CN108629108A - Design method of parametric wave rider with controllable fuselage and wing parts - Google Patents
Design method of parametric wave rider with controllable fuselage and wing parts Download PDFInfo
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Abstract
A design method of a parameterized waverider with controllable wing components of a fuselage comprises the steps of firstly giving flow field parameters, waverider-related geometric constraints and shock wave outlet molded lines, then using cubic spline curves as leading edge line horizontal projection molded lines and parameterizing the waverider-related geometric constraints and the shock wave outlet molded lines by setting control parameters, then completing solution of a kissing plane flow field based on the given outlet molded lines and the leading edge line horizontal projection molded lines, and finally directly generating the waverider with controllable wing components of the fuselage. The wave rider designed by the method provided by the invention is parameterized based on a given leading edge line horizontal projection profile, and the wave rider with controllable wing parts of the fuselage is generated and better applied to engineering practice.
Description
Technical field
The invention belongs to hypersonic aircraft technical field, more particularly to a kind of parameter that fuselage airfoil member is controllable
Change Waverider design method.
Background technology
Waverider design is one of emphasis and hot spot of the current research of hypersonic aircraft aerodynamic arrangement in the world.When
Preceding Waverider design method is broadly divided into two classes：One is the design theory of given shock wave body, another kind is osculating design
Theoretical (including osculating cone and osculating axisymmetry, osculating flow Field Design theory).
The former is and to give one of upper and lower surface rear molded line to stationary shock molded line on Waverider bottom section, by
This two molded line track streamline in benchmark flow field and obtain Waverider upper and lower surface, to obtain Waverider.The benchmark flow field can
To be axial symmetry or non-axis symmetry.The latter is to be answered on each osculating face come approximate by axial symmetry flow by Three-dimensional Flow
Waverider design is realized with the former design method.
But above-mentioned Waverider design method needs to carry out streamlined impeller in reference body flow field just after given molded line
Waverider shape can be obtained, the configurations of components such as fuselage, the wing of aircraft and corresponding geometric dimension cannot be directly controlled
(length and angle of sweep etc.).To obtain the Waverider aircraft configuration of performance satisfaction, it is necessary to Waverider is first designed, and
By Design of Performance and screening, aircraft body can be just obtained.On this basis, artificial division or addition fuselage,
The components such as wing could form aircraft configurations.It therefore, can not be according to Waverider aircraft pair in existing Waverider design method
The directly given design parameter of the requirement of airfoil member, design process complexity are cumbersome.
Invention content
In view of the defects existing in the prior art, the present invention provides a kind of parametrization Waverider that fuselage airfoil member is controllable
Design method.Requirement that can not be according to Waverider aircraft to airfoil member it is an object of the invention to solve existing design method
The problem of directly giving design parameter.The design method is based on given costa floor projection molded line and parameterizes, and both may be used
Control the geometric dimension of Waverider, but can according to engineering the requirement design parameter to Waverider aircraft in practice, directly generate
The satisfactory Waverider with component feature.
Purpose to realize the present invention, is achieved using following technical scheme：
A kind of parametrization Waverider design method that fuselage airfoil member is controllable, includes the following steps：
S1 gives flow field parameter, Waverider correlation geometrical constraint and shock wave outlet molded line；
Given flow field parameter includes Mach number Ma, Angle of Shock Waves β.
Given Waverider correlation geometrical constraint includes：Rider body length L and Waverider width W.
S2 arrange parameter costa floor projection molded line.
Make costa floor projection molded line using cubic spline curve and is parameterized.
Waverider is axially symmetric structure, can determine after given rider body length L, width W Waverider vertex M and
Rear point N coordinates；Vertex M and rear point N is costa floor projection molded line starting point and distal point respectively.With Waverider vertex
Subpoint in Waverider bottom surface is origin, and Waverider is longitudinally x-axis, is laterally z-axis, vertical direction is y-axis, establishes rider
Body coordinate system.
