Wing in ground effect vehicle: modelling and control

Ghafoor, Abdul
The “Ground Effect” is the increase in the force which is acting on a lifting surface like wing, when it come to the close proximity of the ground. Ground effect vehicles (GEV) are the kind of amphibious vehicles that fly in close proximity of ground, making use of the aerodynamic interaction between the wings of the ground effect vehicle and ground (Sea or Earth surface) and it increases their efficiency 3-4 times more. There are many other advantages of the vehicles employing GE; they do not require a take-off/landing place, they can land anywhere in case of malfunctioning, they can be constructed in a variety of sizes for both military and civil purposes. This study includes a detailed study of Ground Effect (GE), its implementation using Wing in Ground (WIG) effect vehicle or Ground Effect Vehicle (GEV). Next, this thesis report includes its mathematical model explaining GE, motion, translational and rotational dynamics and kinematics, aerodynamics, gravity, atmospheric, mass inertia, forces and moments. Nonlinear 6DOF dynamical model is implemented in Matlab/Simulink and its response is investigated in open loop simulations. Next step is to develop and implement its autopilot. Autopilot consists of a controller and a guidance unit, to get a vehicle to a destination by following a desired trajectory. For the controller, PID controllers from classical feedback theory are used for controlling pitch, yaw, roll, altitude and speed. Their performances are compared based on simulation studies. Final part is the guidance, which is done for the yaw plane (Heading) using Line Of Sight (LOS) method, through Way Points (WPs). Major challenges during this work are the lack of available technical data and the need for multidisciplinary skills like aerodynamics, mathematical modeling and finding suitable controller design techniques.


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© 2022 Elsevier Masson SASIn this paper, the effect of ground on aerodynamics and longitudinal static stability of a non-slender delta wing with sweep angle of 45 degree and thickness-to-chord ratio (t/c) of 5.9% was characterized at Reynolds number of 9×104 in a low-speed wind tunnel using force and pressure measurements. The measurements were conducted for angles of attack varying between 0≤α≤30 degrees and non-dimensional heights between 3%≤h/c≤107% and height stability of the wing based on aerodynamic c...
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Citation Formats
A. Ghafoor, “Wing in ground effect vehicle: modelling and control,” M.S. - Master of Science, Middle East Technical University, 2015.