Piyush R Shah, 5919226 Burnt Bridge Dr, Leesburg, VA 20176

2012008, Apr 5, 2012

Aug 24, 2011

13/216838

Steven Thomas SMITH - Fairfax Station VA, US
Piyush S. SHAH - Houston TX, US
John D. MILLER - Katy TX, US
David PERRY - Alexandria VA, US

EXXONMOBIL RESEARCH AND ENGINEERING COMPANY - Annandale NJ

B01D 53/77
B01J 19/00

210759, 422168, 422170, 210758

Method for SOx remediation in a manufacturing operation includes providing a process stream including an organic compound and an amount of a sulfur-containing compound, an oxidation stream including at least one chemical oxidant, and combining at least a portion of the oxidant stream with at least a portion of the process stream to obtain an organic stripper feed stream, in which the amount of the sulfur-containing compound is reduced upon reaction with the at least one chemical oxidant. The method can further include directing at least a portion of the organic stripper feed stream to a combustion operation, and emitting a SOx remediated off gas from the combustion operation. A system using the disclosed method also is provided.

6003818, Dec 21, 1999

Mar 11, 1998

9/038022

Piyush R. Shah - Germantown MD
Douglas J. Bender - Redondo Beach CA
David S. Uetrecht - Palos Verdes CA

Hughes Electronics Corporation - Los Angeles CA

B64G 128

244165

A system and method for slewing a spacecraft with a reaction wheel system including determining initial total momentum, determining maximum forward and reverse rates that can be realized within the reaction wheel system maximum storage capacity, determining a slew rate and slew direction from the maximum forward and reverse rates so as to minimize slew time for known slew angles or maximize slew rate for arbitrary slew angles, and slewing the spacecraft.

6019320, Feb 1, 2000

Sep 15, 1998

9/153123

Piyush R. Shah - Germantown MD
Douglas J. Bender - Redondo Beach CA

Hughes Electronics Corporation - Los Angeles CA

B64G 124

244171

A system and method for acquiring Sun pointing in a three-axis stabilized spacecraft including slewing at least one solar wing until the Sun is detected, determining an initial Sun vector, performing one or more rotations of the spacecraft body so as to bring the instantaneous Sun vector coincident with a preferred final Sun vector, at least one rotation about an optimal axis, and slewing at least one solar wing to a preferred attitude relative to the Sun. In one embodiment, the optimal axis is chosen so as to minimize the time required to achieve an optimal thermal attitude. In another embodiment, the optimal axis is chosen so as to minimize the time required to align the instantaneous Sun vector with the final desired Sun vector. In a further embodiment, the optimal axis is chosen so as to maintain Earth lock.

6282467, Aug 28, 2001

Oct 14, 1997

8/949634

Piyush R. Shah - Germantown MD
Garry Didinsky - Los Angeles CA
David S. Uetrecht - Palos Verdes CA

The Boeing Company - Seattle WA

B64G 124

701 13

A system and method for determining the attitude in an inertial frame of a spacecraft spinning about an axis in a body frame including determining momentum vector direction in the inertial frame; determining momentum vector direction in the body frame; acquiring information from an at least single-axis sensor; obtaining reference information on the at least single-axis sensor; updating the attitude in the inertial reference frame using the momentum vector direction in the inertial frame, the momentum vector direction in the body frame, the output of the at least single-axis sensor, and the reference information on the at least single-axis sensor; and propagating the attitude using data from one or more inertial sensors.

6076774, Jun 20, 2000

Aug 12, 1998

9/132343

Piyush R. Shah - Germantown MD
Thomas M. Tanner - Aurora CO
Richard A. Noyola - Torrance CA

Hughes Electronics Corporation - El Segundo CA

B64G 124

244164

A system and method for acquiring the Earth by a three-axis stabilized spacecraft in the presence of a significantly time-varying Sun-Earth angle including obtaining an Earth cone described by rotating the nadir vector about the Sun vector, slewing the spacecraft about an axis until the Earth sensor boresight touches an edge of the Earth cone, updating the Earth cone due to the changing Sun-Earth separation angle, performing a spiral coning maneuver about the updated Earth cone until the Earth sensor detects the Earth, and locking onto the Earth so as to hold the Earth sensor boresight coincident with the nadir vector. Additionally, the spacecraft may be rotated about the nadir vector so as to bring the spacecraft into a desired final attitude.

2022036, Nov 17, 2022

Apr 11, 2022

17/717264

- Wright-Patterson AFB OH, US
Piyush J Shah - West Chester OH, US
Derek A Bas - Dayton OH, US

H01P 1/32
H03H 9/02
H03H 9/145
H03H 9/25

A nonreciprocal microwave transmission device includes a substrate, a transducer on a surface of the substrate and configured to reciprocally convert between electrical signals to acoustic waves, a first piezoelectric material configured to generates and transports acoustic waves from a signal applied to the transducer, and a thin film magnetic material configured to couple to acoustic waves through magnetoelastic coupling so as to have non-reciprocal magnetoelastic coupled acoustic wave transport. Transmission of acoustic waves through the thin film magnetic material is in a direction toward the transducer has a first magnitude and transmission of acoustic waves through the thin film magnetic material in a direction away from the transducer has a second magnitude, the first and second magnitude being significantly different.