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Author:
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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:
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:
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 : 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 : 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 :
Languages : en
Pages : 2180
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 1342
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Author: United States. Federal Aviation Administration
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Category :
Languages : en
Pages : 590
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Author: L. G. Hofmann
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ISBN:
Category :
Languages : en
Pages : 376
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Author: Duane T. McRuer
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ISBN:
Category : Large space structures (Astronautics)
Languages : en
Pages : 150
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Book Description
This report presents methodologies for the direct digital control of vehicles with flexible modes. The techniques yield robust control system designs with modest or minimal requirements on the number of sensors and control actuators. the digital system techniques used include primarily the w-transforms for direct design and stability assessment, and the 'hybrid' frequency response, for assessment and understanding of digital system peculiarities. The 'sawtooth Bode' is used as the basic control system design concept. These three elements are applied to several examples, including a comprehensive case study for a fighter aircraft flight and flexible mode control system. Both continuous and discrete system designs are considered and the continuous system characteristics are contrasted with an optimal control design. This comparison pinpoints some of the features needed to make optimal control procedures more practical and mature for flexible vehicle control applications. An important step is taken in this direction by determining the nature of performance criteria which yield, for an example case, a highly robust, extremely simple controller derived from an optimal control procedure.
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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