Simplified model design method suitable for mechanism research of complex hypersonic aircraft

Abstract

The invention relates to a simplified model design method suitable for mechanism research of a complex hypersonic aircraft. The design of the complex hypersonic aircraft is simplified according to thefollowing simplified design criteria to obtain a simplified model for mechanism research; and the complex hypersonic aircraft is a two-stage parallel aircraft. The simplified model comprises a first-stage simplified model and a second-stage simplified model which meet the original parallel relation, the simplified design criterion is that the two-stage simplified model removes the appearance endof an original second-stage standard model, and other characteristics are unchanged; and the appearance of the first-stage simplified model is kept consistent with that of an original first-stage standard model in front of the position of a second-stage standard model head, and a V tail is reserved.

Description

technical field [0001] The invention relates to a method for simplifying the design of a hypersonic aircraft mechanism research model, which belongs to the field of simplified design of aerospace vehicles. Background technique [0002] For a long time, reducing the cost of launching space payloads has been the relentless pursuit of aerospace powers engaged in the development of space-to-earth transportation systems. Reusable aerospace vehicles can be used as transportation platforms for aerospace payloads, which can effectively reduce the cost of space launches. It is cheap, flexible and conventional. Notable features such as airport launch can not only be used as a low-earth orbit load transport platform, but also as an air-space combat weapon platform to carry out combat missions of precision strikes and high-point reconnaissance. Therefore, in recent years, it has attracted much attention from all over the world. For aerospace vehicles, it can be divided into single-stag...

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Problems solved by technology

[0005] Although direct research on the flow mechanism of complex hypersonic vehicles can effectively retain all the characteristics of the flow field, the research is very difficult

Especially when realizing the transient schlieren and PSP technology to simultaneously observe the space flow field image and surface pressure image of the separation process between the two-level simulations, if the shape of the aircraft is too complicated, the number of sensor arrangements will inevitably be greatly increased

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