Patents by Inventor Mason Peck
Mason Peck 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: 8020809Abstract: A control moment gyroscope system for delivering a target torque to a spacecraft including a rotor assembly having a rotor and a motor to spin the rotor about a rotor axis. A gimbal assembly has a gimbal for supporting the rotor assembly and a gimbal torque motor to rotate the gimbal about a gimbal axis, which is normal to the rotor axis, to generate an output torque. A control system has a sensor for determining the output torque and a processor in communication with the rotor assembly, the gimbal assembly and the sensor. The processor requests the target torque and establishes a feedback control loop to generate a torque error signal based on the output torque for bringing the output torque within a predetermined range of the target torque.Type: GrantFiled: April 18, 2008Date of Patent: September 20, 2011Assignee: Ithaco Space Systems, Inc.Inventors: Mason Peck, William E. Bialke
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Patent number: 7693619Abstract: A control system of a spacecraft for controlling two or more sets of collinear control moment gyroscopes (CMGs) comprises an attitude control system. The attitude control system is configured to receive a command to adjust an orientation of the spacecraft, determine an offset for a momentum disk for each of the two or more sets of CMGs that maximizes torque, determine a momentum needed from the two or more sets of CMGs to adjust the orientation of the spacecraft, and calculate a total torque needed by taking the derivative of the momentum. The control system further comprises a momentum actuator control processor coupled to the attitude control system, the momentum actuator control processor configured to calculate a required gimbal movement for each of the CMGs in each of the two or more sets of collinear CMGs from total torque.Type: GrantFiled: November 30, 2005Date of Patent: April 6, 2010Assignee: Honeywell International Inc.Inventors: Michael R. Elgersma, Daniel P. Johnson, Mason A. Peck, Brian K. Underhill, Gunter Stein, Blaise G. Morton, Brian J. Hamilton
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Patent number: 7561947Abstract: Methods and apparatus are provided for reorienting control moment gyros (CMGs) to compensate for CMG failure or change in spacecraft (S/C) mass properties or mission. An improved CMG comprises a drive means for rotating the CMG around an axis not parallel to the CMG gimbal axis. Releasable clamps lock the CMG to the spacecraft except during CMG array reorientation. CMGs arrays are combined with attitude sensors, a command module, memory for storing data and programs, CMG drivers and sensors (preferably for each CMG axis), and a controller coupling these elements. The method comprises determining whether a CMG has failed or the S/C properties or mission changed, identifying the working CMGs of the array, determining a new array reorientation for improved spacecraft control, unlocking, reorienting and relocking the CMGs in the array and updating the S/C control parameters for the new array orientation.Type: GrantFiled: October 6, 2003Date of Patent: July 14, 2009Assignee: Honeywell International Inc.Inventors: J. Jeff Bonn, Mason A. Peck
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Patent number: 7512466Abstract: Methods and apparatus are provided for reaction wheel (RW) assemblies for spacecraft. The apparatus comprises a M/G coupled to an inertia wheel and a controller coupled to the M/G that, in response to commands it receives, couples power to or from an M/G of another RW assembly over a shared transfer connection (VXFR), so that one M/G acts as a generator powering another M/G acting as a motor. The controller compares generator voltage VGEN to the BEMF of the motor on VXFR and reconfigures a multi-winding M/G or steps-up the generated voltage to maintain VGEN>VXFR to maximize direct energy transfer from one RW to the other as long as possible. When VGEN declines sufficiently, the controller can couple the motor to the spacecraft power bus and/or the generator to a power dump so as to continue to provide the commanded torque if needed. Operation is automatic.Type: GrantFiled: June 30, 2005Date of Patent: March 31, 2009Assignee: Honeywell International Inc.Inventors: Robert J. Hart, Mason A. Peck
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Publication number: 20090001220Abstract: A control moment gyroscope system for delivering a target torque to a spacecraft including a rotor assembly having a rotor and a motor to spin the rotor about a rotor axis. A gimbal assembly has a gimbal for supporting the rotor assembly and a gimbal torque motor to rotate the gimbal about a gimbal axis, which is normal to the rotor axis, to generate an output torque. A control system has a sensor for determining the output torque and a processor in communication with the rotor assembly, the gimbal assembly and the sensor. The processor requests the target torque and establishes a feedback control loop to generate a torque error signal based on the output torque for bringing the output torque within a predetermined range of the target torque.Type: ApplicationFiled: April 18, 2008Publication date: January 1, 2009Applicant: Ithaco Space System, Inc.Inventors: Mason Peck, William E. Bialke
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Patent number: 7464899Abstract: A method for avoiding singularities in the movement of CMGs in an array of CMGs in a spacecraft includes a first step where a maneuver command to rotate a spacecraft orientation is received. Then, the torque needed to rotate the spacecraft's orientation is determined. Then, the torque is integrated to determine a momentum path. The momentum path is decomposed into a sequence of straight line segments. For each line segment, a unit vector along the straight line segments is determined. Then, it is determined if there is a continuous path connecting a start point and an end point of the line segment in a plane perpendicular to the unit vector. For each point along the path in the plane perpendicular to the unit vector, a set of gimbal angles is determined.Type: GrantFiled: August 3, 2005Date of Patent: December 16, 2008Assignee: Honeywell International Inc.Inventors: Michael R. Elgersma, Daniel P. Johnson, Gunter Stein, Blaise G. Morton, Dennice F. Gayme, Mason A. Peck
