CN105173112A - Method for adjusting wing class model and system for adjusting wing class model - Google Patents

Method for adjusting wing class model and system for adjusting wing class model Download PDF

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CN105173112A
CN105173112A CN201510500199.9A CN201510500199A CN105173112A CN 105173112 A CN105173112 A CN 105173112A CN 201510500199 A CN201510500199 A CN 201510500199A CN 105173112 A CN105173112 A CN 105173112A
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wing
section
class model
leading edge
coordinate
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侯粉
李军府
付清
史娟娟
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Xian Aircraft Design and Research Institute of AVIC
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Xian Aircraft Design and Research Institute of AVIC
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Abstract

The invention discloses a method for adjusting a wing class model and a system for adjusting the wing class model. The method for adjusting the wing class model comprises the steps that parameters are given to the wing class model, the wing class model is established, and the wing class model comprises N subsections; all the parameters influenced by the number of the sections of the wing class model are determined, and expressions between all the parameters and the N sections are generated; and the value of N in the wing class model is changed freely, and the numerical values of the parameters in the wing class model are adjusted correspondingly according to the expressions between all the parameters and the N sections, and accordingly the adjusted wing class model is established. According to the method for adjusting the wing class model, the expressions between all the parameters and the N sections are generated. Accordingly, the numerical values of the parameters in the wing class model are adjusted correspondingly according to the expressions between all the parameters and the N sections by freely changing the value of N in the wing class model, and thus the adjusted wing class model is established. Compared with the prior art, after the value of N is changed, the wing class model can be obtained without the need for establishing the model again.

Description

A kind of adjust wing class model method and the system of adjustment wing class model
Technical field
The present invention relates to technical field of aerospace, particularly relate to a kind of adjust wing class model method and the system of adjustment wing class model.
Background technology
In the design of aircraft aerodynamic arrangement, in order to obtain better aeroperformance, complexity many inflections blended wing-body topological design of similar wing receives extensive concern, for this layout, can be regarded as the tapered airfoil with multiple segmentation according to the inflection position of wing front and rear edge, then its profile can be reduced to and have multiple segmentation and front and rear edge wing model linearly.
At present, the Parametric Representation of wing planform is mainly for attaching planar and the certain wing of segmentation hop count, adopt aspect ratio, reference area, leading edge sweep and slightly root ratio uniquely can determine wing planform, when needs change wing hop count, then need to increase design parameters, comprise inflection place exhibition to exhibition position, second segment wing slightly root than etc., thus need to re-establish parameterized model, increase work capacity.
Therefore, wish a kind of technical scheme to overcome or at least alleviate at least one above-mentioned defect of prior art.
Summary of the invention
The object of the present invention is to provide a kind of method adjusting wing class model to overcome or at least alleviate at least one above-mentioned defect of prior art.
For achieving the above object, the invention provides a kind of method adjusting wing class model.The method of described adjustment wing class model comprises: give wing class model parameter, set up wing class model, wherein, described wing class model comprises N number of segmentation; Determine the parameters affected by wing class model hop count and the expression formula generated between parameters and N section; The value of the N in any change wing class model, according to the expression formula between parameters and N section, the parameter values in the described wing class model of corresponding adjustment, thus set up the wing class model after adjustment.
Preferably, described wing class model parameter comprises: the coordinate of the coordinate of wing segmentation hop count, wing root leading edge point, wing root stagger angle, each section of leading edge of a wing sweepback angle, each section of wing half length, each section of wing chord length, each section of wing twist angle, each section of position of wing twist axle on wing chord, each section of wing inverted diherdral, each section of wing tip leading edge point;
The described parameters affected by wing class model hop count comprises: the coordinate of each section of leading edge of a wing sweepback angle, each section of wing half length, each section of wing chord length, each section of wing twist angle, each section of position of wing twist axle on wing chord, each section of wing inverted diherdral, each section of wing tip leading edge point.
Preferably, the expression formula between each section of wing half length and N section is specially: b n=(1-Rb n-1) b/2, wherein, b nit is half length of N section wing; Rb n-1be N-1 section wing tip exhibition account for half length ratio to position; B is length.
Preferably, the expression formula between each section of wing chord length and N section is specially: C n=C n-1tR n, wherein, C nit is the wing tip chord length of the wing of N section; C n-1it is the wing chord length of N-1 section; TR nbe the taper ratio of N section wing, wherein, N is greater than 1.
