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    Gossamer apparatus and systems for use with spacecraft
    1.
    发明授权
    Gossamer apparatus and systems for use with spacecraft 有权
    用于航天器的消声器和系统

    公开(公告)号：US09555904B2

    公开(公告)日：2017-01-31

    申请号：US13963761

    申请日：2013-08-09

    Applicant: Analytical Mechanics Associates, Inc.

    Inventor： John Luther Abrams ,  Matthew Ernest Duchek

    IPC: B64G1/22 ,  B64G1/24 ,  B64G1/40 ,  B64G1/64

    CPC classification number: B64G1/222 ,  B64G1/242 ,  B64G1/407 ,  B64G1/641

    Abstract: Gossamer apparatus and systems for use with spacecraft may include a deployable gossamer apparatus. The deployable gossamer apparatus may include a plurality rib members and gossamer material extending therebetween and may be configured in a stowed configuration and a deployed configuration. The rib members of the deployable gossamer apparatus store potential energy used for deployment of the deployable gossamer apparatus.

    Abstract translation: 用于宇宙飞船的消赛器具和系统可以包括可展开的游丝器械。 可展开的游丝器装置可以包括在它们之间延伸的多个肋构件和游丝材料，并且可以被配置成收起构型和展开构型。 可部署的游丝器装置的肋构件存储用于展开可展开的游丝器具的潜在能量。

    MULTIPLE BOOM DEPLOYMENT
    4.
    发明申请
    MULTIPLE BOOM DEPLOYMENT 审中-公开
    多部门部署

    公开(公告)号：US20160311558A1

    公开(公告)日：2016-10-27

    申请号：US15136487

    申请日：2016-04-22

    Applicant: Composite Technology Development, Inc.

    Inventor： Dana Turse ,  Larry Adams ,  Doug Richardson

    IPC: B64G1/22 ,  B64G1/66

    CPC classification number: B64G1/222 ,  B64G1/34 ,  B64G1/407 ,  B64G1/44 ,  B64G1/66

    Abstract: Some embodiments of the invention include a boom deployment system. The boom deployment system, for example, may include a housing, a spool, a first boom, and a second boom. The spool may be disposed within the housing and configured to rotate around an axis that is fixed relative to the housing. The first boom and/or the second boom may have a cylindrical shape in a deployed configuration, a flattened shape in a stowed configuration, and a slit that extends along the longitudinal length of the boom in the deployed configuration. The first boom and/or the second boom may be stowed in the stowed configuration flattened and wrapped around the spool. The first boom and/or the second boom may transition from the stowed configuration to the deployed configuration as the spool rotates around the axis.

    Abstract translation: 本发明的一些实施例包括吊杆展开系统。 例如，悬臂展开系统可以包括壳体，线轴，第一起重臂和第二起重臂。 线轴可以设置在壳体内并且被配置为围绕相对于壳体固定的轴线旋转。 第一起重臂和/或第二起重臂可以具有展开构造的圆柱形形状，收起构型中的扁平形状以及沿展开构型的吊杆的纵向长度延伸的狭缝。 第一起重臂和/或第二起重臂可以收纳在收起的构造中，并且卷绕并缠绕在卷轴上。 当卷轴围绕轴线旋转时，第一悬臂和/或第二起重臂可以从收起的构型转变到展开构型。

    Spacecraft momentum management using solar array
    5.
    发明授权
    Spacecraft momentum management using solar array 有权
    航天器动力管理采用太阳能阵列

    公开(公告)号：US08868263B2

    公开(公告)日：2014-10-21

    申请号：US13115370

    申请日：2011-05-25

    Applicant: Mohammad Saghir Munir ,  John Hutton Cooper ,  Philip Conway Hirschberg

    Inventor： Mohammad Saghir Munir ,  John Hutton Cooper ,  Philip Conway Hirschberg

    IPC: B64G1/24 ,  G05D1/00 ,  G05D1/08

    CPC classification number: G05D1/0883 ,  B64G1/24 ,  B64G1/26 ,  B64G1/283 ,  B64G1/361 ,  B64G1/365 ,  B64G1/405 ,  B64G1/407 ,  B64G1/44

    Abstract: Stored momentum on a spacecraft is managed by determining a target profile of stored momentum as a function of time for the spacecraft; measuring a difference between a momentum value actually stored on the spacecraft and a desired momentum value, where the desired momentum value substantially conforms to the target profile at a particular time; reducing the difference by producing a torque on the spacecraft, where the torque results from selectively controlling at least one solar array position offset angle, the offset angle being an offset of at least one solar array of the spacecraft from a nominal sun pointing direction.

