With the development of the low - altitude economy and the growth of the small unmanned aerial vehicle (UAV) market, rotary wing UAVs have limitations in flight speed and stability, while tilt rotor aircraft, with their unique advantages, have become a research hotspot. Thus, it’s important to design a tilt rotor UAV with excellent performance and stability. This paper used commercial software for structural strength and aerodynamic numerical simulations, conducted wind tunnel force measurement experiments, and designed a tilt servo rotor coordinated heading enhancement control strategy and an airspeed - based tilt transition control strategy. Through these theoretical methods and simulations/tests, it was obtained that the designed twin tail beam tilt rotor UAV shows good maneuverability, wind resistance, and smooth mode transition without altitude loss, verifying the effectiveness of the control strategy and the reliability of the overall layout. This paper will give a reference to the design of small UAVs and composite thrust technology aircraft in the future work.