A Mathematical Model of a Single Main Rotor Helicopter for ... - Read
A Mathematical Model of a Single Main Rotor Helicopter for ... - Read
A Mathematical Model of a Single Main Rotor Helicopter for ... - Read
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HU B-BODY<br />
AIRCRAFT REFERENCE<br />
SYSTEM<br />
Figure B-2.- Hub-body, aircraft reference and body-c.g. axis systems.<br />
Aircraft Reference<br />
The aircraft reference axes are used to locate all <strong>for</strong>ce and moment generating<br />
components and the center <strong>of</strong> gravity. The aircraft reference axes are parallel to<br />
the body-c.g. axes. The axis origin is typically located ahead and below the aircraft<br />
at some arbitrary point within the plane <strong>of</strong> symmetry. Stations are measured<br />
positive aft along the longitudinal axis.<br />
to the pilot's right. Waterlines are measured vertically, positive upward (see<br />
fig. B-2).<br />
Local Wind<br />
'EM<br />
Buttlines are lateral distances, positive<br />
The local-wind axes systems are employed <strong>for</strong> calculation <strong>of</strong> lift and drag<br />
<strong>for</strong>ces on the empennage and on the fuselage. For each empennage surface, the origin<br />
is at the quarter point <strong>of</strong> the mean aerodynamic chord, and the lift <strong>for</strong>ce is normal<br />
to the relative wind and to a spanwise line passing through the quarter chord point.<br />
14<br />
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