Phase II Final Report - NASA's Institute for Advanced Concepts

Chapter 3.0 Vehicle Design
3.1 Wing Sizing
The absolute values associated with the
curves given in Figure 3-2 are dependent
on the size of the wing, flapping rate, and
maximum angle through which the wing
will move. The combination of these variables
must be optimized to maximize the
amount of lift generated by the wing
while operating at a power level that is
achievable by the propulsion system.
Figure 3-4 shows the energy utilized by
the wing throughout the motion of one
flap cycle, as well as the velocity and
acceleration profiles assumed for the wing
motion.
Figure 3-3: Acceleration Force Diagram
The total work performed by the engine to
provide the acceleration during the segments
shown in Figure 3-4 is given by
Equation 3-2. For this initial analysis the
energy recapture portion of the stroke is
not being taken into account. The initial
sizing will utilize no energy capture,
which will build margin into the sizing as
well as account for some of the forces,
such as drag, that are presently not being
taken into account.
Figure 3-4: Wing Motion and Energy Usage,
Velocity and Acceleration Profiles
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