Wing-In-Ground Effect Flight Control: New Role of Automatic Systems

A numerical-based (Reynolds-averaged Navier–Stokes (RANS)) investigation into the role of span and wing angle in determining the performance of an inverted wing in ground effect located forward of a wheel is described, using a generic simplified wheel and NACA 4412 geometry. The complex interactions between the wing and wheel flow structures are investigated to explain either increases or decreases for the downforce and drag produced by the wing and wheel when compared to the equivalent body in isolation. Geometries that allowed the strongest primary wing vortex to pass along the inner face of the wheel resulted in the most significant reductions in lift and drag for the wheel. As a result, the wing span and angle combination that would produce the most downforce, or least drag, in the presence of the wheel does not coincide with what would be assumed if the two bodies were considered only in isolation demonstrating the significance of optimizing these two bodies in unison.

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Wing-in-Ground Effect Vehicles Flight Automatic Control Systems Development Problems

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.629.370 ◽

2014 ◽

Vol 629 ◽

pp. 370-375 ◽

Cited By ~ 2

Author(s):

Alexander Nebylov ◽

Vladimir Nebylov

Keyword(s):

Control Systems ◽

Motion Control ◽

Flight Control ◽

Ground Effect ◽

Operational Performance ◽

Free Flight ◽

Automatic Control Systems ◽

Low Altitude ◽

New Criteria ◽

Wing In Ground Effect

The Wing-in-Ground Effect vehicles (WIG-craft, Wingships) or Ekranoplanes as they are called in Russia are developing in several countries and the problem of perfect flight control is very important for these vehicles' successful application either for commercial or military. An accident-free flight at very low altitude above the rough underlying surface, mainly above the disturbed sea surface, and also take-off and landing require special systems of motion control that are different from those used on planes. The requirements for such motion control systems and the new criteria for their improvement are offered. The aim of this investigation is to define the way for operational performance improvement of the vehicles of advanced design. The experience and achievements in this field of high technology are described.

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Wing in Ground Effect Aircraft: An Airlifter of the Future

10.21236/ada430859 ◽

2001 ◽

Author(s):

Norman J. Leonard ◽

III

Keyword(s):

Ground Effect ◽

The Future ◽

Wing In Ground Effect

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Robust fault-tolerant flight control of quadrotor against faults in multiple motors

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410021999547 ◽

2021 ◽

pp. 095441002199954

Author(s):

Dinesh D Dhadekar ◽

S E Talole

Keyword(s):

Flight Control ◽

Tracking Control ◽

Fault Tolerant ◽

External Disturbances ◽

Detection And Identification ◽

Attitude Tracking ◽

Fault Detection And Identification ◽

Attitude Tracking Control ◽

Disturbance Estimator

In this article, position and attitude tracking control of the quadrotor subject to complex nonlinearities, input couplings, aerodynamic uncertainties, and external disturbances coupled with faults in multiple motors is investigated. A robustified nonlinear dynamic inversion (NDI)-based fault-tolerant control (FTC) scheme is proposed for the purpose. The proposed scheme is not only robust against aforementioned nonlinearities, disturbances, and uncertainties but also tolerant to unexpected occurrence of faults in multiple motors. The proposed scheme employs uncertainty and disturbance estimator (UDE) technique to robustify the NDI-based controller by providing estimate of the lumped disturbance, thereby enabling rejection of the same. In addition, the UDE also plays the role of fault detection and identification module. The effectiveness and benefits of the proposed design are confirmed through 6-DOF simulations and experimentation on a 3-DOF Hover platform.

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