CN113239473B - Lifting body standard die design method for composite material performance prediction and aircraft - Google Patents

Lifting body standard die design method for composite material performance prediction and aircraft Download PDF

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CN113239473B
CN113239473B CN202110781547.XA CN202110781547A CN113239473B CN 113239473 B CN113239473 B CN 113239473B CN 202110781547 A CN202110781547 A CN 202110781547A CN 113239473 B CN113239473 B CN 113239473B
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aircraft
designing
curve
section
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CN113239473A (en
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刘深深
吴晓军
陈坚强
贾洪印
袁先旭
杜雁霞
余婧
尤其
陈兵
桂业伟
周桂宇
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Computational Aerodynamics Institute of China Aerodynamics Research and Development Center
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    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/08—Fluids
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/26—Composites
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces

Abstract

The invention discloses a design method of a lifting body standard model for predicting the performance of a composite material and an aircraft, wherein the design method comprises the following steps: firstly, determining upper and lower surface contour lines of an aircraft according to given constraint conditions, and designing an upper contour line, wherein the upper and lower surface contour lines are symmetrical about an x axis; determining left and right width contour lines according to the designed length and width of the aircraft and the spherical surface chamfer angle of the head, designing a left contour line, wherein the left and right contour lines are completely symmetrical about the x axis; step three, designing a bottom section curve; step four, after designing the bottom section curve, designing the section curve; designing a section curved surface after designing the section curve; step six, designing a head curved surface; step seven, the curved surfaces obtained in the step five and the step six are respectively symmetrical about the y axis and the z axis, so that the curve design at the x section is completed, and the appearance of the aircraft is generated; the method is beneficial to the examination and improvement of the performance prediction method of the composite material.

Description

Lifting body standard die design method for composite material performance prediction and aircraft
Technical Field
The invention relates to the technical field of aerodynamic layout design of aircrafts, in particular to a design method of a lifting body standard model for performance prediction of a composite material and an aircraft.
Background
With the development of the new generation of aircrafts towards the trends of long endurance, complex configuration, higher flying speed and the like, more rigorous requirements are put forward on the thermal safety and thermal reliability of the aircrafts, and a heat-proof/load-bearing integrated non-ablative thermal protection system based on a novel composite material is becoming a new characteristic of the new generation of hypersonic aircrafts. Therefore, the macro/micro performance of the novel composite material is mastered, the prediction method of the material force, the thermal characteristics and the damage evolution behavior in the service process of the novel composite material is developed, and the fine evaluation method of the thermal safety of the material/structure is established, so that the method has important scientific significance and application value for promoting the innovation of the heat-proof composite material and the heat-proof structure and the spanning development of the aircraft.
However, the model mechanism of the cross-scale performance prediction method of the thermal effect of the composite material is very complex, the difficulty in engineering practice is difficult to overcome only by a single research means, a specific standard model flight shape needs to be designed for research, and comprehensive research is carried out on the standard model shape by combining various means such as theoretical analysis, numerical simulation, wind tunnel experiment and the like, so that the performance prediction method of the composite material is examined and improved by using the research results of the various means. And for the design of the standard model pneumatic layout suitable for the performance prediction model assessment of the heat-proof composite material, the following key requirements mainly exist: (1) firstly, the shape of a standard model needs to have the typical characteristics of the current high-speed aircraft, so that a research object has representativeness, and meanwhile, in order to meet the simplicity of comparison research of three means, the configuration characteristics of the aircraft need to be the simplification of the typical aircraft; (2) in order to facilitate the performance evaluation of the heat-proof material in the wind tunnel experiment and flight experiment processes, the overall configuration characteristics of the surface of the aircraft must be smooth, so that the sheet heat-proof material can be easily arranged on the surface of the aircraft, and meanwhile, the sensors can be arranged; (3) to ensure instrument and sensor loading during flight testing, the aircraft must not be too flat and require large loads. (4) In the wind tunnel and flight test process, the error randomness of the sensor measurement is considered, and in order to ensure the availability of flight data, the aircraft needs to be provided with symmetrical test areas for comparison verification research so as to perform comparison analysis on wind tunnel data and flight data.
In order to solve the key problems, the invention provides a novel lifting body model designing method suitable for performance prediction and assessment of composite materials and an aircraft.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, provides a lifting body model design method for predicting the performance of a composite material and an aircraft, can meet the requirements in the background art, has complete analytic design compared with the traditional design method, and is simpler in designed appearance and structure, beneficial to checking and improving the performance prediction method of the composite material and the like.
