CN105825035A - Equivalent treating method for surface distribution force generated when wing supporting poles are axially pressed - Google Patents
Equivalent treating method for surface distribution force generated when wing supporting poles are axially pressed Download PDFInfo
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Abstract
The invention relates to an equivalent treating method for surface distribution force generated when wing supporting poles are axially pressed, and belongs to the field of airplane structure strength tests. The equivalent treating method includes the steps that a whole finite element model of the wing supporting poles and connecting connectors at the two ends of the wing supporting poles is built, the wing supporting rods are divided into a plurality of sections in an equal length mode in the axial direction of the wing supporting poles, a finite element node is taken on any section, and the bending direction of the wing supporting poles under the condition of the surface distribution force serves as the applying direction of concentrated force; the finite element node corresponding to equivalent deformation serves as a concentrated force applying point; the ratio of the node lateral displacement of the surface distribution force condition to the node lateral displacement of the concentrated force condition is used for adjusting the concentrated force, and the final concentrated force is determined in a multi-iteration mode. In a strength test, whether the supporting poles meet strength design or not can be determined by applying the axial compression load and the concentrated force, and the test load is simplified.
Description
Technical field
The invention belongs to aircraft structure strength test field, particularly relate to the equivalent way of surface distributed power during a kind of wing strut axial compression.
Background technology
For using the aircraft of diagonal brace rod-type wing, the design of strut is most important, especially when strut bears axial compression load, it is susceptible to unstability thus loses bearing capacity, the also effect of wing strut surfaces simultaneously has the distributed force that aerodynamic loading produces, and this more can be substantially reduced its compression bearing capacity.
In order to verify whether the design of strut meets requirement of strength, need to make a strength test, and ensure that its stress is as far as possible close to true.But owing to the aerodynamic loading of strut surfaces belongs to EDS maps load, and be uneven, even on the different cross section of strut, load is reverse, if loaded in strict accordance with truth, it is difficult to carry out, it is thus desirable to the equivalent way of a kind of strut surfaces distributed force, in the case of ensureing that strut stress characteristic is constant, it is simple to test is implemented.
Summary of the invention
In order to solve the problems referred to above, the equivalent way of surface distributed power when this invention provides a kind of wing strut axial compression, the surface distributed power of described wing strut is equivalent to concentration power, consequently facilitating carry out the applying of load when its strength test, its equivalent process mainly comprises the steps that
S1, setting up the global finite element model of described wing strut and two ends jointing thereof, in described global finite element model, described wing strut stress includes axial compression load and surface distributed power；
S2, described wing strut the most isometric is divided into some sections along it, a finite element node is taken on either segment, calculate described wing strut simultaneously by the first deformation in the case of axial compression load and surface distributed power, and record the first lateral displacement of arbitrary described finite element node；
S3, using described wing strut bending direction in step s 2 as the applying direction of concentration power；
S4, a given initial set power, by the concentration power determined in step S3, described initial set power is applied direction be respectively acting on each finite element node of described wing strut, arbitrary finite element node is at the same time by all corresponding one second deformation in the case of the axial compression load identical with step S2 and initial set power, find out in some second deformation and deform immediate equivalent deformation with described first, and record the second lateral displacement of arbitrary described finite element node, finite element node corresponding for described equivalent deformation is applied a little as concentration power；
The ratio of S5, the maximum calculated in the first lateral displacement of each finite element node and the second lateral displacement under corresponding node, power size after described initial set power being amplified by described ratio is as the size of new concentration power, described new concentration power is used to repeat step S4-S5, until the first lateral displacement and the second lateral displacement difference are less than threshold value.
Preferably, in described step S2, described wing strut is not less than 10 sections along its hop count axially divided.
, in described step S2, described finite element node is positioned on the end face of either segment in such scheme preferably, and the spacing between each finite element node is identical.
, in described step S2, the first lateral displacement of described arbitrary described finite element node is the meansigma methods of this node lateral displacement under different progression surface distributed power in such scheme preferably.
In such scheme preferably, the progression of described surface distributed power is not less than 3 grades.
, multi-level table force per unit area includes strut close to load progression during unstability as afterbody in such scheme preferably, and with differential other load progression of retrodicting of 10%.
, in described step S3, using the bending direction of described wing strut afterbody surface distributed power in step s 2 as the applying direction of concentration power in such scheme preferably.
