公开(公告)号：US5146742A

公开(公告)日：1992-09-15

申请号：US606984

申请日：1990-10-31

申请人： Hiroshi Iida ,  Kyoichi Kuriki ,  Hitoshi Kuninaka

发明人： Hiroshi Iida ,  Kyoichi Kuriki ,  Hitoshi Kuninaka

IPC分类号： F03H1/00

CPC分类号： H01J27/16 ,  F03H1/0043

摘要： An ion thruster is operable in an interplanetary space with plasma generated by microwaves in a propellant atmosphere. A vessel defines first, second and third hollow spaces and a window between the first hollow space and the second and third hollow spaces, the second hollow space having an opening. A microwave generating unit generates the microwave in the first hollow space as a standing wave penetrating into the second and thid spacers hollow. A propellant supplying unit supplies the propellant into the second and third hollow spaces, the propellant serving as a main and neutralizing propellant and absorbing the standing wave to produce main plasma comprising main ions and main elecrons. An accelerating unit accelerates only the main ions into an ion beam to inject the ion beam through the opening into the interplanetary space. A neutralizing unit defines a third space which is in communication to the first space and into which the standing wave penetrates. The propellant comes into the third space to produce neutralizing ions and electrons. The ions are pulled by the ion beam to leave the neutralizing electrons, which neutralize the vessel.

公开(公告)号：US20070044450A1

公开(公告)日：2007-03-01

申请号：US11431452

申请日：2006-05-09

申请人： Hitoshi Kuninaka

发明人： Hitoshi Kuninaka

IPC分类号： F02K9/68

CPC分类号： B64G1/406 ,  B64G1/403 ,  F03H99/00

摘要： Disclosed is a powder propellant-based space propulsion device using a powder propellant having high density and excellent handleability. The powder propellant-based space propulsion device comprises a powder-propellant storage container for storing a powder propellant, a powder-propellant attracting surface for attracting the powder propellant thereto through an opening of the powder-propellant storage container and attractively holding the attracted powder propellant thereon, powder-propellant transfer means for transferring the held powder propellant to a release position for releasing the powder propellant, and propulsive-energy supply means for energizing the transferred powder propellant to release the powder propellant from the powder-propellant attracting surface, toward a downstream side thereof as a propulsive jet, while accelerating the powder propellant in a direction approximately perpendicular to the powder-propellant attracting surface at said release position. The powder-propellant transfer means is designed to move the powder-propellant attracting surface in such a manner that a powder-propellant holding area of the powder-propellant attracting surface is returned to a position adjacent to the opening of the powder-propellant storage container in a repetitive manner.

摘要翻译： 公开了使用具有高密度和优异的可操作性的粉末​​推进剂的基于粉末推进剂的空间推进装置。 基于粉末推进剂的空间推进装置包括用于储存粉末推进剂的粉末推进剂储存容器，用于通过粉末推进剂储存容器的开口吸引粉末推进剂的粉末推进剂吸附表面并且吸引地保持吸引的粉末推进剂 用于将保持的粉末推进剂转移到用于释放粉末推进剂的释放位置的推进剂转移装置以及用于激励所转移的粉末推进剂以将粉末推进剂从粉末推进剂吸附表面释放的推进能量供给装置， 其下游侧作为推进射流，同时在所述释放位置沿着大致垂直于粉末 - 推进剂吸引表面的方向加速粉末推进剂。 粉末推进剂转移装置设计成以粉末推进剂吸附表面的粉末推进剂保持区域返回到与粉末推进剂储存容器的开口相邻的位置的方式移动粉末推进剂吸附表面 以重复的方式。

公开(公告)号：US07038203B2

公开(公告)日：2006-05-02

申请号：US10759009

申请日：2004-01-20

申请人： Hitoshi Kuninaka ,  Yoshiki Yamagiwa

发明人： Hitoshi Kuninaka ,  Yoshiki Yamagiwa

IPC分类号： B64G1/36

CPC分类号： B64G1/10 ,  B64G1/1021 ,  B64G1/105 ,  G01N33/22

摘要： Ion particles are discharged so as to be influenced by a magnetic field originated from the earth, and collided with high-altitude neutral air to generate high velocity neutral particles through charge exchange. The high velocity neutral particles are analyzed. The distance to the high-altitude neutral air from at least one of the discharging positions of the ion particles and the measured positions of the high velocity neutral particles is determined based upon the period of time between the discharging time of the ion particles and the time the high velocity neutral particles are analyzed. Moreover, the direction of the high-altitude neutral air is determined by measuring the direction of the high velocity neutral particles. In addition, the spatial position of the high-altitude neutral air is determined based upon the measured direction of the high velocity neutral particles.

