CN107680698B - 用于极端环境的多功能复合结构 - Google Patents
用于极端环境的多功能复合结构 Download PDFInfo
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- CN107680698B CN107680698B CN201710486523.5A CN201710486523A CN107680698B CN 107680698 B CN107680698 B CN 107680698B CN 201710486523 A CN201710486523 A CN 201710486523A CN 107680698 B CN107680698 B CN 107680698B
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Abstract
本发明涉及用于极端环境的多功能复合结构。多功能复合结构具有可以取决于极端环境而改变的模块化设计,其中所述结构将暴露于诸如危险辐射、微流星体和轨道碎片冲击、极端温度变化,等。所述多功能复合结构中采用的材料组合提供了一种重量轻且最大限度地防止辐射、碎片冲击和温度变化的支撑结构。
Description
技术领域
本公开涉及一种用于极端环境的复合结构。更具体地,本公开涉及一种具有可以取决于所述极端环境而改变的模块化设计的多功能复合结构,在所述极端环境中,所述结构将被暴露于诸如危险辐射、微流星体和轨道碎片冲击、极端温度变化,等。所述多功能复合结构中采用的材料组合提供了一种重量轻且最大限度地防止辐射、碎片冲击和温度变化的支撑结构。
背景技术
对于在极端环境(例如外层空间或处理核材料)中工作的个人,有必要保护个人免遭极端环境的侵害。这些极端环境中的敏感仪器和/或设备也需要保护。
例如,在空间中,需要受保护的可容纳空间来提供对空间辐射的屏蔽,包括对电离辐射和非电离辐射两者的屏蔽。还需要防止超速微流星体和轨道碎片(MMOD)冲击。也需要对极端温度变化(从低于-200C到+200C)进行隔离。此外,保护性可容纳空间必须具有结构完整性以支撑必要的结构负载。
发明内容
本公开的多功能复合结构特别设计用在极端环境中。所述多功能结构包括两层或更多层复合面板,最外层提供高强度并且最内层提供密封的压力壳体。
支撑结构被定位在外层的复合面板与内层的复合面板之间的空间中。所述支撑结构连接到所述外层的复合面板和所述内层的复合面板两者。所述支撑结构具有蜂窝构造或梯形构造或一些其它等同构造。所述支撑结构的构造将所述外层的复合面板与所述内层的复合面板之间的所述空间分隔为多个分隔空间。
泡沫填充所述外层的复合面板与所述内层的复合面板之间的所述多个分隔空间。所述泡沫为所述结构提供轨道碎片的隔热、辐射屏蔽和能量吸收。
磁性排斥器也设置在所述外层的复合面板与所述内层的复合面板之间的所述空间中。所述磁性排斥器由以螺旋模式形成的超导电线或条带构成。多个线材或条带延伸穿过所述外层的复合面板与所述内层的复合面板之间的所述空间,并且当设置有电流时,所述线材或条带充当带电粒子的磁性排斥器,以提供防护(电离辐射)。当电流流过以螺旋模式形成的超导体线材/条带时,生成磁场。所述磁场通过排斥进入的带电粒子(电离辐射)而提供对空间辐射的防护。
隔离体也设置在所述外层的复合面板与所述内层的复合面板之间的所述空间中。所述隔离体是多层隔离体。所述隔离体提供隔热以防止温度变化。所述隔离体还是提供附加辐射防护的辐射屏蔽隔离体。
除了用在诸如外层空间或处理核材料的极端环境中,所述复合结构还可以用在需要防爆和/或电磁脉冲保护的车辆上,例如军用车辆和飞行器、用于个人保护的装甲车辆,等。
已经讨论的特征、功能和优点可以在各种示例中独立实现或者可在其它示例中组合,可以参考以下描述和附图看出其进一步细节。
附图说明
图1表征穿过复合结构的一部分的一侧的横截面视图。
图2表征图1中表征的复合结构的一部分的立体图。
图3表征复合结构的外面板的横截面。
图4表征复合结构的内面板的横截面。
图5表征复合结构的支撑结构的横截面。
图6表征穿过复合结构的变形例的一部分的一侧的横截面视图。
图7表征图6中表征的复合结构的一部分的立体图。
图8表征在构建方面采用复合结构的航天器的横截面。
图9示意性地表征图8中表征的复合结构的一部分。
图10表征穿过图1中表征的复合结构的变形例的一部分的横截面视图。
图11表征图6中表征的复合结构的变形例的一部分的横截面视图。
图12表征构建采用复合结构的航天器的方法。
图13表征为采用复合结构的航天器屏蔽辐射的方法。
具体实施方式
