Aerodynamic heat measuring method suitable for blunt body reentry vehicle

Abstract

The invention provides an aerodynamic heat measuring method suitable for a blunt body reentry vehicle. The aerodynamic heat measuring method is used for measuring of surface heat flow distribution ofthe side walls, the large bottom, the stagnation point area and the boundary layer transition area of the blunt body reentry vehicle and measuring of total heating capacity of the windward side and the leeward side. The aerodynamic heat measuring method comprises the following steps that according to the appearance and a reentry trajectory of the blunt body reentry vehicle, simulation analysis onaerodynamic heat load on the surface of the blunt body reentry vehicle is conducted; according to the sizes and distribution of aerodynamic heating heat flows, sensor selecting and measuring range determining are conducted; according to the aerodynamic heat measuring task requirement of the blunt body reentry vehicle, configuration demand analysis of sensors is conducted; sensor layout design is conducted; and sensor calibration and mounting are conducted. According to the aerodynamic heat measuring method, the real reentry heat flow load can be obtained, particularly, real-time data of transition of the boundary layer on the surface of the vehicle can be provided, and guiding significance is achieved on a current calculating analysis model and the ground test technical scheme.

Description

technical field [0001] The invention relates to aircraft aerodynamic thermal measurement technology, in particular to an aerodynamic thermal measurement method for a blunt body reentry aircraft, belonging to the technical field of aircraft aerodynamic measurement. Background technique [0002] Accurately grasping the aerodynamic heating characteristics of the blunt body reentry vehicle is the key to the thermal protection design of the reentry vehicle, and high-precision prediction of the reentry aerodynamic heating environment is the basis and important prerequisite for the design of the thermal protection system of the blunt body reentry vehicle. The model parameters and reliability of the traditional calculation and simulation method need to be verified, while the aerothermal test capability of the ground wind tunnel is limited, and it is impossible to reproduce the high Mach number range and the thermophysical characteristics of strong convective heating in the real fligh...

AI Technical Summary

Problems solved by technology

The model parameters and reliability of the traditional calculation and simulation method need to be verified, while the aerothermal test capability of the ground wind tunnel is limited, and it is impossible to reproduce the high Mach number range and the thermophysical characteristics of strong convective heating in the real flight environment of orbital entry / reentry flight , the precise prediction of the thermal environment by the two methods has always been a technical bottleneck that is difficult to break through in the thermal protection technology of re-entry vehicles

Especially when the large-sized blunt body is flying at a semi-ballistic reentry angle of attack, the flow on the surface of the high-altitude aircraft will have a boundary layer transition phenomenon, which will intensify the surface heat flow environment under high Mach number flight conditions, and at the same time increase the design of the heat protection system Difficulty, the current traditional calculation methods and ground tests cannot accurately predict the timing, area and other physical characteristics of the transition under flight conditions

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