This paper describes the design and development of a feedback system for controlling the dynamics of a flapping wing nano air vehcile (NAV). A model of the vehicle dynamics and models of sensors and unique actuator mechanisms are built. An extended Kalman filter is designed to eliminate the effects of sensor bias on state estimation. Results of this study demonstrate stability and yield responses that are approaching desired performance capabilities. ...
The goal of this project is to develop a Nano Air Vehicle (NAV) with a wing span of 7.5 cm. The computational fluid dynamics study is focused on the aerodynamic efficiency of the wings. The primary focus of the computational study is on the aerodynamic performance of the wings in order to obtain a near optimal kinematics of the wing while the NAV is in a hover mode. The secondary ...
A space-time correlation function method is applied to the analysis of Large Eddy Simulation (LES) unsteady ship airwake data computed for the LPD 17. Correlation functions are computed for potentially dangerous velocity bursting events visually tracked in space and time in the air vehicle landing zone. It is shown that a correlation function approach is of potential value but the usefulness of the approach is very sensitive to the knowledge, ...
A two-camera system was devised and created to determine the kinematics of flapping fin and flapping wing vehicles. Each camera is set up to capture triggered, high-speed (up to 10,000 frames per second) images of the appendage in a test environment. Using direct linear transforms, each camera is calibrated to convert image coordinates to an alternate coordinate system. Points of interest on the appendage are selected from each camera image ...
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