CN113306740B - Two-stage compression inner waverider air inlet channel inverse design method based on bending shock wave theory - Google Patents
Two-stage compression inner waverider air inlet channel inverse design method based on bending shock wave theory Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
A two-stage compression inner waverider air inlet inverse design method based on a bending shock wave theory relates to a hypersonic air inlet in a near space. And designating a two-stage compression reference flow field containing two three-dimensional incident shock waves and one three-dimensional reflected shock wave according to design requirements, wherein the three-dimensional incident shock waves and the reflected shock waves are designed in a bent axisymmetric shape. Dispersing the first three-dimensional bending incident shock wave into a series of reference planes, distributing the flow direction angles in each two-dimensional plane according to the incident shock wave angle, the shock wave curvature and the reflected wave, solving the corresponding two-stage compression reference flow field pneumatic parameters, and superposing the planes to obtain the three-dimensional inner contraction reference flow field. Designing the inlet section of the two-stage compression internal waverider air inlet, and tracing the flow line in the reference flow field. Geometrically constructing a hypersonic two-stage compression inner waverider air inlet on the basis of a compression profile; and according to the outlet area requirement, straightening or expanding and stretching the shoulder molded lines to obtain the two-stage compression internal waverider intake duct isolation section. The working performance of the air inlet channel is improved.
Description
Technical Field
The invention relates to a hypersonic inlet channel in a near space, in particular to a two-stage compression inner waverider inlet channel inverse design method based on a 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) 1252-1255.); the HYCAUSE Program proposed in the United states and Australia developed an elliptical inlet adduction-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): 913-920.); 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.); performance comparison of internal waverider-type air inlet with typical lateral pressure-type air inlet [ J ] of Zhu Xiang and the like based on ICFC flow field]Propulsion technology, 2011,032 (002): 151-158). 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): 408-416). 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.); inside-waverider air inlet with variable cross-section designed by osculating axisymmetric theory in Yongyan Cheng et al (Yongyan Cheng, liangdewang. Three-dimensional variable-cross-section hypersonic air inlet [ J ] based on inside-waverider concept]China science, 2009 (08): 127-138), the air inlet can realize full-flow capture and simultaneously control the cross-sectional shapes of an inlet and an outlet; 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.. The internal waverider-derived hypersonic air intake duct based on arbitrary shock wave shape and design method thereof: china, 101392685[ P ], [ 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 invention aims to provide a two-stage compression inner waverider air inlet channel inverse design method based on a bending shock wave theory.
The scheme of the two-stage compression internal waverider air inlet based on the bending shock wave theory is provided with the two-stage compression internal waverider air inlet; the two-stage compression internal waverider air inlet is provided with two-section compression profiles of the two-stage compression internal waverider air inlet, lips of the two-stage compression internal waverider air inlet, shoulders of the two-stage compression internal waverider air inlet and an isolation section of the two-stage compression internal waverider air inlet; and the second section profile of the two-stage compression internal waverider air inlet channel is turned flat at the shoulder part of the two-stage compression internal waverider air inlet channel and enters the two-stage compression internal waverider air inlet channel isolation section.
The invention comprises the following steps:
(1) And designating a two-stage compression reference flow field containing two three-dimensional incident shock waves and one three-dimensional reflection shock wave according to design requirements, wherein the three-dimensional incident shock waves and the reflection shock waves are designed in a bent axisymmetric shape.
(2) Dispersing the first three-dimensional bending incident shock wave into a series of reference planes, distributing the incident shock wave angle, the shock wave curvature and the flow direction angle after reflection in each two-dimensional plane, solving the corresponding pneumatic parameters of the two-stage compression reference flow field by using a bending shock wave equation by combining a multi-stage compression theory, and finally superposing the planes to obtain the three-dimensional internal contraction reference flow field.
(3) Designing an inlet section of a two-stage compression internal waverider air inlet, wherein the section is elliptical or rectangular-like, and performing streamline tracing in the reference flow field in the step (1).
(4) Geometrically constructing the hypersonic two-stage compression inner waverider air inlet on the basis of the compression profile; and according to the outlet area requirement, straightening or expanding and stretching the shoulder molded lines to obtain the two-stage compression internal waverider intake duct isolation section.
