Research of elastic-deformed state Hard and light wings of great loading

Due to the growth of economic requirements for modern aircraft, the parameter of the aerodynamic range Kmax • M, where Kmax is the maximum aerodynamic quality of the airplane, has become especially relevant, M is the flight speed relative to the speed of sound. The increase in the aerodynamic range at the expense of M for modern aircraft of the transport category is problematic because the flight speed reaches M = 0,7 ÷ 0,9, and the increase due to Kmax became possible due to an increase in the lengthening of the wing λ or a decrease in its swept angle χ.Under load, the wing deforms and the nature of the load distribution changes along the width of the wing. Such a phenomenon of static aeroelasticity (SA) leads to a decrease or increase in the existing bending and twisting moments of the wing, especially in the case of swept wings (λ ≥ 8). Therefore, the reliability of the determination of external loads, taking into account the influence of static aeroelasticity, is important. Load is the input parameters for calculation of strength, analysis of elastic-deformed state (EDS) of the design and forecasting its weight efficiency.Taking into account the effects of static aeroelasticity reduces the external load in some sections by wings up to 14%. The comparison of relative moment’s shows that the value of the bending moment coincides with the bending moment obtained from the experimental data.The method of aerodynamic influence coefficients (AIC) has a significant advantage over other methods, which is that a once-defined matrix of aerodynamic influence coefficients can be used in different load scenarios. This reduces the time spent on the calculations and eliminates the need for repeated experiments.