State-dependent pseudo-linear filters for spacecraft attitude and rate estimation Academic Article uri icon

abstract

  • ABSTRACT This paper presents the development and performance of a special algorithm for estimating the attitude and angular rate of a spacecraft. The algorithm is a pseudolinear Kalman filter, which is an ordinary linear Kalman filter that operates on a linear model whose matrices are current state estimate dependent. The nonlinear rotational dynamics equation of the spacecraft is presented in the state space as a state-dependent linear system. Two types of measurements are considered; one type is a measurement of the quaternion of …

publication date

  • January 1, 2002