Patents by Inventor Jerome K. Fuller
Jerome K. Fuller 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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Publication number: 20240147626Abstract: A dynamic flex circuit includes a plurality of hole sets arranged along the dynamic flexible circuit. The dynamic flex circuit also includes a plurality of actuator wires coupled to the dynamic flexible circuit by way of intertwining each of the plurality of actuator wires through each hole set in the plurality of hole sets arrange along the dynamic flexible circuit. Each of the plurality of actuator wires are configured to impart a motion onto the dynamic flexible circuit depending on the amount of heat applied to each of the plurality of actuator wires.Type: ApplicationFiled: November 2, 2022Publication date: May 2, 2024Applicant: The Aerospace CorporationInventors: Jerome K. FULLER, Todd Fillmore SHEERIN
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Patent number: 11420775Abstract: To reduce space debris and decrease risks for future space flights and currently operating satellites, NASA requires all satellites to have an end of life deorbiting plan to prevent satellites from having long and indefinite orbit lifespan. Accordingly, disclosed herein are systems and methods for deploying a deorbiting drag device to dramatically decrease the orbit lifespan of satellites. One of the methods comprises: providing power, using a photovoltaic panel, to a central processing unit (CPU) of the satellite; determining, using a health sensor, a health status of the satellite by monitoring activities of the CPU; and releasing a deorbiting drag device based on the health status by diverting power from the photovoltaic panel to a release actuator.Type: GrantFiled: October 4, 2018Date of Patent: August 23, 2022Assignee: THE AEROSPACE CORPORATIONInventor: Jerome K. Fuller
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Patent number: 11119256Abstract: Many in the space weather community consider our understanding of the buoyancy of the thermosphere and its effects on the orbits of satellites in Low Earth Orbit (LEO) to be insufficient during short time frames. Disclosed herein is an approach for making on-demand thermosphere buoyancy measurements using a deployable low mass retroreflector with CubeSat-like dimensions. A CubeSat storing many retroreflectors can dispense one or more of these passive satellites according to a predetermined schedule or on-command, in response to an observed space weather phenomenon like a coronal mass ejection. With measurements of the orbit decay from these passive satellites, a better understanding of the relationship between space weather and orbital decay can be established with relatively low cost.Type: GrantFiled: April 3, 2019Date of Patent: September 14, 2021Assignee: THE AEROSPACE CORPORATIONInventor: Jerome K. Fuller
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Patent number: 10914842Abstract: A data recovery device configured to store data onboard a hypersonic vehicle travelling at hypersonic speeds. The data recovery device is released from the hypersonic vehicle upon a release command or an anomalous event. Upon release, the data recovery device is configured to receive Global Positioning System (GPS) position data and configured to broadcast the GPS position data in short bursts during decent to a surface of the Earth and upon impact with the surface of the Earth to aid in recovery of the data recovery device.Type: GrantFiled: November 23, 2018Date of Patent: February 9, 2021Assignee: The Aerospace CorporationInventors: William H. Ailor, III, Jeffrey Arthur Lang, James Lawrence Hoffman, II, Jerome K. Fuller, Jeffry Padin, Michael Alan Weaver, Franklin John Bayuk
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Publication number: 20200319385Abstract: Many in the space weather community consider our understanding of the buoyancy of the thermosphere and its effects on the orbits of satellites in Low Earth Orbit (LEO) to be insufficient during short time frames. Disclosed herein is an approach for making on-demand thermosphere buoyancy measurements using a deployable low mass retroreflector with CubeSat-like dimensions. A CubeSat storing many retroreflectors can dispense one or more of these passive satellites according to a predetermined schedule or on-command, in response to an observed space weather phenomenon like a coronal mass ejection. With measurements of the orbit decay from these passive satellites, a better understanding of the relationship between space weather and orbital decay can be established with relatively low cost.Type: ApplicationFiled: April 3, 2019Publication date: October 8, 2020Inventor: Jerome K. Fuller
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Patent number: 10683107Abstract: A release apparatus includes a base member and a channel having a first portion and a second portion. A first rod positioned within the first portion includes a first end portion having a first coupling device and a second end portion coupled to a first portion of a panel assembly. A second rod positioned within the channel's second portion includes a first end portion having a second coupling device such that the second coupling device is positioned proximate to the first coupling device. The second rod includes a second end portion coupled to a second portion of the panel assembly. First and second coupling devices rotate such that a linear force is generated between the first and second rods, enabling the first rod second end portion and the second rod second end portion to simultaneously release the first and second portions of the panel assembly, respectively.Type: GrantFiled: August 4, 2017Date of Patent: June 16, 2020Assignee: The Aerospace CorporationInventors: Jerome K. Fuller, Alexander August-Schmidt, Geoffrey A. Maul, Cody L. Shaw