图1表征本公开的复合结构10的一部分的横截面。图2表征图1的复合结构10的一部分的立体图。在图1和图2中,复合结构10上方的区域是复合结构10被设计使用的极端环境的区域,并且复合结构10下方的区域是受复合结构保护的区域。
复合结构10根据图12中表征的方法构建,具有提供高强度且暴露于极端环境的外面板12。外面板12在外面板的外表面14与内表面16之间具有厚度。外面板12的厚度可以在0.3cm到0.6cm或以上的范围内,例如,0.2cm到2.0cm,这取决于外面板12所暴露的外部环境类型以及外面板12的重量和抗冲击性要求。外面板12的外表面14和外面板12的内表面16是平滑连续表面。如图1中表征的,外面板12的外表面14和外面板12的内表面16是平面的且大致平行。表面14、16也可以是非平面表面(诸如曲面)或其它成形表面。例如,当外面板12用于构建航天器时,具有柱形构造。
外面板12由复合材料构成。外面板12的复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/高密度聚乙烯(HDPE)、石墨/环氧树脂带或者其它等同材料或等同材料组合(诸如石墨/光谱/高密度聚乙烯层压物)的组。
进入外面板12的构建中的复合材料和复合材料组合的类型取决于外面板12所暴露的极端环境的特性。可能复合材料的示例示出在下表中,其列出了复合材料、它们的氢百分比含量及材料指数,具有更大指数的材料提供更好的辐射防护。
存在表中列出的可以用于形成外面板12的材料的许多潜在组合。复合材料的一种可能组合被表征在图3中。如图3中表征的,外面板12包括由光谱织物片材22分开的多层HDPE片材18。各片材通过树脂、粘合剂或其它等效手段接合。
选择外面板12的复合材料主要是为了防止穿刺或损坏复合结构10的相对侧上的内面板24。外面板12的设计是为了吸收离开微流星体和轨道碎片(MMOD)与复合结构10进行弹丸冲击的大部分能量并且气化MMOD弹丸。外面板12的设计是为了承受具有高达1cm的直径尺寸以及从3km/s变化到30km/s的速度的MMOD弹丸的冲击。
为了构建外面板12而选择的复合材料的氢含量还将提供额外辐射防护以及附加隔热,并且还将增加可以由外面板12支撑的结构负载。
复合结构10的内面板24的构建主要是为了在复合结构内侧提供密封且温度/湿度受控的环境。内面板24在内面板的外表面26与内表面28之间具有厚度。内面板24的厚度可以在0.2cm到0.4cm或以上的范围内,例如,0.2cm到2.0cm,这取决于内面板24所暴露的环境类型。内面板24的外表面26和内面板24的内表面28是平滑连续表面。如图1中表征的,内面板24的外表面26和内面板24的内表面28是平面的且大致平行。表面26、28也可以是非平面表面(诸如曲面)或其它成形表面。例如,当内面板24用于构建航天器时,具有柱形构造。
内面板24由诸如上表中列出的复合材料构成。内面板24的复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/高密度聚乙烯(HDPE)、石墨/环氧树脂带或者其它等同材料或等同材料组合(诸如石墨/光谱/高密度聚乙烯层压物)的组。
存在上表中列出的可以用于形成内面板24的材料的许多潜在组合。复合材料的一种可能组合被表征在图4中。如图4中表征的,内面板24包括由石墨片材34分开的多层HDPE片材32。各片材通过树脂、粘合剂或其它等效手段接合。
内面板24的复合材料被选择成使得内面板24为人或动物和/或敏感设备及仪器提供密封且温度/湿度受控的环境。
为了构建内面板24而选择的复合材料的氢含量还将提供额外辐射防护以及附加隔热,并且还将增加可以由内面板24支撑的结构负载。
如图1和图2中表征的,在复合结构10中,在外面板12的内表面16与内面板24的内表面28之间设置有空间或距离42。外面板12的内表面16与内面板24的内表面28之间的空间42的距离介于5cm到10cm的范围内。空间42的距离的选择取决于复合结构10所暴露的极端环境,例如复合结构10是否将被暴露于MMOD弹丸冲击。
支座或支撑结构44被定位在空间42中。支撑结构44连接到外面板12的内表面16和内面板24的内表面28。支撑结构44具有由与外面板12的内表面16和内面板24的内表面28连接的多个壁46构成的格子构造。多个壁46包围外面板12的内表面16与内面板24的内表面28之间的多个分隔空间48,多个壁46将多个分隔空间48分开。在图1和图2的复合结构10的表征中,将多个分隔空间48分开的多个壁46具有梯形构造。多个壁46的构造可以不同于图1和图2中表征的梯形构造,这取决于复合结构10的负载和重量要求。为了构建支撑结构44而选择的复合材料可以与构建外面板12和/或内面板24所使用的材料相同。构建支撑结构44也可以采用复合材料的其它组合。
