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    Closed electron drift plasma thruster with a steerable thrust vector
    1.
    发明授权
    Closed electron drift plasma thruster with a steerable thrust vector 有权
    闭合电子漂移等离子体推进器，具有可控推力矢量

    公开(公告)号：US06279314B1

    公开(公告)日：2001-08-28

    申请号：US09474546

    申请日：1999-12-29

    申请人： Dominique Valentian ,  Eric Klinger ,  Michel Lyszyk

    发明人： Dominique Valentian ,  Eric Klinger ,  Michel Lyszyk

    IPC分类号： F03H100

    CPC分类号： F03H1/0075

    摘要： The thruster comprises, on a common plate, a plurality of main annular ionization and acceleration channels having axes that are not parallel and that converge in the outlet direction of the channels. A magnetic circuit sets up a magnetic field in the annular channels. The thruster also has a hollow cathode, a device for regulating the ionizable gas feed rate to each annular channel, and a device for controlling the ion discharge acceleration current in the channels. The direction of the thrust vector of the thruster can be controlled without significantly increasing the mass of the thruster.

    摘要翻译： 推进器在公共板上包括多个主环形电离和加速通道，其具有不平行的轴线并且在通道的出口方向上会聚。 磁路在环形通道中设置磁场。 推进器还具有中空阴极，用于调节每个环形通道的可电离气体进料速率的装置，以及用于控制通道中的离子放电加速电流的装置。 可以控制推进器推力矢量的方向，而不会显着增加推进器的质量。

    Closed electron drift plasma thruster adapted to high thermal loads
    2.
    发明授权
    Closed electron drift plasma thruster adapted to high thermal loads 有权
    闭合电子漂移等离子体推进器适用于高热负荷

    公开(公告)号：US06281622B1

    公开(公告)日：2001-08-28

    申请号：US09378795

    申请日：1999-08-23

    申请人： Dominique Valentian ,  Jean-Pierre Bugeat ,  Eric Klinger

    发明人： Dominique Valentian ,  Jean-Pierre Bugeat ,  Eric Klinger

    IPC分类号： H01J2702

    CPC分类号： F03H1/0075 ,  F03H1/0031 ,  H05H1/54

    摘要： The closed electron drift plasma thruster uses a magnetic circuit to create a magnetic field in a main annular channel for ionization and acceleration, said magnetic circuit comprises: an essentially radial first outer pole piece; a conical second outer pole piece; an essentially radial first inner pole piece; a conical second inner pole piece; a plurality of outer magnetic cores surrounded by outer coils to interconnect the first and second outer pole pieces; an axial magnetic core surrounded by a first inner coil and connected to the first inner pole piece; and a second inner coil placed upstream from the outer coils. The thruster also comprises a plurality of radial arms included in the magnetic circuit, and a structural base which is separate from the magnetic circuit and which serves, amongst other things, to cool the coils.

    摘要翻译： 闭合电子漂移等离子体推进器使用磁路在主环形通道中产生用于电离和加速的磁场，所述磁路包括：基本上径向的第一外极片; 锥形第二外极片; 基本上是径向的第一内极片; 锥形第二内极片; 由外部线圈包围的多个外部磁芯，用于互连第一和第二外部极片; 由第一内部线圈包围并连接到第一内部极靴的轴向磁芯; 以及设置在外部线圈上游的第二内部线圈。 推进器还包括包括在磁路中的多个径向臂，以及与磁路分离的并且用于冷却线圈的结构基座。

    Compression-evaporation system for liquefied gas
    4.
    发明申请
    Compression-evaporation system for liquefied gas 失效
    液化气压缩蒸发系统

    公开(公告)号：US20060222523A1

    公开(公告)日：2006-10-05

    申请号：US11305367

    申请日：2005-12-16

    申请人： Dominique Valentian ,  Damien Feger ,  Noel Marchal ,  Francois Danguy ,  Olivier Lagnel

    发明人： Dominique Valentian ,  Damien Feger ,  Noel Marchal ,  Francois Danguy ,  Olivier Lagnel

