CN106240842A - A kind of asymmetric fuselage bulkhead four-point bending test method and device - Google Patents
A kind of asymmetric fuselage bulkhead four-point bending test method and device Download PDFInfo
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- CN106240842A CN106240842A CN201610541264.7A CN201610541264A CN106240842A CN 106240842 A CN106240842 A CN 106240842A CN 201610541264 A CN201610541264 A CN 201610541264A CN 106240842 A CN106240842 A CN 106240842A
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Abstract
The invention discloses a kind of asymmetric fuselage bulkhead four-point bending test method and device.Described asymmetric fuselage bulkhead four-point bending test method comprises the steps: step 1: add test block for asymmetric fuselage bulkhead to be measured；Step 2: for increasing a loading head assembly on two relative weighted platforms of experiment loading unit respectively, described loading head assembly can adapt to the flexural deformation that fuselage bulkhead is occurred, remains loading force vertical with bulkhead flat segments (lower same)；Step 3: asymmetric fuselage bulkhead to be measured is arranged between two loading head assemblies, and carries out four-point bending test.Asymmetric fuselage bulkhead four-point bending test method in the present invention makes the asymmetric fuselage bulkhead pressure heart that loads when load test pass through the cross section flexual center of described asymmetric fuselage bulkhead, adjust the flexural deformation of asymmetric fuselage bulkhead to be measured by the way of deforming when loading head assembly is in stress when loading, reach to measure the purpose of asymmetric eccentric structure.
Description
Technical field
The present invention relates to aircaft configuration static(al)/fatigue test technology field, particularly relate to a kind of asymmetric fuselage bulkhead
Four-point bending test method and asymmetric fuselage bulkhead four-point bending test device.
Background technology
In aircaft configuration static(al)/fatigue test, the testpieces carrying out four-point bending is usually symmetrical structure, due to fuselage
The cross-sectional profile that bulkhead loads is asymmetric eccentric structure, directly applies to produce eccentric moment during ballast on testing machine,
Make testpieces attitude run-off the straight.This eccentric moment can be transferred to testing machine by fixture, causes testing machine chuck to bend, and with
The increase of ballast, this moment also can become big, in divergent trend, consequently, it is possible to cause testpieces test data set failure mode
Inaccurate.
Thus, it is desirable to have a kind of technical scheme overcomes or at least alleviates at least one drawbacks described above of prior art.
Summary of the invention
It is an object of the invention to provide a kind of asymmetric fuselage bulkhead four-point bending test method overcome or at least subtract
At least one drawbacks described above of light prior art.
For achieving the above object, the invention provides a kind of asymmetric fuselage bulkhead four-point bending test method, described non-
Symmetrical fuselage bulkhead four-point bending test method comprises the steps: step 1: add test for asymmetric fuselage bulkhead to be measured
Block, so that asymmetric fuselage bulkhead loading when load test presses the heart curved by the cross section of described asymmetric fuselage bulkhead
The heart；Step 2: for increasing a loading head assembly, described loading on two relative weighted platforms of experiment loading unit respectively
Head assembly adapts to the flexural deformation that fuselage bulkhead is occurred, and remains that loading force is vertical with bulkhead flat segments；Step 3: will
Asymmetric fuselage bulkhead to be measured is arranged between two loading head assemblies, and carries out four-point bending test.
Preferably, described asymmetric fuselage bulkhead four-point bending test method farther includes: previous step 1: calculate institute
State the cross section flexual center of asymmetric fuselage bulkhead to be measured.
