Low-Thrust Control of Lunar Orbits
A method is presented for the control of lunar orbiters using continuous low-thrust propulsion. While the proposed approach is fairly general and could be useful for a variety of mission scenarios, in this work it is applied to the partic-utar case of obtaintng a lunar Sun-synchronous orbit for use in a lunar mapping mission. Using optimal control theory, it is shown that a lunar orbit can be obtained that is low-altitude, near-polar, and Sun-synchronous. The analytis of the optimal control probtem leads to the commonly seen two-point boundary value problem, which is solved ustng an indirect shoottng algorithm.
N. Harl and H. J. Pernicka, "Low-Thrust Control of Lunar Orbits," Advances in the Astronautical Sciences, American Institute of Aeronautics and Astronautics (AIAA), Jan 2009.
19th AAS/AIAA Space Flight Mechanics Meeting
Mechanical and Aerospace Engineering
Keywords and Phrases
Low Thrust; Low-Altitude; Low-Thrust Propulsion; Lunar Orbit; Lunar Orbiter; Mapping Missions; Optimal Control Theory; Optimal Controls; Sun Synchronous Orbits; Two-Point Boundary Value Problem
Article - Conference proceedings
© 2009 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Jan 2009