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Rotor Blade Motion in a Vertical Sharpedged Gust

Rotor Blade Motion in a Vertical Sharpedged Gust Part IConstant Chord Blades 1. Summary Rotorfuselage 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 sharpedged down gust impinging on the rotor when it is not generating thrust for example, whilst runningup 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 undcrestimates 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. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Rotor Blade Motion in a Vertical Sharpedged Gust

Payne, P.R.
Aircraft Engineering and Aerospace Technology , Volume 26 (1): 5 – Jan 1, 1954
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032377
Publisher site
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Abstract

Part IConstant Chord Blades 1. Summary Rotorfuselage 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 sharpedged down gust impinging on the rotor when it is not generating thrust for example, whilst runningup 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 undcrestimates 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.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Jan 1, 1954

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