Patents by Inventor Michael Freestone
Michael Freestone has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
Patent number: 12227313Abstract: A satellite includes a first radiator panel with first heat-generating components attached to its surface and a second radiator panel with second heat-generating components attached to its surface. One or more actuators are configured to deploy the first and second radiator panels from a compact configuration in which the first and second radiator panels are overlapping to a deployed configuration in which the first and second radiator panels are non-overlapping.Type: GrantFiled: November 30, 2021Date of Patent: February 18, 2025Assignee: Maxar Space LLCInventors: Michael Freestone, Joel Boccio
-
Patent number: 12162631Abstract: A passively damped mechanical system is disclosed, for example for use in aerospace applications where vibration can adversely affect navigational and operational instruments. In one example, the passively damped mechanical system includes an end fitting of a strut used to connect a structural element to a payload. The end fitting may include outer and inner cylindrical hubs, with a space between the outer and inner cylindrical hub at least partially filled with a viscoelastic material. In a further example, the passively damped mechanical system includes legs used to connect a structural element to a bracket configured to support a payload. Each leg may include a hollow interior having a lattice structure to add strength and a viscoelastic material to provide passive damping.Type: GrantFiled: December 17, 2020Date of Patent: December 10, 2024Assignee: Maxar Space LLCInventors: Michael Freestone, Brian M. Cayton, John Rappolt, Shane Abraham Seiwerts, Daniel Fluitt, Kevin Ziemann
-
Patent number: 12040740Abstract: 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.Type: GrantFiled: October 19, 2021Date of Patent: July 16, 2024Assignee: Maxar Space LLCInventors: Michael Freestone, Varouj Baghdasarian
-
Patent number: 12028016Abstract: 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.Type: GrantFiled: August 10, 2021Date of Patent: July 2, 2024Assignee: Maxar Space LLCInventors: Varouj Baghdasarian, Michael Freestone
-
Patent number: 12017808Abstract: 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.Type: GrantFiled: December 17, 2021Date of Patent: June 25, 2024Assignee: Maxar Space LLCInventors: Michael Freestone, Joel Boccio
-
Publication number: 20240140622Abstract: A radiator structure for a satellite is provided. A first radiator panel adapted to be positioned on a first side of a central body, and a second radiator panel adapted to be positioned on a second side of the central body. Other implementations include a third radiator panel positioned on a third side of the central body. The apparatus also includes at least one heat pipe embedded between a first face and a second face of each radiator panel and extending from the first radiator panel through the first radiator panel and through the second radiator panel. The heat pipe structurally supports the first radiator panel and the second radiator panel relative to the intermediate radiator panel. A method of manufacturing a radiator structure is also provided.Type: ApplicationFiled: November 2, 2022Publication date: May 2, 2024Applicant: Maxar Space LLCInventor: Michael Freestone
-
Publication number: 20230257137Abstract: 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.Type: ApplicationFiled: March 29, 2022Publication date: August 17, 2023Applicant: Maxar Space LLCInventors: Michael Freestone, Sean Dougherty
-
Publication number: 20230192325Abstract: 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.Type: ApplicationFiled: December 17, 2021Publication date: June 22, 2023Applicant: Maxar Space LLCInventors: Michael Freestone, Joel Boccio
-
Publication number: 20230166871Abstract: An example of a satellite includes a first radiator panel with first heat-generating components attached to its surface and a second radiator panel with second heat-generating components attached to its surface. One or more actuators are configured to deploy the first and second radiator panels from a compact configuration in which the first and second radiator panels are overlapping to a deployed configuration in which the first and second radiator panels are non-overlapping.Type: ApplicationFiled: November 30, 2021Publication date: June 1, 2023Applicant: Maxar Space LLCInventors: Michael Freestone, Joel Boccio
-
Publication number: 20230050780Abstract: 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.Type: ApplicationFiled: August 10, 2021Publication date: February 16, 2023Applicant: Maxar Space LLCInventors: Varouj Baghdasarian, Michael Freestone
-
Publication number: 20230049753Abstract: 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.Type: ApplicationFiled: October 19, 2021Publication date: February 16, 2023Applicant: Maxar Space LLCInventors: Michael Freestone, Varouj Baghdasarian
-
Publication number: 20220194636Abstract: A passively damped mechanical system is disclosed, for example for use in aerospace applications where vibration can adversely affect navigational and operational instruments. In one example, the passively damped mechanical system includes an end fitting of a strut used to connect a structural element to a payload. The end fitting may include outer and inner cylindrical hubs, with a space between the outer and inner cylindrical hub at least partially filled with a viscoelastic material. In a further example, the passively damped mechanical system includes legs used to connect a structural element to a bracket configured to support a payload. Each leg may include a hollow interior having a lattice structure to add strength and a viscoelastic material to provide passive damping.Type: ApplicationFiled: December 17, 2020Publication date: June 23, 2022Applicant: MAXAR SPACE LLCInventors: Michael Freestone, Brian M. Cayton, John Rappolt, Shane Abraham Seiwerts, Daniel Fluitt, Kevin Ziemann
-
Patent number: 11327261Abstract: A composite fiber braid arrangement includes at least one fiber optic sensor embedded in a polymer resin. The polymer resin encloses a tow formed from an untwisted bundle of graphite fibers, and the untwisted bundle, together with the polymer resin, is enclosed by an outer jacket comprised of relatively dry, non-resin-impregnated, graphite fibers. Techniques for controlling alignment of an assembly of structural members, each structural member including such a fiber braid arrangement are also disclosed.Type: GrantFiled: April 22, 2020Date of Patent: May 10, 2022Assignee: Space Systems/Loral, LLCInventors: Maxwell Perham, Kevin Ziemann, Michael Freestone