41–50 of 118 hits
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    BUCKLING OF ULTRALIGHT LADDER-TYPE COILABLE SPACE STRUCTURES

    Royer, Fabien / Pellegrino, Sergio | TIBKAT | 2020

    Closed-loop vibration control experiments on a rotor with blade mounted actuation

    Prechtl, E.F. / Hall, S.R. | Tema Archive | 2000
    A Mach-scaled CH-47 model rotor blade with an actively controlled servo-flap near the tip was designed, manufactured, and tested. The servo ...
    Publisher: American Institute of Aeronautics and Astronautics (AIAA) , Reston

    Corrosion prediction in aging aircraft materials using neural networks

    Bailey, R.A. / Pidaparti, R.M. / Jayanti, S. et al. | Tema Archive | 2000
    exposed to two corrosive environments. Given the corrosion environment and time of exposure the first neural network predicts the ASTM G34 ...
    Publisher: American Institute of Aeronautics and Astronautics (AIAA) , Reston

    Damage tolerance of cracked cylindrical shells under internal pressure

    Hoogkamer, D. / Waas, A.M. / Arbocz, J. | Tema Archive | 2000
    centralized cracks at angles to the shell generators ranging from 0 degree to 90 degree at an interval of 15 degree and of various crack length, are ...
    Publisher: American Institute of Aeronautics and Astronautics (AIAA) , Reston

    Damage tolerance of fiber composite airfoils with piezoelectric adaptive control system

    Minnetyan, L. / Chamis, C.C. / Abdi, F. | Tema Archive | 2000
    . Progressive damage and fracture of a laminated composite airfoil subjected to external pressure loading and adaptive control stresses is evaluated via ...
    Publisher: American Institute of Aeronautics and Astronautics (AIAA) , Reston

    DEPLOYMENT DYNAMIC ANALYSIS OF A SPACE STRUCTURE

    Luo, Haiyang / Wu, Tanhui / Hou, Yangqing et al. | TIBKAT | 2021

    DEPLOYMENT DYNAMICS OF FOLDABLE THIN SHELL SPACE STRUCTURES

    Pedivellano, Antonio / Pellegrino, Sergio | TIBKAT | 2021

    Design and experimental testing of an induced-shear piezoelectric actuator for rotor blade trailing edge flaps

    Centolanza, L.R. / Smith, E.C. | Tema Archive | 2000
    deflection and hinge moment. A finite element model of the actuator tube and trailing edge flap is used to compare the performance of the new tube ...
    Publisher: American Institute of Aeronautics and Astronautics (AIAA) , Reston