SUPERSONIC AEROELASTIC EFFECTS ON STATIC STABILITY AND CONTROL PARTⅢ. AEROELASTIC INTERACTION

摘要

Static aeroelastic interaction equations are derived in matrix form for wing-aileron lifting surfaces, considering the wing and aileron being independently flexible, and the wing and aileron as a single structural assemblage. The equations are stated in general form so as to accept inputs in the form of aerodynamic and structural deformation influence coefficient matrices. Closed form and series solutions for the equations are presented. Prom these solutions expressions are developed for the flexible to rigid ratios of lifting pressure, span loadings, and aerodynamic center locations. Matrix expressions for the flexible to rigid ratio of pertinent derivatives demonstrate the effects of flexibility on stability and control. Inertia effects are also included. Sample problems illustrate the use of the derived equations in an aeroelastic analy¬sis.