In step (4), the geometric configuration includes an inlet compression profile, a backward equal straight or expanding stretch of the isolated section.
The invention has the following advantages: the two-stage compression internal waverider air inlet channel based on the bending shock wave theory generated by the design method simultaneously considers 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, realizes the controllable design of a two-stage compression flow field with a wave system structure and 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 obtained reference flow field has wider range. The design idea of the 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 schematic diagram of a reference flow field of a two-stage compression inner-multiplied-wave inlet scheme based on a bending shock wave theory.
FIG. 2 is a schematic diagram of a solution to bending shock theory.
FIG. 3 is a two-dimensional projection of the inlet and outlet cross sections of a two-stage compression internal waverider air inlet scheme based on flexural shock theory.
FIG. 4 is a schematic diagram of a half-section structure of a two-stage compression internal waverider inlet scheme based on a bending shock wave theory.
FIG. 5 is a schematic bottom view of a two-stage compression internal waverider inlet scheme based on the bending shock theory.
FIG. 6 is a schematic diagram of the general structure of a two-stage compression internal waverider inlet scheme based on the bending shock theory.
Each of the labels in the figure is: 1 represents two-path incident shock waves of a two-stage compression reference flow field, 2 represents reflection shock waves of the two-stage compression reference flow field, 3 represents two-stage compression profile of different reference planes of the two-stage compression reference flow field, 4 represents a center (body) line of the two-stage compression reference flow field, 5 represents an effective part of a streamline of the two-stage compression reference flow field, 6 represents the position of a front edge point of the two-stage compression inner waverider air inlet, 7 represents an intersection point of the streamline and the reflection shock waves, 8 represents a lip of the two-stage compression inner waverider air inlet, 9 represents an oval outlet section of the two-stage compression inner waverider air inlet, 10 represents a front edge capturing profile of the two-stage compression inner waverider air inlet, 11 represents different reference planes, 12 represents two-stage compression profiles obtained by streamline tracking, 13 represents two-stage compression inner waverider air inlet two-stage compression profiles, 14 represents a shoulder profile of the two-stage compression inner waverider air inlet, 15 represents a two-stage compression inner waverider air inlet isolating section, and 16 represents an outlet of the two-stage compression inner waverider air inlet isolating section.
Detailed Description
The following examples will further illustrate the present invention with reference to the accompanying drawings.
As shown in fig. 1 to 6, the design scheme of the two-stage compression internal waverider intake duct based on the bending shock wave theory includes a two-stage compression internal waverider intake duct, which is composed of two-stage compression internal waverider intake duct two-section compression profiles 13, two-stage compression internal waverider intake duct lips 8, two-stage compression internal waverider intake duct shoulder profiles 14 and two-stage compression internal waverider intake duct isolation segments 15, and can realize internal waverider. The second section of the compression profile 13 of the two-stage compression internal waverider intake duct enters the isolation section 15 of the two-stage compression internal waverider intake duct at the shoulder profile 14 of the two-stage compression internal waverider intake duct, and the position of the lip 8 of the two-stage compression internal waverider intake duct is determined by the position of the two-stage incident shock wave reflection point of the two-stage compression internal waverider intake duct under the design condition.
The method for designing the inverse of the two-stage compression internal waverider air inlet based on the bending shock wave theory mainly comprises the following steps:
(1) And two three-dimensional bending axisymmetric incident shock waves and one three-dimensional bending axisymmetric reflected shock wave at the inlet of the two-stage compression reference flow field are designated according to design requirements. Due to the axial symmetry of the two-stage compression reference flow field, the two incident shock wave 1-shaped lines of the two-stage compression reference flow field in different reference planes are the same. Similarly, the two sections of compression molded lines 3 of different reference planes of the two-stage compression reference flow field to be solved and the two-stage compression reference flow field reflected shock waves 2 are also the same.