, in described step S5, described threshold value is 3% in such scheme preferably.
Present invention introduces the concentration power of an equivalence to substitute the dispersion force that surface is the most uneven, i.e. carry out all surface distributed force suffered by equivalent strut surfaces by a concentration power.The position and size that this concentration power applies is determined by theoretical relative analysis.In strength test, can determine whether strut meets Intensity Design by the axial compression load and this concentration power that apply strut, simplify test and load.
Accompanying drawing explanation
The flow chart of one preferred embodiment of the equivalent way of surface distributed power when Fig. 1 is wing strut axial compression of the present invention.
Fig. 2 is the wing strut schematic diagram by axial compression load Yu surface distributed power of embodiment illustrated in fig. 1.
Fig. 3 be embodiment illustrated in fig. 1 wing strut concentration power equivalence before and after node deviation ratio relatively schematic diagram.
Fig. 4 be embodiment illustrated in fig. 1 equivalence after the application point of concentration power, direction and big logotype.
Detailed description of the invention
Clearer for the purpose making the present invention implement, technical scheme and advantage, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, the most same or similar label represents same or similar element or has the element of same or like function.Described embodiment is a part of embodiment of the present invention rather than whole embodiments.The embodiment described below with reference to accompanying drawing is exemplary, it is intended to is used for explaining the present invention, and is not considered as limiting the invention.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art are obtained under not making creative work premise, broadly fall into the scope of protection of the invention.Below in conjunction with the accompanying drawings embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " orientation or the position relationship of the instruction such as " center ", " longitudinally ", " laterally ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " they be based on orientation shown in the drawings or position relationship; be for only for ease of the description present invention and simplifying and describe; rather than instruction or imply the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that limiting the scope of the invention.
Below by embodiment, the present invention is described in further details.
For using the aircraft of diagonal brace rod-type wing, wing strut is when bearing axial compression load, it is susceptible to unstability thus loses bearing capacity, the also effect of wing strut surfaces simultaneously has the distributed force that aerodynamic loading produces, this more can be substantially reduced its compression bearing capacity, in order to verify the intensity of strut, above two load must be applied during test, stretching for strut two ends, the load such as torsion can directly apply, its surface distributed power then is difficult to apply by practical situation due to shape contact area etc., for this, present invention introduces an equivalent force to reach above-mentioned purpose, i.e. carry out all surface distributed force suffered by equivalent strut surfaces by a concentration power.
Therefore, in the present embodiment, the determination process of concentration power mainly includes following three aspects:
Determine the applying direction of concentration power；
Determine the applying position of concentration power；
Determine the size of concentration power.
As it is shown in figure 1, the equivalent way of surface distributed power during wing strut axial compression of the present invention, mainly comprise the steps that
S1, setting up the global finite element model of described wing strut and two ends jointing thereof, in described global finite element model, described wing strut stress includes axial compression load and surface distributed power；
S2, described wing strut the most isometric is divided into some sections along it, a finite element node is taken on either segment, calculate described wing strut simultaneously by the first deformation in the case of axial compression load and surface distributed power, and record the first lateral displacement of arbitrary described finite element node；
S3, using described wing strut bending direction in step s 2 as the applying direction of concentration power；
S4, a given initial set power, by the concentration power determined in step S3, described initial set power is applied direction be respectively acting on each finite element node of described wing strut, arbitrary finite element node is at the same time by all corresponding one second deformation in the case of the axial compression load identical with step S2 and initial set power, find out in some second deformation and deform immediate equivalent deformation with described first, and record the second lateral displacement of arbitrary described finite element node, finite element node corresponding for described equivalent deformation is applied a little as concentration power；
The ratio of S5, the maximum calculated in the first lateral displacement of each finite element node and the second lateral displacement under corresponding node, power size after described initial set power being amplified by described ratio is as the size of new concentration power, described new concentration power is used to repeat step S4-S5, until the first lateral displacement and the second lateral displacement difference are less than threshold value.
It should be noted that in the present embodiment, described wing strut is not less than 10 sections along its hop count axially divided
It is understandable that, the present embodiment uses an equivalent concentration power to process for the surface distributed power of wing strut, so that loading more convenient during test, as shown in Figure 2, except wing strut two ends or wherein one end apply axial 25933N load in addition to, its each surface in axial direction is also distributed some surface distributed power, actually, these surface distributed power sizes, directions etc. all may be different, the surface distributed force direction even having is the most contrary, this is difficult to apply in process of the test, for this, the present invention uses concentration power to replace, as shown in Figure 4, concentration power for a 450N after equivalence, below to its direction, size, the determination method of application point is described in detail.
