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A dynamic boundary control system for the dynamic and stable propagation of detonation in supersonic airflow

A dynamic stability and boundary control technology, applied to ramjet engines, machines/engines, jet propulsion devices, etc., can solve the problems that the conceptual design of new scramjet engines has not been reported, and achieve the effect of flexible and efficient control functions

Active Publication Date: 2018-11-20
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

The scramjet engine has gradually moved towards engineering applications, but the conceptual design of a new scramjet engine based on detonation combustion has not yet been reported

Method used

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  • A dynamic boundary control system for the dynamic and stable propagation of detonation in supersonic airflow
  • A dynamic boundary control system for the dynamic and stable propagation of detonation in supersonic airflow
  • A dynamic boundary control system for the dynamic and stable propagation of detonation in supersonic airflow

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Embodiment Construction

[0022] In order to make the technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0023] The embodiment of the present invention proposes a dynamic boundary control system for the dynamic and stable propagation of detonation in supersonic airflow, figure 1 is a schematic diagram of the structure of this embodiment, such as figure 1 As shown, it includes a detonation wave state monitoring system, an information analysis module, and an expansion wall adjustment control system. The expansion wall adjustment control system includes an expansion wall and an expansion wall power system, and at least one expansion wall 3 capable of adjusting the expansion angle of the wall of the combustion ...

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Abstract

The invention provides a dynamic boundary control system for detonation dynamic stable propagation in a supersonic airflow. The dynamic boundary control system comprises a detonation wave state monitoring system, an information analysis module and an expansion wall face adjustment and control system. When a detonation wave face position is monitored by the detonation wave state monitoring system to reach a set wave face critical position, an expansion wall power system is enabled; when the propagation state of the detonation wave is attenuation back-pass and the detonation wave reaches a detonation wave back-pass threshold position, an expansion angle of the expansion wall face is decreased, and the detonation wave is made to pass forwards till to reach a relatively stable dynamic standingposition; when the propagation state of the detonation wave is overdrive forward-pass and the detonation wave reaches a detonation wave forward-pass threshold position, the expansion angle of the expansion wall face is increased, the detonation wave is made to pass backwards till to reach the relatively stable dynamic standing position; and when the detonation wave is monitored to reach the dynamic standing position, the expansion wall face adjustment and control system is turned off, so that the relative dynamic stable propagation of the detonation wave is realized, and the continuous thrustis generated.

Description

technical field [0001] The invention relates to the technical field of vibration stable propagation control, in particular to a control system for realizing dynamic and stable propagation of detonation in a supersonic expansion profile combustion chamber. Background technique [0002] The scramjet engine (Scramjet) has excellent performance under high Mach (Ma>5) flight conditions, and has become the preferred solution for the propulsion system of hypersonic aircraft. However, combined with the current research and the US X-51A flight test, it can be known that the acceleration performance of the scramjet demonstrator is not obvious, and the net thrust is relatively small. Therefore, based on current research, there is an urgent need to improve engine thrust performance. The scramjet engine is designed according to the Brayton isobaric combustion cycle, and its thermodynamic cycle efficiency is much lower than that of the detonation combustion of the approximate constant...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K7/14F02C3/14F02C9/00F23R3/02
CPCF02C3/14F02C9/00F02K7/14F05D2240/35F23R3/02
Inventor 蔡晓东梁剑寒刘世杰林志勇陈伟强
Owner NAT UNIV OF DEFENSE TECH
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