CN110763424A - Method, system and device for measuring surface pressure of wing - Google Patents
Method, system and device for measuring surface pressure of wing Download PDFInfo
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L9/00—Measuring steady of quasi-steady pressure of fluid or fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a method, a system and a device for measuring the surface pressure of an airfoil, comprising the following steps: the method comprises the following steps that firstly, the wing is divided into a plurality of wing blocks through a block strategy, so that the surface pressure between each point in each wing block does not have a gradient; secondly, acquiring the position of a strain measurement point on the wing based on a finite element model and a blocking strategy; thirdly, mounting a strain measurement assembly at the position of a strain measurement point on the wing for strain measurement; and fourthly, obtaining the pressure of each wing block on the wing according to the measured strain data, and obtaining the pressure distribution value on the wing. The wing is divided into a plurality of wing blocks through a block strategy, the position of a strain measurement point on the wing is obtained by utilizing a finite element model and a calculation result thereof, the actual strain of the strain measurement point on the wing is measured to calculate the actual pressure value of the wing in the working process in a reverse-pushing mode, and the obtained wing surface pressure has high precision, convenient implementation method, high economy and high efficiency.
Description
Technical Field
The invention relates to the technical field of pressure measurement, in particular to a method, a system and a device for measuring the surface pressure of a wing.
Background
In various wing design and manufacturing processes, it is often necessary to calculate and measure the surface pressure of the wing in order to analyze and study the distribution of the surface pressure of the wing. The prior art generally mounts a pressure sensor directly on the surface of the wing or provides a pressure tap on the wing to send a pressure signal to the pressure sensor via a pipeline. The pressure sensor converts the pressure signal into a weak electric signal, and the weak electric signal is amplified and processed to restore the pressure value.
Currently, there are two methods for obtaining airfoil surface pressure:
the first method comprises the following steps: based on a Computational Fluid Dynamics (CFD) method, the method is used for calculating the pressure of the whole flow field, in order to calibrate the CFD model, the pressure of a plurality of points on the surface of the wing can be measured, and the pressure is recalculated after the corrected computational Fluid model is checked to obtain the global pressure value of the surface of the wing;
and the second method comprises the following steps: the method adopts a wind tunnel test method, and the theoretical basis of the wind tunnel test is a motion relativity principle and a flow similarity principle. According to the principle of relativity, the aerodynamic force received by the aircraft flying in the still air is the same as that of the aircraft which is still and blows air in the opposite direction at the same speed. However, the frontal area of the airplane is relatively large, such as several meters, tens of meters and several tens of meters (the boeing 747 is 60 meters) of wing span, so that the airflow with such a large frontal area is blown at a speed equivalent to the flying speed, and the power consumption of the airplane is remarkable. According to the similarity principle, the airplane can be made into a small-scale model with similar geometry, the tested air flow speed can be lower than the flying speed within a certain range as long as certain similar parameters are kept consistent, and the aerodynamic force acting on the airplane during real flying can be calculated according to the test result.
Currently, there are two methods of obtaining airfoil skin pressure that have their own disadvantages.
The first method, namely the computational fluid dynamics CFD-based method, has the main disadvantages of a discrete approximation algorithm, the problem to be solved needs to be fully understood during computation, and the programming and correct use requirements are high. The CFD method has higher calculation accuracy for the wing surface pressure of low-speed, steady and stable fluid, but the calculation accuracy for the wing surface pressure of unsteady fluid is difficult to guarantee for the turbulent flow.
The second method is a wind tunnel test method, and the method has the main defects that the wind tunnel test cost is high, the test conditions are limited by wind tunnel design parameters, and when some unsteady fluids, such as wings, rotate, the wind tunnel test is difficult to simulate, and even cannot accurately measure.
Disclosure of Invention
The invention provides a method, a system and a device for measuring the surface pressure of a wing, aiming at the problem that the surface of the wing cannot be accurately measured in the prior art.
In order to achieve the above object, the present invention provides a method for measuring a surface pressure of an airfoil, comprising:
the method comprises the following steps that firstly, the wing is divided into a plurality of wing blocks through a block strategy, so that the surface pressure between each point in each wing block does not have a gradient;
secondly, acquiring the position of a strain measurement point on the wing based on a finite element model and a blocking strategy;
thirdly, mounting a strain measurement assembly at the position of a strain measurement point on the wing for strain measurement;
and fourthly, obtaining the pressure of each wing block on the wing according to the measured strain data, and obtaining the pressure distribution value on the wing.
