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1.发明申请公开(公告)号：US20250051042A1
公开(公告)日：2025-02-13
申请号：US18721813
申请日：2022-12-23
Applicant: MacDonald, Dettwiler and Associates Inc.
Inventor： Tej Singh Sachdev , Philip Raymond Apperly , Steve Fisher , Charles Cass
Abstract: Systems, methods, and devices for robotic capture of an object are provided. A system for robotic-based capture of a free flyer object includes a grapple fixture for mounting to the free flyer object and an end effector for capturing the free flyer object by interfacing with the grapple fixture. The grapple fixture includes a base and a deflectable probe. The end effector includes a probe guiding surface for deflecting and guiding a probe tip of the probe through an opening in the probe guiding surface and into a grappling position. The end effector includes a probe sensing element for sensing when the probe tip is in the grappling position and triggering a capture mechanism. The capture mechanism grapples the probe tip and an actuator retracts the capture mechanism to a predetermined position to establish a load-bearing interface between the free flyer object and the end effector.
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公开(公告)号：US12221235B2
公开(公告)日：2025-02-11
申请号：US18048312
申请日：2022-10-20
Applicant: Sidus Space, Inc.
Inventor： Carol Craig , Ryan Jeffrey , Anthony Boschi
Abstract: A cube satellite deployer system having a body plate, a communication unit, a power unit, and a control unit. The body plate is adapted to be connected to a space arm assembly. The communication unit and the power unit are attached to the body plate. Each of the communication unit, power unit, and the control unit are in communication with one another. The body plate is also adapted to receive one or more cube satellite housings. The cube satellite housings are adapted to house and selectively launch one or more of the cube satellites that are housed by the cube satellite housings.
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公开(公告)号：US20250011011A1
公开(公告)日：2025-01-09
申请号：US18891826
申请日：2024-09-20
Applicant: Astroscale Israel Ltd.
Inventor： Arnon Spitzer
Abstract: Satellite systems and methods to perform rendezvous between a servicer satellite and an on-orbit satellite, and specifically to satellite systems and methods to perform rendezvous between a servicer satellite and an on-orbit client satellite using electric propulsion thrusters. In one aspect, a servicer satellite fires thrusters to reduce a separation distance between the servicer satellite and the client satellite and to remove an angular momentum or a rotational velocity of the servicer satellite, and fires thrusters to reduce a rate of closure between the servicer satellite and the client satellite and to remove the angular momentum or the rotational velocity of the servicer satellite.
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4.发明申请公开(公告)号：US20240391610A1
公开(公告)日：2024-11-28
申请号：US18673290
申请日：2024-05-23
Applicant: UNIVERSITY OF MALTA
Inventor： Daniel CUMBO , Marc Anthony AZZOPARDI
Abstract: The disclosure concerns a satellite for inclusion in a satellite assembly comprising a plurality of satellites for deployment in space. The satellite comprising a satellite disengagement mechanism configured to separate the satellite from one or more adjacent satellites of the satellite assembly. The satellite disengagement mechanism comprises one or more disengagement coils configured to generate a repulsive electromagnetic force to separate the satellite from the one or more adjacent satellites.
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公开(公告)号：US12152628B1
公开(公告)日：2024-11-26
申请号：US17061653
申请日：2020-10-02
Applicant: Cornerstone Research Group, Inc.
Inventor： Jason Rice , Mark Cridge , Trang Young , Brian Pleiman , Kory Evanson , Jason Hermiller
Abstract: A reversible joint includes male and female components. The male component has a rigid stud with a shaft region and a head region having a greater width, than the shaft region. The female component includes a polymer-based bushing including a polymer sleeve and an embedded heating element. The polymer sleeve is formed from a shape memory polymer (SMP) or an SMP composite and includes a central channel. The polymer-based bushing is capable of being activated by heating with the embedded heating element to reversibly render the polymer sleeve elastic and allow deformation of the central channel to an expanded channel width during insertion of the head region. The polymer sleeve becomes rigid after deactivation of the polymer-based bushing for retention of the male component. Load bearing assemblies formed by connecting modular structures with the reversible joint are also provided along with installation tools for the same.
