In this paper an adaptive control system for a passenger aircraft with active high-lift system is presented. Failures in the high-lift system parts of such aircraft are critical and consequently need to be handled automatically. An adaptive controller is proposed which consists of incremental nonlinear dynamic inversion (INDI) with a reference model and linear controller. As the INDI is adaptive against uncertainties or system failures, no additional adaptive element like a neural network is needed. The implementation of the INDI requires a nonlinear system model which is permanently linearized during the runtime in order to obtain the current input matrix which here basically consists of the control surfaces effectiveness. It also requires feedback of the translational and rotational acceleration measurements which usually suffer from noise. In order to test the adaptivity of the INDI, a partial failure of the high-lift system during the landing approach is regarded. It shows that the INDI is capable of compensating the error by only using the conventional control surfaces. * Research Associate, Ph.D. Student, y.beyer@tu-bs.de. † Research Associate, Ph.D. Student, a.kuzolap@tu-bs.de. ‡ Senior Researcher, m.steen@tu-bs.de. § Research Scientist, jobst.diekmann@dlr.de. ¶ Scientific Advisor, nicolas.fezans@dlr.de Downloaded by Yasim Hasan on July 12, 2018 | http://arc.aiaa.org |

Gust load alleviation (GLA) can reduce the maximum loads encountered by airplanes, allowing the structure to be designed lighter, thus saving fuel. Active GLA therefore represents an important subarea in the research of energy-efficient passenger airplanes. However, from a flight dynamics perspective, there are no publicly available simulation environments that allow for an efficient and modular investigation of different technologies like novel GLA controllers or novel flow actuators. Therefore, this paper presents such a simulation environment. The presented aeroelastic flight dynamics model is based on indicial functions combined with a dynamic stall model to predict the unsteady aerodynamics similar to a strip theory approach, while the downwash is considered using a nonlinear steady lifting line method. The structural dynamics are based on the mode displacement method and coupled with the aerodynamics model using constant transformation matrices as well as nonlinear transformations for the inflow. A comparison of the presented model with unsteady Reynolds-Averaged Navier-Stokes simulations shows good agreement for a selected gust case. The presented simulation model is parameterized as an energy-efficient passenger airplane with a light-weight wing sizing by reducing the limit loads from 2.5 g to 2.0 g for equivalent pull-up maneuvers. Open-loop gust load envelopes are presented and discussed for the energy-efficient airplane with different model settings, e.g. with and without dynamic stall model. The source code of the simulation modules is available at: https://github.com/iff-gsc/se2a_aviation_2023.

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