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Design method and system of a forced transition device

A design method, a transitional technology, applied in the field of aerodynamics research

Active Publication Date: 2019-06-18
TSINGHUA UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

A forced transition device can be installed on the high-speed aircraft to enable the high-speed aircraft to realize the transition function, but the size design of the forced transition device is a major problem in research

Method used

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  • Design method and system of a forced transition device
  • Design method and system of a forced transition device
  • Design method and system of a forced transition device

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Embodiment Construction

[0043] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0044] figure 1 It is a schematic flow chart of the design method of the forced transition device in the embodiment of the present invention, such as figure 1 As shown, the design method of the forced transition device provided by the embodiment of the present invention includes:

[0045] S1. Obtain the flow parameters of the flight of the aircr...

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Abstract

The embodiment of the invention provides a design method and system of a forced transition device. The method includes the steps that the flow parameters of air vehicle flight are acquired, and a perturbation control equation is established; according to the perturbation control equation, a hypersonic boundary layer Gertler vortex growing most rapidly is acquired; according to the parameters of the Gertler vortex, the spanwise length and height of the forced transition device are obtained. The system is used for implementing the method. In the method, the Gertler vortex growing most rapidly is obtained through solving according to the perturbation control equation, and the spanwise length and height of the forced transition device are obtained according to the parameters of the Gertler vortex, so that the dimensional design of the forced transition device is completed, and the rationality of the dimensional design of the forced transition device is improved.

Description

technical field [0001] The embodiments of the present invention relate to the technical field of aerodynamic research, and in particular to a design method and system for a forced transition device. Background technique [0002] With the development of science and technology, the appearance of aircraft has had a great impact on both people's daily life and the country's military development. [0003] For waverider high-speed aircraft, on the one hand, we need to use the low resistance characteristics of laminar flow to save fuel, and on the other hand, we also need to use the characteristics of turbulent flow that is not easy to separate and fully mixed to ensure the normal operation of the scramjet. The precondition for utilizing the above-mentioned flow characteristics is to be able to master the transition control method, that is, convert laminar flow into turbulent flow, so as to reduce flow separation, improve flow anti-backpressure ability, and facilitate the start of ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/17Y02T90/00
Inventor 符松任杰罗金玲汤继斌
Owner TSINGHUA UNIV