CN213450609U - Full three-dimensional inward-rotation air inlet channel based on bending shock wave theory inverse design method - Google Patents
Full three-dimensional inward-rotation air inlet channel based on bending shock wave theory inverse design method Download PDFInfo
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Abstract
A full three-dimensional inward-turning air inlet based on a bending shock wave theory inverse design method relates to the field of hypersonic speed air inlets in near space, and comprises a full three-dimensional inward-turning air inlet compression profile, an air inlet lip, an air inlet shoulder and a full three-dimensional inward-turning air inlet isolation section; the compression molded surface of the full three-dimensional inward turning air inlet channel is turned flat at the shoulder part of the air inlet channel and enters the isolation section of the full three-dimensional inward turning air inlet channel; the inlet lip is positioned at the position where the compression molded surface of the full three-dimensional inward turning inlet corresponds to the incident shock wave cut-off; the air inlet shoulder is positioned at the cut-off position of the corresponding reflection shock wave of the compression profile of the full three-dimensional inward turning air inlet. The full flow is ensured to capture the incoming flow, the thrust of the engine is increased, and the outflow resistance is 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.
Description
Technical Field
The utility model relates to a close on space hypersonic inlet duct field, especially relate to a full three-dimensional adversion intake duct based on crooked shock wave theory inverse design method.
Background
The development of the adjacent space aircraft relates to national safety and peaceful space utilization, and is one of the focuses of the international competition for space-capturing technology at present. The world's strong nations, represented by The United states and Russia, have vigorously pursued their Hypersonic Flight development programs (Joseph, M.H, James S.M. Richard C.M., The X-51A Scramjet Engine Flight recommendation Program,15th AIAA International Space plants and Hypersonic Systems and Technologies Conference, 2008). Air intake ducts are a major component in the propulsion system of hypersonic aircraft. It is located in the front of the aircraft, and is directly connected with the front body of the hypersonic aircraft, and plays the role of compressing incoming flow and providing high-energy airflow as much as possible for the downstream. Through long-term development, a series of hypersonic air inlet forms are proposed, which mainly comprise: the two-dimensional air inlet, the axial symmetric air inlet and the lateral pressure air inlet are researched according to the design method, the flow characteristic, the working characteristic, the engineering design research and the like of the two-dimensional air inlet, the axial symmetric air inlet and the lateral pressure air inlet. In addition, foreign researchers also provide a series of three-dimensional internally-contracted hypersonic air inlet design ideas and schemes. Such as: streamlining the Busemann Inlet channel proposed by F.S. Billing, university of John Hopkins, USA (Brien, T.F. and Collille, J.R. analytical Computation of Leading Edge traversal Effects on acquired Busemann Inlet Performance, AIAA paper, 2007); the "Funnel" type inlet concept proposed by P.K.Ajay et al of Astrox corporation, USA (Billing, F.S. and Kothari, A.P., Streamline training: Technique for Designing Hypersonic Vehicles, Journal of Propulsion and Power, Vol.16, No.3,2000, pp.465-471); the U.S. Aerospace research center, m.k.smart et al, proposed ideas to smoothly convert a Rectangular Inlet to an oval outlet (Smart, m.k.and Trexler, c.a.mach4performance of a Fixed-Geometry Hypersonic Inlet with Rectangular-to-elastic Shape Transition,41st AIAA Aerospace Sciences Meeting & exit, 2002), and the like. In China, scholars such as Yongcheng and the like firstly apply the outer-flow waverider theory to the research of the inner flow of the air inlet, and a three-dimensional inner-contraction hypersonic air inlet called an inner waverider is provided. The numerical simulation and the high enthalpy wind tunnel test prove that: in a design state, the air inlet can capture incoming flow at full flow; in a non-design state, the air inlet channel can obviously improve the working capacity of low Mach number by the automatic overflow of the inlet, thereby having better overall characteristics.
Although various studies have made significant progress in the field of hypersonic inlet duct research, component performance is also being improved. However, so far, the three-dimensional inward-turning inlet inversion design adopts an axisymmetric reference flow field of a given axisymmetric shock wave, and then utilizes a streamline tracing technology to obtain a corresponding profile. However, the three-dimensional inward-turning air inlet channel obtained based on the axisymmetric reference flow field does not have full three-dimensional flow, and only has pseudo three-dimensional flow without transverse flow. At present, scientific researchers have not found an effective method for obtaining a full three-dimensional reference flow field so as to obtain a three-dimensional inward-turning air inlet channel with full three-dimensional flow. And the cross flow plays a crucial role in improving the performance of the aircraft. Meanwhile, scientific researchers generally adopt a traditional characteristic line method to carry out reverse design of a reference flow field, programming is complex, stability is poor, the selection range of the basic 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 full three-dimensional inward-turning inlet based on a bending shock wave theory inverse design method is lacked.
