Unscented Kalman Filtering: NPSAT1 Ground Test Results
Ross, Michael I.
MetadataShow full item record
NPSAT1 is a small satellite that employs magnetic sensing and actuation for attitude control. The spacecraft orientation and angular velocity should, therefore, be estimated from the magnetometer readings. The inherent nonlinear dynamics of the system poses a challenging problem on the observer design. This paper demonstrates the ground test results of NPSAT1 state estimation using the Unscented Kalman Filter (UKF) - a fairly recent method with inherent appeals of extended Kalman 'Filter but with no need for linearization; thus more suitable for highly nonlinear 'filtering and control applications. The quaternion-based modeling constraint that the quaternion has a unit norm is enforced by treating the norm of the quaternion as a dummy measurement. The experimental results show the superior performance of the UKF in practice.
The article of record as published may be located at http://dx.doi.org/10.2514/6.2006-6352Approved for public display, distribution unlimitedProceedings of AIAA-Guidance, Navigation, and Control Conference and Exhibit ; Paper no. AIAA-2006-6352, Keystone, Colorado, Aug. 21-24, 2006
Showing items related by title, author, creator and subject.
Sekhavat, Pooya; Ross, I. Michael; Gong, Qi (IEEE, 2007-07-11);NPSAT1 is a small satellite being built at the Naval Postgraduate School and scheduled to launch in 2007. It primarily employs magnetic sensing and actuation for attitude control. The nature of the in-house fabrication and ...
Hall, Jason S. (Monterey, California: Naval Postgraduate School, 2009-09);A laboratory spacecraft simulator testbed is first introduced to examine the problem of multiple spacecraft interacting in close proximity. This testbed enables validation of guidance, navigation and control (GNC) algorithms ...
Development of a hardware-in-the-loop simulator for control moment gyroscope-based attitude control systems Fields, Brian C. (Monterey, California: Naval Postgraduate School, 2015-12);In this thesis, an open-architecture control moment gyroscope (CMG) system is developed for hardware-in-the-loop (HIL) simulation of spacecraft attitude control. This effort included construction of four single-gimbal CMGs, ...