Abstract:
A conceptual design methodology was produced and subsequently coded into a
Visual C++ (GUI) environment to facilitate the rapid comparison of several possible
configurations to satisfy High Altitude Long Endurance (FIALE) unmanned aircraft (UAV)
missions in the Low Speed (propeller driven aircraft) regime.
Several comparative studies were performed to verify the applicability of traditional
design methods. The traditional computational design methodologies fail in several areas
such as high aspect ratio wing weight estimation and design, low Reynolds number wing
design, high altitude engine performance, low Reynolds number drag estimation, unmanned
aircraft design, and the conceptual design of unconventional configurations. The
methodology developed for this thesis was robust enough to allow not only for
consideration of these areas of inadequacy in traditional methods, but also to allow for the
inclusion of advancements in the relevant technologies as they become more widely
available.
The following configurations were evaluated for suitability to the Low Speed HALE
UAV application: conventional, canard, twin boom, multiple fuselage (conventional or
canard), tandem wing, multiple fuselage tandem wing or flying wing configuration. The
configurations were compared on the basis of aircraft endurance for takeoff weights ranging
from 2,000 to 20,000 pounds and wing loadings ranging from 5 to 25 lbs1fe.
Initial drag estimates were made using traditional parabolic drag estimation
techniques. A more refined drag buildup was performed using a vortex lattice drag
estimation for the lift induced drag (for all lifting components) and calculated skin friction
coefficients for the parasite drag. Statistically based methods were used for other
components of drag having much smaller contributions. In addition, a statistical approach
was taken to the weight estimation of the major aircraft components. However, this
approach made comparison of alternative configurations more difficult. Thus wing bending
moments trends were evaluated and utilized in the development of weight saving values for
multiple fuselage wing weight estimation.
The comparative performance of each configuration is justified with direct reference
to the terms in the Breguet Endurance equation. Validation was performed where possible
on all modules and segments associated with the methodology, as well as for the
macroscopic results. In addition, parametric studies on endurance were performed for the
conventional configuration for geometric characteristics and operating conditions directly
and indirectly effecting the calculated endurance and generalized results presented. Finally, a
case study was performed to demonstrate this capability.
A new relation was developed for aircraft empty weight prediction, a low speed
airfoil figure of merit was proposed, and new constants were offered for UAV fuselage
length prediction. In addition, horizontal and vertical tail volume coefficients were proposed
for all of the Low Speed HALE UAV configurations considered. It was determined that the
multiple fuselage configurations showed comparatively superior endurance performance
across a range of takeoff weights, with several other configurations demonstrating marginal
endurance improvements. Finally, a highly flexible and robust computer based conceptual
design methodology was developed and validated enabling the quick comparison of a greater
number of possible configurations to satisfy a given mission for Low Speed HALE UAV's
and providing detailed drag and weight breakdown data.