Goodrich Corporation

Ast & Science, LLC

Ithaco Space Systems, Inc.

William Edward Bialke

Abel Avellan

Huiwen Yao

Adam H Halperin

Eric Hansell

Darren J Zanon

Daniele Addari

Darko Filipi

Mason A Peck

Eric Stromswold

A spacecraft has a flat antenna array having an edge and a middle portion. A reconfigurable reaction-momentum wheel is coupled to the antenna array to roll and/or pitch the antenna array in small magnitudes. The reconfigurable reaction-momentum has a reaction operating state or mode (high-torque, low momentum) and a momentum operating state or mode (low-torque, high momentum). A thruster is coupled to the antenna array to move the antenna array.

Momentum wheels and reaction wheels for objects in space

A method of electro-dynamically matching a bearing assembly includes electrically separating inner and outer races from rolling elements of the bearing assembly with lubricant and rotating the inner race relative to the outer race. A voltage differential is applied across the inner and the outer races and via isolated rolling elements and the race eroded an electrical discharge event across a gap defined between the one or more of the races and rolling elements. Electro-dynamically matched bearing assemblies and reaction/momentum flywheel arrangements for artificial satellites are also described.

Bearing assemblies with electrodynamically matched races

A method of electrodynamically finishing a plain bearing includes electrically separating a bearing housing from a journal shaft with a lubricant disposed on a bearing surface of the bearing housing. The bearing housing or the bearing housing is rotated relative to the other and a voltage differential applied across the bearing housing and the journal shaft. One or more asperities disposed on the bearing surface are eroded with electric discharge events between the journal shaft and the bearing housing. Electrodynamically finished bearing assemblies and reaction/momentum wheel arrangements having such bearing assemblies are also described.

Electrodynamically finished plain bearings

An attitude control system for a spacecraft is disclosed that includes a scissored pair of control moment gyroscopes for delivering an output torque to the spacecraft along a an output axis, wherein each gyroscope has a spin motor for spinning a rotor about a rotor axis and a gimbal torque motor for rotating the rotor about a gimbal axis, and wherein the system includes a generator for extracting kinetic energy from the rotors during rotor deceleration to power the gimbal torque motors of the gyroscopes.

Control moment gyroscope array and method of power distribution therefor

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.

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Trumansburg, NY, United States of America

William Edward Bialke