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2 Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

2 1999

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The application of nonlinear inverse dynamics for aircraft control at high angles of attack

Złocka M.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

1999

nr 9

179-184

The main objective of this work is the elimination of the wing-rock phenomenon during the aircraft motion at high angles of attack. Two wing-rock models having three or one degree of freedom are considered. In the paper, the nonlinear control laws have been synthesised for stabilization of the steady horizontal motion of the aircraft. The synthesis is based on the nonlinear inverse dynamics. As an example the numerical simulation of the controlled motion is carried out employing the aerodynamic and mass data of the F-16 aircraft.

A comparison of center-manifold reduction of nonlinear integro-differential flutter equation and approximate set of ordinary differential equations

Grzędziński J.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

1999

nr 9

7-14

A nonlinear integro-differential flutter equation of a thin airfoil placed in an incompressible flow is solved by two different methods. The first method involves the center-manifold reduction and gives the asymptotic limit cycle amplitude and frequency in terms of power series expansions. The second method replaces the integro-differential equation by an approximate set of first-order ordinary differential equations which are solved by using bifurcation and continuation software package. A comparison of these two methods shows that the domain of a good agreement between them varies significantly depending on the parameters of the problem.