Abstract The vibration characteristics of a rigid-flexible coupling spacecraft with double-direction hinged solar arrays are studied. The Kirchhoff plate theory is adopted to derive the governing equations. The Chebyshev polynomials are introduced as admissible functions to construct the dynamic model of each solar panel. The Lagrange multiplier method is employed to describe the continuity conditions of the flexible hinges. The Rayleigh-Ritz method is used to obtain the natural frequencies and rigid-flexible coupling global mode shapes. The validity of the present method is verified by comparing with the ANSYS results. Then, detailed studies are carried out to illustrate the effects of the inertia moment of the central rigid body, hinges stiffness, and aspect ratio of solar panels on the natural frequencies and mode shapes of the spacecraft. The results demonstrate that there exist a series of frequency veering and mode shift phenomena due to the variation of inertia moment, hinges stiffness, and aspect ratio. The inertia moment of the central rigid body plays a significant role in the attitude motion of the central rigid body. Finally, the mode localization factor is introduced to compare the mode localization degrees of three types of spacecraft. Results reveal that the longer the length of chord-wise direction solar panels, the more severe mode localization degree.

    Highlights The dynamical model of rigid-flexible coupling spacecraft with double-direction hinged solar arrays is established. Improved continuity conditions for the flexible hinges are proposed. Effect of inertia moment of central rigid body is revealed. The mode localization, frequency veering, and mode shift phenomena are discovered.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Vibration characteristics analysis of rigid-flexible spacecraft with double-direction hinged solar arrays


    Beteiligte:
    Xing, Wu Ce (Autor:in) / Wang, Yan Qing (Autor:in)

    Erschienen in:

    Acta Astronautica ; 193 ; 454-468


    Erscheinungsdatum :

    2022-01-24


    Format / Umfang :

    15 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    General Hinged Rigid-Body Dynamics Approximating First-Order Spacecraft Solar Panel Flexing

    Allard, Cody / Schaub, Hanspeter / Piggott, Scott | AIAA | 2018


    Rigid-Flexible Coupling Dynamic Analysis of Flexible Spacecraft

    Wang, Jie / Li, Dong-Xu | Springer Verlag | 2021


    Passive spacecraft solar wing flexible vibration suppression device and spacecraft

    DONG YAOHAI / LI HAO / JIANG SHICHEN et al. | Europäisches Patentamt | 2023

    Freier Zugriff

    Motion of Spinning Spacecraft with Hinged Appendages

    Sellappan, R. / Bainum, P.M. | AIAA | 1977


    HINGED JOINT DRIVE FOR DEPLOYMENT OF SOLAR PANELS OR SPACECRAFT ANTENNAE

    NEMCHANINOV STANISLAV IGOREVICH / PARAFEJNIK VALENTIN IVANOVICH | Europäisches Patentamt | 2019

    Freier Zugriff