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

Planetary Exploration Using Biomimetics
An Entomopter for Flight on Mars
0.14
0.12
Mass (kg) Variable Chord
Mass (kg) Constant Cord
0.1
0.08
0.06
0.04
0.02
0
0 0.05 0.1 0.15 0.2 0.25 0.3 0.35 0.4 0.45 0.5
Radial Station
Figure 3-13: Mass Distribution Along the Wing Length (Based on 10 Incremental Mass
Sections)
By using Equations 3-11 through 3-17 the loading on the wing was determined at 10 radial stations.
Flapping frequency, wing length and maximum wing angle were varied to see what effect
these had on the loading. The following figures show what effect these variables have on the
wing loading. The tangential loading in N/m is at various times throughout the complete stroke
cycle. This tangential load will vary from positive (upward away from the surface) to negative
(downward toward the surface) depending on the direction the wing is moving.
Based on the sizing analysis the wing angle will need to be as great as possible (on the order of
±75°). It is worth noting that the increase in wing angle has a greater effect on the radial loading
then on the normal (tangential) or bending loads.
The maximum loading at each point along the wing occurs when the wing is at its maximum
downward position. It this position the wing sees both a maximum acceleration load as well as a
gravitational load both working in the downward direction.
Utilizing the wing loading profile (W(r) given in Equation 3-19 and shown in Figure 3-14) the
shear force, bending moment and deflection of the wing can be calculated. The shear loading is
calculated by integrating the wing loading profile. This integration can be done numerically or
analytically, utilizing an equation for the loading profile. For example using the wing loading for
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Phase II Final Report