Patents by Inventor Walter Holemans
Walter Holemans 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).
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Patent number: 11572202Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all of the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.Type: GrantFiled: December 21, 2021Date of Patent: February 7, 2023Assignee: Planetary Systems CorporationInventors: Walter Holemans, Ryan Williams
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Patent number: 11565833Abstract: After deploying its payload, the final stage of a launch vehicle is maneuvered to couple the nosecone of the launch vehicle to the ‘rear’, or ‘engine-end’ of the final stage. The nosecone covers the engine of the final stage, to protect the engine and related components from the heat of re-entry and the impact of landing. Placing the nosecone over the engine and orienting the combination such that the nosecone ‘leads’ the final stage during re-entry, places the center of gravity of the combination ahead of the center of pressure in the direction of travel. Accordingly, the combination is inherently stable as it re-enters the atmosphere and falls to earth. Parachutes and directional devices are used to provide a controlled soft landing.Type: GrantFiled: September 9, 2020Date of Patent: January 31, 2023Assignee: Planetary Systems CorporationInventors: Walter Holemans, Ryan Williams
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Publication number: 20220119135Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.Type: ApplicationFiled: December 21, 2021Publication date: April 21, 2022Applicant: Planetary Systems CorporationInventors: Walter HOLEMANS, Ryan Williams
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Publication number: 20220111980Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all of the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.Type: ApplicationFiled: December 21, 2021Publication date: April 14, 2022Applicant: Planetary Systems CorporationInventors: Walter Holemans, Ryan Williams
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Patent number: 11267591Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all of the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.Type: GrantFiled: July 15, 2019Date of Patent: March 8, 2022Assignee: Planetary Systems CorporationInventors: Walter Holemans, Ryan Williams
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Publication number: 20210070480Abstract: After deploying its payload, the final stage of a launch vehicle is maneuvered to couple the nosecone of the launch vehicle to the ‘rear’, or ‘engine-end’ of the final stage. The nosecone covers the engine of the final stage, to protect the engine and related components from the heat of re-entry and the impact of landing. Placing the nosecone over the engine and orienting the combination such that the nosecone ‘leads’ the final stage during re-entry, places the center of gravity of the combination ahead of the center of pressure in the direction of travel. Accordingly, the combination is inherently stable as it re-enters the atmosphere and falls to earth. Parachutes and directional devices are used to provide a controlled soft landing.Type: ApplicationFiled: September 9, 2020Publication date: March 11, 2021Applicant: Planetary Systems CorporationInventors: Walter HOLEMANS, Ryan Williams
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Patent number: 10703512Abstract: A spacecraft coupling system includes a locking component that can be deformed and placed into a stable state that locks one component into a mating component, and can easily be released from the deformed state, decoupling the two components. The locking component may include a central ring, a plurality of leaf elements arranged at the perimeter of the locking component, and a plurality of fins that extend outward from the ring to the plurality of leaf elements. A rotation of the ring element while the component is held stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently tension the leaf elements against surfaces on the mating component. To reduce cost and complexity, the locking component comprises a metal, such as titanium, that can be formed using an additive manufacturing process, commonly termed a 3-D printing process.Type: GrantFiled: June 16, 2017Date of Patent: July 7, 2020Assignee: Planetary Systems CorporationInventor: Walter Holemans
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Patent number: 10611449Abstract: A substantially hollow wingsail is configured to enable electrical components to be situated within the wingsail. In particular, the wingsail may be configured to contain the solar panels used to power the other electrical components of the vessel, as well as other items that are conventionally situated on the exterior of the vessel, such as antennas, navigation lights, and so on. The interior of the wingsail may also include a deployment device for deploying components stored in the wingsail into the sea or the atmosphere. The surface of the wingsail may include transparent or translucent areas to provide light to the solar panels, as well as optical and electromagnetic reflective areas within the wingsail to enhance the performance of the solar panels and antennas. The wingsail may also include an internal light that illuminates the translucent areas of the wingsail for enhanced visibility to other vessels.Type: GrantFiled: October 11, 2018Date of Patent: April 7, 2020Assignee: Marine Robotics, LLCInventors: Walter Holemans, Vincent Vandyck
