In this paper, the influence of heating of the structure on its strength is considered in three aspects: a decrease in the mechanical characteristics of structural materials at high temperature, heating of the structure can lead to temperature stresses in its elements and elements of aircraft systems and the occurrence of the phenomenon of creep of structural materials - continuous plastic deformation of structural elements under constant load. There are several options for reducing heat flows due to modification of the basic aerodynamic layout: increasing the sweep angles of the bearing surfaces and the radius of the wing tip and the front edges of the inflows, reducing the area of the washed surface due to the “flattening” of the initial aerodynamic contours. Each of the considered existing and promising methods of thermal protection separately will not allow to fully develop thermal protection of promising reusable supersonic aircraft. A comprehensive approach is needed. At the same time, it is necessary to consider both the replacement of structural materials of panels and cladding with titanium or steel alloys, as well as design solutions for the use of fuel lines.
A modern gas turbine engine, in the layout of the designed aircraft, allows us to consider fundamentally different placement options. The contradictory influence of the type, number and location of engines on the safety and efficiency of flight leads to the need to study these tasks at the early stages of design. This article discusses an approach to determining the optimal position of engines by wingspan at the stage of preliminary design. The calculation features consist in taking into account various factors: strength, for different design cases, mass-inertial, operational-technological and others. In the course of the study, the aircraft wing power set was simulated with its subsequent calculation in the NX system. As a result of the study, the optimal arrangement of engines for a four-engine aircraft with known geometric characteristics of the wing and its shape was obtained. An approach is shown, as a result of which it is possible to determine the optimal position of the engines, both in terms of the magnitude of bending moments in the root part of the wing and moments of inertia. The same method can be used to prove or correct the already accepted position of the engines on the designed aircraft.
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