CN101268302A - 用于低温液体的动力燃料容器 - Google Patents
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Abstract
在尤其是用于储存例如空间飞行器的低温动力燃料并且用一种作为输送介质使用的驱动气体工作的动力燃料容器中,在动力燃料取出装置中动力燃料与驱动气体的分离借助于筛并且在利用静压力和毛细力的情况下进行。取出装置具有可重复充注的储备器的形式,该储备器在动力燃料容器的底部区域上在容器壳外部安置在容器底部附近并且该储备器通过多个洞与动力燃料容器的内部相连接。取出装置本身包括一个双壁的壳体并且附加地被隔热。毛细板和附加的加固部以L形状安置在储备器中。另外,为了在很大程度上抑制气体从动力燃料管路进入,在动力燃料管路的端部上安置有一个圆柱状的打褶的筛。
Description
本发明涉及一种动力燃料容器、尤其是用于储存空间飞行器工作所用的低温液体的容器,具有一种作为输送介质使用的驱动气体以及具有呈可重复充注的储备器形式的至少一个取出装置,在所述动力燃料容器中在利用表面张力的情况下引起动力燃料与驱动气体的分离。
在空间飞行器中,驱动气体经常用于将动力燃料从动力燃料容器输送到燃烧室或反应室。对于低温液体,作为驱动气体通常使用氦(He),氦对动力燃料罐加载并且氦由此将动力燃料压到通到各自的发动机的管道系统中。在例如由DE 101 17 557 A1公知的这种容器中重要的是在此作为输送介质使用的驱动气体与到达发动机中的动力燃料之间的完全且可靠的分开,因为所述动力燃料在其点火时必须绝对不夹杂外界气体。
由于在重量较小的同时其效率较高,低温动力燃料可能优于传统的液态动力燃料,例如MMH。但在低温动力燃料中不利的影响是,与传统的动力燃料不同,这种低温动力燃料不能在室温下储存。也被称为LH2的液态氢例如在约30K的温度时转变到气态,由此,动力燃料容器的足够的隔热是必要的,以便保证足够时间段上的储存能力。类似情况也适用与LH2一同使用并且储存在分开的容器中的液态氧(LOX)。由于主要通过太阳辐射和热部件例如发动机造成的热量引入,在储存时间较长的情况下动力燃料容器的隔热是必要的。
与使用能储存的非低温动力燃料不同,在低温动力燃料中,通常较热的容器壁可导致在容器壁附近液体沸腾,由此使无气泡的动力燃料输送变难。因此,尤其是构成取出装置的储备器的用于避免在储备器内部形成气体的隔热和设置在储备器中的引导板的构型对这种容器提出了特别的要求。这些引导板在此这样设置在储备器内部,使得液体在储备器中稳定地定位并且气体泡从储备器被驱出返回到容器中。通过毛细压力的局部变化支持这种保持作用。
一个附加问题是在失重状态下无气泡的动力燃料输送。无气泡的动力燃料输送例如可以通过借助于所携带的辅助火箭的预加速度来实现。该预加速度于是引起液体在排出管附近的重新定向和定位。点火过程在此首先包括:将管路系统冷却到工作温度的冷却阶段接着进行发动机的真正点火阶段。在冷却阶段,最大程度上冷的液态动力燃料从动力燃料容器输送到管路系统中。并且对于该冷却阶段,本发明也可以不受限制地提供动力燃料。仅当在冷却到工作温度之后整个系统无气泡时才进行发动机的点火。
本发明的任务在于,这样构造开头所述类型的动力燃料容器,使得该动力燃料容器在使用低温动力燃料时除了预加速度外通过利用静压力以及毛细力保证无气泡的动力燃料输送。
本发明通过一种动力燃料容器来解决该任务,在该动力燃料容器中,取出装置设置在容器壁的外侧上的下部区域中。该储备器通过容器壁中的优选圆形的开口与动力燃料容器的内部相连接,由此,液体可流动到储备器中。
在本发明的优选实施形式中,储备器设置有一个隔热装置以及一个热量捕集器并且由此尤其适用于环形的容器以及具有中间底部的容器,这种容器以类似形式例如作为LH2容器用于或者将来用于Ariane 5的低温末级ESC-A中或计划的ESC-B中。