The purpose of the invention is realized by the following scheme:
a design method of a lifting body marking die for predicting the performance of a composite material comprises the following steps:
firstly, determining upper and lower surface contour lines of an aircraft according to given constraint conditions, and designing an upper contour line, wherein the upper and lower surface contour lines are symmetrical about an x axis;
determining left and right width contour lines according to the designed length and width of the aircraft and the spherical surface chamfer angle of the head, designing a left contour line, wherein the left and right contour lines are completely symmetrical about the x axis;
step three, after the left and right contour lines are designed, designing a bottom section curve;
step four, after designing the bottom section curve, designing the section curve;
designing a section curved surface after designing the section curve;
step six, designing a head curved surface;
and seventhly, the curved surfaces obtained in the fifth step and the sixth step are respectively symmetrical about the y axis and the z axis, so that the curve design at the x section is completed, and the appearance of the aircraft is generated.
Further, in the step one, the method comprises the steps of:
given the length L of the aircraft design, the bottom section half height
Figure 467773DEST_PATH_IMAGE001
Radius of head
Figure 67381DEST_PATH_IMAGE002
Spherical corner cut of head
Figure 48982DEST_PATH_IMAGE003
The constraint of (2); determining the contour lines of the upper and lower surfaces of the aircraft according to the constraint conditions, wherein the radius of the head part of the contour line of the upper surface is
Figure 835672DEST_PATH_IMAGE002
Is formed by adding a line segment BC, and the corresponding angle of the arc segment is
Figure 678863DEST_PATH_IMAGE004
At a tangent angle to the line segment
Figure 398557DEST_PATH_IMAGE003
Tangent, point A is the origin of coordinates, point B is the end point of the arc segment,
Figure 52524DEST_PATH_IMAGE005
is a line segment, the tangent point of the circular arc and the line segment is B according to the radius of the head
Figure 326510DEST_PATH_IMAGE002
Angle of arc
Figure 973392DEST_PATH_IMAGE004
And calculating to obtain the coordinates of the point B as follows:
Figure 282014DEST_PATH_IMAGE006
thus obtained from point A, B coordinates
Figure 608346DEST_PATH_IMAGE007
As a center of circle, in
Figure 635208DEST_PATH_IMAGE002
Is a circular arc AB of radius;
according to both the length L and the half height of the bottom section
Figure 820202DEST_PATH_IMAGE001
Constraining to obtain the coordinate of the point C as
Figure 248909DEST_PATH_IMAGE008
(ii) a And connecting the two points to obtain a contour line BC, so that the design of an upper contour line is completed, and the upper surface contour line and the lower surface contour line are completely symmetrical about the x axis.
Further, in the second step, the method comprises the following steps:
length L, width W and spherical head chamfer angle according to aircraft design
Figure 244678DEST_PATH_IMAGE009
Determining left and right width contour lines, wherein the point A is the origin of coordinates which are
Figure 758836DEST_PATH_IMAGE010
(ii) a Constrained according to the length L and the width W to obtain
Figure 481941DEST_PATH_IMAGE011
Point coordinates of
Figure 765155DEST_PATH_IMAGE012
；
Figure 430361DEST_PATH_IMAGE013
Dot sum
Figure 166236DEST_PATH_IMAGE014
The points are located on the same plane
Figure 224190DEST_PATH_IMAGE015
Thus, can obtain
Figure 96331DEST_PATH_IMAGE016
(ii) a Known circular arc
Figure 699482DEST_PATH_IMAGE017
And line segment
Figure 657074DEST_PATH_IMAGE018
Tangent to point
Figure 518719DEST_PATH_IMAGE013
According to the head section cutting angle
Figure 510946DEST_PATH_IMAGE009
And
Figure 520884DEST_PATH_IMAGE013
point x coordinate, determining the sum of points A and B
Figure 965772DEST_PATH_IMAGE013
The radius of the circle of points is
Figure 365529DEST_PATH_IMAGE019
Center of circle
Figure 212262DEST_PATH_IMAGE020
The coordinates are
Figure 157216DEST_PATH_IMAGE021
(ii) a Is calculated to obtain
Figure 823820DEST_PATH_IMAGE022
The point coordinates are:
Figure 761689DEST_PATH_IMAGE023
according to the radius of the arc, the starting point A and the end point of the arc
Figure 462929DEST_PATH_IMAGE013
Center of circle
Figure 342898DEST_PATH_IMAGE020
Determining a circular arc
Figure 762378DEST_PATH_IMAGE024
Contour lines; connection point
Figure 238359DEST_PATH_IMAGE013
And point
Figure 59684DEST_PATH_IMAGE025
To obtain a line segment
Figure 346440DEST_PATH_IMAGE026
，
Figure 253217DEST_PATH_IMAGE013
The point being a circular arc
Figure 532888DEST_PATH_IMAGE027
And line segment
Figure 208720DEST_PATH_IMAGE028
The tangent point of (A); the design of the left contour line is completed, and the left contour line and the right contour line are completely symmetrical about the x axis.
