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公开(公告)号：US12091199B2
公开(公告)日：2024-09-17
申请号：US18118296
申请日：2023-03-07
发明人： Andrew Paul Turner , Tej Sachdev , Andrew Scott Ogilvie , Natalie Panek , Steve Fisher , Michael Honeybrown , Drew Alexander Grandy , Victor Nifo
CPC分类号： B64G1/646 , B64D39/04 , B64G1/1078 , B64G1/402 , B64G1/4024 , B64G2004/005
摘要： The present disclosure relates to a robotically controlled satellite refueling tool and associated robotically controlled support and site preparation tools which facilitates on-orbit refueling by teleoperation of fill/drain valves of various designs and dimensions on satellites not originally prepared for on-orbit servicing, through the installation of quick connect safety valves, using vision-based feedback as well as feedback from sensors embedded in the refueling tool to operate a suite of adaptable and adjustable mechanisms. The refueling tool has an open architecture to allow a refueling tool vision system to see the fill/drain valve and the section of the refueling tool that is engaged with the fill/drain valve. The support tools include a blanket cutter tool, a blanket handler tool, a wire cutter tool, a gripper tool, and the site preparation tools include a B-nut removal tool and a crush seal removal tool. Each of these tools includes a common base structure which is interfaced to the end effector of the robotic arm for transmitting rotation and torque to the various tools.
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公开(公告)号：US20240262535A1
公开(公告)日：2024-08-08
申请号：US18216571
申请日：2023-06-29
申请人： True Anomaly, Inc.
CPC分类号： B64G1/223 , B64G1/36 , B64G1/4022 , B64G1/443 , B64G4/00 , B64G2004/005
摘要： A spacecraft bus system described herein includes a propulsion assembly, a top plate assembly, and a bottom plate assembly. Each one of the propulsion assembly, the top plate assembly, and the bottom plate assembly is configured to be separately assembled and tested for spaceworthiness. Also described herein is a propulsion assembly for use with a spacecraft. The propulsion assembly includes a propellant tank containing propellant therein, at least one thruster, and a frame configured for supporting the propellant tank and the at least one thruster thereon. The propulsion assembly, as an individual module, is configured to be assembled and subjected to testing related to spaceworthiness. Additionally, the frame may be further configured for attachment to other components of the spacecraft, after being assembled and subjected to testing, without modification to the propulsion assembly or the other components of the spacecraft.
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公开(公告)号：US20180093786A1
公开(公告)日：2018-04-05
申请号：US15689993
申请日：2017-08-29
发明人： Robert Erik Schwarz , Robert Edward Helmer , Paul Anthony Briggs , John Douglas Lymer , Alfred Heikal Tadros , Andrew E. Turner
CPC分类号： B64G1/10 , B64G1/002 , B64G1/1078 , B64G1/222 , B64G1/64 , B64G1/646 , B64G4/00 , B64G2001/1092 , B64G2004/005
摘要： A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.
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公开(公告)号：US09878806B2
公开(公告)日：2018-01-30
申请号：US14642486
申请日：2015-03-09
CPC分类号： B64G1/222 , B64G1/641 , B64G1/66 , B64G4/00 , B64G2004/005
摘要： A spacecraft including a main body structure and at least a first deployable element is reconfigured from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a first arrangement. In the on-orbit configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a second arrangement. Reconfiguring the spacecraft includes detaching the first deployable element from the first arrangement, moving the first deployable element with respect to the spacecraft main body structure; and attaching the first deployable element to the second arrangement.
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公开(公告)号：US09669950B2
公开(公告)日：2017-06-06
申请号：US14703709
申请日：2015-05-04
CPC分类号： B64G4/00 , B64G1/1078 , B64G1/222 , B64G1/646 , B64G2004/005
摘要： The present invention provides a capture mechanism for capturing and locking onto the Marman flange located on the exterior surfaces of spacecraft/satellites. The capture mechanism achieves its goal of quickly capturing a client spacecraft by splitting the two basic actions involved into two separate mechanisms. One mechanism performs the quick grasp of the target while the other mechanism rigidises that grasp to ensure that the target is held as firmly as desired.
