Date: Thursday, April 7, 2011
Speaker: Dr Krzysztof Sibilski, Professor of Aerospace Engineering, Wroclaw University of Technology.
Time: 13:00
Place: Carleton University, Department of Mechanical and Aerospace Engineering, 1125 Colonel By Drive, Mackenzie Bldg., Room 3124 ME
Parking: Please use University visitor’s parking
Information: Please contact Professor J. Z. Sasiadek at jsas@connect.carleton.ca for more information
Organized By: IEEE Robotics and Automation Society (RAS) and IEEE Control Systems Society (CSS) Joint Chapter and Department of Mechanical and Aerospace Engineering, Carleton University

Abstract: In the background of preparing this lecture lies our believe that transferring ideas from the more matured discipline like aircraft technology to emerging “animal” like technology should be beneficial for the later one and vice-versa. One common idea, of special interest to both disciplines, is an active, flexible wing concept. This concept represents a return to the Wright Brothers’ idea of wing warping or twisting by combining wing structures and flight controls to perform the desired manoeuvres. It is well known that the dynamics of very small flying vehicles (Nano-Aerial Vehicles – or Entomopter) within the flight envelope is highly nonlinear. The characteristics of the loads acting on Nano Aerial Vehicles (NAV), particularly aerodynamics, vary substantially over the angle of attack operating range (which may include post-stall incidences). Control of this type of plant can be achieved adequately via variety of approaches, provided that the parameters of the controller (and its gains in particular) are scheduled according to flight conditions. The nonlinearity of the system makes it difficult to implement a strategy of interpolating between gains derived from a few trim points available. This is because interactions between the plant and the controller are very complex. It is not known precisely what the closed loop trim points are in broad flight regions. The aerodynamic load often becomes asymmetric and resultant inertial coupling is significant. This presentation shows aeroelastic analysis for a flexible wing with an imposed harmonic flapping motion about the root chord of the wing. An algorithm and related computer code based on the analysis were developed. This software was used to find average aerodynamic loads, control forces and moments. It was also used in simulation of controlled flying vehicle motion.