The Influence of Aeroelasticity on the Longitudinal Stability of a Swept Wing Subsonic Transport Aircraft

摘要

A numerical treatment of the influence of the aeroelastic deformations on the longitudinal stability and control characteristics of an aircraft with a swept-back wing of large aspect ratio is carried out for the sub-critical speed range. Only the deformation of the wing and the bending of the fuselage were taken into consideration. The method used to calculate the deformations of the wing is based on the superposition of a number of preselected load distributions. An investigation of the accuracy of the method was made by comparing the numerical results with those of another more exact method which proved the reliability of the present method. As a result of the study it was found that the stability and control of the aircraft are only slightly affected by the aeroelastic deformation. (Author)