The Minor Invention is Balanced and Delayed Ti -rotor Fixed-wing Unmanned Aerial Vehicle

Abstract

The invention relates to 8 ftilt-rotor hybrid fixed-wing and vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) and an associated operating method that improves transition stability, energy efficiency, and control simplicity. In one of its embodiments, the UAV consists of multiple tiltable rotor assemblies (16a, 16b, 17a, and 17b), at least one forward-thrust propulsion unit (18), and a passive delay mechanism integrated with the rotor tilting system (19a, 19b, 20a, and 20b). The rotor assemblies provide vertical lift during takeoff and hover, and the puller propulsion unit generates forward thrust to initiate the rotor tilting until a predefined thrust level or flight condition is reached. This delayed and gradual tilting process improves aerodynamic stability and minimizes transition-induced disturbances without the need for complicated active timing control. Certain rotor assemblies are deactivated and kept at preset, adjustable, or dynamically controlled opposing tilt angles during forward flight. ል aerodynamic surfaces, the inactive rotors produce balancing trim moments that mitigate pitching effects caused by the puller propulsion unit and enhance passive flight stability. While increasing flight efficiency, the opposing rotor orientations reduce the need for constant active control inputs. To minimize system complexity and weight, several rotor assemblies can be mechanically connected and controlled by 8 single actuator. The deactivated rotor assemblies can be reactivated to offer additional propulsion in an optional high-speed operating ጠ6ዐ6. Reliable VTOL-to-forward-flight transition, lower power consumption during cruise, improved aerodynamic balance, and simplified flightcontrol architecture are all made possible by the disclosed invention.