ABSTRACT
This chapter summarizes the basic theories and engineering applications of spacecraft orbit design, including various basic knowledge and important theories on spacecraft orbit mechanics, as well as the orbiting theory, calculation method, orbit control, propellant budget and other engineering application methods of various spacecrafts. The transition of a spacecraft from its initial orbit (or parking orbit) to its target orbit is an orbital transfer, usually accomplished by orbital maneuvers. Orbital transfer can be achieved in many ways, including one maneuver, two maneuvers and multiple maneuvers depending on the number of orbital maneuvers. In the Sun-Synchronous Orbit, the angle between the spacecraft-sun line and the spacecraft orbit plane is constant, so is the angle for viewing the sun. This orbit is used by the vast majority of optical remote sensing spacecrafts. The purpose of Earth-Mars transfer orbit design is to select the appropriate launch window and flight time, so that the probe can fly from spacecraft-rocket separation point to periareon.