Present invention also offers a kind of asymmetric fuselage bulkhead four-point bending test device, for by asymmetric machine to be measured
Body bulkhead is installed to experiment loading unit and carries out asymmetric fuselage bulkhead four-point bending test method as above, described examination
Test charger for for described asymmetric fuselage bulkhead imposed load to be measured, each asymmetric fuselage bulkhead have two every
Frame loaded segment；It is characterized in that, described asymmetric fuselage bulkhead four-point bending test device includes: test block assembly, described examination
Testing block assembly is two groups, and test block assembly described in one of which is arranged on a bulkhead of asymmetric fuselage bulkhead to be measured and loads
Duan Shang, another is organized described test block assembly and is arranged in another bulkhead loaded segment；Loading head assembly, described loading head assembly
Quantity is four, and wherein, each two loading head assembly is used for a bulkhead loaded segment, thus four loading head assemblies are divided into the
One loading group and the second loading group；A loading head assembly in described first loading group is arranged on the one of experiment loading unit
On one face of individual weighted platform；Another loading head assembly is arranged on a face of another weighted platform, and two add
Carrier head assembly is oppositely arranged, thus forms loading space, and this loading space is for one bulkhead loaded segment of clamping；Described second adds
On one face of the weighted platform that a loading head assembly in load group is arranged on experiment loading unit；Another loading head
Assembly is arranged on a face of another weighted platform, and two loading head assemblies are oppositely arranged, thus forms loading space,
This loading space is used for clamping another bulkhead loaded segment；Wherein, described test block assembly is used for following fuselage bulkhead and is occurred
Flexural deformation, remain that loading force is vertical with bulkhead flat segments, thus ensure in this four-point bending test apply constant
Moment of flexure is constant；Described loading head assembly for following described asymmetric fuselage at described asymmetric fuselage bulkhead when stand under load deforms
Bulkhead moves, and each loading head assembly coordinates, thus keep in loading procedure experiment loading unit to described asymmetric fuselage every
The direction of the power that frame applies is perpendicular to described asymmetric fuselage bulkhead all the time.
Preferably, described test block assembly includes multiple test block, each test block all with described bulkhead loaded segment with can
Dismounting mode connects.
Preferably, described test block is connected with described bulkhead loaded segment bolt.
Preferably, each described loading head assembly includes: support, and described support is connected with described weighted platform；First adds
Carrier head, described first loading head is arranged on the bracket, and the face away from described support of described first loading head is concave surface；The
Two loading heads, a face of described second loading head is concave surface, and another face is plane, described plane and described bulkhead loaded segment
Contact, the concave surface of described second loading head is relative with the concave surface of described first loading head, and the concave surface of described first loading head and
Formed between the concave surface of described second loading head and accommodate space；Cylinder, described cylinder is arranged in described receiving space, and can
Rotate in described receiving space.
Preferably, the area in the face carrying described first loading head of described support is more than described first loading head with described
The area in the face of support contact.
Asymmetric fuselage bulkhead four-point bending test method in the present invention makes asymmetric fuselage bulkhead when load test
Load the pressure heart by the cross section flexual center of described asymmetric fuselage bulkhead, and when loading by loading head assembly in stress time
The mode deformed is to adjust the flexural deformation of asymmetric fuselage bulkhead to be measured, thus has reached the asymmetric eccentric knot of measurement
The purpose of structure, and the method art of the present invention the most easily implements, can guarantee that and be loaded onto during the bending of testpieces is made a concerted effort in the heart, will not produce
Raw torsion, and loading accuracy is high.
Accompanying drawing explanation
Fig. 1 is the schematic flow sheet of the most asymmetric fuselage bulkhead four-point bending test method.
Fig. 2 is the structural representation of the most asymmetric fuselage bulkhead four-point bending test device.
Reference
| 1 | Experiment loading unit | 31 | Support |
| 2 | Asymmetric fuselage bulkhead | 32 | First loading head |
| 3 | Loading head assembly | 33 | Second loading head |
| 11 | Weighted platform | 34 | Cylinder |
| 4 | Test block |
Detailed description of the invention
Clearer for the purpose making the present invention implement, technical scheme and advantage, below in conjunction with in the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, the most identical or class
As label represent same or similar element or there is the element of same or like function.Described embodiment is the present invention
A part of embodiment rather than whole embodiments.The embodiment described below with reference to accompanying drawing is exemplary, it is intended to use
In explaining the present invention, and it is not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under not making creative work premise, broadly falls into the scope of protection of the invention.Under
Face combines accompanying drawing and is described in detail embodiments of the invention.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " laterally ", "front", "rear",
The orientation of the instruction such as "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " or position relationship are for based on accompanying drawing institute
The orientation shown or position relationship, be for only for ease of and describe the present invention and simplify description rather than instruction or the dress of hint indication
Put or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that protect the present invention
The restriction of scope.
