CN113094953A - Finite element analysis method for hinge moment balance with wing deformation - Google Patents
Finite element analysis method for hinge moment balance with wing deformation Download PDFInfo
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Abstract
The invention provides a finite element analysis method for a hinge moment balance with wing deformation, and belongs to the technical field of wind tunnel pneumatic tests. Aiming at the measurement of the hinge moment of the control surface of the high-aspect-ratio aircraft, the method adopts a finite element analysis method, in the design stage of the hinge moment balance, a three-dimensional model of the wing and the hinge moment balance is constructed through three-dimensional modeling software, the stress conditions of the hinge moment balance and the wing in a wind tunnel test are simulated and analyzed through the finite element analysis software, the simulation result is contrasted and analyzed, the structural design of the hinge moment balance and a cover plate is optimized, the influence of the wing deformation and the model cover plate on the measurement result of the hinge moment balance is reduced, and a reasonable hinge moment balance calibration and test scheme is formulated. By adopting the invention, the measurement uncertainty of the hinge moment balance can be improved, the development cycle of the hinge moment balance is shortened, the working efficiency is improved, and the hinge moment balance has good use value and social benefit.
Description
Technical Field
The application relates to the technical field of wind tunnel pneumatic tests, in particular to a finite element analysis method of a hinge moment balance with wing deformation. More specifically, the invention provides a design method of a hinge moment balance with wing deformation, which is beneficial to the structural optimization of the hinge moment balance and a cover plate, makes a reasonable calibration and test scheme, improves the measurement accuracy of the hinge moment balance, shortens the development cycle of the hinge moment balance, improves the working efficiency and has a better application prospect.
Background
The hinge moment balance is mainly used for measuring the hinge moment acting on an aircraft control surface (aileron and rudder) or a full-motion airfoil surface (horizontal tail and canard) model. With the continuous development of aircraft technology, aircrafts with large aspect ratios are more and more common, and the requirement on the uncertainty of hinge moment measurement is higher and higher.
The aircraft with the large aspect ratio is characterized in that: the model has long wing, thin wing profile and poor wing rigidity. The wing model connected with the control surface is thin, the installation space of the hinge moment balance in the wing is greatly limited, so that the width and the thickness of the hinge moment balance are large, the hinge moment is mostly sheet balance which is three-component or four-component, but the measurement uncertainty of the hinge moment component is focused, and the rest components are used as references. The rigidity of the balance and the model connected with the balance is weak, so that the model is seriously stressed and deformed in the wind tunnel test, and the accurate measurement of the hinge moment of the control surface is influenced.
At present, in order to improve the measurement accuracy of the hinge moment, before a wind tunnel test, after balance calibration and when a loading error is large, a bridge (called an external bridge) is arranged on a wing model to correct component signals of the hinge moment balance, so that the workload is large and the efficiency is low.
To this end, a new method and/or apparatus is urgently needed to solve the above problems.
Disclosure of Invention
The invention of the present application aims to: in order to solve the existing problems, a finite element analysis method of the hinge moment balance with wing deformation is provided. Aiming at the measurement of the hinge moment of the control surface of the high-aspect-ratio aircraft, the method adopts a finite element analysis method, and in the design stage of the hinge moment balance, on one hand, the element structure of the hinge moment balance is optimized, the influence of wing deformation on the hinge moment balance is reduced, whether external bridge correction is needed to be set or not is determined, and the measurement uncertainty of the hinge moment balance is improved; on the other hand, the cover plate structure and size are optimized and the measurement uncertainty of the hinge moment balance is improved through the influence of the cover plate on the measurement accuracy of the hinge moment balance. The hinge moment balance calibration and test method can be used for guiding the optimal design of the hinge moment balance and the model cover plate, formulating a reasonable hinge moment balance calibration and test scheme, improving the measurement accuracy of the hinge moment balance, shortening the development period of the hinge moment balance, improving the working efficiency and having good use value and social benefit.
