Quadcopter structures are predominantly deployed in multifaceted environments and diverse applications due to their inherent hovering characteristics and agile maneuverability. The centre frame of Quadcopter is occupying more weight in comparison to other elements and assembly of these kind of structures consume lot of time with significant effort. In view of this, the present study focuses on design of unified Quadcopter frame structure to minimize the assembly time. The structural characteristics are assessed through performing buckling, modal and harmonic response analysis. It is observed that, less deformation is experience in buckling mode and the natural frequencies are far away from the operating frequency which is quite evident from the modal analysis. The steady state response through harmonic analysis reveals that it can withstand the vibration level. The simulation results suggested that the unified Quadcopter frame can withstand uncertain loads and thrust generated from the propellers for achieving stable flight. 

The study is about a two-dimensional (2D) numerical simulation of six square cylinders in 2×3 formation at a low Reynolds number (100) using numerical simulation. The distance between the cylinders was 1 ≤ L/D ≤ 4 .It is noticed that the gap spacing directly affects the flow characteristics and vortex shedding formation. Three wake patterns were found 

• a stable shielding wake pattern for L/D=1 

• a wiggling shielded wake pattern for 2≤ L/D ≤3 

• a vortex shedding wake pattern for L/D=4. 

The study found that the drag and lift coefficient increases with increasing spacing. Drag coefficient decreases for upstream cylinders and increases for downstream cylinders with increasing L/D. FFT was done to analyze the vortex shedding frequency. A single peak, which indicates the primary Strouhal number was observed in the PSD spectrum except for L/D=2.For better understanding vorticity contours and force coefficient pots are analyzed in this paper also.