公开(公告)号：US20240317677A1

公开(公告)日：2024-09-26

申请号：US18519989

申请日：2023-11-27

申请人： Skeyeon, Inc.

发明人： Ronald E. Reedy ,  Thomas E. Schwartzentruber

IPC分类号： C07C259/06 ,  A61P35/00 ,  B64G1/10 ,  B64G1/42 ,  B64G1/44 ,  B64G1/66 ,  G01S13/90 ,  G01S19/39 ,  H04B7/185 ,  H04B7/195

CPC分类号： C07C259/06 ,  A61P35/00 ,  B64G1/1021 ,  B64G1/425 ,  B64G1/443 ,  G01S19/39 ,  H04B7/18513 ,  H04B7/195 ,  B64G1/1028 ,  B64G1/1035 ,  B64G1/66 ,  G01S13/90

摘要： A satellite system operates at altitudes between 180 km and 350 km relying on vehicles including an engine to counteract atmospheric drag to maintain near-constant orbit dynamics. The system operates at altitudes that are substantially lower than traditional satellites, reducing size, weight and cost of the vehicles and their constituent subsystems such as optical imagers, radars, and radio links. The system can include a large number of lower cost, mass, and altitude vehicles, enabling revisit times substantially shorter than previous satellite systems. The vehicles spend their orbit at low altitude, high atmospheric density conditions that have heretofore been virtually impossible to consider for stable orbits. Short revisit times at low altitudes enable near-real time imaging at high resolution and low cost. At such altitudes, the system has no impact on space junk issues of traditional LEO orbits, and is self-cleaning in that space junk or disabled craft will de-orbit.

公开(公告)号：US20230227155A1

公开(公告)日：2023-07-20

申请号：US17566811

申请日：2021-12-31

申请人： Hyundai Motor Company ,  Kia Corporation

发明人： Ernestine Fu ,  Grey Parker ,  Prasanna Natarajan ,  Matt Korich ,  Jacob Viau ,  David Wilson ,  John Suh ,  David Byron ,  Mark Lister

IPC分类号： B64C37/02 ,  B64G1/16 ,  B64G1/42

CPC分类号： B64C37/02 ,  B64G1/16 ,  B64G1/425 ,  B64D2221/00

摘要： A combination two vehicle system is provided that includes a land-based vehicle configured for traversal over ground and an aerial vehicle configured for travel through air, where the aerial vehicle is configured to detachably couple with the land-based vehicle. The aerial vehicle includes stabilizing legs to provide stability for take-off or landing. A method of operating the vehicle system includes steps of: providing the land-based and the aerial vehicle having the stabilizing legs, and aerially transporting the vehicle system including the land-based vehicle and the aerial vehicle, where the stabilizing legs provide stability for take-off or landing. In addition, the land-based vehicle may transport a removable cargo pod, which the aerial vehicle may independently retrieve from the land-based vehicle.

公开(公告)号：US20190118980A1

公开(公告)日：2019-04-25

申请号：US16218556

申请日：2018-12-13

申请人： Technion Research & Development Foundation Limited

发明人： Oded SHMUELI ,  Ehud BEHAR

IPC分类号： B64G1/10 ,  B64G1/42 ,  B64G1/66 ,  B64G1/64 ,  B64C39/02 ,  B64G1/22

CPC分类号： B64G1/1085 ,  B64C39/024 ,  B64C2201/143 ,  B64G1/10 ,  B64G1/222 ,  B64G1/425 ,  B64G1/64 ,  B64G1/66 ,  B64G2001/643

摘要： A ground-based satellite control station to control an array of nanosatellites in low earth orbit to produce an illumination event visible at a predetermined ground location. The nanosatellites in the array may have an illumination element, and array of nanosatellites in low earth orbit (LEO) may controllably apply their illumination to be visible on the ground. The nanosatellites may be coordinated by the control station to provide illumination events visible on the ground at particular locations and particular times.