Further, in step three, the method comprises the steps of:
designing a bottom section curve, wherein the bottom section curve is respectively symmetrical about a y axis and a z axis, so that only one quarter of the bottom section curve is required to be designed; from step one, the coordinates of point C are obtained
Figure 167842DEST_PATH_IMAGE029
From the second step
Figure 561915DEST_PATH_IMAGE025
Point coordinates of
Figure 379698DEST_PATH_IMAGE030
(ii) a According to the length of CDDegree of rotation
Figure 175615DEST_PATH_IMAGE031
And bottom section half height
Figure 538595DEST_PATH_IMAGE001
Two constraints, get the coordinates of the D point as
Figure 419963DEST_PATH_IMAGE032
(ii) a Connecting C, D to obtain segment CD; circular arc
Figure 182383DEST_PATH_IMAGE033
Is a point
Figure 957441DEST_PATH_IMAGE034
As the center of a circle, the radius is R, and the angle of the arc
Figure 881534DEST_PATH_IMAGE035
Determining a circular arc; line segment DE and arc
Figure 358521DEST_PATH_IMAGE036
Tangent to point E, half height of bottom section
Figure 393473DEST_PATH_IMAGE001
Width W and circle
Figure 288617DEST_PATH_IMAGE035
And (4) constraining the radius R, and determining the coordinates of the point E as follows:
Figure 383612DEST_PATH_IMAGE037
connecting D, E two points to obtain a line segment DE; at this point, the bottom section curve is complete.
Further, in step four, the method comprises the steps of:
the cross-sectional curve is designed,
Figure 114939DEST_PATH_IMAGE038
the section curve is a quarter ellipse, namely a circular arc
Figure 688002DEST_PATH_IMAGE039
(ii) a Respectively obtaining a point B from the first step and the second step,
Figure 437653DEST_PATH_IMAGE040
Point coordinates from which the minor and major semi-axes of the ellipse are determined, respectively
Figure 969128DEST_PATH_IMAGE038
Cross-sectional curve of (a).
Further, in step five, the method comprises the steps of:
the section curved surface from the point B to the point C adopts a multi-section curved surface connection mode; obtaining a line segment BC and a line segment BC from the step one and the step two
Figure 411918DEST_PATH_IMAGE041
Obtained by the third step and the fourth step
Figure 788672DEST_PATH_IMAGE042
、
Figure 392829DEST_PATH_IMAGE043
Cross-sectional curve of (a); selecting
Figure 829627DEST_PATH_IMAGE042
、
Figure 269966DEST_PATH_IMAGE043
Upper section curve, with line segments BC and
Figure 715991DEST_PATH_IMAGE041
and (3) adopting a multi-section curved surface connection mode for guiding the line to complete the design of the section curved surface.
Further, in the sixth step, the method comprises the steps of:
the section curved surface before the point B adopts a bridging curved surface connection mode; from step two, the arc can be obtained
Figure 909075DEST_PATH_IMAGE044
From the fourth step, the arc can be obtained
Figure 782353DEST_PATH_IMAGE045
(ii) a Selecting arcs using bridged surface definitions
Figure 834623DEST_PATH_IMAGE045
Selecting a circular arc as a first curve, taking the curved surface obtained in the step five as a first supporting surface
Figure 192661DEST_PATH_IMAGE044
And the design of the head curved surface is finished for the second curve.
An aircraft based on the lifting body standard model design method for composite material performance prediction adopts the steps from one step to seven to process to generate the appearance of the aircraft; and the overall configuration characteristic of the generated aircraft shape is a symmetrical configuration formed by splicing six flat plates, the aircraft shape is symmetrical up and down and left and right, and the aircraft shape is smoothly transited from a head ellipse to a bottom hexahedral section.
The invention has the beneficial effects that:
(1) the design method and the aircraft obtained by the design method provided by the invention can meet the requirements in the background technology, and compared with the traditional design method, the design method has the advantages that the method can be completely analyzed and designed, the designed appearance is simpler, the structure is simpler, and the performance prediction method of the composite material is favorably examined and improved. Specifically, in the embodiment of the invention, a typical large-sweepback delta wing lifting body is selected as a reference layout configuration of the aircraft, so that the typical layout characteristics of the current mainstream lifting body type hypersonic aircraft can be embodied; meanwhile, the overall configuration of the aircraft is characterized by a symmetrical configuration formed by splicing six flat plates, and the six flat plate regions can facilitate the mounting of the composite material in a patch in a wind tunnel experiment and a flight experiment and the mounting requirements of corresponding sensors; meanwhile, the aircraft is designed in a vertically and horizontally symmetrical mode, the upper flat plate and the lower flat plate can perform contrastive analysis on test results under a zero-degree attack angle state, the left flat plate and the right flat plate can also perform contrastive analysis on the test results and correction of sensor errors, and the bilaterally symmetrical design also can ensure contrastive analysis on the test results and correction of the sensor errors under a non-zero-degree attack angle state; finally, the aircraft is designed to be in smooth transition from the head ellipse to the hexahedral section at the bottom, so that the aircraft keeps the similar convex curved surface characteristic, and the aircraft has a large filling space and can facilitate the installation of instruments in the flight test process. Therefore, the scheme of the invention can provide a new design method and the appearance of the aircraft for the standard model suitable for the performance prediction and assessment of the composite material.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 shows the results of the design of the upper and lower surface contours in an embodiment of the present invention;
FIG. 2 is a left and right width contour design in accordance with an embodiment of the present invention;
FIG. 3 is a bottom section contour design in accordance with an embodiment of the present invention, wherein (a) is a schematic design of a semi-section curve of an aircraft and (b) is a schematic design of a radius curve of an aircraft;
FIG. 4 is a bottom part of an embodiment of the present invention
Figure 381197DEST_PATH_IMAGE046
And (4) designing a section profile.