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Publication number: 20200166651Abstract: A data recovery device configured to store data onboard a hypersonic vehicle travelling at hypersonic speeds. The data recovery device is released from the hypersonic vehicle upon a release command or an anomalous event. Upon release, the data recovery device is configured to receive Global Positioning System (GPS) position data and configured to broadcast the GPS position data in short bursts during decent to a surface of the Earth and upon impact with the surface of the Earth to aid in recovery of the data recovery device.Type: ApplicationFiled: November 23, 2018Publication date: May 28, 2020Inventors: William H. AILOR, III, Jeffrey Arthur LANG, James Lawrence HOFFMAN, II, Jerome K. FULLER, Jeffry PADIN, Michael Alan WEAVER, Franklin John BAYUK
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Publication number: 20200108953Abstract: To reduce space debris and decrease risks for future space flights and currently operating satellites, NASA requires all satellites to have an end of life deorbiting plan to prevent satellites from having long and indefinite orbit lifespan. Accordingly, disclosed herein are systems and methods for deploying a deorbiting drag device to dramatically decrease the orbit lifespan of satellites. One of the methods comprises: providing power, using a photovoltaic panel, to a central processing unit (CPU) of the satellite; determining, using a health sensor, a health status of the satellite by monitoring activities of the CPU; and releasing a deorbiting drag device based on the health status by diverting power from the photovoltaic panel to a release actuator.Type: ApplicationFiled: October 4, 2018Publication date: April 9, 2020Inventor: Jerome K. Fuller
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Patent number: 10414518Abstract: Attitude of a vehicle may be controlled using movable mass. The movable mass may move inside a vehicle or its outline, outside of the vehicle or its outline, inside-to-outside and/or outside-to-inside of the vehicle or its outline, or any combination thereof. The movable mass may be a solid, liquid, and/or gas. When the center-of-mass of the vehicle is moved relative to the line-of-action of applied forces such as thrust, drag, or lift, a torque can be generated for attitude control or for other purposes as a matter of design choice. In the case of external movable masses that extend from the vehicle or its outline, when operating in endoatmospheric flight, or general travel through a fluid, aerodynamic forces from the atmosphere or general fluid forces may further be leveraged to control the attitude of the vehicle (e.g., aerodynamic flaps).Type: GrantFiled: November 7, 2016Date of Patent: September 17, 2019Assignee: The Aerospace CorporationInventors: Kevin L Zondervan, Jerome K Fuller
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Publication number: 20190039758Abstract: A release apparatus includes a base member and a channel having a first portion and a second portion. A first rod positioned within the first portion includes a first end portion having a first coupling device and a second end portion coupled to a first portion of a panel assembly. A second rod positioned within the channel's second portion includes a first end portion having a second coupling device such that the second coupling device is positioned proximate to the first coupling device. The second rod includes a second end portion coupled to a second portion of the panel assembly. First and second coupling devices rotate such that a linear force is generated between the first and second rods, enabling the first rod second end portion and the second rod second end portion to simultaneously release the first and second portions of the panel assembly, respectively.Type: ApplicationFiled: August 4, 2017Publication date: February 7, 2019Inventors: Jerome K. FULLER, Alexander AUGUST-SCHMIDT, Geoffrey A. MAUL, Cody L. SHAW
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Patent number: 9919792Abstract: Attitude and/or attitude rate of a vehicle may be controlled using jet paddles and/or movable masses. Thrust direction generally may also be controlled using jet paddles. The jet paddles may be moved into and/or sufficiently close to the exhaust flow, and out of the exhaust flow, to change the thrust direction. Movable masses may also be used in addition to, or in lieu of, jet paddles. Movement of the movable masses alters a center-of-mass of the vehicle, generating torque that changes vehicle attitude.Type: GrantFiled: July 2, 2014Date of Patent: March 20, 2018Assignee: The Aerospace CorporationInventors: Kevin L Zondervan, Jerome K Fuller
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Publication number: 20170297748Abstract: Attitude of a vehicle may be controlled using movable mass. The movable mass may move inside a vehicle or its outline, outside of the vehicle or its outline, inside-to-outside and/or outside-to-inside of the vehicle or its outline, or any combination thereof. The movable mass may be a solid, liquid, and/or gas. When the center-of-mass of the vehicle is moved relative to the line-of-action of applied forces such as thrust, drag, or lift, a torque can be generated for attitude control or for other purposes as a matter of design choice. In the case of external movable masses that extend from the vehicle or its outline, when operating in endoatmospheric flight, or general travel through a fluid, aerodynamic forces from the atmosphere or general fluid forces may further be leveraged to control the attitude of the vehicle (e.g., aerodynamic flaps).Type: ApplicationFiled: November 7, 2016Publication date: October 19, 2017Applicant: The Aerospace CorporationInventors: Kevin L. Zondervan, Jerome K. Fuller
