CN100567936C - Aviation control soft shaft integrated test stand - Google Patents
Aviation control soft shaft integrated test stand Download PDFInfo
- Publication number
- CN100567936C CN100567936C CNB2008101006283A CN200810100628A CN100567936C CN 100567936 C CN100567936 C CN 100567936C CN B2008101006283 A CNB2008101006283 A CN B2008101006283A CN 200810100628 A CN200810100628 A CN 200810100628A CN 100567936 C CN100567936 C CN 100567936C
- Authority
- CN
- China
- Prior art keywords
- working gantry
- assembly
- aviation control
- control soft
- soft shaft
- Prior art date
- 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 - Fee Related
Links
Images
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention relates to a kind of aviation control soft shaft integrated test stand, be used for long aviation control soft shaft fatigue, efficient, move detection and test sliding, stroke push-and-pull power.Comprise: middle Working gantry assembly (5), left Working gantry (14), right Working gantry (12), peak value keep instrument (1), toggle (8), cartridge type tension-compression sensor (3), operating slide guideway rail assembly (11) and hydraulic jack (10) or handwheel screw-nut body (15).Middle Working gantry assembly (5) constitutes by some joint Working gantries are end to end, peak value keeps instrument (1) and cartridge type tension-compression sensor (3) device on left and right Working gantry, toggle (8) is installed on the left Working gantry (14), operating slide guideway rail assembly (11) is installed on the right Working gantry (12), and described hydraulic jack (10) or handwheel screw-nut body (15) are installed on the operating slide guideway rail assembly (11).The present invention can finish fatigue, efficient, move detection and test sliding, stroke push-and-pull power on an equipment.
Description
Technical field
The present invention 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 present invention 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 objective of the invention is to overcome above-mentioned deficiency, provide a kind of and can on an equipment, finish fatigue, efficient, move cunning, the detection of stroke push-and-pull power and the aviation control soft shaft integrated test stand of test.
The object of the present invention is achieved like this: 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 present invention has following characteristics:
1, testing table of the present invention 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 present invention 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
Fig. 1 is the aviation control soft shaft integrated test stand embodiment one Facad structure synoptic diagram that the present invention relates to.
Fig. 2 is the vertical view of Fig. 1.
Fig. 3 is the aviation control soft shaft integrated test stand embodiment two Facad structure synoptic diagram that the present invention relates to.
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 present invention 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, a kind of 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 |
|---|---|---|---|
| CNB2008101006283A CN100567936C (en) | 2008-05-08 | 2008-05-08 | Aviation control soft shaft integrated test stand |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2008101006283A CN100567936C (en) | 2008-05-08 | 2008-05-08 | Aviation control soft shaft integrated test stand |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101334336A CN101334336A (en) | 2008-12-31 |
| CN100567936C true CN100567936C (en) | 2009-12-09 |
Family
ID=40197080
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2008101006283A Expired - Fee Related CN100567936C (en) | 2008-05-08 | 2008-05-08 | Aviation control soft shaft integrated test stand |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100567936C (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104568407B (en) * | 2014-12-31 | 2017-03-29 | 柳州市金元机械制造有限公司 | A kind of flexible axle integration test experimental bench |
| CN106706300A (en) * | 2017-01-18 | 2017-05-24 | 珠海中航艾维检测技术有限公司 | Push-and-pull steel cable measuring equipment |
| CN112798236A (en) * | 2019-10-28 | 2021-05-14 | 南通深南电路有限公司 | Clamp test system and clamp test method |
| CN111456711A (en) * | 2020-05-06 | 2020-07-28 | 中国石油天然气集团有限公司 | Azimuth gamma test platform |
