During the process of span extension for an aircraft wing equipped with a telescopic morphing mechanism, the wing aspect ratio increases, and hence, the geometrical nonlinearities might become more significant. In this regard, this paper aims to investigate the effect of structural nonlinearity on the aeroelasticity of span morphing wings using the exact fully intrinsic equations for the first time. Furthermore, the effects of various parameters such as thrust force, engine location, chord size, flight altitude, initial angle of attack, and overlapping mass on the aeroelasticity of the wing are studied. The applied aerodynamic loads in an incompressible flow regime are determined using Peters’ unsteady aerodynamic model. In order to check the stability of the system, first the resulting nonlinear partial differential equations are discretized by using the central finite difference method and then linearized about the static equilibrium. Finally, by obtaining the eigenvalues of the linearized system, the stability of the wing is evaluated. It is observed that by using the fully intrinsic equations, the instability of the axially moving telescopic wing can be determined more accurately. Moreover, the results show that the morphing length and overlapping mass have significant effects on the aeroelastic stability of the telescopic wing.
In this paper, the flutter instability of a conventional two-stage axially moving telescopic UAV wing is investigated. To this aim, and to be as close as possible to the reality, the effects of temporal variation of mass and length, due to the movement of stages and their overlapping, along with the effects of morphing speed are considered for the first time. The bending-torsional dynamics of the two-stage wing is modeled by modifying the Euler–Bernoulli beam theory to take into account the effects of morphing speed and variations of mass and length. Furthermore, the aerodynamic loads are simulated using Peters' unsteady aerodynamic model. The governing aeroelastic equations are discretized using a finite element approach, and a length-based stability analysis is proposed to investigate the aeroelasticity of the wing. The obtained results are compared with those available in the literature, and a good agreement is observed. It is found that the aeroelastic stability of a telescopic wing is more sensitive to the fixed part parameters than the moving part. Also, it is shown that the wing critical length is sensitive to the morphing speed. Therefore, by selecting the telescopic wing morphing parameters properly, the aeroelastic stability of the system can significantly be improved.
In this paper, the aeroelastic instability of folding wings by using the geometrically exact fully intrinsic beam equations is investigated. The important advantages of these equations in comparison with other structural beam equations are complete modeling without simplifying assumptions in large deformations, low-order nonlinearities, and thus less complexity. For the first time, folding angles have been implemented in the geometrically exact fully intrinsic beam equations and hence this is the main novelty of this study. The applied aerodynamic loads in an incompressible flow regime are determined using Peter’s unsteady aerodynamic model. In order to check the stability of the system, first the resulting non-linear partial differential equations are discretized by employing the central finite difference method, and then linearized about the nonlinear steady-state condition. By obtaining the eigenvalues of the linearized system, the stability of the wing is evaluated. Furthermore, investigation of the effects of some important parameters such as stiffness ratio and length ratio on the flutter speed of the folding wing for various folding angles, is another achievement of this study. It is observed that the geometrically exact fully intrinsic beam equations can model the folding angles for the aeroelastic analysis more accurately and the capabilities of these equations became more specific.
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