Abstract
Air speed, angle of sideslip and angle of attack are fundamental aerodynamic parameters for controlling most aircraft. For small aircraft for which conventional detecting devices are too bulky and heavy to be utilized, a novel and practical methodology by which the aerodynamic parameters are inferred using a micro hot-film flow sensor array mounted on the surface of the wing is proposed. A back-propagation neural network is used to model the coupling relationship between readings of the sensor array and aerodynamic parameters. Two different sensor arrangements are tested in wind tunnel experiments and dependence of the system performance on the sensor arrangement is analyzed.
Highlights
Small unmanned air vehicles (UAVs) and micro air vehicles (MAVs) are attracting growing interest for their multi-purpose applications [1]
We propose the use of a micro hot-film flow sensor array and a back-propagation (BP) neural network to deduce three aerodynamic parameters: air speed, angle of attack and angle of sideslip
A novel and practical methodology for detecting aerodynamic flight parameters using a micro hot film flow sensor array and neural network-based data fusion technology is proposed in this paper
Summary
Small unmanned air vehicles (UAVs) and micro air vehicles (MAVs) are attracting growing interest for their multi-purpose applications [1]. They suffer from certain particular characteristics such as small Reynolds number, low inertia, low flight speed, rolling instability and so on [2], which cause flight instability and make them highly prone to wind. To improve the performance of MAVs/UAVs, their aerodynamic parameters need to be introduced into flying control systems, as complementary information to inertial guiding systems and auto pilots. What’s more, installing more than one device, especially distributing sensors on flapping wings or flexible membrane wings for detecting multiple aerodynamic parameters, calls for more space, power and payload which can hardly be afforded by small aircrafts. The method described in [7] required a hemispherical nose installed on the aircraft, which limited its application
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