公开(公告)号：US09745083B2

公开(公告)日：2017-08-29

申请号：US14676568

申请日：2015-04-01

申请人： WorldVu Satellites Limited

发明人： Alexander D. Smith ,  Armen Askijian ,  Daniel W. Field ,  James Grossman

IPC分类号： B64G1/52 ,  B64G1/58 ,  B64G1/10 ,  B64G1/50 ,  B64G1/24 ,  B64G1/66 ,  B64G1/42

CPC分类号： B64G1/58 ,  B64G1/1007 ,  B64G1/242 ,  B64G1/425 ,  B64G1/50 ,  B64G1/503 ,  B64G1/66

摘要： A method for thermally stabilizing a communication satellite in orbit around the Earth relies on the discrete rotational symmetry of the pattern of antenna beams of the satellite. Exploiting the symmetry, the orientation of the satellite is changed from time to time by rotating the satellite through a symmetry angle of the rotational symmetry. Because of the symmetry, the beam pattern is unchanged after the rotation; but, because the rotation angle is less than 360°, a different side of the satellite is exposed to sunlight. The use of different thermal radiators and thermal shields on different sides of the satellite means that the thermal budget of the satellite is different after the rotation. By judiciously applying rotations as needed, as the orbit's orientation relative to the Sun evolves in time, it is possible to achieve effective control on the thermal budget of the satellite.

公开(公告)号：US09463883B2

公开(公告)日：2016-10-11

申请号：US14121324

申请日：2014-08-20

申请人： Bigelow Aerospace LLC

发明人： Robert T. Bigelow

IPC分类号： B64G1/64 ,  B64G1/40 ,  B64G1/42 ,  B64G1/44 ,  B64G1/12 ,  B64G1/26

CPC分类号： B64G1/646 ,  B64G1/12 ,  B64G1/26 ,  B64G1/401 ,  B64G1/402 ,  B64G1/425 ,  B64G1/44 ,  B64G1/648

摘要： A spacecraft capture tug is disclosed. The tug can capture objects in space, including spacecraft and satellites, using an engagement system and provide propulsion for the object to a point of servicing, repair, or other desired operations. Further, the tug may dock with other specialty tugs to form a custom transport system.

公开(公告)号：US20140107865A1

公开(公告)日：2014-04-17

申请号：US13650738

申请日：2012-10-12

申请人： THE AEROSPACE CORPORATION ,  NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

发明人： Anthony D. Griffith, SR. ,  Rajiv Kohli ,  Susan H. Burns ,  Stephen J. Damico ,  David J. Gruber ,  Christsopher J. Hickey ,  David E. Lee ,  Travis M. Robinson ,  Jason T. Smith ,  Peter T. Spehar ,  David S. Adlis ,  Brian M. Kent

IPC分类号： G06F17/00 ,  B64G1/10 ,  B64G1/62 ,  G05D1/00

CPC分类号： B64G1/66 ,  B64G1/002 ,  B64G1/1078 ,  B64G1/24 ,  B64G1/242 ,  B64G1/283 ,  B64G1/36 ,  B64G1/361 ,  B64G1/363 ,  B64G1/401 ,  B64G1/402 ,  B64G1/425 ,  B64G1/428 ,  B64G1/44 ,  B64G1/62 ,  B64G1/64 ,  B64G1/646 ,  G05D1/00 ,  G05D1/0005 ,  G05D1/0094 ,  G05D1/0883 ,  G05D1/10 ,  G06F17/00

摘要： Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

摘要翻译： 提供了用于去除轨道碎片的系统，装置和方法。 在一个实施例中，一种装置包括被配置为将装置引导和导航到目标的航天器控制单元。 该装置还包括被配置为表征目标的运动和捕获特征的动态对象表征单元。 该装置还包括捕获和释放单元，其被配置为捕获目标并且释放或释放目标。 然后，这些装置的收集被用作从单个运载火箭发射的多个独立和单独操作的车辆，用于处理多个碎片物体。