Preferably, when N equals 1, C n-1for wing root chord length, C nfor wing root chord length.
Preferably, the quantity of described each section of leading edge of a wing sweepback angle, described each section of wing twist angle and described each section of wing inverted diherdral is N number of; The quantity of the described each section of position of wing twist axle on wing chord is N+1.
Preferably, the coordinate of described each section of wing tip leading edge point comprise the leading edge point after torsion coordinate and lower anti-after the coordinate of leading edge point, wherein, first determine the coordinate of leading edge point after reversing, the basis of the coordinate of the leading edge point after determining described torsion is determined described lower anti-after the coordinate of leading edge point.
Preferably, the expression formula between the coordinate of the leading edge point after described torsion and N section is specially:
x LEN＝x LE(N-1)+b N·tan(Sweep N)+C N·P axisN·(1-cos(Incidence N))
y LEN＝y LE(N-1)+b N
Z lEN=z lE (N-1)+ C np axisNsin (Incidence n); Wherein,
X lENfor the coordinate of the leading edge point after the torsion of the N section wing of X-axis in wing class model; y lENfor the coordinate of the leading edge point after the torsion of the N section wing of Y-axis in wing class model; z lENfor the coordinate of the leading edge point after the torsion of the N section wing of Z axis in wing class model; x lE (N-1)for the coordinate of the leading edge point after the torsion of the N-1 section wing of X-axis in wing class model; y lE (N-1)for the coordinate of the leading edge point after the torsion of the N-1 section wing of Y-axis in wing class model; z lE (N-1)for the coordinate of the leading edge point after the torsion of the N-1 section wing of Z axis in wing class model; b nit is half length of N section wing; C nit is the wing tip chord length of the wing of N section; Sweep nit is the leading edge sweep of N section wing; P axisNbe the position of N section wing twist axle on wing chord; Incidence nit is the stagger angle of N section wing; And described lower anti-after the coordinate of leading edge point and N section between expression formula be specially:
x LdN＝x Ld(N-1)+b N·tan(Sweep N)+C N·P axisN·(1-cos(Incidence N))
y LdN＝y Ld(N-1)+b tempN·cos(atan(z LEN/y LEN)+Dihedral N)
z LdN＝z Ld(N-1)+C N·P axisN·sin(Incidence N)+b tempN·sin(Dihedral N)
X ldNfor X-axis in wing class model N section wing lower anti-after the coordinate of leading edge point; y ldNfor Y-axis in wing class model N section wing lower anti-after the coordinate of leading edge point; z ldNfor Z axis in wing class model N section wing lower anti-after the coordinate of leading edge point; x ld (N-1)for X-axis in wing class model N-1 section wing lower anti-after the coordinate of leading edge point; y ld (N-1)for Y-axis in wing class model N-1 section wing lower anti-after the coordinate of leading edge point; z ld (N-1)for Z axis in wing class model N-1 section wing lower anti-after the coordinate of leading edge point; b nit is half length of N section wing; C nit is the wing tip chord length of the wing of N section; Sweep nit is the leading edge sweep of N section wing; P axisNbe the position of N section wing twist axle on wing chord; Incidence nit is the stagger angle of N section wing; y lENfor the coordinate of the leading edge point after the torsion of the N section wing of Y-axis in wing class model; z lENfor the coordinate of the leading edge point after the torsion of the N section wing of Z axis in wing class model; b tempNfor ((b 1+ b 2+ ... + b n) 2+ z lEN 2) 0.5.
Preferably, it is characterized in that, described N gets positive integer.
Present invention also offers a kind of adjustment wing class model system, described adjustment wing class model system is used for the method for adjustment wing class model as above, and described adjustment wing class model system comprises: generate parameter expression unit, for generating parameter expression; Call unit, for calling the parameter expression generated in parameter expression unit; Calculating unit, for the parameter expression calculating parameter numerical value called by described call unit; Model generation unit, described model generation unit is for generating wing class model; Man-machine interaction unit, described man-machine interaction unit for controlling described model generation unit and generating parameter expression unit, and for showing the wing class model that described model generation unit generates.
