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公开(公告)号：US20240059431A1
公开(公告)日：2024-02-22
申请号：US18501264
申请日：2023-11-03
申请人： Maxar Space LLC
发明人： Harry A. Yates , Tom Hsieh , Ryan Bieniek , Ben Kwong , Robert Szombathy , Martinus Meerman , Frederick Oey , Peter Amnuaypayoat , Alan J. Szeto , Richard B. Warnock
摘要： A solar array structure for a spacecraft is based on a modular approach, allowing for arrays to be designed, and designed to be modified, and manufactured in reduced time and with reduced cost. The embodiments for the solar array are formed of multiple copies of a “bay” of a multiple strings of solar array cells mounted on semi-rigid face-sheet structural elements. The bays are then placed into frame structures made of tubes connected by nodes to provide an easily scalable, configurable, and producible solar array wing structure. This allows for rapid turnaround of program specific designs and proposal iterations that is quickly adaptable to new/future PhotoVoltaic (PV) technologies and that can create uniquely shaped (i.e., not rectangular) arrays, allowing for mass production with simple mass producible building blocks.
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公开(公告)号：US20230286678A1
公开(公告)日：2023-09-14
申请号：US17694534
申请日：2022-03-14
申请人： Maxar Space LLC
CPC分类号： B64G4/00 , B64G1/36 , B64G1/40 , B64G1/52 , B64G2004/005
摘要： To facilitate on-orbit servicing, such as for a refueling operation, techniques are presented for a servicing satellite to cut through the multi-layer insulation blanket of a client satellite to provide access to the client satellite without releasing unacceptable quantities of foreign object debris from the multi-layer insulation. The serving satellite includes a sealing tool, such as a pair of heater rollers, that apply pressure and heat to the insulating blanket to melt the inner layers and seal the outer layers together. The servicing satellite can then use a cutting tool to cut the sealed region and access the client satellite.
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公开(公告)号：US20230115933A1
公开(公告)日：2023-04-13
申请号：US17948011
申请日：2022-09-19
申请人： Maxar Space LLC
发明人： Harry A. Yates , Tom Hsieh , Ryan Bieniek , Ben Kwong , Robert Szombathy , Martinus Meerman , Frederick Oey , Peter Amnuaypayoat , Alan J. Szeto , Richard B. Warnock
摘要： A solar array structure for a spacecraft is based on a modular approach, allowing for arrays to be designed, and designed to be modified, and manufactured in reduced time and with reduced cost. The embodiments for the solar array are formed of multiple copies of a “bay” of a multiple strings of solar array cells mounted on semi-rigid face-sheet structural elements. The bays are then placed into frame structures made of tubes connected by nodes to provide an easily scalable, configurable, and producible solar array wing structure. This allows for rapid turnaround of program specific designs and proposal iterations that is quickly adaptable to new/future PhotoVoltaic (PV) technologies and that can create uniquely shaped (i.e., not rectangular) arrays, allowing for mass production with simple mass producible building blocks.
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公开(公告)号：US20240239523A1
公开(公告)日：2024-07-18
申请号：US18620445
申请日：2024-03-28
申请人： Maxar Space LLC
CPC分类号： B64G4/00 , B64G1/36 , B64G1/40 , B64G1/52 , B64G2004/005
摘要： To facilitate on-orbit servicing, such as for a refueling operation, techniques are presented for a servicing satellite to cut through the multi-layer insulation blanket of a client satellite to provide access to the client satellite without releasing unacceptable quantities of foreign object debris from the multi-layer insulation. The serving satellite includes a sealing tool, such as a pair of heater rollers, that apply pressure and heat to the insulating blanket to melt the inner layers and seal the outer layers together. The servicing satellite can then use a cutting tool to cut the sealed region and access the client satellite.
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公开(公告)号：US11970292B2
公开(公告)日：2024-04-30
申请号：US17694534
申请日：2022-03-14
申请人： Maxar Space LLC
CPC分类号： B64G4/00 , B64G1/36 , B64G1/40 , B64G1/52 , B64G2004/005
摘要： To facilitate on-orbit servicing, such as for a refueling operation, techniques are presented for a servicing satellite to cut through the multi-layer insulation blanket of a client satellite to provide access to the client satellite without releasing unacceptable quantities of foreign object debris from the multi-layer insulation. The serving satellite includes a sealing tool, such as a pair of heater rollers, that apply pressure and heat to the insulating blanket to melt the inner layers and seal the outer layers together. The servicing satellite can then use a cutting tool to cut the sealed region and access the client satellite.
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公开(公告)号：US11845571B2
公开(公告)日：2023-12-19
申请号：US17948011
申请日：2022-09-19
申请人： Maxar Space LLC
发明人： Harry A. Yates , Tom Hsieh , Ryan Bieniek , Ben Kwong , Robert Szombathy , Martinus Meerman , Frederick Oey , Peter Amnuaypayoat , Alan J. Szeto , Richard B. Warnock
摘要： A solar array structure for a spacecraft is based on a modular approach, allowing for arrays to be designed, and designed to be modified, and manufactured in reduced time and with reduced cost. The embodiments for the solar array are formed of multiple copies of a “bay” of a multiple strings of solar array cells mounted on semi-rigid face-sheet structural elements. The bays are then placed into frame structures made of tubes connected by nodes to provide an easily scalable, configurable, and producible solar array wing structure. This allows for rapid turnaround of program specific designs and proposal iterations that is quickly adaptable to new/future PhotoVoltaic (PV) technologies and that can create uniquely shaped (i.e., not rectangular) arrays, allowing for mass production with simple mass producible building blocks.
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