CN110018066A - A kind of shock loading test device and method for aircraft engine supporting structure - Google Patents
A kind of shock loading test device and method for aircraft engine supporting structure Download PDFInfo
- Publication number
- CN110018066A CN110018066A CN201910383002.6A CN201910383002A CN110018066A CN 110018066 A CN110018066 A CN 110018066A CN 201910383002 A CN201910383002 A CN 201910383002A CN 110018066 A CN110018066 A CN 110018066A
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- supporting structure
- shock loading
- test device
- tup
- aircraft engine
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- 238000012360 testing method Methods 0.000 title claims abstract description 92
- 238000011068 loading method Methods 0.000 title claims abstract description 54
- 230000035939 shock Effects 0.000 title claims abstract description 54
- 238000000034 method Methods 0.000 title claims abstract description 9
- 230000005540 biological transmission Effects 0.000 claims abstract description 32
- 239000011888 foil Substances 0.000 claims abstract description 20
- 230000001133 acceleration Effects 0.000 claims description 10
- 238000006073 displacement reaction Methods 0.000 claims description 10
- 238000010998 test method Methods 0.000 claims description 5
- 230000008569 process Effects 0.000 claims description 4
- 230000006378 damage Effects 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 238000004458 analytical method Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 238000012356 Product development Methods 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009863 impact test Methods 0.000 description 1
- 238000012067 mathematical method Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/30—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight
- G01N3/303—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight generated only by free-falling weight
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0001—Type of application of the stress
- G01N2203/001—Impulsive
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/003—Generation of the force
- G01N2203/0032—Generation of the force using mechanical means
- G01N2203/0039—Hammer or pendulum
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/0202—Control of the test
- G01N2203/0212—Theories, calculations
- G01N2203/0218—Calculations based on experimental data
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a kind of shock loading test devices and method for aircraft engine supporting structure, test device setting uses on drop weight test platform, drop weight test platform includes workbench and tup, test device includes the fixing seat for installing supporting structure and the shock loading for applying tup is transmitted to the force transmission element on supporting structure, fixing seat is arranged on the table, supporting structure is arranged in fixing seat, force transmission element is connect with supporting structure, test device further includes being sticked on supporting structure for testing the foil gauge for the shock loading that supporting structure is born.The shock loading test device structure for being used for aircraft engine supporting structure is simple, manufacturing cost is low, securely and reliably, dynamic test of the supporting structure under different impact energys can be achieved, and the shock loading that supporting structure is born in test can be obtained, to obtain dynamic characteristics and destruction of the supporting structure under different operating conditions.
Description
Technical field
The present invention relates to material properties test technical fields, and in particular to a kind of for aircraft engine supporting structure
Shock loading test device and method.
Background technique
Power producer of the engine as aircraft and automobile, just as human heart.Supporting structure is aircraft turbofan
Important one of the building block of engine, carries extremely complex mechanical load.Cause to reduce when fan blade falls off
The impact of other engine critical components influences, and requires its thinning area when supporting structure is by the shock loading passed over
Domain occurs to be broken broken ring, therefore engine support structure part operating condition is severe, and stress is complicated, it is desirable that its material has higher mechanics
Performance, while also needing to play the role of protecting engine.In order to shorten product development cycle and reduce development cost, at present industry
In using finite element simulation technology carry out structure design have become a kind of mainstream.Supporting structure is very multiple due to itself structure
It is miscellaneous and relatively high to the performance requirement of its various aspects, solely by emulation mode be unable to its stress condition of accurate response and
Collapse state.Therefore, it is necessary to obtain dynamic of the aircraft engine supporting structure under different operating conditions by the means of test
Mechanical characteristic and destruction.
Summary of the invention
The purpose of the present invention is being directed to the problems of the prior art, provide a kind of for aircraft engine supporting structure
Shock loading test device.
In order to achieve the above objectives, the technical solution adopted by the present invention is that:
A kind of shock loading test device for aircraft engine supporting structure, setting use on drop weight test platform, institute
Stating drop weight test platform includes workbench and tup, and test device includes fixing seat for installing supporting structure and for by institute
The force transmission element that the shock loading that tup applies is transmitted on the supporting structure is stated, the fixing seat is arranged in the workbench
On, on the fixing seat, the force transmission element is connect with the supporting structure for the supporting structure setting, the test dress
Set further includes being sticked on the supporting structure for testing the foil gauge for the shock loading that the supporting structure is born.
