CN109250144A - Method for designing osculating cone waverider with directly controllable sweepback angle and upper/lower dihedral angles - Google Patents
Method for designing osculating cone waverider with directly controllable sweepback angle and upper/lower dihedral angles Download PDFInfo
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- CN109250144A CN109250144A CN201811155643.8A CN201811155643A CN109250144A CN 109250144 A CN109250144 A CN 109250144A CN 201811155643 A CN201811155643 A CN 201811155643A CN 109250144 A CN109250144 A CN 109250144A
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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
Abstract
The invention provides a method for designing osculating cone waverider with directly controllable sweepback angle and upper/lower dihedral, which comprises the steps of firstly, giving reference flow field parameters, giving a sweepback angle change rule of a horizontal projection molded line of a front edge line of the waverider along the z direction of a coordinate system of a machine body, namely giving a sweepback angle equation, and solving the horizontal projection molded line of the front edge line of the waverider; then, a shock wave bottom section molded line is designed and solved, a front edge point on a wave multiplication body front edge line is solved, then, a flow line forming the lower surface of the wave multiplication body is generated by starting from the front edge point and adopting a forward flow line tracking method, and finally, the wave multiplication body is generated by geometric lofting. Based on the design method, the final target that the swertive cone-waverider leading edge line sweepback angle and the dihedral angle are controllable is achieved.
Description
Technical field
The invention belongs to hypersonic aircraft Design of Aerodynamic Configuration technical fields, and in particular to a kind of angle of sweep and rider
The directly controllable osculating of body up/down dihedral bores Waverider design method.
Background technique
Hypersonic aircraft is the aircraft that a kind of speed is more than Mach 5, including Air-breathing hypersonic vehicle, fire
Arrow power hypersonic aircraft and unpowered glide vehicle, concrete application form include hypersonic cruise missile, height
Supersonic speed someone/a variety of aircraft such as unmanned aerial vehicle and sky and space plane.
In order to pursue good cruise and blow performance, hypersonic aircraft must lift resistance ratio with higher and larger
Available space, to improve payload proportion in total measurement (volume).
Hypersonic aircraft aerodynamic configuration mainly has axial symmetry configuration, lifting body configuration and waverider-derived three categories,
Wherein waverider-derived realizes high lift-drag ratio under the conditions of hypersonic flight using shock wave compression principle (rider principle)
It is pneumatic to require.
Currently used Waverider design method includes that cone leads Waverider design method and osculating cone Waverider design method.
Waverider is led relative to cone, it is higher that osculating bores Waverider design method outlet compressed air stream quality.At the same time, osculating bores rider
Body shock wave bottom section molded line be no longer limited to it is arc-shaped, effectively increase Waverider design freedom degree.
Sobieczky etc. proposes the generation side of osculating cone Waverider (Osculating Cone Waverider, OCW)
Method, and have conducted extensive research, basic ideas are that approximate arbitrary three-dimensional flow field is removed using Conical Flow Field, enormously simplify meter
It calculates.Go out a complete shock wave particular by stationary shock bottom section Profile Design, then intercepts a system in above-mentioned molded line
Column osculating face, and a series of taper flow fields are constructed in each osculating face, this series of taper flow field is exactly Waverider design
Benchmark flow field.Waverider leading edge is determined by the intersection that osculating bores shock wave and flows capture duct, finally in osculating coning tower tray field
Streamlined impeller is carried out since leading edge obtains Waverider.
By taking Fig. 1,2 as an example, 1 is Waverider costa floor projection molded line in figure, and general osculating bores Waverider design method
In input molded line be shock wave bottom section molded line 8 plus Waverider upper surface bottom section molded line 9 or Waverider lower surface bottom
Portion section molded line 10.It, can be by adjusting the B point of Waverider upper surface bottom section molded line 9 to realize that the Waverider upper counterangle is controllable
It completes position.But the scheme is using the Waverider upper counterangle as Waverider design driver, therefore the Waverider upper counterangle
Can not be directly controllable, need to measure by design, Waverider generation, the upper counterangle and etc., and obtained finally after several wheel iteration
Shape.Also, being typically designed Waverider costa floor projection molded line in method is indirect controlled curve, cannot achieve angle of sweep
Controllable design.
Summary of the invention
It is bored in Waverider design method for general osculating, costa angle of sweep and two, upper counterangle geometric shape parameter phase
Mutual coupling, the defect that can not be directly controlled, the present invention is based on floor projection molded line Waverider design method, a kind of sweepback of proposition
Angle and the direct controllable osculating of up/down dihedral bore Waverider design method.
Heretofore described angle of sweep and the definition of up/down dihedral are as shown in Figure 1.Coordinate system is body coordinate system, machine in Fig. 1
The origin of body coordinate system is the midpoint of shock wave bottom section molded line 8, and the longitudinal axis (x-axis), horizontal axis (z-axis) and vertical pivot (y-axis) are built
It is vertical to refer to 3.1.4 body coordinate system in GV/T 14410.1-93.
Heretofore described angle of sweep definition is with reference to 3.1.19 wing setting in GB/T16638.3-1996.In Fig. 1
In, 1 is Waverider costa floor projection molded line, PlIt is horizontal for any point on Waverider costa floor projection molded line 1
To coordinate z=zl。PtPoint is the intersection point and Waverider costa level of Waverider costa floor projection molded line and y-z plane
Project molded line transverse direction the widest part.2 be air-flow direction of flow.
3 be point P on Waverider costa floor projection molded linelAngle of sweep, i.e., Waverider costa floor projection type
Point P on linelTangent line and cross Waverider costa floor projection molded line on PlThe angle of the uprush direction reference line of point,
That is Waverider costa is in z=zl(definition is substantially local with reference to 3.1.18 wing in GB/T16 638.3-1996 at the angle of sweep of point
Angle of sweep).Therefore, there is different numerical value at angle of sweep in different transverse directions (z coordinate) position.The present invention passes through design angle of sweep edge
The equation of change in the direction coordinate z simultaneously solves Waverider costa floor projection molded line, realizes that Waverider costa angle of sweep is direct
Controllable target.
4 be P on Waverider costa floor projection molded linelThe uprush direction reference line of point, uprush direction
Reference line 4 crosses P on Waverider costa floor projection molded linelIt puts and parallel with abscissa line (z-axis).
5 be point P on Waverider costa floor projection molded linelTangent line.
