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Author:
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Category : Aeroelasticity
Languages : en
Pages : 42
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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).
Author:
Publisher:
ISBN:
Category : Aeroelasticity
Languages : en
Pages : 42
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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).
Author: B.F. Pearce
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Category :
Languages : en
Pages :
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Author: B. F. Pearce
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Book Description
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).
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).
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).
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).
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 746
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Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
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ISBN:
Category :
Languages : en
Pages : 780
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Author: Aeronautical Research Council (Great Britain)
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 934
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Author:
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ISBN:
Category : Shock (Mechanics)
Languages : en
Pages : 736
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