CN214690217U - Two-stage compression inner waverider air inlet channel based on bending shock wave theory inverse design method - Google Patents

Abstract

A two-stage compression inner waverider air inlet based on a bending shock wave theory inverse design method relates to a hypersonic air inlet in a near space. A two-stage compression inner waverider air inlet is arranged; the two-stage compression internal waverider air inlet is provided with a two-stage compression internal waverider air inlet compression profile, a two-stage compression internal waverider air inlet lip, a two-stage compression internal waverider air inlet shoulder and a two-stage compression internal waverider air inlet isolation section; the two-stage compression inner waverider air inlet compression profile turns flat at the shoulder of the two-stage compression inner waverider air inlet and enters a two-stage compression inner waverider air inlet isolation section, and the two-stage compression inner waverider air inlet isolation section equally straightens or expands and stretches the shoulder profile according to the outlet area requirement. The flow field characteristics of the two-stage compression internal waverider air inlet channel and the outlet performance of the two-stage compression internal waverider air inlet channel are considered, the controllable design of the two-stage compression flow field with the wave system structure and the outlet parameter distribution is realized, the total pressure recovery is greatly improved under the condition of ensuring the pressure ratio, the compression efficiency is greatly improved, and the characteristic length of the air inlet channel is shortened.

Description

Two-stage compression inner waverider air inlet channel based on bending shock wave theory inverse design method

Technical Field

The utility model relates to a close on space hypersonic inlet duct especially relates to a two-stage compression internal waverider inlet duct based on the inverse design method of bending shock wave theory.

Background

Hypersonic aircraft have become the leading position of the global aerospace industry since the 21 st century. The air inlet channel serving as a core structure can capture enough air and realize efficient compression at the same time, and the whole propulsion system can generate enough thrust to meet the working range of wide Mach number. At present, the more mature development is binary, axisymmetric and side-pressure. In the last 40 th century, scholars at home and abroad put forward three-dimensional internal-contraction type air inlets with high compression efficiency, low external resistance and wide Mach number working range, and research is carried out on the problems of design methods, flow characteristics, working characteristics, engineering design research and the like of the air inlets.

The direct flow line tracks the inner contraction inlet channel:

truncated-profile Busemann inlet channels (MOELDER, s. internal, axisymmetric, chemical flow]Aiaa Journal,1967,5(7): 1252-; the HYCAUSE Program proposed in the United states and Australia developed an elliptical inlet adduction inlet (Walker S, Rodgers F, Paull A, et al. HYCAUSE Flight Test Program [ C ]]//15th AIAA International Space plants and Hypersonic Systems and Technologies conference.2008.); matthews designs a missile Modular wave-rider Hypersonic Intake (Matthews A J, Jones T V.design and Test of a Modular Waverider Hypersonic Intake [ J].Journal of Propulsion&Power,2006,22(4):913 and 920.); ajay P.K. of Astrox corporation, USA, with reference to the concept of cone guided wave body, proposes the concept of a Funnel-type air inlet (Kothari A, Tarpley C, Mclaighlin T, et al]//32nd Joint Propulsion Conference and inhibition. 1996.); interior waverider formula intake duct of rectangular exit has been designed based on ICFC flow field to zhui etc(Zhu Xiang, Huang Ping, Yongcheng, etc.. Performance comparison of interior waverider-derived air intake duct with typical side pressure air intake duct [ J]Advancing technique, 2011,032(002), 151-. The aspect of the geometric transition variable cross section internal contraction air inlet channel is as follows: smart et al, the national NASA Langley research center, designs an internal contraction air inlet with a Rectangular inlet and an Elliptical outlet (Smart, M.K. design of Three-Dimensional Hypersonic Inles with Rectangular-to-elastic Shape Transition [ J.].Journal of Propulsion&Power,1999,15(3): 408-. The pneumatic transition variable cross section internal contraction air inlet passage aspect: the FALCON aircraft of Rocksied-Martin, USA, adopts a variable-section wing-body fusion air inlet scheme (Elvin J D. integrated aircraft channels and non-rotors for hypersonic air vehicles [ J J.]2007.); yoyan Cheng et al adopts osculating axisymmetric theory to design variable cross-section internal waverider air intake duct (Yoyan Cheng, Liangdewang. three-dimensional variable cross-section hypersonic air intake duct [ J ] based on internal waverider concept]127-; youyancheng et al also provide a design method of variable cross-section internal waverider-derived air intake duct with freely selectable shock wave shape (Youyancheng, Huangguping, Guo military, etc.. Inward waverider-derived hypersonic air intake duct based on arbitrary shock wave shape: China, 101392685[ P].2009-03-25.)。