Fig. 1 is the schematic flow sheet of the most asymmetric fuselage bulkhead four-point bending test method.
Fig. 2 is the structural representation of the most asymmetric fuselage bulkhead four-point bending test device.
Asymmetric fuselage bulkhead four-point bending test method as shown in Figure 1 comprises the steps: step 1: for be measured
Asymmetric fuselage bulkhead adds test block, so that the loading pressure heart that asymmetric fuselage bulkhead is when load test is by described non-
The cross section flexual center of symmetrical fuselage bulkhead；Step 2: for increasing by one respectively on two relative weighted platforms of experiment loading unit
Individual loading head assembly, described loading head assembly adapts to the flexural deformation that fuselage bulkhead is occurred, remain loading force with every
Frame flat segments is vertical；Step 3: asymmetric fuselage bulkhead to be measured is arranged between two loading head assemblies, and carries out 4 points
Bend test.
Asymmetric fuselage bulkhead four-point bending test method in the present invention makes asymmetric fuselage bulkhead when load test
Load the pressure heart by the cross section flexual center of described asymmetric fuselage bulkhead, and when loading by loading head assembly in stress time
The mode deformed is to adjust the flexural deformation of asymmetric fuselage bulkhead to be measured, thus has reached the asymmetric eccentric knot of measurement
The purpose of structure, and the method art of the present invention the most easily implements, can guarantee that and be loaded onto during the bending of testpieces is made a concerted effort in the heart, will not produce
Raw torsion, and loading accuracy is high.
It is understood that asymmetric fuselage bulkhead four-point bending test method farther includes previous step 1: obtain and treat
The cross section flexual center of the asymmetric fuselage bulkhead surveyed.This cross section flexual center can be calculated by this cross section geometric profile and obtain
, it is also possible to it is previously known.
Present invention also offers a kind of asymmetric fuselage bulkhead four-point bending test device, for by asymmetric machine to be measured
Body bulkhead is installed to experiment loading unit and carries out asymmetric fuselage bulkhead four-point bending test method as above, and test adds
Carrying and put 1 for for asymmetric fuselage bulkhead 2 imposed load to be measured, each asymmetric fuselage bulkhead 2 has two bulkheads and adds
Carry section.
Asymmetric fuselage bulkhead four-point bending test device as shown in Figure 2 includes test block assembly and loading head assembly
3, test block assembly is two groups, and one of which test block assembly is arranged on a bulkhead of asymmetric fuselage bulkhead 2 to be measured and adds
Carrying in section, another group test block assembly is arranged in another bulkhead loaded segment；The quantity of loading head assembly 3 is four, wherein,
Each two loading head assembly 3 is for a bulkhead loaded segment, thus four loading head assemblies are divided into the first loading group and the
Two loading groups；A loading head assembly 3 in first loading group is arranged on the one of a weighted platform 11 of experiment loading unit 1
On individual face；Another loading head assembly 3 is arranged on a face of another weighted platform 11, and two loading head assembly 3 phases
To setting, thus forming loading space, this loading space is for one bulkhead loaded segment of clamping；One in second loading group adds
Carrier head assembly 3 is arranged on a face of a weighted platform 11 of experiment loading unit；Another loading head assembly 3 is arranged on
On one face of another weighted platform 11, and two loading head assemblies 3 are oppositely arranged, thus form loading space, this loading
Space is used for clamping another bulkhead loaded segment；Wherein, test block assembly is used for following the flexural deformation that fuselage bulkhead is occurred,
Remain that loading force is vertical with bulkhead flat segments, thus ensure that the constant moment of flexure applied in this four-point bending test is constant；Add
Carrier head assembly for following the motion of asymmetric fuselage bulkhead, each loading head assembly at asymmetric fuselage bulkhead when stand under load deforms
Coordinate, thus keep the direction of the power that experiment loading unit applies to asymmetric fuselage bulkhead in loading procedure to be perpendicular to non-all the time
Symmetrical fuselage bulkhead.
