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An Investigation of Helicopter Dynamic Coupling Using an Analytical Model
AUTHOR | Nasa, National Aeronautics and Space Adm |
PUBLISHER | Independently Published (10/24/2018) |
PRODUCT TYPE | Paperback (Paperback) |
Description
Many attempts have been made in recent years to predict the off-axis response of a helicopter to control inputs, and most have had little success. Since physical insight is limited by the complexity of numerical simulation models, this paper examines the off-axis response problem using an analytical model, with the goal of understanding the mechanics of the coupling. A new induced velocity model is extended to include the effects of wake distortion from pitch rate. It is shown that the inclusion of these results in a significant change in the lateral flap response to a steady pitch rate. The proposed inflow model is coupled with the full rotor/body dynamics, and comparisons are made between the model and flight test data for a UH-60 in hover. Results show that inclusion of induced velocity variations due to shaft rate improves correlation in the pitch response to lateral cycle inputs. Keller, Jeffrey D. Unspecified Center NAG2-561...
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Product Format
Product Details
ISBN-13:
9781729165799
ISBN-10:
1729165796
Binding:
Paperback or Softback (Trade Paperback (Us))
Content Language:
English
More Product Details
Page Count:
26
Carton Quantity:
157
Product Dimensions:
8.50 x 0.05 x 11.02 inches
Weight:
0.19 pound(s)
Country of Origin:
US
Subject Information
BISAC Categories
Science | Space Science - General
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Many attempts have been made in recent years to predict the off-axis response of a helicopter to control inputs, and most have had little success. Since physical insight is limited by the complexity of numerical simulation models, this paper examines the off-axis response problem using an analytical model, with the goal of understanding the mechanics of the coupling. A new induced velocity model is extended to include the effects of wake distortion from pitch rate. It is shown that the inclusion of these results in a significant change in the lateral flap response to a steady pitch rate. The proposed inflow model is coupled with the full rotor/body dynamics, and comparisons are made between the model and flight test data for a UH-60 in hover. Results show that inclusion of induced velocity variations due to shaft rate improves correlation in the pitch response to lateral cycle inputs. Keller, Jeffrey D. Unspecified Center NAG2-561...
Show More