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First published online July 20, 2007
Journal of Experimental Biology 210, 2714-2722 (2007)
Published by The Company of Biologists 2007
doi: 10.1242/jeb.004507
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Flight stabilization control of a hovering model insect

Mao Sun* and Ji Kang Wang

Institute of Fluid Mechanics, Beijing University of Aeronautics and Astronautics, Beijing 100083, People's Republic of China


Figure 1
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  		Fig. 1. Definition of the state variables u, w, q and {theta} and sketches of the reference frames. The model insect is shown during a perturbation (u, w, q and {theta} are zero at equilibrium).

 

Figure 2
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  		Fig. 2. Portions of the grid for the hoverfly wing.

 

Figure 3
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  		Fig. 3. (A) Time courses of vertical force coefficient (Cv), (B) horizontal force coefficient (CH) and pitching moment coefficient (CM) in one wingbeat cycle at equilibrium.

 

Figure 4
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  		Fig. 4. The u-series (A), w-series (B) and q-series (C) force and moment data. {Delta}X+ and {Delta}Z+, non-dimensional x- and z-components of the total aerodynamic force, respectively; {Delta}M+, non-dimensional pitching moment; {Delta}u+, non-dimensional x-components of velocity of center of mass (prefix {Delta} indicates that the equilibrium value is subtracted from each quantity).

 

Figure 5
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  		Fig. 5. The {Phi}-series (A), {alpha}1-series (B), {phi}-series (C) and {alpha}2-series (D) force and moment data. {Delta}X+ and {Delta}Z+, non-dimensional x- and z-components of the total aerodynamic force, respectively; {Delta}M+, non-dimensional pitching moment. {Delta}{Phi} and {Delta}{phi}, changes in stroke amplitude and mean stroke angle, respectively; {Delta}{alpha}1, equal change in the down- and upstroke angles of attack; {Delta}{alpha}2, differential change in the down- and upstroke angles of attack. {Delta} Prefix indicates that the equilibrium value is subtracted from the quantity.

 

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© The Company of Biologists Ltd 2007