Attitude scheme for satellite with defective inertia characteristic

Abstract

Purpose

The purpose of this paper is to propose an attitude determination and control scheme for a low‐cost Micro‐satellite with defective inertia. Restricted by the payload design, the z‐axis inertia of this satellite is larger than the x and y axes, which is unstable for natural attitude dynamics.

Design/methodology/approach

An original operation mode is designed to avoid z axis from long‐time pointing to the sun during damping, which avoids some unexpected damage. In attitude determination design, EKF and UKF algorithms are compared on estimation accuracy, convergence time and computation complexity in attitude estimation design, which is referred to determine the final estimation scheme. A DSP‐based hardware solution is achieved and a semi‐physical testing and simulation system is built.

Findings

Simulation results show the 3‐axis stable mode can be built with the proposed scheme, and the unprotected facet of the satellite can be kept away from long‐time pointing to the sun.

Originality/value

The proposed ADCS scheme can be a reference for the future Micro‐satellite programs which share the similar configuration.

Citation

Jin, J., Baoyin, H. and Li, J. (2013), "Attitude scheme for satellite with defective inertia characteristic", Aircraft Engineering and Aerospace Technology, Vol. 85 No. 5, pp. 422-431. https://doi.org/10.1108/AEAT-05-2012-0067