Upper counterangle definition of the present invention is with reference to the 3.5.21 wing upper counterangle in GB/T16638.3-1996.Due to Waverider
For the wing described in bottom section projection profile and GB/T16638.3-1996 standard there are difference, string point, which has no way of determining, leads to nothing
Method evaluates the upper anti-espionage of Waverider by the concept of string.The present invention can from principle of the upper counterangle to aircraft lateral stability
Know and (is hit by a bullet the influence of wing dihedral angle with reference to " missile flight aerodynamics " 1-7 section, Qian Xingfang etc. writes), the cross that when yawed flight generates
It is acted on wing to speed, so that Vehicle Roll torque changes, finally influences lateral stability when aircraft flight
Property.Waverider is similar in the geometrical characteristic of different longitudinal directions (x coordinate) cross-sectional shape, and the present invention uses Waverider bottom section following table
Face dihedral characteristic represents the upper anti-espionage of Waverider.It is specifically defined as shown in Fig. 2, in Fig. 2: PcPoint is the outlet of Waverider lower surface
The intersection point of section molded line and x-y plane.6 be PtThe horizontal line and P of pointtAnd PcAngle between the line of point-to-point transmission.In Fig. 2
PtAnd PcThe line of point-to-point transmission was located at PtAbove the horizontal line of point, P is crossedtThe horizontal line and P of pointtAnd PcBetween the line of point-to-point transmission
Angle namely the referred to as upper counterangle；If PtAnd PcThe line of point-to-point transmission was located at PtBelow the horizontal line of point, P is crossedtThe horizontal line of point
With PtAnd PcAngle between the line of point-to-point transmission is then known as inverted diherdral.7 be PtThe horizontal line and parallel with z-axis of point；8 be sharp
Wave base portion section molded line, is made of straightway and power curved section.9 be Waverider upper surface bottom section molded line.10 be to multiply
Wave body lower surface bottom section molded line.11 be PtAnd PcThe line of point-to-point transmission.
Purpose to realize the present invention, is achieved using following technical scheme:
Angle of sweep and the direct controllable osculating of up/down dihedral bore Waverider design method, comprising the following steps:
S1: given benchmark flow field parameter, wherein benchmark flow field parameter includes free stream Mach number Ma, Angle of Shock Waves β.
S2: design sweepback angle equation simultaneously solves Waverider costa floor projection molded line；
In the present invention: angle of sweep directly controllably refers to real along the z Regularity Changes of body coordinate system by giving angle of sweep
It is existing.Symmetry based on Waverider, to the half curvilinear equation x=f (z) of Waverider costa floor projection molded line, z ∈ [0,
W/2] it discusses, the other half can be obtained according to symmetry transformation.
Assuming that the angle of sweep of Waverider costa floor projection molded line is χ=χ along the z Regularity Changes of body coordinate system
(z), any point P on Waverider costa floor projection molded linelCorresponding its numerical value of angle of sweep of point is χl；Waverider costa
P on floor projection molded linelThe corresponding angle of sweep χ of pointlWith Waverider costa floor projection curved dies there are following relationship, see
Formula (1):
Waverider costa floor projection curved dies are x=f (z), z ∈ [0, W/2], and wherein W is Waverider width.
For solving sweepback angle equation χ (z), the present invention provides following A, B two schemes:
Option A:
Given sweepback angle equation is shown in formula (2), wherein χA1,χA2It is constant, χA1With χA2Respectively sweepback angle equation is not
With the angle of sweep of section；
Assume that sweepback angle equation is χ (z)=χ in option AcForm.Formula (2) use piecewise function form, will after
Sweep angle equation segment design, aircraft available in this way have segmentation feature, i.e., have different sweepback with different sections
Angle.
Formula (2) are substituted into known to (1):
It further may be assumed that in option A shown in costa floor projection curved dies such as formula (4):
Wherein kA1,bA1,kA2,bA2,z1It is parameter to be asked.
Known conditions is sweepback angle equation χ=χA(z) and rider body length L and width W, then costa floor projection type
Parameter to be asked can be provided by following formula (5) and formula (6) in line equation (4):
Causef(z1) ∈ (0, L), the angle of sweep χ in sweepback angle equation (2)A1,χA2Formula need to be met simultaneously
(7) requirement:
min(tan(χA1),tan(χA2)) < tan (χAb) < max (tan (χA1),tan(χA2)) (7)
Above-mentioned is the half curvilinear equation x=f (z) to Waverider costa floor projection molded line, and z ∈ [0, W/2] is carried out
It solves, the symmetry based on Waverider can obtain the other half curve of Waverider costa floor projection molded line according to solution
Half curve negotiating symmetry transformation obtain.
Option b:
It is rightIntegration type, and sweepback angle equation χ=χ (z) is substituted into, and use integration by substitution abbreviation
Obtain formula (8):
Formula (1) is substituted into formula (8), further abbreviation obtains formula (9).Formula (9) is costa floor projection molded line
The relational expression of EQUATION x=f (z) and sweepback angle equation χ=χ (z).
Wherein sweepback angle equation χ (z) need to meet the following conditions:
I. when z ∈ [0, W/2], χ '=χ ' (z) equation is continuous；
Ii. wherein sweepback angle equation extreme coordinates value χ (0)=χ1, χ (W/2)=χ2, and when [0, W/2] z ∈, χ
(z)∈[χ1,χ2]。
Sweepback angle equation is assumed in B scheme along z coordinate linear change, i.e., shown in formula (10):
Formula (10) is substituted into formula (9) and is obtained formula (11), as the costa floor projection curved dies of option b.
Parameter to be asked is m in formula (11)B、dB、CB, specifically solve and see formula (12).Known parameters are in formula (12)
χBn、χBt、W。χBn、χBtRespectively P on costa floor projection molded linen、PtThe corresponding angle of sweep of two o'clock, W are Waverider width.
Rider body length L is parameter to be asked, and sees formula (13):
By formula (12) it is found that option b passes through two endpoint, that is, P of head and the tail on costa floor projection molded linen、PtTwo o'clock pair
The angle of sweep χ answeredBn、χBtAnd Waverider width W, control costa sweepback angular rate of change χ 'B(z)=mB, it is finally reached
The directly controllable target in costa angle of sweep.
Above-mentioned is the half curvilinear equation x=f (z) to Waverider costa floor projection molded line, and z ∈ [0, W/2] is carried out
It solves, the symmetry based on Waverider can obtain the other half curve of Waverider costa floor projection molded line according to solution
Half curve negotiating symmetry transformation obtain.
Comprehensive and more above-mentioned two scheme, in option A input condition include rider body length and width (L, W) and after
Sweep angle equation.Input condition includes Waverider width W and sweepback angle equation in option b, and rider body length L is by sweepback angle equation
And width W is acquired.
S3: shock wave bottom section molded line is solved.
Shock wave bottom section molded line to be solved is the combination profile that straight line adds power curve.
Pass through length of straigh line 2*LS, Waverider width W and power in given upper counterangle ψ, shock wave bottom section molded line
Curve power n acquires Waverider shock wave bottom section molded line in conjunction with the symmetrical face thickness H of Waverider that solution obtains.Specific method
It is as follows:
S3.1 gives Waverider upper counterangle ψ, in the molded line of shock wave bottom section length of straigh line 2*LS, Waverider width W with
And power curve power n,；
S3.2 designs Waverider shock wave bottom section curved dies
Shock wave bottom section curved dies are that straight line adds power curve, see formula (14):
Wherein on the y-z plane, a is power curve coefficients for Waverider bottom section, for coefficient of discharge to be asked.
The thickness H of the S3.3 solution Waverider plane of symmetry；
Known Angle of Shock Waves β and rider body length L solves the Waverider plane of symmetry using T-M equation and streamlined impeller method
(specific method for solving is referring to [the hypersonic gliding of fourth peak-cruise two-stage rider for benchmark flow field and streamline in the osculating face of place
The Changsha design method research [D]: defense science and technology university (master) .2012.] in 4.2 sections taper flow field calculation side
Method)；According to the length that streamline is projected in Waverider bottom surface, the symmetrical face thickness H of Waverider can be acquired.
