Research projects at the Flight Dynamics Division focus on multidisciplinary aspects of flight, involving aerodynamics, structural response of flexible aircraft and control system properties. Numerical modeling is routinely augmented by specialized wind tunnel experiments to investigate critical aspects of the problem at hand.
Control of Tailless Aircraft
Flying wings, or tailless aircraft, can be designed to have very low radar signature. The particular shape, and especially the absence of a vertical tail, require rather unconventional concepts to ensure that the aircraft is laterally controllable in all flight conditions.
Robust Flutter Analysis for Certification
Within the framework of the Swedish Aeronautics Research Program (NFFP 5), the mu-p flutter solution method developed by Dan Borglund will be made suitable for industrial applications. The primary goal of this research is to enable industry to efficiently handle modeling uncertainties, such as variation of component weights or certain aerodynamic modeling inaccuracies, in a robust manner. This project is conducted in collaboration with Saab Aerosystems.
Flight Loads from Simulation
The intention of this project is to extend flight simulation models with additional states representing structural deformations. Using the time history results obtained from the simulation, aerodynamic and inertial loads acting on the structure can then be reconstructed for every instant of the flight simulated. This project is conducted in collaboration with Saab Aerosystems.
Recently Concluded Work
Improving the Efficiency of Flight using Optimization
Optimization is used to improve the performance of aircraft, with a focus on operating current generation aircraft more efficiently rather than designing new aircraft. Real-time minimization of measured drag and aircraft trajectory optimization are used to increase efficiency. Suitable optimization methods are implemented and evaluated on different problem formulations.
Aeroelastic Concepts for Flexible Aircraft Structures
In this thesis, aeroelastic concepts for increased aircraft performance are developed and evaluated. Active aeroelastic concepts are in focus as well as robust analysis methods aiming at efficient analysis using numerical models with uncertain or varying model parameters.
Design and Testing of Flexible Aircraft Structures
Methods for structural design, control, and testing of flexible aircraft structures are considered. Focus is on nonconventional aircraft con-figurations and control concepts. The interaction between analysis and testing is a central topic, and all studies include validation testing and comparison between computational and experimental results.