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

Planetary Exploration Using Biomimetics
An Entomopter for Flight on Mars
W =
R
∫ F(r)θrdr
Equation 3-2
0
The total work performed, under a given operational condition and wing geometry, by the
engine per flap (represented by the red-shaded areas in Figure 3-4) is the area under the forcedistance
traveled curve. Examples are shown in Figure 3-5 for various flapping frequencies,
wing lengths, and flapping angle.
3
2.5
2
0.5m, 10 Hz, 30°
0.5m, 10 Hz, 45°
0.5m, 15 Hz, 45°
0.5m, 15 Hz, 30°
0.4m, 15 Hz, 45°
0.4m, 15 Hz, 30°
0.4m, 10 Hz, 45°
0.4m, 10 Hz, 30°
1.5
1
0.5
0
0 0.05 0.1 0.15 0.2 0.25 0.3 0.35 0.4 0.45
Distance Travled byWing (m)
Figure 3-5: Examples of the Effect of Wing Length, Flapping Rate and Flap Angle on the
Work Performed by the Engine
An optimization of the vehicle geometry and operational characteristics was performed. To
determine the combination of flapping frequency, wing length, and flap angle that maximized
lift and minimized wing weight for a given amount of engine power. The effect of engine power
on the maximum lifting capacity of the vehicle was also examined.
The lift generated (L) by the wing can be estimated from Equation 3-3 below, where ρ is the
atmospheric density of Mars near the surface, C L is the lift coefficient of the wing, A w is the
wing area, and V res is the resultant velocity due to the forward motion of the Entomopter and the
flapping of the wings. The resultant velocity is shown in Figure 3-6.
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Phase II Final Report