Preferably, the force transmission element has the stress surface for bearing the shock loading that the tup applies, and the stress surface is
It is parallel to horizontally arranged plane.
Preferably, the force transmission element and the supporting structure are mutually detachably connected.
Further, the force transmission element has the interconnecting piece being connected with the supporting structure, the interconnecting piece and institute
It states between supporting structure using interference fit connection.
Preferably, the force transmission element has the stress surface for bearing the shock loading that the tup applies and ties with the support
The interconnecting piece that component is connected, the stress surface are located at the top of the interconnecting piece.
Preferably, the foil gauge is sticked at the position that the supporting structure wall thickness is thinned.
Further, the foil gauge is provided with multiple, and multiple foil gauges are along the circumference side of the supporting structure
It is arranged to interval, the upper and lower part on the circumferencial direction of at least described supporting structure and the falling direction phase with the tup
Being sticked respectively on parallel direction has the foil gauge.
Preferably, the test device further includes that test is passed for testing the acceleration of the acceleration of the tup in the process
The displacement test system of the displacement of sensor and the test tup.
Preferably, it is arranged on the workbench to the fixing seat position adjustable.
The present invention also provides a kind of shock loading test methods for aircraft engine supporting structure, using such as above-mentioned
Described in any item test devices are tested, and the test method includes:
(1) the support structure part is mounted in the test device, and the test device is installed on the workbench；
(2) tup, which is fallen, applies shock loading to the force transmission element；
(3) force transmission element is transmitted to the shock loading that the tup applies on the supporting structure, passes through the strain
Piece obtains the shock loading that the supporting structure is born.
Due to the application of the above technical scheme, compared with the prior art, the invention has the following advantages: of the invention is used for
The shock loading test device structure of aircraft engine supporting structure is simple, and manufacturing cost is low, safe and reliable, it can be achieved that support
Dynamic test of the structural member under different impact energys, and the shock loading that supporting structure is born in test can be obtained,
To obtain dynamic characteristics and destruction of the supporting structure under different operating conditions.
Detailed description of the invention
Attached drawing 1 is the perspective view of the shock loading test device for aircraft engine supporting structure of the invention；
Attached drawing 2 is the front view of the shock loading test device for aircraft engine supporting structure of the invention；
Attached drawing 3 is the left view of the shock loading test device for aircraft engine supporting structure of the invention；
Attached drawing 4 is the top view of the shock loading test device for aircraft engine supporting structure of the invention；
Attached drawing 5 is the perspective view of fixing seat of the invention；
Attached drawing 6 is the perspective view of force transmission element of the invention；
Attached drawing 7 is the left view of force transmission element of the invention；
Attached drawing 8 is the structural schematic diagram of the position that is sticked of foil gauge of the invention.
Specific embodiment
The technical solution of the present invention will be further described below with reference to the accompanying drawings.
Shock loading test device for aircraft engine supporting structure of the invention makes with the cooperation of drop weight test platform
With drop weight test platform includes workbench (not shown) and tup (not shown).It is of the invention as shown in Fig. 1 ~ Fig. 4
Test device includes fixing seat 1 and force transmission element 2, and fixing seat 1 is installed on the workbench, and the tested setting of supporting structure 3 exists
In fixing seat 1, force transmission element 2 is connect with supporting structure 3, and force transmission element 2 is used to bear the shock loading of tup application, and by tup
The shock loading of application is transmitted on supporting structure 3.
As shown in figure 5, fixing seat 1 includes bottom plate 11 and the vertical plate 12 being arranged perpendicular to bottom plate 11, bottom plate 11 and workbench
Connection, supporting structure 3 is bolted on vertical plate 12, for the rigidity for improving fixing seat 1, in the opposite sides of vertical plate 12
It is also respectively provided with reinforcing rib 13.
It is arranged on the table to 1 position adjustable of fixing seat, can needs to adjust the position of test device according to test in this way,
To facilitate test, so that the applicability of the test device is wider.
