The flying wing layout exhibits broad application prospects in the fields of unmanned aerial vehicles (UAV) and strategic bombers due to its advantages such as high lift-to-drag ratio, low radar cross-section, and high structural efficiency. However, issues like weak stability, insufficient control effectiveness, and the lack of flight test technology have restricted its further development. This paper presents a comprehensive design and validation of autonomous take-off and landing (ATOL) control laws for a flying wing UAV demonstrator. Addressing the challenges of longitudinal static instability, weak directional control authority, and ground effect disturbances inherent to tailless configurations, the proposed control architecture integrates aerodynamic modeling, multi-surface allocation, and robust trajectory tracking which systematically addresses the key technical challenges of flying wing layout aircraft.