Further preferably, in the second step, the process of acquiring the position of the strain measurement point on the wing includes the following steps:
step 1, finite element modeling: establishing a finite element analysis model for the wing needing pressure measurement to obtain a wing model for dividing finite element units;
step 2, calculating strain values of all finite element units in the wing model under the action of each unit pressure load, wherein the number of the unit pressure loads is equal to the number of the wing blocks and corresponds to the number of the wing blocks one by one;
step 3, selecting a plurality of finite element units on the wing model as candidate units;
step 4, selecting n candidate units from the candidate units as candidate measuring points, and calculating a strain-load relation matrix corresponding to the n candidate measuring points according to strain values of the candidate measuring points under the action of each unit pressure load, wherein n represents the number of the strain measuring points;
and 5, selecting n candidate measuring points corresponding to the strain-load relation matrix with the local minimum condition number or the global minimum condition number as strain measuring points.
Further preferably, in step 3, the number of the candidate units is 1000 or less.
Further preferably, in step 4, the number of the candidate measurement points selected is 1.5 to 2 times the total number of the unit pressure loads.
Further preferably, in step 4, the calculation process of the strain-load relationship matrix is as follows:
step 401, obtaining a relational expression of the strain and the unit pressure load of n candidate measuring points:
in formula (1), the matrix [ epsilon ]]Is the strain, epsilon, corresponding to m unit pressure loads corresponding to n candidate measuring pointsm,nRefers to the candidate measuring point of the serial number nStrain at the mth unit pressure load; matrix [ C ]]n×mThe strain-load relation matrix corresponding to the n candidate measuring points is obtained; the right side of equation (1) represents the load matrix, where F1，F2，…，FmRepresents m unit pressure loads;
step 402, standardizing the load matrix on the right side of the formula (1) to obtain:
in the formula (2), [ I ] is an identity matrix having a diagonal term of 1;
step 403, constructing a strain-load relation matrix [ C ] according to the formula (2)]n×mThe pseudo-inverse matrix of (a), namely:
[C]n×m＝[εTε]-1εT
in step 5, the matrix [ ε ]Tε]-1The n candidate measurement points corresponding to the condition number local minimum or global minimum are the n candidate measurements corresponding to the strain-load relationship matrix with the condition number local minimum or global minimum.
Further preferably, in the third step, the strain measurement component is installed at the position of the strain measurement point on the wing, and the process of performing strain measurement is as follows:
placing the wing provided with the strain measurement assembly in an actual working environment, synchronously recording the strain of n strain measurement points, wherein the recording time is t seconds, sampling is performed for h times per second, and finally, within t seconds, the strain data of n strain measurement points in a t x h line are derived:
wherein the matrix [ epsilon ]t]Strain data for n strain measurement points are taken for t × h.
Further preferably, the fourth step is specifically:
and 6, obtaining the pressure of each wing block on the wing according to the measured strain data as follows:
wherein, the left matrix [ C ] of the formula (3)]n×mNamely a strain-load relation matrix corresponding to the n strain measurement points, and the right side of the formula (3) is the pressure of each wing block.
To achieve the above object, the present invention also provides a system for measuring surface pressure of an airfoil, comprising: a memory storing a wing surface pressure measurement program and a processor executing the steps of the method described above when executing the program.
To achieve the above object, the present invention provides a wing surface pressure measuring device, comprising:
the strain measurement assembly is arranged on the wing and used for measuring strain data of the position of a strain measurement point on the wing;
and the control module comprises the wing surface pressure measuring system and is electrically connected with the strain measuring component.
According to the method, the system and the device for measuring the surface pressure of the wing, the wing is divided into a plurality of wing blocks through a block strategy, the position of a strain measurement point on the wing is obtained by utilizing a finite element model and a calculation result of the finite element model, the actual strain of the strain measurement point on the wing is measured, the actual pressure value of the wing in the working process is calculated in a reverse-pushing mode, and the obtained surface pressure of the wing is high in precision, convenient to implement, high in economy and high in efficiency.
