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A fixed geometry binary hypersonic inlet and its design method

A hypersonic and air inlet technology, applied in the design of fixed geometry binary hypersonic air inlet, can solve the problems of increased weight, decreased reliability and complex structure, etc. To achieve the effect of easy implementation and simple structure

Inactive Publication Date: 2018-07-27
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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  • A fixed geometry binary hypersonic inlet and its design method
  • A fixed geometry binary hypersonic inlet and its design method
  • A fixed geometry binary hypersonic inlet and its design method

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specific Embodiment approach

[0022] However, the present invention also provides a specific implementation of the above-mentioned optimal design method for the fixed-geometry binary hypersonic inlet, including:

[0023] Step 1: Design a binary hypersonic inlet prototype ( 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 7, and the tangent direction at the end is the horizontal direction. According to the configuration of the binary hypersonic inlet, the airfl...

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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 fixed-geometry binary hypersonic air inlet. [0002] The invention also provides a design method of the 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 to make up for the lack of external compression, resulting in an increase in the ...

Claims

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Application Information

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Patent Type & Authority Patents(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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