Abstract
A novel guidance law that utilizes optimal control theory in combination with linear time-varying state-transition matrices to calculate the optimal path for a chaser spacecraft from its initial point to a desired final point and a desired amount of time is proposed in this paper. The optimal guidance law is formulated using more accurate second-order integral form of Gauss Variational Equations to map control accelerations to the dynamics in terms of relative orbital elements. When comparing the second-order form against the traditional Gauss Variational Equations, the guidance law results in a 15% reduction in control demand. In addition, this paper presents a new method that allows for the closed-loop testing of guidance, navigation and control systems with realistic software models of GPS receivers, RADAR systems for on-board relative navigation, and ground-station up-links of the target states. Specifically, utilizing the signal-to-noise ratio of various sensors, the errors that arise due to hardware noise and/or environmental factors can be modeled accurately based on the communication link. The guidance law is tested using the newly developed software-in-the-loop test-bed for a far-range formation flight scenario around the non-cooperative Alouette-2 spacecraft as well as on an arbitrary defined highly elliptical orbit.
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Chihabi, Y., Ulrich, S. Software-in-the-Loop Validation of a Novel Two-Point Optimal Guidance for Perturbed Spacecraft Rendezvous and Formations. J Astronaut Sci 70, 43 (2023). https://doi.org/10.1007/s40295-023-00405-8
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DOI: https://doi.org/10.1007/s40295-023-00405-8