CN201193982Y - Aviation operating soft shaft synthetic experimental bench - Google Patents
Aviation operating soft shaft synthetic experimental bench Download PDFInfo
- Publication number
- CN201193982Y CN201193982Y CNU2008201163311U CN200820116331U CN201193982Y CN 201193982 Y CN201193982 Y CN 201193982Y CN U2008201163311 U CNU2008201163311 U CN U2008201163311U CN 200820116331 U CN200820116331 U CN 200820116331U CN 201193982 Y CN201193982 Y CN 201193982Y
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- CN
- China
- Prior art keywords
- working gantry
- assembly
- soft shaft
- toggle
- rail assembly
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Abstract
The utility model relates to a aviation operated flexible shaft combined test bed used in fatigue, efficiency, slip and stroke push pull force detection and test for major aviation operated flexible shaft. The test bed comprises a middle work bench pedestal assembly (5), a left workbench frame (14), a right workbench frame (12), a peak holding apparatus (1), a crank-link mechanism (8), a solid bowl type pull/push sensor (3), a slide guide rail assembly (11) and a hydraulic ram (10) or hand wheel leading screw nut mechanism (15). The middle work bench pedestal assembly (5) consists of several work bench frames connected end to end; the peak holding apparatus (1) an the solid bowl type pull/push sensor (3) are disposed on the left and right workbench frame respectively; the crank-link mechanism (8) is disposed on the left workbench frame (14); the slide guide rail assembly (11) is disposed on the right workbench frame (12), and the hydraulic ram (10) or hand wheel leading screw nut mechanism (15) is disposed on the slide guide rail assembly (11). The utility model can implement fatigue, efficiency, slip and stroke push pull force detection and test on a same equipment.
Description
Technical field
The utility model relates to a kind of testing table.Be mainly used in long aviation control soft shaft fatigue, efficient, move detection and test sliding, stroke push-and-pull power.Belong to and detecting and the testing equipment technical field.
Background technology
For satisfying the specific (special) requirements of aviation field, aviation control soft shaft must carry out fatigue, efficient, move detection and test sliding, stroke push-and-pull power before dispatching from the factory.Before the utility model was made, general manipulation flexible axle testing table length was about 5M, and totally five machines or testing machine are formed by fatigue tester, load efficiency machines, travel efficiency machines, pulling-out force testing machine and thrust test machine.It mainly has the following disadvantages:
1, the full Performance Detection of push-and-pull flexible axle must be carried out one by one by five equipment, and is time-consuming;
2, five occupation area of equipment are big, the total cost height;
3, separate unit machines or testing machine can only be tested the following flexible axle of 5M, and device length is not enough, can not regulate arbitrarily.
Summary of the invention
The purpose of this utility model is to overcome above-mentioned deficiency, provides a kind of and can finish fatigue, efficient on an equipment, moves cunning, the detection of stroke push-and-pull power and the aviation control soft shaft integrated test stand of test.
The purpose of this utility model is achieved in that a kind of aviation control soft shaft integrated test stand, comprise: middle Working gantry assembly, left Working gantry, right Working gantry, peak value keep instrument, change speed motor, toggle, cartridge type tension-compression sensor, operating slide guideway rail assembly and hydraulic jack or handwheel screw-nut body
The Working gantry assembly constitutes by some joint Working gantries are end to end in the middle of described, the two ends, the left and right sides of Working gantry assembly in the middle of described left Working gantry and right Working gantry are separately positioned on, the bottom of Working gantry assembly, left Working gantry and right Working gantry is provided with universal wheel in the middle of described
Described peak value keeps instrument to have two, about each one, install respectively on left Working gantry and right Working gantry,
Described cartridge type tension-compression sensor has two, about each one, be installed on respectively on left Working gantry and the right Working gantry, place the side of aviation control soft shaft to be tested,
Described change speed motor and toggle all are installed on the left Working gantry, and the change speed motor output terminal links to each other with the toggle head end, and the tail end of toggle links to each other with left end with aviation control soft shaft to be tested by left frock clamp assembly,
Described operating slide guideway rail assembly apparatus is on right Working gantry, described hydraulic jack or handwheel screw-nut body are installed on the operating slide guideway rail assembly, and hydraulic jack or handwheel screw-nut body link to each other with right-hand member with aviation control soft shaft to be tested by right frock clamp assembly.
Compare with the existing flexible axle testing table of handling, the utlity model has following characteristics:
1, the utility model testing table is made up of some joint stands, can be according to aviation control soft shaft length, and free splicing testing table length is to satisfy the performance test of all size length aviation control soft shaft.
2, the utility model can be used for simultaneously aviation control soft shaft fatigue, efficient, move detection and test sliding, stroke push-and-pull power, occupation area of equipment is little, total cost is low.
3, the peak value that is installed on the testing table keeps instrument can effectively write down various data in the short time.
4, testing table adopts hydraulic load mechanism and the negative tool mechanism of machinery principle of combining, and structure is more advanced more reasonable.
5, increase a high-low temperature test chamber again, can handle the thermocycling of flexible axle continuously.
Description of drawings
The aviation control soft shaft integrated test stand embodiment one Facad structure synoptic diagram that Fig. 1 relates to for the utility model.
Fig. 2 is the vertical view of Fig. 1.
The aviation control soft shaft integrated test stand embodiment two Facad structure synoptic diagram that Fig. 3 relates to for the utility model.
