CN113704876B - 3D combined screening method for airfoil load - Google Patents
3D combined screening method for airfoil load Download PDFInfo
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- CN113704876B CN113704876B CN202110895751.4A CN202110895751A CN113704876B CN 113704876 B CN113704876 B CN 113704876B CN 202110895751 A CN202110895751 A CN 202110895751A CN 113704876 B CN113704876 B CN 113704876B
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- G—PHYSICS
- 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
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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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- 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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The application belongs to the field of airplane load analysis and strength design, and particularly relates to a 3D combined screening method for airfoil loads. Comprising the following steps: step one, determining a local coordinate system of an aircraft structure, wherein the aircraft structure comprises an airfoil; step two, load data of the aircraft structure are obtained, and shearing force, bending moment and torque of the aircraft structure are calculated according to the load data; thirdly, calculating a load pressing center position coordinate corresponding to the shearing force under a local coordinate system according to the shearing force, the bending moment and the torque of the aircraft structure; drawing a shear-press core 3D envelope map according to the shear force, the spreading press core and the chord direction press core coupling, and/or drawing a load-press core 3D envelope map according to the load, the spreading press core and the chord direction press core coupling; and fifthly, screening envelope critical points of the 3D envelope map, screening out all boundary extreme points, and ensuring that the appearance surface of all boundary extreme point connection structures covers all points in the 3D envelope map.
Description
Technical Field
The application belongs to the field of airplane load analysis and strength design, and particularly relates to a 3D combined screening method for airfoil loads.
Background
In the calculation of the aerodynamic load of the aircraft, the load conditions obtained by carrying out load calculation aiming at various combinations of parameters such as different weights, gravity centers, inertial weights, speeds, heights, flight attitudes and the like can reach thousands, and the critical load conditions of the aircraft strength design are very necessary and important work to be screened out from the huge load data.
The aeroplane each airfoil is the main lifting surface of the aeroplane, the critical design point of aerodynamic load is the main design load condition of the airfoil structural strength, and the common methods for screening the aerodynamic load condition of the aeroplane include a single-value envelope method and a combined envelope method. The traditional combined envelope method can respectively combine shearing force, bending moment and torque of the airfoil into bending shear, bending torsion and shearing torsion, and the critical load condition on the envelope boundary is selected from the combined envelope after drawing the combined envelope as the main design condition. The method can only carry out 2 factor combination screening in the shear force, bending moment and torque 3 load values, 3 combination wrapping lines are required to be drawn for each section in the screening process for analysis, the analysis workload is large, and the comprehensive influence of the shear force, the bending moment and the torque cannot be simultaneously considered in a coupling mode.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The object of the present application is to provide an airfoil load 3D combination screening method to solve at least one problem existing in the prior art.
The technical scheme of the application is as follows:
an airfoil load 3D combination screening method comprising:
determining a local coordinate system of an aircraft structure, wherein the aircraft structure comprises an airfoil;
step two, load data of the aircraft structure are obtained, and shearing force, bending moment and torque of the aircraft structure are calculated according to the load data;
thirdly, calculating a load pressing center position coordinate corresponding to the shearing force under a local coordinate system according to the shearing force, the bending moment and the torque of the aircraft structure:
spanwise centre of pressure = bending moment/shear
Chordwise core = torque/shear;
drawing a shear-press core 3D envelope map according to the shear force, the spanwise press core and the chordwise press core coupling, and/or
Drawing a load-press core 3D envelope map according to the load, the spanwise press core and the chordwise press core coupling;
and fifthly, screening envelope critical points of the 3D envelope map, screening out all boundary extreme points, and ensuring that the appearance surface of all boundary extreme point connection structures covers all points in the 3D envelope map.
In at least one embodiment of the present application, in step one, the airfoil is a tail.
In at least one embodiment of the present application, the local origin of coordinates of the tail wing is selected to be located at the front edge fixed point of the root of the airfoil, the direction of the X axis parallel to the edge rib of the root of the airfoil is positive backwards, the direction of the Y axis perpendicular to the chord plane of the airfoil is positive upwards, and the Z axis is along the span-wise direction of the airfoil, which is determined by the right-hand rule.
In at least one embodiment of the present application, in step one, the aircraft structure further comprises an airfoil typical section.
In at least one embodiment of the present application, in the fourth step, the shear force-press core 3D packing diagram uses the spanwise press core and the chordwise press core as two scale coordinate values of a basic plane, and uses the shear force as a third scale coordinate value.
In at least one embodiment of the present application, in step two, the load data of the aircraft structure includes aerodynamic load data of the aircraft structure and total load data of the aircraft structure.
