Low-Thrust Lunar Capture Leveraging Nonlinear Orbit Control

Abstract Nonlinear orbit control with the use of low-thrust propulsion is proposed as an effective strategy for autonomous guidance a space vehicle directed toward Moon. Orbital motion described in ephemeris model, inclusion most relevant perturbations. Unfavorable initial conditions, associated weak, temporary lunar capture, are considered, representative conditions that may be encountered real mission scenarios. These occur when spacecraft released nonnominal flight which would naturally lead it to impact Moon or escape gravitational attraction. To avoid this, propulsion, conjunction nonlinear control, employed, drive two different, prescribed, low-altitude orbits. leads identifying saturated feedback law (for magnitude and direction) proven enjoy global stability properties. The at hand successfully tested on three different Then, capture region identified, includes large set achieve final acquisition. For purpose achieving shown more if ignited aposelenium.