Aerodynamics and Design for Ultra-Low Reynolds Number Flight
Aerodynamics and Design for Ultra-Low Reynolds Number Flight
Aerodynamics and Design for Ultra-Low Reynolds Number Flight
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Chapter 7<br />
required <strong>for</strong> hover is 16V at a current draw of one ampere. Sixteen Watts is considerably<br />
more power than predicted <strong>for</strong> the rotors alone. Each rotor has been shown to require<br />
roughly 0.6W of power when generating the necessary thrust, a value that has been<br />
verified by OVERFLOW-D computations <strong>and</strong> experiment. This tremendous loss of<br />
power between source <strong>and</strong> rotor represents a practical challenge <strong>for</strong> developing micro-<br />
rotorcraft <strong>and</strong> likely places this scale of vehicle somewhat beyond the current state-of-<br />
the-art, but efficient electrical power management <strong>and</strong> motor control are beyond the<br />
scope of this thesis.<br />
7.3 The 65g Prototype<br />
The intermediate size rotorcraft, with a target gross mass of 65g, has been created<br />
primarily as a testbed <strong>for</strong> electronic systems integration, <strong>and</strong> implementation of<br />
augmented stability <strong>and</strong> control. Two versions have been built, one using remote radio<br />
control without any stability augmentation, <strong>and</strong> the second incorporating on-board solid<br />
state gyroscopes, a microprocessor, <strong>and</strong> small transceiver. Photographs of each version<br />
provided in Figures 7.2 <strong>and</strong> 7.3. The mass allocation <strong>for</strong> the two versions is provided in<br />
Table 7.2.<br />
154<br />
TABLE 7.2 Mass allocation <strong>for</strong> the 65g prototype electric rotorcraft.<br />
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