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High-internal-contraction-ratio fixed-geometry two-dimensional hypersonic air inlet duct and design method

A hypersonic, air inlet technology, applied in the design of large internal shrinkage ratio, fixed geometry binary hypersonic air inlet, and fixed geometry binary hypersonic air inlet field, can solve the problem of weight increase, reliability decline, Complex structure and other problems, to achieve the effect of easy implementation and simple structure

Inactive Publication Date: 2017-08-25
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

But its shortcomings are also very prominent: increased weight, complex structure, reduced reliability, and more prominent problems of sealing and heat protection

Method used

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  • High-internal-contraction-ratio fixed-geometry two-dimensional hypersonic air inlet duct and design method
  • High-internal-contraction-ratio fixed-geometry two-dimensional hypersonic air inlet duct and design method
  • High-internal-contraction-ratio fixed-geometry two-dimensional hypersonic air inlet duct and design method

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specific Embodiment approach

[0022] However, the present invention also provides specific implementations of the method for optimal design of the above-mentioned large internal contraction ratio and fixed geometry binary hypersonic inlet, including:

[0023] Step 1: Design a binary hypersonic inlet prototype with a large internal contraction ratio based on the oblique shock wave theory and the seal Mach number ( figure 1 As shown), the inlet contains two stages of outer compression surfaces, and the inner compression shock wave system is composed of oblique shock waves at the leading edge of the lip shroud and flat oblique shock waves at the inner profile of the lip shroud. The geometric configuration of the inlet shoulder 13 is a NURBS spline (NURBS spline reference is Piegl, L., Tiller, W., "The NURBS book," Springer-Verlag Berlin Heidelberg, 1997, pp.117. ) to fit the curve, take 4 points for spline fitting, the tangent direction at the start end is the direction of the second-stage compression surface...

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Abstract

The invention provides a high-internal-contraction-ratio fixed-geometry two-dimensional hypersonic air inlet duct. An arc-bridge-shaped partition plate arranged horizontally is arranged near a lip cover inlet of the hypersonic air inlet duct. According to the working principle of the hypersonic air inlet duct, as for captured incoming flow, the throat of the high-internal-contraction-ratio two-dimensional hypersonic air inlet duct is too small, the self-starting performance of the high-internal-contraction-ratio two-dimensional hypersonic air inlet duct is poor generally, the partition plate is introduced into the position near the lip cover inlet of the air inlet duct, through the partition function of the partition plate, an original internal contraction section of the air inlet duct is partitioned into three internal contraction sections, the compression amount of the original internal contraction section is shared by the three internal contraction sections. The internal contraction ratio of each internal contraction subsection is greatly lowered compared with that of the original internal contraction section, and thus the self-starting mach number of the two-dimensional hypersonic air inlet duct can be remarkably lowered through the structure. The hypersonic air inlet duct is fixed in geometrical shape, simple in structure and easy to achieve, and the self-starting performance of the two-dimensional hypersonic air inlet duct can be greatly improved.

Description

technical field [0001] The invention relates to the field of aircraft aerodynamic design, and is a binary hypersonic air inlet with a large internal contraction ratio and fixed geometry. [0002] The invention also provides a design method for a large internal contraction ratio and a fixed geometry binary hypersonic inlet. Background technique [0003] Scramjet is the core propulsion system of air-breathing hypersonic vehicles, and has broad application prospects in hypersonic cruise missiles and hypersonic aircraft. As one of the key aerodynamic components of the scramjet, the hypersonic inlet is crucial to the efficient and stable operation of the scramjet and even the entire aircraft. In order to reduce the flight resistance of the aircraft as much as possible, the overall aircraft usually requires a low external resistance design for the hypersonic inlet. However, the intake port designed with low external resistance needs to increase the amount of internal compression...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/042F02K7/10G06F17/50
CPCF02C7/042F02K7/10G06F30/17
Inventor 谢文忠高晓天谭慧俊施欢王肖
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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