Boundary layer transition array plane dynamic evolution process determination method based on flight test data

Abstract

The invention discloses a boundary layer transition array plane dynamic evolution process determination method based on flight test data. The method comprises the following steps: (1), converting an original measurement result output by a sensor mounted on a surface measurement point of a hypersonic aircraft into heat flow or temperature information at the position of the surface measurement pointof the aircraft, and filtering abnormal measurement point information to obtain available heat flow or temperature information at the surface measurement point of the aircraft; (2), according to theheat flow or temperature information of the available aircraft surface measuring points, obtaining the transition moment of each measuring point; (3), for any moment, judging whether transition occursat each measuring point at the moment or not according to the obtained moment when transition occurs at each measuring point; (4), in a transition measurement time window, selecting a plurality of time points, and for each time point, obtaining a transition array plane image at the time; and (5), binding the transition array plane images at each moment obtained in the step (3) into an animation according to a flight time sequence, and obtaining a transition array plane dynamic evolution process, thereby obtaining a transition area on the surface of the aircraft at each moment.

Description

technical field [0001] The invention relates to a method for determining the dynamic evolution process of a boundary layer transition front based on flight test data, and belongs to the technical field of transition measurement using sensor arrays. Background technique [0002] A key issue in the design of a hypersonic vehicle is to accurately predict the transition of the boundary layer on the surface of the vehicle: for a lifting body vehicle flying at a hypersonic speed, foreign flight test results have shown that the transition will lead to complex and uncertain vertical and horizontal transitions. Lateral aerodynamic disturbance will affect the aerodynamic stability and maneuverability of the aircraft. Poor design will lead to loss of flight stability and flight failure. For example, the failure of the first flight test of HTV2 and the impact of transition on aerodynamic and control characteristics may There is a direct relationship. On the other hand, after the transi...

AI Technical Summary

Problems solved by technology

[0002] A key issue in the design of a hypersonic vehicle is to accurately predict the transition of the boundary layer on the surface of the vehicle: for a lifting body vehicle flying at a hypersonic speed, foreign flight test results have shown that the transition will lead to complex and uncertain vertical and horizontal transitions. Lateral aerodynamic disturbance will affect the aerodynamic stability and maneuverability of the aircraft. Poor design will lead to loss of flight stability and flight failure. For example, the failure of the first flight test of HTV2 and the impact of transition on aerodynamic and control characteristics may there is a direct relationship

On the other hand, after the transition occurs, the heat flow on the surface of the aircraft increases sharply, which poses a huge challenge to the thermal protection design of superb aircraft

[0003] The transition of the boundary layer of a hypersonic vehicle is very complicated, and there are many factors that affect the transition, mainly including three aspects: the influence of the shape of the vehicle itself, including the curvature of the vehicle head, the curvature of the surface shape, the cabin gap and the antenna window and other local protrusions and Grooves, etc.; the impact of flight status, including flight altitude, Mach number, angle of attack, sideslip angle, etc.; the impact of aircraft surface status, including roughness, wall temperature, surface quality ejection caused by ablation and pyrolysis, etc. The transition mechanism and the mechanism of action of the above-mentioned influencing factors have not been clearly understood so far.

[0004] The establishment of the dynamic evolution process of the surface transition under the real flight state of the aircraft is of great significance for the theoretical research of the transition problem and the engineering design of the aircraft. Establish a method to obtain the dynamic evolution process of aircraft surface transition in actual flight

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