Patents by Inventor Michael A. Leal
Michael A. Leal 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: 20240167844Abstract: A method and system for determining a geographical location and orientation of a vehicle travelling through a road network is disclosed. The method comprises obtaining, from one or more cameras associated with the vehicle travelling through the road network, a sequence of images reflecting the environment of the road network on which the vehicle is travelling, wherein each of the images has an associated camera location at which the image was recorded. A local map representation representing an area of the road network on which the vehicle is travelling is then generated using at least some of the obtained images and the associated camera locations. The generated local map representation is compared with a section of a reference map, the reference map section covering the area of the road network on which the vehicle is travelling, and the geographical location and orientation of the vehicle within the road network is determined based on the comparison.Type: ApplicationFiled: December 3, 2023Publication date: May 23, 2024Inventors: Tinosch Kolagheichi-Ganjineh, Philipp Holzschneider, Dimitri Schachmann, Sergej Mann, Sebastian Ihlefeld, Michael Hofmann, Olaf Booij, Nicolau Leal Werneck
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Patent number: 9115964Abstract: A projectile includes a propulsion booster for producing pressurized gases, a nozzle for expelling the pressurized gases produced by the booster, and a supplementary integrated actuation system. The integrated actuation system selectively directs propellant from a storage reservoir of the integrated actuation system through an interiorly-located outlet of the integrated actuation system located at the nozzle and into the nozzle, thus changing a direction of the pressurized gases expelled by the booster. The integrated actuation system also selectively directs propellant from the storage reservoir through a peripherally-located outlet of the integrated actuation system, to produce thrust at an external periphery of the projectile, thus diverting the projectile.Type: GrantFiled: December 27, 2013Date of Patent: August 25, 2015Assignee: Raytheon CompanyInventors: Andrew B Facciano, Michael S Alkema, Michael A Leal, Daniel Chasman, Robert T Moore
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Publication number: 20150184988Abstract: A projectile includes a propulsion booster for producing pressurized gases, a nozzle for expelling the pressurized gases produced by the booster, and a supplementary integrated actuation system. The integrated actuation system selectively directs propellant from a storage reservoir of the integrated actuation system through an interiorly-located outlet of the integrated actuation system located at the nozzle and into the nozzle, thus changing a direction of the pressurized gases expelled by the booster. The integrated actuation system also selectively directs propellant from the storage reservoir through a peripherally-located outlet of the integrated actuation system, to produce thrust at an external periphery of the projectile, thus diverting the projectile.Type: ApplicationFiled: December 27, 2013Publication date: July 2, 2015Applicant: Raytheon CompanyInventors: Andrew B Facciano, Michael S Alkema, Michael A Leal, Daniel Chasman, Robert T Moore
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Patent number: 9068808Abstract: An air vehicle, such as a missile or a steerable submunition released from a missile or another air vehicle, has a bilateral thrust system for steering. The thrust system includes a pair of diametrically-opposed divert thrusters that provide thrust having radial components in opposite radial directions. In order to control the direction of thrust, the air vehicle controls rotation of the divert thrusters and/or timing of the firing of the thrusters. The air vehicle (or some part of the air vehicle that includes the divert thrusters) may be discretely rolled to position the divert thrusters to produce desired steering thrust. Alternatively, the air vehicle or part of the air vehicle may be continuously rolled, with the steering controlled by timing the thrust to the divert thrusters, such as by allocating thrust between the diametrically-opposed thrusters. Pressurized gas may be allocated between the two thrusters by use of pintle valve.Type: GrantFiled: January 17, 2013Date of Patent: June 30, 2015Assignee: Raytheon CompanyInventors: Robert W Morgan, Eric J Borg, Michael A Leal, Adam D Nicholl
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Patent number: 8800913Abstract: An aeronautical vehicle includes at least one set of tandem divert thrusters incorporated into the body. Each set of tandem divert thrusters includes a first divert thruster and a second divert thruster, each configured to provide substantially equal thrust forces at substantially the same time and in substantially opposite directions such that the moment reference point lies between the first and second divert thrusters.Type: GrantFiled: January 29, 2010Date of Patent: August 12, 2014Assignee: Raytheon CompanyInventors: Philip W. Pagliara, Michael A. Leal, Justin C. Jenia, Teryn Dalbello, John M. Hitner
