The present method for strength and stability analyses of stiffened, fiber-reinforced composite panels to be used in hypersonic vehicle structures is of great generality, and can be linked with planar finite-element analysis (FEA). Nonlinear temperature and load-dependent material data for each laminate are used to 'build-up' the stiffened panel's membrane, bending, and membrane-bending coupling stiffness terms, as well as thermal coefficients. The resulting, FEA-solved thermomechanical forces and moments are used to calculate strain at any location in the panel; this allows an effective ply-by-ply orthotropic strength analysis to be conducted, together with orthotropic instability checks for each laminated segment of the cross-section.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Structural analysis and sizing of stiffened, metal matrix composite panels for hypersonic vehicles


    Contributors:

    Conference:

    AIAA, International Aerospace Planes Conference ; 1992 ; Orlando, FL, United States


    Publication date :

    1992-12-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English