Part I—Constant Chord Blades 1. Summary Rotor/fuselage clearance is the most fundamental design consideration when laying out a new project, and it is essential to estimate this accurately at a very early stage. When centrifugal force droop stops are fitted to a rotor, the design criterion is usually the effect of a sharp-edged down gust impinging on the rotor when it is not generating thrust; for example, whilst running-up on the deck of an aircraft carrier. In this paper the dynamics of blade flapping motion are developed and a method for rapidly obtaining maximum gust deflexion is presented in the form of a Data Sheet (FIG. 5). This enables the maximum deflexion in a gust to be determined with no calculation. The solution obtained is exact; hitherto the only attempts to calculate gust deflexion known to the writer have developed an approximate equation of motion for the blade, and offered the Particular Integral as a sufficiently accurate solution. It is shown in Part II of this paper that this can be very misleading, and undcr-estimates the true deflexion. In preliminary project design, the blade inertia is, of course, unknown. It is shown that this is a function of the coning angle and CL, basic only, probably the two most fundamental design parameters.
Rotor Blade Motion in a Vertical Sharp-edged Gust
A Study of the Dynamics of Helicopter Blade Flapping with a Method of Deriving Maximum Gust Deflexion
Aircraft Engineering and Aerospace Technology ; 26 , 1 ; 10-14
01.01.1954
5 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Rotor Blade Motion in a Vertical Sharp-edged Gust
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