In at least one embodiment of the present application, in step four, the drawing the load-core 3D envelope graph according to the load, the spanwise core, and the chordwise core coupling includes:
and drawing a pneumatic load-press core 3D envelope graph according to the pneumatic load, the spanwise press core and the chordwise press core coupling, wherein the pneumatic load-press core 3D envelope graph takes the spanwise press core and the chordwise press core as two scale coordinate values of a basic surface and takes the pneumatic load as a third scale coordinate value.
In at least one embodiment of the present application, in step four, the drawing the load-core 3D envelope graph according to the load, the spanwise core, and the chordwise core coupling includes:
and drawing a total load-press core 3D envelope graph according to the total load, the spanwise press core and the chordwise press core coupling, wherein the total load-press core 3D envelope graph takes the spanwise press core and the chordwise press core as two scale coordinate values of a basic surface and takes the total load as a third scale coordinate value.
The invention has at least the following beneficial technical effects:
according to the airfoil load 3D combined screening method, the original screening work of 3 combined envelopes is reduced to 1 combined envelope screening, the load characteristics of the airfoil are displayed more intuitively, the obtained airfoil load screening result is more accurate, and the analysis screening efficiency is remarkably improved.
Drawings
FIG. 1 is a flowchart of an airfoil load 3D combination screening method according to one embodiment of the present application;
fig. 2 is a load-centre-of-pressure 3D envelope of an empennage according to an embodiment of the application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application. Embodiments of the present application are described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of protection of the present application.
The present application is described in further detail below with reference to fig. 1-2.
The application provides an airfoil load 3D combined screening method, which comprises the following steps:
s100, determining a local coordinate system of an aircraft structure, wherein the aircraft structure comprises an airfoil;
s200, acquiring load data of the aircraft structure, and calculating shearing force, bending moment and torque of the aircraft structure according to the load data;
s300, calculating a load pressing center position coordinate corresponding to the shearing force under a local coordinate system according to the shearing force, the bending moment and the torque of the aircraft structure:
spanwise centre of pressure = bending moment/shear
Chordwise core = torque/shear;
s400, drawing a shear-press core 3D envelope map according to the shear force, the spanwise press core and the chordwise press core coupling, and/or
Drawing a load-press core 3D envelope map according to the load, the spanwise press core and the chordwise press core coupling;
s500, screening envelope critical points of the 3D envelope map, screening out all boundary extreme points, and ensuring that the appearance surface of all boundary extreme point connection structures covers all points in the 3D envelope map.
The airfoil load 3D combined screening method is suitable for pneumatic load screening of the aircraft airfoil and screening of total airfoil load, and can also be used for load screening of typical airfoil sections.
Firstly, determining the position of an airfoil or a typical tangent plane to be analyzed and a local coordinate system, and carrying out statistical calculation on data of all load conditions to obtain shearing force, bending moment and torque of the airfoil or the typical tangent plane of the airfoil, thereby calculating a load pressure center position coordinate value corresponding to the shearing force under the local coordinate system.
Pressing core position:
spanwise centre of pressure = bending moment/shear
Chordwise barycenter = torque/shear force
And the 3-D envelope curve of the shear force-pressing core is drawn according to the coupling of the shear force, the spreading pressing core and the chordwise pressing core, and/or the 3-D envelope curve of the load-pressing core is drawn according to the coupling of the load, the spreading pressing core and the chordwise pressing core, so that the simultaneous coupling analysis and screening of the shear force, the bending moment and the torque of 3 load elements are realized.
In the preferred embodiment of the application, the shear force-press core 3D packing diagram takes the spanwise press core and the chordwise press core as two scale coordinate values of a basic surface, so that the load press core position is represented, the coupling effect result of bending moment and torque is represented, and the shear force is taken as a third scale coordinate value, so that the load size and direction are represented.
In a preferred embodiment of the present application, the load data of the aircraft structure comprises aerodynamic load data of the aircraft structure and total load data of the aircraft structure. Drawing a load-core 3D envelope graph according to load, spanwise core and chordwise core coupling comprises:
and drawing a pneumatic load-pressure core 3D packing diagram according to pneumatic load, the spanwise pressure core and the chordwise pressure core coupling, wherein the pneumatic load-pressure core 3D packing diagram takes the spanwise pressure core and the chordwise pressure core as two scale coordinate values of a basic surface and takes the pneumatic load as a third scale coordinate value.
And drawing a total load-pressure core 3D packing diagram according to the total load, the spanwise pressure core and the chordwise pressure core coupling, wherein the total load-pressure core 3D packing diagram takes the spanwise pressure core and the chordwise pressure core as two scale coordinate values of a basic surface and takes the total load as a third scale coordinate value.