在根据本发明的动力燃料容器中设置的取出装置的构型在此具有优点:该取出装置即使在绕容器纵轴线的旋转率非常高的情况下也能够给装备有这种容器的火箭级输送动力燃料。因此,即使在该级的非正常特性的情况下也保证可靠的动力燃料输送。已经完全组装好后,可以在一个分开的测试台中来检验根据本发明的取出装置。另外,在动力燃料容器内部不需要其它构件,而是将取出装置作为分开的构件在外部安置在容器壁上。在大容器中,如在Ariane 5的ESC-A LH2容器中,容器壳通常由几个区段组成,由此,在容器壳组装好之前可以将储备器压入到这些区段中的一个中。
放弃预加速度并且由此放弃携带分开的辅助火箭可实现附加的重量节省并且因此可实现在多次再点火时较高的有效负荷。储备器保证动力燃料在排出口处稳定地定位并且不限制再点火的次数,在容器中的剩余充填度非常小的情况下也不限制。因此,可能的再点火的次数仅仅取决于相应所需的动力燃料量。根据本发明的容器在此以相同方式不仅适用于保存低温动力燃料、如LH2,而且适用于保存LOX形式的液态氧。
下面要借助于附图中所示的实施例对根据本发明的动力燃料容器进行详细说明。附图表示:
图1具有取出装置的LH2动力燃料容器的一个局部,
图2根据图1的取出装置,从上面观察并且在筛适配器的区域中被剖开,
图3根据图1和图2的取出装置的一个局部的三维视图,以及
图4根据图1至图3的取出装置内部的排出管的一个局部,该排出管构造成所谓的热管。
在图1中以部分剖面示出的动力燃料容器涉及一种用于接收和储存低温动力燃料的、作为环形容器子元件的容器,该容器如以类似形式例如构成Ariane 5火箭当前的末级ESC-A中的LH2容器的下部分。一般来说,环形容器的特征在于:四个动力燃料容器共同构成一个环形形状,这四个动力燃料容器中每两个用于LH2,每两个用于LOX。在这种容器实施形式中,在此所示的实施例对于每个动力燃料容器使用一个分开的排出口。
图1中所示的动力燃料容器包括两个半壳1和1′,这些半壳彼此相连接并且这些半壳形成一个环形的接收罐7。在这两个半壳1和1′的连接区域中,容器壁由此形成非常强的弯曲,由此在失重状态下液体优选聚集在该区域中。此外,在该区域中毛细压差特别高,由此产生在朝该角部的方向上的泵作用。动力燃料容器的该区域因此特别好地适合在此设置一个呈可重复充注的储备器2形式的取出装置,如图1中所示。
为了即使在具有高旋转率的飞行阶段期间也保证无缺点的输送,储备器2这样从外部安置在容器壁1′上,使得液体即使在纯自旋负荷下也优选聚集在该储备器2中。储备器2构造成双壁的,以便使到储备器2中的热量引入降低到最低程度,如下面还要详细描述的那样。
动力燃料从储备器2经由一个设置有折皱的、即“打褶的”筛3被抽吸出来。该筛不仅具有污物筛的功能而且具有气泡捕集器的功能,该气泡捕集器在最大程度上抑制气体从在长时间弹道阶段期间充注有蒸汽的动力燃料管路4进入到储备器2中。动力燃料管路4也被称为排出管,该动力燃料管路根据图3位于储备器2外部,通到该储备器中并且终止在筛适配器3上。从动力燃料管路4到储备器2中,进入的气体通过设置在储备器2中的板5和6导出到动力燃料容器的接收罐7中。由此保证在弹道阶段期间筛3被润湿。为了保证通过筛3的足够高的通流率,筛面必须尽可能大。出于该原因,如在图2中可看到的那样,两个圆柱形的具有星形横截面的、也被称为打褶的筛元件17在排出管4的左侧和右侧安置在储备器2内部。排出管4在其在储备器2内部延伸的部分区域中构造成所谓的热管并且具有一个设置有纵向槽的外表面。由此,进入的热量被更好地从管4释放给液体。在图4中用参考标号15标记的在管壁上蒸发的液体被由于有效毛细力而在后流动的液体所代替,由此,该区域中的表面又被润湿并且管表面的干燥得到避免;同时,通过该过程使热量从管4导出。沿着管4在朝筛适配器3的方向上的热量引入由此减小。此外,在真正的再点火之前实施的冷却阶段中,管必须不太强地冷却下来。