First, in step sl, setting up the FEM (finite element) model of wing strut, including strut body and the jointing at two ends, two ends carry out hinged constraint by the practical situation of structure, and load includes axial compression load and surface distributed power, as shown in Figure 2.
Secondly, in step s 2, node division is first carried out, wing strut body is axially divided into 25 sections along it by the present embodiment, it comprises 25 cross sections, finite element node is positioned on the end face of either segment in (or cross section), and the spacing between each finite element node is identical.In alternate embodiment, finite element node can also be arranged in each section in the heart.
In the present embodiment, in described step S2, the first lateral displacement of described arbitrary described finite element node is the meansigma methods of this node lateral displacement under different progression surface distributed power.nullSuch as，By considering the finite element nonlinear analysis method of geometrical large distortion，Wings strut is at the same time by the deformation under axial compression load and surface distributed load effect，And record 80%、90%、100%、The lateral displacement of finite element node on 110% and 120% 5 lower 25 cross section of load progression，Wherein，The meansigma methods of all node lateral displacements can be chosen on each cross section as the lateral displacement of this section，Lateral displacement under every one-level load can also all carry out record to indicate，As shown in Figure 3，Transverse axis represents stay length direction，The longitudinal axis is the lateral displacement of node，Zero is the bottom terminal ends of strut，In diagram as a example by solid line，It represents the node lateral displacement situation under raw payload，The most in step s 2，Not before equivalence concentration power，The lateral displacement situation of each finite element node under surface distributed power effect.
The progression of surface distributed power of the present invention is not less than 3 grades, the present embodiment illustrates as a example by 5 grades, wherein 100% load is test requirements document load, load more than 100% is overload, the load of 120% is collapsing load, multi-level table force per unit area includes strut close to load progression during unstability as afterbody, and with differential other load progression of retrodicting of 10%, i.e. in the present embodiment, first determine that the load of 120% is as afterbody, thus place's 110% load of retrodicting, 100% load, 90% load and 80% load, it should be noted that, load progression choose it is desirable that the progression at 100% load place is middle progression, if the load i.e. during unstability is 130%, differential is 10%, the most typically choose 7 load progression；If load during unstability is 120%, differential is 5%, the most typically chooses 9 load progression.
In the present embodiment, first have to determine the applying direction of concentration power by the method, concrete, in described step S3, using the bending direction of described wing strut afterbody surface distributed power in step s 2 as the applying direction of concentration power, the direction of the applying of concentration power should make strut identical by curved direction unstability final with the strut above calculated (120% load) bending direction.
Next to that determine the application point of concentration power, as shown in step s 4, the size of the most initial given concentration power is 400N, apply to 25 cross sections by the direction determined in step S3 one by one, consider the axial compression load of strut simultaneously, the deformation of strut in the case of calculating every kind respectively, and record the lateral displacement of 5 lower 25 sections of load progression, then calculated lateral displacement contrasts with step 3, found by contrast with under same load progression, concentration power is applied to the 16th section (from strut lower end upwards terminal number), load simplify before and after the lateral displacement of each cross section ratio closest to, the i.e. deformation form of load simplification rear pole is front with simplification closest, it is thus determined that concentration power is applied to this section.
As shown in Figure 3, dotted line represents the drift condition of each node when applying concentration power, determine that two deformations before and after equivalence are the most identical to be determined to introduce the modes such as variance, such as, two lines any node before and after equivalence all includes a difference, the variance of 25 differences is the least, represent the shape of this two lines closer to.In alternate embodiment, also include determining that the shape of two lines is the most close by way of contrast such as standard deviation or parabola opening angles.
Present invention introduces the concentration power of an equivalence to substitute the dispersion force that surface is the most uneven, i.e. carry out all surface distributed force suffered by equivalent strut surfaces by a concentration power.The position and size that this concentration power applies is determined by theoretical relative analysis.In strength test, can determine whether strut meets Intensity Design by the axial compression load and this concentration power that apply strut, simplify test and load.