    IPC分类号： F04B53/00

    CPC分类号： F17C7/04 ,  F17C2221/033 ,  F17C2223/0161 ,  F17C2223/033 ,  F17C2225/0123 ,  F17C2225/036 ,  F17C2227/0142 ,  F17C2227/0157 ,  F17C2227/0316 ,  F17C2227/0393 ,  F17C2260/046 ,  F17C2265/05 ,  F17C2265/068 ,  F17C2270/0136 ,  Y02E20/14

    摘要： The compressor-evaporator system for liquefied gas contained in a tank comprises, in addition to a deice for evaporation by heat exchange with a liquid and devices for conditioning and transferring gas to a pipeline, a motor-driven turbopump comprising a rotary assembly of high bending stiffness on a common shaft line, with at least one high pressure pump, a turbine, and a central electrical machine capable of being used in motor mode or in generator mode. The rotary assembly of the motor-driven turbopump is adapted to present a high speed of rotation, greater than 12,000 rpm, while remaining outside ranges for exciting critical speeds in rotation. All of the internal portions of the motor-driven turbopump are immersed in a cryogenic fluid that is the same as the liquefied gas contained in the tank. The internal cavities of the motor-driven turbopump that are under different thermodynamic conditions are separated by contactless dynamic seals. Electronic power circuits connected to an electricity network control the central electrical machine in motor mode or generator mode.

    摘要翻译： 包含在罐中的用于液化气体的压缩机 - 蒸发器系统除了用于与液体进行热交换的蒸发用壳体和用于调节和将气体转移到管道的装置之外，还包括马达驱动的涡轮泵，其包括高弯曲的旋转组件 具有至少一个高压泵，涡轮机和能够用于电动机模式或发电机模式的中央电机的公共轴线上的刚度。 马达驱动的涡轮泵的旋转组件适于呈现大于12,000rpm的高转速旋转，同时保持旋转临界速度的外部范围。 马达驱动的涡轮泵的所有内部部分浸入与罐中所含的液化气体相同的低温流体。 在不同热力学条件下的电动涡轮泵的内部空腔由非接触式动态密封件分开。 连接到电力网络的电力电路以电机模式或发电机模式控制中央电机。

    Electrolytic igniter for rocket engines using monopropellants
    5.
    发明授权
    Electrolytic igniter for rocket engines using monopropellants 有权
    使用单一推进剂的火箭发动机电解点火器

    公开(公告)号：US08387359B2

    公开(公告)日：2013-03-05

    申请号：US12593727

    申请日：2008-03-28

    申请人： Dominique Valentian

    发明人： Dominique Valentian

    IPC分类号： F02C7/264

    CPC分类号： F02K9/95 ,  F02K9/52

    摘要： The electrolytic ignitor comprises an injector constituting a first electrode, a second electrode that is electrically insulated from the injector and that extends downstream beyond the injector, and a distribution channel to deliver a first mono-propellant to a first mono-propellant injector device constituted by at least one injection hole opening out in the vicinity of the second electrode, and an electrical power supply circuit adapted to raise the second electrode to a potential lying in the range 50 V to 1000 V relative to the potential of the first electrode. The electrical power dissipated by ionic conduction in the free jet of the first mono-propellant is suitable for giving rise to spontaneous decomposition of the first mono-propellant and for producing combustion gas that ensures ignition of jets of a second mono-propellant coming from a main injector situated in the vicinity of the second electrode.

    摘要翻译： 电解点火器包括构成第一电极的喷射器，与喷射器电绝缘且延伸到喷射器下游的第二电极，以及分配通道，用于将第一单推进剂输送到由第一单推喷剂喷射器装置 在第二电极附近开口的至少一个注入孔，以及适于将第二电极升高到相对于第一电极的电位为50V至1000V的电位的电源电路。 在第一单推进剂的自由射流中由离子传导消散的电功率适合于引起第一单推进剂的自发分解，并且用于产生燃烧气体，其确保来自第一单推进剂的第二单推进剂的射流的点燃 主喷射器位于第二电极附近。

    Electrolytic igniter for rocket engines using liquid propellants
    6.
    发明授权
    Electrolytic igniter for rocket engines using liquid propellants 有权
    使用液体推进剂的火箭发动机的电解点火器