摘要翻译： 离子粒子被排出，受到来自地球的磁场的影响，并与高空中性空气相撞，通过电荷交换产生高速中性粒子。 分析高速中性粒子。 基于离子粒子的放电时间和离子粒子的放电时间之间的时间长度，确定离子粒子的排出位置和高速中性粒子的测定位置中至少一个的高空中性空气的距离， 分析高速中性粒子。 此外，通过测量高速中性粒子的方向来确定高空中性空气的方向。 另外，基于所测量的高速中性粒子的方向，确定高空中性空气的空间位置。

公开(公告)号：US07641150B2

公开(公告)日：2010-01-05

申请号：US11435521

申请日：2006-05-16

申请人： Hitoshi Kuninaka

发明人： Hitoshi Kuninaka

IPC分类号： B64G1/40

CPC分类号： B64G1/405 ,  B64G1/406 ,  F03H1/0012

摘要： Disclosed is a space propulsion device capable of continuous operation using a solid propellant having high density and excellent handleability. The solid propellant-based space propulsion device comprises solid-propellant support means for supporting a solid propellant, a solid-propellant attachment surface for permitting the solid propellant to be attached thereon, solid-propellant feed means for feeding the solid propellant to an attachment position on the solid-propellant attachment surface, adhesion-energy supply means for heatingly melting or sublimating the solid propellant in the attachment position to adherently attach the solid propellant onto the solid-propellant attachment surface, solid-propellant transfer means for transferring the solid propellant to a release position for releasing the solid propellant, and propulsive-energy supply means for energizing the transferred solid propellant to release the solid propellant from the solid-propellant attachment surface at the release position, as a propulsive jet, while accelerating the solid propellant in a direction approximately perpendicular to the solid-propellant attachment surface. The solid-propellant transfer means is designed to move the solid-propellant attachment surface in such a manner that a area of the solid-propellant attachment surface for adherently holding the solid propellant is returned to a position adjacent to an end of the solid propellant in a repetitive manner.

摘要翻译： 公开了能够使用具有高密度和优异的可操作性的固体推进剂连续操作的空间推进装置。 基于固体推进剂的空间推进装置包括用于支撑固体推进剂的固体推进剂支撑装置，用于允许固体推进剂附着在其上的固体推进剂附着表面，固体推进剂进料装置，用于将固体推进剂进料到附着位置 在固体推进剂附着表面上的粘附能量供应装置，用于在附着位置中将固体推进剂加热熔融或升华，以将固体推进剂附着在固体推进剂附着表面上，固体推进剂转移装置将固体推进剂转移至 用于释放固体推进剂的释放位置，以及推进能量供应装置，用于激励所转移的固体推进剂，以将固体推进剂从释放位置处的固体推进剂附着表面释放，作为推进射流，同时在固体推进剂中加速固体推进剂 方向大致垂直于固体推进剂a ttachment表面。 固体推进剂转移装置被设计成使固体推进剂附着表面移动，使得固定保持固体推进剂的固体推进剂附着表面的面积返回到与固体推进剂末端相邻的位置 重复的方式。

