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    Liquid-propellant management apparatus
    1.
    发明授权
    Liquid-propellant management apparatus 失效
    液体推进剂管理装置

    公开(公告)号：US4901762A

    公开(公告)日：1990-02-20

    申请号：US251736

    申请日：1988-10-03

    Applicant: John A. Miller, Jr. ,  R. K. Grove

    Inventor： John A. Miller, Jr. ,  R. K. Grove

    IPC: B64G1/40 ,  F17C13/00

    CPC classification number: B64G1/402 ,  F17C13/008 ,  F17C2201/0109 ,  F17C2201/0166 ,  F17C2203/012 ,  F17C2205/0397 ,  F17C2250/075 ,  F17C2260/016 ,  F17C2270/0197 ,  Y10T137/86212 ,  Y10T137/86348

    Abstract: A liquid-propellant tank for a spacecraft is symmetric about a longitudinal axis, and has a transverse partition (15) and a truncated conical partition (16), which divide the interior of the tank into a remote chamber (20), a proximate peripheral chamber (21) and a proximate axial chamber (22). Communication between the remote chamber (20) and the proximate peripheral chamber (21) is provided by a port structure (23), and communication between the proximate peripheral chamber (21) and the proximate axial chamber (22) is provided by a port structure (24). As liquid propellant is withdrawn from the tank, pressurant gas in the remote chamber (20) causes liquid propellant to pass from the remote chamber (20) into the proximate peripheral chamber (21) to replace liquid propellant thereby forced from the proximate peripheral chamber (21) into the proximate axial chamber (22), which replaces the liquid propellant withdrawn from the tank. Emptying of the three chambers in sequence limits the extent of migration of liquid propellant within the tank, thereby minimizing the effects of liquid-propellant migration on attitude stability of the spacecraft.

    Abstract translation: 用于航天器的液体推进剂罐关于纵向轴线对称，并且具有横向分隔件（15）和截头圆锥形分隔件（16），其将罐的内部分成远程室（20），邻近的外围 室（21）和邻近的轴向室（22）。 远程室（20）和邻近周边室（21）之间的通信由端口结构（23）提供，并且邻近的外围室（21）和邻近轴向室（22）之间的连通由端口结构 （24）。 当液体推进剂从罐中取出时，远程室（20）中的加压气体使得液体推进剂从远程室（20）进入邻近的周边室（21），以更换液体推进剂，从而迫使其从邻近的外围室 21）进入邻近的轴向室（22），其代替从罐排出的液体推进剂。 这三个舱室依次排空限制了液体推进剂在罐内的迁移程度，从而使液体推进剂迁移对航天器姿态稳定性的影响最小化。

    Flow management apparatus for cryogenic liquid
    3.
    发明授权
    Flow management apparatus for cryogenic liquid 失效
    低温液体流量管理装置

    公开(公告)号：US5263329A

    公开(公告)日：1993-11-23

    申请号：US812145

    申请日：1991-12-23

    Applicant: R. K. Grove ,  Ronald W. King ,  Julie M. L'Heureux

    Inventor： R. K. Grove ,  Ronald W. King ,  Julie M. L'Heureux

    IPC: F17C9/00 ,  F17C13/00 ,  F28D15/04 ,  F17C7/02

    CPC classification number: F17C13/008 ,  F17C9/00 ,  F28D15/04 ,  F17C2201/0109 ,  F17C2209/221 ,  F17C2221/011 ,  F17C2221/012 ,  F17C2223/0161 ,  F17C2250/0636 ,  F17C2260/027 ,  F17C2270/0197 ,  Y02E60/321 ,  Y10S220/901 ,  Y10T137/86348

    Abstract: In a tank 10 for cryogenic liquid to be used in a low-gravity environment (e.g., on a space vehicle), a liquid transfer apparatus 15 (which comprises an elongate array of fins 32 and a sponge structure formed from panels 31) functions to transfer cryogenic liquid from the interior of the tank 10 to a bowl structure 20 defining a reservoir region adjacent an outlet of the tank 10. A perforated plate 22 disposed between the sponge structure and the outlet of the tank 10 causes cryogenic liquid to pass through the outlet into an outlet line 40 in a regular and generally unbroken flow. To prevent any substantial amount of heat transfer into the reservoir region of the tank 10, the bowl structure 20 is separated from the inner surface of the tank 10 by a capillary distance in order to provide a thermally insulating space therebetween. A well for cryogenic fluid, which is in communication with the thermally insulating space between the bowl structure 20 and the inner surface of the tank 10, is formed around an outlet duct 21 leading from the bowl structure 20 in order to prevent any significant transfer of heat into cryogenic liquid that is being withdrawn from the tank 10 through the outlet duct 21.

    Abstract translation: 在用于低重力环境（例如，在太空车上）的低温液体的罐10中，液体输送装置15（其包括细长的翅片阵列32和由板31形成的海绵结构）用于 将低温液体从罐10的内部转移到限定与罐10的出口相邻的储存区域的碗形结构20.设置在海绵结构和罐10的出口之间的多孔板22使低温液体通过 出口到出口管线40中，其规则且通常不间断的流动。 为了防止任何大量的热传递到罐10的储存区域中，碗结构20与罐10的内表面分离毛细管距离，以便在其间提供隔热空间。 与碗结构20和罐10的内表面之间的绝热空间连通的低温流体的井形成在从碗结构20通向的出口导管21周围，以防止任何显着的转移 热量进入通过出口管道21从罐10抽出的低温液体。

    Liquid-propellant management system with capillary pumping vanes
    4.
    发明授权
    Liquid-propellant management system with capillary pumping vanes 失效
    具有毛细管抽吸叶片的液体推进剂管理系统