    公开(公告)号：US08375697B2

    公开(公告)日：2013-02-19

    申请号：US12593755

    申请日：2008-03-28

    申请人： Dominique Valentian

    发明人： Dominique Valentian

    IPC分类号： F02C7/264

    CPC分类号： F02K9/52 ,  F02K9/95 ,  H05H1/48 ,  H05H2001/3484

    摘要： The electrolytic ignitor comprises an injector constituting a first electrode and including a fuel injector device, an oxidizer injector device, and an electrolyte injector device. A second electrode electrically insulated from the injector extends downstream beyond the injector. An electrolyte distribution channel for delivering electrolyte in the form of free jets through the electrolyte injector device comprises at least one injection hole in the vicinity of the fuel injector device and the oxidizer injector device. An electrical power supply circuit is adapted to raise the second electrode to a potential in the range 50 V to 1000 V relative to the potential of the first electrode. The electrolyte injected through the injection hole is capable of causing ignition of a gaseous mixture in a combustion chamber of an ignitor torch suitable for incorporating in a main injector of a rocket engine.

    摘要翻译： 电解点火器包括构成第一电极并包括燃料喷射器装置，氧化剂注入装置和电解液注入装置的喷射器。 与喷射器电绝缘的第二电极在喷射器的下游延伸。 用于通过电解液注入装置输送自由射流形式的电解质的电解质分配通道包括在燃料喷射器装置和氧化剂注入装置附近的至少一个喷射孔。 电源电路适于将第二电极升高到相对于第一电极的电位为50V至1000V的电位。 通过喷射孔注入的电解质能够引燃点火器火炬的燃烧室中的气体混合物的点燃，该燃烧室适用于并入火箭发动机的主喷射器中。

    Closed electron drift thruster
    7.
    发明授权
    Closed electron drift thruster 有权
    闭合电子漂移推进器

    公开(公告)号：US08129913B2

    公开(公告)日：2012-03-06

    申请号：US12693705

    申请日：2010-01-26

    申请人： Olivier Duchemin ,  Dominique Valentian

    发明人： Olivier Duchemin ,  Dominique Valentian

    IPC分类号： H05B31/26

    CPC分类号： F03H1/0075

    摘要： In a closed electron drift thruster, a magnetic circuit for creating a magnetic field in a main annular channel comprises at least one axial magnetic core surrounded by a first coil and an inner upstream pole piece forming a body of revolution, together with a plurality of outer magnetic cores surrounded by outer coils. The magnetic circuit further comprises an essentially radial outer first pole piece defining a concave inner peripheral surface and an essentially radial second pole piece defining a convex outer peripheral surface. The concave inner peripheral surface and the convex outer peripheral surface present respective adjusted profiles that are distinct from circular cylindrical surfaces so as to form between them a gap of varying width presenting zones of maximum value in register with the outer coils and zones of minimum value in between the outer coils so as to create a uniform radial magnetic field.

    摘要翻译： 在闭合电子漂移推进器中，用于在主环形通道中产生磁场的磁路包括由第一线圈和形成旋转体的内部上游极片包围的至少一个轴向磁芯，以及多个外部 磁芯由外圈包围。 磁路还包括限定凹入的内周表面的基本上径向的外部第一极靴和限定凸形外周表面的基本上径向的第二极靴。 凹形内周面和凸形外周面具有不同于圆柱形表面的相应调整轮廓，以便在它们之间形成具有与外部线圈对齐的最大值的变化宽度呈现区域的间隙和最小值的区域 在外圈之间形成均匀的径向磁场。

    Compression-evaporation system for liquefied gas
    8.
    发明授权
    Compression-evaporation system for liquefied gas 失效
    液化气压缩蒸发系统

    公开(公告)号：US07406830B2

    公开(公告)日：2008-08-05

    申请号：US11305367

    申请日：2005-12-16

    申请人： Dominique Valentian ,  Damien Feger ,  Noël Marchal ,  François Danguy ,  Olivier Lagnel

    发明人： Dominique Valentian ,  Damien Feger ,  Noël Marchal ,  François Danguy ,  Olivier Lagnel