公开(公告)号：US20060290287A1

公开(公告)日：2006-12-28

申请号：US11141189

申请日：2005-06-01

申请人： Hitoshi Kuninaka

发明人： Hitoshi Kuninaka

IPC分类号： H01J7/24

CPC分类号： H05H1/54 ,  F03H1/0075 ,  H01J27/18

摘要： Disclosed is a high-frequency discharge plasma generation-based two-stage Hall-effect plasma accelerator, which comprises an annular acceleration channel having a gas inlet port, a high-frequency wave supply section, an anode, a cathode, a neutralizing electron generation portion and a magnetic-field generation means, wherein: gas introduced from the gas inlet port into the annular acceleration channel is ionized by a high-frequency wave supplied from the high-frequency wave supply section, to generate plasma; a positive ion includes in the generated plasma is accelerated by an acceleration voltage applied between the anode and cathode, and ejected outside; and an electron included in the generated plasma is restricted in its movement in the axial direction of the annular acceleration channel by an interaction with a magnetic field. The two-stage Hall-effect plasma accelerator is designed to control a degree of ion acceleration in accordance with the acceleration voltage serving as an acceleration control parameter, and control an amount of plasma generation in accordance with the high-frequency wave output serving as a plasma-generation control parameter. The two-stage Hall-effect plasma accelerator of the present invention can control the ion acceleration and the plasma generation in a highly independent manner.

摘要翻译： 公开了一种基于高频放电等离子体生成的两级霍尔效应等离子体加速器，其包括具有气体入口，高频波供应部，阳极，阴极，中和电子发生部 部分和磁场产生装置，其中：从气体入口引入环形加速通道的气体通过从高频波供应部分提供的高频波电离，以产生等离子体; 所产生的等离子体中的正离子被施加在阳极和阴极之间的加速电压加速并被外部喷出; 包含在所产生的等离子体中的电子通过与磁场的相互作用而限制其在环形加速通道的轴向方向上的移动。 两级霍尔效应等离子体加速器被设计成根据用作加速度控制参数的加速电压来控制离子加速度，并且根据作为加速度控制参数的高频波输出来控制等离子体产生量 等离子体发生控制参数。 本发明的两级霍尔效应等离子体加速器可以以非常独立的方式控制离子加速度和等离子体产生。

公开(公告)号：US5500052A

公开(公告)日：1996-03-19

申请号：US245966

申请日：1994-05-19

申请人： Yasuo Horiuchi ,  Hitoshi Kuninaka

发明人： Yasuo Horiuchi ,  Hitoshi Kuninaka

IPC分类号： H01L31/04 ,  G05F1/67 ,  H02J3/38 ,  H02J7/35 ,  H01L31/05

CPC分类号： G05F1/67 ,  B64G1/443 ,  H02J3/385 ,  H02S40/30 ,  Y10S136/293 ,  Y10S323/906

摘要： In a solar photovoltaic power generation device comprising a plurality of power generation units (31-34) each of which comprises first through n-th generation elements, the first through the n-th generation elements are connected in parallel and have their polarity directed in the same direction. The plurality of power generation units are arranged so that adjacent power generation units have polarities which are opposite to each other. Each of the plurality of power generation units further comprises a plurality of switch elements, each of which has active and inactive states, for connecting the first through the n-th generation elements in series in the active state. The solar photovoltaic power generation device further comprises a power control unit (37) for controlling the plurality of switch elements for placing it into the active state in each of the plurality of power generation units.

摘要翻译： 在包括多个发电单元（31-34）的太阳能光伏发电装置中，每个发电单元包括第一至第n代元件，第一至第n代元件并联连接，极性指向 方向相同 多个发电单元被布置成使得相邻的发电单元具有彼此相反的极性。 多个发电单元中的每一个还包括多个开关元件，每个开关元件具有有源和非活动状态，用于在激活状态下串联连接第一至第n代元件。 太阳能光伏发电装置还包括用于控制多个开关元件以将其置于多个发电单元中的每一个中的活动状态的功率控制单元（37）。

