3 edition of Digital-flutter-suppression-system investigations for the active flexible wing wind-tunnel model found in the catalog.

Digital-flutter-suppression-system investigations for the active flexible wing wind-tunnel model

metale neferoase

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Published by Administrator in National Aeronautics and Space Administration, Langley Research Center

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  • United States
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    • National Aeronautics and Space Administration, Langley Research Center


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      • Cover title.Shipping list no.: 1990-0860-M.Distributed to depository libraries in microfiche.March 1990.Includes bibliographical references (p. 7).Also available via Internet from the NTRS web site. Address as of 5/1/06: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19900010777%5F1990010777.pdf; current access is available via PURL.Microfiche. [Washington, D.C. : National Aeronautics and Space Administration], 1990. 1 microfiche : negative ; 11 x 15 cm.

        StatementNational Aeronautics and Space Administration, Langley Research Center
        PublishersNational Aeronautics and Space Administration, Langley Research Center
        Classifications
        LC Classifications1990
        The Physical Object
        Paginationxvi, 104 p. :
        Number of Pages62
        ID Numbers
        ISBN 10nodata
        Series
        1
        2NASA technical memorandum -- 102618.
        3

        nodata File Size: 9MB.


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Digital-flutter-suppression-system investigations for the active flexible wing wind-tunnel model by National Aeronautics and Space Administration, Langley Research Center Download PDF EPUB FB2


Off-line aerodynamic simulations may be required to estimate the impact of the difference between the actual and the desired shape on the achieved aerodynamic performance and reduced fuel consumption.

200 3000 120 flange Steel The adaptive leading edge consisted of a massive and highly deformable fiberglass skin connected to stiff ribs which produced an established form and maintained it under the action of external forces. The process developed for the morphing wing trailing edge model control is illustrated in Fig.

Early predictions for the VCCTEF state benefits up to 9. To increase the adhesion strength between the silicone and metal interface, the metal profiles were degreased and primered with an adhesion promoter for platinum catalyzed silicones. A special mention could be given to the elastic polymeric element which linked the small flap to the main structure [11].

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The materials studied at Virginia Polytechnic were thermoplastic polyurethanes, copolyester elastomers, shape memory polymers and a variety of woven materials Kikuta, 2003.

" ADAMan Aeroservoelastic Analysis Method for Analog or Digital Systems' ' Journal. Monner published the concept of the adaptive wing project in 1998 [30]. This function also depends upon the main acceleration parameter restrictions like the acceleration function trapezium, sinusoidal, or jerk-free ramp, etc. Apparently this seems a paradox in force of the conflicting design requirements. The Wright brothers used French sateen fabric, and NASA has used carbon-reinforced plastic skins on the F-111 MAW and the F-18 AEW.

In the same way as before, two fairings were installed on the prototype to preserve the geometrical continuity. As a reference application, the controller design workflow is described considering its use for a novel variable wing camber trailing edge control.

the costs with reference to both the direct and the maintenance expense ;• The desired properties of the skin are dependent on whether the skin is an integral component of the aircraft structure, as with the NASA aircraft, or just a smooth fairing material. Numerous studies are currently being done on the application of micro- electro-mechanical systems MEMS flaps, which can be much like the scales on a fish or the feathers of a bird.

Gern, in2001 Smart Wing Technology Traditionally, aircraft designers attempted to avoid aeroelastic instabilities by increasing structural stiffness. An adaptive wing may be made of several elements, depending on the objectives of the system.