The method of the adjustment wing class model in the present invention generates the expression formula between parameters and N section, thus can by changing arbitrarily the value of the N in wing class model, according to the expression formula between parameters and N section, parameter values in the described wing class model of corresponding adjustment, thus set up the wing class model after adjustment.Relative to prior art, without the need to re-establishing model, the wing class model after the value of the N that can acquire change.
Accompanying drawing explanation
Fig. 1 is the schematic flow sheet of the method adjusting wing class model according to an embodiment of the invention.
Detailed description of the invention
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
Fig. 1 is the schematic flow sheet of the method adjusting wing class model according to an embodiment of the invention.
The method of adjustment wing class model as shown in Figure 1 comprises: give wing class model parameter, set up wing class model, wherein, described wing class model comprises N number of segmentation; Determine the parameters affected by wing class model hop count and the expression formula generated between parameters and N section; The value of the N in any change wing class model, according to the expression formula between parameters and N section, the parameter values in the described wing class model of corresponding adjustment, thus set up the wing class model after adjustment.
Particularly, in the present embodiment, wing class parameter comprises: the coordinate of the coordinate of wing segmentation hop count, wing root leading edge point, wing root stagger angle, each section of leading edge of a wing sweepback angle, each section of wing half length, each section of wing chord length, each section of wing twist angle, each section of position of wing twist axle on wing chord, each section of wing inverted diherdral, each section of wing tip leading edge point;
The parameters affected by wing class model hop count comprises: the coordinate of each section of leading edge of a wing sweepback angle, each section of wing half length, each section of wing chord length, each section of wing twist angle, each section of position of wing twist axle on wing chord, each section of wing inverted diherdral, each section of wing tip leading edge point.
In the present embodiment, the expression formula between each section of wing half length and N section is specially: b n=(1-Rb n-1) b/2, wherein, b nit is half length of N section wing; Rb n-1be N-1 section wing tip exhibition account for half length ratio to position; B is length.
In the present embodiment, the expression formula between each section of wing chord length and N section is specially: C n=C n-1tR n, wherein, C nit is the wing tip chord length of the wing of N section; C n-1it is the wing chord length of N-1 section; TR nbe the taper ratio of N section wing, wherein, N is greater than 1.When N equals 1, C n-1for wing root chord length, C nfor wing root chord length.
Be understandable that, the quantity of each section of leading edge of a wing sweepback angle, each section of wing twist angle and each section of wing inverted diherdral is N number of; The quantity of each section of position of wing twist axle on wing chord is N+1.
Be understandable that, the coordinate of each section of wing tip leading edge point comprise the leading edge point after torsion coordinate and lower anti-after the coordinate of leading edge point, wherein, first determine the coordinate of leading edge point after reversing, the basis of the coordinate of the leading edge point after determining described torsion is determined described lower anti-after the coordinate of leading edge point.
In the present embodiment, the expression formula between the coordinate of the leading edge point after torsion and N section is specially:
x LEN＝x LE(N-1)+b N·tan(Sweep N)+C N·P axisN·(1-cos(Incidence N))
y LEN＝y LE(N-1)+b N
Z lEN=z lE (N-1)+ C np axisNsin (Incidence n); Wherein,
X lENfor the coordinate of the leading edge point after the torsion of the N section wing of X-axis in wing class model; y lENfor the coordinate of the leading edge point after the torsion of the N section wing of Y-axis in wing class model; z lENfor the coordinate of the leading edge point after the torsion of the N section wing of Z axis in wing class model; x lE (N-1)for the coordinate of the leading edge point after the torsion of the N-1 section wing of X-axis in wing class model; y lE (N-1)for the coordinate of the leading edge point after the torsion of the N-1 section wing of Y-axis in wing class model; z lE (N-1)for the coordinate of the leading edge point after the torsion of the N-1 section wing of Z axis in wing class model; b nit is half length of N section wing; C nit is the wing tip chord length of the wing of N section; Sweep nit is the leading edge sweep of N section wing; P axisNbe the position of N section wing twist axle on wing chord; Incidence nit is the stagger angle of N section wing; And lower anti-after the coordinate of leading edge point and N section between expression formula be specially:
x LdN＝x Ld(N-1)+b N·tan(Sweep N)+C N·P axisN·(1-cos(Incidence N))
y LdN＝y Ld(N-1)+b tempN·cos(atan(z LEN/y LEN)+Dihedral N)
z LdN＝z Ld(N-1)+C N·P axisN·sin(Incidence N)+b tempN·sin(Dihedral N)
X ldNfor X-axis in wing class model N section wing lower anti-after the coordinate of leading edge point; y ldNfor Y-axis in wing class model N section wing lower anti-after the coordinate of leading edge point; z ldNfor Z axis in wing class model N section wing lower anti-after the coordinate of leading edge point; x ld (N-1)for X-axis in wing class model N-1 section wing lower anti-after the coordinate of leading edge point; y ld (N-1)for Y-axis in wing class model N-1 section wing lower anti-after the coordinate of leading edge point; z ld (N-1)for Z axis in wing class model N-1 section wing lower anti-after the coordinate of leading edge point; b nit is half length of N section wing; C nit is the wing tip chord length of the wing of N section; Sweep nit is the leading edge sweep of N section wing; P axisNbe the position of N section wing twist axle on wing chord; Incidence nit is the stagger angle of N section wing; y lENfor the coordinate of the leading edge point after the torsion of the N section wing of Y-axis in wing class model; z lENfor the coordinate of the leading edge point after the torsion of the N section wing of Z axis in wing class model; b tempNfor ((b 1+ b 2+ ... + b n) 2+ z lEN 2) 0.5.