公开(公告)号：US08152108B2

公开(公告)日：2012-04-10

申请号：US12140978

申请日：2008-06-17

申请人： Craig H. Becker-Irvin ,  Winnie W. Choy

发明人： Craig H. Becker-Irvin ,  Winnie W. Choy

IPC分类号： B64G1/42

CPC分类号： B64G1/428 ,  B64G1/425 ,  B64G1/443 ,  H01L31/02021 ,  H02J1/14 ,  Y02E10/50

摘要： Apparatuses and methods for optimizing power generation of a solar array are disclosed. The bus voltage is regulated with a regulator controlled through one or more reference signals. When the power bus is being used by electrical systems that are tolerant of a higher variable voltage range, the bus voltage can be temporarily set higher by a commanded reference signal to allow additional solar array power to supply to the power bus. The peak power point may be identified through an established relationship with the solar array performance as a function of temperature, season and/or the age of the solar array. In addition, a reference signal controlled by one or more temperature sensors on the solar array may also modify the bus voltage set-point. Improved solar array power may be extracted from spacecraft beginning-of-life to end-of-life operations due to low insertion loss of a direct energy transfer scheme.

摘要翻译： 公开了一种用于优化太阳能电池阵列发电的装置和方法。 总线电压通过一个或多个参考信号控制的调节器进行调节。 当电力总线被容纳在更高可变电压范围的电气系统使用时，总线电压可以通过指令的参考信号临时设置得更高，以允许额外的太阳能阵列电力供应到电力总线。 可以通过与太阳能阵列性能的确定关系来确定峰值功率点，作为太阳能阵列的温度，季节和/或年龄的函数。 此外，由太阳能电池阵列上的一个或多个温度传感器控制的参考信号也可以修改总线电压设定点。 由于直接能量转移方案的低插入损耗，改进的太阳能阵列功率可以从航天器的寿命开始到寿命终止操作。

公开(公告)号：US20110037427A1

公开(公告)日：2011-02-17

申请号：US12710598

申请日：2010-02-23

申请人： Wayne Boncyk ,  Gerald Murphy

发明人： Wayne Boncyk ,  Gerald Murphy

IPC分类号： H02J7/00

CPC分类号： H01M10/4207 ,  B60L53/80 ,  B60L58/22 ,  B60L2200/10 ,  B60L2240/545 ,  B64G1/425 ,  B64G2001/1092 ,  Y02T10/7005 ,  Y02T10/7061 ,  Y02T10/7072 ,  Y02T90/124 ,  Y02T90/14 ,  Y02T90/16

摘要： The present invention provides an energy storage device for spacecraft application. The energy storage device includes an energy storage component including a plurality of cells. Each cell has a minimum shelf life. The energy storage device also includes a first interface to an external power source configured for charging of the energy storage component, a second interface to a spacecraft for outputting power from the energy storage component and a third interface for communicating to spacecraft. The energy storage device further includes a charge controller operatively coupled with the energy storage component and the first, second and third interface. The charge controller includes an internal power supply configured to provide power for the charge controller. The charge controller also includes a microprocessor incorporating a firmware to accommodate a system configuration of the energy storage component.

摘要翻译： 本发明提供了一种用于航天器应用的能量存储装置。 能量存储装置包括包括多个单元的能量存储组件。 每个电池具有最小的保质期。 能量存储装置还包括被配置为对能量存储部件进行充电的外部电源的第一接口，用于从能量存储部件输出功率的航天器的第二接口和用于与航天器通信的第三接口。 能量存储装置还包括与能量存储部件和第一，第二和第三接口可操作地耦合的充电控制器。 充电控制器包括被配置为为充电控制器提供电力的内部电源。 充电控制器还包括具有固件的微处理器，以适应能量存储部件的系统配置。

公开(公告)号：US06923249B1

公开(公告)日：2005-08-02

申请号：US10447971

申请日：2003-05-28

申请人： Harry H. Porter ,  Jose Valenzuela ,  James D. Williams ,  Timothy W. Harvey

发明人： Harry H. Porter ,  Jose Valenzuela ,  James D. Williams ,  Timothy W. Harvey

