CN114455099A - 一种用于航天器的空间碎片防护结构及其制备方法 - Google Patents
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Abstract
本发明公开一种用于航天器的空间碎片防护结构及其制备方法,所述空间碎片防护结构包含防护层结构,所述防护层结构包含至少三组结合固定的防护层组合,所述防护层组合包含缓冲层以及位于缓冲层外侧的防护层,所述缓冲层包含收纳状态和展开状态。本发明提供的空间碎片防护结构可提高对空间碎片的防御能力,与传统的玄武岩‑聚氨酯泡沫复合防护结构相比,其防护性能提升10%~15%,并且兼具重量轻、体积小、服役周期长、隔防热效果好的特点,与同等防护效能的三层whipple结构相比减重25%~30%,体积减少60%~70%,可在轨空间服役5年。
Description
技术领域
本发明属于航天技术领域。尤其涉及一种用于航天器的空间碎片防护结构及其制备方法。
背景技术
空间碎片,又称空间垃圾,主要是指人类在航天活动过程中遗留在空间的废弃的航天器残骸和因爆炸或碰撞而产生的碎片。随着人类空间活动的日益频繁,空间碎片环境日趋恶化。据美国空间监视网估计,目前在轨的空间碎片中尺寸大于l0 cm的约有2~2.2万个,尺寸大于1cm的约有50万个,尺寸大于1mm的大于1亿个。空间碎片的重量约6300吨,其中约2700吨分布在低地轨道。未来50年,碎片数量将以每年10%的速度递增。
对于载人航天器,飞行时间长,体积较大,遭遇空间碎片撞击的风险最高。若空间碎片击穿密封舱舱壁,将导致密封舱气体泄漏,严重威胁航天器及航天员的生命安全。而在航天器外增加防护结构是目前普遍采用的方法,通常是在航天器易损和关键部位加装防护屏,传统的Whipple防护结构及其改进结构从上世纪60年代至今依然是防护的主要方式。但是,随着空间站、卫星等航天器种类及功能日益复杂化,现有笨重的Whipple防护结构已不能满足功能的需求。在约束防护结构的体积、质量的运载技术条件下,提升空间碎片防护结构的性能,一直是空间碎片防护领域的核心工作。同时空间站、卫星在轨期间,结构系统同时有承载、隔防热的基本功能需求,而长期以来力学承载、隔防热、碎片防护这三部分均为独立设计,造成了空间站发射重量和体积上的浪费。
因此亟须研发一种兼具承载、隔防热、空间碎片防护性能的航天器一体化结构,以适应未来航天器发展要求。
发明内容
本发明的一个目的在于提供一种用于航天器的空间碎片防护结构。
本发明的另一个目的在于提供一种制备如上所述的空间碎片防护结构的制备方法。
为达到第一个目的,本发明采用下述技术方案:
本发明提供一种用于航天器的空间碎片防护结构,包含防护层结构,所述防护层结构包含至少三组结合固定的防护层组合,所述防护层组合包含缓冲层以及位于缓冲层外侧的防护层,其中缓冲层可分为收纳状态和充气展开状态。
进一步,所述空间碎片防护结构还包括收集层,所述收集层结合固定在防护层结构的内侧。
进一步,所述防护层由外向内依次设置有用于承力的陶瓷纤维织物、用于承接碎片的网状纤维织物以及阻气薄膜;所述收集层由外向内依次设置有用于承接碎片的网状纤维织物以及阻气薄膜。
进一步,所述陶瓷纤维织物的材料为氧化铝纤维、氧化锆纤维、碳化硅纤维或氮化硼纤维中的一种或多种。
进一步,所述网状纤维织物的材料为芳纶纤维、PBO纤维、F-12纤维或F-3纤维中的一种或多种。
