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1. 发明授权

US5775094A Apparatus and method for controlling thruster valve 失效
标题翻译：用于控制推进器阀的装置和方法
公开(公告)号：US5775094A
公开(公告)日：1998-07-07
申请号：US698083
申请日：1996-08-15
申请人： Junichiro Kawaguchi , Tatsuaki Hashimoto , Yasuhiro Morita
发明人： Junichiro Kawaguchi , Tatsuaki Hashimoto , Yasuhiro Morita
IPC分类号： B64G1/26 , B64G1/40 , F02K9/52 , F02K9/80 , F02K9/58
CPC分类号： B64G1/402 , B64G1/26 , F02K9/805
摘要： When the operation of an electromagnetic thruster valve disposed in a fluidassage for establishing the connection between a gas tank and a thruster unit for jetting gas filled in the gas tank is controlled to follow a thrust command, rise time of thrust at certain thrust is measured based on a state of the operation of the electromagnetic thruster valve. Then, the measured value and a predetermined delay value are subject to a comparison. The obtained difference is used as previous delay time to correct delay time of operation control of the electromagnetic thruster valve with respect to a next thrust command when the operation of the electromagnetic valve is controlled.
摘要翻译：当设置在用于建立气罐和用于喷射填充在气罐中的气体的推进器单元之间的连接的流体通道中的电磁推力阀的操作被控制为遵循推力指令时，测量在某个推力下的推力的上升时间基于电磁推进器阀的操作状态。然后，将测量值和预定延迟值进行比较。当控制电磁阀的操作时，获得的差值用作先前的延迟时间来校正电磁推力阀相对于下一推力命令的操作控制的延迟时间。

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

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。

4. 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。

5. 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。

6. 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。

7. 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。

8. 发明授权

US09567875B2 Power generation apparatus, power generation method, decomposition-gas turbine and decomposition-gas boiler 有权
标题翻译：发电设备，发电方式，分解燃气轮机和分解燃气锅炉
公开(公告)号：US09567875B2
公开(公告)日：2017-02-14
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 , B01D53/86 , F02C3/20 , F02C1/04 , F02C1/08 , F02C1/10 , F02C6/02 , F01K7/16 , F02C1/00 , F02C9/28 , F02C9/40 , F01K13/02 , F01K23/10
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（N2，O2）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。

9. 发明申请

US20100108819A1 METHOD FOR DESIGNING AN ORBIT OF A SPACECRAFT 有权
标题翻译：用于设计空间的轨道的方法
公开(公告)号：US20100108819A1
公开(公告)日：2010-05-06
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。

10. 发明授权

US07623956B2 Method and a device for stabilization control of a vehicle traffic volume 失效
标题翻译：一种用于稳定车辆交通量控制的方法和装置
公开(公告)号：US07623956B2
公开(公告)日：2009-11-24
申请号：US11365316
申请日：2006-02-28
申请人： Junichiro Kawaguchi
发明人： Junichiro Kawaguchi
IPC分类号： G08G1/01 , G06F19/00
CPC分类号： G08G1/22 , B60W30/165 , G08G1/161
摘要： The present invention provides a method and a device, which is in one hand implemented as a man-machine system in which the operations are shared such that a driver takes in charge of an inter-vehicle distance and speed control, while on the other hand a quantity of controls for stabilizing the inter-vehicle distance sequence is calculated automatically and additionally incorporated by the addition in respective vehicles. The stabilization of the inter-vehicle distance can be realized by employing the distributed control method in which a set of acceleration and deceleration information from a vehicle traveling ahead is appropriately integrated and transmitted in relay to a following vehicle. This enables the stabilization of the inter-vehicle distance sequence without requiring the inter-vehicle distance measurement in itself and the easy installation of equipment, and realizes a method in which safety is ensured by allowing the driver to still take charge of a local control.
摘要翻译：本发明提供了一种方法和装置，其一方面实现为人机系统，其中共享操作，使得驾驶员负责车辆间距离和速度控制，而另一方面自动计算用于稳定车辆间距离序列的量的控制，并且通过在相应的车辆中的添加另外地并入。车辆间距离的稳定化可以通过采用分散控制方法来实现，其中来自前方行驶的车辆的一组加速和减速信息被适当地整合并且以继电器的形式发送给后续的车辆。这使得能够稳定车辆间距离序列，而不需要本身的车间距离测量和设备的容易安装，并且实现了通过允许驾驶员仍然负责本地控制来确保安全性的方法。

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