参照图5,示出了支撑结构44的一部分的侧视图的表征。在图5中,支撑结构44由多层光谱织物片材54所分开的多层HDPE片材52构成,各层通过树脂、粘合剂或其它等效手段接合。多个壁46中的每个的厚度可以从0.2cm到0.4cm或以上变化,这取决于复合结构10期望的结构负载和重量考虑。
如上所述,复合结构10的支撑结构44的构造可以不同于所描述的梯形构造。参照图6和图7,示出了变形,即,复合结构10'。图6和图7中表征的复合结构10'的构建与图1和图2中表征的构建基本相同,并且用于标记图6和图7中表征的复合结构10'的组成部分的附图标记与构建图1和图2的复合结构10所使用的附图标记相同,附图标记后面是一撇(')。
在支撑结构56的构造方面,图6和图7中表征的复合结构10'的构建不同于之前描述的复合结构10的构建。在图6和图7表征的复合结构10'的示例中,所述支撑结构56具有也连接在外面板12'的内表面16'与内面板24'的内表面28'之间的多个壁58。线材66'围绕支撑结构56呈螺线形。多个壁58将空间42'分隔为外面板12'的内表面16'与内面板24'的内表面28'之间的多个分隔空间62,多个壁58将多个分隔空间62分开。将多个分隔空间62分开的多个壁58具有蜂窝构造。图6和图7的支撑结构56可以由上文参考图1和图2的复合结构10的支撑结构44描述的相同复合材料构成。
回到图1和图2的复合结构10,泡沫64被插置于空间42和支撑结构44中。泡沫64填充外面板12的内表面16与内面板24的内表面28之间的多个分隔空间48。泡沫64完全填充分隔空间48。泡沫64可以是隔热泡沫、辐射屏蔽泡沫,或两者。在图1和图2表征的复合结构10中,泡沫64是聚乙烯/脲油泡沫。这种相同的泡沫可以用在前述图6和图7的复合结构10'中。
线材66延伸穿过空间42。线材66穿过外面板12的内表面16与内面板24的内表面28之间的空间42。线材66可以具有常规线材的横截面构造,或者可以具有条带的横截面构造或其它等同横截面构造。线材66可以是多个线材。线材66具有高导电性并且可以是超导体。如图1和图2中表征的,考虑到重量和安全性,线材66沿着内面板24的内表面28定位。线材66还可以沿着外面板12的外表面14或内表面16定位,以提供对高能带电粒子(电离辐射)的附加防护。
隔离体72也设置在外面板12的内表面16与内面板24的内表面28之间的空间42中。隔离体72是多层隔离体。如图1和图2中表征的,隔离体72在内面板24的内表面28上延伸。隔离体72还可以定位在内面板24的外表面26上。隔离体72提供附加隔热以防止穿过复合结构10的温度变化,并且还可以是辐射屏蔽隔离体以提供附加辐射防护。
图8表征在构建飞行器或航天器中采用的复合结构10。图8表征封闭的航天器的柱形横截面。图12表征构建采用复合结构10的航天器74的方法。如图8和图12中表征的,在航天器74的构建中,复合结构10的内面板24包围航天器的内部容积76,并且外面板12围绕内面板24延伸。复合结构10的外面板12形成航天器的外部并且暴露于航天器在空间中时遭受的极端环境78。如前所述,外面板12由选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组的复合材料构成。内面板24由选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组的复合材料构成。在航天器74的构建中,在外面板12与内面板24之间提供空间42。支撑结构44在复合结构10的内面板24与外面板12之间延伸并且将复合结构10的内面板24和外面板12连接。将泡沫64插置在空间22和支撑结构44中。在线材以螺旋结构进行构造的情况下使线材66延伸穿过空间42。电源84设置在航天器74的构建中并且连接到线材66。如图8和图12中表征的,线材66围绕内面板24的内表面28延伸并穿过支撑结构44的壁46。多层隔离体72在线材66之上且在支撑结构44的壁46之间延伸。泡沫64在多层隔离体72之上延伸。
图12的方法表征了为航天器构建围绕航天器的内部容积延伸的内面板和围绕内面板延伸的外面板。构建由复合材料构成的外面板,复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组。构建由复合材料构成的内面板,复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组。在外面板与内面板之间提供空间。将支撑结构定位在所述空间中并且将支撑结构连接到外面板和内面板。将泡沫插置到所述空间和支撑结构中。在线材以螺旋结构进行构造的情况下使线材延伸穿过所述空间。将电源连接到线材。
