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公开(公告)号：US12040740B2
公开(公告)日：2024-07-16
申请号：US17505359
申请日：2021-10-19
申请人： Maxar Space LLC
摘要： A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.
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公开(公告)号：US12017806B2
公开(公告)日：2024-06-25
申请号：US17580966
申请日：2022-01-21
申请人： Maxar Space LLC
发明人： Joel Boccio
CPC分类号： B64G1/503 , B64G1/443 , F28D2021/0021
摘要： A satellite includes a first radiator panel, a second radiator panel, a space defined between the first radiator panel and the second radiator panel, and one or more first heat-generating components located in the space. Each of the first heat-generating components is attached to at least one of the first or second radiator panels. The satellite further includes a third radiator panel extending from the space and one or more second heat-generating components located in the space, each of the second heat-generating components is attached to the third radiator panel.
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公开(公告)号：US20240159386A1
公开(公告)日：2024-05-16
申请号：US18054747
申请日：2022-11-11
申请人： Maxar Space LLC
发明人： Raymond Antetomoso
CPC分类号： F21V23/06 , F21V23/005 , F21Y2115/10
摘要： A connector loading device may comprise a receptacle, a plurality of light sources, and a controller. The receptacle may comprise a first plurality of holes. The first plurality of holes are configured to respectively line up with a second plurality of holes in a connector when the connector is inserted in the receptacle. Each one of the first plurality of holes comprises a respective and corresponding one of a plurality of unique indexes. The plurality of light sources respectively correspond to the first plurality of holes. Each one of the plurality of light sources, when initiated, is configured to illuminate light from a bottom of its respective one of the first plurality of holes through a top of its respective one of the first plurality of holes. The controller is configured to receive an input and initiate a one of the plurality of light sources corresponding to the index.
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公开(公告)号：US20240124167A1
公开(公告)日：2024-04-18
申请号：US17966470
申请日：2022-10-14
申请人： Maxar Space LLC
发明人： Theodore Marcopulos
IPC分类号： B64G7/00
摘要： An electric propulsion simulator console (EPSC) which electronically simulates an electric propulsion assembly of a spacecraft as well as propulsion fuel control components and positioning components of the spacecraft. The EPSC simulates a spacecraft thruster electrical interface can test four thruster interfaces simultaneously and continuously. The simulator additionally facilitates the testing of spacecraft fault detection, isolation, and recovery by simulating failed magnet circuits, open anode paths, and flameout conditions. The EPSC includes an electrical propulsion unit load simulator adapted to receive propulsion unit control signals from a spacecraft under test and a spacecraft propulsion unit positioner simulator the simulator adapted to display a simulated state of three axes of movement for at least one propulsion unit positioner responsive to positioning signals received from the spacecraft under test. A propulsion unit fuel valve simulator is also provided and can display a simulated state of propulsion unit fuel valves responsive to control signals received from the spacecraft under test.
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公开(公告)号：US20230370020A1
公开(公告)日：2023-11-16
申请号：US17748970
申请日：2022-05-19
申请人： Maxar Space LLC
CPC分类号： H02S50/00 , H02J3/381 , H02S10/40 , B64G1/443 , H02J2300/24
摘要： Technology is disclosed herein for reverse current protection for a photovoltaic module string. An apparatus has a switch connected between each respective PV module string and a power bus. A control circuit closes a set of the switches to connect a set of the PV module strings to the power bus to transfer power from the set of the photovoltaic PV module strings to the power bus. The control circuit determines whether a reverse current flows in the direction from the power bus to any of the PV module strings. The control circuit maintains the switch associated with a particular PV module string in an open state to prevent reverse current from flowing in the particular PV module string responsive to a determination that a reverse current flows in the particular PV module string when the particular PV module string is connected to the power bus.
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公开(公告)号：US11807403B2
公开(公告)日：2023-11-07
申请号：US17180615
申请日：2021-02-19
申请人： Maxar Space LLC
发明人： Jason J. Chiang , Gordon Wu
摘要： Techniques for minimizing diurnal temperature variation of a radiator of a spacecraft are disclosed. In one aspect, a spacecraft includes a body, a radiator panel, and a heat dissipating unit thermally coupled with the radiator panel. The spacecraft is configured to operate in an orbital plane, and has a yaw axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbital plane, and a roll axis orthogonal to the pitch axis and the yaw axis. The radiator panel includes a surface area external to a body of the spacecraft, a first portion of the surface area facing a first direction that is substantially parallel to the roll axis, and a second portion of the surface area facing a second direction that has a substantial component parallel to the yaw axis.
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公开(公告)号：US20230286672A1
公开(公告)日：2023-09-14
申请号：US18116106
申请日：2023-03-01
申请人： Maxar Space LLC
发明人： Sean Dougherty
CPC分类号： B64G1/16 , B62D7/06 , B62D5/0418 , B60G3/00
摘要： A rover includes a suspension configured to traverse uneven and unpredictable terrain, such as for example on an astronomical body. Each wheel is independently suspended off of the rover chassis with a linkage assembly comprising a pair of canted links which are able to continuously rotate relative to each other without collision or interference. The links allow the rover to independently adjust the height of each wheel relative to the chassis to drive over difficult terrain, and further allow the linkage assembly at each wheel to rotate 360° to effectively step or walk over particularly difficult terrain.
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公开(公告)号：US20230257137A1
公开(公告)日：2023-08-17
申请号：US17707475
申请日：2022-03-29
申请人： Maxar Space LLC
发明人： Michael Freestone , Sean Dougherty
摘要： An orbital satellite has a pair of multi-axis booms including both thrusters for course/attitude adjustment and an end effector for grappling payloads and manipulating other tools and objects. The satellite may launch with a primary payload affixed to a bus and one or more secondary payloads affixed to an ESPA ring. Once in orbit, the end effector may be used to grapple the primary and/or secondary payloads and rearrange them on the bus. In further aspects, the end effector may be used to make bus repairs or take measurements, or hold tools that are used to make bus repairs or take measurements.
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公开(公告)号：US20230234724A1
公开(公告)日：2023-07-27
申请号：US17580966
申请日：2022-01-21
申请人： Maxar Space LLC
发明人： Joel Boccio
摘要： An example of a satellite includes a first radiator panel, a second radiator panel, a space defined between the first radiator panel and the second radiator panel, and one or more first heat-generating components located in the space. Each of the first heat-generating components is attached to at least one of the first or second radiator panels. The satellite further includes a third radiator panel extending from the space and one or more second heat-generating components located in the space, each of the second heat-generating components is attached to the third radiator panel.
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公开(公告)号：US20230062667A1
公开(公告)日：2023-03-02
申请号：US17410702
申请日：2021-08-24
申请人： Maxar Space LLC
发明人： Varouj Baghdasarian
IPC分类号： B64G1/64
摘要： Technology is disclosed herein for a spacecraft launch restraint and dispensing structure. The dispensing structure has a number of trusses and a central structure. When the trusses are in a support position, each spacecraft may be supported at one point by the central structure and at two points by one or more of the trusses. Therefore, each spacecraft may be supported at three points, thereby providing a stable support for each spacecraft. The spacecrafts do not touch each other and do not bear the weight of other spacecrafts. In a deployment position, the trusses extend away from the satellites and do not support the satellites; however, the satellites initially remain connected to the central structure. In the deployment position, the trusses are out of an ejection path such that the satellites can be ejected in a desired sequence from the central structure.
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