E-Books →Active Spanwise Lift Control A Distributed Parameter Approach

In the work herein, the unsteady aerodynamics of a finite wing featuring multiple trailing edge flaps is modeled using the Unsteady Vortex Lattice Method (UVLM), yielding a linear, time-invariant, high-order state-space model. An Eigensystem Realization Algorithm (ERA) is applied for model-order reduction and modal identification, providing aerodynamic mode shapes and associated eigenvalues. By representing the system output (lift distribution) as a truncated superposition of aerodynamic mode shapes, a low-order MIMO modal representation is obtained, suitable for controller synthesis. This methodology is used to synthesize regulators, to suppress gust disturbances in lift distribution, and trackers, to dynamically follow any desired reference lift profile. A special observer structure decouples the gust input from the state estimation process and provides estimates for the gust amplitude along time, thus rendering the gust measurements ahead of the aircraft unnecessary.
Contents
Preface
Chapter 1: Introduction
Chapter 2: Unsteady Aerodynamic Modeling of a Multiflap Wing
Chapter 3: Review of Model Order Reduction Methods
Chapter 4: Modal Identification of Aerodynamic Systems
Chapter 5: Spatial Control of Spanwise Lift Distribution