Method for cutting Mach surface of hypersonic aircraft with forebody/air inlet pipeline in integrated design

A technology of hypersonic speed and cutting method, which is applied in the combustion direction of the intake port of the power plant, and can solve the problem of large shock wave resistance on the compression surface

Active Publication Date: 2015-12-16
BEIHANG UNIV
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  • Abstract
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  • Application Information

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Problems solved by technology

However, since the wedge-shaped precursor needs to provide the Mach number required by the inlet, the object plane angle of the compression surface in front of the inlet lip is often already relatively large, which makes the shock wave resistance of the compression surface relatively large

Method used

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  • Method for cutting Mach surface of hypersonic aircraft with forebody/air inlet pipeline in integrated design
  • Method for cutting Mach surface of hypersonic aircraft with forebody/air inlet pipeline in integrated design
  • Method for cutting Mach surface of hypersonic aircraft with forebody/air inlet pipeline in integrated design

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Embodiment

[0038] Example : Design Mach number Ma=5 for incoming flow, Mach number Ma=2 for inlet outlet outlet. The integrated precursor / intake channel designed according to the Mach surface cutting method provided by the present invention is as follows: Figure 4 and Figure 5 shown. In this example, the inlet 3 of the air inlet is a rectangular cross-section inlet, and the designed compression surface is a four-stage compression surface, wherein the third and fourth compression surfaces are arranged inside the lip, and the first and fourth stages are arranged on the front body. Secondary compression face.

[0039]The design method of the compression surface inside the lip is as follows: start from the lower edge of the inlet 3, reverse the flow direction, that is, trace the edge 5 of the fourth-stage compression surface upstream to obtain the fourth-stage compression surface, and the edge 6 of the fourth-stage compression surface The position should be such that the shock wave ge...

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Abstract

The invention discloses a method for cutting a Mach surface of a hypersonic aircraft with a forebody/air inlet pipeline in integrated design, and belongs to the technical field of design of hypersonic aircrafts. The method comprises the following steps: designing the ratio of the width to the height of a section of the air inlet pipeline according to the requirements of a combustion chamber; according to design parameters of a compression system of the air inlet pipeline, determining parameters of the incoming flow of the air inlet pipeline and a Mach number, a shock wave angle and airflow turning angle parameters of each level of compression surfaces; according to the width of an inlet of the air inlet pipeline and the Mach number of the compression surface superior to the air inlet pipeline, tracing a Mach line upstream so as to form the edge of each level of the compression surfaces; and then according to the shock wave angle of each level of the compression surfaces, obtaining the final compression system of external compression/air inlet pipeline. Through the adoption of the method for cutting the Mach surface, disclosed by the invention, uniform air currents of the air inlet pipeline can be guaranteed through the obtained forebody, besides the width of the inlet of the air inlet pipeline is equal to the width of the air inlet pipeline, and the situation that the shock wave drag is increased because the width of the forebody is increased is avoided, so that the lift-drag ratio of the whole aircraft is increased.

Description

technical field [0001] The invention belongs to the technical field of hypersonic aircraft design, and in particular relates to a Mach surface cutting method for the integrated design of a hypersonic aircraft precursor / inlet. Background technique [0002] The integrated design of the precursor / inlet is one of the key technologies in the design of an air-breathing hypersonic vehicle. The lower surface of the precursor body is equivalent to the external compression surface of the scramjet engine. After the gas flow is compressed by the shock wave, the speed drops to the Mach number required by the intake port, and then flows into the intake port to be further compressed, and finally reaches the Mach number and temperature required for combustion. and stress. Therefore, the integrated design of the front body / intake port directly affects the performance of the engine, and because the front body is also a part of the airframe, the design of the front body will also affect the a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/02
Inventor 蒋崇文高振勋李椿萱
Owner BEIHANG UNIV
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