Detailed Description
All features disclosed in all embodiments in this specification, or all methods or process steps implicitly disclosed, may be combined and/or expanded, or substituted, in any way, except for mutually exclusive features and/or steps.
As shown in fig. 1 to 4, the invention aims to provide a lifting body model designing method and an aircraft suitable for performance prediction and assessment of composite materials. The innovation point of the embodiment of the invention is to provide a design method of a sweepback delta wing lifting body standard die with the surface-symmetric multi-flat-plate splicing configuration characteristic. The characteristic features of the hypersonic aircraft are represented by adopting sweepback delta wing characteristics, the flat area installation test requirements of composite materials in a plurality of areas are met by adopting an upper flat plate, a lower flat plate, a left flat plate and a right flat plate, meanwhile, the test data comparison and check under the states of a zero attack angle and a non-zero attack angle can be realized by adopting the upper and lower symmetrical and left and right symmetrical design, and meanwhile, the filling space of a marking mold of the hypersonic aircraft is ensured by the smooth transition from the head ellipse to the bottom hexagonal section, so that the filling of a sensor measuring device in a flight test is facilitated.
The technical scheme of the invention is as follows: a novel design method of a lifting body standard model suitable for performance prediction and assessment of composite materials and an aircraft are disclosed, and the design method comprises the following steps:
the method comprises the following steps: given the length L of the aircraft design, the bottom section half height, the head radius
Figure 284431DEST_PATH_IMAGE002
Spherical corner cut of head
Figure 823996DEST_PATH_IMAGE003
A constraint condition. Determining the contour lines of the upper and lower surfaces of the aircraft according to the constraint conditions, wherein the radius of the head part of the contour line of the upper surface is
Figure 221611DEST_PATH_IMAGE002
Is formed by adding a line segment BC, and the corresponding angle of the arc segment is
Figure 530232DEST_PATH_IMAGE004
At a tangent angle to the line segment
Figure 604368DEST_PATH_IMAGE003
The tangent is shown in the attached figure 1 in a concrete curve form. The point A is the origin of coordinates, the point B is the end point of the circular arc segment,
Figure 631229DEST_PATH_IMAGE005
is a line segment, the tangent point of the circular arc and the line segment is B according to the radius of the head
Figure 68420DEST_PATH_IMAGE002
Angle of arc
Figure 231548DEST_PATH_IMAGE004
And calculating to obtain the coordinates of the point B as follows:
Figure 742164DEST_PATH_IMAGE006
from which point coordinates of A, B can be obtained
Figure 990743DEST_PATH_IMAGE007
As a center of circle, in
Figure 730160DEST_PATH_IMAGE002
Is a circular arc AB of radius.
Filling half height according to length L and bottom section
Figure 13374DEST_PATH_IMAGE001
Constraining, can obtain the C point coordinate as
Figure 429312DEST_PATH_IMAGE008
. And connecting the two points to obtain a contour line BC, so as to complete the design of the upper contour line. The upper and lower surface contours are completely symmetrical about the x-axis.
