Analysis & Design
Part 1The unmanned aerial vehicle (UAV) platform is designed in a quadcopter configuration to support a 7.3 kg empty weight and a maximum payload capacity of 5 kg. The propulsion optimization was calculated in SolidWorks so that the total take-off weight — comprising the airframe, battery, and maximum mission payload — is sustained at the 50% throttle (hover) level, and the motor efficiency band is kept at the maximum thrust-to-energy ratio.
A stacked airframe architecture was developed to damp the disturbing effects of the high-mass energy block (6S 30,000 mAh) and variable mission payloads on flight dynamics. In this configuration, the lower layer is allocated to the SIYI A8 Mini gimbal and payload-release systems, where field of view is critical; the middle layer to the high-current Power Distribution Board (PDB) and cable harnesses; and the upper layer to the low-interference-tolerance flight-control and communication avionics.
The battery block is positioned at the volumetric center of the airframe to minimize Center of Gravity (CG) deviations that directly affect autonomous cruise stability, and it is fed from a dedicated carbon fiber housing (top-accessible) with electromagnetic and thermal insulation. To shorten setup time during field deployment and reduce transport volume, carbon fiber tube-type foldable motor arms and quick-release landing gear mechanisms were integrated into the system. The rigidity of the entire system was validated through SolidWorks Finite Element Analysis (FEA) processes.
Quadcopter Stacked Airframe CG Optimization SolidWorks FEA