参照图9,表征围绕内面板24延伸的线材66的示意性表征。如图9中表征的,线材66的第一端82连接到电源84,例如连接到电源84的正端子。线材66的第二端86连接到电源84的相对端,例如连接到电源84的负端子。这段从第一端82延伸到第二端86的线材66以螺线形或螺旋结构围绕内面板24的内表面28缠绕。围绕内面板24的线材66的螺线形或螺旋结构的间距的确定是基于:经过线材66的电流所需的电磁场强度、可从电源84获得的功率量、线材66的电阻及影响电磁场强度的其它因素。
线材66提供了为构建有如上文参考图8和图12描述的复合结构10的航天器74屏蔽辐射的方法。如图9和图13中表征的,为航天器74构建围绕航天器的内部容积76延伸的内面板24和围绕内面板24延伸的外面板12,在内面板与外面板之间具有空间42。如图9中表征的,将这段长度的线材66定位在内面板24上,这段长度的线材以螺线形或螺旋结构围绕内面板24延伸。线材66连接到电源84。通过将电流流动从电源84和线材66的第一端82引导到线材66的第二端86,创建了围绕内面板24的磁场。在外面板12与内面板24之间的空间42内创建磁场。在航天器74遭受空间的极端环境78的情况下,创建的磁场排斥辐射,从而为在图8中表征的航天器74屏蔽辐射。屏蔽航天器74的结构的该方法被表征在图13中。
图13的方法表征航天器遭受空间的极端环境,其中为航天器构建围绕航天器的内部容积延伸的内面板和围绕内面板延伸的外面板,在内面板与外面板之间具有空间,并且电导体在所述空间中具有一段长度,这段长度具有相对的第一端和第二端,这段长度的电导体以螺旋结构围绕所述空间延伸。将电流流动引导经过这段长度的电导体。利用经过这段长度的电导体的电流流动在所述空间中创建磁场。利用磁场来排斥辐射,从而为航天器屏蔽辐射。
在需要附加强度和保护的复合结构10的应用中,可采用多层复合结构10。图10表征图1和图2的分层复合结构10,而图11表征图6和图7的分层复合结构10’。
此外,本公开包括根据以下条款的示例:
条款1、一种复合结构(10),所述复合结构(10)包括:
外面板(12),所述外面板(12)由复合材料构成,所述外面板(12)在所述外面板(12)的外表面(14)与所述外面板(12)的内表面(16)之间具有厚度,所述外面板(12)的所述外表面(14)和所述外面板(12)的所述内表面(16)是大致平行的平滑连续表面;
内面板(24),所述内面板(24)由复合材料构成,所述内面板(24)在所述内面板(24)的外表面(26)与所述内面板(24)的内表面(28)之间具有厚度,所述内面板(24)的所述外表面(26)和所述内面板(24)的所述内表面(28)是大致平行的平滑连续表面;
空间(42),所述空间(42)位于所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间;
所述空间(42)中的支撑结构(44),所述支撑结构(44)连接到所述外面板(12)的所述内表面(16)和所述内面板(24)的所述内表面(28);
泡沫(64),所述泡沫(64)被插置到所述空间(42)和所述支撑结构(44)中;以及
线材(66),所述线材(66)延伸穿过所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42),所述线材(66)具有高导电性。
条款2、根据条款1所述的复合结构(10),所述复合结构(10)进一步包括:
隔离体(72),所述隔离体(72)位于所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42)中,所述隔离体(72)是多层隔离体。
条款3、根据条款2所述的复合结构(10),其中:
所述隔离体(72)是隔热的,并且所述隔离体(72)是辐射屏蔽隔离体。
条款4、根据条款1所述的复合结构(10),其中:
所述线材(66)具有延伸穿过所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42)的螺旋结构。
条款5、根据条款1所述的复合结构(10),其中:
所述支撑结构(44)具有由与所述外面板(12)的所述内表面(16)和所述内面板(24)的所述内表面(28)连接的多个壁(46)构成的格子构造,所述多个壁(46)在所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的多个分隔空间(48)之间延伸,所述多个壁(46)将所述多个分隔空间(48)分开;并且
