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1. 发明授权

US08769923B2 Liquid-fuel storage vessel and vapor jet system using the same 有权
标题翻译：液体燃料储存容器和使用其的蒸气喷射系统
公开(公告)号：US08769923B2
公开(公告)日：2014-07-08
申请号：US12401496
申请日：2009-03-10
申请人： Takayuki Yamamoto , Osamu Mori , Junichiro Kawaguchi
发明人： Takayuki Yamamoto , Osamu Mori , Junichiro Kawaguchi
IPC分类号： B64G1/40
CPC分类号： F02K9/42 , B64G1/401 , B64G1/402
摘要： Disclosed is a liquid-fuel storage vessel for use in a vapor jet system to store liquid fuel, wherein the vapor jet system is adapted to jet the fuel in a state after being vaporized inside the liquid-fuel storage vessel, outside the liquid-fuel storage vessel, to obtain a thrust. The liquid-fuel storage vessel comprises: a hollow tank for storing the liquid fuel, wherein the tank has an ejection port for ejecting the vaporized fuel, outside the liquid-fuel storage vessel therethrough; a heating device for heating the tank; and a porous metal formed to have a plurality of interconnected cells and provided inside the tank, wherein at least a part of the liquid fuel is held in the cells of the porous metal, and heat energy given from the heating device to the tank is transferred to the liquid fuel through the porous metal to cause vaporization of at least a part of the liquid fuel. The liquid-fuel storage vessel of the present invention can obtain a stable thrust level and ensure spacecraft attitude control.
摘要翻译：公开了一种用于蒸汽喷射系统中储存液体燃料的液体燃料储存容器，其中蒸气喷射系统适于在液体 - 燃料储存容器内蒸发之前的状态下喷射燃料，在液体燃料外储存容器，以获得推力。液体燃料储存容器包括：用于储存液体燃料的中空罐，其中罐具有用于喷射蒸发燃料的喷射口，在液体燃料储存容器的外面; 用于加热罐的加热装置; 以及形成为具有多个相互连接的电池并设置在所述槽内的多孔金属，其中所述液体燃料的至少一部分保持在所述多孔金属的电池中，并且从所述加热装置向所述罐传递的热能被转移通过多孔金属使液体燃料通过至少一部分液体燃料蒸发。本发明的液体燃料储存容器可获得稳定的推力水平并确保航天器的姿态控制。

2. 发明授权

US07747361B2 Method of injecting plurality of spacecraft into different orbits individually 有权
标题翻译：将多个航天器分别注入不同轨道的方法
公开(公告)号：US07747361B2
公开(公告)日：2010-06-29
申请号：US11326440
申请日：2006-01-06
申请人： Junichiro Kawaguchi , Yasuhiro Kawakatsu , Osamu Mori
发明人： Junichiro Kawaguchi , Yasuhiro Kawakatsu , Osamu Mori
IPC分类号： G05D1/00 , B64G1/00 , B64G1/10
CPC分类号： B64G1/242 , B64G1/007 , B64G1/1085
摘要： In a method for injecting a plurality of spacecraft into different circum-earth or interplanetary orbits individually in a single launch, a plurality of spacecraft coupled to an assist module are injected into an interplanetary orbit having a periodicity synchronous with the earth's revolution period. Then, in a maneuver allowing the assist module to re-counter with and pass near to the earth (Earth swing-by), the assist module appropriately performs an orbital change maneuver and a separation maneuver for each of the spacecraft in a sequential order. Through these maneuvers, a closest-approach point to the earth is changed for each of the spacecraft so as to drastically change a subsequent orbital element for each of the spacecraft. The assist module takes a sufficient time to determine a target orbit for each of the spacecraft with a high degree of accuracy until a half month to several days before a closest-approach time in the Earth swing-by. Based on the determined orbit, the assist module makes an orbit correction of about several m/sec in a sequential order, and then separates the spacecraft therefrom in a sequential order. In this process, an inertia navigation is performed based on an accelerometer mounted in the assist module and information about attitude.
摘要翻译：在单个发射中单独地将多个航天器注入不同的环形或星际轨道的方法中，耦合到辅助模块的多个航天器被注入具有与地球旋转周期同步的周期的行星际轨道。然后，辅助模块在允许辅助模块重新对抗并通过接近地球（地球绕行）的操作中，按顺序适当地执行每个航天器的轨道改变机动和分离机动。通过这些演习，对于每个航天器，对地球的最接近的点都会发生变化，从而大大改变每个航天器的后续轨道元素。辅助模块需要足够的时间以高精确度确定每个航天器的目标轨道，直到地球中最接近的时间之前的半个月到几天。基于所确定的轨道，辅助模块按顺序进行约几m / sec的轨道校正，然后以顺序的顺序分离航天器。在该过程中，基于安装在辅助模块中的加速度计和关于姿态的信息执行惯性导航。