Although various studies have made significant progress in the field of hypersonic inlet duct research, component performance is also being improved. However, the three-dimensional inner contraction inlet reflection design is based on a reference flow field of a single incident wave, and a streamline tracing technology is adopted to obtain a compression profile. The reference flow field directly determines the pneumatic performance of the air inlet channel, but the current flow field and design method still have inherent defects: the shock wave compression ratio is small, and the flow field loss is large; during design, a wall profile or on-way pneumatic parameters need to be given, and wave system distribution cannot be directly controlled, so that the design flexibility of the air inlet channel is greatly influenced. The shock wave curved surfaces with different shapes can greatly influence the flow of an engine and the geometric shape of an inlet of an air inlet. It can be seen that the determination of the shock wave is the central importance of the design of the air inlet channel, and considering the balance of the supercharging ratio and the total pressure recovery, the compression efficiency is expected to be improved through multi-stage compression under the condition that other parameters are kept unchanged. Meanwhile, scientific researchers generally adopt a traditional characteristic line method to carry out reverse design of the reference flow field, programming is complex, stability is poor, the selection range of the reference flow field is limited, and the geometric construction range of the air inlet channel is further reduced. Therefore, one of the problems of restricting the performance of the hypersonic inlet is that a two-stage compression inner waverider inlet inverse design method which is based on a bending shock wave theory and can realize controllable shock wave profile and outlet parameter distribution is lacked.

Disclosure of Invention

The utility model aims at providing a two-stage compression inner wave intake duct based on the reverse design method of bending shock wave theory.

The utility model is provided with a two-stage compression internal waverider intake duct; the two-stage compression internal waverider air inlet is provided with a two-stage compression internal waverider air inlet compression profile, a two-stage compression internal waverider air inlet lip, a two-stage compression internal waverider air inlet shoulder and a two-stage compression internal waverider air inlet isolation section; the two-stage compression inner waverider air inlet compression profile turns flat at the shoulder of the two-stage compression inner waverider air inlet and enters a two-stage compression inner waverider air inlet isolation section, and the two-stage compression inner waverider air inlet isolation section equally straightens or expands and stretches the shoulder profile according to the outlet area requirement.

The position of the lip of the two-stage compression inner waverider air inlet is determined by the position of two incident shock wave reflecting points of the two-stage compression inner waverider air inlet.

The cross section of the outlet of the two-stage compression internal waverider air inlet channel is elliptical or similar to a rectangle.

The utility model has the advantages that: the two-stage compression internal waverider air inlet channel simultaneously takes the flow field characteristics of the two-stage compression internal waverider air inlet channel and the outlet performance of the two-stage compression internal waverider air inlet channel into consideration, realizes the controllable design of the two-stage compression flow field with the wave system structure and the outlet parameter distribution, greatly improves the total pressure recovery under the condition of ensuring the pressure ratio, greatly improves the compression efficiency and shortens the characteristic length of the air inlet channel. The air inlet channel is a three-dimensional inner wave air inlet channel, so that the full flow capture of incoming flow can be realized, the thrust of the engine is increased, and the external flow resistance is also reduced; and the overflow can be automatically adjusted under the condition of low Mach number, so that the working Mach number range of the air inlet channel is widened. Compared with the traditional characteristic line method, the bending shock wave theory has higher precision, the number of required grids is greatly reduced, the calculation efficiency is higher, and the range of the obtained reference flow field is wider. The design idea of supersonic flow field is enriched by reasonably designing the two-stage compression structure of the two-stage compression internal waverider air inlet, and the design range of the internal waverider air inlet is widened, so that the working performance of the air inlet is further improved.

Drawings

Fig. 1 is a two-dimensional projection of the inlet and outlet cross-sections of an embodiment of the invention.