进一步,所述阻气薄膜包括含氟硅橡胶薄膜或聚酰亚胺薄膜。
进一步,所述缓冲层通过航天器内的充气单元进行充气展开,所述缓冲层有与所述充气单元连同的气体通道,所述充气单元的气体通过所述气体通道向缓冲层充气,所述充气的气体为氮气或氦气,充气压力为50~100kpa。
进一步,所述缓冲层充气后处于完全展开状态时,所述防护层与相邻的防护层间距为150~200mm,所述缓冲层由收纳状态到充气后完全展开状态所需时间为10~60s。
为达到另一个目的,本发明采用下述技术方案:
本发明提供一种制备如上所述空间碎片防护结构的制备方法,包括如下步骤:
将收集层固定于航天器外表面,然后用网状纤维织物编织形成至少三层气体缓冲层初始框架,网状纤维织物内侧固定阻气薄膜,经固化后形成缓冲层结构框架,然后在网状纤维织物外侧固定陶瓷纤维织物,经固化后即得空间碎片防护结构。
进一步,所述固化的温度为25~150℃,所述固化温度为6~24h;优选地,所述固化温度为25~50℃,所述固化温度为22~24h;优选地,所述固化温度为100~150℃,所述固化温度为6~8h。
本发明的有益效果如下:
本发明提供的空间碎片防护结构,可提高对空间碎片的防御能力,其中防护层对空间碎片实现充分破碎、减速和收集,缓冲层在展开状态下形成的大防护间距可促进碎片云的充分扩散,缓冲层内的气体与碎片云间的摩擦还可促进碎片烧蚀并减速,多层级的防护层组合进一步提高其对空间碎片破碎、减速和收集的效果。与传统的玄武岩-聚氨酯泡沫复合防护结构相比,其防护性能提升10%~15%,并且该防护结构以气体填充代替传统防护结构支撑构件,兼具重量轻、体积小、服役周期长、隔防热效果好的特点,与同等防护效能的三层whipple结构相比减重25%~30%,体积减少60%~70%,热导率≤0.03W/m·K,可在轨空间服役5年。
附图说明
下面结合附图对本发明的具体实施方式作进一步详细的说明。
图1示出本发明提供的空间碎片防护结构的结构示意图及各部分的细节图;
其中,1为缓冲层,2为收集层,3为防护层,4为网状纤维织物,5陶瓷纤维织物,6为阻气薄膜,7充气气体。
图2示出本发明提供的空间碎片防护结构充气展开状态(a)及收纳状态(b)的示意图。
具体实施方式
为了进一步理解本发明,下面将结合本发明实施例,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。
本发明提供的空间碎片防护结构用于航天器中,可有效解决传统设计中功能重复、质量重、体积大等问题,使应用系统得以简化,不仅重量轻、体积小和成本低,还具有优良的隔热、抗碎片撞击的能力,进一步保证应用系统的稳定性和安全性。
本发明提供的防护层由陶瓷纤维织物、网状纤维织物和阻气薄膜三层结构组成,陶瓷纤维织物具有一定抗撞击能力,当航天器在轨工作时,有空间碎片以第一宇宙速度撞向航天器,防护层最外侧的陶瓷纤维织物承受空间碎片的撞击,使空间碎片受到阻力造成动能的一次耗散,并且陶瓷纤维织物具有一定韧性可以使空间碎片发生碎裂并解体,碎裂的空间碎片穿过陶瓷纤维织物进入第二层的网状纤维织物,有部分空间碎片会被网状纤维织物收集在第二层,穿过第二层的空间碎片会穿过阻气薄膜进入呈展开状态的缓冲层,阻气薄膜主要是防止缓冲层内的气体泄露,保持一定压力,在轨期间漏气率≤5Kpa/h,并且必须具备足够的强度,同时也要易于收纳和缝纫,这样才能保证缓冲层充气后迅速膨胀展开而不发生破裂,同时可在航天器内配备补充充气单元及充气控制装置,根据压力传感器提示进行气体补充。