所述泡沫(64)填充所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述多个分隔空间(48)。
条款6、根据条款5所述的复合结构(10),其中:
所述多个壁(46)为所述多个分隔空间(48)中的每个空间均赋予蜂窝构造。
条款7、根据条款5所述的复合结构(10),其中:
所述多个壁(46)为所述多个分隔空间(48)中的每个空间均赋予梯形构造。
条款8、根据条款1所述的复合结构(10),其中:
所述外面板(12)的所述复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组;并且
所述内面板(24)的所述复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组。
条款9、根据条款1所述的复合结构(10),其中:
所述外面板(12)的所述厚度介于0.2cm到2.0cm的范围内;并且
所述内面板(24)的所述厚度介于0.2cm到2.0cm的范围内。
条款10、根据条款9所述的复合结构(10),其中:
所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42)介于5cm到10cm的范围内。
条款11、一种复合结构(10),所述复合结构(10)包括:
外面板(12),所述外面板(12)由复合材料构成,所述外面板(12)在所述外面板(12)的外表面(14)与所述外面板(12)的内表面(16)之间具有厚度,所述外面板(12)的所述外表面(14)和所述外面板(12)的所述内表面(16)是大致平行的平滑连续表面;
内面板(24),所述内面板(24)由复合材料构成,所述内面板(24)在所述内面板(24)的外表面(26)与所述内面板(24)的内表面(28)之间具有厚度,所述内面板(24)的所述外表面(26)和所述内面板(24)的所述内表面(28)是大致平行的平滑连续表面;
空间(42),所述空间(42)位于所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间;
所述空间(42)中的支撑结构(44),所述支撑结构(44)连接到所述外面板(12)的所述内表面(16)和所述内面板(24)的所述内表面(28),所述支撑结构(44)具有由与所述外面板(12)的所述内表面(16)和所述内面板(24)的所述内表面(28)连接的多个壁(46)构成的格子构造,所述多个壁(46)在所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的多个分隔空间(48)之间延伸,所述多个壁(46)将所述多个分隔空间(48)分开;
泡沫(64),所述泡沫(64)填充所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述多个分隔空间(48);以及
线材(66),所述线材(66)延伸穿过所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42),所述线材(66)具有高导电性。
条款12、根据条款11所述的复合结构(10),所述复合结构(10)进一步包括:
隔离体(72),所述隔离体(72)位于所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42)中,所述隔离体(72)是多层隔离体。
条款13、根据条款12所述的复合结构(10),其中:
所述隔离体(72)是隔热的,并且所述隔离体是辐射屏蔽隔离体。
条款14、根据条款11所述的复合结构(10),其中:
所述线材(66)具有延伸穿过所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42)的螺旋结构。
条款15、根据条款11所述的复合结构(10),其中:
所述多个壁(46)为所述多个分隔空间(48)中的每个空间均赋予蜂窝构造。
条款16、根据条款11所述的复合结构(10),其中:
所述多个壁(46)为所述多个分隔空间(48)中的每个空间均赋予梯形构造。
条款17、根据条款11所述的复合结构(10),其中:
所述外面板(12)的所述复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组;并且
所述内面板(24)的所述复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组。
条款18、根据条款11所述的复合结构(10),其中:
所述外面板(12)的所述厚度介于0.2cm到2.0cm的范围内;并且
所述内面板(24)的所述厚度介于0.2cm到2.0cm的范围内。