Advantageously, N is positive integer.
Present invention also offers a kind of adjustment wing class model system, described adjustment wing class model system is used for the method for adjustment wing class model as above, and described adjustment wing class model system comprises: generate parameter expression unit, for generating parameter expression; Call unit, for calling the parameter expression generated in parameter expression unit; Calculating unit, for the parameter expression calculating parameter numerical value called by described call unit; Model generation unit, described model generation unit is for generating wing class model; Man-machine interaction unit, described man-machine interaction unit for controlling described model generation unit and generating parameter expression unit, and for showing the wing class model that described model generation unit generates.
Be understandable that, following description is used for each definition in specific explanations foregoing description, defines known wing parametric variable and comprises:
Wing segmentation hop count: N
Reference area: S ref
Aspect ratio: AR
Wing root leading edge R point coordinate: (x 0, y 0, z 0)
Wing root stagger angle: Incidence 0
Each section of leading edge of a wing sweepback angle: Sweep 1, Sweep 2..., Sweep i..., Sweep n
Each section of wing tip exhibition accounts for half length ratio: Rb to position 1, Rb 2... Rb i..., Rb n
Each section of wing slightly root ratio: TR 1, TR 2..., TR i..., TR n
Each section of wing twist angle: Twist 1, Twist 2..., Twist i..., Twist n
Each section of wing twist axle chordwise location: P axis0, P axis1..., P axisi..., P axisN(0≤P axisi≤ 1)
The each section of wing dihedral angle: Dihedral 1, Dihedral 2..., Dihedral i..., Dihedral n
In addition, the definition of other correlation parameters comprises:
Stagger angle: each section chord line of wing around the corner of its rotating shaft relative to fuselage datum, with aircraft angle of attack in the same way;
Twist angle: the difference of each section of wing tip stagger angle self wing root stagger angle relative;
The dihedral angle: the vertical line of horizontal datum and the angle of level reference in the string of a musical instrument pivot point to the plane of symmetry of place, wing section.
Coordinate axle: X-axis points to tail along fuselage, Y-axis is along exhibition to sensing right side wing, and Z axis and XY plane orthogonal are just upwards.
