Method of detonating oblique detonation wave in supersonic air flow by using additional instantaneous energy source
A technology of instantaneous energy and supersonic speed, applied in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve problems such as large inlet resistance and total pressure loss, high inlet compression degree, etc., to reduce resistance and the effect of the total pressure loss in the intake port
Active Publication Date: 2020-05-29
CHINA AERODYNAMICS RES & DEV CENT
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However, from the perspective of high-speed propulsion, large size and large angle of wedge will bring greater resistance, and higher incoming static pressure means higher intake port compression, so it also means higher Large inlet resistance and total pressure loss
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[0023] The present invention will be described in further detail below in conjunction with the accompanying drawings.
[0024] The method for detonating an oblique detonation wave in a supersonic airflow by using an external instantaneous energy source comprises the following steps:
[0025] S1: Add an instantaneous energy source generator at the shock wave generator;
[0026] S2: Determine the local CJ detonation propagation velocity of the corresponding combustible gas;
[0027] S3: The angle of the shock wave generating device is set so that the ratio of the flow velocity behind the front shock wave to the local CJ detonation propagation velocity is less than 1.05.
[0028] In the above scheme, the oblique wedge is used as the shock wave generator as an example for illustration: the oblique wedge is only used as a stabilizing device (flame stabilizer) for the oblique detonation shock wave, not as an initiation device; the instantaneous energy source is located near the...
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The invention discloses a method of detonating an oblique detonation wave in a supersonic air flow by using an additional instantaneous energy source and relates to the technical field of air-breathing hypersonic aircrafts. The specific scheme of the method comprises the following steps of S1, additionally arranging an instantaneous energy source generator at a shock wave generation device; S2, determining a local CJ detonation propagation velocity of corresponding combustible gas; and S3, setting an angle of the shock wave generation device, wherein the ratio of the post-wave flowing velocityof a front edge shock wave and the local CJ detonation propagation velocity is smaller than 1.05. The method of detonating the oblique detonation wave in the supersonic air flow by using the additional instantaneous energy source can be used for detonating the oblique detonation wave on a bevel cut with a relatively small incoming flow static pressure, small size and small angle, so that resistance of an engine and an air inlet and the total pressure loss of the air inlet are reduced advantageously.
Description
technical field [0001] The invention relates to the technical field of air-breathing hypersonic aircraft, more specifically, it relates to a method for detonating an oblique detonation shock wave in a supersonic airflow by using an external instantaneous energy source. Background technique [0002] The oblique detonation combustion organization method is a new type of combustion organization method in high Mach number flight, and the oblique detonation initiation is realized by shock wave generating devices (such as oblique wedges, cones, etc.), such as figure 1 shown. According to the classical oblique detonation initiation energy criterion and the chemical kinetics criterion, it can be known that the oblique detonation requires a sufficient size and angle of the oblique wedge and a sufficiently high incoming static pressure to achieve oblique detonation initiation. However, from the perspective of high-speed propulsion, large size and large angle of wedge will bring great...
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IPC IPC(8): F02K9/95F02K7/00
CPCF02K9/95F02K7/00
Inventor 肖保国刘彧陈伟强王超蔡建华郑榆山王兰邢建文何粲
Owner CHINA AERODYNAMICS RES & DEV CENT