CN114750973A - Longitudinal segmented multistage compression design method for osculating cone height super waverider precursor - Google Patents
Longitudinal segmented multistage compression design method for osculating cone height super waverider precursor Download PDFInfo
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Abstract
The invention discloses a longitudinal segmented multistage compression design method for osculating cone high-speed super-wavelet precursor, which relates to the technical field of design of a hypersonic aircraft air inlet precursor, and adopts the technical scheme that: the method comprises the following steps: 1) dividing the wave rider leading edge curve into a first-stage leading edge line and a multi-stage edge line according to design requirements; 2) extracting all flow field parameters of points on a cut-off curve of the first-stage compression surface to obtain a first-stage compression surface; 3) obtaining a next-stage compression curved surface by adopting streamline tracing; 4) length L according to two-stage compressioni、Li+1Obtaining a next-stage shock wave compression angle beta i by the flow field parameters of the previous-stage compression; 5) and adjusting the shock wave angle beta i in different osculating planes to ensure that the change of the shock wave angle is continuous. The design method can change the compression stages, the compression strength of different stages, the compression length of different stages and the like according to the performance requirement of the air inlet, and has larger compression strength, compression length of different stages and the like in the field of design of precursors of hypersonic aircraftThe potential for application of (1).
Description
Technical Field
The invention relates to the technical field of designing of a hypersonic aircraft air inlet forebody, in particular to a longitudinal segmented multistage compression design method of a osculating cone hypersonic wave forebody.
Background
The air-breathing hypersonic aerocraft takes the scramjet engine as power and can obtain oxygen from the air, so that no oxidant is required to be carried in the flying process, and high-speed long-range flight can be realized. The front body of the air-breathing hypersonic aircraft is tightly combined with the air inlet channel, the front body provides compressed air flow for the hypersonic aircraft, and the compression performance of the front body plays a decisive role in the performance of the air inlet channel and the performance of the scramjet.
The wave multiplier is used as a hypersonic speed and has a promising aerodynamic shape, can pre-compress hypersonic speed incoming flow and provides high-pressure and uniform air flow for the air inlet channel.
The compression performance of the waverider is closely related to the design of the shock angle, and if single-stage compression is adopted, the requirement of the air inlet channel airflow supercharging ratio can be met only by the large shock angle, but the pneumatic performance of the waverider precursor is influenced by the large shock angle, so that the aircraft generates large head raising moment and large resistance. The pressure increase ratio of the air inlet channel is improved on the premise of ensuring the aerodynamic performance by adopting the isentropic compression, but the length of a front body of the air inlet channel is very long due to the isentropic compression. Therefore, in order to improve the compression performance of the air inlet, a multi-stage compression design technology needs to be explored, the multi-stage compression technology of a two-dimensional model is relatively mature, but the actual aircraft is a three-dimensional model, and the adoption of the two-stage compression precursor can cause large overflow on two sides of the aircraft precursor, so that the pressure loss and the aerodynamic performance are reduced.
Disclosure of Invention
The invention aims to provide a osculating cone hypersonic aircraft forebody longitudinal segmentation multistage compression design method, provides a multistage compression technology capable of realizing longitudinal segmentation on the basis of osculating cone waverider, and aims at the requirements of the compression performance of an air inlet channel and a forebody of an air-breathing hypersonic aircraft.
The technical purpose of the invention is realized by the following technical scheme: a osculating cone height super waverider precursor longitudinal segmented multi-stage compression design method specifically comprises the following steps:
1) dividing the front edge curve of the waverider into a first-stage front edge line and a multi-stage edge line according to design requirements, so as to obtain the longitudinal three-stage length L of the waverider1、L2、L3……Li；
2) According to a first-stage leading edge line, solving reference flow fields in different osculating planes, tracking by adopting a flow line to obtain a first-stage lower surface flow line, cutting off the obtained flow line by taking the longitudinal length of the first stage as a limit, and extracting all flow field parameters of points on a cut-off curve of the first-stage compression surface to obtain a first-stage compression surface;
3) The outlet line of the front-stage compression surface and the edge line of the rear-stage compression surface jointly form a front edge line of the rear-stage compression surface; reestablishing the corresponding reference flow field circle center, incoming flow direction, Mach number and shock wave angle according to the geometrical relation of the next-stage compression surface, and obtaining the next-stage compression curved surface by adopting streamline tracing with the distance of the section of the next-stage compression outlet as the limit;
4) length L according to two-stage compressioni、Li+1And the previous stage pressureObtaining a compression angle beta i of the next-stage shock wave by the contracted flow field parameters;
5) adjusting the shock wave angle beta i in different osculating planes to ensure that the change of the shock wave angle is continuous;
6) constructing a local conical flow field according to the local Mach number, the speed, the flow direction and the shock wave angle, thereby obtaining a lower surface streamline corresponding to each characteristic point;
7) the streamline corresponding to the front edge line inside the next-stage compression is according to the length L of the next-stage compressioni+1The flow line is cut off to obtain an internal outlet line of the next stage of compression; the streamline corresponding to the next-stage edge line is according to the length L of the next-stage compressed segmenti+1Stopping to obtain two side outlet lines, wherein the obtained inner outlet line and the two side outlet lines form a next-stage compression surface;
8) the outlet line of the lower surface of the next stage of compression and the outlet line of the upper surface of the air inlet form the bottom surface of the wave-rider precursor, so that a multi-stage compression osculating pyramid wave-rider is formed.
