The Boeing Company

Robert Boschgmbh

John Y Liu

Mark Andrew Lundgren

Ketao Liu

Gregory S Becker

Richard W Guthrie

Douglas Bender

Peter J Sedivec

Kirk K Kohnen

Yiu-Hung Monte Ho

Ray E McVey

Michael A McVeigh

John Gatza

Carlos Atoche-Juarez

Michael Lindemann

Robert J Mayer

A system and methods for calculating an attitude and a position of an object in space are disclosed. Measurements in relation to an object, stars, and a signal timing are received at a combined orbit and attitude determination system to provide received measurements. An estimated separation angle error, an estimated position error, and an estimated attitude error are estimated based upon the received measurements to provide estimated errors.

Combined orbit and attitude determination system and methods

Provided herein is a Coriolis vibratory gyroscope ('CVG'). The CVG includes a first plurality of actuators electrically coupled to the vibratory member and arranged about a drive axis of the CVG and operable to obtain a control signal from the controller and provide a voltage sufficient to cause and maintain the vibratory member to vibrate in a first mode of oscillation; a second plurality of actuators electrically coupled to the vibratory member and arranged about a sense axis of the CVG and operable to detect a voltage based on a second mode of oscillation of the vibratory member caused by a rotation of the CVG about an axis of rotation and to provide a counter-balancing signal sufficient to null the voltage based on the second mode of oscillation, wherein the controller is operable to determine a rate of the rotation of the CVG based, in part, on the counter-balancing signal.

Approach for control redistribution of coriolis vibratory gyroscope (CVG) for performance improvement

Provided herein is a method for determining a bias-compensated inertial rotation rate of a Coriolis vibratory gyroscope ('CVG'). The method comprises determining an initial mode that the CVG is operating; obtaining average uncompensated inertial rotation rate measurements from a previous mode transition period; obtaining average uncompensated bias measurements from the previous mode transition period; determining a first transition between a AGC mode and a FTR mode of a given axis; calculating a first estimate of bias of the CVG based on the first transition that was determined and the average uncompensated bias measurements from the previous mode transition period; and calculating, by a processor, a first bias-compensated inertial rotation rate of the CVG based on the first bias that was calculated and the average uncompensated inertial rotation rate measurements from a previous mode transition period.

High bandwidth Coriolis vibratory gyroscope (CVG) with in-situ bias self-calibration

Combined location and attitude determination system and methods

A method and apparatus for maneuvering a satellite in orbit to alternately optimize the collection of solar energy and to take sensor data of terrestrial objects is disclosed The longitudinal axis of a large payload package is oriented perpendicular to the orbital plane to minimize the disturbance torque due to gravity gradient, and to allow simple rotation about the axis for attitude change between optimal Sun and optimal ground coverage.

Optimal sun safe attitude for satellite ground tracking

Systems and techniques for laser metrology. Two or more fanned probe beams are scanned relative to a surface including one or more targets. A position detection module receives return beam information from the fanned probe beams, and determines a position of at least a first target of the one or more targets based on the return beam information.

Multiple fanned laser beam metrology system

Systems and techniques for laser metrology. A system may include a laser source and a fanning apparatus configured to generate a fanned laser beam. The fanned laser beam may be scanned across the surface of an object, and may reflect off a plurality of targets positioned on the surface. A position detection module may determine a position of the metrology targets based on the reflected beam.

Fanned laser beam metrology system

Method and device for controlling the braking action of at least one wheel brake of a four-wheel-drive motor vehicle having at least one rear axle and one front axle. A first rpm signal representing the speeds of rotation of the front-axle wheels and a second rpm signal representing the speeds of rotation of the rear-axle wheels are detected. The difference between the first and second rpm signals is then determined, and braking action is controlled as a function of the difference that has been determined.

Method and device for controlling a braking action of at least one wheel brake of a four-wheel-drive motor vehicle

A tiltrotor aircraft includes a spanwise-flow redirector having a pair of flow-redirection panels respectively mounted on the aircraft's mid-fuselage area for rotation about a panel pivot axis between a stowed position and a deployed position. In the stowed position, each panel is substantially flush with an adjacent surface of the mid-fuselage area. In the deployed position, each panel is raised into the path of one of the inbound spanwise flows generated by the aircraft's rotors during hover operation, whereupon each panel redirects the respective one of the inbound spanwise flows either forward or aft of the other inbound spanwise flow. In this manner, the deployed panels prevent stagnation of the inbound spanwise flow atop the mid-fuselage area while further serving to minimize re-ingestion of merged spanwise flow into the rotors, resulting in decreased airframe download forces, increased rotor thrust, and reduced noise levels during hover operation.

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San Marino, CA, United States of America

John Y Liu