Standard model layout design method suitable for shock wave/boundary layer interference and heat protection research

Abstract

The invention discloses a standard model layout design method suitable for shock wave / boundary layer interference and heat protection research. The method comprises the following steps of 1, determining left and right width contour lines of an aircraft, 2, determining upper and lower surface contour lines of the aircraft, 3, designing a section curve at the position x=L, 4, designing a cross section curve at x=xB, 5, designing a section curved surface from the point B to the point C, 6, designing a section curve at the position where x is equal to L1, 7, designing a section curved surface in front of the point B, 8, designing a section curved surface from the point E to the point E1, 9, designing a section curved surface of a compression corner area at the lower part of a section curve from the point E to the point E1, and 10, enabling the cross section curved surfaces obtained in the fifth step, the eighth step and the ninth step to be symmetrical about the zx plane, and enabling the curved surfaces obtained in the sixth step to be symmetrical about the zx plane and the xy plane. According to the method, the standard model layout suitable for shock wave / boundary layer interference and heat protection research can be designed.

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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