William E Bialke

8020809, Sep 20, 2011

Apr 18, 2008

12/148467

Mason Peck - Ithaca NY, US
William E. Bialke - Trumansburg NY, US

Ithaco Space Systems, Inc. - Ithaca NY

B64G 1/28

244165, 74 547

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.

8210062, Jul 3, 2012

Apr 18, 2007

11/787967

William Edward Bialke - Trumansburg NY, US
Eric Stromswold - Spencer NY, US

Ithaco Space Systems, Inc. - Ithaca NY

G01C 19/30
G01C 19/10

74 547, 74 522

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.

20080099626, May 1, 2008

Oct 27, 2006

11/588801

William E. Bialke - Trumansburg NY, US

B64G 1/28

244165

The invention provides a reconfigurable reaction wheel for a spacecraft, a spacecraft, and a method of using the reconfigurable reaction wheel to control the movement of a spacecraft. The reaction wheel includes a reaction wheel housing, a flywheel rotatably disposed in the housing and an electric motor operably coupled to the flywheel. The electric motor includes a plurality of electrical windings. The motor is adapted and configured to operate in a first selectable operating state wherein the windings are arranged in a first electrical configuration, and a second selectable operating state wherein the windings are arranged in a second electrical configuration different from the first electrical configuration.

56200609, Apr 15, 1997

Feb 6, 1996

8/597614

William E. Bialke - Ithaca NY

Ithaco, Inc. - Ithaca NY

F01M 500

1841041

The present invention is a system for replenishing an article of equipment with a supply of lubricant. A housing is provided which defines a reservoir. The housing includes an open end connected to the equipment article such that the reservoir and the equipment article are in fluid communication. Lubricant is disposed in the reservoir and a check valve is secured at the open end of the housing to allow one-way flow of lubricant from the reservoir to the housing. Heating the lubricant to a predetermined temperature results in a precisely ascertainable mass of lubricant being forced from the reservoir to the equipment article.

20220297857, Sep 22, 2022

Mar 16, 2022

17/696506

- Miami FL, US
Abel Avellan - Coral Gables FL, US
William E. Bialke - Trumansburg NY, US
Daniele Addari - London, GB
Darren J. Zanon - Falls Church VA, US
Adam H. Halperin - Silver Spring MD, US
Huiwen Yao - Potomac MD, US

B64G 1/28
B64G 1/24

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.