公开(公告)号：US07294969B2

公开(公告)日：2007-11-13

申请号：US11141189

申请日：2005-06-01

申请人： Hitoshi Kuninaka

发明人： Hitoshi Kuninaka

IPC分类号： H01J1/52

CPC分类号： H05H1/54 ,  F03H1/0075 ,  H01J27/18

摘要： Disclosed is a high-frequency discharge plasma generation-based two-stage Hall-effect plasma accelerator, which comprises an annular acceleration channel having a gas inlet port, a high-frequency wave supply section, an anode, a cathode, a neutralizing electron generation portion and a magnetic-field generation element, wherein: gas introduced from the gas inlet port into the annular acceleration channel is ionized by a high-frequency wave supplied from the high-frequency wave supply section, to generate plasma; a positive ion includes in the generated plasma is accelerated by an acceleration voltage applied between the anode and cathode, and ejected outside; and an electron included in the generated plasma is restricted in its movement in the axial direction of the annular acceleration channel by an interaction with a magnetic field. The two-stage Hall-effect plasma accelerator is designed to control a degree of ion acceleration in accordance with the acceleration voltage serving as an acceleration control parameter, and control an amount of plasma generation in accordance with the high-frequency wave output serving as a plasma-generation control parameter. The two-stage Hall-effect plasma accelerator of the present invention can control the ion acceleration and the plasma generation in a highly independent manner.

摘要翻译： 公开了一种基于高频放电等离子体生成的两级霍尔效应等离子体加速器，其包括具有气体入口，高频波供应部，阳极，阴极，中和电子发生部 部分和磁场产生元件，其中：从气体入口引入环形加速通道的气体通过从高频波供应部分提供的高频波电离，以产生等离子体; 所产生的等离子体中的正离子被施加在阳极和阴极之间的加速电压加速并被外部喷出; 包含在所产生的等离子体中的电子通过与磁场的相互作用而限制其在环形加速通道的轴向方向上的移动。 两级霍尔效应等离子体加速器被设计成根据用作加速度控制参数的加速电压来控制离子加速度，并且根据作为加速度控制参数的高频波输出来控制等离子体产生量 等离子体发生控制参数。 本发明的两级霍尔效应等离子体加速器可以以非常独立的方式控制离子加速度和等离子体产生。

公开(公告)号：US20070075190A1

公开(公告)日：2007-04-05

申请号：US11435521

申请日：2006-05-16

申请人： Hitoshi Kuninaka

发明人： Hitoshi Kuninaka

IPC分类号： B64G1/40

CPC分类号： B64G1/405 ,  B64G1/406 ,  F03H1/0012

摘要： Disclosed is a space propulsion device capable of continuous operation using a solid propellant having high density and excellent handleability. The solid propellant-based space propulsion device comprises solid-propellant support means for supporting a solid propellant, a solid-propellant attachment surface for permitting the solid propellant to be attached thereon, solid-propellant feed means for feeding the solid propellant to an attachment position on the solid-propellant attachment surface, adhesion-energy supply means for heatingly melting or sublimating the solid propellant in the attachment position to adherently attach the solid propellant onto the solid-propellant attachment surface, solid-propellant transfer means for transferring the solid propellant to a release position for releasing the solid propellant, and propulsive-energy supply means for energizing the transferred solid propellant to release the solid propellant from the solid-propellant attachment surface at the release position, as a propulsive jet, while accelerating the solid propellant in a direction approximately perpendicular to the solid-propellant attachment surface. The solid-propellant transfer means is designed to move the solid-propellant attachment surface in such a manner that a area of the solid-propellant attachment surface for adherently holding the solid propellant is returned to a position adjacent to an end of the solid propellant in a repetitive manner.

摘要翻译： 公开了能够使用具有高密度和优异的可操作性的固体推进剂连续操作的空间推进装置。 基于固体推进剂的空间推进装置包括用于支撑固体推进剂的固体推进剂支撑装置，用于允许固体推进剂附着在其上的固体推进剂附着表面，固体推进剂进料装置，用于将固体推进剂进料到附着位置 在固体推进剂附着表面上的粘附能量供应装置，用于在附着位置中将固体推进剂加热熔融或升华，以将固体推进剂附着在固体推进剂附着表面上，固体推进剂转移装置将固体推进剂转移至 用于释放固体推进剂的释放位置，以及推进能量供应装置，用于激励所转移的固体推进剂，以将固体推进剂从释放位置处的固体推进剂附着表面释放，作为推进射流，同时在固体推进剂中加速固体推进剂 方向大致垂直于固体推进剂a ttachment表面。 固体推进剂转移装置被设计成使固体推进剂附着表面移动，使得固定保持固体推进剂的固体推进剂附着表面的面积返回到与固体推进剂末端相邻的位置 重复的方式。