Publication Date:
2019-07-13
Description:
Deterministic errors in angular rate gyros, such as thermal biases, can have a significant impact on spacecraft attitude knowledge. In particular, thermal biases are often the dominant error source in MEMS gyros after calibration. Filters, such as J\,fEKFs, are commonly used to mitigate the impact of gyro errors and gyro noise on spacecraft closed loop pointing accuracy, but often have difficulty in rapidly changing thermal environments and can be computationally expensive. In this report an existing nonlinear adaptive filter is used as the basis for a new nonlinear adaptive filter designed to estimate and cancel thermal bias effects. A description of the filter is presented along with an implementation suitable for discrete-time applications. A simulation analysis demonstrates the performance of the filter in the presence of noisy measurements and provides a comparison with existing techniques.
Keywords:
Spacecraft Design, Testing and Performance
Type:
GSFC.CP.5989.2012
,
GSFC.CP.6788.2012
,
AIAA Guidance, Navigation, and Control Conference; Aug 13, 2012 - Aug 16, 2012; Minneapolis, MN; United States
Format:
application/pdf
