CN111982724B - Aircraft floor fatigue reliability testing device - Google Patents
Aircraft floor fatigue reliability testing device Download PDFInfo
- Publication number
- CN111982724B CN111982724B CN202010922496.3A CN202010922496A CN111982724B CN 111982724 B CN111982724 B CN 111982724B CN 202010922496 A CN202010922496 A CN 202010922496A CN 111982724 B CN111982724 B CN 111982724B
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- transmission
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- aircraft floor
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- 238000012360 testing method Methods 0.000 title claims abstract description 20
- 238000005096 rolling process Methods 0.000 claims abstract description 5
- 230000005540 biological transmission Effects 0.000 claims description 42
- 239000003638 chemical reducing agent Substances 0.000 claims description 9
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- 238000009661 fatigue test Methods 0.000 description 2
- 238000006563 Carroll rearrangement reaction Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
Classifications
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- 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
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
- G01N3/38—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces generated by electromagnetic means
-
- 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
- G01N3/02—Details
-
- 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
- G01N2203/0005—Repeated or cyclic
-
- 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
- G01N2203/005—Electromagnetic means
-
- 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
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
-
- 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
- G01N2203/026—Specifications of the specimen
- G01N2203/0262—Shape of the specimen
- G01N2203/0278—Thin specimens
- G01N2203/0282—Two dimensional, e.g. tapes, webs, sheets, strips, disks or membranes
-
- 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
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0682—Spatial dimension, e.g. length, area, angle
-
- 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
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0688—Time or frequency
Landscapes
- 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)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Electromagnetism (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The application relates to a device for testing fatigue reliability of an aircraft floor, in order to solve the problem that loading and position adjustment cannot be realized for rolling durable equipment of the aircraft floor in China at present, the device comprises a platform, an adjusting frame and a loading mechanism, wherein the loading mechanism is slidably connected and installed on the adjusting frame, and the adjusting frame is fixedly installed on the platform.
Description
Technical Field
The invention relates to a floor fatigue testing device, in particular to an aircraft floor fatigue reliability testing device which is used for fatigue testing of civil aircraft interior trim parts.
Background
Under the condition that the dining car rolls for a long time, the civil aviation aircraft floor can cause damage of different degrees, and the structural design of the aviation floor supporting frame and the selection of floor materials need to be accurately evaluated and detected in the early stage of design and development. Thus, there is a need for a practical test tool to directly reflect the load-bearing capacity of an aircraft floor, thereby detecting the quality of the floor. At present, domestic floor rolling endurance equipment cannot realize loading and position adjustment, and cannot accurately evaluate the quality of the floor endurance.
Disclosure of Invention
The invention aims to solve the problem that loading and position adjustment cannot be realized for the rolling durable equipment of the aircraft floor in China at present, and further provides an aircraft floor fatigue reliability testing device.
The technical scheme adopted for solving the technical problems is as follows:
the device comprises a platform, an adjusting frame and a loading mechanism, wherein the loading mechanism is installed on the adjusting frame in a sliding connection mode, and the adjusting frame is fixedly installed on the platform.
Compared with the prior art, the invention has the following beneficial effects:
1. According to the invention, the position of the connecting plate 3-1 on the beam assembly 2-1 is adjusted, so that the loading mechanism 3 is transversely adjusted on the beam assembly 2-1, the motor reducer 3-4 of the loading mechanism 3 rotates to drive the plurality of roller assemblies 3-9 to adjust tracks, the adjustment of different tracks of the dining car is realized, the number of loading weights is adjusted, the simulation of the weight of different dining cars is realized, the simulation of actual working conditions is completed, and further the accurate and efficient detection is realized.
2. According to the invention, the driving assembly 2-6 is controlled by the external control mechanism to drive the beam assembly 2-1 to adjust the height, and the simulation operation precision is high, the stability is good, and a more reliable basis is provided for evaluating the rolling loading endurance quality of the aviation floor.
