A novel aircraft design integrating multiple modes of flapping rotor, flapping wing and fixed wing is proposed to make micro aircraft perform vertical take-off and landing and efficient forward flight simultaneously. To evaluate the aerodynamic characteristics and stability of the aircraft during the transition between flapping rotor and flapping wing modes, the dynamic grid method is used to simulate the conversion process, and the aerodynamic characteristics of the aircraft at various flapping angles and twist angles are analyzed. The results indicate that the lift force generated during the mode conversion is sufficient to maintain stability, confirming the feasibility of the proposed scheme. The optimal flapping angle and twist angle are determined to provide the greatest lift force.