CN111268179A - 一种月面居住舱舱体防护结构 - Google Patents
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Abstract
本发明公开了一种月面居住舱舱体防护结构，属于载人航天工程中可展开式太空舱的空间环境防护设计领域。包括靠近舱体内侧设置的气密层、设置在气密层上的结构限制层、设置在结构限制层上的防热层，所述结构限制层至少有两层，在任意两层所述的结构限制层之间设置有主防护层。本发明的月面居住舱舱体防护结构，能适应月面可展开居住舱的折叠和展开需求。舱体中间的主防护层，在居住舱完全展开后通过月面原位发泡工艺进行填充，成型的有机泡沫材料具有优良的隔热和缓冲性能，能有效抵御月面的交变热环境和微流星体撞击。
Description
技术领域
本发明涉及载人航天工程中可展开式太空舱的空间环境防护设计领域，更具体的说是涉及一种月面居住舱舱体防护结构。
背景技术
月球是人类开展深空探测的首选目标，其独特的环境和资源使之成为开展空间天文、空间物理、行星科学、材料科学等基础研究的理想场所。开展载人月球探测，在月面建立科研站或月球基地，是人类未来实现月球资源深度开发利用的重要手段和必然途径。
月球站或月球基地的居住舱需适应月面的各种特殊环境，包括高真空、低重力(1/6g)、大温差(-183℃至127℃)、空间辐射(高能宇宙线、太阳电磁辐射、太阳风)、微流星体、月尘等。为了给航天员在月面提供一个安全的驻留环境，居住舱的设计和建造应该从选址、材料、结构等方面重点解决热控、辐射防护等问题。
月面居住舱按照结构形式的不同，可分为刚性舱和可展开舱。刚性舱通常由金属材料制成，在地球上加工、制造和组装后通过地月运输系统运送到月球表面，整体来看成熟度较高，技术难度较低，但其提供的工作和生活空间较为有限，若要对舱段进行扩展，需进行多次地月间的物资运输，增加建设成本。可展开式居住舱需在月球表面展开后才能使用，具体可采用充气展开式或者机械展开式。可展开舱可以进行折叠装载，因此在尺寸上受运载的约束较小。相比刚性舱，可展开舱在相同舱体容积下的质量更轻，扩展性更好，应用也更为灵活，但其对材料和结构的要求更高。若采用可展开式居住舱，需从材料选用和结构设计两方面，针对空间辐射、月面高低温、微流星体等恶劣环境因素进行多重防护。
目前，航天工程中对空间辐射、碎片和微流星体撞击的通用防护手段是增加舱体厚度，这种方式的最大弊端是增加了舱体重量和发射成本。对于月面可展开式居住舱，目前没有一种能综合考虑辐射、高低温和微流星体防护且能结合月面原位资源利用的轻量化舱体结构方案。
发明内容
本发明针对月面的特殊恶劣环境，提出一种轻量化的月面居住舱舱体防护结构方案，通过使用多层柔性复合材料和结构，并利用模拟月壤，可实现对空间高能辐射、月面高低温以及微流星体的多重防护，以更小的发射重量代价实现更好的防护效果。
为了实现上述目的，本发明采用以下技术方案：
一种月面居住舱舱体防护结构，包括靠近舱体内侧设置的气密层、设置在气密层上的结构限制层、设置在结构限制层上的防热层，所述结构限制层至少有两层，在任意两层所述的结构限制层之间设置有主防护层。
本发明的月面居住舱舱体防护结构由多层复合材料构成，主要包括气密层、结构限制层、主防护层、防热层。舱体内侧的气密层的主要作用是阻止舱内气体泄漏，维持舱压；结构限制层有内外两层，其主要作用是承受气密层以及主防护层的压力载荷，两层结构限制层之间为主防护层；主防护层是整个舱体防护结构最厚的部分，采用掺杂模拟月壤及含硼化合物的特种有机发泡材料，具有隔热、屏蔽高能辐射以及抵挡微流星体撞击的多重防护作用；舱体最外侧的防热层的作用是保护居住舱抵御月昼及月夜的极端高低温交变环境。
进一步的，所述气密层由单层或多层薄膜材料构成。
进一步的，所述薄膜材料为聚酰亚胺薄膜，其厚度为1-2mm。
进一步的，所述结构限制层由多层高强织物材料构成。
进一步的，所述高强织物为Kevlar织物或Vectran织物，其厚度为2-3mm。
进一步的，所述防热层采用氧化铝纤维层和柔性热控薄膜构成，防热层的厚度为2-3mm。
进一步的，所述主防护层采用掺杂模拟月壤及含硼化合物的聚合物泡沫发泡制成。
进一步的，所述模拟月壤、含硼化合物以及聚合物泡沫材料的用量比为15:4:31。