本发明中陶瓷纤维织物的材料包括但不限于氧化铝纤维、氧化锆纤维、碳化硅纤维或氮化硼纤维等氧化物、碳化物、氮化物的高性能陶瓷纤维,陶瓷纤维织物具有隔防热作用,能够保证在轨航天器的温度稳定,并且网状纤维织物的材料包括但不限于芳纶纤维、PBO纤维、F-12纤维或F-3纤维等高强度化学纤维织物中的一种或多种。
需要说明的是,所述充气单元位于航天器内,可以为储箱充气系统、化学反应气体生成系统或所述储箱充气系统和所述化学反应气体生成系统的混合系统,充气单元可以同时为多个缓冲层进行充气,充气后缓冲层均会迅速展开,缓冲层内的气体使得缓冲层形成150~200mm的大间距,当穿过防护层的空间碎片进入缓冲层后,缓冲层的大间距有利于空间碎片的充分扩散,并且超高速的空间碎片与气体发生剧烈摩擦并烧蚀,使空间碎片的动能发生二次耗散。
空气碎片通过每一组防护层组合后速度或动能衰减15%~30%。
该空间碎片防护结构在发射过程中缓冲层呈柔性收纳状态,可降低运载体积,减少阻力和能力损耗,其收纳方式可根据航天器的具体结构尺寸和内部装载物体进行设计,当进入轨道后该空间碎片防护结构根据航天器探测系统指令控制充气单元向缓冲层快速充气并使其展开,整个过程中该空间碎片防护结构灵活机动,不受航天器总体布局、包络尺寸和火箭发射等诸多瓶颈因素的限制,且该空间碎片防护结构在快速充气展开过程中不需要额外的支撑结构,避免了采用传统固定外挂式柔性防护结构支撑构件带来的体积大、重量大和效费比低的缺点。
防护层组合的数量可以根据实际的应用要求(如:航天器收纳效率、重量、尺寸、空间碎片防护及隔热效率)进行多层设计,可以为三组、四组或五组,提供空间碎片防护和隔热功能。通过至少三组以上的防护层组合,可以实现空间碎片的粉碎、速度的逐级递减以及空间碎片的收集,降低空间碎片对航天器的损害同时,可以减少新的碎片云的生成,有利于降低轨道上空间垃圾的密度。通过多组防护层组合的空间碎片在数量、尺寸和速度方面都发生明显的下降,最终残留的少量空间碎片会被收集层上的网状纤维织物完成收集。
防护层可根据航天器复杂形面进行赋形设计及成型加工,适用于大尺寸航天器异型面的关键部件空间碎片防护。多层组合结构相比传统结构具有降低发射体积及发射载荷,具有轻量化、高动能耗散的结构特点。同时利用超高速碎片与气囊内氮气的动能摩擦作用,二次耗散碎片的动能,并烧蚀碎片,提升航天器的生存能力。相比传统铝合金防护结构及单层囊体防护结构,本结构还具备易于空间站安装及更换的能力,可由天舟货运飞船带置空间站并由机械臂及航天员进行配合安装,同时在防护结构服役期满后可进行结构简易更换,提升防护效能。
实施例1
选择含氟硅橡胶薄膜和芳纶纤维织物作为收集层材料,将芳纶纤维织物粘贴于航天器外表面,然后用含氟硅橡胶薄膜粘贴于芳纶纤维织物上,利用F-12芳纶纤维编织形成三层气体缓冲层初始框架,设置展开后每层间距150mm,F-12芳纶纤维内侧粘贴含氟硅橡胶薄膜,经150℃固化6h,形成缓冲层框架,然后在F-12芳纶纤维外侧使用抗高温柔性胶体粘贴氧化铝纤维织物,经150℃固化6h,最终形成空间碎片防护结构。
实施例2
参照实施例1的制备工艺,仅将F-12芳纶纤维替换为F-12芳纶纤维-碳纤维复合材料,含氟硅橡胶薄膜替换为聚酰亚胺薄膜,其他参数与实施例1相同。
