Nonlinear Deformation and Stability of the GHS Technology Complex Flight Demonstrator Fuselage Compartment

Design of the Flying Vehicles Elements from Polymer Composite Materials


Аuthors

Zheleznov L. P.*, Laznenko A. S.**, Smirnov D. N.***

Siberian Aeronautical Research Institute named after S.A. Chaplygin, 21, Polzunov St., Novosibirsk, 630051, Russia

*e-mail: zgeleznov@sibnia.ru
**e-mail: laznenko.a@sibnia.ru
***e-mail: smirnovd@sibnia.ru

Abstract

Anisogrid mesh structures from composite materials, manufactured by the continuous winding method, became common use in the modern aircraft structures. In practice, anisogrid structures may be employed either as independent structures consisting only of reinforcements, or in conjunction with the skin. The latter is necessary for the aircraft fuselage structures to perceive internal overpressure. The fundamental contribution to the mesh composite structures development was made by the school of V.V. Vasiliev. Analytical estimates of the stress-strain state of a regular mesh shell with variation principle and momentless theory of shells, as well as the rib structure replacing with a conditionally continuous layer with averaged stiffness are adduced in the works of V.V. Vasiliev and V.A. Bunakov. A discrete approach to the mesh anisogrid structures modeling was employed by V.V. Vasiliev, A.F. Razin, A.A. Babichev, V.P. Buldakov and others. Nevertheless, methods for the mesh structures strength and stability computing with account for the initial stress-strain state nonlinearity under conditions of non-uniform, non-axisymmetric loading, are insufficiently developed at present. Most of the known solutions to problems of shell stability have been obtained by analytical methods and, as a rule, in a linear approximation without accounting for the momentness and nonlinearity of the subcritical state of the shells, i.e. in the classical formulation, and a rather small number of works concerning stability at nonlinear deformation. Thus, development of the reliable and effective methods for anisogrid thin-walled structures computation is undoubtedly an urgent task. The authors of the article solved the problem of the cylindrical composite shells strength and stability under combined non-uniform loading by aerodynamic and inertial forces, in the form of bending moment, transverse force and axial compression by the finite element methods and Newton–Kantorovich linearization. The finite elements of the natural curvature composite cylindrical shells, which rigid displacements are being explicitly highlighted, developed by the authors based on the Timoshenko hypothesis were applied. The study of the deformation nonlinearity impact on the stability of the aircraft fuselage compartment in the form of the circular anisogrid composite cylindrical shell was conducted in the wide range of the stiffness parameters of both shell and reinforcements, as well as stacking angle of the reinforcement set. Estimates of the fuselage compartment margin in terms of strength and stability for the five options of the shell loading with external aerodynamic and inertial loads are made. It is found that:
1. The results are brand-new, obtained for the first time, and were not found in the accessible literature sources.
2. Critical values of the load parameter significantly depend on both thickness and stiffness of the reinforcement set. With the increase of the reinforcement, critical values of the load parameter increase sevenfold.
3. Non-linearity reduces critical values of the load parameter for all shell loading options. The impact of the initial stress-and-strain state nonlinearity depends on both the reinforcement set rigidity and the case of loading, as well as on the thickness of the skin. The non-linearity effect for all shell calculation options is negligible, no more than 10%.
4. Optimal stacking angles of the reinforcement are those from 25 to 30°, depending on the skin thickness. Non-linearity reduces (up to 40%) critical values of the load parameter for any values of the reinforcement set stacking angles, and, as a rule, reduces values of the of reinforcements optimal stacking angles within the range of 2.5–5°.

Keywords:

aircraft fuselage compartment, supersonic passenger aircraft, nonlinear initial stress-and-strain state, finite element method, anisogrid composite shells, non-uniform loading

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