In conclusion, the invention has the following beneficial effects:
1. based on osculating cone waverider design, compared with a cone guided waverider, the osculating cone waverider has more flexibility, and the outlet molded line of the lower surface of the air inlet channel can be freely designed and is better matched with an engine air inlet channel;
2. in order to ensure that the multistage compression shock waves in each osculating plane are converged at an inlet of an air inlet, a strict geometric relational expression of a segment length and a corresponding shock wave angle is established, and meanwhile, because the edge line of the osculating cone waverider is kept the same as a single-stage osculating cone waverider in the multistage compression design process, the designed waverider precursor can be ensured to strictly meet the waverider characteristic at the edge without pressure leakage, and the advantages of the waverider characteristic and the multistage compression are fully combined;
3. the method can change the shock angle at different positions according to the requirement to achieve the characteristic of changing the pressure distribution of the inlet of the air inlet;
4. the multi-stage compression precursor obtained by the method has high precompression capacity, can provide high-pressure low-speed relatively uniform air flow for the air inlet, has flexible and adjustable outlet profile of the air inlet, is convenient to match with the air inlet, simultaneously keeps high lift-drag ratio, and has obvious advantages compared with the traditional single-stage compression or isentropic compression.
Drawings
FIG. 1 is a schematic diagram of a one-stage compression osculating cone waverider in an embodiment of the present disclosure;
FIG. 2 is a schematic diagram of a two-stage compression osculating cone waverider in an embodiment of the present disclosure;
FIG. 3 is a schematic diagram of a three-level compression osculating cone waverider in an embodiment of the present disclosure;
FIG. 4 is a schematic diagram of a osculating cone waverider design method in an embodiment of the invention;
FIG. 5 is a schematic diagram of a two-stage compression geometry in an embodiment of the present invention;
FIG. 6 is a schematic diagram of a three-stage compression geometry in an embodiment of the present invention;
FIG. 7 is a comparison of spanwise shock angle distributions for an embodiment of the invention;
FIG. 8 is a cloud chart of pressure distribution of two-stage compression of osculating cone waverider in the embodiment of the invention;
FIG. 9 is a cloud chart of the pressure distribution of the osculating cone waverider under the second-stage compression in the embodiment of the invention;
FIG. 10 is a cloud graph of pressure distribution of three-stage compression of osculating cone waverider in the embodiment of the invention;
FIG. 11 is a cloud chart of surface pressure distribution under three-stage compression of osculating cone waverider in the embodiment of the invention.
Detailed Description
The present invention is described in further detail below with reference to figures 1-15.
Example (b): a osculating cone height super-waverider precursor longitudinal segmented multi-stage compression design method, as shown in fig. 1 to 15, comprising the following steps:
1) Dividing the front edge curve of the waverider into a first-stage front edge line and a multi-stage edge line according to design requirements, so as to obtain the longitudinal three-stage length L of the waverider1、L2、L3……Li；
2) According to a first-stage leading edge line, solving reference flow fields in different osculating planes, tracking by adopting a flow line to obtain a first-stage lower surface flow line, cutting off the obtained flow line by taking the longitudinal length of the first stage as a limit, and extracting all flow field parameters of points on a cut-off curve of the first-stage compression surface to obtain a first-stage compression surface;
3) the outlet line of the front-stage compression surface and the edge line of the rear-stage compression surface jointly form a front edge line of the rear-stage compression surface; reestablishing the corresponding reference flow field circle center, incoming flow direction, Mach number and shock wave angle according to the geometrical relation of the next-stage compression surface, and obtaining the next-stage compression curved surface by adopting streamline tracing with the distance of the section of the next-stage compression outlet as the limit;
4) length L according to two-stage compressioni、Li+1Obtaining a compression angle beta i of a next-stage shock wave by the flow field parameters of the previous-stage compression;
5) adjusting the shock wave angle beta i in different osculating planes to ensure that the change of the shock wave angle is continuous;
6) constructing a local conical flow field according to the local Mach number, the speed, the flow direction and the shock wave angle, thereby obtaining a lower surface streamline corresponding to each characteristic point;
7) The streamline corresponding to the front edge line inside the next-stage compression is according to the length L of the next-stage compressioni+1The flow line is cut off to obtain an internal outlet line of the next stage of compression; the streamline corresponding to the next-stage edge line is according to the length L of the next-stage compressed segmenti+1Stopping to obtain two side outlet lines, wherein the obtained inner outlet line and the two side outlet lines form a next-stage compression surface;
8) the lower surface outlet line of the next stage of compression and the upper surface outlet line of the air inlet form the bottom surface of the wave-rider precursor, so that a multi-stage compression osculating cone wave-rider is formed.
