Abstract:
Micro-UAAVs are slight unmanned aircraft vehicles (UAVs) that are broadening the
prowess of avionics. Moreover, there is a huge disparity in the shape, size, and abilities
of these aircrafts, despite the tremendous demand for the advancement and develop-
ment of these UAAVs. Many mini-UAAVs can only fly at low cruising velocities, and
thermal systems and electronic parts are just yards away from rocket fuel combustion
at tens hundreds of degrees Kelvin. Countless uses, such as mutual operations with
human controlled aerial vehicles, intelligence gathering in vitriolic airfields, or offering
as a target or decoy, necessitate faster take - off and landing velocities with aerial sys-
tem that responds to the demand of high-performance micro-UAVs. This study aimed
to model and simulate a low-cost and high altitude unmanned autonomous aerial vehi-
cle (UAAV) based on MATLAB/Simulink. Linear and rotational dynamics were de-
signed, while wind disturbances were created to test the performance. The propellers
were developed for consistent engine power generations. A simulation and testing of
aerodynamics and transonic steady states were modeled and simulated to provide guid-
ance using MATLAB/ Flight Gear simulator. An autopilot control system was com-
puted to launch and stabilize the UAAV during deployment. The results show that the
torque of 32000N.m, 2050m of altitude, 300m/s of airspeed, 33000km/h of wind dis-
turbances were observed. To conclude, the developed UAAV was tested, deployed, and
performed at 99.98% of success rate with high peak endurance compared to the current
civilian drones. Further study is recommended for undetectable UAAV using XFLR5
and DATCOM softwares.