实施例3
参照实施例1的制备工艺,仅将F-12芳纶纤维替换为PBO纤维,每层间距设置为200mm,含氟硅橡胶薄膜替换为聚酰亚胺薄膜,其他参数与实施例1相同。
实施例4
参照实施例1的制备工艺,仅将F-12芳纶纤维替换为F-12芳纶纤维-碳纤维-PBO纤维复合材料,含氟硅橡胶薄膜替换为聚酰亚胺薄膜,其他参数与实施例1相同。
试验例1
充入氮气55kpa,安装防护结构测试参试产品,利用二级轻气炮进行毫米级碎片6-7km/s超高速撞击试验,并通过高速摄影及红外摄像进行记录及观察,完成试验分析。通过测试撞击后破坏尺寸、分析超高速视频、分析红外温度场,获得动能耗散及毁伤防护性能。通过分析数据,与同等防护效能的三层whipple结构相比,重量减重25%、体积减小70%、动能耗散情况(即防护性能)提升12%。
显然,本发明的上述实施例仅仅是为清楚地说明本发明所作的举例,而并非是对本发明的实施方式的限定,对于所属领域的普通技术人员来说,在上述说明的基础上还可以做出其它不同形式的变化或变动,这里无法对所有的实施方式予以穷举,凡是属于本发明的技术方案所引伸出的显而易见的变化或变动仍处于本发明的保护范围之列。
Claims (10)
1.一种用于航天器的空间碎片防护结构,其特征在于,包含防护层结构,所述防护层结构包含至少三组结合固定的防护层组合,所述防护层组合包含缓冲层以及位于缓冲层外侧的防护层。
2.根据权利要求1所述的空间碎片防护结构,其特征在于,所述空间碎片防护结构还包括收集层,所述收集层结合固定在防护层结构的内侧。
3.根据权利要求1所述的空间碎片防护结构,其特征在于,所述防护层由外向内依次设置有用于承力的陶瓷纤维织物、用于承接碎片的网状纤维织物以及阻气薄膜;所述收集层由外向内依次设置有用于承接碎片的网状纤维织物以及阻气薄膜。
4.根据权利要求3所述的空间碎片防护结构,其特征在于,所述陶瓷纤维织物的材料为氧化铝纤维、氧化锆纤维、碳化硅纤维或氮化硼纤维中的一种或多种。
5.根据权利要求3所述的空间碎片防护结构,其特征在于,所述网状纤维织物的材料为芳纶纤维、PBO纤维、F-12纤维或F-3纤维中的一种或多种。
6.根据权利要求3所述的空间碎片防护结构,其特征在于,所述阻气薄膜包括含氟硅橡胶薄膜或聚酰亚胺薄膜。
7.根据权利要求1所述的空间碎片防护结构,其特征在于,所述缓冲层通过航天器内的充气单元进行充气展开,所述缓冲层有与所述充气单元连同的气体通道,所述充气单元的气体通过所述气体通道向缓冲层充气,所述充气的气体为氮气或氦气,充气压力为50~100kpa。
8.根据权利要求1所述的空间碎片防护结构,其特征在于,所述缓冲层充气后处于完全展开状态时,所述相邻防护层的间距为150~200mm,所述缓冲层由收纳状态到充气后完全展开状态所需时间为10~60s。
9.一种如权利要求1~8任一所述的空间碎片防护结构的制备方法,其特征在于,包括如下步骤:
将收集层固定于航天器外表面,然后用网状纤维织物编织形成至少三层气体缓冲层初始框架,网状纤维织物内侧固定阻气薄膜,经固化后形成缓冲层结构框架,然后在网状纤维织物外侧固定陶瓷纤维织物,经固化后即得空间碎片防护结构。
10.根据权利要求9所述的制备方法,其特征在于,所述固化的温度为25~150℃,所述固化温度为6~24h。
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