    Abstract translation: 通过确定作为航天器时间的函数的存储动量的目标轮廓来管理航天器上的存储动量; 测量实际存储在航天器上的动量值与期望动量值之间的差异，其中期望动量值在特定时间基本上符合目标轮廓; 通过在航天器上产生扭矩来减小差异，其中扭矩由选择性地控制至少一个太阳能阵列位置偏移角度而产生，该偏移角度是航天器的至少一个太阳能阵列与标称太阳指向方向的偏移。

    Space vacuum propulsion system
    6.
    发明申请
    Space vacuum propulsion system 审中-公开
    太空真空推进系统

    公开(公告)号：US20120325971A1

    公开(公告)日：2012-12-27

    申请号：US13506619

    申请日：2012-04-06

    Applicant: Darrell Eugene Heard

    Inventor： Darrell Eugene Heard

    IPC: B64G1/40

    CPC classification number: B64G1/401 ,  B64G1/407 ,  B64G1/409

    Abstract: This propulsion system is based on the theory of vacuum propulsion wherein a propulsion System utilizes space vacuum to propel the space ship through space. Vacuum Pumps are used to vacuum in space through the rear of the ship where it is gathered or collected in a pressure chamber. There the collected space is contained while yet more space vacuum is collected. The chamber has a containment valve at the end of the chamber and can be breached after vacuum collected reaches critical mass overcoming the containment valve where it is then released into the hull. This release of the vacuum chamber containment valve and the collected vacuum oozes from the vacuum chamber filling the hull mixing with carbon dioxide and heat changing the nature of space vacuum and creating a propellant fuel for propulsion. The chamber is situated at the rear of the starship.

    Abstract translation: 该推进系统基于真空推进理论，其中推进系统利用空间真空推动太空船通过空间。 真空泵用于在空间中通过船的后部进行真空抽真空，将其聚集或收集在压力室中。 收集收集的空间，同时收集更多的空间真空。 腔室在腔室的末端具有一个容纳阀，并且在真空收集达到临界质量以后克服阻塞阀，然后将其释放到船体中时可以被破坏。 真空室容纳阀的释放和收集的真空从真空室渗出，填充船体与二氧化碳的混合和热量改变空间真空的性质并产生用于推进的推进剂燃料。 该舱位于星舰的后方。

    SPACECRAFT MOMENTUM MANAGEMENT USING SOLAR ARRAY
    7.
    发明申请
    SPACECRAFT MOMENTUM MANAGEMENT USING SOLAR ARRAY 有权
    使用太阳辐射阵列的空间管理

    公开(公告)号：US20120303185A1

    公开(公告)日：2012-11-29

    申请号：US13115370

    申请日：2011-05-25

    Applicant: Mohammad Saghir Munir ,  John Hutton Cooper ,  Philip Conway Hirschberg

    Inventor： Mohammad Saghir Munir ,  John Hutton Cooper ,  Philip Conway Hirschberg

    IPC: B64G1/24 ,  G05D1/00

    CPC classification number: G05D1/0883 ,  B64G1/24 ,  B64G1/26 ,  B64G1/283 ,  B64G1/361 ,  B64G1/365 ,  B64G1/405 ,  B64G1/407 ,  B64G1/44

    Abstract: Stored momentum on a spacecraft is managed by determining a target profile of stored momentum as a function of time for the spacecraft; measuring a difference between a momentum value actually stored on the spacecraft and a desired momentum value, where the desired momentum value substantially conforms to the target profile at a particular time; reducing the difference by producing a torque on the spacecraft, where the torque results from selectively controlling at least one solar array position offset angle, the offset angle being an offset of at least one solar array of the spacecraft from a nominal sun pointing direction.