In order to achieve the purpose, the following technical scheme is adopted in the application:
a finite element analysis method of a hinge moment balance with wing deformation comprises the following steps:
(1) three-dimensional modeling software is used for building three-dimensional models of the wing, the hinge moment balance, the first cover plate and the second cover plate; the built three-dimensional model comprises wings, hinge moment balances, a first cover plate and a second cover plate, wherein the hinge moment balances are arranged on the wings and are positioned on one sides of the wings, which are close to the rudder, the first cover plate and the second cover plate are respectively arranged on two sides of the hinge moment balances, and the first cover plate and the second cover plate are respectively and fixedly connected with the wings;
(2) importing the three-dimensional model constructed in the step 1 into finite element analysis software for grid division;
(3) after the wing is fixed, loading is carried out on the hinge moment balance;
(4) fixing the connection surface of the wing and the fuselage, and loading the hinge moment balance;
(5) fixing the connecting surface of the wing and the fuselage, taking a loading point at any place of the wing, marking as a wing loading point, and applying wing load to the wing loading point;
(6) fixing the connecting surface of the wing and the fuselage, applying wing load at the wing loading point in the step (5), and simultaneously loading the hinge moment balance;
(7) a first cover plate and a second cover plate are additionally arranged on two sides of the wing, the connecting surface of the wing and the body is fixed, and the hinge moment balance is loaded;
(8) comparing the analysis results of the components of the hinge moment balance in the step (3) and the step (4) to obtain the influence delta of different positions of the fixed wing on the measurement result of the hinge moment balanceI；
(9) Comparing the analysis results of the components of the hinge moment balance in the step (4), the step (5) and the step (6) to obtain the influence delta of the wing deformation on the measurement result of the hinge moment balanceII；
(10) Comparing the analysis results of the components of the hinge moment balance in the step (6) and the step (7) to obtain the influence delta of the first cover plate and the second cover plate on the measurement result of the hinge moment balanceIII；
(11) If it isδI、δII、δIIIThe measurement uncertainty of the hinge moment balance in the model is smaller when the measurement error of the middle hinge moment component is within the wind tunnel test allowable range; on the contrary, the larger the measurement uncertainty of the hinge moment balance in the model is, one or more of the hinge moment balance, the first cover plate and the second cover plate need to be optimized, or an external bridge needs to be added to correct the measurement result.
And (3) respectively applying design loads of all components to the hinge moment balance at the balance free end of the hinge moment balance, and fitting the design loads to the center of the hinge moment balance.
And (4) respectively applying design loads of all components to the hinge moment balance at the balance free end of the hinge moment balance, and fitting the design loads to the center of the hinge moment balance.
In the step (6), the connecting surface of the wing and the fuselage is fixed, wing load is applied to the wing loading point in the step (5), meanwhile, design load of each component is applied to the hinge moment balance respectively at the free end of the hinge moment balance, and the design load is fitted to the center of the hinge moment balance.
In the steps (3) to (6), the operation is performed on the premise that the first cover plate and the second cover plate are not additionally arranged on the two sides of the wing.
And (7) additionally arranging a first cover plate and a second cover plate on two sides of the wing, fixing the connection surface of the wing and the body, respectively applying design loads of all components to the hinge moment balance at the balance free end of the hinge moment balance, and fitting the design loads to the center of the hinge moment balance.
The wing loading point is arranged on the wing, is positioned on the outer side of the hinge moment balance and is close to the wing tip direction.
In the step (11), the external electric bridge is arranged at the joint of the hinge moment balance and the wing.