条款19、根据条款18所述的复合结构(10),其中:
所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42)介于5cm到10cm的范围内。
条款20、一种构建航天器(74)的复合结构的方法,所述方法包括以下步骤:
为航天器(74)构建围绕所述航天器(74)的内部容积延伸的内面板(24)以及围绕所述内面板(24)延伸的外面板(12);
构建由复合材料构成的所述外面板(12),所述复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组;
构建由复合材料构成的所述内面板,所述复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组;
在所述外面板(12)与所述内面板(24)之间提供空间(42);
将支撑结构(44)定位到所述空间(42)中并且将所述支撑结构(44)连接到所述外面板(12)和所述内面板(24);
将泡沫(64)插置到所述空间(42)和所述支撑结构(44)中;以及
在线材(66)以螺旋结构进行构造的情况下使所述线材(66)延伸穿过所述空间(42);以及
将电源(84)连接到所述线材(66)。
条款21、一种为航天器(74)屏蔽辐射的方法,所述方法包括:
使航天器(74)遭受空间的极端环境,其中所述航天器(74)构建有围绕所述航天器(74)的内部容积延伸的内面板(24)和围绕所述内面板(24)延伸的外面板(12),在所述内面板(24)与所述外面板(12)之间具有空间(42);
将具有一段长度且具有相对的第一端(82)和第二端(84)的电导体(66)定位在所述航天器(74)中,具有所述一段长度的所述电导体(66)围绕所述航天器(74)以螺旋结构从所述电导体的所述第一端(82)延伸到所述电导体(66)的所述第二端(84);
从所述电导体(66)的所述第一端(82)到所述电导体(66)的所述第二端(84),将电流引导经过具有所述一段长度的所述电导体(66);
借助于被引导而流过具有所述一段长度的所述电导体(66)的所述电流在所述空间(42)中创建磁场;以及
利用在所述空间(42)中创建的所述磁场来排斥辐射,从而为所述航天器屏蔽辐射。
在不脱离本发明的范围的情况下,可以在本文描述和图示的设备及其操作方法的构建方面做出各种修改,包含在前述描述中或者在附图中示出的所有事物旨在应被解释为说明性的而非限制性的。由此,本公开的宽度和范围不应该受限于任何上述示例性示例,而是应当仅根据随附的所附权利要求书及其等同物来限定。
Claims (12)
1.一种复合结构(10),所述复合结构(10)包括:
外面板(12),所述外面板(12)由复合材料构成,所述复合材料由具有氢含量的多层片材构成,所述氢含量提供辐射防护、隔热以及结构强度,所述外面板(12)在所述外面板(12)的外表面(14)与所述外面板(12)的内表面(16)之间具有厚度,所述外面板(12)的所述外表面(14)和所述外面板(12)的所述内表面(16)是大致平行的平滑连续表面;
内面板(24),所述内面板(24)由复合材料构成,所述复合材料由具有氢含量的多层片材构成,所述氢含量提供辐射防护、隔热以及结构强度,所述内面板(24)在所述内面板(24)的外表面(26)与所述内面板(24)的内表面(28)之间具有厚度,所述内面板(24)的所述外表面(26)和所述内面板(24)的所述内表面(28)是大致平行的平滑连续表面;
空间(42),所述空间(42)位于所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间;
所述空间(42)中的支撑结构(44),所述支撑结构(44)连接到所述外面板(12)的所述内表面(16)和所述内面板(24)的所述内表面(28);
泡沫(64),所述泡沫(64)被插置到所述空间(42)和所述支撑结构(44)中;以及
线材(66),所述线材(66)延伸穿过所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42),所述线材(66)具有高导电性。
2.根据权利要求1所述的复合结构(10),所述复合结构(10)进一步包括:
隔离体(72),所述隔离体(72)位于所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42)中,所述隔离体(72)是多层隔离体。
3.根据权利要求2所述的复合结构(10),其中:
所述隔离体(72)是隔热的,并且所述隔离体(72)是辐射屏蔽隔离体。
4.根据权利要求1至3中的任一项所述的复合结构(10),其中:
