13:30   Gust 3 Chair: Jonathan Cooper 13:30 30 mins Gust load alleviation efficiency in an optimized composite wing through the integration of wingtip devices: Incorporating folding and twist strategies Touraj Farsadi, Majid Ahmadi, Hamed Haddad Khodaparast Abstract: This paper introduces an advanced numerical approach aimed at designing and optimizing high aspect ratio composite wings with passive control systems, specifically employing folding and twist wingtip devices. The primary objective is to enhance gust load alleviation performance in a baseline wing configuration. Recent studies show potential benefits from incorporating spring devices and wingtip variations to improve gust load alleviation during flight. The baseline wing is developed using an extensive multi-disciplinary optimization framework, considering aerostructural constraints and leveraging the anisotropic properties of composite materials. The proposed methodology integrates Finite Element (FE) software, an in-house Reduced Order Model (ROM) framework for nonlinear aeroelastic analyses, and Particle Swarm Optimization (PSO). Implemented in the Nonlinear Aeroelastic Simulation Software (NAS2) package, this approach facilitates the streamlined design of composite wings with optimized aeroelastic and structural performance. The paper offers two main contributions: it presents a Multidisciplinary Design Optimization (MDO) approach for high aspect ratio composite wings and assesses the effectiveness of Folding and Twist wingtip devices in reducing gust load on the baseline wing, with a focus on the root bending moment. The paper initially showcases the MDO of high aspect ratio composite wings, leading to the development of a baseline wing model. This phase involves considering a range of factors such as structural, composite material, aeroelastic, and manufacturing constraints. The primary goal is to minimize the wing's weight while maximizing its twist factor. After the initial study of MDO, the research evaluates the effectiveness of folding and twist wingtip devices in reducing gust load on the baseline wing, with particular attention to the root bending moment as an interesting quantity. The incorporation of these devices at the end of the baseline wing facilitates a detailed comparison of gust responses between the baseline wing and the wing equipped with the Folding and Twist wingtip devices This research contributes a robust numerical methodology for the holistic design of composite wings, addressing key challenges in aerospace engineering. The systematic approach presented here, combining multi-disciplinary optimization and innovative wingtip devices, serves as a valuable tool for designing lightweight composite wings with improved aeroelastic and structural performance, thus advancing the field of high aspect ratio wing configurations in aerospace engineering. 14:00 30 mins Modelling complex actuator and sensor architectures for gust alleviation systems of flexible aircraft Stefanie Düssler, Thulasi Mylvaganam, Rafael Palacios Abstract: We propose a modular framework for designing and testing control systems for flexible air vehicles that may exhibit geometric nonlinearities and rigid/elastic couplings. This framework supports various controllers and levels of modeling fidelity. It can accurately model nonlinear aeroelastic effects and function as a model-in-the-loop using a network interface. We demonstrate its capabilities using an aircraft model with large wing deformations. A linear quadratic Gaussian controller is developed based on a linear reduced-order model derived from the aircraft’s cruise flight nonlinear equilibrium and designed for gust alleviation. In the design process, we observe substantial rigid/elastic coupling effects in the aircraft, which markedly impact the control design process. We also identify suitable actuator and sensor architectures with the sensor choice being depending on the nonlinear aeroelastic model characteristics. This controller is initially validated using a linear full-order model and then tested in a nonlinear simulation environment. While the controller fulfills the load alleviation and stabilization requirements, a reduced controller performance is observed with the higher-fidelity model in the loop necessitating a thorough reevaluation and adjustment of the control strategy in this computationally demanding setting. 14:30 30 mins Decentralized Control of Ailerons for Gust Load Alleviation Kolja Michel, Simon Schulz, Gertjan Looye, Guido Weber Abstract: This paper describes the design of a so-called decentralized gust load alleviation system for an aircraft with high aspect ratio wings. The system uses control loops at each individual aileron actuator that aim to reduce local structural dynamics at each respective point of installation in the wing structure. To this end, each actuator is equipped with a remote electronic unit that incorporates an inertial measurement unit and a processing unit that allows for implementation of a fast, local control loop that combines control surface positioning with local structural damping. At an aircraft level, this renders a decentralized control structure. Although the number of design degrees of freedom is lower than for a centralized system, over-all system complexity is considerably reduced. The presented design shows that remarkable improvement of structural damping and reduction of wing root bending moments can be achieved.

end %-->