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

will be 1.66 m 2 at standard atmosphere. Higher atmospheric temperature and/or altitude
would require slightly higher takeoff speed due to reduced density. For example at 50 C o ,
sea level, the takeoff speed will be 26.5 m/s, only a 6% increase compared to standard
atmosphere conditions.
Structure
The Present UAV has a conventional aerodynamic configuration with pusher-type
propeller See figure 4. The main fuselage has a maximum diameter of about 350 mm to
contain cameras similar to the BAI 5 as well as large fuel tank and Payload:
Propeller
Fuselage
Camer
a
Figure 4: Basic configuration of the UAV.
The UAV is to be made from composites (glass fiber and/or Carbon fiber) and
Aluminum alloy, to provide high strength to weight ratio. Skin parts and some of the
skeleton supposed to be made from composite material while hard points and joints to be
mainly from aluminum alloy for improved reliability. Part of the wing is supposed to be
separable during storage and transportation for convenience of use and handling. For the
systems contained in the fuselage they have to abide by the dimensional restrictions and
maintain a reasonable static margin for stability purposes. Systems layout in the fuselage is
illustrated in figure 5. Engine, landing gear and camera are supposed to have fixed
locations. Fuel will be stored in multiple tanks, close to center of gravity for stability
during flight and flexibility of payload as well as static margin consideration. The payload
bay should contain flexible mount system for different parts and configuration of
communication, control and payloads. The camera is (which is a part of the payload)
mounted at the bottom of the aircraft as shown in figure 5. Recovery Parachute and airbag
has to be on the center of gravity.
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SSAS UAV Scientific Meeting & Exhibition, Jeddah, Saudi Arabia (June 6, 2006)
Paper No. SSAS-2006-051