In summary, the present application provides a finite element analysis method for a hinge moment balance with wing deformation. In the invention, on one hand, the structure of the hinge moment balance element is optimized by analyzing different positions of the fixed wing (step 3 and step 4), so that the influence of the hinge moment balance element on the measurement result is controlled within an allowable range; on the other hand, by fixing the connecting surface of the wing and the fuselage, under the condition of no wing deformation (step 4, step 5 and step 6), the influence of the wing deformation on the measuring result of the hinge moment balance is obtained by comparing and analyzing the measuring result of the hinge moment balance, and whether a calibration and test scheme for correcting the external bridge is required to be set is determined; thirdly, through the comparison and analysis of the measurement results of the hinge moment balance before and after the cover plate is additionally arranged (step 6 and step 7), the design of the cover plate is optimized, and the influence of the cover plate on the measurement results is reduced as much as possible. The hinge moment balance testing device is beneficial to the structural optimization of the hinge moment balance and the cover plate, reasonable calibration and test schemes are formulated, the measurement accuracy of the hinge moment balance is improved, the development period of the hinge moment balance is shortened, and the working efficiency is improved.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a front view (without a cover plate) of a finite element analysis method of a hinge moment balance with wing deformation in an embodiment;
FIG. 2 is a front view (with cover plate) of a finite element analysis method of a hinge moment balance with wing deformation in an embodiment;
FIG. 3 is a schematic structural view of section A-A in FIG. 2;
fig. 4 is a schematic view of the rudder load point in the embodiment.
Reference numerals: 1. the airplane wing loading device comprises a wing, 2, a wing loading point, 3, a hinge moment balance, 4, a balance free end, 5, a connection surface of the wing and a fuselage, 6a, a first external electric bridge, 6B, a second external electric bridge, 6c, a third external electric bridge, 7, a first cover plate, 8, a second cover plate, 9, a rudder, 10, loading points A and 11 and a loading point B.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
Example 1
This embodiment is a rudder hinge moment balance for a certain type of aircraft.
As shown in fig. 1 to 4, the present embodiment relates to a finite element analysis method for a hinge moment balance with wing deformation, which includes the following steps:
firstly, three-dimensional modeling software is used for building three-dimensional models of the wing 1, the hinge moment balance 3, the first cover plate 7 and the second cover plate 8; the built three-dimensional model comprises a wing 1, a hinge moment balance 3, a first cover plate 7 and a second cover plate 8, wherein the hinge moment balance 3 is arranged on the wing 1, the hinge moment balance 3 is positioned on one side, close to a rudder 9, of the wing 1, the first cover plate 7 and the second cover plate 8 are respectively arranged on two sides of the hinge moment balance 3, and the first cover plate 7 and the second cover plate 8 are respectively fixedly connected with the wing 1.
And step two, importing the three-dimensional model into finite element analysis software by using an interface of the finite element analysis software and the three-dimensional modeling software, and carrying out meshing.
Step three, after the wing 1 is fixed, loading the hinge moment balance 3; specifically, the design loads of all components are respectively applied to the hinge moment balance 3 at the balance free end 4 of the hinge moment balance 3, the design loads are fitted to the center of the hinge moment balance 3, and the strain output epsilon of all components of the hinge moment balance 3 is recordedASee table 1.
Step four, fixing the connection surface 5 of the wing and the fuselage, respectively applying design loads of all components to the hinge moment balance 3 at the balance free end 4 of the hinge moment balance 3, fitting the design loads to the center of the hinge moment balance 3, and recording the strain output epsilon of all components of the hinge moment balance 3BSee table 1.
Step five, fixing a connecting surface 5 of the wing and the fuselage, taking any one loading point on the wing 1 as a wing loading point 2 (the outer side of the hinge moment balance (in the direction close to the wing tip)), applying wing load to the wing loading point 2, and recording components of the hinge moment balance 3Strain output epsilonCSee table 1.
Sixthly, fixing a connecting surface 5 of the wing and the fuselage, applying wing load on a wing loading point 2, simultaneously applying design load of each component to the hinge moment balance 3 at a balance free end 4 of the hinge moment balance 3 respectively, fitting the design load to the center of the hinge moment balance 3, and recording the strain output epsilon of each component of the hinge moment balance 3DSee table 1. Wherein, the third step, the fourth step, the fifth step and the sixth step are carried out on the premise that the first cover plate 7 and the second cover plate 8 are not additionally arranged on the two sides of the wing.