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, 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 the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic step-by-step illustration of a method of measuring airfoil surface pressure in an embodiment of the invention;
FIG. 2 is a schematic flow chart of a method for measuring airfoil surface pressure according to an embodiment of the invention;
FIG. 3 is a schematic view of a wing model according to an embodiment of the invention;
FIG. 4 is a schematic diagram of the partial strain values of all finite element elements in the wing model under a unit input load according to an embodiment of the present invention
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
A method of measuring airfoil surface pressure as shown in fig. 1, comprising:
the method comprises the following steps that firstly, the wing is divided into a plurality of wing blocks through a block strategy, so that the surface pressure between each point in each wing block does not have a gradient;
secondly, acquiring the position of a strain measurement point on the wing based on a finite element model and a blocking strategy;
thirdly, mounting a strain measurement assembly at the position of a strain measurement point on the wing for strain measurement;
and fourthly, obtaining the pressure of each wing block on the wing according to the measured strain data, and obtaining the pressure distribution value on the wing.
In the embodiment, the wing is divided into a plurality of wing blocks by a block strategy, the position of a strain measurement point on the wing is obtained by using a finite element model and a calculation result thereof, and the actual pressure value of the wing in the working process is calculated by backstepping by combining with the actual strain of the strain measurement point on the wing, so that the obtained wing surface pressure has high precision, and the implementation method is convenient, economic and efficient.
In the first step, the objective of the blocking strategy is to make the pressure distribution in each wing block be an average value, i.e. there is no gradient in the surface pressure between points in each wing block, so that some areas on the wing where the pressure gradient may be large are subdivided, for example, into 3cm × 3 cm; for some areas on the wing where the pressure gradient may be smaller, the area may be roughly divided into some areas, for example, 20cm × 20cm, in this embodiment, the wing is divided into N wing blocks by a block strategy, the N wing blocks have N pressure values, and the N pressure values are calculated to obtain the pressure distribution of the entire wing. The specific partitioning strategy can refer to "aircraft part aerodynamics", and is not described in this embodiment.
Referring to fig. 2, in a second step, the process of acquiring the position of the strain measurement point on the wing includes the following steps:
step 1, finite element modeling: establishing a finite element analysis model for the wing needing pressure measurement to obtain a wing model for dividing finite element units;
step 2, calculating strain values of all finite element units in the wing model under the action of each unit pressure load, wherein the number of the unit pressure loads is equal to the number of the wing blocks and corresponds to the number of the wing blocks one by one;
step 3, selecting a plurality of finite element units on the wing model as candidate units;
step 4, selecting n candidate units from the candidate units as candidate measuring points, and calculating a strain-load relation matrix corresponding to the n candidate measuring points according to strain values of the candidate measuring points under the action of each unit pressure load, wherein n represents the number of the strain measuring points;
and 5, selecting n candidate measuring points corresponding to the strain-load relation matrix with the local minimum condition number or the global minimum condition number as strain measuring points.
In step 1, finite element modeling is performed based on general finite element modeling software or a special finite element analysis program, such as ANSYSMechanical, hyperborks, Simcenter 3D, and the like. The finite element modeling in this embodiment is based on the design model of the wing, so the model of the wing to be pressure measured can be easily obtained by finite element modeling software or a special finite element analysis program, i.e. as shown in fig. 3.
In the step 2, in the finite element model of the wing, N pressure values of N wing blocks are used as input loads, a calculation working condition is established independently on the assumption that each input load is a unit pressure load, and each working condition outputs stress strain values of the upper surface and the lower surface of the wing. The calculation of the calculation condition to obtain the strain result corresponding to each independent external force input load is a self-contained function of the finite element modeling software, and the design of the corresponding calculation condition in the finite element modeling software based on the external force input load is well known to those skilled in the art, and the specific design process is related to specific parameters of the external force input load, so that details are not repeated in this embodiment. The calculation conditions designed for N unit pressure loads in this embodiment are shown in table 1:
TABLE 1 finite element calculation conditions
Fig. 4 is a schematic diagram showing the strain values of all finite element elements in the wing model under the action of a unit pressure load.
In step 3, the number of the candidate units is below 1000, the number of the candidate units is not too large, and too many candidate units will cause too long calculation time for finding the optimal measurement point unit, and the calculation efficiency is low.
In step 4, the number of the selected candidate measuring points is 1.5-2 times of the total number of the unit pressure loads. In order to increase the redundancy of the measurement results in this embodiment, the number of candidate measurement points is determined to be 2 times of the number of loads, that is, 2N.
