Method of attitude determination using earth and star sensors

Patent 5412574 Issued on May 2, 1995. Estimated Expiration Date:

May 14, 2013. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.

Abstract Claims Description Full Text

Patent References

Method and apparatus for determining satellite attitude by using star sensor
Patent #: 4658361
Issued on: 04/14/1987
Inventor: Kosaka , et al.

Method and apparatus of determining an attitude of a satellite
Patent #: 4680718
Issued on: 07/14/1987
Inventor: Sasaki , et al.

Star sensor
Patent #: 4944587
Issued on: 07/31/1990
Inventor: Harigae

Active three-axis attitude control system for a geostationary satellite
Patent #: 5054719
Issued on: 10/08/1991
Inventor: Maute

Three-axis spacecraft attitude control using polar star sensor
Patent #: 5107434
Issued on: 04/21/1992
Inventor: Paluszek

Autonomous spacecraft navigation system
Patent #: 5109346
Issued on: 04/28/1992
Inventor: Wertz

Method for determining the position of a space vehicle by means of star acquisition and star identification
Patent #: 5177686
Issued on: 01/05/1993
Inventor: Boinghoff, et al.

Three axis earth/star sensor
Patent #: 5189295
Issued on: 02/23/1993
Inventor: Falbel

Attitude control system for three-axis stabilized satellite in near-equatorial orbit Patent #: 5259577
Issued on: 11/09/1993
Inventor: Achkar, et al.

Inventors

Application

No. 061095 filed on 05/14/1993

US Classes:

701/222, Using star tracker244/164, Attitude control701/226Space orbits or paths

Examiners

Primary: Teska, Kevin J.
Assistant: Yen, Tan Ngu

Attorney, Agent or Firm

Gudemstad; Terje, Denson-Low; Wanda K.

International Classes

G06F 015/50
B64G 001/24

Abstract

A method of attitude measurement for an artificial satellite (100) utilizes one or more star trackers (12) together with an earth sensor (30). Periodic updates of satellite orbital information, either propagated onboard or from a ground station are combined with earth and star position coordinate data to provide a continuous and accurate measurement of the spacecraft body 3-axis attitude. The method can be used for ground-based attitude determination or onboard closed loop control systems.

Other References

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