Step two: length L, width W and spherical head chamfer angle according to aircraft design
Figure 273509DEST_PATH_IMAGE009
Determining left and right width contour lines by the design method shown in figure 2, wherein point A is the origin of coordinates, and the coordinates are
Figure 941250DEST_PATH_IMAGE010
. From the length L and width W constraints, one can obtain
Figure 203604DEST_PATH_IMAGE011
Point coordinates of
Figure 665810DEST_PATH_IMAGE012
。
Figure 764347DEST_PATH_IMAGE013
The point and the B point are positioned on the same plane
Figure 970200DEST_PATH_IMAGE015
Thus, can obtain
Figure 87061DEST_PATH_IMAGE016
. Known circular arc
Figure 985747DEST_PATH_IMAGE017
And line segment
Figure 73045DEST_PATH_IMAGE018
Tangent to point
Figure 817010DEST_PATH_IMAGE013
According to the head section cutting angle
Figure 194902DEST_PATH_IMAGE009
And
Figure 123543DEST_PATH_IMAGE013
point x coordinate, point A and point B can be determined
Figure 321307DEST_PATH_IMAGE013
The radius of the circle of points is
Figure 744329DEST_PATH_IMAGE019
Center of circle
Figure 711148DEST_PATH_IMAGE020
The coordinates are
Figure 76270DEST_PATH_IMAGE021
. Is calculated to obtain
Figure 495750DEST_PATH_IMAGE022
The point coordinates are:
Figure 220998DEST_PATH_IMAGE023
according to the radius of the arc, the starting point A and the end point of the arc
Figure 42324DEST_PATH_IMAGE013
Center of circle
Figure 843927DEST_PATH_IMAGE020
Determining a circular arc
Figure 750703DEST_PATH_IMAGE024
Contour lines. Connection point
Figure 515527DEST_PATH_IMAGE013
And point
Figure 456939DEST_PATH_IMAGE025
To obtain a line segment
Figure 163864DEST_PATH_IMAGE026
，
Figure 557936DEST_PATH_IMAGE013
The point being a circular arc
Figure 516665DEST_PATH_IMAGE027
And line segment
Figure 158255DEST_PATH_IMAGE028
The tangent point of (c). Thus, the design of the left contour line is completed. The left and right width contours are completely symmetrical about the x-axis.
Step three: design the bottom section (
Figure 177026DEST_PATH_IMAGE042
) Curves, as shown in figure 3: the bottom section curves are symmetrical about the y-axis and the z-axis respectively, soOnly one quarter of the bottom section curve (profile) needs to be designed
Figure 183029DEST_PATH_IMAGE047
). From the first step
Figure 679869DEST_PATH_IMAGE048
Point coordinates of
Figure 205659DEST_PATH_IMAGE029
From the second step
Figure 129753DEST_PATH_IMAGE025
Point coordinates of
Figure 623051DEST_PATH_IMAGE030
. Meanwhile, as can be seen from FIG. 3, M is the center point of the bottom section and its coordinate point
Figure 392424DEST_PATH_IMAGE049
. According to line segment CD length
Figure 802415DEST_PATH_IMAGE031
And bottom section half height
Figure 631830DEST_PATH_IMAGE001
Two constraints, the available D point coordinates are
Figure 612425DEST_PATH_IMAGE032
. Two points are connected C, D to obtain the segment CD. Circular arc
Figure 185488DEST_PATH_IMAGE033
Is a point
Figure 685871DEST_PATH_IMAGE034
As the center of a circle, the radius is R, and the angle of the arc
Figure 748505DEST_PATH_IMAGE035
A determined arc of a circle. Line segment DE and arc
Figure 683574DEST_PATH_IMAGE036
Tangent to point E, half height of bottom section
Figure 184962DEST_PATH_IMAGE001
Width W and circle
Figure 274272DEST_PATH_IMAGE035
With the radius R constraint, the E point coordinates can be determined as:
Figure 711070DEST_PATH_IMAGE037
connecting D, E two points, a line segment DE is obtained. At this point, the bottom section curve is complete.
Step four: design section (
Figure 135098DEST_PATH_IMAGE038
) Curves, as shown in fig. 4:
Figure 581123DEST_PATH_IMAGE038
the section curve is a quarter ellipse, namely a circular arc
Figure 23474DEST_PATH_IMAGE039
. B point and B point can be obtained from the first step and the second step respectively,
Figure 755807DEST_PATH_IMAGE040
Point coordinates are obtained, and the minor semi-axis and the major semi-axis of the ellipse are respectively determined by the point coordinates
Figure 808076DEST_PATH_IMAGE038
Cross-sectional curve of (a).
Step five: and the section curved surface from the point B to the point C adopts a multi-section curved surface connection mode. From the first step and the second step, the line segment BC and
Figure 402000DEST_PATH_IMAGE041
can be obtained by the third step and the fourth step
Figure 856115DEST_PATH_IMAGE042
、
Figure 759349DEST_PATH_IMAGE043
Cross-sectional curve of (a). Selecting
Figure 298915DEST_PATH_IMAGE042
、
Figure 197994DEST_PATH_IMAGE043
Upper section curve, with line segments BC and
Figure 506616DEST_PATH_IMAGE041
and (3) adopting a multi-section curved surface connection mode for guiding the line to complete the design of the section curved surface.
Step six: and the section curved surface before the point B adopts a bridging curved surface connection mode. From step two, the arc can be obtained
Figure 580751DEST_PATH_IMAGE044
From the fourth step, the arc can be obtained
Figure 607613DEST_PATH_IMAGE045
. Selecting arcs using bridged surface definitions
Figure 933552DEST_PATH_IMAGE045
Selecting a circular arc as a first curve, taking the curved surface obtained in the step five as a first supporting surface
Figure 972046DEST_PATH_IMAGE044
And the design of the head curved surface is finished for the second curve.