Finally determine the size applying concentration power, in step S5, know when 100% load progression by calculating above, as shown in Figure 3, from 14th cross section (from strut lower end to upper end), lateral displacement is maximum, before and after load simplifies, its lateral displacement ratio is 1.12, and the newest concentration power size is 400N*1.12=448N.
nullOwing to the relation between concentration power size and node lateral displacement is non-linear relation，The present embodiment finally can also be circulated verification，I.e. in the case of new concentration power，New concentration power is replaced initial set power，Repeat step S4-S5，Until the curve before and after equivalence is basically identical，In the present embodiment，Concrete according to new concentration power size，Consider the axial compression load of bar simultaneously，Calculate the deformation of strut，By contrasting with the strut lateral displacement that obtains in abovementioned steps，80%、90%、100%、110% is consistent with the lateral displacement of finite element node on 120% 5 lower 25 cross section of load progression，It is appreciated that，In the present embodiment，If the lateral displacement of two nodes is less than 3%，Think that lateral displacement is consistent，If it is inconsistent，Using 448N as new concentration power，Repeat step S4 and S5.The distributed force of strut surfaces is reduced to a concentration power the most at last, concentration power size 450N the most finally determined, is perpendicular to strut and is axially applied to the 16th section (from strut lower end upwards terminal number).
Last it is noted that above example is only in order to illustrate technical scheme, it is not intended to limit.Although the present invention being described in detail with reference to previous embodiment, it will be understood by those within the art that: the technical scheme described in foregoing embodiments still can be modified by it, or wherein portion of techniques feature is carried out equivalent；And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (8)
1. an equivalent way for surface distributed power during wing strut axial compression, is equivalent to concentration power by the surface distributed power of described wing strut, it is characterised in that including:
S1, setting up the global finite element model of described wing strut and two ends jointing thereof, in described global finite element model, described wing strut stress includes axial compression load and surface distributed power；
S2, described wing strut the most isometric is divided into some sections along it, a finite element node is taken on either segment, calculate described wing strut simultaneously by the first deformation in the case of axial compression load and surface distributed power, and record the first lateral displacement of arbitrary described finite element node；
S3, using described wing strut bending direction in step s 2 as the applying direction of concentration power；
S4, a given initial set power, by the concentration power determined in step S3, described initial set power is applied direction be respectively acting on each finite element node of described wing strut, arbitrary finite element node is at the same time by all corresponding one second deformation in the case of the axial compression load identical with step S2 and initial set power, find out in some second deformation and deform immediate equivalent deformation with described first, and record the second lateral displacement of arbitrary described finite element node, finite element node corresponding for described equivalent deformation is applied a little as concentration power；
The ratio of the second lateral displacement under S5, the maximum calculated in the first lateral displacement and this maximum corresponding node, power size after described initial set power being amplified by described ratio is as the size of new concentration power, described new concentration power is used to repeat step S4-S5, until the first lateral displacement and the second lateral displacement difference are less than threshold value.
2. the equivalent way of surface distributed power during wing strut axial compression as claimed in claim 1, it is characterised in that: in described step S2, described wing strut is not less than 10 sections along its hop count axially divided.
3. the equivalent way of surface distributed power during wing strut axial compression as claimed in claim 1, it is characterised in that: in described step S2, described finite element node is positioned on the end face of either segment, and the spacing between each finite element node is identical.
4. the equivalent way of surface distributed power during wing strut axial compression as claimed in claim 1, it is characterized in that: in described step S2, the first lateral displacement of described arbitrary described finite element node is the meansigma methods of this node lateral displacement under different progression surface distributed power.
5. the equivalent way of surface distributed power during wing strut axial compression as claimed in claim 4, it is characterised in that: the progression of described surface distributed power is not less than 3 grades.
6. the equivalent way of surface distributed power during wing strut axial compression as claimed in claim 5, it is characterized in that: multi-level table force per unit area includes strut close to load progression during unstability as afterbody, and with differential other load progression of retrodicting of 10%.
7. the equivalent way of surface distributed power during wing strut axial compression as claimed in claim 6, it is characterized in that: in described step S3, using the bending direction of described wing strut afterbody surface distributed power in step s 2 as the applying direction of concentration power.
8. the equivalent way of surface distributed power during wing strut axial compression as claimed in claim 1, it is characterised in that: in described step S5, described threshold value is 3%.
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