3. 发明授权

US08347298B2 Autonomous distributed control involving constraint on resources 有权
标题翻译：自主分布式控制涉及资源约束
公开(公告)号：US08347298B2
公开(公告)日：2013-01-01
申请号：US11866366
申请日：2007-10-02
申请人： Junichiro Kawaguchi , Osamu Mori , Yuichi Tsuda , Koji Nakaya
发明人： Junichiro Kawaguchi , Osamu Mori , Yuichi Tsuda , Koji Nakaya
IPC分类号： G06F9/46
CPC分类号： H04L47/70
摘要： Disclosed is a distributed control method of cooperatively allowing a control strategy for satisfying a constraint on an aggregated resource and simultaneously achieving or maintaining a performance of a system to be determined in a real-time manner by any one of a plurality of entities which have the highest need for the resource at any given time, without providing a specified management entity. The proposed method or “card game scheme” of the present invention is designed to dynamically carry out a function of satisfying a constraint on an aggregate resource and simultaneously achieving or maintaining a performance of the entire system, based on a distributed control with high flexibility, wherein an “agent”, i.e., a software having a function of performing autonomous determination and control, is set in each of the entities, to allow the entities to dynamically take turns to perform a processing of determining a strategy for resource allocation.
摘要翻译：公开了一种分散控制方法，其协作地允许控制策略以满足对聚合资源的约束，并且同时实现或维持由多个实体中的任何一个实时地确定的系统的性能，所述多个实体具有在任何给定时间对资源的最高需求，而不提供指定的管理实体。本发明提出的方法或卡片游戏方案被设计为基于具有高灵活性的分布式控制，动态地执行满足聚合资源的约束并同时实现或维持整个系统的性能的功能，其中代理，即具有执行自主确定和控制的功能的软件被设置在每个实体中，以允许实体动态轮流执行确定资源分配策略的处理。

4. 发明申请

US20080082981A1 AUTONOMOUS DISTRIBUTED CONTROL INVOLVING CONSTRAINT ON RESOURCES 有权
标题翻译：涉及资源约束的自动分配控制
公开(公告)号：US20080082981A1
公开(公告)日：2008-04-03
申请号：US11866366
申请日：2007-10-02
申请人： Junichiro Kawaguchi , Osamu Mori , Yuichi Tsuda , Koji Nakaya
发明人： Junichiro Kawaguchi , Osamu Mori , Yuichi Tsuda , Koji Nakaya
IPC分类号： G06F9/50
CPC分类号： H04L47/70
摘要： Disclosed is a distributed control method of cooperatively allowing a control strategy for satisfying a constraint on an aggregated resource and simultaneously achieving or maintaining a performance of a system to be determined in a real-time manner by any one of a plurality of entities which have the highest need for the resource at any given time, without providing a specified management entity. The proposed novel method or “card game scheme” of the present invention is designed to dynamically carry out a function of satisfying a constraint on an aggregate resource and simultaneously achieving or maintaining a performance of the entire system, based on a distributed control with high flexibility, wherein an “agent”, i.e., a software having a function of performing autonomous determination and control, is set in each of the entities, to allow the entities to dynamically take turns to perform a processing of determining a strategy for resource allocation, without specifying the agent serving as a management entity having an authority to determine the strategy, so as to provide a processing method with high versatility.
摘要翻译：公开了一种分散控制方法，其协作地允许控制策略以满足对聚合资源的约束，并且同时实现或维持由多个实体中的任何一个实时地确定的系统的性能，所述多个实体具有在任何给定时间对资源的最高需求，而不提供指定的管理实体。本发明提出的新颖方法或“卡片游戏方案”被设计为基于具有高灵活性的分布式控制来动态地执行满足聚合资源的约束并同时实现或维持整个系统的性能的功能，其中在每个实体中设置“代理”，即具有执行自主确定和控制功能的软件，以允许实体动态轮流执行确定资源分配策略的处理，而无需指定作为具有确定策略的权限的管理实体的代理，以提供具有高通用性的处理方法。