3. The invention is suitable for detecting the durability of the aviation aircraft floor. The external probe sensor is arranged between the adjusting connecting plate 3-1 and the roller groups 3-9, so that the floor friction dent can be effectively measured, and the curve and data of the tolerance times and the friction dent can be realized by combining with the technical counting function of the control system, thereby providing reliable basis for the durability analysis of the product and being convenient for the product evaluation, development and improvement.
Drawings
FIG. 1 is a front elevational view of the overall structure of the present invention;
fig. 2 is a front view of the adjusting frame 2 of the present invention.
Fig. 3 is a view in the direction A-A of fig. 2.
FIG. 4 is a schematic illustration of the connection plate 3-1 sliding over the beam assembly 2-1 via a plurality of slides 3-3.
Fig. 5 is a front view of the loading mechanism 3.
Fig. 6 is a schematic view of the loading mechanism 3.
Detailed Description
The first embodiment is as follows: referring to fig. 1 to 6, an embodiment of an apparatus for testing fatigue reliability of an aircraft floor according to the present embodiment includes a platform 1, an adjusting frame 2, and a loading mechanism 3, wherein the loading mechanism 3 is slidably mounted on the adjusting frame 2, and the adjusting frame 2 is fixedly mounted on the platform 1.
The second embodiment is as follows: 1-3, the adjusting frame 2 comprises a beam component 2-1, a column component 2-2, a limiting component 2-3, a transmission frame 2-4, a transmission component 2-5 and a driving component 2-6; the beam assembly 2-1, the limiting assembly 2-3, the transmission frame 2-4, the transmission assembly 2-5 and the driving assembly 2-6 are arranged on the upright post assembly 2-2, and the driving assembly 2-6 is in transmission connection with the beam assembly 2-1 through the transmission assembly 2-5. The composition and connection are the same as in the first embodiment.
And a third specific embodiment: 1-3, the upright post assembly 2-2 comprises a top connecting frame, two groups of double guide posts 2-21 and two bottom fixing plates 2-22; the two groups of double guide posts 2-21 are symmetrically arranged below the top connecting frame, the top of each group of double guide posts 2-21 is fixedly connected with the top connecting frame, the bottom of each group of double guide posts 2-21 is arranged on the platform 1 through a bottom fixing plate 2-22, and two ends of the beam assembly 2-1 are arranged on the two groups of double guide posts 2-21 in a sliding manner through the transmission assembly 2-5. The composition and the connection mode are the same as those of the second embodiment.
The specific embodiment IV is as follows: referring to fig. 1-3, the embodiment of the device for testing fatigue reliability of an aircraft floor according to the embodiment is described, wherein the limit component 2-3 includes a plurality of limit switches, two limit switches are installed on each of the two guide posts 2-21 from top to bottom, the limit switches on the upper part of the guide post are correspondingly arranged along the same height, and the limit switches on the bottom of the guide post are correspondingly arranged along the same height. The composition and the connection mode are the same as those of the second embodiment.
Fifth embodiment: referring to fig. 1-3, a description is given of the present embodiment of an aircraft floor fatigue reliability testing device, the transmission assembly 2-5 includes two transmission shafts 2-51, two diverters 2-52, two transmission screws 2-53, two lifting blocks 2-54, two nuts and a plurality of bearing fixing seats with bearings, the driving assembly 2-6 is a dual-shaft gear motor, an output shaft at each end of the driving assembly 2-6 is fixedly connected with one end of one transmission shaft 2-51, the other end of the transmission shaft 2-51 is in transmission connection with one end of one transmission screw 2-53 through the diverters 2-52, each end of the transmission screw 2-53 is rotatably connected with one end of one transmission screw 2-53 through the bearing fixing seat with a bearing, two light holes are machined on the lifting blocks 2-54, the nuts are installed in the middle of the two light holes, each transmission screw 2-53 is in threaded connection with the nuts of one lifting block 2-54, and the two light holes of each lifting block 2-54 are in sliding connection with one group of dual guide posts 2-21. The composition and the connection mode are the same as those of the second embodiment.