S3.4 solves shock wave bottom section curved dies；
PtThe coordinate of point is (0, W/2, h1).Whereinh0=Ltan (β)；By PtPoint coordinate
It substitutes into formula (14), obtains formula (15):
Known designs Angle of Shock Waves β, rider body length L and upper counterangle ψ (see Fig. 5), power can be acquired by substituting into formula (15)
Curve coefficients a.
S4: leading edge point on Waverider costa is solved；
Putting 18 in Fig. 3, on Waverider costa 16 is a leading edge point to be asked on costa, below to solve leading edge point
Illustrate specific steps for 18:
S4.1 is discrete by the shock wave bottom section molded line solved in S3, obtains a series of discrete point.
Discrete solution uses equidistant discrete method, and discrete point number given first makes it be equally spaced laterally, then again
Solve all discrete point coordinates.
S4.2 determines the corresponding osculating face of each discrete point on the molded line of shock wave bottom section.
The definition and solution in osculating face refer to [the hypersonic gliding of fourth peak-cruise two-stage the research of rider design method [D]
Changsha: defense science and technology university (master) .2012.] 6.1 sections.
For any discrete point on the molded line of shock wave bottom section, remember that the discrete point is A discrete point.
Shock wave bottom section molded line is found out first in the coordinate of the curvature circle-center point of A discrete point, and curvature circle-center point is A simultaneously
The projection of benchmark conical point in the corresponding osculating face of discrete point in Waverider bottom section.
Benchmark conical point in the corresponding osculating face of A discrete point is located in osculating cone Waverider benchmark conical point trajectory line；
Benchmark conical point on the molded line of shock wave bottom section in the corresponding osculating face in arbitrary point is respectively positioned on the osculating cone Waverider benchmark vertex of a cone
On locus of points line.
Benchmark cone of the shock wave bottom section molded line in curvature circle-center point osculating corresponding with the A discrete point face of A discrete point
On the line benchmark axis of cone line that benchmark is bored in the corresponding osculating face of A discrete point between vertex, the two is conllinear.
The line between benchmark conical point in A discrete point osculating corresponding with A discrete point face is that A discrete point is corresponding
Shock wave molded line in osculating face.Benchmark cone in shock wave molded line osculating corresponding with A discrete point face in the corresponding osculating face of A discrete point
Benchmark cone axis angle is the design Angle of Shock Waves β given in S1.Shock wave molded line and A are discrete in the corresponding osculating face of A discrete point
The corresponding osculating face of plane, that is, A discrete point where the benchmark axis of cone line of benchmark cone in the corresponding osculating face of point.
S4.3 solves the shock wave curved dies on the molded line of shock wave bottom section in the corresponding osculating face of each discrete point.
The line of benchmark conical point in A discrete point osculating corresponding with A discrete point face is the corresponding kiss of A discrete point
Shock wave molded line in section.Because shock wave molded line is straight line in osculating face, shock wave molded line can lead in the corresponding osculating face of A discrete point
The coordinate of the two points of the benchmark conical point and A discrete point crossed in the corresponding osculating face of A discrete point acquires.
S4.4 solves on the molded line of shock wave bottom section leading edge point coordinate in the corresponding osculating face of each discrete point.
By the equation of the equation of shock wave molded line in the corresponding osculating face of A discrete point and Waverider costa floor projection molded line
Simultaneous can acquire the coordinate of the leading edge point in the corresponding osculating face of A discrete point, the leading edge in the corresponding osculating face of A discrete point
Point is the leading edge point on Waverider costa.
It can be respectively corresponding in the hope of all discrete points on the molded line of shock wave bottom section using above-mentioned identical method
Shock wave molded line in osculating face, the corresponding osculating face of each discrete point, so solve obtain in the corresponding osculating face of each discrete point before
The coordinate of edge point.
S5: the streamline of Waverider lower surface is solved；
S5.1 solves on the molded line of shock wave bottom section that in the corresponding osculating face of each discrete point benchmark flow field.
According to the free stream Mach number Ma and Angle of Shock Waves β given in S1, obtained by solving Taylor-Maccoll governing equation
Benchmark flow field in the corresponding osculating face of each discrete point on to shock wave bottom section molded line, each discrete point on the molded line of shock wave bottom section
Benchmark flow field is taper flow field in corresponding osculating face.Specific method for solving is referring to [hypersonic gliding-the cruise two of fourth peak
Grade rider design method research [D] Changsha: defense science and technology university (master) .2012.] in 4.2 sections taper flow field
Method for solving.
S5.2 solves streamline.
On the molded line of shock wave bottom section in the corresponding osculating face of each discrete point, before in each osculating face for being acquired in S4
Edge point sets out, and adopts in benchmark flow field in the corresponding osculating face of each discrete point on the shock wave bottom section molded line acquired in S5.1
The corresponding streamline of the leading edge point i.e. streamline of Waverider lower surface in each osculating face is solved with positive streamline method for tracing, specifically
Method for solving is referring to [the hypersonic gliding of the fourth peak-Changsha cruise two-stage rider design method research [D]: defence science and skill
Art university (master) .2012.] in 4.3 sections streamline method for solving.
S6: geometric sheeting generates Waverider.
Streamline (it is the same solving streamline method, referring to S5.2) combination setting-out of all Waverider lower surfaces is obtained into rider
Body lower surface, Waverider upper surface are generated using free-streamline method (referring to [the hypersonic gliding of fourth peak-cruise two-stage rider is set
Count the Changsha technique study [D]: defense science and technology university (master) .2012.] in 4.1 sections).
Compared with the existing technology, present invention produces following advantageous effects:
Different from the design scheme that Sobieczky et al. is proposed, the present invention bores shock wave by osculating and costa level is thrown
The method of the intersection of shadow molded line determines Waverider costa.This Waverider design method based on floor projection molded line of the present invention
It is with the obvious advantage.
Firstly, Waverider aerodynamic characteristic and its aerodynamic arrangement and relevant parameter contact closely, and costa floor projection type
Line and base profile (base profile is that Waverider following table facial contour is projected in bottom section) are crucial.Floor projection shape (this
In floor projection shape, that is, costa floor projection shape) determine Waverider lift distribution, lift distribution and pressure heart position (pressure
It with respect to the aerodynamic moment of the point is zero that the characteristics of heart, which is total aerodynamic force, and lift distribution determines pressure heart position.Press the heart and particle
Relative position determines the Longitudinal static stability of Waverider) relationship also just determine indirectly floor projection shape to aircraft longitudinal direction
The influence of static stability；Waverider lateral stability can also be adjusted by costa angle of sweep and the upper counterangle (see " guided missile
Flight mechanics " 1-7 section, Qian Xingfang etc. writes), and above-mentioned two formal parameter and Waverider floor projection and base profile phase
It closes.
And the aerodynamic arrangement of certain floor projection shapes can effectively promote Waverider lift resistance ratio performance.As wide fast domain is superb
Velocity of sound aircraft in the flight of subsonic speed stage, can by costa angle of sweep extend the design to the regularity of distribution obtain volume
Outer vortex lift.
