Supersonic hybrid layer hybrid enhanced closed-loop control method and system

A closed-loop control and supersonic technology, applied in design optimization/simulation, machine/engine, rocket engine device, etc., can solve problems such as closed-loop control difficulties, achieve high degree of self-adaptation, strong robustness, and avoid limitations

Active Publication Date: 2022-07-01
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

However, for the turbulent flow with high-dimensional nonlinear characteristics such as the supersonic mixing layer, it is still facing great difficulties to realize its closed-loop control through the classical control method

Method used

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  • Supersonic hybrid layer hybrid enhanced closed-loop control method and system
  • Supersonic hybrid layer hybrid enhanced closed-loop control method and system
  • Supersonic hybrid layer hybrid enhanced closed-loop control method and system

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Embodiment Construction

[0042] In order to make the purposes, technical solutions and advantages of the embodiments of the present invention clearer, the following will clearly illustrate the spirit of the contents disclosed in the present invention with the accompanying drawings and detailed description. , when changes and modifications can be made by the technology taught by the content of the present invention, it does not depart from the spirit and scope of the content of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention, but are not intended to limit the present invention.

[0043] An embodiment of the present invention provides a hybrid enhanced closed-loop control method for a supersonic hybrid layer, including the following steps:

[0044] S1. Build a supersonic hybrid layer hybrid enhanced closed-loop control system;

[0045] refer to figure 1 , the supersonic mixing layer hybrid enhanced closed-loop con...

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Abstract

Supersonic mixing layer hybrid enhanced closed-loop control method and system, comprising a first supersonic flow channel, a second supersonic flow channel, a controller, a console, a velocity field measurement system and a computer, between the first supersonic flow channel and the second supersonic flow channel A mixing intensifying plate is provided, the mixing intensifying plate separates the first supersonic flow channel and the second supersonic flow channel, and the first supersonic air flow and the second supersonic air flow realize enhanced mixing outside the end of the mixing intensifying plate; The console acts the excitation function signal on the hybrid intensifier; the velocity field measurement system measures the velocity of the flow field outside the end of the hybrid intensifier in real time and transmits the measured data to the computer. The computer is preloaded with a machine learning algorithm. The machine learning algorithm generates the excitation function signal to the controller. The invention has the characteristics of being adaptable to a wide range of working conditions, strong robustness, and remarkable in mixing enhancement effect.

Description

technical field [0001] The invention relates to the technical field of hybrid enhancement control in the aerospace field, in particular to a supersonic hybrid layer hybrid enhancement closed-loop control method and system, which can be used for the optimization of fuel and oxidant mixture enhancement in a combined cycle engine. Background technique [0002] Mixed laminar flow is a typical type of flow in engineering applications, such as the mixing of central gas and outer air in a turbofan engine, such as the mixing of rocket gas and ram air in a rocket-based combined cycle engine. Efficient mixing to improve combustion efficiency is one of the key technologies to improve the performance of this type of engine. The ways of controlling the mixing enhancement can be mainly divided into two categories: passive mixing enhancement and active mixing enhancement. [0003] Passive mixing enhancement is usually to install some fixed devices in the flow field or change the structural...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/78F02K1/82F02K9/96G06F30/27
CPCF02K1/78F02K1/82F02K9/96G06F30/27
Inventor 谭建国高政旺刘瑶张冬冬姚霄肖犇侯廙
Owner NAT UNIV OF DEFENSE TECH
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