Structure optimization and implementation of a lightweight sandwiched quadcopter

Abstract

A three-layered sandwiched structure of quadcopter was proposed to lower the weight and rotary inertia, resulting in an increase in endurance time and payload in this present work. The framework was optimized with two carbon fiber layers on the surface and balsa in the middle. The weight was reduced to 148 g via the options of aluminum alloy, balsa and carbon fiber reinforced polymer (CFRP). Stress analysis shows that the stress and strain of this structure were within the safety range even when all four rotors are at maximum thrust with maximum payload which guarantees enough stiffness of the structure. A prototype controlled by an open source controller was used to run the tests. The flight tests indicated that endurance time was 29 min and the payload was 700 g, respectively.