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Analytical Modeling Of Helicopter Static And Dynamic Induced Velocity In Grasp

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Analytical Modeling Of Helicopter Static And Dynamic Induced Velocity In Grasp

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Author :
language : en
Publisher:
Release Date : 1987

Analytical Modeling Of Helicopter Static And Dynamic Induced Velocity In Grasp written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1987 with categories.

This paper describes the methodology used by the General Rotorcraft Aeromechanical Stability Program (GRASP) to model the characteristics of the flow through a helicopter rotor in hovering or axial flight. Since the induced flow plays a significant role in determining the aeroelastic properties of rotorcraft, the computation of the induced flow is an important aspect of the program. Because of the combined finite-element/multibody methodology used as the basis for GRASP, the implementation of induced velocity calculations presented an unusual challenge to the developers. To preserve the modeling flexibility and generality of the code, it was necessary to depart from the traditional methods of computing the induced velocity. This is accomplished by calculating the actuator disc contributions to the rotor loads in a separate element called the air mass element, and then performing the calculations of the aerodynamic forces on individual blade elements within the aeroelastic beam element. Keywords: Rotor flow fields; Rotary wings.

An Investigation Of Helicopter Dynamic Coupling Using An Analytical Model

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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-06-30

An Investigation Of Helicopter Dynamic Coupling Using An Analytical Model written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-06-30 with categories.

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...