In this embodiment, a three-level waverider design is taken as an example:
dividing the wave multiplier front edge curve into a first-stage front edge line, a second-stage edge line and a third-stage edge line according to design requirements, so that the length of each of three longitudinal sections of the wave multiplier is L1、L2、L3；
Designing a first-stage compression surface from a leading edge line, obtaining a lower surface flow line of the first stage by solving reference flow fields in different osculating planes and adopting flow line tracking, cutting off the obtained flow line by taking the longitudinal length of the first stage as a limit, and extracting all flow field parameters of upper points of a cut-off curve of the first-stage compression surface;
the exit line of the first stage compression face and the second stage edge line together form a leading edge line of the second stage compression. At the moment, because the corresponding Mach number, speed, flow direction and pressure on the first-stage compression outlet line are changed, incoming flow parameters of flow fields at different angles along the kiss section are different, the circle center, incoming flow direction, Mach number and laser angle of the corresponding reference flow field need to be reestablished according to the geometric relation of the second-stage compression, and a second-stage compression curved surface is obtained by adopting streamline tracing with the distance of the second-stage outlet section as the limit;
Because the reference flow field in each osculating plane is independently designed, in order to ensure the consistency of the flow field of the lower surface of the second-stage compression, the shock wave angles in different osculating planes can be adjusted according to requirements, namely the shock wave angles in the second-stage compression plane also need to be designed, but along with the angle change of the osculating plane, the change of the shock wave angles must be continuous, otherwise, the distortion of the second-stage compression plane can occur;
the streamline corresponding to the second-stage internal leading edge line is compressed according to the second-stage compression length L2The streamline is cut off to obtain an internal outlet line, and the streamline corresponding to the second-stage edge line is according to the length L of the second-stage compression section2Stopping to obtain two side outlet lines, and forming a front edge line of three-stage compression by the two-stage compression obtained inner outlet line, the two side outlet lines and the third-stage edge line;
because the flow field parameters on the leading edge line of the three-stage compression are different and similar to the solution of the second-stage compression surface in the same way, the shock wave corresponding to the local three-stage compression and the second-stage compression shock wave in each kiss-cut angle are also fit on the inlet profile line of the lower surface of the air inlet channel according to L2、L3The length, the secondary shock angle, the secondary Mach number, the speed and other parameters of the three-stage shock wave are established to obtain a three-stage shock wave compression angle beta 3, wherein the three-stage shock wave compression angle can also be continuously changed in the transverse range according to the design;
Although theoretically, the primary, secondary and tertiary shock waves are required to be converged at one point on each kiss section, under the condition that the height of an unpowered cruise aircraft or an air inlet is not high, the secondary and tertiary compressed shock waves can not limit the position, but only require the longitudinal length;
after the three-stage shock wave compression angle in each kiss-cut angle is determined, a local conical flow field can be constructed according to local Mach number, speed, flow direction and shock wave angle, so that a lower surface streamline corresponding to each characteristic point is obtained;
all streamlines corresponding to the three-stage compression front edge are compressed according to the third-stage compression length L3The restriction of (2) is carried out with streamline cut-off to form a third stage compression outlet line, thereby forming a third stage compression surface;
the bottom surface of the waverider precursor is formed by the three-stage compression lower surface outlet line and the air inlet channel upper surface outlet line, so that the upper surface, the lower surface and the bottom surface of the osculating cone three-stage compression waverider precursor are all generated.
The working principle is as follows: different from a cone guided wave rider, the output molded line of the wave rider designed based on osculating theory can be any two-order conductible continuous curve or can be a multi-section curve connection, as long as the two-order continuity of the connecting point is ensured, the method assumes that flow lines in osculating planes cannot interfere with each other, and a new shock wave flow field is obtained by superposing conical shock waves at different radiuses.
