Stateczność boczna samolotu i drgania lotek z uwzględnieniem odkształcalności giętnej skrzydeł i sprężystości układu sterowania

The paper deals with the effect of rigidity and damping of control system and the effect of aileron static trim degree on the lateral stability of a plane and aileron vibrations. The plane was considered as an ideally rigid mechanical system with flexibly deformable wings and movable ailerons. The equations of motion in quasi-coordinates were written using Boltzmann-Hamel equations for the system with holonomic constraints. Five degrees of freedom were considered, i.e. three degrees of freedom of a plane as a rigid body: rolling, yawing and sideslip and anti-symmetrical flexible wing deformation and elastic aileron displacement. After the equation system linearization the solution was reduced to finding the eigenvectors and the corresponding eigenvalues of the state matrix.