Evaluation of the Load Bearing Capacity of the Honeycomb Core Sandwich Panels with Face Sheets Made of Metal Matrix Comp
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NICAL NOTES STRUCTURAL MECHANICS AND STRENGTH OF FLIGHT VEHICLES
Evaluation of the Load Bearing Capacity of the Honeycomb Core Sandwich Panels with Face Sheets Made of Metal Matrix Composite under Static and Dynamic Loading A. V. Volkova, b, Yu. O. Solyaeva, b, L. N. Rabinskiia, *, and A. A. Shavnevc a
Moscow Aviation Institute (National Research University), Volokolamskoe shosse 4, Moscow, 125993, Russia b Institute of Applied Mechanics, Russian Academy of Sciences, pr. Leningradskii 7, Moscow, 125040 Russia c The All-Russian Institute of Aviation Materials (VIAM), ul. Radio 17, Moscow, 105005 Russia *e-mail: [email protected] Received February 8, 2020; revised February 19, 2020; accepted February 19, 2020
Abstract—This paper presents the simulation results for the three-layered aluminum honeycomb panels with face sheets made of composite aluminum alloy filled with silicon carbide particles. The effect of the filler volume fraction on the load bearing capacity of a simply supported panel under condition of static loading with uniformly distributed pressure and under the impact over the panel surface with a rigid spherical body is investigated. It is shown that the static and dynamic characteristics of the panel change in a different way depending on the filler volume fraction. DOI: 10.3103/S1068799820020245 Keywords: honeycomb core, particulate composite, aluminum composite, silicon carbide, impact, numerical simulations.
INTRODUCTION Three-layer composite structures (sandwich panels) are widely used in aerospace engineering, as they have high specific characteristics of strength and rigidity [1, 2]. In addition, three-layer composites allow multifunctional products to be created, for example, with built-in elements of active thermal protection, acoustic protection, etc. [3–6]. The use of composite materials to create the face sheets or the cores in three-layer structures can further improve their specific mechanical characteristics [7, 8]. Metal composites as a part of three-layer structures are now rarely used, however, these materials have several advantages (high operating temperature, high electrical and thermal conductivity, etc.), and therefore, also have their areas of application [9, 10]. In this paper, we consider honeycomb panels with face sheets made of a particulate aluminum composite filled with silicon carbide particles. Such aluminum silicon carbide metal matrix composites are well known. One of their main features is the fact that the addition of the ceramic filler almost does not change the apparent density of the material [11, 12]. The possibility of using such composites for the manufacture of structural elements of an aircraft and the possibility of increasing the local stability of the skin and reducing the amount of the reinforcing elements by using a metal matrix composite (with Young’s modulus 1.5 times higher than that of conventional aluminum alloys) was discussed in [11]. In this paper, we study not only the possibility of increasing the stiffness of the metal matrix composite three-laye
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