Attitude determination system and method

Details Attitude determination system and method Attitude determination system and method

1998-09-22

2000-11-14

Eldred, J. Woodrow

Aeronautics and astronautics

Spacecraft

Attitude control

244171, B64G 124

Patent

active

061457906

ABSTRACT:
An attitude sensing system utilizing simplified techniques and apparatus includes a spacecraft control processor which receives signals from an inertial measurement unit and two attitude sensors. The spacecraft control processor calculates a time-varying gain matrix for estimating attitude errors and gyroscope drifts corresponding to the axes of the inertial measurement unit. In special cases where the separation angle between the attitude sensor vectors is less than approximately 10 degrees, the time-varying gain matrix is computed as a fixed gain matrix and a corresponding desensitizing factor.

REFERENCES:
patent: 5108050 (1992-04-01), Maute
patent: 5556058 (1996-09-01), Bender
patent: 5558305 (1996-09-01), Surauer et al.
patent: 5806804 (1998-09-01), Goodzeit et al.
patent: 5996941 (1999-12-01), Surauer et al.

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