Patents by Inventor Saghir Munir
Saghir Munir 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: 10230454Abstract: Cloud mask image data is obtained by a secondary imaging payload disposed on a communications or broadcast satellite operating in geosynchronous orbit. The obtained cloud mask image data is provisioned for use, in near real time, by one or more low earth orbit imaging satellite systems. Provisioning the obtained cloud mask image data may include collecting the data on the ground and making it available to one or more operators of the one or more LEO imaging satellite systems and/or transmitting the data from the communications or broadcast satellite to at least one spacecraft in the one or more LEO imaging satellite systems.Type: GrantFiled: August 25, 2016Date of Patent: March 12, 2019Assignee: Space Systems/Loral, LLCInventors: Jared Kauffman Gill, Saghir Munir
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Publication number: 20180062735Abstract: Cloud mask image data is obtained by a secondary imaging payload disposed on a communications or broadcast satellite operating in geosynchronous orbit. The obtained cloud mask image data is provisioned for use, in near real time, by one or more low earth orbit imaging satellite systems. Provisioning the obtained cloud mask image data may include collecting the data on the ground and making it available to one or more operators of the one or more LEO imaging satellite systems and/or transmitting the data from the communications or broadcast satellite to at least one spacecraft in the one or more LEO imaging satellite systems.Type: ApplicationFiled: August 25, 2016Publication date: March 1, 2018Inventors: Jared Kauffman Gill, Saghir Munir
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Patent number: 9663251Abstract: Techniques for performing orbit raising, north-south stationkeeping, east-west stationkeeping, and momentum management with thrusters disposed on a spacecraft are disclosed. The spacecraft includes at least one thruster support mechanism (TSM), including a pointing arrangement and an elongated structural member, the structural member having a long dimension defining a first axis a proximal portion of the structural member is attached to the pointing arrangement each of the thrusters is fixedly coupled with a distal portion of the structural member. The pointing arrangement includes a first, second, and third revolute joint, the first revolute joint being rotatable about the first axis; the third revolute joint being rotatable about a third axis, the third axis being fixed with respect to the spacecraft; and the second revolute joint being rotatable about a second axis, the second axis being orthogonal to each of the first axis and the third axis.Type: GrantFiled: December 22, 2014Date of Patent: May 30, 2017Assignee: Space Systems/Loral, LLCInventors: Mohammad Saghir Munir, Walter Gelon, Darren Stratemeier
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Patent number: 9557169Abstract: This invention allows tracking of a defect across multiple inspections. The inventive solution translates every inspection record into a common set of fields that are first archived into a relational database. Then the defect coordinates from the inspection records of the same mask are all transformed into a common reference frame having the same origin and orientation with respect to the mask coordinate system. Following this, the defect having coordinates within a given tolerance distance are paired up and reported to the user.Type: GrantFiled: March 13, 2013Date of Patent: January 31, 2017Assignee: RETICLE LABS LLCInventor: Mohammad Saghir Munir
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Publication number: 20160176545Abstract: Techniques for performing orbit raising north-south stationkeeping, east-west stationkeeping, and momentum management with thrusters disposed on a spacecraft. The spacecraft includes at least one thruster support mechanism (TSM), including a pointing arrangement and an elongated structural member, the structural member having a long dimension defining a first axis a proximal portion of the structural member is attached to the pointing arrangement each of the thrusters is fixedly coupled with a distal portion of the structural member. The pointing arrangement includes a first, second, and third revolute joint, the first revolute joint being rotatable about the first axis; the third revolute joint being rotatable about a third axis, the third axis being fixed with respect to the spacecraft; and the second revolute joint being rotatable about a second axis, the second axis being orthogonal to each of the first axis and the second axis.Type: ApplicationFiled: December 22, 2014Publication date: June 23, 2016Inventors: Mohammad Saghir Munir, Walter Gelon, Darren Stratemeier
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Patent number: 9108749Abstract: Three-axis spacecraft momentum management is performed for a spacecraft traveling along a trajectory, by an actuator including at least one thruster disposed on a single positioning mechanism. As the spacecraft travels along the trajectory, a desired line of thrust undergoes a substantial rotation in inertial space. When the spacecraft is located at a first location on the trajectory, the single positioning mechanism orients the thruster so as to produce a first torque to manage stored momentum in at least one of a first and a second of the three inertial spacecraft axes. When the spacecraft is located at a second location on the trajectory, the single positioning mechanism orients the thruster so as to produce a second torque to manage stored momentum in at least a third of the three inertial spacecraft axes.Type: GrantFiled: December 15, 2011Date of Patent: August 18, 2015Assignee: Space Systems/Loral, LLCInventors: Byoungsam Woo, Mohammad Saghir Munir, Kam K. Chan
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Patent number: 9108748Abstract: Apparatus and methods for raising the orbit of a satellite having electric propulsion thrusters, an Earth sensor and an inertial reference sensor such as a gyro. A satellite positioning system generates orbital data and a profile generator generates an ideal electric orbit raising profile of the satellite. The ideal profile is one that the satellite must follow so that the perigee, apogee and inclination of the satellite can be adjusted simultaneously in a mass-efficient manner. A state machine processes the ideal profile and a true anomaly to generate a desired electric orbit raising profile. Steering apparatus generates signals that are used to control the attitude of the satellite to follow the desired profile.Type: GrantFiled: October 20, 2010Date of Patent: August 18, 2015Assignee: Space Systems/Loral, LLCInventors: Saghir Munir, Darren Stratemeier, Xen Price, Yassir Azziz, Jorge Delgado, Justo Jacinto