The configuration of the wave multiplier can be determined by giving an ICC (ICC) lower surface shock Curve, a Flow Capture Curve upper surface exit line and a shock angle.
The curvature radius of any node on the shock curve can be calculated by adopting the following formula:
the above is just the curvature radius of the curve at the point M (x, y), and the center M of the curvature circle can be obtained·Having coordinates of
As shown in fig. 4, each curvature radius corresponds to a local conical flow field, ICC is firstly dispersed, then a new local reference conical flow field can be constructed by the curvature radius of each discrete point and the curvature center of the circle, the intersection point of the curvature radius and FCC is reversely tracked to obtain a leading edge point, the leading edge point is tracked by a streamline to obtain a corresponding lower surface flow field, so that a corresponding streamline can be obtained in each osculating plane, the streamlines are lofted to form the lower surface of a waverider, and the upper surface is parallel to the incoming flow, so that the required osculating cone waverider can be obtained;
(1) two-stage compression osculating cone waverider
As shown in fig. 6, given mach number, laser angle, lower surface exit profile and upper surface exit profile, a pyramid waverider can be osculating. The basic principle of two-stage compression can refer to the design method of a multi-stage cone-guide waverider. The geometrical relationship that different osculating planes need to satisfy needs to be explained here, for example, the local osculating plane where O-O' -B-C is located is given in FIG. 7 for explanation:
If the length of the wave-rider of the osculating plane of the local area is L and the length of the first stage is L1Second order length of l2. The distance of the point A from the axis is dAFirst order shock angle is beta1Mach number at primary exit is Ma2The angle between the first-stage outlet speed and the local horizontal axis
The point being at a distance d from the local horizontal axis1Therefore, the following relation formula can be satisfied by the secondary laser angle:
a corresponding secondary shock wave angle can be obtained for each kiss section, so that the secondary shock waves at the local outlet are matched with the primary shock waves;
in particular, to the localThe method comprises the following steps of cutting a section, obtaining a lower surface outlet streamline parameter through first-stage compression and streamline tracing, and obtaining a lower surface Mach number Ma after the length of a first-stage wave multiplier is determined2iLocal coordinate (y)i，xi，zi) Obtaining the local polar angle through coordinate transformation,
the radius of the local shock wave is determined,
Ri＝zi tan(β1i)
the distance of the exit location from the local reference axis,
so that a polar angle at one stage of compression can be obtained,
θi＝atan(d1i/Ri tan(β1i))
so far, the Mach number, the leading edge point coordinate, the speed direction and the secondary compression shock wave angle of the primary compression outlet are obtained, and the streamline starting from the secondary leading edge point in each tangent plane is obtained by continuously adopting the streamline tracing technology. The streamline obtained by the first-stage compression is lofted to obtain a first-stage compression surface, and the second-stage compression streamline can obtain a second-stage compression surface, so that the whole wave-rider body configuration is obtained;
(2) Three-stage compression osculating cone waverider
The three-level osculating cone waverider design is similar to the two-level compression osculating cone waverider, described herein in terms of the three-level compression geometry within the local osculating plane, as shown in FIG. 8, wherein1、l2、l3Respectively representing the lengths corresponding to the three-stage compression; AL, LM and MN are respectively the lower surface streamline corresponding to the third stage; ma1、Ma2And Ma3Respectively representing the incoming flow Mach numbers corresponding to three-stage compression. The distance of the point A from the axis is dAFirst order shock angle of beta1Mach number at primary exit is Ma2The angle between the first stage exit velocity and the local horizontal axis
The point is at a distance d from the local horizontal axis1The method can be obtained by adopting a relational expression of two-stage compression,
solving the node of the first-stage outlet by adopting a conical flow field, and obtaining the Mach number Ma of the second-stage outlet by the same method after the position of the outlet is given3Second stage exit velocity included angle with local horizontal axis
The point is at a distance d from the local horizontal axis2To ensure that all exit shock converges at the precursor exit location, the shock angle β3The following relational expression is satisfied,
so far, the tertiary shock wave angle under different expansion angles is obtained, and the tertiary compression streamline of section under every expansion angle also can be worked out, and the primary compression streamline obtains the primary compression face, and the secondary compression streamline obtains the secondary compression face, and the tertiary compression streamline obtains tertiary compression face.
