UD Factorization Based Non-Traditional Attitude Estimation of Nanosatellite with Rate Gyros FDI

Smart Nanosatellite Attitude Propagator

A GPS Based Attitude Determination System for a UAV Aided by Low Grade Angular Rate Gyros

The Satellite Navigation and Positioning (SNAP) group at The University of New South Wales has been conducting research into high precision attitude determination using a multi-antenna single-frequency GPS array, aided by low grade angular rate gyros. The objective of the research is to develop an accurate, reliable attitude sensor solution at an affordable cost which can be implemented on UAVs...

Non-stationary Noise Estimation Based on Non-negative Matrix Factorization

In this paper, we apply a non-negative matrix factorization (NMF) technique to propose a method of estimating noise occurring in non-stationary environments. In the proposed method, the basis matrix of the target noise is first obtained via NMF training. The noise basis is then applied to estimate an activation matrix of the target noise from the noisy signal. The proposed method is finally app...

Satellite Attitude Determination with Attitude Sensors and Gyros using Steady-state Kalman Filter

Attitude determination, along with attitude control, is critical to functioning of every space mission. Here, we investigate the application of a steady-state Kalman Filter for attitude determination using attitude sensors (sun sensor and horizon sensors) and rate integrating gyros. The three-axis steady-state Kalman Filter formulation, adopted from literature, offers obvious computational adva...

A Novel Adaptive Unscented Kalman Filter Attitude Estimation and Control System for a 3U Nanosatellite

A novel adaptive unscented Kalman filter (AUKF) based estimation algorithm is proposed for a 3U Cubsat. This small satellite employs a three axis magnetometer and three MEMS gyroscopes as well as three magnetic torque rods and one reaction wheel on the pitch axis. Unlike the existing UKF, in this paper, an n+1 sigma set is used to estimate the nanosatellite attitude instead of 2n + 1 sigma poin...