所述线材(66)具有延伸穿过所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42)的螺旋结构。
5.根据权利要求1至3中的任一项所述的复合结构(10),其中:
所述支撑结构(44)具有由与所述外面板(12)的所述内表面(16)和所述内面板(24)的所述内表面(28)连接的多个壁(46)构成的格子构造,所述多个壁(46)在所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的多个分隔空间(48)之间延伸,所述多个壁(46)将所述多个分隔空间(48)分开;并且
所述泡沫(64)填充所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述多个分隔空间(48)。
6.根据权利要求5所述的复合结构(10),其中:
所述多个壁(46)为所述多个分隔空间(48)中的每个空间均赋予蜂窝构造。
7.根据权利要求5所述的复合结构(10),其中:
所述多个壁(46)为所述多个分隔空间(48)中的每个空间均赋予梯形构造。
8.根据权利要求1至3中的任一项所述的复合结构(10),其中:
所述外面板(12)的所述复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组;并且
所述内面板(24)的所述复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组。
9.根据权利要求1至3中的任一项所述的复合结构(10),其中:
所述外面板(12)的所述厚度介于0.2 cm到2.0 cm的范围内;并且
所述内面板(24)的所述厚度介于0.2 cm到2.0 cm的范围内。
10.根据权利要求9所述的复合结构(10),其中:
所述外面板(12)的所述内表面(16)与所述内面板(24)的所述内表面(28)之间的所述空间(42)介于5 cm到10 cm的范围内。
11.一种构建航天器(74)的复合结构的方法,所述方法包括以下步骤:
为航天器(74)构建围绕所述航天器(74)的内部容积延伸的内面板(24)以及围绕所述内面板(24)延伸的外面板(12);
构建由复合材料构成的所述外面板(12),所述复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组,所述复合材料由具有氢含量的多层片材构成,所述氢含量提供辐射防护、隔热以及结构强度;
构建由复合材料构成的所述内面板,所述复合材料选自包括Kevlar 49、玻璃纤维、碳化硼、光谱纤维、Nextel织物、石墨/环氧树脂织物、光谱纤维/聚乙烯、石墨/环氧树脂带和石墨/光谱/高密度聚乙烯层压物的组,所述复合材料由具有氢含量的多层片材构成,所述氢含量提供辐射防护、隔热以及结构强度;
在所述外面板(12)与所述内面板(24)之间提供空间(42);
将支撑结构(44)定位到所述空间(42)中并且将所述支撑结构(44)连接到所述外面板(12)和所述内面板(24);
将泡沫(64)插置到所述空间(42)和所述支撑结构(44)中;以及
在线材(66)以螺旋结构进行构造的情况下使所述线材(66)延伸穿过所述空间(42);以及
将电源(84)连接到所述线材(66)。
12.一种为航天器(74)屏蔽辐射的方法,所述方法包括:
使航天器(74)遭受空间的极端环境,其中所述航天器(74)构建有围绕所述航天器(74)的内部容积延伸的内面板(24)和围绕所述内面板(24)延伸的外面板(12),在所述内面板(24)与所述外面板(12)之间具有空间(42);
构建由复合材料构成的所述内面板,所述复合材料由具有氢含量的多层片材构成,所述氢含量提供辐射防护、隔热以及结构强度;
构建由复合材料构成的所述外面板,所述复合材料由具有氢含量的多层片材构成,所述氢含量提供辐射防护、隔热以及结构强度;
将具有一段长度且具有相对的第一端(82)和第二端(84)的电导体(66)定位在所述航天器(74)中,具有所述一段长度的所述电导体(66)围绕所述航天器(74)以螺旋结构从所述电导体的所述第一端(82)延伸到所述电导体(66)的所述第二端(84);
从所述电导体(66)的所述第一端(82)到所述电导体(66)的所述第二端(84),将电流引导经过具有所述一段长度的所述电导体(66);
借助于被引导而流过具有所述一段长度的所述电导体(66)的所述电流在所述空间(42)中创建磁场;以及
利用在所述空间(42)中创建的所述磁场来排斥辐射,从而为所述航天器屏蔽辐射。
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