Standard Model Layout Design Method Applicable to Shock/Boundary Layer Interference and Thermal Protection Research

Abstract

A standard model layout design method suitable for shock wave / boundary layer interference and heat protection research of the present invention comprises: step 1, determine the left and right width contour lines of the aircraft; step 2, determine the contour lines of the upper and lower surfaces of the aircraft; step 3, design x = L section curve; step 4, design x = x B section curve; step 5, design point B later on C The section surface of ; step six, design x = L 1 Section curve at ; step seven, design point B Previous section surface; step eight, design point E to the point E 1 sectional surface of ; step nine, design point E to the point E 1 The lower part of the section curve compresses the section surface in the corner area; Step 10, the section surface obtained in Step 5, Step 8, and Step 9 is about zx Plane symmetry; the surface obtained in step 6 is respectively about zx flat, xy Planar symmetry. The invention can design a standard model layout suitable for shock wave / boundary layer interference and heat protection research.

Description

technical field [0001] The invention relates to the technical field of aerodynamic layout design of aircraft, in particular to a standard model layout design method applicable to shock wave / boundary layer interference and heat protection research. Background technique [0002] With the increasingly complex aerodynamic layout of aerospace vehicles and the higher flight speeds of the aircraft, the problem of local shock wave interference caused by the small and micro-scale structure of the aircraft and the design of heat-resistant structures based on composite materials have gradually become prominent. The local shock wave disturbance flow has a serious impact on the local mechanical and thermal characteristics of the aircraft, and the pulsating pressure generated by it will cause the local structure of the aircraft to vibrate and even cause damage; the local shock wave disturbance flow will cause local high heat flow, high dynamic friction and shear. Stress, and the local the...

AI Technical Summary

Problems solved by technology

However, the current numerical simulation methods cannot accurately predict the peak heat flow and its position under strong interference conditions, and at the same time cannot accurately establish a fine cross-scale prediction model for composite materials. Due to insufficient equipment simulation capabilities and incompletely clear simulation criteria, there are still many unclear mechanisms and deviations in the current local shock wave / boundary layer interference simulation and thermal performance prediction models of heat-resistant structures, which urgently need to be obtained through flight tests. Improve the prediction model by fluctuating pressure in the local interference area and composite material performance data under real flight conditions

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