Structure design of hybrid wing eVTOL motor beam

The hybrid wing eVTOL motor beam is a key critical structure component，and the flight load is com plex during the conversion and reverse conversion flight stages. Therefore，studying its structure design is of great significance. This article studies the propeller lift loads and flight overload of the motor beam during vertical takeoff，transition，fixed-wing flight，reverse transition，vertical landing flight stages. Under this load，a motor arm structure with dual transmission paths is designed，and the structure optimization of the motor seat is carried out under the given constraint conditions. The motor beam structure design is calculated through simulation analysis，ensure that the stress level of the composite materials and metal parts on the motor arm is lower than the design allow able value. Finally，the experimental loading method is designed based on the structural form of the motor arm. The strain and deformation during the measurement experiment are compared and analyzed with the strength calculation results through static strength tests and flight tests. The accuracy of the motor beam structure design and calculation results are verified. Results show that the eVTOL motor beam designed in this paper can meet the stiffness，strength，fatigue design requirements.