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Patent number: 7367529Abstract: An spacecraft control system is provided that includes a tube and a plurality of microwheels. The plurality of microwheels is disposed within the tube. Each microwheel has a first stator wafer, a second stator wafer, and a rotor wafer disposed therebetween. The first and second stator wafers are configured to spin the rotor wafer.Type: GrantFiled: October 22, 2004Date of Patent: May 6, 2008Assignee: Honeywell International, Inc.Inventors: Jack H. Jacobs, Mason A. Peck
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Patent number: 7364120Abstract: A momentum actuator for steering a spacecraft is disclosed. The momentum actuator comprises a rotor, a gimbal upon which the rotor is mounted, and a stepper motor coupled to the gimbal and operable to rotate the rotor about the gimbal in a series of steps. In one embodiment of the present invention the spin rate of the rotor can be varied to provide torque.Type: GrantFiled: August 26, 2004Date of Patent: April 29, 2008Assignee: Honeywell International, Inc.Inventor: Mason A. Peck
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Publication number: 20070235273Abstract: A mass damper is provided for damping a mass. The mass damper includes a housing configured to couple to the mass and a plurality of electrostatically charged particles disposed within the housing, where the particles do not clump to one another or stick to the housing.Type: ApplicationFiled: June 14, 2007Publication date: October 11, 2007Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: Steve Hadden, Thomas Kreider, Mason Peck
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Patent number: 7246776Abstract: The present method provides a method for avoiding singularities in the movement of CMGs in an array of CMGs in a spacecraft. In a first step, a torque command representing a desired torque to produce an attitude adjustment for the spacecraft is received. Next, a range-space gimbal rate required to produce the desired torque based on the desired torque and a Jacobian matrix is calculated. Then, a null-space gimbal rate that assists in the avoidance of singularities is calculated. The total gimbal rate command is determined by summing the range-space gimbal rate and the null-space gimbal rate. Then, the total gimbal rate command is provided to the CMGs to produce the total gimbal rate.Type: GrantFiled: July 23, 2004Date of Patent: July 24, 2007Assignee: Honeywell International, Inc.Inventors: Mason A. Peck, Brian J. Hamilton, Brian Underhill
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Publication number: 20070124032Abstract: A control system of a spacecraft for controlling two or more sets of collinear control moment gyroscopes (CMGs) comprises an attitude control system. The attitude control system is configured to receive a command to adjust an orientation of the spacecraft, determine an offset for a momentum disk for each of the two or more sets of CMGs that maximizes torque, determine a momentum needed from the two or more sets of CMGs to adjust the orientation of the spacecraft, and calculate a total torque needed by taking the derivative of the momentum. The control system further comprises a momentum actuator control processor coupled to the attitude control system, the momentum actuator control processor configured to calculate a required gimbal movement for each of the CMGs in each of the two or more sets of collinear CMGs from total torque.Type: ApplicationFiled: November 30, 2005Publication date: May 31, 2007Inventors: Michael Elgersma, Daniel Johnson, Mason Peck, Brian Underhill, Gunter Stein, Blaise Morton, Brian Hamilton
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Patent number: 7185855Abstract: A momentum-control system comprising a plurality of momentum actuators and a platform upon which the plurality of momentum actuators are mounted. The momentum control system further comprises a plurality of active struts mounted on the bottom side of the platform. The active struts are configured to produce a force to steer the plurality of momentum actuators and the platform to produce forces and moments for spacecraft attitude control and disturbance suppression.Type: GrantFiled: April 30, 2004Date of Patent: March 6, 2007Assignee: Honeywell International, Inc.Inventor: Mason A. Peck
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Publication number: 20070029447Abstract: A method for avoiding singularities in the movement of CMGs in an array of CMGs in a spacecraft includes a first step where a maneuver command to rotate a spacecraft orientation is received. Then, the torque needed to rotate the spacecraft's orientation is determined. Then, the torque is integrated to determine a momentum path. The momentum path is decomposed into a sequence of straight line segments. For each line segment, a unit vector along the straight line segments is determined. Then, it is determined if there is a continuous path connecting a start point and an end point of the line segment in a plane perpendicular to the unit vector. For each point along the path in the plane perpendicular to the unit vector, a set of gimbal angles is determined.Type: ApplicationFiled: August 3, 2005Publication date: February 8, 2007Inventors: Michael R. Elgersma, Daniel P. Johnson, Gunter Stein, Blaise G. Morton, Dennice F. Gayme, Mason A. Peck