Detailed description of the invention
Fig. 1 is the top view of costa angle of sweep and up/down dihedral conceptual illustration figure,
Fig. 2 is the right view of costa angle of sweep and up/down dihedral conceptual illustration figure；
In Fig. 1 and 2: x, y, z are the longitudinal direction of coordinate system, normal direction, transverse coordinate axis where Waverider；
O is the origin of body coordinate system where Waverider；PlPoint is any one on Waverider costa floor projection molded line
Point, lateral coordinates z=zl；PtPoint be Waverider costa floor projection molded line and y-z plane intersection point and Waverider before
Edge line floor projection molded line transverse direction the widest part； PcPoint is the intersection point of Waverider lower surface outlet molded line and x-y plane；
1, Waverider costa floor projection molded line；2, air-flow direction of flow；3, Waverider costa floor projection molded line
Upper PlAngle of sweep, i.e., point P on Waverider costa floor projection molded linelTangent line and cross Waverider costa level throw
P on shadow molded linelThe angle of the uprush direction reference line of point；4, P on Waverider costa floor projection molded line is crossedlPoint hangs down
Straight airflow direction reference line；5, point P on Waverider costa floor projection molded line is crossedlTangent line；6, P is crossedtThe horizontal line and P of pointt
And PcAngle between the line of point-to-point transmission；P in figuretAnd PcThe line of point-to-point transmission was located at PtAbove the horizontal line of point, P is crossedtPoint
Horizontal line and PtAnd PcAngle between the line of point-to-point transmission namely the referred to as upper counterangle；If PtAnd PcThe line of point-to-point transmission is located at
Cross PtBelow the horizontal line of point, P is crossedtThe horizontal line and P of pointtAnd PcAngle between the line of point-to-point transmission is then known as inverted diherdral；7,
Cross PtThe horizontal line and parallel with z-axis of point；8, shock wave bottom section molded line is made of straightway and power curved section；9, multiply
Wave body upper surface bottom section molded line；10, Waverider lower surface bottom section molded line；11,PtAnd PcThe line of point-to-point transmission.
Fig. 3 is design diagram of the invention.
1, Waverider costa floor projection molded line；8, shock wave bottom section molded line, by straightway and power curved section
Composition；12, free stream Mach number Ma；13, Angle of Shock Waves β；14, osculating bores Waverider benchmark conical point trajectory line；15, A discrete point pair
The benchmark axis of cone line that benchmark is bored in the osculating face answered；16, Waverider costa is costa floor projection molded line in shock surface
On projection；17, a discrete point on Waverider costa floor projection molded line, and the leading edge on the point and Waverider costa
Point 18 is corresponding；18, the leading edge point in the corresponding osculating face of A discrete point, also on Waverider costa floor projection molded line from
Subpoint of the scatterplot 17 on shock surface, while being also shock wave type in the osculating corresponding with A discrete point of Waverider costa 16 face
The intersection point of line 22.19, A discrete point is taken up an official post the discrete point taken for shock wave bottom section molded line；20, shock wave bottom section
Curvature circle-center point of the molded line 8 in A discrete point；21, the streamline acquired from the leading edge point 18s in the corresponding osculating face of A discrete point
The distal point of 18-21 is located at Waverider bottom section；22, shock wave molded line in the corresponding osculating face of A discrete point；23, A is discrete
Benchmark conical point in the corresponding osculating face of point.
Fig. 4 is sweepback angle equation segment design schematic diagram in A scheme；
In Fig. 4: 24, angle of sweep χA1Line segment；25, angle of sweep χA2Line segment.
Fig. 5 is to solve shock wave bottom section molded line schematic diagram；
In Fig. 5: 8 be shock wave bottom section molded line, is made of straightway and power curved section, wherein length of straigh line is
Ls.ψ is the Waverider upper counterangle, and W/2 is Waverider half-breadth.h0It is defined as PnThe length projected with o point line in bottom section.H is fixed
Justice is PnWith PcThe length that two o'clock point line is projected in Waverider bottom section, while being also the thickness at the Waverider plane of symmetry.h1
It is defined as PtDifference in height of the opposite o point of point in normal direction (y-axis).
Fig. 6 is Waverider costa floor projection molded line angle of sweep in B scheme along lateral coordinates (z-axis) linear change
Schematic diagram；χ in Fig. 6BnAnd χBtRespectively PnAnd PtThe angle of sweep of corresponding points；Waverider width W is provided in Fig. 6, rider body length L
It is parameter to be asked；
Fig. 7 and Fig. 8 is respectively the top view and right view of caseA1.
Fig. 9 and Figure 10 is respectively the top view and right view of caseA2.
Figure 11 and Figure 12 is respectively the top view and right view of caseA3.
Figure 13 is that the pressure contour cloud atlas of caseA1 shape bottom section and shock wave bottom section molded line discrete point compare.
Figure 14 and Figure 15 is respectively the top view and right view of caseB1.
Figure 16 and Figure 17 is respectively the top view and right view of caseB2.
Specific embodiment
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 the scope of protection of the present invention according to this.
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 the scope of protection of the present invention according to this.
Angle of sweep and the direct controllable osculating of up/down dihedral bore Waverider design method, comprising the following steps:
S1: given benchmark flow field parameter, wherein benchmark flow field parameter includes free stream Mach number Ma, Angle of Shock Waves β.
S2: design sweepback angle equation simultaneously solves Waverider costa floor projection molded line；
In the present invention: angle of sweep directly controllably refers to real along the z Regularity Changes of body coordinate system by giving angle of sweep
It is existing.Symmetry based on Waverider, to the half curvilinear equation x=f (z) of Waverider costa floor projection molded line, z ∈ [0,
W/2] it discusses, the other half can be obtained according to symmetry transformation.
As shown in Figure 1, 2, it is assumed that the angle of sweep of Waverider costa floor projection molded line becomes along the direction z of body coordinate system
Law is χ=χ (z), any point P on Waverider costa floor projection molded line 1lPutting corresponding its numerical value of angle of sweep is
χl；P on Waverider costa floor projection molded linelThe corresponding angle of sweep χ of pointlWith Waverider costa floor projection curved dies
There are following relationships, see formula (1):
Waverider costa floor projection curved dies are x=f (z), z ∈ [0, W/2], and wherein W is Waverider width.
For solving sweepback angle equation χ (z), the present invention provides following two scheme:
Option A:
Referring to Fig. 4, Fig. 4 is sweepback angle equation segment design schematic diagram, and given sweepback angle equation is shown in formula (2), wherein
χA1,χA2It is constant, χA1With χA2The respectively angle of sweep of sweepback angle equation difference section.As shown in figure 4, after linking together
Sweep angle is χA1Line segment 24 and angle of sweep be χA2Line segment 25 constitute Waverider costa floor projection molded line, and two sections of leading edges
The angle of sweep of line floor projection molded line is remained unchanged along z coordinate direction；PtPoint be Waverider costa floor projection molded line with
The intersection point and Waverider costa floor projection molded line transverse direction the widest part of y-z plane；PnPoint is that Waverider costa level is thrown
The vertex of the intersection point and Waverider of shadow molded line and x-y plane；χAbIt is P for benchmark angle of sweepnAnd PtThe line institute of point-to-point transmission
Corresponding sweepback angle.