Parameter derivation is:
1) span: b=(ARS ref) 0.5(formula 1)
2) each section of wing half length:
b 1＝Rb 1·b/2
b 2＝Rb 2·b/2-Rb 1·b/2＝(Rb 2-Rb 1)·b/2
……
b i＝(Rb i-Rb i-1)·b/2
……
B n=(1-Rb n-1) b/2 (formula 2)
3) each section of wing chord length:
Definition according to each section of wing slightly root ratio obtains:
C 1＝C 0·TR 1
C 2＝C 1·TR 2＝C 0·TR 1·TR 2
……
C i＝C i-1·TR i＝C 0·TR 1·TR 2·…·TR i
……
C n=C n-1tR n=C 0tR 1tR 2tR 3tR n(formula 3)
And obtain according to the definition of each section of wing area (half wing):
S 1＝0.5b 1·(C 0+C 1)＝0.5b 1·(C 0+C 0·TR 1)＝0.5b 1·C 0(1+TR 1)
S 2＝0.5b 2·(C 1+C 2)＝0.5b 2·(C 0·TR 1+C 0·TR 1·TR 2)＝0.5b 2·C 0·TR 1(1+TR 2)
……
S i＝0.5b i·(C i-1+C i)＝0.5b i·(C 0·TR 1·TR 2·…·TR i-1+C 0·TR 1·TR 2·…·TR i)
＝0.5b i·C 0·TR 1·TR 2·…·TR i-1(1+TR i)
……
S N＝0.5b N·(C N-1+C N)＝0.5b N·(C 0·TR 1·TR 2·…·TR N-1+C 0·TR 1·TR 2·…·TR N)
＝0.5b N·C 0·TR 1·TR 2·…·TR N-1(1+TR N)
By full wing area relation:
S ref＝2(S 1+S 2+…S i…+S N)
＝b 1·C 0(1+TR 1)+b 2·C 0·TR 1(1+TR 2)+…+b i·C 0·TR 1·TR 2·…·TR i-1(1+TR i)+…+b N·C 0·TR 1·TR 2·…·TR N-1(1+TR N)
＝C 0(b 1·(1+TR 1)+b 2·TR 1(1+TR 2)+…+b i·TR 1·TR 2·…·TR i-1(1+TR i)+…+b N·TR 1·TR 2·…·TR N-1(1+TR N))
Obtain:
C 0=S ref/ (b 1(1+TR 1)+b 2tR 1(1+TR 2)+... + b itR 1tR 2tR i-1(1+TR i)+... + b ntR 1tR 2tR n-1(1+TR n)) (formula 4)
By formula 4) substitute into formula 3) can obtain: C 1, C 2..., C i..., C n
4) each section of wing half blade area can be obtained according to the area definition expression formula of preceding paragraphs wing:
S 1，S 2，…，S i，…，S N
5) consider that the wing root leading edge point coordinate of wing root stagger angle is:
x LE0＝x 0+C 0·P axis0·(1-cos(Incidence 0))
y LE0＝y 0
z LE0＝z 0+C 0·P axis0·sin(Incidence 0)
6) each section of wing tip leading edge point coordinate after consideration twist angle
According to the relation of stagger angle and twist angle, the stagger angle obtaining each section of wing tip is:
Incidence 1＝Incidence 0+Twist 1
Incidence 2＝Incidence 1+Twist 2
……
Incidence i＝Incidence i-1+Twist i
……
Incidence N＝Incidence N-1+Twist N
After obtaining considering twist angle by deriving, the coordinate of each section of wing tip leading edge point is:
X lE1=x 0(wing root R point)+b 1tan (Sweep 1)+C 1p axis1(1-cos (Incidence 1))
y LE1＝y 0+b 1
z LE1＝z 0+C 1·P axis1·sin(Incidence 1)
x LE2＝x LE1+b 2·tan(Sweep 2)+C 2·P axis2·(1-cos(Incidence 2))
y LE2＝y LE1+b 2
z LE2＝z LE1+C 2·P axis2·sin(Incidence 2)
……
x LEi＝x LE(i-1)+b i·tan(Sweep i)+C i·P axisi·(1-cos(Incidence i))
y LEi＝y LE(i-1)+b i
z LEi＝z LE(i-1)+C i·P axisi·sin(Incidence i)
……
x LEN＝x LE(N-1)+b N·tan(Sweep N)+C N·P axisN·(1-cos(Incidence N))
y LEN＝y LE(N-1)+b N
z LEN＝z LE(N-1)+C N·P axisN·sin(Incidence N)
7) each section of wing tip leading edge point coordinate after consideration inverted diherdral
On each section of wing tip elevation profile string of a musical instrument, leading edge point is to the vertical distance (after reversing) of horizontal datum:
b temp1＝(b 1 2+z LE1 2) 0.5
b temp2＝((b 1+b 2) 2+z LE2 2) 0.5
……
b tempN＝((b 1+b 2+…+b N) 2+z LEN 2) 0.5
After considering inverted diherdral, the leading edge point coordinate of wing tip is:
x Ld1＝x 0+b 1·tan(Sweep 1)+C 1·P axis1·(1-cos(Incidence 1))
y Ld1＝y 0+b temp1·cos(atan(z LE1/y LE1)+Dihedral 1)
z Ld1＝z 0+C 1·P axis1·sin(Incidence 1)+b temp1·sin(Dihedral 1)
x Ld2＝x Ld1+b 2·tan(Sweep 2)+C 2·P axis2·(1-cos(Incidence 2))
y Ld2＝y Ld1+b temp2·cos(atan(z LE2/y LE2)+Dihedral 2)
z Ld2＝z Ld1+C 2·P axis2·sin(Incidence 2)+b temp2·sin(Dihedral 2)
……
x Ldi＝x Ld(i-1)+b i·tan(Sweep i)+C i·P axisi·(1-cos(Incidence i))
y Ldi＝y Ld(i-1)+b tempi·cos(atan(z LEi/y LEi)+Dihedral i)
z Ldi＝z Ld(i-1)+C i·P axisi·sin(Incidence i)+b tempi·sin(Dihedral i)
……
x LdN＝x Ld(N-1)+b N·tan(Sweep N)+C N·P axisN·(1-cos(Incidence N))
y LdN＝y Ld(N-1)+b tempN·cos(atan(z LEN/y LEN)+Dihedral N)
z LdN＝z Ld(N-1)+C N·P axisN·sin(Incidence N)+b tempN·sin(Dihedral N)
According to above parameter derivation, the data expressing whole wing profile can be obtained, determine the planar profile of whole wing.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.