    IPC分类号： F17C9/02 ,  F01K17/00 ,  F04B23/00

    CPC分类号： F17C7/04 ,  F17C2221/033 ,  F17C2223/0161 ,  F17C2223/033 ,  F17C2225/0123 ,  F17C2225/036 ,  F17C2227/0142 ,  F17C2227/0157 ,  F17C2227/0316 ,  F17C2227/0393 ,  F17C2260/046 ,  F17C2265/05 ,  F17C2265/068 ,  F17C2270/0136 ,  Y02E20/14

    摘要： The compressor-evaporator system for liquefied gas contained in a tank comprises, in addition to a deice for evaporation by heat exchange with a liquid and devices for conditioning and transferring gas to a pipeline, a motor-driven turbopump comprising a rotary assembly of high bending stiffness on a common shaft line, with at least one high pressure pump, a turbine, and a central electrical machine capable of being used in motor mode or in generator mode. The rotary assembly of the motor-driven turbopump is adapted to present a high speed of rotation, greater than 12,000 rpm, while remaining outside ranges for exciting critical speeds in rotation. All of the internal portions of the motor-driven turbopump are immersed in a cryogenic fluid that is the same as the liquefied gas contained in the tank. The internal cavities of the motor-driven turbopump that are under different thermodynamic conditions are separated by contactless dynamic seals. Electronic power circuits connected to an electricity network control the central electrical machine in motor mode or generator mode.

    摘要翻译： 包含在罐中的用于液化气体的压缩机 - 蒸发器系统除了用于与液体进行热交换的蒸发用壳体和用于调节和将气体转移到管道的装置之外，还包括马达驱动的涡轮泵，其包括高弯曲的旋转组件 具有至少一个高压泵，涡轮机和能够用于电动机模式或发电机模式的中央电机的公共轴线上的刚度。 马达驱动的涡轮泵的旋转组件适于呈现大于12,000rpm的高转速旋转，同时保持旋转临界速度的外部范围。 马达驱动的涡轮泵的所有内部部分浸入与罐中所含的液化气体相同的低温流体。 在不同热力学条件下的电动涡轮泵的内部空腔由非接触式动态密封件分开。 连接到电力网络的电力电路以电机模式或发电机模式控制中央电机。

    Method and a system for launching satellites on non-coplanar orbits, making the use of gravitational assistance from the moon
    9.
    发明授权
    Method and a system for launching satellites on non-coplanar orbits, making the use of gravitational assistance from the moon 失效
    在非共面轨道上发射卫星的方法和系统，利用月球的引力协助

    公开(公告)号：US6059233A

    公开(公告)日：2000-05-09

    申请号：US896

    申请日：1997-12-30

    申请人： Christophe Koppel ,  Dominique Valentian

    发明人： Christophe Koppel ,  Dominique Valentian

    IPC分类号： B64G1/00 ,  B64G1/10 ,  B64G1/24 ,  B64G1/34

    CPC分类号： B64G1/1085 ,  B64G1/007 ,  B64G1/242 ,  B64G1/002

    摘要： A first satellite is placed practically directly by a launcher on a first final orbit. A second satellite is placed on the same launcher is initially transferred to a highly elliptical waiting orbit whose semi-major axis points to intercept the torus formed by the sphere of influence of the moon on its orbit, and then during a maneuver at the perigee of the highly elliptical orbit, the second satellite is transferred to lunar transfer orbit. Changes in the perigee altitude and the inclination of an intermediate orbit on which the second satellite is to be found are obtained mainly by gravitational reaction in the sphere of influence of the moon, and during a last maneuver, the second satellite is placed on a final orbit having orbital parameter values that are quite different from those of the orbital parameters of the first final orbit.

    摘要翻译： 第一颗卫星实际上直接由第一个最终轨道上的发射器放置。 第二颗卫星放置在同一发射器上，最初被转移到一个高度椭圆形的等待轨道上，其半长轴指向截取由月球在其轨道上的影响范围形成的环面，然后在近地点 高度椭圆轨道，第二颗卫星转移到月球转移轨道。 主要通过月球影响范围内的引力反应获得近地点高度的变化和第二颗卫星所在的中间轨道的倾斜度，而在最后一次演习中，第二颗卫星被置于最后 轨道具有与第一最终轨道的轨道参数的轨道参数值完全不同的轨道参数值。