In step 4, the calculation process of the strain-load relationship matrix is as follows:
step 401, obtaining a relational expression of the strain and the unit pressure load of n candidate measuring points:
because there is a linear relationship between the external force input load and the strain value of the candidate measurement point, it is mathematically similar to:
F＝Kx (4)
equation (4) is an expression of hooke's law, F is force, x is displacement, K is the elastic coefficient, which can be written as:
εC＝F (5)
in the formula (5), ∈ is strain, F is external force input load, C is a coefficient of relationship between load and strain, and if the strains and external force input loads of n candidate measurement points are all substituted in the formula (6), the following results are obtained:
in formula (1), the matrix [ epsilon ]]Is the strain, epsilon, corresponding to m unit pressure loads corresponding to n candidate measuring pointsm,nThe strain is the strain of a candidate measuring point with the serial number n under the action of the mth unit pressure load; matrix [ C ]]n×mThe strain-load relation matrix corresponding to the n candidate measuring points is obtained; the right side of equation (1) represents the load matrix, where F1，F2，…，FmDenotes m unit pressure loads, where m is N, N is 2N, F1＝F2＝…＝Fm＝1000；
Step 402, standardizing the load matrix on the right side of the formula (1) to obtain:
in the formula (2), [ I ] is an identity matrix having a diagonal term of 1;
step 403, constructing a strain-load relation matrix [ C ] according to the formula (2)]n×mThe pseudo-inverse matrix of (a), namely:
[C]n×m＝[εTε]-1εT
because the strain values of each finite element unit on the wing model under the action of each unit input load are different, the strain-load relation matrix [ C ] obtained by final calculation is obtained according to the difference of the n candidate measuring points selected in the step 4]n×mAlso different. In step 5 of this embodiment, n candidate measurement points corresponding to the strain-load relationship matrix with the locally minimum condition number or the globally minimum condition number are selected as the strain measurement points, that is, the n candidate measurement points are: matrix [ epsilon ]Tε]-1The n candidate measurement points corresponding to the condition number local minimum or global minimum are the n candidate measurements corresponding to the strain-load relationship matrix with the condition number local minimum or global minimum.
For example, if there are 10 candidate units, they are each [ a ]1,a2,a3,a4,a5,a6,a7,a8,a9,a10]The selected n is 4 candidate measuring points in common [ a1,a2,a3,a4]、[a1,a2,a3,a5]、[a1,a2,a3,a6]、[a1,a2,a3,a7]、
[a1,a2,a3,a8]、[a1,a2,a3,a9]In the case of 210, the specific implementation of step 5 calculates the strain-load relationship matrix [ C ] in the case of 210]n×mThen from 210 strain-load relationship matrices [ C]n×mPicks out matrix [ epsilon ]Tε]-1The strain measurement points are 4 candidate measurement points corresponding to the condition number of local minimum or global minimum.
In the third step, a strain measurement component is installed on the inner wall of the wing at the position of the strain measurement point, and the process of strain measurement is as follows:
placing the wing provided with the strain measurement assembly in an actual working environment, synchronously recording the strain of n strain measurement points, wherein the recording time is t seconds, sampling is performed for h times per second, and finally, within t seconds, the strain data of n strain measurement points in a t x h line are derived:
namely:
wherein the matrix [ epsilon ]t]Strain data for 2N strain measurement points are taken for t × h.
Therefore, the process in the fourth step is specifically as follows:
and 6, obtaining the pressure of each wing block on the wing according to the measured strain data as follows:
wherein, the left matrix [ C ] of the formula (3)]n×mNamely a strain-load relation matrix corresponding to the n strain measurement points, and the right side of the formula (3) is the pressure of each wing block.
After the pressure distribution of each wing block is obtained, workers can obtain other parameters for research through pressure distribution calculation, for example, the method can be effectively applied to calculating the lift force and the drag force of the whole wing:
the lift and drag of the wing are:
in the formula, FLifting forceFor total wing lift, FResistance forceIn order to provide the overall resistance of the wing,
is the pressure in the region of the wing,
is a unit vector of the lifting force direction,
is a unit vector of the direction of resistance, SiIs the area of the wing block.
To achieve the above object, the present embodiment further provides a system for measuring surface pressure of an airfoil, including: a memory storing a wing surface pressure measurement program and a processor executing the steps of the method described above when executing the program.