Disclosure of Invention
An object of the utility model is to solve the above-mentioned problem among the prior art, provide a full three-dimensional adversion intake duct based on the anti-design method of bending shock wave theory.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a full three-dimensional inward-turning air inlet based on a bending shock wave theory inverse design method comprises a full three-dimensional inward-turning air inlet compression profile, an air inlet lip, an air inlet shoulder and a full three-dimensional inward-turning air inlet isolation section; the compression molded surface of the full three-dimensional inward turning air inlet channel is turned flat at the shoulder part of the air inlet channel and enters the isolation section of the full three-dimensional inward turning air inlet channel; the inlet lip is positioned at the position where the compression molded surface of the full three-dimensional inward turning air passage corresponds to the incident shock wave cut-off; the air inlet shoulder is positioned at the cut-off position of the corresponding reflection shock wave of the compression profile of the full three-dimensional inward turning air inlet.
The compression molded surface of the full three-dimensional inward-rotation air inlet channel is a non-axisymmetric curved surface and is in bilateral symmetry.
The full three-dimensional inward-rotation air inlet passage isolation section is a non-axisymmetric curved surface and is bilaterally symmetric.
Compared with the prior art, the utility model discloses technical scheme obtains beneficial effect is:
the utility model simultaneously considers the outlet performance of the three-dimensional inward-rotation air inlet channel and the transverse flow of the three-dimensional inward-rotation air inlet channel, and realizes the full three-dimensional flow reverse design of the known shock wave; the full three-dimensional inward rotation air inlet channel ensures that the full flow captures incoming flow, and reduces the outflow resistance while increasing the thrust of the engine; 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. In addition, compared with the traditional characteristic line method, the bending shock wave theory has the advantages of higher calculation efficiency, higher precision and wider range. The design scope of three-dimensional adversion intake duct is widened through rational design lateral flow to three-dimensional adversion intake duct to further improve intake duct working property.
Drawings
Fig. 1 is a schematic diagram of a reference flow field of a scheme of a full three-dimensional inward-turning air inlet channel based on a bending shock wave theory.
FIG. 2 is a schematic diagram of the solution of bending shock theory.
FIG. 3 is a two-dimensional projection diagram of the inlet and outlet cross sections of a full three-dimensional inward-turning air inlet scheme based on the bending shock wave theory.
FIG. 4 is a schematic diagram of a half-section structure of a full three-dimensional inward-turning air inlet scheme based on a bending shock wave theory.
Fig. 5 is a schematic bottom view of a full three-dimensional inward-turning air inlet scheme based on the bending shock wave theory.
Fig. 6 is a general structural diagram of a full three-dimensional inward-turning air inlet scheme based on a bending shock wave theory.
Detailed Description
In order to make the technical problem, technical solution and beneficial effects to be solved by the present invention clearer and more obvious, the following description is made in detail with reference to the accompanying drawings and embodiments.
As shown in fig. 6, the utility model comprises a compression profile 13 of the full three-dimensional inward-turning air inlet, an air inlet lip 8, an air inlet shoulder 14, and a full three-dimensional inward-turning air inlet isolation section 15, and the three-dimensional inward-turning air inlet can realize internal waverider;
the compression molded surface 13 of the full three-dimensional inward turning air inlet channel is turned flat at the shoulder part 14 of the air inlet channel and enters the isolation section 15 of the full three-dimensional inward turning air inlet channel; the inlet lip 8 is positioned at the stop position of the compression molded surface 13 of the full three-dimensional inward turning inlet corresponding to the incident shock wave; the air inlet shoulder 14 is positioned at the position where the compression molded surface 13 of the full three-dimensional inward turning air inlet corresponds to the reflected shock wave cut-off; the compression molded surface of the full three-dimensional inward-turning air inlet channel is a 13-non-axisymmetric curved surface and is bilaterally symmetric; the full three-dimensional inward-turning air inlet passage isolation section 15 is a non-axisymmetric curved surface and is bilaterally symmetric.
As shown in fig. 1 to 6, the design method of the present invention comprises the following steps:
1) appointing a full three-dimensional incident shock wave 1 in a full three-dimensional reference flow field according to design requirements, wherein the full three-dimensional incident shock wave 1 is designed in an elliptical or other non-axisymmetric shape; due to the non-axial symmetry of the full three-dimensional reference flow field, the profiles of the full three-dimensional incident shock waves 1 in different reference planes are different, and similarly, the compression profiles 3 and the reflection shock wave profiles 2 in different reference planes to be solved are also different.
