0888

Item 0888

DESIGN: UniCopter ~ Rotor - Blade - NACA00xx - Leading Edge Weight

Drawing:

Notes: Go to Note below. This note is probably obsolete since it assumes that leading edge chord dimension is less at the root then at the 25% of R

Consider locating the leading edge weight near 25% of radius (R).

Reasons:

This is the location where the chord is the greatest and therefore the moment arm about the feathering axis can be the greatest and the weight the least.
Locating it close to the root will reduce the centrifugal force and therefore the size of the pitch thrust bearings. This should not be detrimental to autorotation because there still is a large amount of mass in the six blades.
The blades will be stiff enough to accept the fact that the weight is concentrated.

Notes:

Consider locating the leading edge weight in the machined out portion of the leading edge of the spar at the tip end. One reason for this is that the tip control will probably not have any power assist.

The axis of pitch will probably at 505 of chord at the root, because of the blade designed for reverse velocity. Therefor a small localized weight might be located in the leading edge at approximately 25% of R.

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Last Revised: May 5, 2005