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公开(公告)号：US20170058929A1
公开(公告)日：2017-03-02
申请号：US15251075
申请日：2016-08-30
IPC分类号： F16B5/06
CPC分类号： F16B5/0642 , B64G4/00 , B64G2004/005 , F16B2/12 , Y10T29/49826 , Y10T403/591 , Y10T403/602 , Y10T403/608 , Y10T403/7067
摘要： A rigidizing latch assembly, in embodiments, is a robotically compatible aerospace attachment mechanism may be used to rigidly attach units to a structure and typically comprises a male latch and a receptacle configured to cooperatively couple. The male latch typically comprises a male latch housing and a latch assembly movably disposed within the male latch housing; a driver operatively in communication with a latch support; a male latch core; a driver interface access port; and one or more extraction feet operatively in communication with the driver. The receptacle comprises a receptacle housing sized to receive a lower portion of the male latch housing; a positioning target adapted to provide a visual positioning targeting cue; and one or more latch interfaces dimensioned to releasably mate with a corresponding lead-in guide of the plurality of lead-in guides.
摘要翻译： 在实施例中，刚性化闩锁组件是机器人兼容的航空航天附接机构可以用于将单元刚性地附接到结构，并且通常包括配置为协作地耦合的阳锁闩和插座。 阳锁闩通常包括阳锁闩壳体和可移动地设置在阳闩锁壳体内的闩锁组件; 操作地与闩锁支撑件通信的驱动器; 一个雄性锁芯; 驱动程序接口访问端口; 以及可操作地与驾驶员通信的一个或多个提取脚。 插座包括容纳壳体，其尺寸适于容纳阳锁闩壳体的下部; 适于提供视觉定位瞄准提示的定位目标; 以及一个或多个闩锁接口，其尺寸设计成可释放地与多个导入引导件的相应导入引导件配合。
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公开(公告)号：US09573276B2
公开(公告)日：2017-02-21
申请号：US13479128
申请日：2012-05-23
CPC分类号： B25J9/1689 , B25J3/04 , B25J11/00 , B64G4/00 , B64G2001/1064 , B64G2004/005 , G05B2219/40116 , G05B2219/40191 , G06N3/004 , G06N3/008
摘要： A system and method of space exploration with a human-controlled proxy robot surrogates is disclosed. The method includes: training the human controlled proxy robot surrogates using human handlers; controlling the human-controlled proxy robot surrogates using the human handlers; and deploying a plurality of human-controlled proxy robot surrogates for extraterrestrial missions, missions on Earth, the Moon, and near-Earth locations. Each of the human-controlled proxy robot surrogates are in communication with each of the human handlers and wherein each one of the plurality of proxy robot surrogates is paired with each one of the plurality of human handlers. The human-controlled proxy robot surrogates further comprise an artificial intelligence (AI). The artificial intelligence of the disclosed method includes learned behavior.
摘要翻译： 公开了一种具有人机代理机器人代理的空间探索系统和方法。 该方法包括：使用人类处理程序来训练人控代理机器人代理; 使用人类处理程序来控制人为受控的代理机器人代理; 并为地外任务，地球上的任务，月球和近地点部署多个人为受控的代理机器人代理。 每个人控代理机器人代理与每个人类处理程序通信，并且其中多个代理机器人代理中的每一个与多个人类处理程序中的每一个配对。 人控代理机器人代理进一步包括人工智能（AI）。 所披露方法的人工智能包括学习行为。
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8.发明申请公开(公告)号：US20160185471A1
公开(公告)日：2016-06-30
申请号：US15040816
申请日：2016-02-10
申请人： John Jeffrey Blincow
发明人： John Jeffrey Blincow
CPC分类号： B64G4/00 , B64G1/1078 , B64G1/646 , B64G9/00 , B64G2004/005
摘要： A method for autonomously constructing structural bodies in a zero gravity environment utilizes an assembly line space structure to fabricate segments for constructing a modular space structure. An assembly housing provides an open ended structure through which materials are processed in order to construct a segment. The materials are loaded into a plurality of workstations positioned along the assembly housing through the use of a plurality of external manipulators adjacently connected to the assembly housing. Each of the plurality of workstations provides the equipment for sequentially loading materials into the assembly housing. An assembly line conveyor, positioned throughout the plurality of workstations, guides materials through the assembly housing as the materials are mated to form the segment. Upon completion of the segment, a plurality of segment transport units transports the segment to an orbital construction site, wherein the segment is mated with subsequent segments to form the space station.
