Autonomous Astronomical Method of Spacecraft Tracking

T. V. Danilova, M. A. Arkhipova, M. A. Maslova

Transactions of IAA RAS, issue 52, 17–22 (2020)

DOI: 10.32876/ApplAstron.52.17-22

Keywords: autonomous navigation, recognition of stars, star sensors, optical electronic devices, onboard management systems, observation systems, space debris

Abstract

The paper describes the astronomical method of autonomous navigation and tracking of orbital objects of space control. The purpose of the study is to develop a method for the formation of high-precision navigation data of the objects observed, which include spacecraft of various classes, as well as fragments of space debris. The method should also be supplemented with the algorithms that ensure the prompt detection of facts of orbit changes of the object observed. The tracking method proposed is based on the sighting of the observed object in an optical-electronic device (star sensor) and the refinement of its orbit parameters based on the results of the measurements of the angles “observed object – star”. The identification of the maneuvers of the sighted object is based on the analysis of the dynamics of the orbit corrections sums and the sums of the absolute values of the measurement errors formed in the process of solving the navigation problem. Two versions of the pulse fact detection algorithm are presented. The factors affecting the accuracy of the method are analyzed. It was simulated and tested for spacecraft with orbits that varied over a wide range, including for the artificial satellites of the Moon. The simulation results demonstrate the high accuracy characteristics of the tracking method. With average values of the positioning errors of the sighting spacecraft $R' \in [1.5 m, 15.0 m]$, having random instrumental errors in measuring the coordinates of stars in an optical-electronic device $σ = 0.3ʺ$, the posterior estimates of the orbit of the observed object are as follows: average deviations by the position and velocity vectors $dR < 7.5 m$, $dV < 8 mm/s$, the maximum deviations – $dR_{max} < 11 m$, $dV_{max} < 11 mm/s$, at least for the classes of orbits presented in the paper. This method provides the identification of the maneuvers of the object observed, including at weak impulses – from 1 m/s to 3 m/s. The development results can be applied to onboard spacecraft control systems, including autonomous space monitoring systems.

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