It should be noted that when the above principle is used to solve in practice, the situation that the compression angle of the next-stage shock wave is not understood by an object is faced. The reason is mainly that for the conical flow field, after the position of the outlet is determined, the Mach number of the lower surface of the waverider is gradually increased from the middle to the two sides, meanwhile, the length corresponding to the local first-stage compression is gradually reduced, and the lengths of the second-stage compression are equal, so that the compression angle of the second-stage shock wave obtained by the second-stage solution is possibly smaller than the corresponding Mach angle. As shown in the figure, when non-physical understanding is met in the actual design process, the size of the shock wave angle needs to be correspondingly adjusted so as to ensure that the streamline is solvable, and when the shock wave angle obtained through calculation is too small, the local shock wave angle can be increased so as to make the flow field solvable.
The present embodiment is only for explaining the present invention, and it is not limited to the present invention, and those skilled in the art can make modifications of the present embodiment without inventive contribution as needed after reading the present specification, but all of them are protected by patent law within the scope of the claims of the present invention.
Claims (1)
1. A osculating cone height super waverider precursor longitudinal segmentation multi-stage compression design method is characterized by comprising the following steps: the method specifically comprises the following steps:
1) Dividing the front edge curve of the waverider into a first-stage front edge line and a multi-stage edge line according to design requirements, so as to obtain the longitudinal three-stage length L of the waverider1、L2、L3……Li；
2) According to a first-stage leading edge line, solving reference flow fields in different osculating planes, tracking by adopting a flow line to obtain a first-stage lower surface flow line, cutting off the obtained flow line by taking the longitudinal length of the first stage as a limit, and extracting all flow field parameters of points on a cut-off curve of the first-stage compression surface to obtain a first-stage compression surface;
3) the outlet line of the front-stage compression surface and the edge line of the rear-stage compression surface jointly form a front edge line of the rear-stage compression surface; reestablishing the corresponding center of a circle of a reference flow field, an incoming flow direction, a Mach number and a shock wave angle according to the geometrical relation of the next-stage compression surface, and obtaining the next-stage compression curved surface by adopting streamline tracing with the distance of the section of the next-stage compression outlet as a limit;
4) length L according to two-stage compressioni、Li+1Obtaining a compression angle beta i of a next-stage shock wave by the flow field parameters of the previous-stage compression;
5) adjusting the shock wave angle beta i in different osculating planes to ensure that the change of the shock wave angle is continuous;
6) constructing a local conical flow field according to the local Mach number, the speed, the flow direction and the shock wave angle, thereby obtaining a lower surface streamline corresponding to each characteristic point;
7) The streamline corresponding to the front edge line inside the next-stage compression is according to the length L of the next-stage compressioni+1The restriction of (2) is carried out with streamline cutoff to obtain an internal outlet line of the next stage of compression; last level edge line correspondenceAccording to the length L of the last stage of compression sectioni+1Stopping to obtain two side outlet lines, wherein the obtained inner outlet line and the two side outlet lines form a next-stage compression surface;
8) the outlet line of the lower surface of the next stage of compression and the outlet line of the upper surface of the air inlet form the bottom surface of the wave-rider precursor, so that a multi-stage compression osculating pyramid wave-rider is formed.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116341106A (en) * | 2023-03-14 | 2023-06-27 | 南京航空航天大学 | Strong-expansion-direction pressure gradient compression surface design method based on flow field similarity transformation |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105151316A (en) * | 2015-09-24 | 2015-12-16 | 中国人民解放军国防科学技术大学 | Design method of gliding-and-cruising two-stage waverider based on variable shock wave angles and osculating cone principle |
| CN105667811A (en) * | 2016-01-27 | 2016-06-15 | 南京航空航天大学 | Design method for multi-stage coupling integrated structure of front body and air inflow channel of hypersonic aircraft |
-
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- 2022-03-26 CN CN202210304413.3A patent/CN114750973A/en not_active Withdrawn
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105151316A (en) * | 2015-09-24 | 2015-12-16 | 中国人民解放军国防科学技术大学 | Design method of gliding-and-cruising two-stage waverider based on variable shock wave angles and osculating cone principle |
| CN105667811A (en) * | 2016-01-27 | 2016-06-15 | 南京航空航天大学 | Design method for multi-stage coupling integrated structure of front body and air inflow channel of hypersonic aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 陈立立: "参数化高超声速巡航飞行器组合布局设计与气动优化分析", 中国博士学位论文全文数据库 (工程科技Ⅱ辑), 15 January 2022 (2022-01-15), pages 118 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116341106A (en) * | 2023-03-14 | 2023-06-27 | 南京航空航天大学 | Strong-expansion-direction pressure gradient compression surface design method based on flow field similarity transformation |
| CN116341106B (en) * | 2023-03-14 | 2024-06-07 | 南京航空航天大学 | Strong-expansion-direction pressure gradient compression surface design method based on flow field similarity transformation |
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Application publication date: 20220715 |