Autonomous Navigation during the Final Ascent of a Spacecraft into the Geostationary Orbit. Autonomous Integrated Navigation System Concept

摘要

This paper is the first in a series of works devoted to the problems of a spacecraft in the geostationary orbit autonomous operation. The paper presents the conceptual design of the spacecraft onboard autonomous navigation system applying to its final ascent to the geostationary orbit using the low-thrust electric propulsion system. This design is based on both stochastic and minimax uncontrollable factors interpretation. The composition of needed hardware and the architecture of the spacecraft onboard integrated navigation system, which should be configured in accordance with standard sections of the final ascent trajectory, are determined. It is proposed to involve so-called interval estimation algorithms in order to ensure the reliability of obtained estimations, taking into account unknown nature of possible navigation measurements information violations. An optional smoothing algorithm based on dynamic Bayesian measurements filtering, considering preliminarily obtained estimations of systematic errors. As an additional means of improving the accuracy of the navigation estimations it is proposed also to involve navigation measurements optimal scheduling methods and algorithms in order to generate optimal schedules of measurements directly on board the spacecraft.