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22 条记录 (耗时 0.012 秒)

    Satellite propulsion and power system
    5.
    发明授权
    Satellite propulsion and power system 失效
    卫星推进和电力系统

    公开(公告)号：US5417049A

    公开(公告)日：1995-05-23

    申请号：US748990

    申请日：1991-08-21

    申请人： Robert L. Sackheim ,  Dale L. Hook ,  Gary W. Joseph

    发明人： Robert L. Sackheim ,  Dale L. Hook ,  Gary W. Joseph

    IPC分类号： B64G1/40 ,  B64G1/00 ,  B64G1/24 ,  B64G1/26 ,  F02K9/42 ,  F02K9/44 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68 ,  F02K9/28

    CPC分类号： F02K9/42 ,  B64G1/401 ,  B64G1/402 ,  B64G1/406 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68 ,  B64G1/007 ,  B64G1/242 ,  B64G1/26

    摘要： In the preferred embodiment of the invention, a cooled bipropellant thruster 70 for controlling the on-orbit position and orientation of a spacecraft is provided. The cooled bipropellant thruster 70 uses a liquid fuel and liquid oxidizer. The liquid fuel is decomposed in a first chamber 72 with a catalytic bed of decomposition material 74 and produces at least one reaction gas, which flows to the second reaction chamber 90. The second reaction chamber 90 is heated by the reaction gas, but is cooled by liquid oxidizer flowing through cooling passages 92, 94, 98, and 102, which brings the oxidizer into a heat exchange relationship with the second reaction chamber 90. During the heat exchange relationship, heat is transferred from the second reaction chamber 90 to the oxidizer and the oxidizer transforms into a gas. The gaseous oxidizer is fed into a second reaction chamber 90 to secondarily react with the reaction gas.

    摘要翻译： 在本发明的优选实施例中，提供了用于控制航天器的在轨位置和取向的冷却双组元推进器推进器70。 冷却的双组元推进剂推进器70使用液体燃料和液体氧化剂。 液体燃料在分解材料74的催化床的第一室72中分解，并产生至少一个流到第二反应室90的反应气体。第二反应室90被反应气体加热，但被冷却 通过液体氧化剂流过冷却通道92,94,98和102，其使氧化剂与第二反应室90成热交换关系。在热交换关系期间，热量从第二反应室90转移到氧化剂 氧化剂转化为气体。 将气态氧化剂进料到第二反应室90中以与反应气体二次反应。

    High-performance dual-mode integral propulsion system
    6.
    发明授权
    High-performance dual-mode integral propulsion system 失效
    高性能双模整体推进系统

    公开(公告)号：US5282357A

    公开(公告)日：1994-02-01

    申请号：US511153

    申请日：1990-04-19

    申请人： Robert L. Sackheim

    发明人： Robert L. Sackheim

    IPC分类号： B64G1/00 ,  B64G1/24 ,  B64G1/26 ,  B64G1/40 ,  F02K9/42 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68 ,  F02K9/44

    CPC分类号： F02K9/42 ,  B64G1/401 ,  B64G1/402 ,  B64G1/406 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68 ,  B64G1/007 ,  B64G1/242 ,  B64G1/26

    摘要： A propulsion system in which pure hydrazine is used as the fuel for both a bipropellant rocket engine for high-thrust performance and in multiple monopropellant thrusters for station keeping and attitude control functions. Use of a common fuel for both modes of operation significantly reduces propellant weight and inert propulsion system weight for any given mission requirements, and therefore increases the payload that can be delivered to and maintained in a desired orbit. Further, for station-keeping, the monopropellant thrusters can be augmented in performance by employing either electrothermal or additional direct chemical energy, arc jet operation, or force field acceleration, to provide increased specific impulse values up to 2,000 seconds or higher.

    摘要翻译： 一种推进系统，其中使用纯肼作为用于高推力性能的双组元推进剂火箭发动机的燃料和用于站保持和姿态控制功能的多个单推进剂推进器。 对于任何给定的任务要求，对于这两种操作模式使用普通燃料都显着地减少了推进剂重量和惰性推进系统的重量，因此增加了可以输送到并保持在所需轨道中的有效载荷。 此外，对于驻车保持，可以通过采用电热或附加的直接化学能，电弧喷射操作或力场加速来增加单组元推进器的性能，以提供高达2,000秒或更高的增加的比冲量。

    Liquid propellant rocket engine turbopump drain
    8.
    发明授权
    Liquid propellant rocket engine turbopump drain 有权

    公开(公告)号：US11333074B2

    公开(公告)日：2022-05-17

    申请号：US16316703

    申请日：2017-07-26

    申请人： Aerojet Rocketdyne, Inc.

    发明人： Neil H. Orr

    IPC分类号： F02K9/54 ,  F02C7/232 ,  F02K9/48 ,  F01D25/32 ,  F02C7/22

    摘要： A liquid propellant rocket engine includes a pump that is disposed along a central axis. The pump includes a purge system, a collection annulus in fluid communication with the purge system, and a drain. The collection annulus has an outer diameter wall, an inner diameter wall, and an end wall. The end wall defines an annular channel that has a channel depth that varies circumferentially. The drain opens to the collection annulus. At the drain, the annular channel has a lowest point at which the channel depth is maximum depth.