Referring to Fig. 4, assume that sweepback angle equation is χ (z)=χ in option AcForm.Formula (2) is using piecewise function
Form, by sweepback angle equation segment design, aircraft available in this way has segmentation feature, i.e., has or not different sections
Same angle of sweep.
Formula (2) are substituted into known to (1):
It further may be assumed that in option A shown in costa floor projection curved dies such as formula (4):
Wherein kA1,bA1,kA2,bA2,z1It is parameter to be asked.
Known conditions is sweepback angle equation χ=χA(z) and rider body length L and width W, then costa floor projection type
Parameter to be asked can be provided by following formula (5) and formula (6) in line equation (4):
Further, byf(z1) ∈ (0, L), the angle of sweep χ in sweepback angle equation (2)A1,χA2It need to expire simultaneously
The requirement of sufficient formula (7):
min(tan(χA1),tan(χA2)) < tan (χAb) < max (tan (χA1),tan(χA2)) (7)
Above-mentioned is the half curvilinear equation x=f (z) to Waverider costa floor projection molded line, and z ∈ [0, W/2] is carried out
It solves, the symmetry based on Waverider can obtain the other half curve of Waverider costa floor projection molded line according to solution
Half curve negotiating symmetry transformation obtain.
Option b:
It is rightIntegration type, and sweepback angle equation χ=χ (z) is substituted into, and use integration by substitution abbreviation
Obtain formula (8):
Angle of sweep and costa floor projection curved dies relational expression (1) are substituted into formula (8), further abbreviation obtains public affairs
Formula (9).Formula (9) is the relational expression of costa floor projection curved dies x=f (z) and sweepback angle equation χ=χ (z).
Wherein sweepback angle equation χ (z) need to meet the following conditions:
Iii. when z ∈ [0, W/2], χ '=χ ' (z) equation is continuous；
Iv. wherein sweepback angle equation extreme coordinates value χ (0)=χ1, χ (W/2)=χ2, and when [0, W/2] z ∈, χ
(z)∈[χ1,χ2]
Referring to Fig. 6, sweepback angle equation is assumed in B scheme along z coordinate linear change, i.e., shown in formula (10):
Formula (10) is substituted into formula (9) and is obtained formula (11), as the costa floor projection curved dies of option b.
Parameter to be asked is m in formula (11)B、dB、CB, specifically solve and see formula (12).Known parameters are in formula (12)
χBn、χBt、W。χBn、χBtRespectively P on costa floor projection molded linen、PtThe corresponding angle of sweep of two o'clock, W are Waverider width.
Rider body length L is parameter to be asked, and sees formula (13):
By formula (12) it is found that option b passes through two endpoint, that is, P of head and the tail on costa floor projection molded linen、PtTwo o'clock pair
The angle of sweep χ answeredBn、χBtAnd Waverider width W, control costa sweepback angular rate of change χ 'B(z)=mB, it is finally reached
The directly controllable target in costa angle of sweep.
Above-mentioned is the half curvilinear equation x=f (z) to Waverider costa floor projection molded line, and z ∈ [0, W/2] is carried out
It solves, the symmetry based on Waverider can obtain the other half curve of Waverider costa floor projection molded line according to solution
Half curve negotiating symmetry transformation obtain.
Comprehensive and more above-mentioned two scheme, in option A input condition include rider body length and width (L, W) and after
Sweep angle equation.Input condition includes Waverider width W and sweepback angle equation in option b, and rider body length L is by sweepback angle equation
And width W is acquired.
S3: shock wave bottom section molded line is solved.
Shock wave bottom section molded line to be solved is the combination profile that straight line adds power curve.
As shown in figure 5, passing through length of straigh line 2*LS, Waverider width in given upper counterangle ψ, shock wave bottom section molded line
W and power curve power n acquires Waverider shock wave bottom section type in conjunction with the symmetrical face thickness H of Waverider that solution obtains
Line.The specific method is as follows:
S3.1 is as shown in figure 5, given Waverider upper counterangle ψ, length of straigh line 2*LS, rider in the molded line of shock wave bottom section
Body width W and power curve power n,；
S3.2 designs Waverider shock wave bottom section curved dies
Shock wave bottom section curved dies are that straight line adds power curve, see formula (14):
Wherein on the y-z plane, a is power curve coefficients for Waverider bottom section, for coefficient of discharge to be asked.
The thickness H of the S3.3 solution Waverider plane of symmetry；
Known Angle of Shock Waves β and rider body length L solves the Waverider plane of symmetry using T-M equation and streamlined impeller method
(specific method for solving is referring to [the hypersonic gliding of fourth peak-cruise two-stage rider for benchmark flow field and streamline in the osculating face of place
The Changsha design method research [D]: defense science and technology university (master) .2012.] in 4.2 sections taper flow field calculation side
Method)；According to the length that streamline is projected in Waverider bottom surface, the symmetrical face thickness H of Waverider can be acquired.
S3.4 solves shock wave bottom section curved dies；
Specifically, P in Fig. 5tThe coordinate of point is (0, W/2, h1).In Fig. 5h0=Ltan
(β)；By P in Fig. 5tPoint coordinate substitutes into formula (14), obtains formula (15):
Known designs Angle of Shock Waves β, rider body length L (being provided in S2, see Fig. 4) and upper counterangle ψ (see Fig. 5), generation
Power curve coefficients a can be acquired by entering formula (15).
S4: leading edge point on Waverider costa is solved；
Putting 18 in Fig. 3, on Waverider costa 16 is a leading edge point to be asked on costa, below to solve leading edge point
Illustrate specific steps for 18:
S4.1 is discrete by the shock wave bottom section molded line 8 solved in S3, obtains a series of discrete point.
Discrete solution uses equidistant discrete method, and discrete point number given first makes it be equally spaced laterally, then again
Solve all discrete point coordinates.
S4.2 determines the corresponding osculating face of each discrete point on the molded line of shock wave bottom section.
The definition and solution in osculating face refer to [the hypersonic gliding of fourth peak-cruise two-stage the research of rider design method [D]
Changsha: defense science and technology university (master) .2012.] 6.1 sections.
As shown in figure 3, illustrate the step of determining osculating face by taking any discrete point on shock wave bottom section molded line 8 as an example,
Take a discrete point for A discrete point 19 if appointing.
Firstly, finding out shock wave bottom section molded line 8 in the coordinate of the curvature circle-center point 20 of A discrete point, curvature circle-center point 20
It is simultaneously projection of the benchmark conical point 23 in the corresponding osculating face of A discrete point in Waverider bottom section.
Benchmark conical point 23 in the corresponding osculating face of A discrete point is located at osculating cone Waverider benchmark conical point trajectory line 14
On.Benchmark conical point on shock wave bottom section molded line 8 in the corresponding osculating face in arbitrary point is respectively positioned on osculating cone Waverider benchmark
In conical point trajectory line 14.
