Abstract:
This Report presents a matrix formulation of a method which employs influence coefficients to solve static aeroelastic problems. Linear structural characteristics are assumed and the aerodynamic loading, including that due to elastic deformation, is assumed to be compounded from a linear combination of 'elementary' distributions. Details of the method are here considered only for symmetric flight cases, though in essence it is universally applicable. The method has been applied to a 'Concorde'-like supersonic transport aircraft in symmetric flight at M = 2.2. Linearised supersonic theory has been used to derive the load due to elastic deformation. Results are presented for the incidences and elevator angles to trim and to sustain quasi-steady manoeuvres, for the longitudinal distributions of shear force and bending moment, and for the elastic deformation acquired. The potentialities of the method are considered sufficient to justify the expenditure of the further effort which is necessary to develop it into a fully automated design procedure of wide applicability.