进一步的，所述含硼化合物为碳化硼、氧化硼或硼酸中的一种；所述聚合物泡沫为聚氨酯泡沫或聚酰亚胺泡沫。
进一步的，所述模拟月壤的粒径为100-500微米。
本发明与现有技术相比具有的有益效果是：
1、本发明的月面居住舱舱体防护结构，能适应月面可展开居住舱的折叠和展开需求。舱体中间的主防护层，在居住舱完全展开后通过月面原位发泡工艺进行填充，成型的有机泡沫材料具有优良的隔热和缓冲性能，能有效抵御月面的交变热环境和微流星体撞击。
2、有机泡沫材料通过掺杂月壤和含硼化合物后，利用高原子序数结合低原子序数材料的组合屏蔽作用以及硼元素对中子的高效吸收，能对宇宙线高能粒子以及宇宙线与月表作用产生的大量次级中子形成更好的防护效能。
附图说明
图1是本发明的一种月面居住舱舱体防护结构的结构示意图。
图中标记：1-气密层，2-结构限制层，3-主防护层，4-防热层。
具体实施方式
下面结合实施例对本发明作进一步的描述，所描述的实施例仅仅是本发明一部分实施例，并不是全部的实施例。基于本发明中的实施例，本领域的普通技术人员在没有做出创造性劳动前提下所获得的其他所用实施例，都属于本发明的保护范围。
实施例1:
如图1所示，一种月面居住舱舱体防护结构，包括靠近舱体内侧设置的气密层1、设置在气密层1上的结构限制层2、设置在结构限制层2上的防热层4，所述结构限制层2有两层，在两层所述的结构限制层2之间设置有主防护层3。
舱体内侧的气密层1的主要作用是阻止舱内气体泄漏，维持舱压。在本实施中，所述气密层1由单层薄膜材料构成。所述薄膜材料为聚酰亚胺薄膜，其厚度为1mm。
结构限制层2有内外两层，其主要作用是承受气密层1以及主防护层3的压力载荷，两层结构限制层2之间为主防护层3；所述结构限制层2由多层高强织物材料构成，所述高强织物为Kevlar织物，其厚度为2mm。
主防护层3是整个舱体防护结构最厚的部分，采用掺杂模拟月壤及含硼化合物的有机发泡材料，具有隔热、屏蔽高能辐射以及抵挡微流星体撞击的多重防护作用；所述主防护层3采用掺杂模拟月壤及含硼化合物的聚合物泡沫发泡制成。所述模拟月壤、含硼化合物以及聚合物泡沫材料的用量比为15:4:31。所述含硼化合物为碳化硼；所述聚合物泡沫为聚氨酯泡沫。模拟月壤的粒径为100微米
舱体最外侧的防热层4的作用是保护居住舱抵御月昼及月夜的极端高低温交变环境。所述防热层4采用氧化铝纤维层和柔性热控薄膜构成，防热层4的厚度为2mm。其中柔性热控薄膜是与外太空接触的一层，其主要是控制太阳辐射的吸收，而氧化铝纤维层是起高温隔热作用的，两者都是起到防热的作用。
舱体的主防护层3位于两层结构限制层2之间，采用聚氨酯泡沫材料。月面可展开式居住舱在发射上月球时，采用本发明的防护结构支撑的舱体类似帐篷结构，舱体处于折叠压缩状态，在月面完全展开就位后，两层结构限制层2之间形成空腔。通过遥控操作或航天员人工操作，将与居住舱一同发射上月面的模拟月壤以及发泡组分注入居住舱舱体的空腔内，并添加适量的含硼化合物以吸收宇宙线重离子与舱体作用产生的次级中子。所述模拟月壤、含硼化合物以及聚合物泡沫材料的用量比为15:4:31。所有成分混合均匀后，在舱体空腔中进行发泡，将结构限制层2之间的空间完全填充，形成夹层结构。固化成型后的主防护层3厚度不小于30cm，兼具隔热保温、抵御微流星体撞击、屏蔽高能宇宙线辐射、吸收次级中子辐射等多功能防护效能。
实施例2：
如图1所示，一种月面居住舱舱体防护结构，包括靠近舱体内侧设置的气密层1、设置在气密层1上的结构限制层2、设置在结构限制层2上的防热层4，所述结构限制层2有三层，在任意两层所述的结构限制层2之间设置有主防护层3。
舱体内侧的气密层1的主要作用是阻止舱内气体泄漏，维持舱压。在本实施中，所述气密层1由多层薄膜材料构成。所述薄膜材料为聚酰亚胺薄膜，其厚度为2mm。
结构限制层2有内外两层，其主要作用是承受气密层1以及主防护层3的压力载荷，两层结构限制层2之间为主防护层3；所述结构限制层2由多层高强织物材料构成，所述高强织物为Vectran织物，其厚度为3mm。
主防护层3是整个舱体防护结构最厚的部分，采用掺杂模拟月壤及含硼化合物的有机发泡材料，具有隔热、屏蔽高能辐射以及抵挡微流星体撞击的多重防护作用；所述主防护层3采用掺杂模拟月壤及含硼化合物的聚合物泡沫发泡制成。所述模拟月壤、含硼化合物以及聚合物泡沫材料的用量比为3:1:6。所述含硼化合物为氧化硼；所述聚合物泡沫为聚酰亚胺泡沫。模拟月壤的粒径为500微米
