Conceptual Design Requirements of a Newly Developed UAV as a ...

composite material to comply with limited aircraft dry weight of 36 kg. This would
provide a tolerance of 4 kg for the structural components of the aircraft in the design and
construction phase compared to the typical design in table 3. Wings should be separable
for ease of store and transportation. Moreover, aerodynamic performance (L/D) have to be
grater than 13, which requires a retractable landing gear configuration. In addition, the
engine has to have high specific power > 2.5 hp/kg, with low SFC< 0.33 kg/hp.hr. Also,
the propeller should have high efficiency during cruise (> 50%). Survivability of the UAV
is improved by a recovery system composed of a parachute and an airbag in case of
emergencies.
Acknowledgment
The author acknowledges the support of King Fahd University of Petroleum and
Minerals during this research.
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SSAS UAV Scientific Meeting & Exhibition, Jeddah, Saudi Arabia (June 6, 2006)
Paper No. SSAS-2006-051