Abstract
This paper systematically studies the application of orbital dynamics theory in spacecraft orbit design. In this paper, two linearized equations with J2 relative term perturbation are introduced firstly, and their advantages and disadvantages are compared and analyzed. On this basis, an improved method is proposed and applied to the design of hovering orbit and fast flying orbit, and good results are obtained in some cases. The traditional numerical solution algorithm for ballistic design is innovated and improved, and the improved Newton iterative method is comprehensively applied to ensure that the algorithm can still converge quickly under the condition of inaccurate initial value; The simulation results show that the orbit integrated rapid design method studied in this paper is reliable, fast and accurate, and can be applied to the rapid orbit design of spacecraft.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: 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.