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Publication number: 20160194089Abstract: Attitude and/or attitude rate of a vehicle may be controlled using jet paddles and/or movable masses. Thrust direction generally may also be controlled using jet paddles. The jet paddles may be moved into and/or sufficiently close to the exhaust flow, and out of the exhaust flow, to change the thrust direction. Movable masses may also be used in addition to, or in lieu of, jet paddles. Movement of the movable masses alters a center-of-mass of the vehicle, generating torque that changes vehicle attitude.Type: ApplicationFiled: July 2, 2014Publication date: July 7, 2016Inventors: Kevin L. Zondervan, Jerome K. Fuller
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Patent number: 9038368Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for providing a multi-fuel hybrid rocket motor. According to an example embodiment of the invention, a method is provided for producing a multi-fuel hybrid motor. The method can include forming a body, where the body includes one or more intake ports; one or more exit nozzles; one or more channels connecting the one or more intake ports with the one or more exit nozzles; and a plurality of cavities comprising segment walls in communication with the one or more channels. The method also includes depositing a propellant fuel within the plurality of cavities, wherein at least a portion of the propellant fuel is exposed to the one or more channels and wherein the propellant fuel has a higher burn consumption rate than the segment walls.Type: GrantFiled: August 1, 2011Date of Patent: May 26, 2015Assignee: THE AEROSPACE CORPORATIONInventor: Jerome K. Fuller
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Patent number: 8844133Abstract: A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design,Type: GrantFiled: July 23, 2012Date of Patent: September 30, 2014Assignee: The Aerospace CorporationInventor: Jerome K. Fuller
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Patent number: 8707676Abstract: A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, the hybrid rocket motor including radial channels for defining a desired burn profile including the oxidizer to fuel burn ratio.Type: GrantFiled: February 28, 2008Date of Patent: April 29, 2014Assignee: The Aerospace CorporationInventor: Jerome K. Fuller
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Patent number: 8616496Abstract: Embodiments of the invention relate to systems and methods for a self-deploying vehicle drag device. In one embodiment, a drag device for a vehicle can be provided. The drag device can include a chute body, wherein the chute body is connected to the vehicle. The drag device can also include at least one collapsible member mounted to the chute body, wherein the at least one collapsible member and chute body are maintained in respective compressed configurations until deployed. Furthermore, the drag device can include at least one device adapted to release the chute body from the vehicle, wherein the chute body and the at least one collapsible member are deployed in expanded configurations with respect to the vehicle.Type: GrantFiled: August 3, 2011Date of Patent: December 31, 2013Assignee: The Aerospace CorporationInventors: Brian S. Hardy, Jerome K. Fuller
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Patent number: 8601790Abstract: A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, the hybrid rocket motor including buried radial channels for defining a desired burn profile including the oxidizer to fuel burn ratio.Type: GrantFiled: February 28, 2008Date of Patent: December 10, 2013Assignee: The Aerospace CorporationInventor: Jerome K. Fuller
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Patent number: 8538606Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for sensing flight direction of a spacecraft. According to an example embodiment of the invention, a method is provided for determining flight direction of a spacecraft. The method includes providing at least one imaging detector associated with a spacecraft; imaging at least a portion of a celestial body onto the at least one imaging detector; acquiring, by the at least one imaging detector, sequential images of at least a portion of the celestial body; and determining the spacecraft flight direction relative to the celestial body based at least in part on processing the sequential images, wherein the processing is performed by one or more computer processors.Type: GrantFiled: November 3, 2010Date of Patent: September 17, 2013Assignee: The Aerospace CorporationInventors: Siegfried W. Janson, Jerome K. Fuller
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Publication number: 20130031888Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for providing a multi-fuel hybrid rocket motor. According to an example embodiment of the invention, a method is provided for producing a multi-fuel hybrid motor. The method can include forming a body, where the body includes one or more intake ports; one or more exit nozzles; one or more channels connecting the one or more intake ports with the one or more exit nozzles; and a plurality of cavities comprising segment walls in communication with the one or more channels. The method also includes depositing a propellant fuel within the plurality of cavities, wherein at least a portion of the propellant fuel is exposed to the one or more channels and wherein the propellant fuel has a higher burn consumption rate than the segment walls.Type: ApplicationFiled: August 1, 2011Publication date: February 7, 2013Applicant: THE AEROSPACE CORPORATIONInventor: Jerome K. Fuller