A numerical procedure for the determination of stresses and deformations in cantilevered thin-wall aircraft lifting surfaces under a varying in time load is generalized to take into account the motion of the structure in the aircraft systems as a whole. It was assumed that the aircraft was located in a subsonic compressible flow. Equations of its perturbed motion were derived, only taking into account deformations of its lifting surfaces. External non-stationary aerodynamic loads on deformable lifting surfaces and on a non-deformable aircraft body were determined using the discrete vortex method. The set of equations for deriving parameters of dynamic stress-strain state of aircraft lifting surfaces, of displacements of an aircraft as a whole and of a non-stationary dynamic load consisted of three groups of equations describing the dynamic reaction of the aircraft. Initial conditions for solving these equations are presented.
Aircraft Dynamic Response Calculation Based on Discrete-Continual Model. Abstract Only
1987
1 pages
Report
Keine Angabe
Englisch