Benchmark of the shock wave bottom section molded line 8 in 20 osculating corresponding with the A discrete point face of curvature circle-center point of A discrete point
On the line benchmark axis of cone line 15 that benchmark is bored in the corresponding osculating face of A discrete point between conical point 23, the two is conllinear.
The line between benchmark conical point 23 in the osculating corresponding with A discrete point of A discrete point 19 face is A discrete point pair
Shock wave molded line 22 in the osculating face answered.In the corresponding osculating face of A discrete point in the osculating corresponding with A discrete point of shock wave molded line 22 face
15 angle of benchmark axis of cone line of benchmark cone is the design Angle of Shock Waves β given in S1.Shock wave in the corresponding osculating face of A discrete point
15 place plane of benchmark axis of cone line, that is, corresponding kiss of A discrete point 19 that benchmark is bored in the osculating corresponding with A discrete point of molded line 22 face
Section.
S4.3 solves the shock wave curved dies in the corresponding osculating face of A discrete point 19.
It is illustrated for the solution of shock wave molded line 22 in the corresponding osculating face of A discrete point described in the S4.2 step.
As shown in figure 3, the line of the benchmark conical point 23 in the osculating corresponding with A discrete point of A discrete point 19 face be A from
Shock wave molded line 22 in the corresponding osculating face of scatterplot.Shock wave molded line is straight line in osculating face, is swashed in the corresponding osculating face of A discrete point
Wave mode line 22 can be asked by coordinates of benchmark conical point 23 in the corresponding osculating face of A discrete point and A discrete point 19 the two points
?.
S4.4 solves leading edge point coordinate in the corresponding osculating face of A discrete point 19.
As shown in figure 3, the equation of shock wave molded line 22 in the corresponding osculating face of A discrete point and Waverider costa level are thrown
The equations simultaneousness of shadow molded line 1 can acquire the coordinate of the leading edge point 18 in the corresponding osculating face of A discrete point.A discrete point is corresponding
Leading edge point 18 in osculating face is the leading edge point on Waverider costa.
S4.5 uses method of the S4.2 into S4.4, can be in the hope of all discrete on the molded line of shock wave bottom section in S4.1
Shock wave molded line in the respective corresponding osculating face of point, the corresponding osculating face of each discrete point, and then solve and obtain each discrete point pair
The coordinate of leading edge point in the osculating face answered.
S5: the streamline of Waverider lower surface is solved；
S5.1 solves on the molded line of shock wave bottom section that in the corresponding osculating face of each discrete point benchmark flow field.
According to the free stream Mach number Ma and Angle of Shock Waves β given in S1, obtained by solving Taylor-Maccoll governing equation
Benchmark flow field in the corresponding osculating face of each discrete point on to shock wave bottom section molded line, each discrete point on the molded line of shock wave bottom section
Benchmark flow field is taper flow field in corresponding osculating face.Specific method for solving is referring to [hypersonic gliding-the cruise two of fourth peak
Grade rider design method research [D] Changsha: defense science and technology university (master) .2012.] in 4.2 sections taper flow field
Method for solving.
S5.2 solves streamline.
On the molded line of shock wave bottom section in the corresponding osculating face of each discrete point, before in each osculating face for being acquired in S4
Edge point sets out, and uses in benchmark flow field in the corresponding osculating face of each discrete point on the shock wave bottom section molded line acquired in S5.1
Positive streamline method for tracing solves the corresponding streamline of the leading edge point i.e. streamline of Waverider lower surface in each osculating face, specifically asks
Solution method is referring to [the hypersonic gliding of the fourth peak-Changsha cruise two-stage rider design method research [D]: defense science and technology
University (master) .2012.] in 4.3 sections streamline method for solving.
As shown in figure 3, in the benchmark flow field in the corresponding osculating face of A discrete point, out of A discrete point corresponding osculating face
Leading edge point 18 is set out, and can acquire streamline 18-21 in the corresponding osculating face discrete point A using positive streamline method for tracing.Discrete point A
The starting point of streamline 18-21 is the leading edge point 18 in the corresponding osculating face of A discrete point, distal point 21 in corresponding osculating face
Positioned at Waverider bottom section.
For other discrete points on shock wave bottom section molded line 8, solve to obtain using method identical with A discrete point each
Streamline in the corresponding osculating face of discrete point.
S6: geometric sheeting generates Waverider.
Streamline (it is the same solving streamline method, referring to S5.2) combination setting-out of all Waverider lower surfaces is obtained into rider
Body lower surface, Waverider upper surface are generated using free-streamline method (referring to [the hypersonic gliding of fourth peak-cruise two-stage rider is set
Count the Changsha technique study [D]: defense science and technology university (master) .2012.] in 4.1 sections).
As given sweepback angle equation according to option A in S2 and solving Waverider costa floor projection molded line, then known to it
Parameter is divided into benchmark flow field parameter (Ma, β) and geometric shape parameter (L, ψ, n, W, Ls, χA1、χA2) two kinds, it is referred to as Waverider
The input condition of design.Benchmark angle of sweep (the χ in rider body thickness (H) and S2 solved in S3Ab) it is intermediate quantity.Wherein multiply
Wave body thickness (H) is determining by rider body length L and benchmark flow field (Ma, β), benchmark angle of sweep (χAb) by formula tan (χBb)=
2L/W is determined.
A specific embodiment of the invention is provided below, wherein gives sweepback angle equation according to option A in S2 and solution multiplies
Wave body costa floor projection molded line, specific as follows:
Given benchmark flow field parameter: Ma=6, β=12 °；
Give stationary shock bottom section molded line parameter: L=6m, W=4.37m, n=3, LS=0.01W.
According to the constraint of formula, costa floor projection molded line sweepback angular dimensions (χA1、χA2) value is as follows: first group:
χA1=75 °, χA2=65 °；Second group: χA1=80 °, χA2=65.
Waverider up/down dihedral ψ takes two groups, first group: ψ=- 7 °；Second group of ψ=10 °.
The scheme of angle of sweep assembled scheme and up/down dihedral is arranged in pairs or groups, three kinds of shape schemes shown in table 1 are obtained.
Table 1
Fig. 7~Figure 12 is the top view and right view of three shapes.Wherein in top view and right view, design scheme shape
Angle of sweep and up/down dihedral meet design requirement.
It is calculated by no viscosity number value and is met the requirements it is found that designing obtained osculating and boring Waverider.As shown in figure 13, in figure
The pressure contour cloud atlas of flow field bottom section shows that high pressure draught is respectively positioned on Waverider lower surface, and designs shock wave bottom section
Molded line discrete point is consistent with calculated result.
As given sweepback angle equation according to option b in S2 and solving Waverider costa floor projection molded line, then S1 extremely
Known parameters in S3 are divided into benchmark flow field parameter (Ma, β) and geometric shape parameter (ψ, n, W, Ls, χBn、χBt) two kinds, it is referred to as
The input condition designed for Waverider.Rider body length L is acquired in S2.Rider body thickness (H) is by rider body length L and base
Quasi- flow field (Ma, β) determines.
Another specific embodiment of the invention is provided below, wherein give sweepback angle equation according to option b in S2 and solves
Waverider costa floor projection molded line, specific as follows:
Given benchmark flow field parameter: Ma=6, β=16 °；
Give stationary shock bottom section molded line parameter: W=4.32m, n=3, LS=0.01W.
