Eigenstructure synthesis of an oblique wing flight control system

A flight control system design employing the recently developed linear control techniques of eigenstructure synthesis and command generator tracking is presented for an oblique wing fighter. The eigenvalues governing modal frequency and damping are developed such that the vehicle dynamics are compliant with MIL-F-8785c, "Flying Qualities of Piloted Aircraft."1 Eigenvectors are deterministically developed through output feedback in an attempt to achieve orthogonality, decoupling the symmetric and asymmetric modes of motion. The design is unique in that longitudinal and lateral/directional SAS are developed simultaneously using the same linear model. A simplified constrained controller is examined weighing complexity against performance, after which feed-forward gains are developed to translate desired pilot control to multisurface commands. For example, the NASA Oblique Wing Research Aircraft (OWRA) in transonic flight with the wing highly swept is presented as a demanding situation.