5. 发明申请

US20060241824A1 Method of injecting plurality of spacecrafts into different orbits individually 有权
标题翻译：将多个航天器分别注入不同轨道的方法
公开(公告)号：US20060241824A1
公开(公告)日：2006-10-26
申请号：US11326440
申请日：2006-01-06
申请人： Junichiro Kawaguchi , Yasuhiro Kawakatsu , Osamu Mori
发明人： Junichiro Kawaguchi , Yasuhiro Kawakatsu , Osamu Mori
IPC分类号： G06F17/00
CPC分类号： B64G1/242 , B64G1/007 , B64G1/1085
摘要： Disclosed is a method for injecting a plurality of spacecrafts into different circum-earth or interplanetary orbits individually in a single launch. A plurality of spacecrafts coupled to an assist module are injected into an interplanetary orbit having a periodicity synchronous with the earth's revolution period. Then, in a maneuver for allowing the assist module to re-counter with and pass near to the earth Earth swing-by), the assist module appropriately performs an orbital change maneuver and a separation maneuver for each of the spacecrafts in a sequential order. Through these maneuvers, a closest-approach point to the earth is changed for each of the spacecrafts so as to drastically change a subsequent orbital element for each of the spacecrafts. The assist module takes a sufficient time to determine a target orbit for each of the spacecrafts with a high degree of accuracy until a half month to several days before a closest-approach time in the Earth swing-by. Based on the determined orbit, the assist module makes an orbit correction of about several m/sec in a sequential order, and then separates the spacecrafts therefrom in a sequential order. In this process, an inertia navigation is performed based on an accelerometer mounted in the assist module and information about attitude.
摘要翻译：公开了一种在单次发射中单独地将多个航天器注入不同的环形或星际轨道的方法。耦合到辅助模块的多个航天器被注入具有与地球旋转周期同步的周期的行星际轨道。然后，辅助模块在一个允许辅助模块重新对抗并通过接近地球地球的方法中，辅助模块按照顺序适当地执行每个航天器的轨道改变机动和分离机动。通过这些演习，对于每个航天器来说，对地球的最接近的点都是改变的，以便大幅改变每个航天器的后续轨道元素。辅助模块需要足够的时间以高精确度确定每个航天器的目标轨道，直到地球最近接近时间之前的半个月至几天。基于所确定的轨道，辅助模块按顺序进行约几m /秒的轨道校正，然后以顺序的顺序分离其中的航天器。在该过程中，基于安装在辅助模块中的加速度计和关于姿态的信息执行惯性导航。

6. 发明授权

US07744036B2 Method for designing an orbit of a spacecraft 有权
标题翻译：设计航天器轨道的方法
公开(公告)号：US07744036B2
公开(公告)日：2010-06-29
申请号：US11490344
申请日：2006-07-19
申请人： Junichiro Kawaguchi , Kohta Tarao
发明人： Junichiro Kawaguchi , Kohta Tarao
IPC分类号： B64G1/10
CPC分类号： B64G1/242 , B64G1/26
摘要： A method is disclosed for designing an orbit of a spacecraft which allows the spacecraft to take a small-radius halo orbit near a Lagrange point while avoiding the prohibited zone where the spacecraft may be shadowed or might be prevented from making communication. The method makes it possible to have a closed orbit although being similar to a Lissajous orbit, under a restricted condition where a propulsion force magnitude applied to a spacecraft is fixed, and where it rotates at a constant angular velocity, based on the equation of motion close to a Lagrange point. The method also provide a theory for guiding/controlling the orbit of a spacecraft, that is, the embodiment of the above orbit design method.
摘要翻译：公开了一种用于设计航天器的轨道的方法，其允许航天器在拉格朗日点附近采取小半径的光环轨道，同时避免航天器可能被遮蔽或可能被阻止进行通信的禁止区域。该方法使得尽可能地具有闭合轨道，但是在受到限制的条件下，其中施加到航天器的推进力大小是固定的，并且其以恒定的角速度旋转，基于运动方程靠近拉格朗日点。该方法还提供了用于引导/控制航天器轨道的理论，即上述轨道设计方法的实施例。