Control parameter is set：Control parameter includes on costa floor projection molded line between its starting point M and distal point N
(referring to Fig.1, insertion point is the point 1 in Fig. 1 to point K for the insertion point of setting.) and costa floor projection molded line on point N
The angle theta of its tangential direction and z-axisN；It is required that according to control parameter, that is, insertion point of setting and θNSolve obtained costa
Floor projection molded line meets claimed below：(1) any point coordinate on costa floor projection molded line meets
x∈(0,L)；(2) have on costa floor projection molded line and only 2 points of (z1,x1) and (z2,x2) meet x'(z)=0, and x1
＜ x2, z1＜ z2。
Referring to Fig.1, it is known that starting point M (tangent slope is defaulted as 0 at M points), k insertion point and the total k+2 of distal point N (k >=
0；When wherein k=0, it is 0 to indicate that insertion is counted out, and control parameter at this time is starting point M and distal point N and angle thetaN) a point
Coordinate and point N its tangential direction and z-axis on costa floor projection molded line angle thetaN, starting point M, insertion point and end
Cubic spline curve, that is, costa floor projection molded line is divided into k+1 sections of curves by endpoint N；The one of adjacent two sections of curve tie points
Order derivative and second dervative are equal, and coefficient a can be found out by substituting into equation (1)i、bi、ci、di(i≤k+1) obtains costa water
Flat projection curved dies：
S3 calculates osculating surface current field；
The method for solving of osculating surface current field is as follows in S3：
S3.1 is uniformly discrete to the shock wave outlet molded line progress given in S1, obtains a series of discrete point.Discrete point
Density need to ensure that the streamline that difference generates can generate smooth curved surface.
S3.2 exports shock wave any one discrete point P of the discrete gained of molded line1, obtained discrete point P1The circle of curvature and
Circle of curvature center of circle O1Coordinate, the circle of curvature namely cross discrete point P1Conical Shock Wave, generated discrete point P1Conical Shock Wave
Benchmark cone be osculating bore, osculating cone axis be parallel to x-axis；O1To cross discrete point P1The circle of curvature the center of circle, be also osculating
Subpoints of the conical point O on shock wave outlet.
By discrete point P1、O1The coordinate that point and Angle of Shock Waves β can get osculating conical point O points (crosses O1Point is parallel to x-axis
Straight line, osculating conical point O points to be asked and discrete point P1Between line OP1Angle with the straight line is β, is closed according to this geometry
System can be obtained the coordinate of osculating conical point O points), O1The line of point and osculating conical point O points is discrete point P1Corresponding osculating
Axis of cone line；O1Point, P1Point and osculating conical point O points constituted discrete point P1Osculating face AA1, discrete point P1With osculating conical point
The line of O points is osculating face AA1Interior shock-wave spot was obtained by solving Taylor-Maccoll flow field control equations
Discrete point P1Corresponding osculating surface current field.Referring to Anderson J D.Fundamentals of aerodynamics [M]
.3rd edition. McGraw-Hill Companies, 2001.
S3.3 discrete points P1Costa floor projection type is handed over the projection of the lines of osculating conical point O points in the horizontal plane
Line is in P4Point, discrete point P1On line between osculating conical point O points with P4The identical point of point x coordinate is corresponding leading edge
Point P.It crosses leading edge point P and is parallel to OO1Straight line hand over Waverider bottom surface in point P3, straight line PP3For discrete point P1Corresponding osculating
Upper surface streamline in surface current field.From leading edge point P in discrete point P1Streamlined impeller is carried out in corresponding osculating surface current field
Obtain lower surface streamline PP2, P2For discrete point P1The point on the rear line of lower surface in corresponding osculating surface current field.
S3.4 according to identical method in S3.2 to S3.3, can obtain other all discrete points on shock wave outlet molded line
The corresponding osculating face of each discrete point and upper surface streamline, lower surface streamline in respective osculating face on shock wave outlet molded line
And the point on the rear line of lower surface.
S4 completes Waverider design.
All lower surface streamlines are subjected to setting-out and obtain Waverider lower surface；All upper surface streamlines are put
Sample obtains Waverider upper surface；Point on all lower surface rear lines is smoothly connected and constitutes Waverider lower surface rear line；
Finally Waverider bottom is closed, then Waverider design is completed.
Compared with the existing technology, present invention produces following advantageous effects：
Based on method provided by the present invention, by given different control parameter, i.e., given different insertion points
Mesh, the coordinate of insertion point and angle thetaNCosta floor projection molded line of different shapes can be obtained, so that generating different
The Waverider of shape.The requirement design parameter to Waverider shape in practice according to engineering, directly generating fuselage airfoil member can
The Waverider of control is preferably applied for engineering reality.
Description of the drawings
Fig. 1 is costa floor projection control parameter schematic diagram；
Fig. 2 is costa floor projection control parameter schematic diagram (the given two insertion points i.e. insertion point in an embodiment
1 and insertion point 2)
Fig. 3 is Waverider schematic bottom view；
Fig. 4 was discrete point P1Osculating face schematic diagram
Fig. 5 is discrete point P1Costa floor projection type is handed over the projection of the lines of osculating conical point O points in the horizontal plane
Line is in P4The schematic diagram of point；
Fig. 6 is the schematic diagram of the Waverider generated in one embodiment of the invention.