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Patent number: 8735788Abstract: Embodiments of a propulsion and maneuvering system that may be suitable for use during a terminal phase in an interceptor are generally described herein. The propulsion and maneuvering system may include one or more axial thrusters to provide thrust along axial thrust lines that run through a center-of-gravity of the interceptor and a plurality of divert thrusters to provide thrust in radial directions. The combination of divert and axial thrusters may allow the interceptor to respond to a maneuvering target and may allow the interceptor to increase its velocity along a line-of-sight (LOS) to a target to change target impact/engagement time.Type: GrantFiled: February 18, 2011Date of Patent: May 27, 2014Assignee: Raytheon CompanyInventors: Kenneth G. Preston, Michael A. Leal, Rondell J. Wilson, Richard C. Hussey
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Publication number: 20120211596Abstract: Embodiments of a propulsion and maneuvering system that may be suitable for use during a terminal phase in an interceptor are generally described herein. The propulsion and maneuvering system may include one or more axial thrusters to provide thrust along axial thrust lines that run through a center-of-gravity of the interceptor and a plurality of divert thrusters to provide thrust in radial directions. The combination of divert and axial thrusters may allow the interceptor to respond to a maneuvering target and may allow the interceptor to increase its velocity along a line-of-sight (LOS) to a target to change target impact/engagement time.Type: ApplicationFiled: February 18, 2011Publication date: August 23, 2012Applicant: Raytheon CompanyInventors: Kenneth G. Preston, Michael A. Leal, Rondell J. Wilson, Richard C. Hussey
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Publication number: 20110029160Abstract: An aeronautical vehicle includes at least one set of tandem divert thrusters incorporated into the body. Each set of tandem divert thrusters includes a first divert thruster and a second divert thruster, each configured to provide substantially equal thrust forces at substantially the same time and in substantially opposite directions such that the moment reference point lies between the first and second divert thrusters.Type: ApplicationFiled: January 29, 2010Publication date: February 3, 2011Applicant: RAYTHEON COMPANYInventors: Philip W. Pagliara, Michael A. Leal, Justin C. Jenia, Teryn Dalbello, John M. Hitner
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Patent number: 7494090Abstract: The present invention provides a MKV interceptor including multiple kill vehicles with autonomous management capability and kinematic reach to prosecute a large threat extent. Each KV can self-manage its own KV deployment and target engagement for a determined target volume assigned by a designated master KV. At least one KV is master capable of managing the post-separation of all of the KVs without requiring updates to the mission plan post-separation. The autonomous capability and increased kinematic reach provides for a more efficient use of boosters and more effective engagement of the threat.Type: GrantFiled: February 23, 2007Date of Patent: February 24, 2009Assignee: Raytheon CompanyInventors: Michael A. Leal, Todd L. Baker, Kent P. Pflibsen
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Publication number: 20080093498Abstract: The present invention provides a MKV interceptor including multiple kill vehicles with autonomous management capability and kinematic reach to prosecute a large threat extent. Each KV can self-manage its own KV deployment and target engagement for a determined target volume assigned by a designated master KV. At least one KV is master capable of managing the post-separation of all of the KVs without requiring updates to the mission plan post-separation. The autonomous capability and increased kinematic reach provides for a more efficient use of boosters and more effective engagement of the threat.Type: ApplicationFiled: February 23, 2007Publication date: April 24, 2008Inventors: Michael Leal, Todd Baker, Kent Pflibsen
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Patent number: 7287725Abstract: A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rotatable relative to the other. Control of flow through the nozzle plate may be effected by relative positioning of the portions of the nozzle plate. An upstream convergent portion of the nozzle plate may be fixed relative to the missile, with a downstream throat and/or divergent portion of the nozzle plate moveable. Movement of the movable portion of the nozzle plate may be accomplished by use of an actuator that is external to the missile body. The control valve provides a simple, lightweight and compact way of controlling flow from a divert thruster.Type: GrantFiled: April 25, 2005Date of Patent: October 30, 2007Assignee: Raytheon CompanyInventors: Daniel B. Chasman, Michael Leal, Stephen D. Haight
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Publication number: 20060284006Abstract: A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rotatable relative to the other. Control of flow through the nozzle plate may be effected by relative positioning of the portions of the nozzle plate. An upstream convergent portion of the nozzle plate may be fixed relative to the missile, with a downstream throat and/or divergent portion of the nozzle plate moveable. Movement of the movable portion of the nozzle plate may be accomplished by use of an actuator that is external to the missile body. The control valve provides a simple, lightweight and compact way of controlling flow from a divert thruster.Type: ApplicationFiled: April 25, 2005Publication date: December 21, 2006Inventors: Daniel Chasman, Michael Leal, Stephen Haight