Abstract
This research is focused on the definition, analysis, and numerical testing of an effective nonlinear orbit control technique tailored to compensating orbit perturbations, as well as possible errors at orbit injection of low- and medium-altitude Earth-orbit satellites. A general, systematic approach to real-time orbit control is presented, under the assumption that the satellite of interest is equipped with a steerable and throttleable low-thrust propulsion system. Two different operational orbits are considered: (a) very-low-altitude Earth orbit and (b) medium-altitude Earth orbit. A feedback control law based on Lyapunov stability theory is proposed and tested. Some remarkable stability properties are established analytically. Then, the overall performance of the nonlinear control at hand is investigated for cases (a) and (b), over 5 years. The effect of satellite eclipsing on available electrical power is considered as well. For mission scenario (a), suitable tolerances on the desired (nominal) conditions allow substantial savings in terms of propellant requirements.
Submitted Version (Free)
Published Version
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.