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Publication number: 20200017243Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all of the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.Type: ApplicationFiled: July 15, 2019Publication date: January 16, 2020Applicant: Planetary Systems CorporationInventors: Walter HOLEMANS, Ryan Williams
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Publication number: 20190047670Abstract: A substantially hollow wingsail is configured to enable electrical components to be situated within the wingsail. In particular, the wingsail may be configured to contain the solar panels used to power the other electrical components of the vessel, as well as other items that are conventionally situated on the exterior of the vessel, such as antennas, navigation lights, and so on. The interior of the wingsail may also include a deployment device for deploying components stored in the wingsail into the sea or the atmosphere. The surface of the wingsail may include transparent or translucent areas to provide light to the solar panels, as well as optical and electromagnetic reflective areas within the wingsail to enhance the performance of the solar panels and antennas. The wingsail may also include an internal light that illuminates the translucent areas of the wingsail for enhanced visibility to other vessels.Type: ApplicationFiled: October 11, 2018Publication date: February 14, 2019Applicant: Marine Robotics, LLC.Inventors: Walter Holemans, Vincent Vandyck
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Patent number: 10124868Abstract: A substantially hollow wingsail is configured to enable electrical components to be situated within the wingsail. In particular, the wingsail may be configured to contain the solar panels used to power the other electrical components of the vessel, as well as other items that are conventionally situated on the exterior of the vessel, such as antennas, navigation lights, and so on. The surface of the wingsail may include transparent or translucent areas to provide light to the solar panels, as well as optical and electromagnetic reflective areas within the wingsail to enhance the performance of the solar panels and antennas. The wingsail may also include an internal light that illuminates the translucent areas of the wingsail for enhanced visibility to other vessels.Type: GrantFiled: February 22, 2017Date of Patent: November 13, 2018Assignee: Marine Robotics, LLC.Inventors: Vincent Vandyck, Walter Holemans
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Publication number: 20180217588Abstract: An apparatus and method for control of at least one of a plurality of semiautonomous marine vessels are provided. The system includes a control station with a communications system for network communication with marine vessels, and provides diagnostics and control for control and monitoring of the marine vessels, according to a mission plan.Type: ApplicationFiled: September 11, 2017Publication date: August 2, 2018Applicant: Autonomous Marine Systems Inc.Inventors: Thomas Edwards, Eamon Carrig, Scott Nguyen, James Nugen, Walter Holemans
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Publication number: 20170283097Abstract: A spacecraft coupling system includes a locking component that can be deformed and placed into a stable state that locks one component into a mating component, and can easily be released from the deformed state, decoupling the two components. The locking component may include a central ring, a plurality of leaf elements arranged at the perimeter of the locking component, and a plurality of fins that extend outward from the ring to the plurality of leaf elements. A rotation of the ring element while the component is held stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently tension the leaf elements against surfaces on the mating component. To reduce cost and complexity, the locking component comprises a metal, such as titanium, that can be formed using an additive manufacturing process, commonly termed a 3-D printing process.Type: ApplicationFiled: June 16, 2017Publication date: October 5, 2017Applicant: Planetary Systems CorporationInventor: Walter HOLEMANS
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Publication number: 20170267324Abstract: A substantially hollow wingsail is configured to enable electrical components to be situated within the wingsail. In particular, the wingsail may be configured to contain the solar panels used to power the other electrical components of the vessel, as well as other items that are conventionally situated on the exterior of the vessel, such as antennas, navigation lights, and so on. The surface of the wingsail may include transparent or translucent areas to provide light to the solar panels, as well as optical and electromagnetic reflective areas within the wingsail to enhance the performance of the solar panels and antennas. The wingsail may also include an internal light that illuminates the translucent areas of the wingsail for enhanced visibility to other vessels.Type: ApplicationFiled: February 22, 2017Publication date: September 21, 2017Applicant: Marine Robotics, LLC.Inventors: Vincent VANDYCK, Walter Holemans