Fig. 7 is Waverider pressure cloud atlas.
Specific implementation mode
Below in conjunction with the attached drawing in figure of the embodiment of the present invention, technical solution in the embodiment of the present invention carry out it is clear,
It is fully described by, is described in further details, but do not limit protection scope of the present invention according to this.
With reference to Fig. 2 Fig. 6, the present embodiment provides a kind of parametrization Waverider design method that fuselage airfoil member is controllable, packets
Include following steps：
S1 gives flow field parameter, Waverider correlation geometrical constraint and shock wave outlet molded line；
Given flow field parameter includes Mach number Ma, Angle of Shock Waves β.
Given Waverider correlation geometrical constraint includes：Rider body length L and Waverider width W.
S2 arrange parameter costa floor projection molded line.
Make costa floor projection molded line using cubic spline curve and is parameterized.
Waverider is axially symmetric structure, therefore can determine the vertex of Waverider after given rider body length L, width W
M and rear point N coordinates.Vertex M and rear point N is costa floor projection molded line starting point and distal point respectively simultaneously.With rider
Subpoint of the body vertex in Waverider bottom surface is origin, and Waverider is longitudinally x-axis, is laterally z-axis, vertical direction is y-axis, is built
Vertical Waverider coordinate system.
Control parameter is set：Control parameter includes on costa floor projection molded line between its starting point M and distal point N
The angle theta of the insertion point of setting and point N its tangential direction and z-axis on costa floor projection molded lineN.It is required that according to setting
The control parameter set i.e. insertion point and θNThe costa floor projection molded line that solution obtains meets claimed below：(1) costa
Any point coordinate on floor projection molded line meetsx∈(0,L)；(2) have on costa floor projection molded line
And only 2 points of (z1,x1) and (z2,x2) meet x'(z)=0, and x1＜ x2, z1＜ z2。
As shown in Fig. 2, coordinate, that is, insertion point 1 of given two insertion points and insertion point 2 and θ in the present embodimentN,
Rooting is according to two insertion points of setting and θNThe costa floor projection molded line that solution obtains meets claimed below：(1) leading edge
Any point coordinate on line floor projection molded line meetsx∈(0,L)；(2) on costa floor projection molded line
Have and only 2 points of (z1,x1) and (z2,x2) meet x'(z)=0, and x1＜ x2, z1＜ z2。
In the present embodiment, it is known that starting point M (tangent slope is defaulted as 0 at M points), 1 (x of insertion point1, z1), 2 (x of insertion point2,
z2) and distal point the N coordinate of totally 4 points and the angle of point N its tangential direction and z-axis on costa floor projection molded line
θN, starting point M, 1 (x of insertion point1, z1), 2 (x of insertion point2, z2) and distal point N by cubic spline curve, that is, costa floor projection
Molded line is divided into 3 sections of curves；The first derivative and second dervative of adjacent two sections of curve tie points are equal, and substituting into equation (1) can ask
Go out coefficient ai、bi、ci、di(i≤3) obtain costa floor projection curved dies：
S3 calculates osculating surface current field；
S3.1 is uniformly discrete to the shock wave outlet molded line progress given in S1, obtains a series of discrete point.Discrete point
Density need to ensure that the streamline that different discrete points generate can generate smooth curved surface.
S3.2 exports shock wave any one discrete point P of the discrete gained of molded line with reference to Fig. 3, Fig. 4 and Fig. 51, obtained
Discrete point P1The circle of curvature and circle of curvature center of circle O1Coordinate, the circle of curvature namely cross discrete point P1Conical Shock Wave, generated
Discrete point P1Conical Shock Wave benchmark cone be osculating bore, osculating cone axis be parallel to x-axis；O1To cross discrete point P1Curvature
The round center of circle, the also subpoint for osculating conical point O on shock wave outlet.
By discrete point P1、O1The coordinate that point and Angle of Shock Waves β can get osculating conical point O points (crosses O1Point is parallel to x-axis
Straight line, osculating conical point O points to be asked and discrete point P1Between line OP1Angle with the straight line is β, is closed according to this geometry
System can be obtained the coordinate of osculating conical point O points), O1The line of point and osculating conical point O points is discrete point P1Corresponding osculating
Axis of cone line；O1Point, P1Point and osculating conical point O points constituted discrete point P1Osculating face AA1, discrete point P1With osculating conical point
The line of O points is osculating face AA1Interior shock-wave spot was obtained by solving Taylor-Maccoll flow field control equations
Discrete point P1Corresponding osculating surface current field.Referring to Anderson J D.Fundamentals of aerodynamics [M]
.3rd edition. McGraw-Hill Companies, 2001.
