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Alfred H Tadros

from Los Altos, CA
Age ~58
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Also known as:
Afred H Tadros, Alfred Heikel Tawadrous
Phone and address:
373 Marich Way, Los Altos, CA 94022
(650) 947-4841
Related to:
Zach J Scott, 37Karim H Tadros, 57Florence S Morrell, 74Roula Elasmar, 63Ronia E Tadros, 59Carol L Tadros, 57Alexandra A Tadros, 26Helen H Tadros
Connected to:
Christina Tadros, 34Denise Tadros, 61Edmund P Tadros, 41Eman E Tadros, 32Hanan G Tadros, 40Lorees B Tadros, 78Mazen J Tadros, 64Mazin D Tadros, 58Mina M Tadros, 82Rebecca Tadros, 122

Alfred Tadros Phones & Addresses

  • 373 Marich Way, Los Altos, CA 94022 (650) 947-4841
  • San Jose, CA
  • 14183 Northwoods Blvd, Truckee, CA 96161
  • Fenton, MO
  • 1755 Ednamary Way, Mountain View, CA 94040
  • Cambridge, MA
  • Novato, CA
  • Santa Clara, CA
  • Berkeley, CA

Publications

Us Patents

Satellite Gravity Gradient Compensation Using On-Orbit Solar Array Reorientation

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US Patent:
56695861, Sep 23, 1997
Filed:
Dec 6, 1994
Appl. No.:
8/349950
Inventors:
Alfred H. Tadros - Palo Alto CA
Assignee:
Space Systems/Loral, Inc. - Palo Alto CA
International Classification:
B64G 134
US Classification:
244167
Abstract:
A method for operating an orbiting spacecraft includes the steps of (a) changing a mass distribution of the spacecraft from a first mass distribution for setting a first principal moment of inertia of the spacecraft along a first axis approximately equal to a second principal moment of inertia of the spacecraft along a second axis, thereby minimizing a gravity gradient torque about a third axis; (b) performing a desired activity while the gravity gradient torque about the third axis is minimized; and (c) resetting the mass distribution back to the first mass distribution at a completion of the desired activity. The spacecraft includes a plurality of solar array panels, and the step of changing is accomplished by varying a position of at least two of the solar array panels away from a sun-pointing configuration. Also disclosed is a method for stabilizing the spacecraft to resist a rotation about an axis by varying the positions of solar array panels.

Spacecraft Antenna Pointing Error Correction

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US Patent:
55877141, Dec 24, 1996
Filed:
Mar 10, 1995
Appl. No.:
8/401863
Inventors:
Peter Y. Chu - Palo Alto CA
Alfred H. Tadros - San Jose CA
Assignee:
Space Systems/Loral, Inc. - Palo Alto CA
International Classification:
H04B 7185
US Classification:
342354
Abstract:
A system and method employ a sensing of the attitude or orientation of a spacecraft for correcting the orientation of a line of sight of an instrument carried by a spacecraft to compensate for a transient perturbation in the attitude of the spacecraft. The instrument may be a microwave antenna for communicating with a station on the earth, or a camera for viewing the earth. The transient perturbation in the orientation, such as may be caused by the firing of a thruster of the spacecraft, is extracted from a measurement of the spacecraft orientation, such as the orientation relative to the earth. The line of sight of the instrument is reoriented by injection of an incremental orientation equal and opposite to the transient perturbation. The application of the incremental orientation can be accomplished in mechanical fashion, in the case of an antenna mechanically mounted to the spacecraft, and electrically, as in the case of a phased array antenna carried by the spacecraft.

Differential Phase Measurement Scheme For A Multiplexing Gps Attitude Receiver

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US Patent:
59298057, Jul 27, 1999
Filed:
Apr 10, 1997
Appl. No.:
8/835684
Inventors:
Alfred Tadros - San Jose CA
Hai Ping Jin - Sunnyvale CA
David Mleczko - San Jose CA
International Classification:
H04B 7185
G01S 502
US Classification:
342357
Abstract:
A method for reducing master antenna tracking errors in a multiplexing GPS receiver resulting in a differential phase measurement scheme which is insensitive to the master antenna tracking loop errors is disclosed. The master antenna tracking loop error at a given update K is subtracted from a phase measurement associated with a slave antenna signal at update K. The method comprises the determination of interpolation coefficients by which the master antenna tracking loop errors are weighted in order to minimize each of the slave antenna differential measurements.

Self-Assembling Persistent Space Platform

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US Patent:
20200247563, Aug 6, 2020
Filed:
Apr 22, 2020
Appl. No.:
16/855356
Inventors:
- Palo Alto CA, US
Robert Edward Helmer - Pleasanton CA, US
Paul Anthony Briggs - San Francisco CA, US
John Douglas Lymer - Mountain View CA, US
Alfred Heikal Tadros - Los Altos CA, US
Andrew E. Turner - Mountain View CA, US
International Classification:
B64G 1/10
B64G 4/00
B64G 1/64
B64G 1/22
B64G 1/00
Abstract:
A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.

Cross-Feeding Propellant Between Stacked Spacecraft

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US Patent:
20180354659, Dec 13, 2018
Filed:
Jun 7, 2017
Appl. No.:
15/616803
Inventors:
- Palo Alto CA, US
Jonathan Noland - San Jose CA, US
Alfred Heikal Tadros - Los Altos CA, US
Jeffrey Donald Stoen - Palo Alto CA, US
Adam Maher - Palo Alto CA, US
International Classification:
B64G 1/40
B64G 1/00
B64G 1/64
B64G 1/24
B64G 1/26
Abstract:
A first spacecraft and a second spacecraft are configured to be disposed together, in a launch configuration, for launch by a single launch vehicle. In the launch configuration, the first spacecraft is mechanically coupled with a primary payload adapter of the launch vehicle, and the second spacecraft is mechanically coupled with the first spacecraft by way of an inter-spacecraft coupling arrangement. The spacecraft are configured to be deployed, following injection into a first orbit by the launch vehicle, by separating the first spacecraft from the primary payload adapter while the second spacecraft is mechanically coupled with the first spacecraft. A first onboard propulsion subsystem of the first spacecraft includes one or more thrusters configured to execute an orbit transfer maneuver from the first orbit to a second orbit. A propellant line arrangement detachably couples the first onboard propulsion subsystem with a second propellant storage arrangement on the second spacecraft.

Self-Assembling Persistent Space Platform

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US Patent:
20180093786, Apr 5, 2018
Filed:
Aug 29, 2017
Appl. No.:
15/689993
Inventors:
- Palo Alto CA, US
Robert Edward Helmer - Pleasanton CA, US
Paul Anthony Briggs - San Francisco CA, US
John Douglas Lymer - Mountain View CA, US
Alfred Heikal Tadros - Los Altos CA, US
Andrew E. Turner - Mountain View CA, US
International Classification:
B64G 1/10
B64G 1/64
B64G 4/00
Abstract:
A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.
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Alfred H Tadros from Los Altos, CA, age ~58 Get Report