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Patent number: 9707748Abstract: A spacecraft coupling system includes an integral component that can be deformed and placed into a stable state that locks one component into a mating component, and can easily be released from the deformed state, decoupling the two components. The integral component may include a central ring, a plurality of leaf elements arranged at the perimeter of the component, and a plurality of fins that extend outward from the ring to the plurality of leaf elements. A rotation of the ring element while the component is held stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently force the leaf elements against surfaces on the mating component. To reduce cost and complexity, the integral component is a metal, such as titanium, that can be formed using an additive manufacturing process, commonly termed a 3-D printing process.Type: GrantFiled: October 3, 2014Date of Patent: July 18, 2017Assignee: Planetary Systems CorporationInventor: Walter Holemans
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Publication number: 20170097639Abstract: An apparatus and method for control of at least one of a plurality of semiautonomous marine vessels are provided. The system includes a control station with a communications system for network communication with marine vessels, and provides diagnostics and control for control and monitoring of the marine vessels, according to a mission plan.Type: ApplicationFiled: August 10, 2016Publication date: April 6, 2017Applicant: Autonomous Marine Systems Inc.Inventors: Thomas Edwards, Eamon Carrig, Scott Nguyen, James Nugen, Walter Holemans
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Patent number: 9415883Abstract: A canisterized satellite dispenser includes one or more of: a pair of guide rails that eliminate the requirement of a rectangular profile for the satellite; a preload system that secures the canisterized satellite during transport and launch, and releases to deploy the canisterized satellite; a constant-force spring to provide a uniform and predictable dispensing force; an external rectangular profile in each dimension; and internal support surfaces that simplify the design of canisterized satellites, particularly those with deployable components. Each canisterized satellite includes a pair of opposing flanges on a lower portion of the satellite that ride in a channel formed by the dispenser's guide rails and restraining flanges; no other support constraints are imposed. During travel and launch, the satellite flanges are held against the restraining flanges, rigidly fixing the satellite to the dispenser until the satellite is deployed.Type: GrantFiled: November 21, 2013Date of Patent: August 16, 2016Assignee: Planetary Systems CorporationInventors: Walter Holemans, Ryan Hevner
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Publication number: 20160147223Abstract: An apparatus and method for control of at least one of a plurality of semiautonomous marine vessels are provided. The system includes a control station with a communications system for network communication with marine vessels, and provides diagnostics and control for control and monitoring of the marine vessels, according to a mission plan.Type: ApplicationFiled: January 15, 2015Publication date: May 26, 2016Inventors: Thomas Edwards, Eamon Carrig, Scott Nguyen, James Nugen, Walter Holemans
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Patent number: 9086033Abstract: Propulsion systems and method for making a propulsion system include additively manufacturing a casing body into a single-piece structure having no bonded or bolted joints. The casing body defines a combustion chamber therein and is at least partially composed of a material useful as a solid rocket fuel and capable of being consumed during combustion. Other embodiments are also described.Type: GrantFiled: September 13, 2011Date of Patent: July 21, 2015Inventors: Matthew Dushku, Walter Holemans
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Publication number: 20150097085Abstract: A spacecraft coupling system includes an integral component that can be deformed and placed into a stable state that locks one component into a mating component, and can easily be released from the deformed state, decoupling the two components. The integral component may include a central ring, a plurality of leaf elements arranged at the perimeter of the component, and a plurality of fins that extend outward from the ring to the plurality of leaf elements. A rotation of the ring element while the component is held stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently tension the leaf elements against surfaces on the mating component. To reduce cost and complexity, the integral component is a metal, such as titanium, that can be formed using an additive manufacturing process, commonly termed a 3-D printing process.Type: ApplicationFiled: October 3, 2014Publication date: April 9, 2015Applicant: Planetary Systems CorporationInventor: Walter HOLEMANS