Claims (10)

1. adjust a method for wing class model, it is characterized in that, the method for described adjustment wing class model comprises:
Give wing class model parameter, set up wing class model, wherein, described wing class model comprises N number of segmentation;
Determine the parameters affected by wing class model hop count and the expression formula generated between parameters and N section;
The value of the N in any change wing class model, according to the expression formula between parameters and N section, the parameter values in the described wing class model of corresponding adjustment, thus set up the wing class model after adjustment.
2. the method for adjustment wing class model as claimed in claim 1, it is characterized in that, described wing class model parameter comprises: the coordinate of the coordinate of wing segmentation hop count, wing root leading edge point, wing root stagger angle, each section of leading edge of a wing sweepback angle, each section of wing half length, each section of wing chord length, each section of wing twist angle, each section of position of wing twist axle on wing chord, each section of wing inverted diherdral, each section of wing tip leading edge point;
The described parameters affected by wing class model hop count comprises: the coordinate of each section of leading edge of a wing sweepback angle, each section of wing half length, each section of wing chord length, each section of wing twist angle, each section of position of wing twist axle on wing chord, each section of wing inverted diherdral, each section of wing tip leading edge point.
3. the method for adjustment wing class model as claimed in claim 2, it is characterized in that, the expression formula between each section of wing half length and N section is specially:
B n=(1-Rb n-1) b/2, wherein,
B nit is half length of N section wing; Rb n-1be N-1 section wing tip exhibition account for half length ratio to position; B is length.
4. the method for adjustment wing class model as claimed in claim 2, it is characterized in that, the expression formula between each section of wing chord length and N section is specially:
C n=C n-1tR n, wherein,
C nit is the wing tip chord length of the wing of N section; C n-1it is the wing chord length of N-1 section; TR nbe the taper ratio of N section wing, wherein, N is greater than 1.
5. the method for adjustment wing class model as claimed in claim 4, is characterized in that, when N equals 1, and C n-1for wing root chord length, C nfor wing root chord length.
6. the method for adjustment wing class model as claimed in claim 2, is characterized in that, the quantity of described each section of leading edge of a wing sweepback angle, described each section of wing twist angle and described each section of wing inverted diherdral is N number of;
The quantity of the described each section of position of wing twist axle on wing chord is N+1.
7. the method for adjustment wing class model as claimed in claim 2, it is characterized in that, the coordinate of described each section of wing tip leading edge point comprise the leading edge point after torsion coordinate and lower anti-after the coordinate of leading edge point, wherein, first determine the coordinate of leading edge point after reversing, the basis of the coordinate of the leading edge point after determining described torsion is determined described lower anti-after the coordinate of leading edge point.