Asymmetric fuselage bulkhead four-point bending test device in the present invention use test block assembly make asymmetric fuselage every
The frame pressure heart that loads when load test passes through the cross section flexual center of described asymmetric fuselage bulkhead, and when loading by loading
The mode that head assembly deforms when stress is to adjust the flexural deformation of asymmetric fuselage bulkhead to be measured, thus has reached to survey
Measure the purpose of asymmetric eccentric structure, and the asymmetric fuselage bulkhead four-point bending test device art of the present invention the most easily implemented,
Can guarantee that and be loaded onto in the bending with joint efforts of testpieces in the heart, torsion will not be produced, and loading accuracy is high.
It is understood that test block assembly includes multiple test block 4, each test block 4 all with bulkhead loaded segment with can
Dismounting mode connects.It is understood that depending on the shape that the quantity of this test block is according to asymmetric fuselage bulkhead.Such as, exist
In embodiment shown in Fig. 2, each bulkhead loaded segment of this asymmetric fuselage bulkhead is provided with 3 test block.
Understandable volume is, the asymmetric fuselage bulkhead 4 being attached facilitating the application by removably is curved
The recycling of bent assay device.
Advantageously, test block 4 is connected with described bulkhead loaded segment bolt.With bolts is a kind of simplest company
Connect mode, and need not the shape of too much tampering devic, structure such that it is able to prevent increasing connected mode and cause to be measured non-
The situations such as the centre of form transfer of symmetrical fuselage bulkhead occur.
Seeing Fig. 2, in the present embodiment, each loading head assembly includes support the 31, first loading head 32 2 loading head 33
And cylinder 34, support 31 is connected with weighted platform 11；First loading head 32 is arranged on support 31, the first loading head 32 remote
It is concave surface from the face of support；One face of the second loading head 33 is concave surface, and another face is plane, and plane connects with bulkhead loaded segment
Touch, the concave surface of the second loading head 33 and the concave surface of the first loading head relatively, and the concave surface of the first loading head and the second loading head
Formed between concave surface and accommodate space；Cylinder 34 is arranged in receiving space, and can rotate within accommodating space.May be appreciated
It is to adopt in this way, when power is transferred on the second loading head, contacts owing to itself and cylinder are round and smooth, now, the second loading head
Changed the direction of power by motion, thus reach the purpose of the application.
Advantageously, the face that the area in the face of carrying first loading head of support 31 contacts with support more than the first loading head
Area.Use this structure, it is possible to make the first loading head be arranged on more stably on support.
Last it is noted that above example is only in order to illustrate technical scheme, it is not intended to limit.To the greatest extent
The present invention has been described in detail by pipe with reference to previous embodiment, it will be understood by those within the art that: it is still
Technical scheme described in foregoing embodiments can be modified, or wherein portion of techniques feature is carried out equivalent replace
Change；And these amendments or replacement, do not make the essence of appropriate technical solution depart from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (7)
1. an asymmetric fuselage bulkhead four-point bending test method, it is characterised in that described asymmetric fuselage bulkhead 4 is curved
Bent test method comprises the steps:
Step 1: add test block for asymmetric fuselage bulkhead to be measured, so that asymmetric fuselage bulkhead is when load test
Load the pressure heart cross section flexual center by described asymmetric fuselage bulkhead；
Step 2: for increasing a loading head assembly, described loading on two relative weighted platforms of experiment loading unit respectively
Head assembly adapts to the flexural deformation that fuselage bulkhead is occurred, and remains that loading force is vertical with bulkhead flat segments；
Step 3: asymmetric fuselage bulkhead to be measured is arranged between two loading head assemblies, and carries out four-point bending test.
