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Hypersonic inlet starting method and starting device

A hypersonic, air intake technology, applied in the ignition of the turbine/propulsion device, the starting of the turbine/propulsion device, the starting of the engine, etc., can solve the overall performance decline of the engine, poor anti-back pressure performance of the intake port, Complex structure, etc.

Active Publication Date: 2019-09-27
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The present invention provides a hypersonic inlet starting control method and control device, which are used to overcome defects in the prior art such as complex structure for inlet starting, poor anti-backpressure performance of the inlet, and decline in overall engine performance. , so as to simplify and change the mechanical structure of the intake port without affecting the overall performance of the intake port and the engine

Method used

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  • Hypersonic inlet starting method and starting device
  • Hypersonic inlet starting method and starting device
  • Hypersonic inlet starting method and starting device

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Embodiment 1

[0023] Please refer to Figure 1 to Figure 3 , the present invention provides a hypersonic inlet start control method, comprising:

[0024] Step S1, obtaining the best starting profile inside the lip cover according to the known performance parameters of the air inlet, the design profile inside the lip cover and the Mach number for starting control;

[0025] In order to fully illustrate the control method of auxiliary starting used in the present invention, firstly, a two-dimensional inlet as shown in the figure is given, and the self-starting Mach number Ma of the inlet is given ss , Restart Mach number Ma rs and design Mach number Ma d and other performance parameters, and the inner profile of the lower lip cover at the design Mach number is also given, which is called the design profile in the present invention. It should be noted that, for the convenience of expressing the content of the present invention, the air intake precursor and the isolation section that are not ...

Embodiment 2

[0070] A lip cover elastic auxiliary panel is arranged around the edge of the inner top wall of the lip cover top plate, and the lip cover top plate and the lip cover elastic auxiliary panel are jointly arranged to form a cavity, and there is a gaseous medium or a liquid medium in the cavity. In order to reduce the weight of the aircraft itself, air is selected as the medium here, and the step 2 includes:

[0071] When the flight state of the aircraft reaches the control Mach number, control the air pressure change in the cavity formed by the lip cover top plate and the lip cover elastic auxiliary panel, so that the deformed shape of the lip cover elastic auxiliary panel tends to the above-mentioned The best starting line on the inner side of the lip cover;

[0072] Specifically, the amount of air input into the cavity can be controlled through the air intake equipment and the air intake valve installed on the air intake pipe. When the air pressure value reaches the starting s...

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Abstract

The invention discloses a hypersonic-speed gas inlet channel starting control method and control device. The method comprises the following steps that according to known gas inlet channel performanceparameters, a lip cover inner side design type line and a starting controlling mach number, the lip cover inner side optimum starting type line is acquired; when the flight state of an aircraft reaches the controlling mach number, the lip cover inner side type line is controlled to deform and tend to be the lip cover inner side optimal starting type line; after the gas inlet channel is started andflowing is stable, the lip cover inner side type line is controlled to deform and tend to be the lip cover inner side design type line. According to the scheme, the hysteresis phenomenon in the gas inlet channel starting process is utilized, the gas inlet channel starting performance can be greatly improved only by changing the lip opening type line, and meanwhile, the anti-backpressure performance of a gas inlet channel and the overall performance of an engine are ensured.

Description

technical field [0001] The invention relates to the technical field of hypersonic engines, in particular to a hypersonic inlet starting method and a starting device. Background technique [0002] The hypersonic intake port is a key component of the hypersonic ramjet engine. Its function is to capture a certain flow of air, decelerate and compress it, and then deliver it to the combustion chamber for combustion. However, due to the fact that the Mach number of the incoming flow of the aircraft is too low or the working pressure of the combustion chamber is too high, the intake port may enter the non-starting state, the flow capture capacity of the intake port is reduced, and the flow loss is increased, resulting in severe thrust of the engine. descended, causing the flight to fail. Therefore, only when the air inlet is in the starting state can it ensure that it can capture enough high-quality airflow and the engine can generate enough thrust. Therefore, the starting perform...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/04F02C7/26
Inventor 陆雷刘雄王翼徐尚成范晓樯赵星宇
Owner NAT UNIV OF DEFENSE TECH
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