Specific embodiment six: referring to fig. 1 to 3, a description will be given of the present embodiment of an aircraft floor fatigue reliability test device, in which a beam assembly 2-1 includes a beam and two slide rails, the beam is mounted on two lifting blocks 2-54, and the two slide rails are mounted in parallel on the lower end face of the beam. The composition and the connection mode are the same as those of the fifth embodiment.
Seventh embodiment: referring to fig. 1, 5 and 6, in this embodiment, a loading mechanism 3 includes a connecting plate 3-1, a clamp 3-2, a motor reducer 3-4, a transmission assembly 3-5, an adapter plate connecting flange 3-7, an adapter plate 3-8, a plurality of sliders 3-3, a plurality of loads 3-6 and a plurality of roller assemblies 3-9, wherein the plurality of roller assemblies 3-9 are uniformly distributed on the adapter plate 3-8 along the circumferential direction, one load 3-6 is mounted on each roller assembly 3-9, the adapter plate 3-8 is fixedly connected with the bottom of the adapter plate connecting flange 3-7, the bottom of the transmission assembly 3-5 is fixedly connected with the top of the adapter plate connecting flange 3-7, the output end of a rotating shaft of the motor reducer 3-4 is fixedly connected with the top of the transmission assembly 3-5, a housing of the motor reducer 3-4 is fixedly connected with the lower end of the connecting plate 3-1, and the clamp 3-2 and the plurality of sliders 3-3 are fixedly mounted on the connecting plate 3-1. The composition and the connection mode are the same as those of the first embodiment.
Eighth embodiment: referring to fig. 4, the present embodiment of an aircraft floor fatigue reliability testing device is described, in which a plurality of sliding blocks 3-3 are symmetrically disposed on two sliding rails in two rows, and a connecting plate 3-1 is slidably connected to two sliding rails of a beam assembly 2-1 through the plurality of sliding blocks 3-3. The composition and the connection mode are the same as those of the sixth or seventh embodiment.
Principle of operation
The application is operated by connecting the adjusting frame 2 and the loading mechanism 3 with an external controller. When in operation, the device comprises: the connecting plate 3-1 is manually pushed to adjust the position of the loading assembly 3, the locking clamp 3-2 is fixed, an instruction is input through an external controller instruction input device, the driving assembly 2-6 in the adjusting frame 2 is driven to adjust the height position of the beam assembly 2-1, the beam assembly 2-1 is driven to be lifted and adjusted, the external controller input device is used for inputting the instruction, the motor reducer 3-4 is driven to drive the load 3-6 and the roller assembly 3-9 to circularly move through the transmission assembly 3-5, the durable floor is rolled, and the durable test is carried out. And adjusting the size of the load according to the stress requirement.
Claims (7)
1. The utility model provides an aircraft floor fatigue reliability testing arrangement, it includes platform (1), adjusting frame (2) and loading mechanism (3), its characterized in that: the loading mechanism (3) comprises a connecting plate (3-1), a clamp (3-2), a motor reducer (3-4), a first transmission component (3-5), an adapter plate connecting flange (3-7), an adapter plate (3-8), a plurality of sliding blocks (3-3), a plurality of loads (3-6) and a plurality of roller components (3-9), wherein the loading mechanism (3) is installed on the adjusting frame (2) in a sliding manner, the adjusting frame (2) is fixedly installed on the platform (1), the plurality of roller components (3-9) are uniformly distributed on the adapter plate (3-8) along the circumferential direction, one load (3-6) is installed on each roller component (3-9), the adapter plate (3-8) is fixedly connected with the bottom of the adapter plate connecting flange (3-7), the bottom of the first transmission component (3-5) is fixedly connected with the top of the adapter plate connecting flange (3-7), the output end of a rotating shaft of the motor reducer (3-4) is fixedly connected with the top of the first transmission component (3-5), the shell of the motor reducer (3-4) is fixedly connected with the bottom of the housing (3-1) of the clamp (3-4) and the connecting plate (3-3) fixedly connected with the connecting plate, the driving motor reducer (3-4) drives the load (3-6) and the roller assembly (3-9) to circularly move through the transmission assembly I (3-5), and the rolling floor is subjected to endurance test.