7. 发明申请

US20150007568A1 POWER GENERATION APPARATUS, POWER GENERATION METHOD, DECOMPOSITION-GAS TURBINE AND DECOMPOSITION-GAS BOILER 有权
标题翻译：发电装置，发电方法，分解 - 气体涡轮机和分解燃气锅炉
公开(公告)号：US20150007568A1
公开(公告)日：2015-01-08
申请号：US14379698
申请日：2012-02-23
申请人： Shigehiro Chaen , Junichiro Kawaguchi , Hiroto Habu , Yoshitsugu Sone
发明人： Shigehiro Chaen , Junichiro Kawaguchi , Hiroto Habu , Yoshitsugu Sone
IPC分类号： F01K15/00 , F02C9/40 , F02C9/28 , F01K7/16 , F02C1/00
CPC分类号： F01K15/00 , B01D53/8625 , B01D2255/1023 , B01D2255/1025 , B01D2255/2047 , B01D2255/2073 , B01D2255/20738 , B01D2255/20753 , B01D2255/20792 , B01D2255/2092 , B01D2257/402 , F01K7/16 , F01K7/165 , F01K13/02 , F01K23/10 , F02C1/00 , F02C1/04 , F02C1/08 , F02C1/10 , F02C3/20 , F02C6/02 , F02C9/28 , F02C9/40 , Y02C20/10 , Y02E20/14
摘要： A power generation apparatus, a power generation method, a decomposition-gas boiler, and a decomposition-gas turbine with which nitrous oxide may be used as an environmentally friendly energy source. A fuel gas including nitrous oxide (N2O) is supplied to a decomposition reactor (22) in which a catalyst (21) for decomposing nitrous oxide is disposed. Steam is generated by a decomposition-gas boiler by heat recovery from decomposition gas (N2, O2) generated by decomposing the nitrous oxide, the steam generated by the decomposition-gas boiler is used to drive the rotation of a steam turbine to obtain motive power, and the motive power is subsequently used to drive a generator to obtain electrical power. Alternatively, the decomposition gas (N2, O2) generated by decomposing the nitrous oxide is used to drive the rotation of a decomposition-gas turbine to obtain motive power.
摘要翻译：发电装置，发电方法，分解气体锅炉和分解燃气轮机，其中可以使用一氧化二氮作为环境友好型能源。将包含一氧化二氮（N 2 O）的燃料气体供给到分解反应器（22）中，在分解反应器（22）中设置有用于分解一氧化二氮的催化剂（21）。蒸汽是由分解气体锅炉通过从分解气体分解产生的分解气体（N 2，O 2）进行热回收产生的，由分解燃气锅炉产生的蒸汽用于驱动蒸汽轮机的旋转以获得动力并且随后使用动力来驱动发电机以获得电力。或者，通过分解一氧化二氮产生的分解气体（N 2，O 2）用于驱动分解燃气涡轮机的旋转以获得动力。

8. 发明申请

US20090007541A1 THRUSTER USING NITROUS OXIDE 审中-公开
标题翻译：使用硝酸氧化物的电击
公开(公告)号：US20090007541A1
公开(公告)日：2009-01-08
申请号：US11951298
申请日：2007-12-05
申请人： Junichiro Kawaguchi , Shinichiro Tokudome , Hiroto Habu , Tsuyoshi Yagishita , Masatoshi Hotta
发明人： Junichiro Kawaguchi , Shinichiro Tokudome , Hiroto Habu , Tsuyoshi Yagishita , Masatoshi Hotta
IPC分类号： C06D5/00
CPC分类号： F02K9/42 , F02K9/425 , F02K9/68
摘要： A thruster is provided that makes it possible to reduce and eventually eliminate the toxicity of storable liquid propellant and improve the low-temperature environment adaptability of propulsion system using the storable liquid propellant. The thruster produces thrust by using catalytic decomposition gas obtained by catalytically decomposing nitrous oxide with a nitrous oxide decomposition catalyst.
摘要翻译：提供了一种推进器，可以减少并最终消除可储存液体推进剂的毒性，并提高使用可储存液体推进剂的推进系统的低温环境适应性。推进器通过使用通过用一氧化二氮分解催化剂催化分解一氧化二氮获得的催化分解气体产生推力。

