Application of Celestial Mechanics Theory in Spacecraft Orbit Design

Abstract

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.