Among the figure: peak value keeps instrument 1, electric box 2, cartridge type tension-compression sensor 3, left frock clamp assembly 4, middle Working gantry assembly 5, change speed motor 6, universal wheel 7, toggle 8, right frock clamp assembly 9, hydraulic jack 10, operating slide guideway rail assembly 11, right Working gantry 12, hydraulic power unit 13, left Working gantry 14, handwheel screw-nut body 15.
Embodiment
Embodiment one:
Referring to Fig. 1～2, the aviation control soft shaft integrated test stand that the utility model relates to mainly keeps instrument 1, change speed motor 6, toggle 8, cartridge type tension-compression sensor 3, hydraulic jack 10 and operating slide guideway rail assembly 11 to form by middle Working gantry assembly 5, left Working gantry 14, right Working gantry 12, universal wheel 7, peak value.
Working gantry assembly 5 constitutes by some joint Working gantries are end to end in the middle of described.The two ends, the left and right sides of Working gantry assembly 5 in the middle of described left Working gantry 14 and right Working gantry 12 are separately positioned on.Universal wheel 7 is arranged at the bottom of described middle Working gantry assembly 5, left Working gantry 14 and right Working gantry 12 all device.Described peak value keeps instrument 1 to have two, about each one, install respectively on left Working gantry 14 and right Working gantry 12, described change speed motor 6 and toggle 8 all are installed on the left Working gantry 14, and change speed motor 6 output terminals link to each other with toggle 8 head ends.Described cartridge type tension-compression sensor 3 has two, about each one, be installed on respectively on left Working gantry 14 and the right Working gantry 12, and place the side of aviation control soft shaft to be tested.Described hydraulic jack 10 and operating slide guideway rail assembly 11 are installed on the right Working gantry 12, and the cylinder body of hydraulic jack 10 links to each other with operating slide guideway rail assembly 11.
During test, the left end of aviation control soft shaft to be tested tail end by the toggle 8 on left frock clamp assembly 4 and the right Working gantry 12 is linked to each other, and the piston rod that the right-hand member of aviation control soft shaft to be tested is passed through the hydraulic jack 10 on right frock clamp assembly 9 and the left Working gantry 14 links to each other and gets final product.
Embodiment two:
The difference of present embodiment and embodiment one is hydraulic jack 10 is replaced to handwheel screw-nut body 15, handwheel screw-nut body 15 is installed on the operating slide guideway rail assembly 11, the right-hand member of aviation control soft shaft to be tested is linked to each other with described handwheel screw-nut body 15 by right frock clamp assembly 9, as Fig. 3.
Claims (1)
1. aviation control soft shaft integrated test stand, it is characterized in that described testing table comprises: middle Working gantry assembly (5), left Working gantry (14), right Working gantry (12), peak value keep instrument (1), change speed motor (6), toggle (8), cartridge type tension-compression sensor (3), operating slide guideway rail assembly (11) and hydraulic jack (10) or handwheel screw-nut body (15)
Working gantry assembly (5) constitutes by some joint Working gantries are end to end in the middle of described, the two ends, the left and right sides of Working gantry assembly (5) in the middle of described left Working gantry (14) and right Working gantry (12) are separately positioned on, the bottom of Working gantry assembly (5), left Working gantry (14) and right Working gantry (12) is provided with universal wheel (7) in the middle of described
Described peak value keeps instrument (1) to have two, about each one, install respectively on left Working gantry (14) and right Working gantry (12),
Described cartridge type tension-compression sensor (3) has two, about each one, be installed on respectively on left Working gantry (14) and the right Working gantry (12), place the side of aviation control soft shaft to be tested,
Described change speed motor (6) and toggle (8) all are installed on the left Working gantry (14), change speed motor (6) output terminal links to each other with toggle (8) head end, the tail end of toggle (8) links to each other with left end with aviation control soft shaft to be tested by left frock clamp assembly (4)
Described operating slide guideway rail assembly (11) is installed on the right Working gantry (12), described hydraulic jack (10) or handwheel screw-nut body (15) are installed on the operating slide guideway rail assembly (11), and hydraulic jack (10) or handwheel screw-nut body (15) link to each other with right-hand member with aviation control soft shaft to be tested by right frock clamp assembly (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008201163311U CN201193982Y (en) | 2008-05-08 | 2008-05-08 | Aviation operating soft shaft synthetic experimental bench |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008201163311U CN201193982Y (en) | 2008-05-08 | 2008-05-08 | Aviation operating soft shaft synthetic experimental bench |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201193982Y true CN201193982Y (en) | 2009-02-11 |
Family
ID=40393516
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2008201163311U Expired - Lifetime CN201193982Y (en) | 2008-05-08 | 2008-05-08 | Aviation operating soft shaft synthetic experimental bench |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201193982Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100567936C (en) * | 2008-05-08 | 2009-12-09 | 苏钧杰 | Aviation control soft shaft integrated test stand |
| CN104374507A (en) * | 2014-11-14 | 2015-02-25 | 苏州迈创信息技术有限公司 | Automobile flexible shaft test system |
-
2008
- 2008-05-08 CN CNU2008201163311U patent/CN201193982Y/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100567936C (en) * | 2008-05-08 | 2009-12-09 | 苏钧杰 | Aviation control soft shaft integrated test stand |
| CN104374507A (en) * | 2014-11-14 | 2015-02-25 | 苏州迈创信息技术有限公司 | Automobile flexible shaft test system |
| CN104374507B (en) * | 2014-11-14 | 2017-02-22 | 苏州迈创信息技术有限公司 | Automobile flexible shaft test system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Effective date of abandoning: 20080508 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |