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The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Patent No.:

US 4883244 B1

PDFFull Text
Date of Patent:
Nov. 28, 1989

Filed:

Dec. 23, 1987

Satellite attitude determination and control system with agile beam

Applicant:
Inventors:

A Dorian Challoner, Manhattan Beach, CA (US);

U A von der Embse, Westchester, CA (US);

Mark P Mitchell, Playa del Rey, CA (US);

Donald C Chang, Thousand Oaks, CA (US);

Richard A Fowell, Palos Verdes Estates, CA (US);

Ken Y Huang, Redondo Beach, CA (US);

Joseph H Hayden, Rancho Palos Verdes, CA (US);

Gene E Allen, Torrance, CA (US);

Assignee:

Hughes Aircraft Company, Los Angeles, CA (US);

Attorneys:

Mitchell; Steven M.

Denson-Low; Wanda

Primary Examiner:

Joseph F Peters, Jr

Assistant Examiner:

Rodney Corl

Int. Cl.
CPC ...
B64G / ; B64G / ;
U.S. Cl.
CPC ...
244171 ; 244166 ; 244164 ; 364459 ; 342354 ; 342355 ;
Abstract

Agile (electronically steerable) beam sensing with associated on-board processing, previously used exclusively for positioning of antennas for beam formation and tracking in communications systems, is now also used for satellite active attitude determination and control. A spinning satellite (100) is nadir oriented and precessed at orbit rate using magnetic torquing determined through use of an on-board stored magnetic field model (520) and attitude and orbit estimates (212). A Kalman filter (211) predicts parameters (202, 203) associated with a received signal (204) impinging on the satellite's wide angle beam antenna (201). The antenna system measures the error between the parameter predictions and observed values and sends appropriate error signals (207) to the Kalman filter for updating its estimation procedures. The Kalman filter additionally outputs the spacecraft attitude error signals (215) to an attitude control law (213), which determines commands to attitude-altering magnetic torque elements (220) to close the control loop via the spacecraft dynamics (230).

Find Patent Forward Citations

Challoner, A. (1989). Satellite attitude determination and control system with agile beam (U.S. Patent No. 4883244). U.S. Patent and Trademark Office. https://idiyas.com/patent/badge/4883244

Data source: USPTO (United States Patent and Trademark Office) public patent records. Weekly synchronization. How IDiyas builds this profile

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