为了使进入的残余热量降低到最低程度,储备器2构造成双壁的和真空隔热的,如图1中可看到的那样。由于约为3bar的较高的容器内部压力,出于结构原因,储备器2构造成壳元件。在起动之前,出于更好隔热的目的,可以在底部上连接一个真空泵,该真空泵可在该阶段期间在底部上工作并且在起动前不久被截断。此外,在储备器2的构造成双壁的壁8内部设置有一个所谓多层隔热结构(MLI)形式的附加的多层隔热装置,该多层隔热结构对辐射热进行隔热。此外,储备器2从外部附加地被隔热泡沫材料9隔热。
在储备器2内部,如图3中可看到的那样,与储备器壁间隔开约六至八毫米安置有一个L形的板6。该板6中的钻孔在此可实现该板被穿流。垂直的横向肋5加强L形的板6并且附加地促进气体从储备器2被驱出。根据图2,横向肋5朝容器彼此相对稍微锥状地安置。由此实现的毛细作用附加地支持气体或蒸汽从储备器2被驱出。打褶的筛3位于L形的板6的转角中,该打褶的筛通过两个垂直的端部板并且通过排出管4与L形的板6相连接。
板6通过距离保持件14与内部的储备器壁10相连接。这些距离保持件14位于与打褶的筛3最大可能的距离处,以便使筛3在热方面更好地与热的容器壁1、1′脱耦。此外,距离保持件14这样制造,使得这些距离保持件保证储备器壁8与L形的板6之间的最佳隔热。
筛3一方面通过储备器壁8、另一方面通过类似于圆柱局部的形式的加工有洞的板11限定边界。这由于其毛细作用而促进筛3被重复润湿。产生的气体泡通过内部的储备器壁10与L形的板6之间的缝隙从储备器2被驱回到动力燃料容器的接收罐7中。
容器壁1′中的到储备器2的优选圆形或椭圆形的开口12、13允许不仅液体而且气体在这两个区域之间交换。气体或蒸汽可通过这些开口返回到动力燃料容器的接收罐7中,并且来自动力燃料容器的接收罐7的液体可补充气体体积。在此,如其直径与排出管4的直径大致相应的多个较大的开口12设置在储备器2的下部区域和上部区域中,多个较小的开口13设置在储备器2的中间部分中。
Claims (11)
1.动力燃料容器、尤其是用于储存空间飞行器工作所用的低温液体的容器,具有一种作为输送介质使用的驱动气体以及具有呈可重复充注的储备器形式的至少一个取出装置,在所述动力燃料容器中在利用表面张力以及静压力的情况下引起动力燃料与驱动气体的分离,其特征在于:所述取出装置(2)设置在容器壁(1′)的外侧上的下部区域中。
2.根据权利要求1所述的动力燃料容器,其特征在于:所述储备器(2)构造成双壁的和真空隔热的。
3.根据权利要求2所述的动力燃料容器,其特征在于:所述储备器(2)在真空区域中附加地被一个多层隔热膜屏蔽。
4.根据权利要求1至3中一项所述的动力燃料容器,其特征在于:所述储备器(2)被隔热泡沫材料(9)对外屏蔽。
5.根据权利要求1至4中一项所述的动力燃料容器,其特征在于:在该容器壁(1′)中设置有一些钻孔(12,13)作为到所述储备器(2)的连接装置。
6.根据权利要求1至5中一项所述的动力燃料容器,其特征在于:在所述储备器(2)中设置有一个锥状的近似L形的板(6),在该板的转角中设置有一个圆柱局部形式的被裁切出的板(11)。
7.根据权利要求6所述的动力燃料容器,其特征在于:这些板(6,11)设置有一些洞。
8.根据权利要求6或7所述的动力燃料容器,其特征在于:一个圆柱状的且打褶的筛(3)借助于一些端部板在右侧和左侧以及附加地在一个排出管(4)的区域中固定在该L形的板(6)上。
9.根据权利要求7所述的动力燃料容器,其特征在于:多个板(5)锥状地安置在该L形的板(6)上,其中,所述多个板不具有与容器壁(1)的接触。
10.根据权利要求7所述的动力燃料容器,其特征在于:用于固定这些板(6,11)的保持支撑点(14)设置在与作为取出部位起作用的筛(3)的最大距离处。
11.根据权利要求1所述的动力燃料容器,其特征在于:该排出管(4)在其在所述储备器(2)内部延伸的区域中构造成热管并且在其外表面上设置有一些纵向沟。
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DE102005044534A DE102005044534B3 (de) | 2005-09-17 | 2005-09-17 | Treibstofftank für kryogene Flüssigkeiten |