2. An aircraft floor fatigue reliability test device according to claim 1, wherein: the adjusting frame (2) comprises a beam assembly (2-1), a column assembly (2-2), a limiting assembly (2-3), a transmission frame (2-4), a transmission assembly II (2-5) and a driving assembly (2-6); the beam assembly (2-1), the limiting assembly (2-3), the transmission frame (2-4), the transmission assembly II (2-5) and the driving assembly (2-6) are arranged on the upright post assembly (2-2), and the driving assembly (2-6) is in transmission connection with the beam assembly (2-1) through the transmission assembly II (2-5).
3. An aircraft floor fatigue reliability test device according to claim 2, wherein: the upright post component (2-2) comprises a top connecting frame, two groups of double guide posts (2-21) and two bottom fixing plates (2-22); the two groups of double guide posts (2-21) are symmetrically arranged below the top connecting frame, the top of each group of double guide posts (2-21) is fixedly connected with the top connecting frame, the bottom of each group of double guide posts (2-21) is arranged on the platform (1) through a bottom fixing plate (2-22), and two ends of the beam assembly (2-1) are slidably arranged on the two groups of double guide posts (2-21) through a transmission assembly II (2-5).
4. An aircraft floor fatigue reliability test device according to claim 2, wherein: the limit component (2-3) comprises a plurality of limit switches, two limit switches are arranged on each guide pillar in the double guide pillars (2-21) from top to bottom, the limit switches on the upper parts of the guide pillars are correspondingly arranged along the same height, and the limit switches on the bottoms of the guide pillars are correspondingly arranged along the same height.
5. An aircraft floor fatigue reliability test device according to claim 2, wherein: the second transmission component (2-5) comprises two transmission shafts (2-51), two steering gears (2-52), two transmission lead screws (2-53), two lifting blocks (2-54), two nuts and a plurality of bearing fixing seats with bearings, the driving component (2-6) is a double-shaft speed reducing motor, an output shaft at each end of the driving component (2-6) is fixedly connected with one end of one transmission shaft (2-51) respectively, the other end of the transmission shaft (2-51) is in transmission connection with one end of one transmission lead screw (2-53) through the steering gears (2-52), each end of the transmission lead screw (2-53) is rotatably connected with a bearing fixing seat with a bearing and is arranged on the upright post component (2-2) and the transmission frame (2-4), two unthreaded holes are machined on the lifting blocks (2-54), the nuts are arranged in the middle of the two unthreaded holes, each transmission lead screw (2-53) is in threaded connection with the nut of one lifting block (2-54), and the two unthreaded holes of each lifting block (2-54) are in sliding connection with one group of two guide posts (2-21).
6. The aircraft floor fatigue reliability test device according to claim 5, wherein: the beam assembly (2-1) comprises a beam and two sliding rails, the beam is arranged on two lifting blocks (2-54), and the two sliding rails are arranged on the lower end face of the beam in parallel.
