公开(公告)号：US20240351711A1

公开(公告)日：2024-10-24

申请号：US18304249

申请日：2023-04-20

Applicant: Maxar Space LLC

Inventor： Harry A. Yates ,  Ryan Bieniek ,  Alan J. Szeto ,  Kate Psyk ,  Jonathan Briend

IPC: B64G1/44 ,  B64G1/10

CPC classification number: B64G1/443 ,  B64G1/10

Abstract: An example of an apparatus includes a spacecraft body and a solar array that is attached to the spacecraft body. In addition, a solar array spring element is configured to provide a force between the solar array and one or more components of a neighboring spacecraft in a stack of spacecraft.

公开(公告)号：US11845571B2

公开(公告)日：2023-12-19

申请号：US17948011

申请日：2022-09-19

Applicant: Maxar Space LLC

Inventor： Harry A. Yates ,  Tom Hsieh ,  Ryan Bieniek ,  Ben Kwong ,  Robert Szombathy ,  Martinus Meerman ,  Frederick Oey ,  Peter Amnuaypayoat ,  Alan J. Szeto ,  Richard B. Warnock

IPC: B64G1/44 ,  H02S30/10 ,  H02S30/20

CPC classification number: B64G1/443 ,  H02S30/10 ,  H02S30/20

Abstract: 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.

公开(公告)号：US20240059431A1

公开(公告)日：2024-02-22

申请号：US18501264

申请日：2023-11-03

Applicant: Maxar Space LLC

Inventor： Harry A. Yates ,  Tom Hsieh ,  Ryan Bieniek ,  Ben Kwong ,  Robert Szombathy ,  Martinus Meerman ,  Frederick Oey ,  Peter Amnuaypayoat ,  Alan J. Szeto ,  Richard B. Warnock

IPC: B64G1/44 ,  H02S30/10 ,  H02S30/20

CPC classification number: B64G1/443 ,  H02S30/10 ,  H02S30/20

Abstract: 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.

公开(公告)号：US20230299714A1

公开(公告)日：2023-09-21

申请号：US17698437

申请日：2022-03-18

Applicant: Maxar Space LLC

Inventor： Harry A. Yates ,  Roselin Campos

IPC: H02S40/10 ,  B08B7/02 ,  B08B7/04 ,  B08B13/00 ,  B06B1/06 ,  H02S30/20

CPC classification number: H02S40/10 ,  B08B7/02 ,  B08B7/04 ,  B08B13/00 ,  B06B1/0629 ,  H02S30/20 ,  B06B2201/70

Abstract: Described herein are apparatuses and methods for use therewith that can be used to remove dust and other types of particulates from a solar array of a spacecraft, a lander, a rover, or the like. Such an apparatus can include a main body and a solar array extending from the main body. One or more piezoelectric devices is/are attached to the solar array. The piezoelectric device(s), when activated, is/are configured to vibrate at least a portion of the solar array to thereby loosen particulates adhered thereto. The apparatus also includes one or more linear actuators that when actuated is/are configured to at least one of bump against, push on, or pull on at least a portion of the solar array to thereby jettison from the solar array at least some of the particulates that were loosened by the one or more piezoelectric devices.

公开(公告)号：US20230115933A1

公开(公告)日：2023-04-13

申请号：US17948011

申请日：2022-09-19

Applicant: Maxar Space LLC

Inventor： Harry A. Yates ,  Tom Hsieh ,  Ryan Bieniek ,  Ben Kwong ,  Robert Szombathy ,  Martinus Meerman ,  Frederick Oey ,  Peter Amnuaypayoat ,  Alan J. Szeto ,  Richard B. Warnock

IPC: B64G1/44 ,  H02S30/10 ,  H02S30/20

Abstract: 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.