A fixed-geometry wide-velocity range supersonic inlet, its working method and aircraft

An air inlet, fixed geometry technology, which is applied to the air inlet of turbine/propulsion device, machine/engine, jet propulsion device, etc. The effect of increasing the performance of the intake port, reducing the amount of exhaust air, and increasing the flow capacity

Active Publication Date: 2021-10-01
JIANGXI HONGDU AVIATION IND GRP
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Problems solved by technology

[0004] In order to solve the above-mentioned technical problems, embodiments of the present invention provide a fixed-geometry wide-velocity range supersonic inlet, its working method and an aircraft, to solve the existing fixed-geometry supersonic inlet, which has high Mach number state performance and Low Mach number state start incompatibility issue

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  • A fixed-geometry wide-velocity range supersonic inlet, its working method and aircraft
  • A fixed-geometry wide-velocity range supersonic inlet, its working method and aircraft

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Embodiment Construction

[0029] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined arbitrarily with each other.

[0030] The above-mentioned background technology has explained that the existing fixed-geometry supersonic inlet generally takes the cruise state of the missile as the design point, that is, the design is based on the state of high Mach number. In actual application, the aircraft must experience low Mach number relay during flight. , there is a risk of the inlet not starting at low Mach numbers. That is to say, the existing fixed-geometry wide-velocity range supersonic inlet has the problem of incompatibility between high Mach number state performance and low Mach number stat...

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Abstract

The embodiment of the present invention discloses a supersonic air inlet with fixed geometry and wide speed range, its working method and aircraft, including: an air inlet lip, an inner channel formed by an air inlet lip and an outer compression section, which is arranged on The deflation chamber and the airflow regulating device of the constriction section of the air inlet; wherein, the airflow regulating device is arranged at the position of the deflation port of the deflation chamber, and is configured to adjust the air flow through the deflation port according to the requirements of the flight Mach number; The air cavity is configured to deflate the incoming flow of the air intake channel with the airflow adjusted by the airflow adjusting device. The embodiment of the present invention solves the problem that the existing constant-geometry supersonic inlet is incompatible with the performance in the high Mach number state and the start in the low Mach number state.

Description

technical field [0001] The present application relates to but not limited to the technical field of aircraft air inlets, especially a supersonic air inlet with fixed geometry and wide speed range, its working method and aircraft. Background technique [0002] The supersonic inlet is a very important aerodynamic component of a supersonic air-breathing aircraft (such as a missile), and its performance has a great influence on the engine's operating capability and performance. [0003] Limited by the space of the aircraft, the supersonic inlets in active service are basically in a fixed geometric form, and the fixed geometry supersonic inlets are generally designed with the cruise state of the missile as the design point, and the Mach number is high in the cruise state of the missile. In order to ensure the high Mach number The performance of the inlet port during flow requires that the shrinkage ratio in the inlet port should not be too small. At this time, the shrinkage rati...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/04F02C7/057
CPCF02C7/04F02C7/057
Inventor 万丽颖肖毅高骏冬王天绥卢杰刘涛安平陈尊敬赵政衡王春利万志明戴佳周俊伟任志文万俊丹
Owner JIANGXI HONGDU AVIATION IND GRP
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