Topics on Flexible Airplane Dynamics. Pt. 1. Residual Stiffness Effects in Truncated Modal Analysis

Topics on Flexible Airplane Dynamics. Pt. 1. Residual Stiffness Effects in Truncated Modal Analysis PDF Author: B.F. Pearce
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Category :
Languages : en
Pages :

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Topics on Flexible Airplane Dynamics. Pt. 1. Residual Stiffness Effects in Truncated Modal Analysis

Topics on Flexible Airplane Dynamics. Pt. 1. Residual Stiffness Effects in Truncated Modal Analysis PDF Author: B.F. Pearce
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Topics on Flexible Airplane Dynamics: Residual stiffness effects in truncated modal analysis

Topics on Flexible Airplane Dynamics: Residual stiffness effects in truncated modal analysis PDF Author:
Publisher:
ISBN:
Category : Aeroelasticity
Languages : en
Pages : 42

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pt.3: The dynamic coupling of rigid and elastic degrees of freedom of an airplane are described by two methods. In the first, coupling is described by the changes in airframe characteristic equation roots caused by the introduction of coupling terms to the equations of motion. The second method employs modal response coefficients to compare the relative amplitudes of rigid and elastic degrees of freedom at each coupled mode frequency. Simple literal expressions are obtained for each of these descriptors and physical interpretations given. Time vector diagrams are also used to show the major parameters affecting coupling. (Author).

Topics on Flexible Airplane Dynamics. Part I. Residual Stiffness Effects in Truncated Modal Analysis

Topics on Flexible Airplane Dynamics. Part I. Residual Stiffness Effects in Truncated Modal Analysis PDF Author: B. F. Pearce
Publisher:
ISBN:
Category :
Languages : en
Pages : 26

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The flexible airframe equations of motion are derived with an arbitrary number of elastic de grees of freedom included. The number of equa tions is reduced to include only those necessary for adequate dynammic representation of the air frame, and the effects of the excluded modes are shown. The result is that a matrix X sub in finity must be calculated which is a function of the flexibility represented by the excluded modes. The calculation of this matrix is com plicated by the fact that it is, in explicit form, a function of the mode shapes for the ex cluded elastic degrees of freedom. Usually only a few of these higher order mode shapes can be found withh any accuracy. The problem is resolved by identifying two quantities, X sub f and X sub f infinity, which are ssuperposable to give the complete effects of structural static deflections, X sub infinity. This physi cally satisfying result is implemented by re lating X sub f infinity and X sub f to basic geometrical, inertial, and stiffness properties. The solution is completely general and applies to all elastic systems. (Author).

Topics on Flexible Airplane Dynamics: Coupling of the rigid and elastic degrees of freedom of an airframe

Topics on Flexible Airplane Dynamics: Coupling of the rigid and elastic degrees of freedom of an airframe PDF Author:
Publisher:
ISBN:
Category : Aeroelasticity
Languages : en
Pages : 86

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Book Description
pt.3: The dynamic coupling of rigid and elastic degrees of freedom of an airplane are described by two methods. In the first, coupling is described by the changes in airframe characteristic equation roots caused by the introduction of coupling terms to the equations of motion. The second method employs modal response coefficients to compare the relative amplitudes of rigid and elastic degrees of freedom at each coupled mode frequency. Simple literal expressions are obtained for each of these descriptors and physical interpretations given. Time vector diagrams are also used to show the major parameters affecting coupling. (Author).

Topics on Flexible Airplane Dynamics

Topics on Flexible Airplane Dynamics PDF Author:
Publisher:
ISBN:
Category : Aeroelasticity
Languages : en
Pages : 38

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Book Description
pt.3: The dynamic coupling of rigid and elastic degrees of freedom of an airplane are described by two methods. In the first, coupling is described by the changes in airframe characteristic equation roots caused by the introduction of coupling terms to the equations of motion. The second method employs modal response coefficients to compare the relative amplitudes of rigid and elastic degrees of freedom at each coupled mode frequency. Simple literal expressions are obtained for each of these descriptors and physical interpretations given. Time vector diagrams are also used to show the major parameters affecting coupling. (Author).

Topics on Flexible Airplane Dynamics: The application of flexible airframe transfer function approximations and the sensitivity of airframe transfer functions to elastic mode shapes

Topics on Flexible Airplane Dynamics: The application of flexible airframe transfer function approximations and the sensitivity of airframe transfer functions to elastic mode shapes PDF Author:
Publisher:
ISBN:
Category : Aeroelasticity
Languages : en
Pages : 62

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Book Description
pt.3: The dynamic coupling of rigid and elastic degrees of freedom of an airplane are described by two methods. In the first, coupling is described by the changes in airframe characteristic equation roots caused by the introduction of coupling terms to the equations of motion. The second method employs modal response coefficients to compare the relative amplitudes of rigid and elastic degrees of freedom at each coupled mode frequency. Simple literal expressions are obtained for each of these descriptors and physical interpretations given. Time vector diagrams are also used to show the major parameters affecting coupling. (Author).

U.S. Government Research Reports

U.S. Government Research Reports PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 2180

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Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 276

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Aeroelastic Effects from a Flight Mechanics Standpoint

Aeroelastic Effects from a Flight Mechanics Standpoint PDF Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Flight Mechanics Panel
Publisher:
ISBN:
Category : Aeroelasticity
Languages : en
Pages : 874

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Selected Technical Reports

Selected Technical Reports PDF Author: United States. Federal Aviation Administration
Publisher:
ISBN:
Category :
Languages : en
Pages : 590

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