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Author: W. E. Sharpe
Publisher:
ISBN:
Category :
Languages : en
Pages : 10
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Book Description
The paper first describes results of static aeroelastic calculations for a recent canard/cranked delta fighter project, in which a complete aircraft aerodynamic and structural model is used to demonstrate full-interacted 'free' aircraft deflection modes and resulting stability effects. The significance of these results is illustrated by comparison with corresponding 'fixed root' calculations, thereby indicating a requirement for complete aircraft aeroelastic modelling at the earliest possible stage in project design. Aeroelastic modelling of external stores in the context of store/aircraft integration is also discussed. Finally, the correction of high-speed wind-tunnel model results for aeroelastic distortion is addressed, indicating those parameters which are likely to be significantly affected.
Author: W. E. Sharpe
Publisher:
ISBN:
Category :
Languages : en
Pages : 10
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Book Description
The paper first describes results of static aeroelastic calculations for a recent canard/cranked delta fighter project, in which a complete aircraft aerodynamic and structural model is used to demonstrate full-interacted 'free' aircraft deflection modes and resulting stability effects. The significance of these results is illustrated by comparison with corresponding 'fixed root' calculations, thereby indicating a requirement for complete aircraft aeroelastic modelling at the earliest possible stage in project design. Aeroelastic modelling of external stores in the context of store/aircraft integration is also discussed. Finally, the correction of high-speed wind-tunnel model results for aeroelastic distortion is addressed, indicating those parameters which are likely to be significantly affected.
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author:
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ISBN:
Category : Aeroelasticity
Languages : en
Pages : 280
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Author: E. G Wilson (Jr)
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Category :
Languages : en
Pages : 8
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Book Description
Static aeroelastic effects are manifested in the form of changes in the total load or lift on the aircraft, or in changes in the overall distribution of load or lift. These changes affect the structural integrity of the vehicle, its static stability, the effectiveness of various control surfaces, and the overall flight performance. The characteristics and magnitude of these aeroelastic effects are dependent on the aerodynamic shape of the vehicle, the structural orientation, the structural stiffness, and the particular flight condition in terms primarily of Mach number and dynamic pressure. A review of fighter aircraft development programs over the past 30 years indicates a trend of increasing emphasis on the consideration of static aeroelastic effects. While early concerns addressed only the impact on air vehicle structural integrity, current design philosophy recognizes and addresses aeroelasticity as a primary design parameter affecting structural optimization, vehicle aerodynamic stability, control effectiveness, and overall performance. Examples from wind tunnel testing, analytical studies and operational aircraft applications are presented to justify this emphasis illustrate current methodology and analysis techniques, and make a case for an integrated approach to the consideration of static aeroelastic effects at all stages of the design process.
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Category : Government reports announcements & index
Languages : en
Pages : 1832
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Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
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Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 538
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Author:
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ISBN:
Category : Government reports announcements & index
Languages : en
Pages : 1600
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Author: ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRAN CE)
Publisher:
ISBN:
Category :
Languages : en
Pages : 186
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Modern high performance aircraft designs tend to employ very thin airfoils having a degree and a distribution of stiffness far from the ideal; in consequence, there is a loss of control effectiveness and maneuverability. Moreover, the introduction of the highly forward-swept-wing planform poses a static aeroelastic effect of fundamental importance; these effects are felt at model as well as at full scale. This meeting was organized not only to review instances of these problems but to see how successfully modern tools for structural and aeroelastic analysis can be applied. The individual papers of the meeting cover many aspects of static aeroelasticity not only for military aircraft but also for modern transport aircraft. The various papers also address problems and recent progress in wind tunnel model testing, in particular measurement of static deformations on wind tunnel models. Keywords: Flutter, Supercritical wings, Aerodynamic loading, Jet fighters, Aerodynamic trim, Symposia, Maneuverability, Sweptforward wings, Aeroelasticity, Aerostatics, Structural analysis, Military aircraft, Transport aircraft, Wind tunnel models.
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 700
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