Asymmetric fuselage bulkhead four-point bending test method the most as claimed in claim 1, it is characterised in that described asymmetric machine
Body bulkhead four-point bending test method farther includes:
Previous step 1: calculate the cross section flexual center of described asymmetric fuselage bulkhead to be measured.
3. an asymmetric fuselage bulkhead four-point bending test device, for installing asymmetric fuselage bulkhead to be measured to test
Charger also carries out asymmetric fuselage bulkhead four-point bending test method as claimed in claim 1 or 2, and described test loads
Device (1) is for for described asymmetric fuselage bulkhead (2) imposed load to be measured, and each asymmetric fuselage bulkhead (2) has two
Individual bulkhead loaded segment；It is characterized in that, described asymmetric fuselage bulkhead four-point bending test device includes:
Test block assembly, described test block assembly is two groups, and test block assembly described in one of which is arranged on to be measured asymmetric
In one bulkhead loaded segment of fuselage bulkhead (2), another is organized described test block assembly and is arranged in another bulkhead loaded segment；
Loading head assembly (3), the quantity of described loading head assembly (3) is four, and wherein, each two loading head assembly (3) is used for
One bulkhead loaded segment, thus four loading head assemblies are divided into the first loading group and the second loading group；
A loading head assembly (3) in described first loading group is arranged on a weighted platform of experiment loading unit (1)
(11) on a face；Another loading head assembly (3) is arranged on a face of another weighted platform (11), and two add
Carrier head assembly (3) is oppositely arranged, thus forms loading space, and this loading space is for one bulkhead loaded segment of clamping；
A loading head assembly (3) in described second loading group is arranged on a weighted platform (11) of experiment loading unit
On one face；Another loading head assembly (3) is arranged on a face of another weighted platform (11), and two loading head groups
Part (3) is oppositely arranged, thus forms loading space, and this loading space is used for clamping another bulkhead loaded segment；Wherein,
Described test block assembly, for following the flexural deformation that fuselage bulkhead is occurred, remains loading force and bulkhead flat segments
Vertically, thus ensure in this four-point bending test apply constant moment of flexure constant；
Described loading head assembly for following described asymmetric fuselage bulkhead at described asymmetric fuselage bulkhead when stand under load deforms
Motion, each loading head assembly coordinates, thus keeps experiment loading unit in loading procedure to execute to described asymmetric fuselage bulkhead
The direction of the power added is perpendicular to described asymmetric fuselage bulkhead all the time.
Asymmetric fuselage bulkhead four-point bending test device the most as claimed in claim 3, it is characterised in that described test block group
Part includes that multiple test block (4), each test block (4) are all removably connected with described bulkhead loaded segment.
Asymmetric fuselage bulkhead four-point bending test device the most as claimed in claim 4, it is characterised in that described test block
(4) it is connected with described bulkhead loaded segment bolt.
Asymmetric fuselage bulkhead four-point bending test device the most as claimed in claim 5, it is characterised in that each described loading
Head assembly includes:
Support (31), described support (31) is connected with described weighted platform (11)；
First loading head (32), described first loading head (32) is arranged on described support (31), described first loading head (32)
The face away from described support be concave surface；
Second loading head (33), a face of described second loading head (33) is concave surface, and another face is plane, described plane with
Described bulkhead loaded segment contacts, and the concave surface of described second loading head (33) is relative and described with the concave surface of described first loading head
Formed between concave surface and the concave surface of described second loading head of the first loading head and accommodate space；
Cylinder (34), described cylinder (34) is arranged in described receiving space, and can rotate in described receiving space.
Asymmetric fuselage bulkhead four-point bending test device the most as claimed in claim 6, it is characterised in that described support (31)
The area in face that contacts with described support more than described first loading head of the area in the face carrying described first loading head.