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Patent Agency Ranking
公开(公告)号：US12145751B2
公开(公告)日：2024-11-19
申请号：US18228311
申请日：2023-07-31
Applicant: Ensign-Bickford Aerospace & Defense Company
Inventor： William Fairlie , Erik Saucier
Abstract: Separation device assemblies are provided. The assemblies include a plurality of first segment elements, each first segment element having an attachment portion and a frangible portion, the attachment portion of the first segment elements is arranged to fixedly connect to a first structural component and at least one second segment element having an attachment portion and a securing portion, wherein the attachment portion of the at least one second segment element is arranged to fixedly connect to a second structural component. At least two of the plurality of first segment elements are attached to the at least one second segment element adjacent to each other and a first segment joint is formed between adjacent first segment elements. An expansion device cavity is formed between the attached first and second segment elements.
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公开(公告)号：US12097979B1
公开(公告)日：2024-09-24
申请号：US18205526
申请日：2023-06-03
Applicant: Astroscale Israel Ltd.
Inventor： Arnon Spitzer
Abstract: Satellite systems and methods to perform rendezvous and docking between a servicer satellite and an on-orbit satellite, and specifically to satellite systems and methods to perform rendezvous and docking between a servicer satellite and an on-orbit client satellite using electric propulsion thrusters. In one aspect, a servicer satellite with a set of thruster arms each attached to an electric propulsion thruster performs acceleration, deceleration, and steering maneuvers through six degree of freedom positioning of the thrusters, the same set of thruster arms and thrusters performing station keeping of the docked servicer-client satellite system.
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公开(公告)号：US20240275071A1
公开(公告)日：2024-08-15
申请号：US18626902
申请日：2024-04-04
Applicant: Blue Digs LLC
Inventor： Chris Cosner , Ying Feria , Raenaurd Turpin , Andre Houle , Richard Aston , Brett Cope , Ricardo Leon
CPC classification number: H01Q21/0018 , B64G1/641 , H01Q1/288 , H01Q5/42 , H01Q5/50 , B64G1/643 , H01Q1/08 , H04B7/18513 , H04B7/18515
Abstract: A satellite system can include one or more satellites that orbit the Earth. The one or more satellites may have satellite buses that support antenna arrays. The antenna arrays may include space fed arrays. Each space fed array may have an antenna feed array and an inner array that is coupled to a direct radiating array. The direct radiating array may operate in the same satellite band as the space fed array, or upconversion and downconversion circuitry may be used to communicatively couple a direct radiating array that operates in a different satellite band to the space fed array. The satellites may have peripheral walls with corner fittings that can be selected to provide the satellite bus with particular leg strengths. This can reduce overall mass of the satellites in a payload fairing while accommodating different types of antenna arrays.
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公开(公告)号：US20240270413A1
公开(公告)日：2024-08-15
申请号：US18441637
申请日：2024-02-14
Applicant: Lunar Outpost Inc.
Inventor： Andrew J. Gemer , Van Wagner , Bradley Jesteadt
Abstract: A vehicle locking assembly is disclosed, which couples a vehicle to a support member, for example using a frangible bolt and an actuator. When actuated, the actuator causes the frangible bolt to fail, thereby decoupling the vehicle from the support member. Ground-engaging members of the vehicle include terrain interaction features along an outer portion, thereby forming a portion of the ground-engaging member where the terrain interaction features (or, as another example, lack thereof) form a contact region that is radially closer to the center of the ground-engaging member as compared to the contact region(s) corresponding to other terrain interaction features. Accordingly, once the fastener is released, the ground-engaging members of the vehicle are actuated, such that the terrain interaction features engage with the plate/surface beneath the vehicle as the radially closer contact region rotates out from under the vehicle, thereby raising the vehicle off the support member.
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公开(公告)号：US12017808B2
公开(公告)日：2024-06-25
申请号：US17554000
申请日：2021-12-17
Applicant: Maxar Space LLC
Inventor： Michael Freestone , Joel Boccio
Abstract: Technology is disclosed for a dispenserless multi-satellite launch configuration in which multiple satellites are interconnected to form a composite beam structure that provides stability independently of the launch vehicle. When in the launch configuration, the satellites are formed into a bundle, where each satellite connects by one or more simple connector along the edges of its inner facing vertical side to the satellite adjacent on each side. This composite beam structure provides a stable launch configuration independently of the launch vehicle. Each of the satellites also has one or more connectors along the bottom edge of the inner facing vertical side allowing the bundle to be attached to a ring type launch vehicle interface. Once launched, the satellites can be dispensed by releasing the connector.
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