Two kinds of shape scheme costa angle of sweep equation parameter values and upper counterangle value shown in table 2.
Table 2
Figure 14~Figure 17 is the top view and right view of above-mentioned shape.The angle of sweep of design outline is accorded with up/down dihedral
Close design requirement.
Although in conclusion the present invention has been disclosed as a preferred embodiment, however, it is not to limit the invention, any
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 this hair
Bright protection scope is subject to the range defined depending on claims.
Claims (7)
1. a kind of angle of sweep and the direct controllable osculating of up/down dihedral bore Waverider design method, which is characterized in that including following
Step:
S1: given benchmark flow field parameter, wherein benchmark flow field parameter includes free stream Mach number Ma, Angle of Shock Waves β；
S2: given sweepback angle equation simultaneously solves Waverider costa floor projection molded line；
Assuming that the angle of sweep of Waverider costa floor projection molded line is χ=χ (z) along the z Regularity Changes of body coordinate system,
Any point P on Waverider costa floor projection molded linelCorresponding its numerical value of angle of sweep of point is χl；Waverider costa is horizontal
Project P on molded linelThe corresponding angle of sweep χ of pointlWith Waverider costa floor projection curved dies there are following relationship, formula is seen
(1):
Waverider costa floor projection curved dies are x=f (z), z ∈ [0, W/2], and wherein W is Waverider width；
Waverider costa floor projection molded line can be solved by given sweepback angle equation and known Waverider parameter；
S3: shock wave bottom section molded line is solved；
Set the combination profile that shock wave bottom section molded line to be solved adds power curve as straight line；By given upper counterangle ψ, swash
Length of straigh line 2*LS, Waverider width W and power curve power n in wave base portion section molded line multiply in conjunction with what solution obtained
The symmetrical face thickness H of wave body acquires Waverider shock wave bottom section molded line；
S4: leading edge point on Waverider costa is solved；
S5: the streamline of Waverider lower surface is solved；
S6: geometric sheeting generates Waverider；
The streamline combination setting-out of all Waverider lower surfaces is obtained into Waverider lower surface, Waverider upper surface is using own streamline
Method generates.
2. angle of sweep according to claim 1 and the direct controllable osculating of up/down dihedral bore Waverider design method, special
Sign is that the solution procedure of S2 is as follows:
Given sweepback angle equation is shown in formula (2), wherein χA1,χA2It is constant, χA1With χA2Respectively sweepback angle equation difference section
Angle of sweep；
Formula (2) are substituted into known to (1):
Assuming that shown in costa floor projection curved dies such as formula (4):
Wherein kA1,bA1,kA2,bA2,z1It is parameter to be asked；
Known conditions is sweepback angle equation χ=χA(z), rider body length L and width W, then costa floor projection curved dies
(4) parameter to be asked can be provided by following formula (5) and formula (6) in:
CauseAngle of sweep χ in sweepback angle equation (2)A1,χA2Wanting for formula (7) need to be met simultaneously
It asks:
min(tan(χA1),tan(χA2)) < tan (χAb) < max (tan (χA1),tan(χA2)) (7)
Above-mentioned is the half curvilinear equation x=f (z) to Waverider costa floor projection molded line, and z ∈ [0, W/2] is solved,
Symmetry based on Waverider, the half that the other half curve of Waverider costa floor projection molded line can be obtained according to solution
Curve negotiating symmetry transformation obtains.
3. angle of sweep according to claim 1 and the direct controllable osculating of up/down dihedral bore Waverider design method, special
Sign is that the solution procedure of S2 is as follows:
It is rightIntegration type, and sweepback angle equation χ=χ (z) is substituted into, and is obtained using integration by substitution abbreviation
Formula (8):
Formula (1) is substituted into formula (8), further abbreviation obtains formula (9)；Formula (9) is costa floor projection curved dies x
The relational expression of=f (z) and sweepback angle equation χ=χ (z):
Wherein sweepback angle equation χ (z) need to meet the following conditions:
I. when z ∈ [0, W/2], χ '=χ ' (z) equation is continuous；
Ii. wherein sweepback angle equation extreme coordinates value χ (0)=χ1, χ (W/2)=χ2, and when [0, W/2] z ∈, χ (z) ∈
[χ1,χ2]；
If sweepback angle equation is along z coordinate linear change, i.e., as shown in formula (10):
Formula (10) is substituted into formula (9) and is obtained formula (11), as the costa floor projection curved dies of option b.
Parameter to be asked is m in formula (11)B、dB、CB, solve and see formula (12)；Known parameters are χ in formula (12)Bn、χBt, W,
χBn、χBtRespectively P on costa floor projection molded linen、PtThe corresponding angle of sweep of two o'clock, W are Waverider width,
Rider body length L is parameter to be asked, and sees formula (13):
By formula (12) it is found that option b passes through two endpoint, that is, P of head and the tail on costa floor projection molded linen、PtTwo o'clock is corresponding
Angle of sweep χBn、χBtAnd Waverider width W, control sweepback angular rate of change χ 'B(z)=mB, it is finally reached costa sweepback
The directly controllable target in angle；
Above-mentioned is the half curvilinear equation x=f (z) to Waverider costa floor projection molded line, and z ∈ [0, W/2] is solved,
Symmetry based on Waverider, the half that the other half curve of Waverider costa floor projection molded line can be obtained according to solution
Curve negotiating symmetry transformation obtains.
4. angle of sweep according to claim 2 or 3 and the direct controllable osculating of up/down dihedral bore Waverider design method,
It is characterized in that, the method for solving of S3 is as follows:
S3.1 gives Waverider upper counterangle ψ, length of straigh line 2*LS, Waverider width W and power in the molded line of shock wave bottom section
Secondary curve power n,；
S3.2 designs Waverider shock wave bottom section curved dies；
Shock wave bottom section curved dies are that straight line adds power curve, see formula (14):
Wherein on the y-z plane, a is power curve coefficients for Waverider bottom section, for coefficient of discharge to be asked；
The thickness H of the S3.3 solution Waverider plane of symmetry；
Known Angle of Shock Waves β and rider body length L solves Waverider plane of symmetry place using T-M equation and streamlined impeller method
Benchmark flow field and streamline in osculating face；According to the length that streamline is projected in Waverider bottom surface, it is thick that the Waverider plane of symmetry can be acquired
Spend H；
S3.4 solves Waverider shock wave bottom section curved dies；
PtThe coordinate of point is (0, W/2, h1), whereinh0=Ltan (β)；By PtPoint coordinate substitutes into
Formula (14) obtains formula (15):
Known designs Angle of Shock Waves β, rider body length L and upper counterangle ψ, power curve coefficients a can be acquired by substituting into formula (15).
5. angle of sweep according to claim 4 and the direct controllable osculating of up/down dihedral bore Waverider design method, special
Sign is that the method for solving of S4 is as follows:
S4.1 is discrete by the shock wave bottom section molded line solved in S3, obtains a series of discrete point；
S4.2 determines the corresponding osculating face of each discrete point on the molded line of shock wave bottom section；
S4.3 solves the shock wave curved dies on the molded line of shock wave bottom section in the corresponding osculating face of each discrete point；
S4.4 solves on the molded line of shock wave bottom section leading edge point coordinate in the corresponding osculating face of each discrete point.
