔性聚合物,优选的是包括但不限于聚二甲基硅氧烷(PDMS)、Ecoflex硅橡胶等柔性聚合物材料。表层发汗热防护微结构层1、中层柔性多孔泡沫层2和底层柔性进液层3采用相同的PDMS材料,易于铸造,提高各层之间的粘接强度。
冷却剂从冷却剂进液孔31进入后,渗入中层柔性多孔泡沫层2,再经冷却剂溢出孔11均匀渗出,通过控制冷却剂溢出孔11的大小和间距可控制冷却液渗出的均匀度,冷却剂溢出孔11的孔径为0.1mm-30mm,间距范围视极端热环境决定,间距为2.5mm-40mm。
与现有技术3中多级发汗微通道相比,本发明中层柔性多孔泡沫层2具有较大流阻,冷却剂从冷却剂进液孔31进入后,渗入并充满中层柔性多孔泡沫层2后,经冷却剂溢出孔11中均匀渗出。保证了柔性蒙皮表面冷却液渗出的均匀性,而且极大降低了重力、蒙皮的移动和反转等因素对表面冷却液渗出均匀性的影响,提高热防护效果;不需要冷却液泵,只需要一个可以泵出冷却剂的泵,避免冷却液泵的控制误差对表面冷却液渗出均匀性的影响。
在流体力学中,不可压缩粘性流体(例如水)在空间内的水头损失分为沿程损失与结构损失,公式:hw=∑hf+∑hj,其中hw为水头损失,hf为沿程损失,hj为局部损失。本发明中层柔性多孔泡沫层2作用是增大局部损失,使水流重力、供水管道等沿程损失相较于局部损失变为相对小量,降低其对冷却剂溢出均匀性的影响,使得每个冷却剂溢出孔11一致性更好。中层柔性多孔泡沫层2内部孔的直径越小,孔隙率越高,通道曲折交错复杂,局部损失越大,使局部损失远大于沿程损失;因此,中层柔性多孔泡沫层2内部的孔隙率高于表层发汗热防护微结构层1,中层柔性多孔泡沫层2内部孔的直径小于冷却剂溢出孔11的直径。
基于多孔泡沫的高速飞行器超限热防护柔性蒙皮的制备方法,如图3所示,具体按照以下步骤进行:
S1,分别制备与表层发汗热防护微结构层1、中层柔性多孔泡沫层2、底层柔性进液衬底层3的结构相对应的糖模;糖模通过局部加热融化糖颗粒,使糖颗粒按照固定的形状粘合在一起制备而成,糖颗粒直径为x(x=0.001—1mm之一),糖水比例为50:1-100:1,搅拌均匀,压紧,置于80℃的真空干燥箱中,加热6-12个小时;或者采用3d打印技术,加工精度为0.016毫米,最小壁厚为0.1mm;由于糖颗粒的直径可达到0.001mm,小于三维打印最小壁厚0.1mm,采用局部加热融化糖颗粒的方法可以制备出孔直径更小的中层柔性多孔泡沫层2。
S2,将中层柔性多孔泡沫层2对应的糖模与壳体模具组合,形成糖模组;
S3,向糖模组内浇注已经添加固化剂但尚未固化的聚二甲基硅氧烷或Ecoflex硅橡胶;
S4,真空环境下,18-25℃下固化40-50小时或者40-90℃下固化3-10小时;
S5,40-60℃水浴加热融化糖模,糖模沿中层柔性多孔泡沫层2内部的孔流出;
S6,用水和酒精冲洗以去除残留的糖模颗粒和未固化的高分子基团,在50-60℃下烘干,得到最终的中层柔性多孔泡沫层2;
S7,将表层发汗热防护微结构层1对应的糖模置于中层柔性多孔泡沫层2的上表面,糖模与壳体模具组合形成糖模组;重复步骤S3-S5;
S8,将底层柔性进液衬底层3对应的糖模置于中层柔性多孔泡沫层2的另一表面,糖模与壳体模具组合形成糖模组;重复步骤S3-S5;
S9,用水和酒精冲洗以去除残留的糖模颗粒和未固化的高分子基团,在50-60℃下烘干,得到基于多孔泡沫的高速飞行器超限热防护柔性蒙皮。
本发明有望进一步推动柔性蒙皮在超高温环境下应用的的快速发展。本发明柔性仿生皮肤结构使得柔性蒙皮在超高温环境下的应用成为可能,将进一步促进新型柔性蒙皮的研究和发展。因此,作为柔性蒙皮在超高温环境的基础性关键问题,本发明可广泛应用于高超声速飞行器蒙皮、可往返航天器、空天飞机和返回式卫星外表面中,具有重要的科研意义和应用价值。
