The present application relates to the technical field of aircraft control, and discloses a
distributed power ground effect aircraft convenient to control and a control method thereof; the present application replaces traditional
rudder control with a
distributed power system, realizes full-range efficient control from static to high speed, and directly generates multi-dimensional
control torque through
power difference by adopting independent control of positive and negative rotors in cooperation with differential adjustment, so that not only the failure defect of traditional
rudder at
low speed stage is completely eliminated, but also precise attitude adjustment and in-place turning are completed at zero
airspeed, and the response capability of the aircraft in a complex environment is improved; in combination with
air cushion effect optimization design, directional
airflow of front and rear rotors forms a stable
air cushion in combination with a skid structure, low-speed maneuverability is improved, a body-level
turning radius is realized, and the risk of touching water is avoided. The distributed architecture simplifies the
mechanical system, relies on pure electric driving, seamlessly integrates short take-off and landing, cruising and landing processes, reduces
energy consumption, and enhances adaptability in narrow water areas.