Seventhly, a first cover plate 7 and a second cover plate 8 are additionally arranged on the wing 1 (at the moment, the first cover plate 7 is arranged on one side of the hinge moment balance 3, and the second cover plate 8 is arranged on the other side of the hinge moment balance 3), the connecting surface 5 of the wing and the fuselage is fixed, and the hinge moment balance 3 is loaded; specifically, the design loads of all components are respectively applied to the hinge moment balance 3 at the balance free end 4 of the hinge moment balance 3, the design loads are fitted to the center of the hinge moment balance 3, and the strain output epsilon of all components of the hinge moment balance 3 is recordedESee table 1.
TABLE 1 hinge moment balance Strain analysis results
In table 1, Z is the lateral force, Mx is the yaw moment, and Mj is the hinge moment.
Step eight, comparing results of all components of the hinge moment balance 3 in the step three and the step four, analyzing to obtain the influence of different positions of the fixed wing 1 on the measurement result of the hinge moment balance 3, wherein a calculation formula of relative errors is as follows:
the calculation results are shown in Table 2.
Step nine, comparing results of all components of the hinge moment balance 3 in the step four, the step five and the step six, analyzing to obtain the influence of the loaded deformation of the wing 1 on the measurement result of the hinge moment balance 3, wherein a calculation formula of relative errors is as follows:
the calculation results are shown in Table 2.
Step ten, comparing results of all components of the hinge moment balance 3 in the step six and the step seven, analyzing to obtain the influence of the first cover plate 7 and the second cover plate 8 on the measurement result of the hinge moment balance 3, wherein a calculation formula of relative errors is as follows:
the calculation results are shown in Table 2.
TABLE 2 influence on the measurement results of the hinge moment balance
As can be seen from table 2: in this embodiment, the different positions of the fixed wing 1, the deformation of the wing 1 and the presence or absence of the first cover plate 7 and the second cover plate 8, the moment component M of the hingejThe measurement result has small influence, the measurement error is within the allowable range of the wind tunnel test, but the measurement error is in the Z and MxThe component influence is large.
In this embodiment, the wing loading point 2 is located on the wing 1 and outside the hinge moment balance 3 (in the direction close to the wing tip); the external bridge is arranged at the joint of the hinge moment balance 3 and the wing 1.
In this embodiment, three external bridges are provided, which are sequentially referred to as a first external bridge 6a, a second external bridge 6b, and a third external bridge 6c, and the external bridges are provided at a connection portion between the hinge moment balance 3 and the wing 1, and are used for measuring deformation of the wing 1 after being loaded. Table 3 shows the static integrated calibration uncertainty of the hinge moment balance 3 of this example.
TABLE 3 comprehensive calibration uncertainty of hinge moment balance
As can be seen from table 3: the uncertainty of each component of the hinge moment balance 3 meets the measurement requirement, the uncertainty of the hinge moment balance 3 can be improved by the external bridge, but the uncertainty is not obvious, and the external bridge can be not corrected by the embodiment.
After the hinge moment balance 3 is calibrated, the hinge moment balance is loaded according to the wind tunnel test state, the connecting surface 5 of the fixed wing and the machine body respectively applies 10kg of load to the hinge moment balance 3 at the loading point A and the loading point B in the directions of + Z and-Z, the loading result is shown in a table 4, and the error values in the table are the ratio of the measured value to the true value of the hinge moment balance 3.