    Abstract translation: 通过确定作为航天器时间的函数的存储动量的目标轮廓来管理航天器上的存储动量; 测量实际存储在航天器上的动量值与期望动量值之间的差异，其中期望动量值在特定时间基本上符合目标轮廓; 通过在航天器上产生扭矩来减小差异，其中扭矩由选择性地控制至少一个太阳能阵列位置偏移角度而产生，该偏移角度是航天器的至少一个太阳能阵列与标称太阳指向方向的偏移。

    Electric sail with voltage multipliers in tethers
    8.
    发明申请
    Electric sail with voltage multipliers in tethers 有权
    电动帆与电缆乘法器在系绳

    公开(公告)号：US20120104176A1

    公开(公告)日：2012-05-03

    申请号：US12915282

    申请日：2010-10-29

    Applicant: Tatu J. Ylonen

    Inventor： Tatu J. Ylonen

    IPC: B64G1/10 ,  B64G1/40

    CPC classification number: B64G1/407

    Abstract: The effective area of an electric sail depends on the voltage applied to tethers. The use of higher voltages is made possible by moving voltage multipliers to tethers, perhaps 100 meters out from the body of the spacecraft.

    Abstract translation: 电动帆的有效面积取决于施加到系绳的电压。 通过将电压倍增器移动到距离航天器主体100米的系绳上，可以实现更高电压的使用。

    Electric sail for producing spacecraft propulsion
    9.
    发明授权
    Electric sail for producing spacecraft propulsion 有权
    电帆用于生产航天器推进

    公开(公告)号：US07641151B2

    公开(公告)日：2010-01-05

    申请号：US11365875

    申请日：2006-03-02

    Applicant: Pekka Janhunen

    Inventor： Pekka Janhunen

    IPC: B64G1/40

    CPC classification number: B64G1/407 ,  B64G1/222

    Abstract: A spacecraft propulsion system includes a plurality of wires (102) or other electrically conductive elongated members deployed from a main body (101) into respective radial directions. An electric potential generator (605) generates an electric potential on board the main body (101). The electric coupling between the electric potential generator (605) and the elongated members is controlled (604) so that all or some of the elongated members (102) assume a high positive potential. An auxiliary propulsion system (203) rotates the main body around a rotational axis (502) that is perpendicular to the radial directions, thus creating a centrifugal supporting force to the elongated members.

    Abstract translation: 航天器推进系统包括多个线（102）或从主体（101）向相应的径向方向展开的其它导电细长构件。 电位发生器（605）在主体（101）上产生电位。 控制电位发生器（605）和细长构件之间的电耦合（604），使得所有或一些细长构件（102）呈现高的正电位。 辅助推进系统（203）围绕垂直于径向的旋转轴（502）旋转主体，从而为细长构件产生离心支撑力。

    System and method for propellantless photon tether formation flight
    10.
    发明授权
    System and method for propellantless photon tether formation flight 有权
    无抛物线光子系链形成飞行的系统和方法

    公开(公告)号：US07413147B2

    公开(公告)日：2008-08-19

    申请号：US11491830

    申请日：2006-07-22

    Applicant: Young Kun Bae

    Inventor： Young Kun Bae

    IPC: B64G1/24

    CPC classification number: B64G1/648 ,  B64G1/1085 ,  B64G1/24 ,  B64G1/407 ,  F03H3/00

    Abstract: The invention is a system and method for propellantless, ultrahigh precision satellite formation flying based on ultrahigh precision intracavity laser thrusters and tethers with an intersatellite distance accuracy of nanometers at maximum estimated distances of tens of kilometers. The repelling force of the intracavity laser thruster and the attracting force of tether tension between satellites form the basic forces to stabilize matrix structures of satellites. Users of the present invention can also use the laser thruster for ultrahigh precision laser interferometric metrology, resulting in simplification and payload weight reduction in integrating the thruster system and the metrology system.

    Abstract translation: 本发明是基于超高精度腔内激光推进器和系绳的无推进，超高精度卫星形成飞行的系统和方法，其最大距离为数十公里，卫星距离精度为纳米。 星内激光推进器的排斥力和卫星之间系绳张力的吸引力构成了稳定卫星基体结构的基本力量。 本发明的用户还可以使用激光推进器进行超高精度激光干涉测量，从而在推进器系统和计量系统的整合中简化和有效负载重量减少。

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