2) Dispersing the full three-dimensional incident shock waves into a series of reference planes, and solving a corresponding full three-dimensional internal contraction basic flow field by using a bending shock wave theory according to the full three-dimensional incident shock wave angle, the shock wave curvature and the wave-rear parameters;
specifically, the solving process is performed in different reference planes 11, as shown in fig. 2, the lateral projection of the full three-dimensional incident shock wave 1 is the full three-dimensional inward-turning air inlet leading edge capturing profile 10, according to the shock wave angle, shock wave curvature and wave rear parameters of the discrete point (coinciding with the full three-dimensional inward-turning air inlet leading edge point 6 in position) on the full three-dimensional incident shock wave 1, the compression profiles 3 in the different reference planes 11 are obtained by using the bending shock wave theory, and the compression profiles 3 in all the reference planes 11 are combined to obtain the corresponding full three-dimensional inward-turning flow field.
The governing equation of bending shock theory is as follows:
wherein P is pressure, δ is a flow angle, μ is a Mach angle, ρ is density, V is a flow direction velocity, w is a circumferential velocity, γ is a specific heat ratio, j is a judgment factor, s is a streamline, l is a characteristic line, φ is a circumferential angle, P is a derivative of pressure along the streamline, D is a derivative of an airflow angle along the streamline, y is an ordinate in a Cartesian coordinate system, and a is a local sound velocity.
3) Designing an outlet cross section of the full three-dimensional inward turning air inlet, and performing streamline tracing in the full three-dimensional inward shrinkage basic flow field in the step 2) to obtain a hypersonic speed full three-dimensional inward turning air inlet compression molded surface 13; the shape of the cross section is elliptical or similar to rectangular;
specifically, in the full three-dimensional internal contraction flow field, the three-dimensional coordinates (x, y, z) of each point on the effective flow line 5 in different reference planes 11 are obtained by solving by using the coordinates (x, y) of each point on the outlet section 9, namely the intersection point 7 of the flow line and the reflected shock wave, and then the three-dimensional coordinates of each point on the effective flow line 5 are combined to obtain the flow line tracking compression molded line 12. The streamline tracing compression profiles 12 in different reference planes 11 are combined to form a full three-dimensional inward turning inlet compression profile 13.
4) The hypersonic speed all-three-dimensional internal rotation air inlet channel is geometrically constructed on the basis of the compression molded surface 13 of the all-three-dimensional internal rotation air inlet channel: according to the area requirement of an outlet 16 of the isolation section of the full three-dimensional inward turning air inlet channel, the shoulder molded lines 14 are stretched in an equal straight or expanding mode to obtain the isolation section 15 of the full three-dimensional inward turning air inlet channel, and the full three-dimensional inward turning air inlet channel based on the bending shock wave theory in the designed flight state is obtained.
The utility model discloses three-dimensional adversion intake duct is when keeping three-dimensional adversion intake duct advantage in the whole three-dimensional adversion intake duct based on crooked shock wave theory, realizes the inside three-dimensional flow of three-dimensional adversion intake duct. The working performance of the air inlet channel can be improved by reasonably designing the full three-dimensional reference flow field through the three-dimensional transverse flow of the air flow, so that the overall performance of the aircraft is improved. In addition, the design range of the air inlet channel is widened by the aid of the full three-dimensional reference flow field, and more choices are provided for aircraft structure matching.
Claims (3)
1. The utility model provides a full three-dimensional adversion intake duct based on reverse design method of bending shock wave theory which characterized in that: the full three-dimensional inward turning air inlet comprises a full three-dimensional inward turning air inlet compression molded surface, an air inlet lip, an air inlet shoulder and a full three-dimensional inward turning air inlet isolating section; the compression molded surface of the full three-dimensional inward turning air inlet channel is turned flat at the shoulder part of the air inlet channel and enters the isolation section of the full three-dimensional inward turning air inlet channel; the inlet lip is positioned at the position where the compression molded surface of the full three-dimensional inward turning inlet corresponds to the incident shock wave cut-off; the air inlet shoulder is positioned at the cut-off position of the corresponding reflection shock wave of the compression profile of the full three-dimensional inward turning air inlet.
2. The full three-dimensional inward turning air inlet channel based on the bending shock wave theory inverse design method as claimed in claim 1, characterized in that: the compression molded surface of the full three-dimensional inward-rotation air inlet channel is a non-axisymmetric curved surface and is in bilateral symmetry.
3. The full three-dimensional inward turning air inlet channel based on the bending shock wave theory inverse design method as claimed in claim 1, characterized in that: the full three-dimensional inward-rotation air inlet passage isolation section is a non-axisymmetric curved surface and is bilaterally symmetric.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113868770A (en) * | 2021-10-11 | 2021-12-31 | 厦门大学 | Inverse design method for combined air inlet channel based on three-dimensional bending shock wave |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113868770A (en) * | 2021-10-11 | 2021-12-31 | 厦门大学 | Inverse design method for combined air inlet channel based on three-dimensional bending shock wave |
| CN113868770B (en) * | 2021-10-11 | 2024-05-31 | 厦门大学 | Reverse design method for combined air inlet channel based on three-dimensional bending shock wave |
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