以上所述仅为本发明的较佳实施例而已,并非用于限定本发明的保护范围。凡在本发明的精神和原则之内所作的任何修改、等同替换、改进等,均包含在本发明的保护范围内。
Claims (6)
1.一种基于多孔泡沫的高速飞行器超限热防护柔性蒙皮,其特征在于,从外至内依次包括表层发汗热防护微结构层(1)、中层柔性多孔泡沫层(2)和底层柔性进液衬底层(3);表层发汗热防护微结构层(1)通过中层柔性多孔泡沫层(2)与底层柔性进液衬底层(3)连通;
所述表层发汗热防护微结构层(1)的层内均匀设置有贯通的冷却剂溢出孔(11),中层柔性多孔泡沫层(2)的上表面与冷却剂溢出孔(11)相通;
所述中层柔性多孔泡沫层(2)为内部孔相互交错连通的开孔泡沫,中层柔性多孔泡沫层(2)内部的孔隙率高于表层发汗热防护微结构层(1),中层柔性多孔泡沫层(2)内部孔直径小于冷却剂溢出孔(11)的直径;
所述冷却剂溢出孔(11)的孔径为0.1mm-30mm,间距为2.5mm-40mm;
所述表层发汗热防护微结构层(1)、中层柔性多孔泡沫层(2)和底层柔性进液衬底层(3)采用聚二甲基硅氧烷或Ecoflex硅橡胶。
2.根据权利要求1所述的一种基于多孔泡沫的高速飞行器超限热防护柔性蒙皮,其特征在于,所述底层柔性进液衬底层(3)的层内设有贯通的冷却剂进液孔(31),冷却剂进液孔(31)的直径不小于冷却剂溢出孔(11)的直径,中层柔性多孔泡沫层(2)的下表面与冷却剂进液孔(31)相通。
3.根据权利要求1或2所述的一种基于多孔泡沫的高速飞行器超限热防护柔性蒙皮,其特征在于,所述表层发汗热防护微结构层(1)、中层柔性多孔泡沫层(2)和底层柔性进液衬底层(3)均采用材质相同的柔性聚合物制得,表层发汗热防护微结构层(1)、中层柔性多孔泡沫层(2)、底层柔性进液衬底层(3)的厚度比为0.5:1:0.5至1:1:1。
4.一种如权利要求1或2所述基于多孔泡沫的高速飞行器超限热防护柔性蒙皮的制备方法,其特征在于,具体按照以下步骤进行:
S1,分别制备与表层发汗热防护微结构层(1)、中层柔性多孔泡沫层(2)、底层柔性进液衬底层(3)的结构相对应的糖模;
S2,将中层柔性多孔泡沫层(2)对应的糖模与壳体模具组合,形成糖模组;
S3,向糖模组内浇注已经添加固化剂但尚未固化的聚二甲基硅氧烷或Ecoflex硅橡胶;
S4,真空环境下,18-25℃下固化40-50小时或者40-90℃下固化3-10小时;
S5,40-60℃水浴加热融化糖模,糖模沿相互交错连通的孔流出;
S6,用水和酒精冲洗以去除残留的糖模颗粒和未固化的高分子基团,在50-60℃下烘干,得到中层柔性多孔泡沫层(2);
S7,将表层发汗热防护微结构层(1)对应的糖模置于中层柔性多孔泡沫层(2)的上表面,糖模与壳体模具组合形成糖模组;重复步骤S3- S5;
S8,将底层柔性进液衬底层(3)对应的糖模置于中层柔性多孔泡沫层(2)的另一表面,糖模与壳体模具组合形成糖模组;重复步骤S3- S5;
S9,用水和酒精冲洗以去除残留的糖模颗粒和未固化的高分子基团,在50-60℃下烘干,得到基于多孔泡沫的高速飞行器超限热防护柔性蒙皮。
5.根据权利要求4所述的一种基于多孔泡沫的高速飞行器超限热防护柔性蒙皮的制备方法,其特征在于,所述步骤S1中的糖模通过局部加热融化糖颗粒,使糖颗粒按照固定的形状粘合在一起制备而成。
6.根据权利要求4所述的一种基于多孔泡沫的高速飞行器超限热防护柔性蒙皮的制备方法,其特征在于,所述步骤S1中糖模采用3d打印制成,加工精度为0.016毫米,最小壁厚为0.1mm。
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