| CN113702034B (en) * | 2021-08-30 | 2023-10-20 | 辽宁通用航空研究院 | Push-pull steel cable fatigue test device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6694812B2 (en) * | 2001-04-12 | 2004-02-24 | Schenck Rotec Corporation | Rotatable shaft balancing machine and method with automatic flexible shaft balancing equipment |
| CN1603811A (en) * | 2004-10-28 | 2005-04-06 | 上海交通大学 | Detection device for residual fatigue life of automobile obsolete crankshaft |
| US6954685B2 (en) * | 2002-04-23 | 2005-10-11 | Lord Corporation | Aircraft vehicular propulsion system monitoring device and method |
| CN2876754Y (en) * | 2006-03-17 | 2007-03-07 | 燕山大学 | Internal oscillation type fatique tester for joint bearing of automatic clinometer of helicopter rotary swing |
| CN2913182Y (en) * | 2006-06-02 | 2007-06-20 | 江西洪都航空工业集团有限责任公司 | Flexible shaft driving device of airplane trailing edge flap control system |
| CN201193982Y (en) * | 2008-05-08 | 2009-02-11 | 苏钧杰 | Aviation operating soft shaft synthetic experimental bench |
-
2008
- 2008-05-08 CN CNB2008101006283A patent/CN100567936C/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6694812B2 (en) * | 2001-04-12 | 2004-02-24 | Schenck Rotec Corporation | Rotatable shaft balancing machine and method with automatic flexible shaft balancing equipment |
| US6954685B2 (en) * | 2002-04-23 | 2005-10-11 | Lord Corporation | Aircraft vehicular propulsion system monitoring device and method |
| CN1603811A (en) * | 2004-10-28 | 2005-04-06 | 上海交通大学 | Detection device for residual fatigue life of automobile obsolete crankshaft |
| CN2876754Y (en) * | 2006-03-17 | 2007-03-07 | 燕山大学 | Internal oscillation type fatique tester for joint bearing of automatic clinometer of helicopter rotary swing |
| CN2913182Y (en) * | 2006-06-02 | 2007-06-20 | 江西洪都航空工业集团有限责任公司 | Flexible shaft driving device of airplane trailing edge flap control system |
| CN201193982Y (en) * | 2008-05-08 | 2009-02-11 | 苏钧杰 | Aviation operating soft shaft synthetic experimental bench |
Non-Patent Citations (2)
| Title |
|---|
| 软轴疲劳断裂原因分析及改进措施. 黄国钦.航空精密制造技术，第30卷第3期. 1994 |
| 软轴疲劳断裂原因分析及改进措施. 黄国钦.航空精密制造技术，第30卷第3期. 1994 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101334336A (en) | 2008-12-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100567936C (en) | Aviation control soft shaft integrated test stand | |
| CN201974359U (en) | End-surface twisting friction-wear testing machine | |
| CN204255765U (en) | A kind of load test device of structural member otic placode | |
| CN107202739A (en) | Sliding rolling test device and friction wear testing machine for friction wear testing machine | |
| CN104122087A (en) | Ball screw performance experiment table driven by linear motor | |
| CN209589707U (en) | For testing the testing machine of pulling force and pressure | |
| CN102692319A (en) | Passive follow-up force-applied linear guiderail pair test bed with controllable load | |
| CN106053114A (en) | Simulation testing platform for traction force and braking force of elevator traction machine | |
| CN205981945U (en) | Normal position indentation mechanical testing device based on under biaxial stretching load | |
| CN203672620U (en) | Ball screw assembly reliability testing device | |
| CN201193982Y (en) | Aviation operating soft shaft synthetic experimental bench | |
| CN104296979B (en) | A kind of synthetical restraint friction test device and method | |
| CN101788382B (en) | Ball screw pair experiment table | |
| CN202676449U (en) | Load controllable passive type servo-actuated force application linear guide rail pair test device | |
| CN202330039U (en) | Locomotive wheelset running test device | |
| CN205175828U (en) | Tensile testing machine | |
| CN202049086U (en) | Tension and compression testing machine for construction thermal insulation materials | |
| CN104777001A (en) | Vertical cylinder liner piston ring friction-wear test device | |
| CN204269362U (en) | The pneumatically loading ball screw assembly, dynamic efficiency testing table of interchangeable leading screw | |
| CN204944857U (en) | A kind of wheel track fault detect testing table | |
| CN104634490A (en) | Three-axis adjustable combined type dynamometer loading and driving device | |
| CN210981782U (en) | Sliding bearing test bed for applying random regular variable load | |
| CN201903487U (en) | Variable-load bending fatigue testing machine for steel rope | |
| CN204101702U (en) | Platypelloid type linear electric motors continuous service testing table | |
| CN207556728U (en) | A kind of multidirectional tension tester |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20091209 Termination date: 20140508 |