Nomenclature a, b, c, d, e, f = active control law parameters b = damping of aileron with actuation and additional regulator EPa = Young's modulus f, G, g,regulator force amplitude Hm = height k = stiffness of aileron with actuation and additional regulator kN:m −1 = spring constant mkg = mass m = mass of aileron with actuation and additional mass of regulator n1 = load factor ny1 = Poisson's ratio Rm = radius ts = time xm = aileron actuation rod deflection ym = spring deflection y 0 m = spring initial stretch

No abstract

This paper addresses a methodology for aeroelastic analysis of a light sport aircraft using experimentally gained data. It is focused on the aeroelastic analyses and related ground tests. The procedure is simple, fast, and low cost; however, it maintains a high standard regarding the quality and reliability of its results. It is applicable to the light aircraft category airworthiness standards, such as German standard LTF-UL, European standards CS-LSA and CS-VLA, and others. The procedure is based on a ground vibration test of the aircraft and measurements of the mass of control surfaces. Subsequent flutter analyses are based on the experimental data. The paper is focussed on the experimental and analytical tools and methodologies used. The entire process is demonstrated using the FM-250 ''Vampire II'' light sport aircraft as an example.

The paper is focused on the design and development of the system simulating nonlinear attachment of the aileron actuation on the aeroelastic demonstrator. The system is based on the concept of the digitally controlled additional stiffness, activated by the real time control law system, controlling the required ratio of the force and deformation. The solution is based on the electromagnetic exciter. The nonlinear force is simulated by means of the system of the exciter and the deformation sensor. The active control system is independent of the excitation system. It adds the force ensuring the required characteristics and it allows to simulate the additional stiffness, damping or mass. Doing this, it is possible to adjust the selected vibration mode by controlling the force and obtain the required nonlinear characteristics. In the second order, there is also a constant influence of the exciter mass, stiffness and damping. The simulation of the linear, quadratic and cubic additional stiffness were verified.

The article is focused on the design and development of the system simulating nonlinear attachment of the engine on the aeroelastic demonstrator. The aim is at obtaining the nonlinear (i.e., amplitude dependent) modal characteristics of the engine pitch vibration mode. Three mechanical concepts were tested to simulate the incremental stiffness characteristic of the engine pitch attachment. The nonlinear demonstrator is utilized for research and development of the advanced methods for the identification of nonlinear modal parameters.