Abstract
The orbital dynamics of solar sail spacecraft are similar in many respects to the orbital dynamics of other spacecraft utilising low thrust propulsion. That is, a small continuous thrust is used to modify the spacecraft orbit over an extended period of time. However, a solar-electric propulsion system may orient its thrust vector in any direction, whereas solar sails are constrained to thrust vector orientations within 90° of the Sun-line. For some mission applications this constraint leads to significant differences between the spacecraft trajectories. For example, to transfer from a prograde to a retrograde orbit, a solar-electric propulsion system may direct its thrust vector perpendicular to the Sun-line to lose prograde angular momentum and then gain retrograde angular momentum. However, for solar sails the transfer is made by increasing the spacecraft ecliptic inclination to greater than 90° by alternately orienting the solar radiation pressure force vector above and below the ecliptic plane. The analysis of such cranking orbit manoeuvres is of importance for some mission applications for both initial mission design and sail sizing. It is this type of preliminary orbit analysis that will be addressed in this chapter. In particular, closed form analytical solutions will be derived wherever possible to provide physical insight. Such analytical solutions also provide a simple and effective means of generating trajectory data for preliminary mission design. More specialised optimal trajectories which require a numerical solution will also be discussed later in this chapter.
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
Schedule a call