S3.3 is with reference to Fig. 5, discrete point P1Costa water is handed over the projection of the lines of osculating conical point O points in the horizontal plane
Flat projection molded line is in P4Point, discrete point P1On line between osculating conical point O points with P4The identical point of point x coordinate is pair
The leading edge point P answered.It crosses leading edge point P and is parallel to OO1Straight line hand over Waverider bottom surface in P3, as shown in figure 4, straight line PP3For from
Scatterplot P1Upper surface streamline in corresponding osculating surface current field.From leading edge point P in discrete point P1Corresponding osculating surface current field
Interior progress streamlined impeller obtains lower surface streamline PP2, P2For discrete point P1Lower surface rear line in corresponding osculating surface current field
On point.
S3.4 according to identical method in S3.2 to S3.3, can obtain other all discrete points on shock wave outlet molded line
The corresponding osculating face of each discrete point and upper surface streamline, lower surface streamline in respective osculating face on shock wave outlet molded line
And the point on the rear line of lower surface.
S4 completes Waverider design.
All lower surface streamlines are subjected to setting-out and obtain Waverider lower surface；All upper surface streamlines are put
Sample obtains Waverider upper surface；Point on all lower surface rear lines is smoothly connected and constitutes Waverider lower surface rear line；
Finally Waverider bottom is closed, then Waverider design is completed.
Using the above method of the present invention, θ is setN=45 °, insertion point number is 2, it is desirable that is inserted according to set two
Enter point coordinates and θNThe costa floor projection molded line that solution required by=45 ° obtains meets claimed below：(1) costa is horizontal
Any point coordinate projected on molded line meetsx∈(0,L)；(2) have on costa floor projection molded line and only
There are 2 points of (z1,x1) and (z2,x2) meet x'(z)=0, and x1＜ x2, z1＜ z2.Machine can be ultimately generated according to the above method
The controllable Waverider of body airfoil member is as shown in Figure 6.Using method for numerical simulation demonstrate this method correctness and effectively
Property, as shown in Figure 7.
From pressure nephanalysis it is found that this Waverider lower surface keeps preferable high pressure effect, and basic no pressure is let out
Dew has " rider " characteristic, it was demonstrated that the fuselage airfoil member based on costa floor projection molded line controllable parametrization rider
Body design method is correct.
Based on the method, you can according to engineering demand selection parameter of the Waverider to component in practice, directly generate and meet
It is required that Waverider aircraft.
In conclusion although the present invention has been disclosed as a preferred embodiment, however, it is not to limit the invention, appoints
What those of ordinary skill in the art, without departing from the spirit and scope of the present invention, when can make it is various change and retouch, therefore
Protection scope of the present invention is subject to the range defined depending on claims.
Claims (4)
1. a kind of parametrization Waverider design method that fuselage airfoil member is controllable, which is characterized in that include the following steps：
S1 gives flow field parameter, Waverider correlation geometrical constraint and shock wave outlet molded line；
Given flow field parameter includes Mach number Ma, Angle of Shock Waves β；
Given Waverider correlation geometrical constraint includes：Rider body length L and Waverider width W；
S2 arrange parameter costa floor projection molded line；
Make costa floor projection molded line using cubic spline curve and is parameterized；
Waverider is axially symmetric structure, and the vertex M and rear point of Waverider are can determine after given rider body length L, width W
N coordinates；Vertex M and rear point N is costa floor projection molded line starting point and distal point respectively；With Waverider vertex in Waverider
The subpoint of bottom surface is origin, and Waverider is longitudinally x-axis, is laterally z-axis, vertical direction is y-axis, establishes Waverider coordinate system；
Control parameter is set：Control parameter includes being arranged between its starting point M and distal point N on costa floor projection molded line
The angle theta of point N its tangential direction and z-axis on insertion point and costa floor projection molded lineN；It is required that according to the control of setting
Parameter, that is, insertion point and θNThe costa floor projection molded line that solution obtains meets claimed below：(1) costa floor projection
Any point coordinate on molded line meetsx∈(0,L)；(2) have on costa floor projection molded line and only 2 points
(z1,x1) and (z2,x2) meet x'(z)=0, and x1＜ x2, z1＜ z2；
S3 calculates osculating surface current field；
S4 completes Waverider design.