Table 4 hinge moment balance 3 with or without cover plate loading results (%)
As can be seen from table 4: the cover plate of the present embodiment has an influence on the loading result of the hinge moment balance 3, but the Z component and MjThe component influence is small, the requirement of measuring error in wind tunnel test is met, and M is measuredxThe component influence is large and basically consistent with the finite element analysis result, but the hinge moment test focuses on MjComponent, the requirements for the remaining components are lower.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (8)
1. A finite element analysis method of a hinge moment balance with wing deformation is characterized by comprising the following steps:
(1) three-dimensional modeling software is used for building three-dimensional models of the wing, the hinge moment balance, the first cover plate and the second cover plate; the built three-dimensional model comprises wings, hinge moment balances, a first cover plate and a second cover plate, wherein the hinge moment balances are arranged on the wings and are positioned on one sides of the wings, which are close to the rudder, the first cover plate and the second cover plate are respectively arranged on two sides of the hinge moment balances, and the first cover plate and the second cover plate are respectively and fixedly connected with the wings;
(2) importing the three-dimensional model constructed in the step 1 into finite element analysis software for grid division;
(3) after the wing is fixed, loading is carried out on the hinge moment balance;
(4) fixing the connection surface of the wing and the fuselage, and loading the hinge moment balance;
(5) fixing the connecting surface of the wing and the fuselage, taking a loading point at any place of the wing, marking as a wing loading point, and applying wing load to the wing loading point;
(6) fixing the connecting surface of the wing and the fuselage, applying wing load at the wing loading point in the step (5), and simultaneously loading the hinge moment balance;
(7) a first cover plate and a second cover plate are additionally arranged on two sides of the wing, the connecting surface of the wing and the body is fixed, and the hinge moment balance is loaded;
(8) comparing the analysis results of the components of the hinge moment balance in the step (3) and the step (4) to obtain the influence delta of different positions of the fixed wing on the measurement result of the hinge moment balanceI；
(9) Comparing the analysis results of the components of the hinge moment balance in the step (4), the step (5) and the step (6) to obtain the influence delta of the wing deformation on the measurement result of the hinge moment balanceII；
(10) Comparing the analysis results of the components of the hinge moment balance in the step (6) and the step (7) to obtain the influence delta of the first cover plate and the second cover plate on the measurement result of the hinge moment balanceIII；
(11) If deltaI、δII、δIIIThe measurement uncertainty of the hinge moment balance in the model is smaller when the measurement error of the middle hinge moment component is within the wind tunnel test allowable range; on the contrary, the larger the measurement uncertainty of the hinge moment balance in the model is, one or more of the hinge moment balance, the first cover plate and the second cover plate need to be optimized, or an external bridge needs to be added to correct the measurement result.
2. The finite element analysis method for a hinge moment balance with airfoil deformation according to claim 1, wherein in the step (3), the design loads of all components are respectively applied to the hinge moment balance at the balance free end of the hinge moment balance, and the design loads are fitted to the center of the hinge moment balance.
3. The finite element analysis method for a hinge moment balance with airfoil deformation according to claim 1, wherein in the step (4), the design loads of all components are respectively applied to the hinge moment balance at the balance free end of the hinge moment balance, and the design loads are fitted to the center of the hinge moment balance.
4. A finite element analysis method of a hinge moment balance with wing deformation according to any one of claims 1 to 3, wherein in the step (6), the connection surface of the wing and the fuselage is fixed, the wing load is applied at the wing load point in the step (5), simultaneously the design loads of all components are respectively applied to the hinge moment balance at the balance free end of the hinge moment balance, and the design loads are fitted to the center of the hinge moment balance.
5. A finite element analysis method of a hinge moment balance with wing deformation according to any one of claims 1 to 4, wherein the steps (3) to (6) are performed on the premise that the first cover plate and the second cover plate are not additionally arranged on two sides of the wing.
6. A finite element analysis method of a hinge moment balance with wing deformation according to any one of claims 1 to 5, wherein in the step (7), a first cover plate and a second cover plate are additionally arranged on two sides of a wing, a connecting surface of the wing and a fuselage is fixed, design loads of all components are respectively applied to the hinge moment balance at a balance free end of the hinge moment balance, and the design loads are fitted to the center of the hinge moment balance.
7. A finite element analysis method of a hinge moment balance with wing deformation according to any one of claims 1 to 6, wherein the wing loading point is arranged on the wing and is positioned outside the hinge moment balance and close to the wing tip.
8. A finite element analysis method of a hinge moment balance with wing deformation according to any one of claims 1-7, characterized in that in the step (11), an external bridge is arranged at the connection of the hinge moment balance and the wing.
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