舱体最外侧的防热层4的作用是保护居住舱抵御月昼及月夜的极端高低温交变环境。所述防热层4采用氧化铝纤维层和柔性热控薄膜构成，防热层4的厚度为3mm。
在本实施中，本发明还有一个优点是之所以选择模拟月壤就是模拟月壤具有与月球样品相似的矿物组成和化学成分,相似的颗粒粒度、机械强度、孔隙度、密度和电学性质,是月球样品的地球化学复制品。所以在发泡制作主防护层3时可用月壤代替模拟月壤。即：
当月面可展开式居住舱在发射上月球时，舱体处于折叠压缩状态，在月面完全展开就位后，两层结构限制层2之间形成空腔。通过遥控操作或航天员人工操作，将与居住舱一同发射上行至月面的发泡组分注入居住舱舱体空腔。在居住舱附近原位收集月壤，筛分出颗粒度合适的月壤掺杂至发泡组分中，并添加适量的含硼化合物以吸收宇宙线重离子与舱体作用产生的次级中子。所有成分混合均匀后，在舱体空腔中进行发泡，将结构限制层2之间的空间完全填充，形成夹层结构。固化成型后的主防护层3厚度不小于30cm，兼具隔热保温、抵御微流星体撞击、屏蔽高能宇宙线辐射、吸收次级中子辐射等多功能防护效能。这样就减少了由地球向月球上运输的重量，减少运输成本。
实施例3：
如图1所示，一种月面居住舱舱体防护结构，包括靠近舱体内侧设置的气密层1、设置在气密层1上的结构限制层2、设置在结构限制层2上的防热层4，所述结构限制层2有三层，在任意两层所述的结构限制层2之间设置有主防护层3。
舱体内侧的气密层1的主要作用是阻止舱内气体泄漏，维持舱压。在本实施中，所述气密层1由4层薄膜材料构成。所述薄膜材料为聚酰亚胺薄膜，其厚度为1.5mm。
结构限制层2有内外两层，其主要作用是承受气密层1以及主防护层3的压力载荷，两层结构限制层2之间为主防护层3；所述结构限制层2由多层高强织物材料构成，所述高强织物为Vectran织物，其厚度为2.5mm。
主防护层3是整个舱体防护结构最厚的部分，采用掺杂模拟月壤及含硼化合物的有机发泡材料，具有隔热、屏蔽高能辐射以及抵挡微流星体撞击的多重防护作用；所述主防护层3采用掺杂模拟月壤及含硼化合物的聚合物泡沫发泡制成。所述模拟月壤、含硼化合物以及聚合物泡沫材料的用量比为4:1:5。所述含硼化合物为硼酸；所述聚合物泡沫为聚酰亚胺泡沫。模拟月壤的粒径为300微米
舱体最外侧的防热层4的作用是保护居住舱抵御月昼及月夜的极端高低温交变环境。所述防热层4采用氧化铝纤维层和柔性热控薄膜构成，防热层4的厚度为3mm。
以上所述仅为本发明的较佳实施例而已，并不用以限制本发明，凡在本发明的精神和原则之内所作的任何修改、等同替换和改进等，均应包含在本发明的保护范围之内。
Claims (10)
1.一种月面居住舱舱体防护结构，其特征在于，包括靠近舱体内侧设置的气密层、设置在气密层上的结构限制层、设置在结构限制层上的防热层，所述结构限制层至少有两层，在任意两层所述的结构限制层之间设置有主防护层。
2.根据权利要求1所述的一种月面居住舱舱体防护结构，其特征在于，所述气密层由单层或多层薄膜材料构成。
3.根据权利要求2所述的一种月面居住舱舱体防护结构，其特征在于，所述薄膜材料为聚酰亚胺薄膜，其厚度为1-2mm。
4.根据权利要求1所述的一种月面居住舱舱体防护结构，其特征在于，所述结构限制层由多层高强织物材料构成。
5.根据权利要求4所述的一种月面居住舱舱体防护结构，其特征在于，所述高强织物为Kevlar织物或Vectran织物，其厚度为2-3mm。
6.根据权利要求1所述的一种月面居住舱舱体防护结构，其特征在于，所述防热层采用氧化铝纤维层和柔性热控薄膜构成，防热层的厚度为2-3mm。
7.根据权利要求1所述的一种月面居住舱舱体防护结构，其特征在于，所述主防护层采用掺杂模拟月壤及含硼化合物的聚合物泡沫发泡制成。
8.根据权利要求7所述的一种月面居住舱舱体防护结构，其特征在于，所述模拟月壤、含硼化合物以及聚合物泡沫材料的用量比为15:4:31。
9.根据权利要求7所述的一种月面居住舱舱体防护结构，其特征在于，所述含硼化合物为碳化硼、氧化硼或硼酸中的一种；所述聚合物泡沫为聚氨酯泡沫或聚酰亚胺泡沫。
10.根据权利要求7所述的一种月面居住舱舱体防护结构，其特征在于，所述模拟月壤的粒径为100-500微米。
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