A thermal environment design method for hypersonic aircraft control rudder gap

Abstract

The invention discloses a thermal environment design method of space between control rudders of a hypersonic flight vehicle. The method comprises the steps of on account of a simplified appearance of the hypersonic flight vehicle, adopting a prediction method of aerodynamic heat engineering to conduct a prediction for aerodynamic-heat thermal environment and obtain a prediction result of aerodynamic heat engineering; according to the prediction result of aerodynamic heat engineering, confirming flow pattern changes of a rudder shaft section of a control rudder along a trajectory, and conducting numerical calculation of thermal environment of the flight vehicle on multiple groups of typical trajectories under a condition of different flow patterns according to the trajectory time period of flow pattern changes, then obtaining heat flow distribution of the space between the control rudders of the flight vehicle; choosing a laminar flow state to conduct numerical calculation of thermal environment of the space between the control rudders, and modifying the prediction result of aerodynamic heat engineering according to the calculation result; designing the thermal environment of the space between the control rudders along a trajectory according to the modified result. The thermal environment design method of space between control rudders of a hypersonic flight vehicle resolves the problems that the flow patterns of space between control rudders of a hypersonic gliding flight vehicle are too complex to predict under a ballistic condition, and the thermal environment is so tough that a part of heat-proofing risks are hard to be estimated.

Description

technical field [0001] The invention belongs to the technical field of aircraft, and in particular relates to a thermal environment design method for control rudder gaps of a hypersonic aircraft. Background technique [0002] The hypersonic gliding maneuvering vehicle produces severe friction with the surrounding atmosphere during flight, and the vehicle faces a severe aerodynamic heating environment; for the control rudder area, due to the existence of local complexities such as the gap between the rudder and the cabin, the rudder shaft / cabin rotation gap, and the rudder shaft structure and needs to swing back and forth to adjust the attitude of the aircraft, the thermal environment of the control rudder and the surrounding area is harsh and the distribution is very complicated, especially the thermal environment of the air rudder gap area (the rudder shaft, the cabin near the rudder shaft, and the rudder gap entrance, etc.) is severe and Difficult to predict. [0003] Usu...

AI Technical Summary

Problems solved by technology

[0006] The technical problem of the present invention is to overcome the deficiencies of the prior art, provide a thermal environment design method for the control rudder gap of a hypersonic vehicle, and solve the complex and difficult-to-predict flow state of the control rudder gap area under the ballistic condition of a hypersonic gliding vehicle. Moreover, the severe thermal environment makes it difficult to assess the local heat protection risk, which can effectively reduce the uncertainty of heat protection design and avoid the risk of heat protection design in local areas of the aircraft

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