Step seven: and (4) respectively enabling the curved surfaces obtained in the fifth step and the sixth step to be symmetrical about the y axis and the z axis. All curve designs at the x section are completed, and the appearance of the aircraft is generated.
The invention has the following advantages and positive effects: firstly, a typical high-sweepback delta wing lifting body is selected as a reference layout configuration of the aircraft, and typical layout characteristics of the current mainstream lifting body type hypersonic aircraft can be embodied; meanwhile, the overall configuration of the aircraft is characterized by a symmetrical configuration formed by splicing six flat plates, and the six flat plate regions can facilitate the mounting of the composite material in a patch in a wind tunnel experiment and a flight experiment and the mounting requirements of corresponding sensors; meanwhile, the aircraft is designed in a vertically and horizontally symmetrical mode, the upper flat plate and the lower flat plate can perform contrastive analysis on test results under a zero-degree attack angle state, the left flat plate and the right flat plate can also perform contrastive analysis on the test results and correction of sensor errors, and the bilaterally symmetrical design also can ensure contrastive analysis on the test results and correction of the sensor errors under a non-zero-degree attack angle state; finally, the aircraft is designed to be in smooth transition from the head ellipse to the hexahedral section at the bottom, so that the aircraft keeps the similar convex curved surface characteristic, and the aircraft has a large filling space and can facilitate the installation of instruments in the flight test process. Therefore, the scheme of the invention can provide a new design method and the appearance of the aircraft for the standard model suitable for the performance prediction and assessment of the composite material.
In other embodiments of the invention, a given aircraft design length
Figure 92449DEST_PATH_IMAGE050
Width of
Figure 731241DEST_PATH_IMAGE051
Bottom section half height
Figure 595291DEST_PATH_IMAGE052
Radius of head
Figure 986827DEST_PATH_IMAGE053
Spherical corner cut of head
Figure 543711DEST_PATH_IMAGE054
A constraint condition. Determining the upper surface contour line of the aircraft according to the constraint condition, wherein the upper surface contour line has a head radius of
Figure 404219DEST_PATH_IMAGE053
Circular arcAdding a line segment, wherein the corresponding angle of the upper arc segment is
Figure 71961DEST_PATH_IMAGE055
At a tangent angle to the line segment
Figure 819468DEST_PATH_IMAGE056
Tangent with point A coordinate of
Figure 547253DEST_PATH_IMAGE057
，
Figure 895057DEST_PATH_IMAGE058
The point is the center of the head radius
Figure 366490DEST_PATH_IMAGE059
The point B is the end point of the upper arc segment,
Figure 469969DEST_PATH_IMAGE060
is a line segment, the tangent point of the circular arc and the line segment is a B point coordinate, and the coordinate is
Figure 634234DEST_PATH_IMAGE061
The slope of the tangent at point B is
Figure 203755DEST_PATH_IMAGE062
The coordinate of the point C can be obtained as
Figure 213300DEST_PATH_IMAGE063
Whereby
Figure 200978DEST_PATH_IMAGE064
The radius for the segment is
Figure 270566DEST_PATH_IMAGE065
The segments BC are connected by line segments. The resulting curves are shown in FIG. 1, and each can be obtained
Figure 468329DEST_PATH_IMAGE066
Corresponding width constraint
Figure 140619DEST_PATH_IMAGE067
。
Calculated by the same principle to obtain
Figure 107438DEST_PATH_IMAGE068
，
Figure 456248DEST_PATH_IMAGE069
The coordinates of the position of the object to be imaged,
Figure 141307DEST_PATH_IMAGE070
the radius for the segment is
Figure 617288DEST_PATH_IMAGE071
Are connected by the circular arcs of the two connecting rods,
Figure 438614DEST_PATH_IMAGE072
the segments are connected by line segments, as shown in FIG. 2, each of which can be obtained
Figure 990949DEST_PATH_IMAGE066
Corresponding width constraint
Figure 897725DEST_PATH_IMAGE073
。
It is known that
Figure 911817DEST_PATH_IMAGE074
，
Figure 853229DEST_PATH_IMAGE075
According to the third step, the coordinate of the point C is obtained by calculation
Figure 546771DEST_PATH_IMAGE076
Coordinates of point D of
Figure 940844DEST_PATH_IMAGE077
The coordinate of point E is
Figure 899572DEST_PATH_IMAGE078
，
Figure 554545DEST_PATH_IMAGE079
Point coordinates of
Figure 573316DEST_PATH_IMAGE080
Knowing the point coordinates and the radius of the arc, the line segments and the arc are connected in sequence to obtain the section curve shown in the attached figure 3.
It is known that
Figure 330051DEST_PATH_IMAGE081
、
Figure 561312DEST_PATH_IMAGE082
And (4) connecting the two points by using a circular arc through point coordinates to obtain the section curve shown in the attached figure 4.