9. 发明申请

US20080029650A1 Ultrahigh Altitude Sun-Synchronous Orbit Satellite System 有权
标题翻译：超高空太阳同步轨道卫星系统
公开(公告)号：US20080029650A1
公开(公告)日：2008-02-07
申请号：US11630087
申请日：2004-06-22
申请人： Junichiro Kawaguchi
发明人： Junichiro Kawaguchi
IPC分类号： B64G1/10
CPC分类号： B64G1/242 , B64G1/1007 , B64G1/1021
摘要： A system which comprises a sun-synchronous orbit satellite (3) revolving around the sun (5) and apparently revolving around the earth at a period of approximately one year while keeping the direction and the geometry to the sun and the earth (4) constant at an ultrahigh altitude of several millions km keeping clear of the influence zone of the earth, and which provides any of astronomical or global observation service and communication service. An observation satellite, which meets such conditions that a vector normal to a virtual orbital plane centering around the earth is substantially fixed regardless of revolution, can sweep the substantially entire celestial sphere during a single revolution while avoiding the effect of light and heat from the earth, and can keep a local solar time at a sub-satellite point on the surface of the earth constant, can be attained. A communication satellite, where the substantially hemisphere of the earth can be covered at a time simultaneously with one satellite and the substantially entire region of the earth can be covered with a small number or three satellites, is attained. Geometrical relations with the sun and the earth can be frozen approximately by the adjustment of the i/e ratio or by the use of perturbation by the attraction of the earth gravity. Operation from launch to insertion into an intended orbit can be achieved with significantly low fuel consumption by utilizing the perturbation owing to the attraction of the earth gravity.
摘要翻译：一种系统，其包括围绕太阳（5）旋转的太阳同步轨道卫星（3），并且在大约一年的时间周围围绕地球旋转，同时保持方向和几何形状对太阳和地球（4）恒定在数百万公里的超高的高度，保持了地球的影响区域，并提供任何天文或全球观测服务和通信服务。一种观测卫星符合如下条件：垂直于围绕地球的虚拟轨道平面的向量基本上是固定的，无论转动如何，可以在单次旋转期间扫掠基本上整个天球，同时避免来自地球的光和热的影响，并且可以在地球表面的亚卫星点保持局部太阳时间常数，可以实现。一个通信卫星，其中地球的大致半球可以同时覆盖一颗卫星，并且可以用少量或三颗卫星覆盖地球的大致整个区域。几乎与太阳和地球的关系可以通过i / e比的调整或通过吸引地球重力的扰动来大致冻结。通过利用由于地球重力的吸引引起的扰动，可以以显着低的燃料消耗实现从发射到插入到预定轨道的操作。

10. 发明授权

US06689952B2 Large membrane space structure and method for its deployment and expansion 失效
标题翻译：大型膜空间结构及其部署和扩展方法
公开(公告)号：US06689952B2
公开(公告)日：2004-02-10
申请号：US10014346
申请日：2001-12-14
申请人： Junichiro Kawaguchi
发明人： Junichiro Kawaguchi
IPC分类号： H01L31045
CPC分类号： H01Q1/288 , H01Q15/161
摘要： A large membrane space structure deployed and spanned by centrifugal force owing to the spin motion, contains a hub located at a central portion thereof and a sail including a plurality of petals attached to the hub by supports. Each of the petals has regions symmetrical to an imaginary center line passing through the center of the hub. Membranes are spanned on the regions. Each of the membranes is divided into parts of suitable shapes, and adjacent membranes are discretely connected to each other by bridge belts to suppress the residual crease strain. The petals are symmetric with respect to the center of the hub. Deployment force is provided in the circumferential direction by the introduction of imaginary tension lines. The petals may be connected to each other to help deployment.
摘要翻译：通过旋转运动由离心力部署和跨越的大的膜空间结构包含位于其中心部分处的轮毂和包括通过支撑件附接到轮毂的多个花瓣的帆。每个花瓣具有与穿过轮毂中心的假想中心线对称的区域。膜跨越区域。每个膜被分成适当形状的部分，并且相邻的膜通过桥接带彼此离散地连接以抑制残余的折痕应变。花瓣相对于轮毂的中心对称。通过引入假想张力线在圆周方向上设置展开力。花瓣可以相互连接以帮助部署。

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