According to the airfoil load 3D combined screening method, all boundary extreme points are selected by screening the envelope critical points of the 3D envelope map drawn above, so that the appearance surface of the extreme point connection structure can cover all points in the envelope map, and the screened critical extreme point corresponds to the load condition of the airfoil.
In a preferred embodiment of the present application, taking a certain aircraft tail wing total load screening as an example, selecting that the local origin of coordinates of the tail wing is located at the front edge fixed point of the airfoil root, the X axis is positive in parallel with the backward direction of the airfoil root side rib, the Y axis is positive in perpendicular to the chord plane of the airfoil, and the Z axis is along the spanwise direction of the airfoil, which is determined by the right hand rule.
Under this local coordinate system, shear, bending moment, torque, and press center coordinate values (including spanwise press center and chordwise press center) are calculated for 134 load conditions to be analyzed, see table 1.
TABLE 1
And drawing a load-pressure core 3D combined envelope diagram of the tail wing according to the method, as shown in figure 2. The chord direction press core position and the spreading direction press core position in fig. 2 embody the distribution characteristics of the load press core, can intuitively represent the bending moment and the torque condition of the total load of the airfoil, simultaneously carries out coupling screening on the total load, determines the critical point connected with the boundary extreme points in the graph as the critical load condition of the airfoil, forms a 3D envelope curve surface to cover all load conditions, and screens out the conditions 1, 2, 21, 22, 26, 29 and 130-134 as the critical load conditions.
According to the airfoil load 3D combined screening method, the problems of airfoil shearing force, bending moment and torque combined screening are solved, adverse factors of an airfoil pneumatic load combined envelope method can be improved, original 3 combined envelope screening work is reduced to 1 combined envelope screening, the load characteristics of airfoils are displayed more intuitively, the obtained airfoil load screening result is more accurate, and analysis screening efficiency is remarkably improved.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. An airfoil load 3D combination screening method, comprising:
determining a local coordinate system of an aircraft structure, wherein the aircraft structure comprises an airfoil;
step two, load data of the aircraft structure are obtained, and shearing force, bending moment and torque of the aircraft structure are calculated according to the load data;
thirdly, calculating a load pressing center position coordinate corresponding to the shearing force under a local coordinate system according to the shearing force, the bending moment and the torque of the aircraft structure:
spanwise centre of pressure = bending moment/shear
Chordwise core = torque/shear;
drawing a shear-press core 3D envelope map according to the shear force, the spanwise press core and the chordwise press core coupling, and/or
Drawing a load-press core 3D envelope map according to the load, the spanwise press core and the chordwise press core coupling;
and fifthly, screening envelope critical points of the 3D envelope map, screening out all boundary extreme points, and ensuring that the appearance surface of all boundary extreme point connection structures covers all points in the 3D envelope map.
2. The method of claim 1, wherein in step one, the airfoil is a tail.
3. The method for 3D combined screening of airfoil loads according to claim 2, wherein the local origin of coordinates of the tail wing is selected to be located at a front edge fixed point of the airfoil root, the X-axis is positive in parallel with the backward direction of the airfoil root side rib, the Y-axis is positive in perpendicular to the chord plane of the airfoil, and the Z-axis is along the spanwise direction of the airfoil, which is determined by the right-hand rule.
4. The method of claim 1, wherein in step one, the aircraft structure further comprises an airfoil representative section.
5. The method according to claim 1, wherein in the fourth step, the shear-press core 3D packing diagram uses a spanwise press core and a chordwise press core as two scale coordinate values of a basic plane and uses a shear force as a third scale coordinate value.
6. The method of claim 1, wherein in step two, the load data of the aircraft structure comprises aerodynamic load data of the aircraft structure and total load data of the aircraft structure.
7. The airfoil load 3D combination screening method of claim 6, wherein in step four, the mapping load-core 3D envelope map based on load, spanwise core, and chordwise core coupling comprises:
and drawing a pneumatic load-press core 3D envelope graph according to the pneumatic load, the spanwise press core and the chordwise press core coupling, wherein the pneumatic load-press core 3D envelope graph takes the spanwise press core and the chordwise press core as two scale coordinate values of a basic surface and takes the pneumatic load as a third scale coordinate value.
8. The airfoil load 3D combination screening method of claim 6, wherein in step four, the mapping load-core 3D envelope map based on load, spanwise core, and chordwise core coupling comprises:
and drawing a total load-press core 3D envelope graph according to the total load, the spanwise press core and the chordwise press core coupling, wherein the total load-press core 3D envelope graph takes the spanwise press core and the chordwise press core as two scale coordinate values of a basic surface and takes the total load as a third scale coordinate value.
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