PCT/DE2006/001605 WO2007031064A1 (de) | 2005-09-17 | 2006-09-13 | Treibstofftank für kryogene flüssigkeiten |
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- 2005-09-17 DE DE102005044534A patent/DE102005044534B3/de not_active Expired - Fee Related
-
2006
- 2006-09-13 BR BRPI0616028-0A patent/BRPI0616028A2/pt active Search and Examination
- 2006-09-13 US US11/922,810 patent/US8381938B2/en active Active
- 2006-09-13 ES ES06805282T patent/ES2414059T3/es active Active
- 2006-09-13 DE DE112006003074T patent/DE112006003074A5/de not_active Withdrawn
- 2006-09-13 JP JP2008530321A patent/JP4934672B2/ja active Active
- 2006-09-13 CN CN2006800340327A patent/CN101268302B/zh not_active Expired - Fee Related
- 2006-09-13 EP EP06805282.8A patent/EP1924804B1/de active Active
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103134395A (zh) * | 2011-11-25 | 2013-06-05 | 阿斯特利乌姆有限公司 | 具有液体驱动系统的火箭级 |
US9347400B2 (en) | 2011-11-25 | 2016-05-24 | Astrium Gmbh | Rocket stage having engine thrust frame integrated with tank |
CN110177972A (zh) * | 2016-12-26 | 2019-08-27 | 气体运输技术公司 | 一种用于储存流体的密封隔热罐 |
CN110177972B (zh) * | 2016-12-26 | 2021-04-16 | 气体运输技术公司 | 一种用于储存流体的密封隔热的罐 |
Also Published As
Publication number | Publication date |
---|---|
CN101268302B (zh) | 2010-08-18 |
DE102005044534B3 (de) | 2007-06-06 |
EP1924804B1 (de) | 2013-04-10 |
US20090134170A1 (en) | 2009-05-28 |
DE112006003074A5 (de) | 2008-09-11 |
WO2007031064A1 (de) | 2007-03-22 |
JP2009507705A (ja) | 2009-02-26 |
JP4934672B2 (ja) | 2012-05-16 |
ES2414059T3 (es) | 2013-07-18 |
BRPI0616028A2 (pt) | 2011-06-07 |
EP1924804A1 (de) | 2008-05-28 |
US8381938B2 (en) | 2013-02-26 |
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