Fig. 2 is a schematic diagram of the overall structure of the embodiment of the present invention.

Fig. 3 is a schematic diagram of a half-section structure of the embodiment of the present invention.

Fig. 4 is a schematic bottom view of an embodiment of the present invention.

The labels in the figure are: 1 represents a lip of a two-stage compression inner waverider intake duct, 2 represents an oval outlet section of the two-stage compression inner waverider intake duct, 3 represents a leading edge capture profile of the two-stage compression inner waverider intake duct, 4 represents two sections of compression profiles in different reference planes of the two-stage compression inner waverider intake duct, 5 represents two sections of compression profiles of the two-stage compression inner waverider intake duct, 6 represents a shoulder profile of the two-stage compression inner waverider intake duct, 7 represents an isolation section of the two-stage compression inner waverider intake duct, and 8 represents an outlet of the isolation section of the two-stage compression inner waverider intake duct.

Detailed Description

As shown in fig. 1-4, the embodiment of the utility model provides a take advantage of in the two-stage compression intake duct, take advantage of in the two-stage compression intake duct by two sections compression faces 5 of wave intake duct in the two-stage compression, take advantage of in the two-stage compression intake duct lip 1, take advantage of in the two-stage compression intake duct shoulder molded lines 6 and the two-stage compression and take advantage of in the wave intake duct isolation section 7 and constitute, can realize inside the taking advantage of the wave. The second section of the compression profile 5 of the two-stage compression internal waverider air inlet enters the isolation section 7 of the two-stage compression internal waverider air inlet at the shoulder profile 6 of the two-stage compression internal waverider air inlet, and the position of the lip 1 of the two-stage compression internal waverider air inlet is determined by the position of two incident shock wave reflection points of the two-stage compression internal waverider air inlet under the design condition; the two-stage compression inner waverider air inlet duct isolation section 7 is obtained by straightening or expanding and stretching the shoulder profile according to the outlet area requirement; the tail end of the two-stage compression internal waverider air inlet isolating section 7 is provided with a two-stage compression internal waverider air inlet isolating section outlet 8; the front edge of the two-stage compression internal waverider air inlet is provided with a two-stage compression internal waverider air inlet front edge capture molded line 3.

In fig. 1, reference numeral 2 denotes an elliptical outlet cross section of the two-stage compression internal waverider intake duct, and 4 denotes two-stage compression profiles in different reference planes of the two-stage compression internal waverider intake duct.

The utility model discloses when keeping interior wave intake duct advantage, realize the inside two-stage compression of interior wave intake duct. The working performance of the air inlet channel can be improved by reasonably designing the two-stage compression reference flow field through the second-stage shock wave compression, so that the overall performance of the aircraft is improved. In addition, compared with the traditional characteristic line method, the two-stage compression inner waverider reference flow field based on the inverse design method of the bending shock wave theory widens the design range of the air inlet channel, and provides more choices for aircraft structure matching.

Claims (3)

1. A two-stage compression inner waverider air inlet channel based on the inverse design method of the bending shock wave theory is characterized in that the two-stage compression inner waverider air inlet channel is arranged; the two-stage compression internal waverider air inlet is provided with a two-stage compression internal waverider air inlet compression profile, a two-stage compression internal waverider air inlet lip, a two-stage compression internal waverider air inlet shoulder and a two-stage compression internal waverider air inlet isolation section; the two-stage compression inner waverider air inlet compression profile turns flat at the shoulder of the two-stage compression inner waverider air inlet and enters a two-stage compression inner waverider air inlet isolation section, and the two-stage compression inner waverider air inlet isolation section equally straightens or expands and stretches the shoulder profile according to the outlet area requirement.

2. The two-stage compression inner waverider intake duct based on inverse bending shock wave theory design method as claimed in claim 1, wherein a lip position of the two-stage compression inner waverider intake duct is determined by a position of a reflection point of two incident shock waves of the two-stage compression inner waverider intake duct.

3. The two-stage compression internal waverider intake duct based on inverse bending shock theory design method of claim 1, wherein the outlet cross-section of the two-stage compression internal waverider intake duct is elliptical or rectangular-like.

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