(2) And dispersing the first bending incident shock wave into a series of reference planes, and solving a corresponding two-stage compression inner waverider reference flow field by using a bending shock wave theory according to an incident shock wave angle, a shock wave curvature and a distribution rule of flow direction angles after reflection. The solving process is carried out in a two-dimensional reference plane, as shown in fig. 2, according to the shock angle, shock curvature and wave front inflow parameters of discrete points on a first shock wave in an incident shock wave 1, a first section of a compressed molded line in different reference planes 11 is obtained by solving through a bending shock wave theory, relevant parameters of a second shock wave are obtained by interpolation in a dependency domain of the first shock wave according to a preset second shock wave, and a second section of the compressed molded line is obtained by solving through combining the bending shock wave theory and a given wave rear flow direction angle distribution; and combining the compressed molded lines in all the different reference planes 11 to obtain the corresponding three-dimensional internal contracted reference flow field. The bending shock wave theory control equation is shown in the following graph, wherein P is pressure, delta is a flow angle, mu is a Mach angle, rho is density, V is speed, gamma is a specific heat ratio, j is a judgment factor, s is a streamline, l is a characteristic line, P is a derivative of pressure along the streamline, and D is a derivative of an airflow angle along the streamline.
(3) Designing an inlet section of a two-stage compression internal waverider air inlet, wherein the section is elliptical or rectangular-like, and performing streamline tracing in the reference flow field in the step (1). Firstly, in a two-stage compression internal waverider reference flow field, the coordinates (x, y) of each point on an inlet section 10 are utilized to solve to obtain the three-dimensional coordinates (x, y, z) of each point on the effective part 5 of the two-stage compression reference flow field flow lines in different reference planes 11, and then the three-dimensional coordinates of each point on the effective part 5 of the two-stage compression reference flow field flow lines are combined to obtain a compression profile 12. Two sections of compression molded lines 12 obtained by tracing flow lines in different reference planes 11 are combined to form a two-section compression molded surface 13 of a two-stage compression internal waverider air inlet.
(4) And geometrically constructing the hypersonic speed two-stage compression internal waverider air inlet on the basis of the two-stage compression internal waverider air inlet two-stage compression molded surface 13. And (3) according to the outlet area requirement, straightening or expanding and stretching the shoulder molded lines 14 of the two-stage compression internal waverider inlet channel to obtain a two-stage compression internal waverider inlet channel isolation section 15. And obtaining a two-stage compression internal waverider air inlet based on a bending shock wave theory in a designed flight state.
The two-stage compression internal waverider air inlet scheme based on the bending shock wave theory realizes the two-stage compression inside the internal waverider air inlet while maintaining the advantages of the internal waverider air inlet. 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 bending shock wave theory inverse design method widens the design range of the air inlet channel, and provides more choices for aircraft structure matching.
Claims (3)
1. The two-stage compression inner waverider air inlet channel inverse design method based on the bending shock wave theory is characterized by comprising the following steps of:
(1) According to design requirements, a two-stage compression reference flow field containing two three-dimensional incident shock waves and one three-dimensional reflected shock wave is designated, and the three-dimensional incident shock waves and the reflected shock waves are designed in a bent axisymmetric shape;
(2) Dispersing the first curved incident shock wave into a series of reference planes; in each two-dimensional reference plane, according to the shock wave angle, the shock wave curvature and the wave front incoming flow parameters of the first incident shock wave, solving by using a bending shock wave theory to obtain a first section of compression molded line; interpolating in the dependence domain of the first incident shock wave according to a preset second incident shock wave to obtain relevant parameters of the second incident shock wave, solving by combining the bending shock wave theory with the given wave-rear flow direction angle distribution to obtain a second section of compression molded line, and obtaining a corresponding two-stage compression inner multiplier wave reference flow field; combining the compression molded lines in all reference planes to obtain a corresponding three-dimensional internal contraction reference flow field;
(3) Designing an inlet cross section of a two-stage compression internal waverider intake duct, and performing streamline tracing in the two-stage compression reference flow field in the step (1);
(4) Geometrically constructing a hypersonic two-stage compression inner waverider air inlet on the basis of a compression profile; and according to the outlet area requirement, straightening or expanding and stretching the shoulder molded lines to obtain the two-stage compression internal waverider intake duct isolation section.
2. The inverse design method for a two-stage compression internal waverider based on the bending shock wave theory as claimed in claim 1, wherein in the step (3), the cross-sectional shape is an ellipse or a rectangle.
3. The method for designing a two-stage compression internal waverider intake duct according to claim 1, wherein in step (4), the geometric configuration includes intake compression profile, backward equal-length isolation section or expansion and stretching.
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