Abstract:
The UAV had been designed in order to meet the
specifications required for surveillance and reconnaissance mission.
It followed the global UAV designs in this industry where the pusher
configuration is dominating over the various other conventional
probabilities. A project was undertaken to study & design Co-axial
propeller for Small unmanned aerial vehicle UAV .the study started
from the comparison between three practical steps ; single propeller ,
single propeller with forward or rearward cascade & Co-axial
propeller. The choice appeared to select a cascade propeller engine to
obtain best criteria with less cost. The design had to be compatible
with the propeller design work being done concurrently. Of
particular interest was comparing the resulting thrust to propel the
UAV at a given airspeed.
The entire propeller design process from airfoil selection to final part
generation in computer-aided drafting program is mentioned. The
Clark-y airfoil defined the propeller cross section.
Design of propeller blades and mechanism to compare the output
thrust between them and determine power that required rotating
propeller. Modification of the mechanism and the manufacture of
propeller from the prototype to the final model will be experimented
and discussed throughout the project.
Static and dynamic analysis for a stability model using the digital
DATCOM had shown UAV is stable statically and dynamically, and
a Simulink model was developed to verify the dynamic modes. A
structural analysis was further initiated to assess the loads acting on
individual components and whether they can sustain the loads or not.