Nonlinear Kalman Filtering for Improved Angles-Only Navigation Using Relative Orbital Elements

Abstract

This paper addresses the design and validation of an accurate estimation architecture for autonomous angles-only navigation in orbits of arbitrary eccentricity. The proposed filtering strategy overcomes the major deficiencies of existing approaches in the literature, which mainly focus on applications in near-circular orbits and generally suffer from poor dynamical observability due to linearizing the filter dynamics and measurement models. Consequently, traditional angles-only navigation solutions require conducting known orbital maneuvers to reconcile the ambiguous range. In contrast, the algorithms developed in this work enable accurate maneuver-free reconstruction of the relative orbital motion. This is done through the full exploitation of nonlinearities in the measurement model using the unscented Kalman filter to improve dynamical observability and filter performance. The filter estimates mean relative orbit elements, adopting a state transition matrix subject to secular and long-period J 2 perturbation effects to decouple observable from unobservable parameters. The complete state is then reconciled with the angle measurements in the measurement model through a nonlinear transformation that includes the conversion from mean to osculating orbital elements. The resulting linear dynamics model is supplemented by either first-order Gauss-Markov processes (that is, differential empirical accelerations) or by a covariance-matching approach to online adaptive process noise tuning to increase performance at minimal computational complexity. Finally, the estimation architecture is completed by a novel deterministic algorithm for batch initial relative orbit determination to accurately initialize the sequential filter.

Formation Design of Distributed Telescopes in Earth Orbit for Astrophysics Applications

“…Studies on design [6][7][8][9][10], guidance [11][12][13], navigation [14][15][16][17], and control [18][19][20][21][22] of spacecraft formations are widely available in the literature. More comprehensive reviews of these studies can be found in recent survey papers [23][24][25][26].…”

“…tel (17) Next, suppose that the pointing vector takes on the values described in Eq. (16) at time t 0 .…”

Flight Demonstration of Autonomous Noncooperative Rendezvous in Low Earth Orbit

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Linear Cotangential Transfers and Safe Orbits for Elliptic Orbit Rendezvous

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