Multi-model convex design of a scheduled lateral feedforward control law for a large flexible BWB aircraft

An ℋ∞full information approach for the feedforward controller design of a large blended wing body flexible aircraft

“…Moreover, the maximum manoeuvre loads can be directly determined. The validation models considered here describe a representative set of grid point models taken equally distributed from the envelope according to (7). In Fig.…”

“…Comparison of maximum and minimum cut moments My (a) and Fz (b) over all cut positions along the wing and over the §ight envelope according to (7) for various validation cases: 1 ¡ G d ; 2 ¡ Gu; 3 ¡ MpK fb ; 4 ¡ MnK fb ; 5 ¡ Mp2DOF; and 6 ¡ Mn2DOF. Solid curves refer to maximum and dashed to minimum loads However, a comparison of the maximum loads caused by manoeuvre and gust gives information which of those external excitations determines the structural sizing loads.…”

“…All these speci¦cations have to be ful¦lled over the considered §ight envelope according to (7). The performance of designed controllers has to be demonstrated together with an appropriate feedback control law on a high-order validation model including nonlinear actuator dynamics and corresponding rate and saturation limits.…”

“…Thereby, signi¦cant reductions of loads and vibrations are obtained. In [7], a multimodel feedforward design approach is shown. Design speci¦cations concerning manoeuvre load reduction and command tracking are addressed.…”

“…Two further convex synthesis approaches for lateral control of a BWB type §exible aircraft are presented in [7,8]. In [8], the focus is on a robust multiobjective feedback design, considering both time-and frequency-domain speci¦cations.…”