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

A technology of hypersonic speed and design method, which is applied to aircraft parts, ground devices, transportation and packaging, etc. It can solve problems such as difficult research, increasing the number of sensor layouts, and complex aircraft shapes, so as to reduce the number of layouts and reduce the difficulty of model processing , the effect of reducing difficulty

Active Publication Date: 2019-12-03
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Abstract
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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 si

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

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Embodiment Construction

[0027] The present invention will be further elaborated below in conjunction with embodiment.

[0028] The invention aims at the problem that it is difficult to carry out the flow mechanism research of the complex hypersonic two-stage orbiting vehicle, and proposes a simplified model design method suitable for the mechanism research of the complex hypersonic two-stage orbiting vehicle. Using this model design method, on the one hand, the main flow characteristics of the original model are retained, and at the same time, the difficulty of studying the separation flow mechanism of the two-stage aircraft is reduced, which lays a certain foundation for the experimental research on the separation flow mechanism of the two-stage aircraft.

[0029] The present invention respectively simplifies the models of the two-stage orbiting hypersonic vehicle. The shape of the first-level simplified model is a wing-body assembly, specifically as figure 1 As shown, this simplified model is cons...

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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...

Claims

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Application Information

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IPC IPC(8): B64F5/00
CPCB64F5/00
Inventor 喻海川何跃龙李盾陈兰甘才俊
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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