To achieve the above object, the present embodiment provides an airfoil surface pressure measuring apparatus, including:
the strain measurement assembly is arranged on the wing and used for measuring strain data of the position of a strain measurement point on the wing;
and the control module comprises the wing surface pressure measuring system and is electrically connected with the strain measuring component.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (9)
1. A method of measuring airfoil surface pressure, comprising:
the method comprises the following steps that firstly, the wing is divided into a plurality of wing blocks through a block strategy, so that the surface pressure between each point in each wing block does not have a gradient;
secondly, acquiring the position of a strain measurement point on the wing based on a finite element model and a blocking strategy;
thirdly, mounting a strain measurement assembly at the position of a strain measurement point on the wing for strain measurement;
and fourthly, obtaining the pressure of each wing block on the wing according to the measured strain data, and obtaining the pressure distribution value on the wing.
2. The method of claim 1, wherein the step of obtaining the location of the strain measurement point on the airfoil comprises the steps of:
step 1, finite element modeling: establishing a finite element analysis model for the wing needing pressure measurement to obtain a wing model for dividing finite element units;
step 2, calculating strain values of all finite element units in the wing model under the action of each unit pressure load, wherein the number of the unit pressure loads is equal to the number of the wing blocks and corresponds to the number of the wing blocks one by one;
step 3, selecting a plurality of finite element units on the wing model as candidate units;
step 4, selecting n candidate units from the candidate units as candidate measuring points, and calculating a strain-load relation matrix corresponding to the n candidate measuring points according to strain values of the candidate measuring points under the action of each unit pressure load, wherein n represents the number of the strain measuring points;
and 5, selecting n candidate measuring points corresponding to the strain-load relation matrix with the local minimum condition number or the global minimum condition number as strain measuring points.
3. The method of claim 2, wherein in step 3, the number of candidate units is less than 1000.
4. The method of claim 2, wherein in step 4, the number of candidate measurement points selected is 1.5 to 2 times the total unit pressure load.
5. The method for measuring the wing surface pressure according to any one of claims 2 to 4, wherein in step 4, the calculation process of the strain-load relation matrix is as follows:
step 401, obtaining a relational expression of the strain and the unit pressure load of n candidate measuring points:
in formula (1), the matrix [ epsilon ]]Is the strain, epsilon, corresponding to m unit pressure loads corresponding to n candidate measuring pointsm,nRefers to a candidate measuring point with the serial number n under the action of the m unit pressure loadStrain; matrix [ C ]]n×mThe strain-load relation matrix corresponding to the n candidate measuring points is obtained; the right side of equation (1) represents the load matrix, where F1，F2，…，FmRepresents m unit pressure loads;
step 402, standardizing the load matrix on the right side of the formula (1) to obtain:
in the formula (2), [ I ] is an identity matrix having a diagonal term of 1;
step 403, constructing a strain-load relation matrix [ C ] according to the formula (2)]n×mThe pseudo-inverse matrix of (a), namely:
[C]n×m＝[εTε]-1εT
in step 5, the matrix [ ε ]Tε]-1The n candidate measurement points corresponding to the condition number local minimum or global minimum are the n candidate measurements corresponding to the strain-load relationship matrix with the condition number local minimum or global minimum.
6. The method for measuring wing surface pressure according to any one of claims 2 to 4, wherein in the third step, a strain measuring assembly is installed at the position of a strain measuring point on the wing, and the process of strain measurement is as follows:
placing the wing provided with the strain measurement assembly in an actual working environment, synchronously recording the strain of n strain measurement points, wherein the recording time is t seconds, sampling is performed for h times per second, and finally, within t seconds, the strain data of n strain measurement points in a t x h line are derived:
wherein the matrix [ epsilon ]t]Strain data for n strain measurement points are taken for t × h.
7. The method for measuring the surface pressure of the wing according to any of claims 2 to 4, characterized in that the fourth step is specifically:
and 6, obtaining the pressure of each wing block on the wing according to the measured strain data as follows:
wherein, the left matrix [ C ] of the formula (3)]n×mNamely a strain-load relation matrix corresponding to the n strain measurement points, and the right side of the formula (3) is the pressure of each wing block.
8. An airfoil surface pressure measurement system, comprising: a memory storing a wing surface pressure measurement program and a processor executing the program to perform the steps of any of the methods of claims 2-7.
9. An airfoil surface pressure measurement device, comprising:
the strain measurement assembly is arranged on the wing and used for measuring strain data of the position of a strain measurement point on the wing;
and the control module comprises the wing surface pressure measuring system and is electrically connected with the strain measuring component.
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