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Publication number: 20070023580Abstract: Methods and apparatus are provided for reaction wheel (RW) assemblies for spacecraft. The apparatus comprises a M/G coupled to an inertia wheel and a controller coupled to the M/G that, in response to commands it receives, couples power to or from an M/G of another RW assembly over a shared transfer connection (VXFR), so that one M/G acts as a generator powering another M/G acting as a motor. The controller compares generator voltage VGEN to the BEMF of the motor on VXFR and reconfigures a multi-winding M/G or steps-up the generated voltage to maintain VGEN>VXFR to maximize direct energy transfer from one RW to the other as long as possible. When VGEN declines sufficiently, the controller can couple the motor to the spacecraft power bus and/or the generator to a power dump so as to continue to provide the commanded torque if needed. Operation is automatic.Type: ApplicationFiled: June 30, 2005Publication date: February 1, 2007Inventors: Robert Hart, Mason Peck
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Patent number: 7152495Abstract: A disturbance-cancellation system and method is provided that facilitates the adaptive cancellation of periodic disturbances. The disturbance-cancellation system and method includes a pair of control moment gyroscopes (CMGs) arranged together as a scissored pair. The scissored pair of CMGs is used to create a periodic torque with a controllable amplitude and frequency. The periodic torque created by the CMGs is adaptively controlled to cancel out periodic disturbances in the system. The system and method creates a periodic torque with a controllable amplitude and frequency by rotating the inner-gimbal assemblies of the CMGs in opposite directions at substantially equal phase and angular velocity. Amplitude matching can be achieved by adjusting the rotor spin rate. The steady-state constant motion results in a periodic torque along the output axis of the scissored pair, while components of torque along axes orthogonal to this one cancel out.Type: GrantFiled: December 19, 2002Date of Patent: December 26, 2006Assignee: Honeywell International, Inc.Inventor: Mason A. Peck
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Patent number: 7090171Abstract: A spacecraft system including a spacecraft assembly or “stack” having an upper stage of a rocket-powered launch vehicle providing a final boost phase during launch. The stack also includes a payload structure rotatably interconnected with the upper stage. The upper stage and the payload structure together define a central axis that is generally coincident with the thrust axis during launch. The stack has an axis of maximum moment of inertia that is not parallel to the central axis. The stack has internal damping such that unstable nutation occurs if the upper stage and the payload structure rotate together about the central axis at the same rotational rate and in the same direction. The system includes a controller that rotates the payload structure relative to the upper stage during the final boost phase to alleviate coning motion of the stack.Type: GrantFiled: April 30, 2003Date of Patent: August 15, 2006Assignee: Honeywell International, Inc.Inventor: Mason A. Peck
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Publication number: 20060145023Abstract: A system is provided for docking two vehicles. In one exemplary embodiment, the system includes a first and a second vehicle. The first vehicle has a port thereon. The port has a first magnetic mechanism coupled thereto, and the first magnetic mechanism is configured to provide a first magnetic polarity. The second vehicle is in communication with the first vehicle and has an interface thereon. The interface has a second magnetic mechanism coupled thereto and is configured to selectively provide a first and a second magnetic polarity. The first and second magnetic mechanisms are magnetically attracted to one another when the second magnetic polarity is selected and repel one another when the first magnetic polarity is selected.Type: ApplicationFiled: December 20, 2004Publication date: July 6, 2006Inventors: William Babb, Jack Jacobs, Mason Peck
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Publication number: 20060086865Abstract: An spacecraft control system is provided that includes a tube and a plurality of microwheels. The plurality of microwheels is disposed within the tube. Each microwheel has a first stator wafer, a second stator wafer, and a rotor wafer disposed therebetween. The first and second stator wafers are configured to spin the rotor wafer.Type: ApplicationFiled: October 22, 2004Publication date: April 27, 2006Inventors: Jack Jacobs, Mason Peck
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Patent number: 7014150Abstract: A momentum-control system for a spacecraft is disclosed. The momentum-control system comprises an attitude-control system. The attitude-control system receives data concerning a desired spacecraft maneuver and determines a torque command to complete the desired spacecraft maneuver. A momentum actuator control processor coupled to the attitude-control system receives the torque command. The momentum actuator control processor calculates a gimbal rate command comprising a range-space gimbal rate required to produce the torque command and a null-space gimbal rate required to maximize the ability to provide torque in the direction of a current torque. At least four control-moment gyros are coupled to the momentum control actuator control processor. Each of the control-moment gyros receives and executes the gimbal rate to produce the desired maneuver.Type: GrantFiled: July 30, 2004Date of Patent: March 21, 2006Assignee: Honeywell International Inc.Inventors: Mason A. Peck, Brian J. Hamilton, Brian Underhill
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Publication number: 20060054433Abstract: A mass damper is provided for damping a mass. The mass damper includes a housing configured to couple to the mass and a plurality of electrostatically charged particles disposed within the housing, where the particles do not clump to one another or stick to the housing.Type: ApplicationFiled: September 15, 2004Publication date: March 16, 2006Inventors: Steve Hadden, Thomas Kreider, Mason Peck