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。

公开(公告)号：US5961077A

公开(公告)日：1999-10-05

申请号：US978

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 ,  B64G1/40

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

摘要： A launcher places a first satellite practically directly on a final orbit. A second satellite carried by the same launcher is initially transferred onto a waiting orbit that is highly elliptical, having a semi-major axis situated in the initial orbital plane. The inclination and the perigee of the waiting orbit are then changed in the vicinity of the apogee of the waiting orbit, thereby placing the second satellite on an intermediate orbit. A maneuver is performed that includes at least one step making use of atmospheric braking in the vicinity of perigee of the intermediate orbit so as to lower the altitude of apogee of the intermediate orbit, and an impulse is supplied to the second satellite at apogee of the intermediate orbit so as to raise its perigee and transform the intermediate orbit into a final orbit having orbital parameters whose values are substantially different from those of the orbital parameters of the final orbit of the first satellite.

摘要翻译： 一个发射器将第一颗卫星实际上直接放在最后一个轨道上。 由同一发射器承载的第二颗卫星最初被转移到高度椭圆形的等待轨道上，半轴位于初始轨道平面内。 然后在等待轨道的远地点附近改变等待轨道的倾斜度和近地点，从而将第二颗卫星置于中间轨道上。 执行包括在中间轨道的近地点附近使用大气制动的至少一个步骤的操纵，以便降低中间轨道的远地点的高度，并且在第二卫星的远地点提供脉冲 中间轨道，以便提高其近地点，并将中间轨道转换成具有轨道参数的最终轨道，其轨道参数的值与第一卫星的最终轨道的轨道参数的值基本上不同。

公开(公告)号：US20100000232A1

公开(公告)日：2010-01-07

申请号：US12489733

申请日：2009-06-23

申请人： Dominique Valentian

发明人： Dominique Valentian

IPC分类号： F25B9/14 ,  F17C5/02

CPC分类号： F17C13/088 ,  B64G1/12 ,  B64G1/401 ,  B64G1/402 ,  B64G1/405 ,  F17C2203/0663 ,  F17C2205/013 ,  F17C2205/0161 ,  F17C2205/0192 ,  F17C2205/0323 ,  F17C2205/0338 ,  F17C2205/0391 ,  F17C2221/011 ,  F17C2221/016 ,  F17C2223/0115 ,  F17C2223/0161 ,  F17C2223/033 ,  F17C2223/035 ,  F17C2225/0115 ,  F17C2225/0161 ,  F17C2227/0135 ,  F17C2227/0353 ,  F17C2227/036 ,  F17C2227/0372 ,  F17C2227/0374 ,  F17C2250/043 ,  F17C2250/0491 ,  F17C2250/0636 ,  F17C2260/027 ,  F17C2270/0194

摘要： A cryogenic liquid storage system for a spacecraft comprising at least one liquid tank with an outer casing and an evacuated space arranged between the tank and the outer casing. The system further comprises a propellant management device made of material that is a good conductor of heat and that is cooled by a cryorefrigerator to localize the liquid inside the tank when in microgravity, a filler pipe situated in the portion of the tank that is at the bottom when the tank is on the ground, and that is surrounded by an evacuated insulating double wall and a purge pipe connecting the tank to the outer casing and presenting an internal length that is not less than half the diameter of the tank.

摘要翻译： 一种用于航天器的低温液体存储系统，包括至少一个具有外壳的液体罐和布置在罐和外壳之间的抽空空间。 该系统还包括由材料制成的推进剂管理装置，该材料是良好的导热体，并且在微重力时由冷冻机冷却以使罐内的液体定位，位于罐中部分的填料管 当罐位于地面上时，其由真空的绝缘双壁和净化管围绕，该排水管将罐连接到外壳，并且具有不小于罐直径一半的内部长度。

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。

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。

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。

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。

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。

公开(公告)号：US08893514B2

公开(公告)日：2014-11-25

申请号：US12489733

申请日：2009-06-23

申请人： Dominique Valentian

发明人： Dominique Valentian

IPC分类号： F17C5/02 ,  F17C7/02 ,  F17C9/02 ,  F17C13/08 ,  B64G1/40 ,  B64G1/12

CPC分类号： F17C13/088 ,  B64G1/12 ,  B64G1/401 ,  B64G1/402 ,  B64G1/405 ,  F17C2203/0663 ,  F17C2205/013 ,  F17C2205/0161 ,  F17C2205/0192 ,  F17C2205/0323 ,  F17C2205/0338 ,  F17C2205/0391 ,  F17C2221/011 ,  F17C2221/016 ,  F17C2223/0115 ,  F17C2223/0161 ,  F17C2223/033 ,  F17C2223/035 ,  F17C2225/0115 ,  F17C2225/0161 ,  F17C2227/0135 ,  F17C2227/0353 ,  F17C2227/036 ,  F17C2227/0372 ,  F17C2227/0374 ,  F17C2250/043 ,  F17C2250/0491 ,  F17C2250/0636 ,  F17C2260/027 ,  F17C2270/0194

摘要： A cryogenic liquid storage system for a spacecraft comprising at least one liquid tank with an outer casing and an evacuated space arranged between the tank and the outer casing. The system further comprises a propellant management device made of material that is a good conductor of heat and that is cooled by a cryorefrigerator to localize the liquid inside the tank when in microgravity, a filler pipe situated in the portion of the tank that is at the bottom when the tank is on the ground, and that is surrounded by an evacuated insulating double wall and a purge pipe connecting the tank to the outer casing and presenting an internal length that is not less than half the diameter of the tank.

摘要翻译： 一种用于航天器的低温液体存储系统，包括至少一个具有外壳的液体罐和布置在罐和外壳之间的抽空空间。 该系统还包括由材料制成的推进剂管理装置，该材料是良好的导热体，并且在微重力时由冷冻机冷却以使罐内的液体定位，位于罐中部分的填料管 当罐位于地面上时，其由真空的绝缘双壁和净化管围绕，该排水管将罐连接到外壳，并且具有不小于罐直径一半的内部长度。

公开(公告)号：US08365512B2

公开(公告)日：2013-02-05

申请号：US12527916

申请日：2008-02-21

申请人： Dominique Valentian

发明人： Dominique Valentian

IPC分类号： F03H1/00

CPC分类号： F03H1/005 ,  H01J27/26

摘要： An emitter for an ion thruster. The emitter is a field-effect emitter for a field emission electric propulsion or colloid thruster. The field-effect emitter has a first and second portions defining an internal reservoir for supplying a liquid metal or a conducting ionic liquid and has a slit connecting the internal reservoir to an exit orifice.

摘要翻译： 离子推进器的发射器。 发射极是用于场发射电推进器或胶体推进器的场效应发射器。 场效应发射器具有限定用于供应液体金属或导电离子液体的内部储存器的第一和第二部分，并且具有将内部储存器连接到出口孔的狭缝。