Complete the process
Figure 336370DEST_PATH_IMAGE083
、
Figure 260464DEST_PATH_IMAGE084
And after the section is designed, generating a section curved surface behind the point B according to the step five, generating a curved surface design before the point B according to the step six, and generating the final appearance of the aircraft according to the step seven.
Other embodiments than the above examples may be devised by those skilled in the art based on the foregoing disclosure, or by adapting and using knowledge or techniques of the relevant art, and features of various embodiments may be interchanged or substituted and such modifications and variations that may be made by those skilled in the art without departing from the spirit and scope of the present invention are intended to be within the scope of the following claims.
The functionality of the present invention, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium, and all or part of the steps of the method according to the embodiments of the present invention are executed in a computer device (which may be a personal computer, a server, or a network device) and corresponding software. And the aforementioned storage medium includes: various media capable of storing program codes, such as a usb disk, a removable hard disk, or an optical disk, exist in a read-only Memory (RAM), a Random Access Memory (RAM), and the like, for performing a test or actual data in a program implementation.

Claims (2)

1. A design method of a lifting body marking die for predicting the performance of a composite material is characterized by comprising the following steps:
firstly, determining upper and lower surface contour lines of an aircraft according to given constraint conditions, and designing an upper contour line, wherein the upper and lower surface contour lines are symmetrical about an x axis;
in step one, the method comprises the following steps:
given the length L of the aircraft design, the bottom section half height
Figure 159209DEST_PATH_IMAGE001
Radius of head
Figure 761092DEST_PATH_IMAGE002
Spherical corner cut of head
Figure 611236DEST_PATH_IMAGE003
The constraint of (2); determining the contour lines of the upper and lower surfaces of the aircraft according to the constraint conditions, wherein the radius of the head part of the contour line of the upper surface is
Figure 982175DEST_PATH_IMAGE002
Is formed by adding a line segment BC, and the corresponding angle of the arc segment is
Figure 259572DEST_PATH_IMAGE004
At a tangent angle to the line segment
Figure 83172DEST_PATH_IMAGE003
Tangent, point A is the origin of coordinates, point B is the end point of the arc segment,
Figure 471428DEST_PATH_IMAGE005
is a line segment, the tangent point of the circular arc and the line segment is B according to the radius of the head
Figure 696873DEST_PATH_IMAGE002
Angle of arc
Figure 879593DEST_PATH_IMAGE004
And calculating to obtain the coordinates of the point B as follows:
Figure 724576DEST_PATH_IMAGE006
thus obtained from point A, B coordinates
Figure 650944DEST_PATH_IMAGE007
As a center of circle, in
Figure 730895DEST_PATH_IMAGE002
Is a circular arc AB of radius;
according to both the length L and the half height of the bottom section
Figure 350096DEST_PATH_IMAGE001
Constraining to obtain the coordinate of the point C as
Figure 413867DEST_PATH_IMAGE008
(ii) a Connecting the two points to obtain a contour line BC, so as to complete the design of an upper contour line, wherein the upper surface contour line and the lower surface contour line are completely symmetrical about the x axis;
determining left and right width contour lines according to the designed length and width of the aircraft and the spherical surface chamfer angle of the head, designing a left contour line, wherein the left and right contour lines are completely symmetrical about the x axis;
in the second step, the method comprises the following steps:
length L, width W and spherical head chamfer angle according to aircraft design
Figure 878346DEST_PATH_IMAGE009
Determining left and right width contour lines, wherein the point A is the origin of coordinates which are
Figure 78383DEST_PATH_IMAGE010
(ii) a Constrained according to the length L and the width W to obtain
Figure 134064DEST_PATH_IMAGE011
Point coordinates of
Figure 153972DEST_PATH_IMAGE012
；
Figure 687722DEST_PATH_IMAGE013
Dot sum
Figure 742266DEST_PATH_IMAGE014
The points are located on the same plane
Figure 703268DEST_PATH_IMAGE015
Thus, can obtain
Figure 476052DEST_PATH_IMAGE016
(ii) a Known circular arc
Figure 547914DEST_PATH_IMAGE017
And line segment
Figure 471612DEST_PATH_IMAGE018
Tangent to point
Figure 603516DEST_PATH_IMAGE013
According to the head section cutting angle
Figure 863596DEST_PATH_IMAGE009
And
Figure 739148DEST_PATH_IMAGE013
point x coordinate, determining the sum of points A and B
Figure 768284DEST_PATH_IMAGE013
The radius of the circle of points is
Figure 805510DEST_PATH_IMAGE019
Center of circle
Figure 818466DEST_PATH_IMAGE020
The coordinates are
Figure 232130DEST_PATH_IMAGE021
(ii) a Is calculated to obtain
Figure 115772DEST_PATH_IMAGE022