摘要翻译： 在零重力环境中自主构造结构体的方法利用组装线空间结构来制造用于构造模块空间结构的段。 组件外壳提供开放式结构，通过该结构处理材料以构建段。 通过使用相邻地连接到组件壳体的多个外部操纵器，将材料装载到沿着组件壳体定位的多个工作站中。 多个工作站中的每一个提供用于将材料顺序地装载到组件壳体中的设备。 定位在整个多个工作站中的装配线输送机当材料配合形成该段时将材料引导通过组件壳体。 在段完成时，多个分段传送单元将该段传送到轨道施工现场，其中段与随后的段配合以形成空间站。
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9.发明申请公开(公告)号：US20150097084A1
公开(公告)日：2015-04-09
申请号：US14505678
申请日：2014-10-03
申请人： Busek Co., Inc.
发明人： James J. Szabo , Vladimir Hruby , Thomas R. Roy , Craig DeLuccia , Jay Andrews , W. Dan Williams , Matthew R. Berlin , Jesse V. Gray
CPC分类号： B64G1/1078 , B64G1/242 , B64G1/26 , B64G1/36 , B64G1/402 , B64G1/405 , B64G1/428 , B64G1/646 , B64G1/648 , B64G4/00 , B64G2004/005 , Y10S901/09 , Y10S901/47
摘要： A spacecraft system and method includes a platform with a dock and an umbilical payout device. A robot is connected to an umbilical paid out by the umbilical payout device and is repeatedly deployable from the dock. The robot includes one or more imagers, an inertial measurement unit, and a plurality of thrusters. A command module receives image data from the one or more robot imagers and orientation data from the inertial measurement unit. An object recognition module is configured to recognize one or more objects from the received image data. The command module determines the robot's orientation with respect to an object and issues thruster control commands to control movement of the robot based on the robot's orientation. The combination of the space platform and robot on umbilical line can be used for towing another object to different orbital location, inspection including self-inspection of the robot carrying platform and for robotic servicing.
摘要翻译： 航天器系统和方法包括具有码头和脐带支付装置的平台。 机器人连接到由脐带支付装置支付的脐带，并且可以从码头重复部署。 机器人包括一个或多个成像器，惯性测量单元和多个推进器。 命令模块从一个或多个机器人成像器和来自惯性测量单元的取向数据接收图像数据。 对象识别模块被配置为从接收的图像数据识别一个或多个对象。 命令模块确定机器人相对于物体的方向，并发出推进器控制命令，以根据机器人的方向来控制机器人的运动。 脐带线上的空间平台和机器人的组合可用于将另一物体拖到不同的轨道位置，检查包括机器人承载平台的自检和机器人维修。
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公开(公告)号：US06408255B1
公开(公告)日：2002-06-18
申请号：US09374110
申请日：1999-08-16
申请人： Hans Hamacher
发明人： Hans Hamacher
IPC分类号： G01M906
摘要： A device for determining the operational condition of a mechanical apparatus (11-15) mounted in or to a spacecraft (10) which includes an acceleration pickup (20) attached to the spacecraft (10) for measuring the acceleration of the spacecraft (10), and an operational condition determination device with a memory for prestored known acceleration patterns of the apparatus (11-15). The acceleration patterns or parameters of the spacecraft (10) detected by the acceleration pickup (20) are compared with the known acceleration patterns or parameters of the apparatus (11-15) from the memory to determine the operational condition of the apparatus (11-15).
摘要翻译： 一种用于确定安装在航天器（10）中的机械设备（11-15）的操作状态的装置，其包括附接到所述航天器（10）的用于测量所述航天器（10）的加速度的加速度拾取器（20） 以及具有用于装置（11-15）的预先存储的已知加速度模式的存储器的操作条件确定装置。 将由加速度拾取器（20）检测的航天器（10）的加速度模式或参数与来自存储器的装置（11-15）的已知加速度模式或参数进行比较，以确定装置（11- 15）。
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