6. angle of sweep according to claim 5 and the direct controllable osculating of up/down dihedral bore Waverider design method, special
Sign is, in S4.2, for any discrete point on the molded line of shock wave bottom section, remembers that the discrete point is A discrete point；
Shock wave bottom section molded line is found out first in the coordinate of the curvature circle-center point of A discrete point, and curvature circle-center point is simultaneously A discrete
The benchmark conical point in corresponding osculating face is put in the projection of Waverider bottom section；
Benchmark conical point in the corresponding osculating face of A discrete point is located in osculating cone Waverider benchmark conical point trajectory line；Shock wave
Benchmark conical point on the molded line of bottom section in the corresponding osculating face in arbitrary point is respectively positioned on osculating cone Waverider benchmark conical point rail
On trace；
Benchmark conical point of the shock wave bottom section molded line in curvature circle-center point osculating corresponding with the A discrete point face of A discrete point
Between line in the corresponding osculating face of A discrete point benchmark bore benchmark axis of cone line on, the two is conllinear；
The line between benchmark conical point in A discrete point osculating corresponding with A discrete point face is the corresponding osculating of A discrete point
Shock wave molded line in face；The benchmark that benchmark is bored in shock wave molded line osculating corresponding with A discrete point face in the corresponding osculating face of A discrete point
Cone axis angle is the design Angle of Shock Waves β given in S1；Shock wave molded line and A discrete point pair in the corresponding osculating face of A discrete point
The corresponding osculating face of plane i.e. A discrete point where the benchmark axis of cone line that benchmark is bored in the osculating face answered；
In S4.3, the line of the benchmark conical point in A discrete point osculating corresponding with A discrete point face is that A discrete point is corresponding
Shock wave molded line in osculating face；Because shock wave molded line is straight line in osculating face, shock wave molded line can lead in the corresponding osculating face of A discrete point
The coordinate of the two points of the benchmark conical point and A discrete point crossed in the corresponding osculating face of A discrete point acquires；
In S4.4, by the equation of shock wave molded line in the corresponding osculating face of A discrete point and Waverider costa floor projection molded line
Equations simultaneousness, can acquire the coordinate of the leading edge point in the corresponding osculating face of A discrete point, in the corresponding osculating face of A discrete point
Leading edge point is the leading edge point on Waverider costa.
7. angle of sweep according to claim 5 and the direct controllable osculating of up/down dihedral bore Waverider design method, special
Sign is that the implementation method of S5 is as follows:
S5.1 solves on the molded line of shock wave bottom section that in the corresponding osculating face of each discrete point benchmark flow field；
According to the free stream Mach number Ma and Angle of Shock Waves β given in S1, swashed by solving Taylor-Maccoll governing equation
Benchmark flow field in the corresponding osculating face of each discrete point on wave base portion section molded line, each discrete point is corresponding on the molded line of shock wave bottom section
Osculating face in benchmark flow field be taper flow field；
S5.2 solves streamline；
On the molded line of shock wave bottom section in the corresponding osculating face of each discrete point, by the leading edge point in each osculating face for being acquired in S4
Set out, on the shock wave bottom section molded line acquired in S5.1 in the corresponding osculating face of each discrete point in benchmark flow field using forward direction
Streamlined impeller method solves the corresponding streamline of the leading edge point i.e. streamline of Waverider lower surface in each osculating face.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109969374A (en) * | 2019-04-09 | 2019-07-05 | 中国空气动力研究与发展中心计算空气动力研究所 | Biao Mo aerodynamic arrangement and design method for hypersonic boundary layer transition research |
| CN111152909A (en) * | 2019-11-12 | 2020-05-15 | 湖南云顶智能科技有限公司 | Projection method based double-sweepback waverider design method for determining plane shape |
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| CN112949199A (en) * | 2021-03-15 | 2021-06-11 | 中国科学院力学研究所 | Method and system for optimizing longitudinal stability of power waverider |
| CN113148222A (en) * | 2021-05-24 | 2021-07-23 | 北京航空航天大学 | Close curved surface wave-rider positive design method suitable for complex leading edge shape |
| CN113212771A (en) * | 2021-04-13 | 2021-08-06 | 南京航空航天大学 | Improved general subsonic diffuser design method |
| CN113665837A (en) * | 2021-09-23 | 2021-11-19 | 中国人民解放军国防科技大学 | Method for designing pointed Von Karman curve steering engine bulge based on equal shock wave intensity of leading edge line |
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| CN113682491A (en) * | 2021-09-23 | 2021-11-23 | 中国人民解放军国防科技大学 | Steering engine bulge design method based on back edge line equal shock wave intensity wedge guided wave |
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| CN109969374A (en) * | 2019-04-09 | 2019-07-05 | 中国空气动力研究与发展中心计算空气动力研究所 | Biao Mo aerodynamic arrangement and design method for hypersonic boundary layer transition research |
| CN111152909A (en) * | 2019-11-12 | 2020-05-15 | 湖南云顶智能科技有限公司 | Projection method based double-sweepback waverider design method for determining plane shape |
| 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 |
| CN112949199A (en) * | 2021-03-15 | 2021-06-11 | 中国科学院力学研究所 | Method and system for optimizing longitudinal stability of power waverider |
| CN112949199B (en) * | 2021-03-15 | 2024-02-02 | 中国科学院力学研究所 | Method and system for optimizing longitudinal stability of power wave 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 |
| CN113212771A (en) * | 2021-04-13 | 2021-08-06 | 南京航空航天大学 | Improved general subsonic diffuser design method |
| CN113212771B (en) * | 2021-04-13 | 2022-04-05 | 南京航空航天大学 | Improved general subsonic diffuser design method |
| WO2022247050A1 (en) * | 2021-05-24 | 2022-12-01 | 北京航空航天大学 | Positive design method for osculating curved surface waverider suitable for complex leading edge shape |
| CN113148222A (en) * | 2021-05-24 | 2021-07-23 | 北京航空航天大学 | Close curved surface wave-rider positive design method suitable for complex leading edge shape |
| CN113148222B (en) * | 2021-05-24 | 2023-01-31 | 北京航空航天大学 | Close curved surface wave-rider positive design method suitable for complex leading edge shape |
| CN113665837A (en) * | 2021-09-23 | 2021-11-19 | 中国人民解放军国防科技大学 | Method for designing pointed Von Karman curve steering engine bulge based on equal shock wave intensity of leading edge line |
| CN113682491A (en) * | 2021-09-23 | 2021-11-23 | 中国人民解放军国防科技大学 | Steering engine bulge design method based on back edge line equal shock wave intensity wedge guided wave |
| CN113665835A (en) * | 2021-09-23 | 2021-11-19 | 中国人民解放军国防科技大学 | Steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave |
| CN113665836A (en) * | 2021-09-23 | 2021-11-19 | 中国人民解放军国防科技大学 | Method for designing pointed Von Karman curve steering engine bulge based on equal shock wave intensity of trailing edge line |
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