The invention discloses a four-
flapping-wing aircraft and an
attitude control system thereof, and relates to the technical field of micro aircrafts, and the four-
flapping-wing aircraft comprises a fixed rack, a guide rod, a slide block mechanism, a pitching frame, a rolling frame, a
pulley and a chord driving
system. The fixed rack is provided with four cantilevers, a sliding block mechanism is installed on a guide rod, and the pitching frame and the rolling frame control pitching and rolling actions through steering engines respectively. The four pulleys are connected to the pitching frame, and each
pulley is hinged to one wing. The string driving
system comprises a guide wheel, a string and a
crank, one end of the string is connected with the slider mechanism, and the other end bypasses the guide wheel and is connected with the
pulley to realize wing
flapping. Through the deflectable spars and fine steering engine control, efficient aerodynamic performance, enhanced thrust output and excellent flight flexibility and adaptability are achieved, meanwhile, due to the design of the
crank sliding blocks,
structural stress is relieved, the service life is prolonged, the aircraft adapts to multiple flight
modes, and the environment adaptability and task execution efficiency of the aircraft are improved.