Specifically, multiple slotted hole 11a are provided on bottom plate 11, the connection bolt for connecting bottom board 11 and workbench can
Slidably it is arranged in slotted hole 11a, to adjust the position of fixing seat 1 on the table.
As shown in Figure 6 and Figure 7, force transmission element 2 has the stress surface 21 for bearing the shock loading that tup applies and ties with support
The interconnecting piece 22 that component 3 is connected, in the present embodiment, stress surface 21 is located at the top of interconnecting piece 22.
Stress surface 21 preferably using horizontally arranged plane is parallel to, i.e., the shock loading that is applied of tup perpendicular to
The stress surface 21, in this way, farthest the shock loading that tup applies can be transmitted on supporting structure 3.Certainly, may be used
By according to test demand using the stress surface 21 in the form of other structures, such as spherical surface.
Interconnecting piece 22 and supporting structure 3 are mutually detachably connected, and in the present embodiment, interconnecting piece 22 is cylindrical, with
Using interference fit connection between supporting structure 3, and the length at position that is matched with supporting structure 3 of interconnecting piece 22 compared with
It is small, magnitude of interference and length of fit between the two need to meet force transmission element 2 bear tup shock loading after can be with supporting structure 3
The mutually requirement of separation.In this way, force transmission element 2 can be with supporting structure 3 after force transmission element 2 bears the shock loading of a tup
It mutually separates and is fallen from supporting structure 3, force transmission element 2 is impacted again after can avoid tup rebound in this way, to make
It is used to support on structural member 3, so that supporting structure 3 bears secondary pulse, and then influences test result.
The test device further includes being sticked to carry on supporting structure 3 for testing the impact that supporting structure 3 is born
The foil gauge 4 of lotus, foil gauge 4 is preferably sticked at the position that 3 wall thickness of supporting structure is thinned, in this way, can more directly obtain
Obtain dynamic characteristics and destruction of the supporting structure 3 under different operating conditions.
For improve test accuracy, foil gauge 4 be sticked along the circumferencial direction of supporting structure 3 have it is multiple, it is preferable that at least
It is sticked respectively on the upper and lower part on the circumferencial direction of supporting structure 3 and the direction parallel with the falling direction of tup
There is foil gauge 4.In the present embodiment, foil gauge 4, which is sticked, eight, and eight foil gauges 4 are uniform along the circumferencial direction of supporting structure 3
Distribution, as shown in Figure 8.
Test device further includes test in the process for testing the acceleration transducer and test tup of the acceleration of tup
Displacement displacement test system, acceleration transducer and displacement test system be arranged on the rack of drop weight test platform, this
In embodiment, displacement test system uses the non-contact analysis of test system of DIC, the position of tup during can accurately being tested
Shifting amount.
The test method tested by the shock loading that the test device bears supporting structure 3 is as follows:
(1) after connecting supporting mechanism part 3 with force transmission element 2, supporting structure 3 is connected in fixing seat 1, then by fixing seat
1 is installed on the workbench；
(2) measurement condition is set, falls tup from certain altitude according to the requirement under current working, directly to force transmission element 2
Stress surface 21 applies shock loading；
(3) shock loading is transmitted on supporting structure 3 by force transmission element 2, to achieve the purpose that dynamic impact test.
Pass through acceleration transducer, the available tup acceleration of the non-contact analysis of test system of DIC, punching during test
Hit displacement and deflection information.Meanwhile it can measure during test by eight foil gauges 4 pasted on supporting structure 3
Strain information after absorbing impact load to supporting structure 3, and by Mathematical Method, the structural member that is supported can be fitted
3 shock loadings born.
To sum up, test device of the invention can be used cooperatively, it can be achieved that dynamic under different impact energys from drop weight test platform
State test；By reasonably designing the matching relationship between force transmission element and supporting structure, test process can be effectively avoided
In to the secondary pulse of supporting structure；The test device can also accurately obtain test during tup acceleration, displacement
The shock loading born with deflection signal and the structural member that can be supported by foil gauge signal analytical calculation；And it should
Test device structure is simple, and manufacturing cost is low, securely and reliably.
The above embodiments merely illustrate the technical concept and features of the present invention, and its object is to allow person skilled in the art
Scholar can understand the contents of the present invention and be implemented, and it is not intended to limit the scope of the present invention, it is all according to the present invention
Equivalent change or modification made by Spirit Essence, should be covered by the scope of protection of the present invention.