IPC分类号： B64G1/42 ,  B64G1/44 ,  B64G1/50 ,  B64G1/66 ,  H01M10/0525 ,  H01M10/46 ,  H01M10/50

CPC分类号： B64G1/443 ,  B64G1/425 ,  B64G1/50 ,  B64G1/503 ,  B64G1/66 ,  H01M10/0525 ,  H01M10/465 ,  H01M10/625 ,  H01M10/647 ,  H01M10/6551 ,  H01M10/6554 ,  H01M10/658 ,  H01M10/667 ,  Y02E60/122

摘要： A passive thermal control system maintains the operating temperature range of protected equipment within desired limits by controlling the conductive attributes of thermal interfaces and physical relationships within the system so as to achieve a desired thermal balance. In one embodiment, an integrated cell unit (100) includes a solar array (102), a Lithium ion cell (108) and an antenna assembly (114) such as a phased array antenna. In operation, a thermal gradient (116) is defined between the array (102) and the assembly (114) as the assembly (114) radiates heat from the array (102) into space. The operating temperature range of the cell (108) is controlled by appropriate design of the thermal interfaces between the cell (108) and the assembly (114) and/or interfaces within the assembly (114), such as a thermal interface associated with dielectric spacers provided between emitter pairs of the assembly (114).

摘要翻译： 被动热控制系统通过控制系统内的热界面和物理关系的导电属性来将受保护设备的工作温度范围保持在期望的范围内，以达到所需的热平衡。 在一个实施例中，集成单元单元（100）包括太阳能阵列（102），锂离子电池（108）和诸如相控阵天线的天线组件（114）。 在操作中，随着组件（114）将热量从阵列（102）辐射到空间中，热梯度（116）被定义在阵列（102）和组件（114）之间。 电池（108）的工作温度范围通过电池（108）和组件（114）之间的热界面和/或组件（114）内的接口的适当设计来控制，例如与电介质相关的热界面 间隔件设置在组件（114）的发射极对之间。

公开(公告)号：US06561461B2

公开(公告)日：2003-05-13

申请号：US09925206

申请日：2001-08-09

申请人： David Goldstein ,  Scott A. McDermott ,  Paul Gloyer ,  Richard Fleeter

发明人： David Goldstein ,  Scott A. McDermott ,  Paul Gloyer ,  Richard Fleeter

IPC分类号： B64G122

CPC分类号： B64G1/10 ,  B64G1/007 ,  B64G1/1085 ,  B64G1/222 ,  B64G1/24 ,  B64G1/242 ,  B64G1/425 ,  B64G1/428 ,  B64G1/50 ,  B64G1/641 ,  B64G2001/224

摘要： An orbit-transfer vehicle provides the navigation, propulsion, and control systems required to transport a payload satellite from a geosynchronous-transfer orbit (GTO) to a predetermined low-earth orbit (LEO). Upon entering low-earth orbit, the payload satellite is deployed from the orbit-transfer vehicle. To reduce the cost and complexity of the payload satellite, the orbit-transfer vehicle is configured to provide common functional services, such as communications and power regulation, to the payload satellite during the transport, and/or after deployment. To reduce the fuel requirements for this deployment via the orbit-transfer vehicle, a preferred embodiment includes aerobraking to bring the satellite into a low-earth orbit. In a preferred embodiment of this method of deployment, the provider of the orbit-transfer vehicle identifies and secures available excess capacity on launch vehicles, and allocates the excess capacity to the satellites requiring deployment, thereby providing a deployment means that is virtually transparent to the purchaser of this deployment service.

摘要翻译： 轨道转移车辆提供将有效载荷从地球同步转移轨道（GTO）运输到预定的低地球轨道（LEO）所需的导航，推进和控制系统。 进入低地球轨道后，载具卫星从轨道转运车辆部署。 为了降低有效载荷卫星的成本和复杂性，轨道转移车辆被配置为在运输期间和/或部署之后向有效载荷卫星提供诸如通信和功率调节之类的共同功能服务。 为了减少通过轨道转运车辆的这种部署的燃料需求，优选实施例包括使卫星进入低地球轨道的航空制动。 在这种部署方法的优选实施例中，轨道转移车辆的提供者识别并确保运载火箭上的可用剩余容量，并且将剩余容量分配给需要部署的卫星，由此提供对于 此部署服务的购买者。