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公开(公告)号：US20230042339A1
公开(公告)日：2023-02-09
申请号：US17791344
申请日：2021-01-13
发明人： Elie Allouis , Alexander Hall , John Carroll
摘要： The present invention relates to an assembly apparatus for assembling components of spacecraft in space. The assembly apparatus comprises: a core platform (7); and a mobile platform (4) comprising an end effector configured to perform an assembly or manufacturing task. The mobile platform (4) is connected to the core platform (7) by a tether (6a). The core platform comprises a body and a coupling element (15a) connected to and extendable from the body (7) such that the coupling element (15a) may be spaced from the body of the core platform (7). The tether (6a) connects the mobile platform (4) to the body (7) via the coupling element (15a). The assembly apparatus further comprises an actuator configured to vary the length of the tether extending between the coupling element and the mobile platform to control the position of the mobile platform relative to the body of the core platform.
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公开(公告)号：US20220242597A1
公开(公告)日：2022-08-04
申请号：US17622875
申请日：2020-08-21
发明人： Hisayuki MUKAE
摘要： A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.
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公开(公告)号：US20210253320A1
公开(公告)日：2021-08-19
申请号：US17247910
申请日：2020-12-30
发明人： Yinzhi WANG , Fei WANG , Wenbei SHI , Liekun YANG
摘要： A laser sample chamber for deep space exploration includes a sample chamber base and a sample chamber top cover. The sample chamber base is a hollow cylinder with bottom end being sealed and top end being open, and an internal cavity in the hollow cylinder is provided for receiving sample plates; and a body of the sample chamber top cover is a hollow cylinder with a top end being sealed and a bottom end being open, and the body consists of a plurality of components which comprise a hollow annulus positioned at a middle of the sample chamber top cover, a circular viewing window positioned at an opening at a top end of the hollow annulus, and a threaded port positioned at an opening at a bottom end of the hollow annulus and protruding outward.
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公开(公告)号：US11014303B1
公开(公告)日：2021-05-25
申请号：US15885484
申请日：2018-01-31
IPC分类号： B29C64/295 , B29C64/118 , B29C64/393 , B33Y10/00 , B33Y50/02 , B64G4/00 , B64G1/52 , B33Y30/00 , B29K101/12
摘要： A spacecraft includes an additive manufacturing (A/M) subsystem and one or both of a thermal control arrangement and a contamination control arrangement. The A/M subsystem includes an A/M tool, feedstock and a workpiece and is configured to additively manufacture the workpiece using material from the feedstock. The thermal control arrangement is operable, in an on-orbit space environment characterized by near vacuum pressure and near zero-g force, to maintain temperature of at least one of the A/M tool, the feedstock, and the workpiece within respective specified ranges. The contamination control arrangement is operable, in the on-orbit space environment, to control outgassing of volatile organic compounds (VOCs).
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公开(公告)号：US20210094709A1
公开(公告)日：2021-04-01
申请号：US17035329
申请日：2020-09-28
发明人： David Barnhart , Rebecca Rogers
摘要： Systems and methods for multi-armed robotic capture devices are disclosed. The systems and methods for multi-armed robotic capture devices include a base that is configured to attach to a robotic arm or a servicer and having a tether. The systems and methods for multi-armed robotic capture devices include a body that is coupled to the base via the tether. Additionally, the systems and methods for multi-armed robotic capture devices include a plurality of tentacles coupled to the body and configured to grip a target object. The systems and methods for multi-armed robotic capture devices also include a plurality of tiles positioned on each tentacle of the plurality of tentacles and configured to apply a shear force on the target object to grip the target object using an adhesive force.
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公开(公告)号：US20210059138A1
公开(公告)日：2021-03-04
申请号：US16991894
申请日：2020-08-12
申请人： SIDON LLC
摘要： Systems and methods for growing plants. The systems and methods can be used for growing plants in low, micro, or zero gravity environments. An injection device can inject a fluid or growth medium into the stem or root of a plant. A plant can also be supported on a platform and a light placed below the plant, or in a direction opposite gravity or a acceleration force to promote plant growth in a direction opposite gravity or the acceleration force.
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7.发明授权公开(公告)号：US10851333B2
公开(公告)日：2020-12-01
申请号：US15882039
申请日：2018-01-29
申请人： Techshot, Inc.
IPC分类号： B29C64/364 , B29C64/40 , A01H4/00 , C12M3/00 , A61L27/36 , A61L27/38 , B33Y80/00 , B33Y10/00 , B33Y30/00 , A61L27/54 , C12M1/26 , C12M1/34 , C12N5/00 , B29C64/393 , B64G4/00 , B64G1/22 , B29K101/12
摘要： A method, apparatus, and system are provided for the printing and maturation of living tissue in an Earth-referenced reduced gravity environment such as that found on a spacecraft or on other celestial bodies. The printing may be three-dimensional structures. The printed structures may be manufactured from low viscosity biomaterials.
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公开(公告)号：US20200247563A1
公开(公告)日：2020-08-06
申请号：US16855356
申请日：2020-04-22
发明人： Robert Erik Schwarz , Robert Edward Helmer , Paul Anthony Briggs , John Douglas Lymer , Alfred Heikal Tadros , Andrew E. Turner
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：US10730643B1
公开(公告)日：2020-08-04
申请号：US15654593
申请日：2017-07-19
摘要： A spacecraft includes a main body structure and a plurality of deployable modular reflector elements, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the modular reflector elements are disposed in a storage system that includes an arrangement for supporting the modular reflector elements with respect to dynamic launch loads. In the on-orbit configuration, in some implementations, an assembly of the plurality of modular reflector elements forms a large-aperture, offset fed, reflector, the reflector being coupled with a boom or yoke with the main body structure by way of a two or three axis positioning mechanism configured to steer the reflector with respect to the main body structure. In some implementations, in the on-orbit configuration, the plurality of modular reflector elements are assembled to form a large aperture reflective surface that is self-supporting.
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公开(公告)号：US10661918B2
公开(公告)日：2020-05-26
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
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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