Claims (10)
1. a kind of shock loading test device for aircraft engine supporting structure, it is characterised in that: setting is in examination of dropping hammer
It tests on platform and uses, the drop weight test platform includes workbench and tup, and test device includes for installing consolidating for supporting structure
Reservation and shock loading for applying the tup are transmitted to the force transmission element on the supporting structure, and the fixing seat is set
It sets on the workbench, the supporting structure is arranged on the fixing seat, the force transmission element and the supporting structure
Connection, the test device further include being sticked to rush on the supporting structure for test that the supporting structure born
Hit the foil gauge of load.
2. the shock loading test device according to claim 1 for aircraft engine supporting structure, feature exist
In: the force transmission element has the stress surface for bearing the shock loading that the tup applies, and the stress surface is to be parallel to level side
To the plane of setting.
3. the shock loading test device according to claim 1 for aircraft engine supporting structure, feature exist
In: the force transmission element and the supporting structure are mutually detachably connected.
4. the shock loading test device according to claim 3 for aircraft engine supporting structure, feature exist
There is the interconnecting piece being connected with the supporting structure in: the force transmission element, the interconnecting piece and the supporting structure it
Between using interference fit connection.
5. the shock loading test device according to claim 1 for aircraft engine supporting structure, feature exist
In: what the force transmission element was connected with the stress surface for bearing the shock loading that the tup applies and with the supporting structure
Interconnecting piece, the stress surface are located at the top of the interconnecting piece.
6. the shock loading test device according to claim 1 for aircraft engine supporting structure, feature exist
In: the foil gauge is sticked at the position that the supporting structure wall thickness is thinned.
7. the shock loading test device according to claim 6 for aircraft engine supporting structure, feature exist
It is provided in: the foil gauge multiple, multiple foil gauges are arranged along the circumferencial direction interval of the supporting structure, at least
On upper and lower part on the circumferencial direction of the supporting structure and the direction parallel with the falling direction of the tup point
Not being sticked has the foil gauge.
8. the shock loading test device according to claim 1 for aircraft engine supporting structure, feature exist
In: the test device further includes test in the process for testing acceleration transducer and the test institute of the acceleration of the tup
State the displacement test system of the displacement of tup.
9. the shock loading test device according to claim 1 for aircraft engine supporting structure, feature exist
In: it is arranged on the workbench to the fixing seat position adjustable.
10. a kind of shock loading test method for aircraft engine supporting structure, it is characterised in that: wanted using such as right
Test device described in asking any one of 1 ~ 9 is tested, and the test method includes:
(1) the support structure part is mounted in the test device, and the test device is installed on the workbench；
(2) tup, which is fallen, applies shock loading to the force transmission element；
(3) force transmission element is transmitted to the shock loading that the tup applies on the supporting structure, passes through the strain
Piece obtains the shock loading that the supporting structure is born.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910383002.6A CN110018066B (en) | 2019-05-09 | 2019-05-09 | Impact load testing device and method for aircraft engine supporting structural member |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910383002.6A CN110018066B (en) | 2019-05-09 | 2019-05-09 | Impact load testing device and method for aircraft engine supporting structural member |
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| Publication Number | Publication Date |
|---|---|
| CN110018066A true CN110018066A (en) | 2019-07-16 |
| CN110018066B CN110018066B (en) | 2024-06-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910383002.6A Active CN110018066B (en) | 2019-05-09 | 2019-05-09 | Impact load testing device and method for aircraft engine supporting structural member |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118090118A (en) * | 2024-04-28 | 2024-05-28 | 太仓点石航空动力有限公司 | Impact load testing device and method for aero-engine supporting structural member |
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2019
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118090118A (en) * | 2024-04-28 | 2024-05-28 | 太仓点石航空动力有限公司 | Impact load testing device and method for aero-engine supporting structural member |
| CN118090118B (en) * | 2024-04-28 | 2024-07-02 | 太仓点石航空动力有限公司 | Impact load testing device and method for aero-engine supporting structural member |
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| Publication number | Publication date |
|---|---|
| CN110018066B (en) | 2024-06-11 |
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