7. The aircraft floor fatigue reliability test device according to claim 6, wherein: the sliding blocks (3-3) are symmetrically arranged on the two sliding rails of the beam assembly (2-1) in two rows, and the connecting plate (3-1) is in sliding connection with the two sliding rails of the beam assembly (2-1) through the sliding blocks (3-3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010922496.3A CN111982724B (en) | 2020-09-04 | 2020-09-04 | Aircraft floor fatigue reliability testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010922496.3A CN111982724B (en) | 2020-09-04 | 2020-09-04 | Aircraft floor fatigue reliability testing device |
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| Publication Number | Publication Date |
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| CN111982724A CN111982724A (en) | 2020-11-24 |
| CN111982724B true CN111982724B (en) | 2024-05-03 |
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| CN202010922496.3A Active CN111982724B (en) | 2020-09-04 | 2020-09-04 | Aircraft floor fatigue reliability testing device |
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Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10260114A (en) * | 1997-03-17 | 1998-09-29 | Railway Technical Res Inst | Rolling-fatigue testing apparatus |
| JP2001289761A (en) * | 2000-04-05 | 2001-10-19 | Mitsubishi Heavy Ind Ltd | Wheel load fatigue testing machine |
| CN101059411A (en) * | 2007-06-06 | 2007-10-24 | 宋立山 | Floor rolling burden functional experiment detector |
| CN202735179U (en) * | 2012-04-17 | 2013-02-13 | 昆山市创新科技检测仪器有限公司 | Device used for detecting abrasion resistance of wooded floor |
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| CN105806630A (en) * | 2016-04-01 | 2016-07-27 | 哈尔滨三迪工控工程有限公司 | Automobile seat vertical loading testing machine |
| CN107235326A (en) * | 2016-12-27 | 2017-10-10 | 山东大学 | A kind of large stone material plate truss-like automatic blanking device and method |
| CN109187192A (en) * | 2018-10-15 | 2019-01-11 | 上海秦耀航空试验技术有限公司 | A kind of airplane floor sled test device and application method |
| CN109374454A (en) * | 2018-12-07 | 2019-02-22 | 武汉理工大学 | Multifunction road pavement material performance testing device and test method |
| CN109752269A (en) * | 2019-01-10 | 2019-05-14 | 刘一楠 | A kind of sport timber floor rolling burden detection device |
| CN209707281U (en) * | 2019-04-10 | 2019-11-29 | 东北林业大学 | Floor board for sports ground shock loading and rolling load comprehensive detector |
| CN210424207U (en) * | 2019-06-19 | 2020-04-28 | 河北领舰科技有限公司 | Floor rolling load tester |
| CN111238783A (en) * | 2020-02-22 | 2020-06-05 | 深圳市守正航空工业有限公司 | Pressure rolling durability testing device for cargo transportation guide roller of cargo airplane floor box |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2017132414A1 (en) * | 2016-01-28 | 2017-08-03 | Coe William B | Rolling cyclic fatigue test platform for determining asphalt ductility |
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2020
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10260114A (en) * | 1997-03-17 | 1998-09-29 | Railway Technical Res Inst | Rolling-fatigue testing apparatus |
| JP2001289761A (en) * | 2000-04-05 | 2001-10-19 | Mitsubishi Heavy Ind Ltd | Wheel load fatigue testing machine |
| CN101059411A (en) * | 2007-06-06 | 2007-10-24 | 宋立山 | Floor rolling burden functional experiment detector |
| CN202735179U (en) * | 2012-04-17 | 2013-02-13 | 昆山市创新科技检测仪器有限公司 | Device used for detecting abrasion resistance of wooded floor |
| CN204939448U (en) * | 2015-09-06 | 2016-01-06 | 山西梁汾醋业有限公司 | Full-automatic cylinder formula turns over unstrained spirits equipment |
| CN105806630A (en) * | 2016-04-01 | 2016-07-27 | 哈尔滨三迪工控工程有限公司 | Automobile seat vertical loading testing machine |
| CN107235326A (en) * | 2016-12-27 | 2017-10-10 | 山东大学 | A kind of large stone material plate truss-like automatic blanking device and method |
| CN109187192A (en) * | 2018-10-15 | 2019-01-11 | 上海秦耀航空试验技术有限公司 | A kind of airplane floor sled test device and application method |
| CN109374454A (en) * | 2018-12-07 | 2019-02-22 | 武汉理工大学 | Multifunction road pavement material performance testing device and test method |
| CN109752269A (en) * | 2019-01-10 | 2019-05-14 | 刘一楠 | A kind of sport timber floor rolling burden detection device |
| CN209707281U (en) * | 2019-04-10 | 2019-11-29 | 东北林业大学 | Floor board for sports ground shock loading and rolling load comprehensive detector |
| CN210424207U (en) * | 2019-06-19 | 2020-04-28 | 河北领舰科技有限公司 | Floor rolling load tester |
| CN111238783A (en) * | 2020-02-22 | 2020-06-05 | 深圳市守正航空工业有限公司 | Pressure rolling durability testing device for cargo transportation guide roller of cargo airplane floor box |
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| CN111982724A (en) | 2020-11-24 |
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