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| CN201610541264.7A CN106240842B (en) | 2016-07-11 | 2016-07-11 | A kind of asymmetric fuselage bulkhead four-point bending test method and device |
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| CN201610541264.7A CN106240842B (en) | 2016-07-11 | 2016-07-11 | A kind of asymmetric fuselage bulkhead four-point bending test method and device |
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| CN106240842B CN106240842B (en) | 2019-02-05 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108334653A (en) * | 2017-10-20 | 2018-07-27 | 北京空天技术研究所 | A kind of Static Analysis Model of Micro-machined modification method, update the system and Static Strength Analysis method |
| CN109357851A (en) * | 2018-10-17 | 2019-02-19 | 中国飞机强度研究所 | A kind of four-point bending test loading method of fuselage song mount structure |
| CN116660055A (en) * | 2023-06-02 | 2023-08-29 | 南京航空航天大学 | Four-point bending loading test device suitable for main cargo compartment door lock hook structure |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005040765A3 (en) * | 2003-10-28 | 2005-08-04 | Univ Do Minho | Multiaxial universal testing machine |
| CN102288483A (en) * | 2011-07-08 | 2011-12-21 | 中国飞机强度研究所 | Supporting clamp for compression stabilization experiment of reinforced wallboard and supporting coefficient testing method for end socket |
| CN102353578A (en) * | 2011-09-30 | 2012-02-15 | 上海交通大学 | Testing device for two-way loading test of material |
| CN103293056A (en) * | 2013-04-19 | 2013-09-11 | 空军工程大学 | Stiffened plate structure axial compression stability test clamp and method |
| CN103604699A (en) * | 2013-12-04 | 2014-02-26 | 中国飞机强度研究所 | Loading method for two-way tensile test |
| EP2407767A4 (en) * | 2009-03-10 | 2014-05-21 | Mitsubishi Materials Corp | Biaxial tensile testing machine |
-
2016
- 2016-07-11 CN CN201610541264.7A patent/CN106240842B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005040765A3 (en) * | 2003-10-28 | 2005-08-04 | Univ Do Minho | Multiaxial universal testing machine |
| EP2407767A4 (en) * | 2009-03-10 | 2014-05-21 | Mitsubishi Materials Corp | Biaxial tensile testing machine |
| CN102288483A (en) * | 2011-07-08 | 2011-12-21 | 中国飞机强度研究所 | Supporting clamp for compression stabilization experiment of reinforced wallboard and supporting coefficient testing method for end socket |
| CN102353578A (en) * | 2011-09-30 | 2012-02-15 | 上海交通大学 | Testing device for two-way loading test of material |
| CN103293056A (en) * | 2013-04-19 | 2013-09-11 | 空军工程大学 | Stiffened plate structure axial compression stability test clamp and method |
| CN103604699A (en) * | 2013-12-04 | 2014-02-26 | 中国飞机强度研究所 | Loading method for two-way tensile test |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108334653A (en) * | 2017-10-20 | 2018-07-27 | 北京空天技术研究所 | A kind of Static Analysis Model of Micro-machined modification method, update the system and Static Strength Analysis method |
| CN109357851A (en) * | 2018-10-17 | 2019-02-19 | 中国飞机强度研究所 | A kind of four-point bending test loading method of fuselage song mount structure |
| CN109357851B (en) * | 2018-10-17 | 2020-08-11 | 中国飞机强度研究所 | Four-point bending test loading method for curved frame structure of machine body |
| CN116660055A (en) * | 2023-06-02 | 2023-08-29 | 南京航空航天大学 | Four-point bending loading test device suitable for main cargo compartment door lock hook structure |
| CN116660055B (en) * | 2023-06-02 | 2023-11-03 | 南京航空航天大学 | Four-point bending loading test device suitable for main cargo compartment door lock hook structure |
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| CN106240842B (en) | 2019-02-05 |
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