2. the controllable parametrization Waverider design method of fuselage airfoil member according to claim 1, which is characterized in that S2
In, it is known that the coordinate of starting point M, k insertion point and the total k+2 point of distal point N and the point N on costa floor projection molded line its
The angle theta of tangential direction and z-axisN, wherein k >=0；Starting point M, insertion point and distal point N are by cubic spline curve, that is, costa water
Flat projection molded line is divided into k+1 sections of curves；The first derivative and second dervative of adjacent two sections of curve tie points are equal, substitute into equation
(1) coefficient a can be found outi、bi、ci、di, wherein i≤k+1 obtains costa floor projection curved dies：
3. the controllable parametrization Waverider design method of fuselage airfoil member according to claim 2, it is characterised in that：S3
Implementation method it is as follows：
S3.1 is uniformly discrete to the shock wave outlet molded line progress given in S1, obtains a series of discrete point；
S3.2 exports shock wave any one discrete point P of the discrete gained of molded line1, obtained discrete point P1The circle of curvature and curvature
Round heart O1Coordinate, the circle of curvature namely cross discrete point P1Conical Shock Wave, generated discrete point P1Conical Shock Wave benchmark
Cone is that osculating is bored, and the axis of osculating cone is parallel to x-axis；O1To cross discrete point P1The circle of curvature the center of circle, be also osculating conical point O
Subpoint on shock wave outlet；
By discrete point P1、O1Point and Angle of Shock Waves β can get the coordinate of osculating conical point O points, O1The company of point and osculating conical point O points
Line is P1The corresponding osculating axis of cone line of point；O1Point, discrete point P1Discrete point P was constituted with osculating conical point O points1Osculating face AA1,
Discrete point P1Line with osculating conical point O points is osculating face AA1Interior shock-wave spot, by solving Taylor-Maccoll
Flow field control equation obtained discrete point P1Corresponding osculating surface current field；
S3.3 discrete points P1Hand over costa floor projection molded line in P with the projection of the lines of osculating conical point O points in the horizontal plane4
Point, discrete point P1On line between osculating conical point O points with P4The identical point of point x coordinate is corresponding leading edge point P；It crosses
Leading edge point P is parallel to OO1Straight line hand over Waverider bottom surface in point P3, straight line PP3For discrete point P1In corresponding osculating surface current field
Upper surface streamline；From leading edge point P in discrete point P1Streamlined impeller is carried out in corresponding osculating surface current field obtains lower surface
Streamline PP2, P2For discrete point P1The point on the rear line of lower surface in corresponding osculating surface current field；
S3.4, according to identical method in S3.2 to S3.3, can get shock wave to other all discrete points on shock wave outlet molded line
Export the corresponding osculating face of each discrete point and upper surface streamline, lower surface streamline and following table in respective osculating face on molded line
Point on the rear line of face.
4. the controllable parametrization Waverider design method of fuselage airfoil member according to claim 3, it is characterised in that：It will
All lower surface streamlines carry out setting-out and obtain Waverider lower surface；All upper surface streamlines are subjected to setting-out and obtain Waverider
Upper surface；Point on all lower surface rear lines is smoothly connected and constitutes Waverider lower surface rear line；Finally to Waverider
Bottom is closed, then Waverider design is completed.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112298599A (en) * | 2020-11-02 | 2021-02-02 | 厦门大学 | Full three-dimensional wave-multiplying body inverse design method based on bending shock wave theory |
| CN112948976A (en) * | 2021-03-15 | 2021-06-11 | 中国科学院力学研究所 | Plane front edge lifting body front edge line optimization method and system and lifting body |
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| CN107672821A (en) * | 2017-09-22 | 2018-02-09 | 中国人民解放军国防科技大学 | Variable Mach number parallel wide-speed-range waverider aircraft design method based on osculating cone theory |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112298599A (en) * | 2020-11-02 | 2021-02-02 | 厦门大学 | Full three-dimensional wave-multiplying body inverse design method based on bending shock wave theory |
| CN112948976A (en) * | 2021-03-15 | 2021-06-11 | 中国科学院力学研究所 | Plane front edge lifting body front edge line optimization method and system and lifting body |
| CN112948976B (en) * | 2021-03-15 | 2024-02-02 | 中国科学院力学研究所 | Plane leading edge lifting body leading edge line optimization method, system and lifting body |
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| CN108629108B (en) | 2019-07-16 |
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