Chaotic time-delay systems are attractive candidates to generate chaotic dynamics because of their relatively simple system model. The circuit realization of the time-delay part is the main drawback of these systems. In order to overcome this drawback, a chaotic time-delay system which features a binary feedback function is presented. The use of binary feedback function results in a considerably simplified implementation of the time-delay unit based on using a flip-flop chain. Modeling the system thus obtained yields a chaotic sampled-data system. The existence of chaotic dynamics in the introduced sampled-data systems is numerically verified by calculating system Lyapunov exponents and applying a detailed bifurcation analysis. The chaotic attractor of the introduced sampled-data system is verified by the circuit realization of the system. In order to minimize the number of flip-flops in the chain while keeping the system in chaos, the spectrum of Lyapunov exponent versus clock frequency of the flip-flops and a bifurcation parameter is computed. The circuit realization of the introduced sampled-data system includes a relatively simple structure compared to other chaotic time-delay systems and this overcomes the complexity of the circuit implementation of the time-delay block.

No abstract

No abstract

No abstract

In this paper, we provide a system identification, model stitching and model-based flight control system design methodology for an agile maneuvering quadrotor micro aerial vehicle (MAV) technology demonstrator platform. The proposed MAV is designed to perform agile maneuvers in hover/low-speed and fast forward flight conditions in which significant changes in system dynamics are observed. As such, these significant changes result in considerable loss of performance and precision using classical hover or forward flight model based controller designs. To capture the changing dynamics, we consider an approach which is adapted from the full-scale manned aircraft and rotorcraft domain. Specifically, linear mathematical models of the MAV in hover and forward flight are obtained by using the frequency-domain system identification method and they are validated in time-domain. These point models are stitched with the trim data and quasi-nonlinear mathematical model is generated for simulation purposes. Identified linear models are used in a multi-objective optimization based flight control system design approach in which several handling quality specifications are used to optimize the controller parameters. Lateral reposition and longitudinal depart/abort mission task elements from ADS-33E-PRF are scaled-down by using kinematic scaling to evaluate the proposed flight control systems. Position hold, trajectory tracking and aggressiveness analysis are performed, Monte-Carlo simulations and actual flight test results are compared. The results show that the proposed methodology provides high precision and predictable maneuvering control capability over an extensive speed envelope in comparison to classical control techniques. Our current work focuses on i) extension of the flight envelope of the mathematical model and ii) improvement of agile maneuvering capability of the MAV.