A neuro-adaptive observer, Modified State Observer (MSO), is combined with a Non-Linear Dynamic Inversion (NDI) controller to provide correction thrusts for a low-thrust spacecraft in cislunar space. The MSO helps capture the system modeling error and non-linear uncertainties of the environment while the NDI controller provides a control law that is control affine. A target reference trajectory ending at a lunar Near-Linear Rectilinear Halo Orbit (NRHO) insertion point with continuous thrust is used to study the effectiveness of the controller. A high-fidelity model is created incorporating the lunar ephemeris to represent the true three-body spacecraft model. The effectiveness of the control law in providing reference tracking in this problem is studied. Moreover, the tests are extended to a case where the true dynamics are available, but a Missed Thrust Event causes the thrust along a direction to cut off. © 2024 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.