8. the method for adjustment wing class model as claimed in claim 7, it is characterized in that, the expression formula between the coordinate of the leading edge point after described torsion and N section is specially:
x LEN＝x LE(N-1)+b N·tan(Sweep N)+C N·P axisN·(1-cos(Incidence N))
y LEN＝y LE(N-1)+b N
Z lEN=z lE (N-1)+ C np axisNsin (Incidence n); Wherein,
X lENfor the coordinate of the leading edge point after the torsion of the N section wing of X-axis in wing class model; y lENfor the coordinate of the leading edge point after the torsion of the N section wing of Y-axis in wing class model; z lENfor the coordinate of the leading edge point after the torsion of the N section wing of Z axis in wing class model; x lE (N-1)for the coordinate of the leading edge point after the torsion of the N-1 section wing of X-axis in wing class model; y lE (N-1)for the coordinate of the leading edge point after the torsion of the N-1 section wing of Y-axis in wing class model; z lE (N-1)for the coordinate of the leading edge point after the torsion of the N-1 section wing of Z axis in wing class model; b nit is half length of N section wing; C nit is the wing tip chord length of the wing of N section; Sweep nit is the leading edge sweep of N section wing; P axisNbe the position of N section wing twist axle on wing chord; Incidence nit is the stagger angle of N section wing; And
Described lower anti-after the coordinate of leading edge point and N section between expression formula be specially:
x LdN＝x Ld(N-1)+b N·tan(Sweep N)+C N·P axisN·(1-cos(Incidence N))
y LdN＝y Ld(N-1)+b tempN·cos(atan(z LEN/y LEN)+Dihedral N)
z LdN＝z Ld(N-1)+C N·P axisN·sin(Incidence N)+b tempN·sin(Dihedral N)
X ldNfor X-axis in wing class model N section wing lower anti-after the coordinate of leading edge point; y ldNfor Y-axis in wing class model N section wing lower anti-after the coordinate of leading edge point; z ldNfor Z axis in wing class model N section wing lower anti-after the coordinate of leading edge point; x ld (N-1)for X-axis in wing class model N-1 section wing lower anti-after the coordinate of leading edge point; y ld (N-1)for Y-axis in wing class model N-1 section wing lower anti-after the coordinate of leading edge point; z ld (N-1)for Z axis in wing class model N-1 section wing lower anti-after the coordinate of leading edge point; b nit is half length of N section wing; C nit is the wing tip chord length of the wing of N section; Sweep nit is the leading edge sweep of N section wing; P axisNbe the position of N section wing twist axle on wing chord; Incidence nit is the stagger angle of N section wing; y lENfor the coordinate of the leading edge point after the torsion of the N section wing of Y-axis in wing class model; z lENfor the coordinate of the leading edge point after the torsion of the N section wing of Z axis in wing class model; b tempNfor ((b 1+ b 2+ ... + b n) 2+ z lEN 2) 0.5.
9. adjust the method for wing class model as claimed in any of claims 1 to 8 in one of claims, it is characterized in that, described N gets positive integer.
10. adjust a wing class model system, it is characterized in that, described adjustment wing class model system is used for the method for adjustment wing class model as in one of claimed in any of claims 1 to 9, and described adjustment wing class model system comprises:
Generate parameter expression unit, for generating parameter expression;
Call unit, for calling the parameter expression generated in parameter expression unit;
Calculating unit, for the parameter expression calculating parameter numerical value called by described call unit;
Model generation unit, described model generation unit is for generating wing class model;
Man-machine interaction unit, described man-machine interaction unit for controlling described model generation unit and generating parameter expression unit, and for showing the wing class model that described model generation unit generates.
CN201510500199.9A 2015-08-14 2015-08-14 Method for adjusting wing class model and system for adjusting wing class model Pending CN105173112A (en)

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CN111907731A (en) * 2020-08-19 2020-11-10 中国航天空气动力技术研究院 Wing rudder surface variable parameter experiment simulation method

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109726408A (en) * 2017-10-30 2019-05-07 北京航空航天大学 Wing quickly becomes formal parameter modeling method
CN109726408B (en) * 2017-10-30 2020-11-20 北京航空航天大学 Wing rapid variable-outline parameter modeling method
CN110940481A (en) * 2019-11-13 2020-03-31 中国航天空气动力技术研究院 Dynamic derivative test model of high-speed wind tunnel of flying wing layout aircraft
CN111907731A (en) * 2020-08-19 2020-11-10 中国航天空气动力技术研究院 Wing rudder surface variable parameter experiment simulation method
CN111907731B (en) * 2020-08-19 2022-03-04 中国航天空气动力技术研究院 Wing rudder surface variable parameter experiment simulation method

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