The point coordinates are:
Figure 589479DEST_PATH_IMAGE023
according to the radius of the arc, the starting point A and the end point of the arc
Figure 558572DEST_PATH_IMAGE013
Center of circle
Figure 775926DEST_PATH_IMAGE020
Determining a circular arc
Figure 514075DEST_PATH_IMAGE024
Contour lines; connection point
Figure 158683DEST_PATH_IMAGE013
And point
Figure 618002DEST_PATH_IMAGE025
To obtain a line segment
Figure 639048DEST_PATH_IMAGE026
，
Figure 497282DEST_PATH_IMAGE013
The point being a circular arc
Figure 312791DEST_PATH_IMAGE027
And line segment
Figure 990897DEST_PATH_IMAGE028
The tangent point of (A); so far, the design of the left contour line is completed, and the left contour line and the right contour line are completely symmetrical about the x axis;
step three, after the left and right contour lines are designed, designing a bottom section curve;
in step three, the method comprises the following steps:
designing a bottom section curve, wherein the bottom section curve is respectively symmetrical about a y axis and a z axis, so that only one quarter of the bottom section curve is required to be designed; from step one, the coordinates of point C are obtained
Figure 815634DEST_PATH_IMAGE029
From the second step
Figure 793954DEST_PATH_IMAGE025
Point coordinates of
Figure 780365DEST_PATH_IMAGE030
(ii) a According to line segment CD length
Figure 211346DEST_PATH_IMAGE031
And bottom section half height
Figure 574194DEST_PATH_IMAGE001
Two constraints, get the coordinates of the D point as
Figure 141442DEST_PATH_IMAGE032
(ii) a Connecting C, D to obtain segment CD; circular arc
Figure 298754DEST_PATH_IMAGE033
Is a point
Figure 951452DEST_PATH_IMAGE034
As the center of a circle, the radius is R, and the angle of the arc
Figure 852412DEST_PATH_IMAGE035
Determining a circular arc; line segment DE and arc
Figure 808254DEST_PATH_IMAGE036
Tangent to point E, half height of bottom section
Figure 136467DEST_PATH_IMAGE001
Width W and circle
Figure 276462DEST_PATH_IMAGE035
And (4) constraining the radius R, and determining the coordinates of the point E as follows:
Figure 715533DEST_PATH_IMAGE037
connecting D, E two points to obtain a line segment DE; so far, the bottom section curve is finished;
step four, after designing the bottom section curve, designing the section curve;
in step four, the method comprises the following steps:
the cross-sectional curve is designed,
Figure 257373DEST_PATH_IMAGE038
the section curve is a quarter ellipse, namely a circular arc
Figure 22067DEST_PATH_IMAGE039
(ii) a Respectively obtaining a point B from the first step and the second step,
Figure 649357DEST_PATH_IMAGE040
Point coordinates from which the minor and major semi-axes of the ellipse are determined, respectively
Figure 892120DEST_PATH_IMAGE038
Cross-sectional curve of (a);
designing a section curved surface after designing the section curve;
in step five, the method comprises the following steps:
the section curved surface from the point B to the point C adopts a multi-section curved surface connection mode; obtaining a line segment BC and a line segment BC from the step one and the step two
Figure 554045DEST_PATH_IMAGE041
Obtained by the third step and the fourth step
Figure 489640DEST_PATH_IMAGE042
、
Figure 338647DEST_PATH_IMAGE043
Cross-sectional curve of (a); selecting
Figure 385101DEST_PATH_IMAGE042
、
Figure 167112DEST_PATH_IMAGE043
Upper section curve, with line segments BC and
Figure 8029DEST_PATH_IMAGE041
the design of the section curved surface is finished by adopting a multi-section curved surface connection mode as a guide line;
step six, designing a head curved surface;
in the sixth step, the method comprises the following steps:
the section curved surface before the point B adopts a bridging curved surface connection mode; from step two, the arc can be obtained
Figure 347262DEST_PATH_IMAGE044
From the fourth step, the arc can be obtained
Figure 197407DEST_PATH_IMAGE045
(ii) a Selecting arcs using bridged surface definitions
Figure 568345DEST_PATH_IMAGE045
Selecting a circular arc as a first curve, taking the curved surface obtained in the step five as a first supporting surface
Figure 580163DEST_PATH_IMAGE044
The head curved surface design is finished for the second curve;
and seventhly, the curved surfaces obtained in the fifth step and the sixth step are respectively symmetrical about the y axis and the z axis, so that the curve design at the x section is completed, and the appearance of the aircraft is generated.
2. An aircraft based on the method for designing the lifting body standard model for predicting the performance of the composite material, which is characterized in that the appearance of the aircraft is generated by adopting the processing of the steps one to seven; and the overall configuration characteristic of the generated aircraft shape is a symmetrical configuration formed by splicing six flat plates, the aircraft shape is symmetrical up and down and left and right, and the aircraft shape is smoothly transited from a head ellipse to a bottom hexahedral section.
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