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Patent number: 9045239Abstract: Spacecraft payload orientation steering is provided for an orbiting spacecraft in motion along an orbit track around a celestial body, the orbit track having a nominal inclination with respect to an equatorial orbit, a substantial eccentricity, and a drift angle with respect to the nominal inclination. Coordinates of an optimal payload target location as a function of a spacecraft position along the orbit track are determined, the target location being on the surface of the celestial body and having a substantial motion with respect to the surface and with respect to a spacecraft nadir. A payload of the spacecraft is substantially aligned with the determined coordinates by steering the satellite body to correct for at least one of the inclination drift angle, and the eccentricity, thereby adjusting the spacecraft orientation as a function of the spacecraft position along the orbit track.Type: GrantFiled: December 2, 2009Date of Patent: June 2, 2015Assignee: Space Systems/Loral, LLCInventors: Saghir Munir, Xen Price, Matthew Machlis
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Patent number: 8868263Abstract: Stored momentum on a spacecraft is managed by determining a target profile of stored momentum as a function of time for the spacecraft; measuring a difference between a momentum value actually stored on the spacecraft and a desired momentum value, where the desired momentum value substantially conforms to the target profile at a particular time; reducing the difference by producing a torque on the spacecraft, where the torque results from selectively controlling at least one solar array position offset angle, the offset angle being an offset of at least one solar array of the spacecraft from a nominal sun pointing direction.Type: GrantFiled: May 25, 2011Date of Patent: October 21, 2014Assignee: Space Systems/Loral, LLCInventors: Mohammad Saghir Munir, John Hutton Cooper, Philip Conway Hirschberg
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Publication number: 20140278209Abstract: This invention allows tracking of a defect across multiple inspections. The inventive solution translates every inspection record into a common set of fields that are first archived into a relational database. Then the defect coordinates from the inspection records of the same mask are all transformed into a common reference frame having the same origin and orientation with respect to the mask coordinate system. Following this, the defect having coordinates within a given tolerance distance are paired up and reported to the user.Type: ApplicationFiled: March 13, 2013Publication date: September 18, 2014Applicant: Reticle Labs LLCInventor: Mohammad Saghir Munir
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Publication number: 20120303185Abstract: Stored momentum on a spacecraft is managed by determining a target profile of stored momentum as a function of time for the spacecraft; measuring a difference between a momentum value actually stored on the spacecraft and a desired momentum value, where the desired momentum value substantially conforms to the target profile at a particular time; reducing the difference by producing a torque on the spacecraft, where the torque results from selectively controlling at least one solar array position offset angle, the offset angle being an offset of at least one solar array of the spacecraft from a nominal sun pointing direction.Type: ApplicationFiled: May 25, 2011Publication date: November 29, 2012Applicant: SPACE SYSTEMS/LORAL, INC.Inventors: Mohammad Saghir Munir, John Hutton Cooper, Philip Conway Hirschberg
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Publication number: 20120097797Abstract: Three-axis spacecraft momentum management is performed for a spacecraft traveling along a trajectory, by an actuator including at least one thruster disposed on a single positioning mechanism. As the spacecraft travels along the trajectory, a desired line of thrust undergoes a substantial rotation in inertial space. When the spacecraft is located at a first location on the trajectory, the single positioning mechanism orients the thruster so as to produce a first torque to manage stored momentum in at least one of a first and a second of the three inertial spacecraft axes. When the spacecraft is located at a second location on the trajectory, the single positioning mechanism orients the thruster so as to produce a second torque to manage stored momentum in at least a third of the three inertial spacecraft axes.Type: ApplicationFiled: December 15, 2011Publication date: April 26, 2012Applicant: SPACE SYSTEMS/LORAL, INC.Inventors: Byoungsam Woo, Mohammad Saghir Munir, Kam K. Chan
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Publication number: 20120097796Abstract: Apparatus and methods for raising the orbit of a satellite having electric propulsion thrusters, an Earth sensor and an inertial reference sensor such as a gyro. A satellite positioning system generates orbital data and a profile generator generates an ideal electric orbit raising profile of the satellite. The ideal profile is one that the satellite must follow so that the perigee, apogee and inclination of the satellite can be adjusted simultaneously in a mass-efficient manner. A state machine processes the ideal profile and a true anomaly to generate a desired electric orbit raising profile. Steering apparatus generates signals that are used to control the attitude of the satellite to follow the desired profile.Type: ApplicationFiled: October 20, 2010Publication date: April 26, 2012Inventors: Saghir Munir, Darren Stratemeier, Xen Price, Yassir Azziz, Jorge Delgado, Justo Jacinto
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Publication number: 20100179711Abstract: Spacecraft payload orientation steering is provided for an orbiting spacecraft in motion along an orbit track around a celestial body, the orbit track having a nominal inclination with respect to an equatorial orbit, a substantial eccentricity, and a drift angle with respect to the nominal inclination. Coordinates of an optimal payload target location as a function of a spacecraft position along the orbit track are determined, the target location being on the surface of the celestial body and having a substantial motion with respect to the surface and with respect to a spacecraft nadir. A payload of the spacecraft is substantially aligned with the determined coordinates by steering the satellite body to correct for at least one of the inclination drift angle, and the eccentricity, thereby adjusting the spacecraft orientation as a function of the spacecraft position along the orbit track.Type: ApplicationFiled: December 2, 2009Publication date: July 15, 2010Inventors: Saghir Munir, Xen Price, Matthew Machlis