    公开(公告)号：US4733531A

    公开(公告)日：1988-03-29

    申请号：US839831

    申请日：1986-03-14

    Applicant: R. K. Grove

    Inventor： R. K. Grove

    IPC: F02K9/44 ,  F02K9/00 ,  E03B11/00 ,  F17D1/00

    CPC classification number: F02K9/44 ,  Y10T137/2931 ,  Y10T137/86348

    Abstract: In a liquid-propellant management system for providing substantially gas-free liquid propellant to thrusters of a space vehicle, a storage tank (10) has an opening (11) through which liquid propellant is delivered via a line (13) to the thrusters. A trap (14) is secured within the tank (10) adjacent the opening (11). and an exit port (15) of the trap (14) is aligned with the opening (11) of the tank (10). A liner (16) is secured inside the trap(14) to define a volume between an interior surface portion of the trap (14) and the liner (16), which volume communicates via the exit port (15) and the opening (11) with the line (13). Liquid propellant enters into the trap (14) through an inlet window screen (27), and passes through porous windows (28) in the liner (16) into the volume between the trap (14) and the liner (16). Vanes (19) are secured to the exterior surface of the trap (14) and extend into the interior of the tank (14) and the liner (16). Vanes (19) are secured to the exterior surface of the trap (14) and extend into the interior of the tank (10). An elongate edge of each vane (19) is spaced apart from the interior wall of the tank (10) by a capillary distance. As the tank (10) approaches an empty status, liquid propellant collected on the interior wall of the tank (10) spreads to the capillary spacings between the interior wall of the tank (10) and the elongate edges of the vanes (19). The liquid propellant is pumped by capillary action between the vanes (19) and the interior wall of the tank (10) to the exterior surface of the trap (14).

    Abstract translation: 在用于向空间车辆的推进器提供基本上无气体的液体推进剂的液体推进剂管理系统中，储罐（10）具有开口（11），液体推进剂经由管线（13）被输送到推进器。 捕集器（14）固定在与开口（11）相邻的罐（10）内。 并且所述捕集器（14）的出口（15）与所述罐（10）的所述开口（11）对准。 衬套（16）固定在所述收集器（14）内以限定所述收集器（14）的内表面部分和所述衬套（16）之间的体积，所述容积通过所述出口（15）和所述开口（11）连通 ）与线（13）。 液体推进剂通过入口窗口（27）进入捕集器（14），并穿过衬套（16）中的多孔窗口（28）进入捕集器（14）和衬套（16）之间的体积。 叶片（19）固定到捕集器（14）的外表面并延伸到罐（14）和衬套（16）的内部。 叶片（19）固定到捕集器（14）的外表面并延伸到罐（10）的内部。 每个叶片（19）的细长边缘通过毛细管距离与罐（10）的内壁间隔开。 当罐（10）接近空状态时，收集在罐（10）的内壁上的液体推进剂扩散到罐（10）的内壁和叶片（19）的细长边缘之间的毛细管间隔。 液体推进剂通过叶片（19）和罐（10）的内壁之间的毛细管作用泵送到捕集器（14）的外表面。

    Liquid-propellant management system for rockets and space vehicles
    6.
    发明授权
    Liquid-propellant management system for rockets and space vehicles 失效
    火箭和太空车液体推进剂管理系统

    公开(公告)号：US4715399A

    公开(公告)日：1987-12-29

    申请号：US665657

    申请日：1984-10-29

    Applicant: Don E. Jaekle, Jr. ,  R. K. Grove

    Inventor： Don E. Jaekle, Jr. ,  R. K. Grove

    IPC: B64G1/40 ,  F02K9/50 ,  B64G1/00

    CPC classification number: F02K9/50 ,  B64G1/402 ,  Y10T137/3127 ,  Y10T137/86212 ,  Y10T137/86228 ,  Y10T137/86348

    Abstract: A system for providing substantially gas-free liquid propellant to the engine(s) of a rocket or space vehicle comprises a storage tank (10) having a first opening (15) that communicates with a "fill, drain and feed" line (17) and a second opening (18) that communicates with a "pressurant and vent" line (20). A hollow trap (13) having a porous inlet window (22) and an exit port (21), which is aligned with the first opening (15), is positioned within the tank (10). A liner (14) having a plurality of porous windows (24) is positioned inside the trap (13), and is secured to the trap (13) circumjacent the inlet window (22) and circumjacent the exit port (21), but is elsewhere spaced apart from the interior wall of the trap (13). The inlet window (22) of the trap (13) and the porous windows (24) of the liner (14) have pores dimensioned to permit passage of liquid propellant therethrough, and to maintain a film of liquid propellant across each pore by surface tension when liquid propellant is not passing therethrough. The films of liquid propellant in the pores of the windows (22) and (24) act as a barrier to the passage of gas therethrough.

    Abstract translation: 一种用于向火箭或空间车辆的发动机提供基本上无气体的液体推进剂的系统包括具有与“填充，排出和进料”管线（17）连通的第一开口（15）的储罐（10） ）和与“加压和排气”管线（20）连通的第二开口（18）。 具有与第一开口（15）对准的多孔入口窗（22）和出口（21）的空心阱（13）位于罐（10）内。 具有多个多孔窗口（24）的衬套（14）位于所述收集器（13）的内部，并且在所述入口窗（22）的周围并且邻近所述出口（21）固定到所述收集器（13），但是 在距离陷阱（13）的内壁隔开的位置处。 捕集器（13）的入口窗口（22）和衬套（14）的多孔窗口（24）具有孔尺寸以允许液体推进剂通过其中，并且通过表面张力保持液体推进剂的膜穿过每个孔 当液体推进剂不通过其时。 窗口（22）和（24）的孔中的液体推进剂的膜用作气体通过其的通道的屏障。

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