CN104729846A - Automatic inclinator nonrotating ring fatigue test device - Google Patents
Automatic inclinator nonrotating ring fatigue test device Download PDFInfo
- Publication number
- CN104729846A CN104729846A CN201510160862.5A CN201510160862A CN104729846A CN 104729846 A CN104729846 A CN 104729846A CN 201510160862 A CN201510160862 A CN 201510160862A CN 104729846 A CN104729846 A CN 104729846A
- Authority
- CN
- China
- Prior art keywords
- rotating ring
- non rotating
- actuator
- ring
- test
- 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.)
- Pending
Links
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention belongs to the technology of helicopter automatic inclinator nonrotating ring fatigue tests and relates to an automatic inclinator nonrotating ring fatigue test device. By means of the device, the fatigue test can be conducted to an automatic inclinator nonrotating ring. The test device comprises an installation device for fixedly installing the nonrotating ring and an actuator loading executing mechanism, and the actuator loading executing mechanism is connected with one of support lugs of the nonrotating ring and used for simulating the operation loading of a helicopter booster and applying the operation loading to the nonrotating ring; by simulating boundary conditions of such aspects of the helicopter immovable ring in installation and loading, the fatigue test is conducted to the automatic inclinator nonrational ring, and through the test verification, the test result is high in accuracy.
Description
Technical field
The invention belongs to helicopter auto-bank unit non rotating ring fatigue test technology, particularly a kind of auto-bank unit non rotating ring fatigue experimental device.
Background technology
Auto-bank unit non rotating ring is load important in helicopter rotor system and drive disk assembly, it can by driver, periodically pitch control and the pitch control of total distance be passed to every sheet blade together with swivel eye, the established angle of periodically-varied each blade, thus manipulation helicopter flies toward all directions.In order to grasp the fatigue behaviour of auto-bank unit non rotating ring, need on ground in the face of non rotating ring carries out torture test, the fatigue properties of grasp non rotating ring, and then evaluate the serviceable life of auto-bank unit non rotating ring.
But, due to non rotating ring fatigue test technology mainly Shortcomings in boundary condition simulation etc., also there is no the test unit that can carry out torture test accordingly to non rotating ring.
Summary of the invention
The present invention will provide a kind of auto-bank unit non rotating ring fatigue experimental device, can carry out torture test to auto-bank unit non rotating ring.
Technical scheme of the present invention:
A kind of auto-bank unit non rotating ring fatigue experimental device, comprising:
Erecting device, for fixedly mounting non rotating ring;
Actuator load topworks, is connected with the journal stirrup of described non rotating ring, for helicopter simulating booster control loads and described control loads is applied to described non rotating ring.
Alternatively, described erecting device comprises:
Test-bed, cylindrically;
Testing table base plate, rounded, be fixedly installed on described test-bed bottom, the axis of described test-bed passes the center of circle of described testing table base plate;
Testing table top board, rounded, be fixedly installed on described test-bed top, the axis of described test-bed passes the center of circle of described testing table top board;
Seat ring, cylindrically, bottom is fixedly connected with described testing table top board, and the axis of described seat ring and the dead in line of described test-bed, described non rotating ring is fixedly installed on described seat ring top.
Alternatively, described seat ring bottom end face offers a coaxial annular recess, and described in described groove, the internal diameter of seat ring equals the diameter of described groove, and the bottom surface of the described seat ring in described groove and the bottom surface of described non rotating ring are positioned at same level;
Be provided with a circular fixed head in described groove, the diameter of described fixed head equals the diameter of described groove, for being connected with described seat ring and described non rotating ring simultaneously.
Alternatively, described actuator load topworks comprises:
Hold-down support;
Actuator, the journal stirrup of one end and described non rotating ring is hinged, and the other end is hinged on described hold-down support.
Alternatively, described actuator is hinged by the journal stirrup of crossover sub assembly and described non rotating ring.
Alternatively, described crossover sub assembly comprises oscillating bearing, and described oscillating bearing is connected with one end away from described hold-down support of described actuator with adapter by the large joint connected successively.
Alternatively, described actuator load topworks also comprises:
Force snesor, is connected with described actuator, for detecting the load that described actuator exports;
Control device, controllably regulates described actuator to the afterburning load of described non rotating circulating application, and judges the size of the load exported according to the data that described force snesor feeds back.
Beneficial effect of the present invention:
Auto-bank unit non rotating ring fatigue experimental device energy accurate simulation helicopter of the present invention not rotating ring at the boundary condition installed and in load etc., to auto-bank unit not rotating ring carry out torture test, through verification experimental verification, test findings accuracy is high.
Accompanying drawing explanation
Fig. 1 is according to structural representation during one embodiment of the invention auto-bank unit non rotating ring fatigue experimental device using state;
Fig. 2 is the cut-open view according to one embodiment of the invention seat ring and non rotating ring coupling part;
Fig. 3 is according to one embodiment of the invention crossover sub assembly and non rotating ring coupling part schematic diagram;
Fig. 4 is according to one embodiment of the invention oscillating bearing and large joint connection diagram.
Embodiment
Below in conjunction with accompanying drawing, auto-bank unit non rotating ring fatigue experimental device involved in the present invention is described in further details.
As shown in Figure 1 to Figure 2, a kind of auto-bank unit non rotating ring fatigue experimental device of the present invention, can comprise erecting device and actuator load topworks.
Wherein, erecting device for fixedly mounting non rotating ring 1, to simulate the solid form of non rotating ring 1 on helicopter.
(non rotating ring 1 generally includes 3 journal stirrups to the journal stirrup of actuator load topworks and non rotating ring 1, can select wherein any one) connect, for simulating the control loads of helicopter booster in practical flight and control loads being applied to non rotating ring 1.
Auto-bank unit non rotating ring fatigue experimental device energy accurate simulation helicopter of the present invention not rotating ring at the boundary condition installed and in load etc., to auto-bank unit not rotating ring carry out torture test, through verification experimental verification, test findings accuracy is high.
Erecting device can be multiple applicable planform, can comprise test-bed 2, testing table base plate 3, testing table top board 4 and seat ring 5 in the present embodiment.
Cylindrically, stability is strong for test-bed 2.Testing table base plate 3 is rounded, is fixedly installed on test-bed 2 bottom, and the axis of test-bed 2 passes the center of circle of testing table base plate 3.Testing table top board 4 is rounded, is fixedly installed on test-bed 2 top, and the axis of test-bed 2 passes the center of circle of testing table top board 4.
Also cylindrically, bottom is fixedly connected with testing table top board 4 seat ring 5, the axis of seat ring 5 and the dead in line of test-bed 2, has the outer toroid that to match with annulus in seat ring 5 top, thus be fixedly installed on seat ring 5 top bottom non rotating ring 1.
Further, offer a coaxial annular recess at seat ring 5 bottom end face, the internal diameter of groove seat ring 5 equals the diameter of groove, and the bottom surface of the seat ring 5 in groove and the bottom surface of non rotating ring 1 are positioned at same level.Be provided with a circular fixed head 6 in groove, the diameter of fixed head 6 equals the diameter of groove.Concrete with reference to shown in Fig. 2, by modes such as bolts, fixed head 6 and seat ring 5 can be fixed, also by modes such as bolts, fixed head 6 and non rotating ring 1 be fixed meanwhile, to make the fixing more firm of non rotating ring 1, test more stable.
Actuator load topworks can comprise hold-down support 7 and actuator 8.
Hold-down support 7 can be multiple applicable shape, also can be such as cylindrical shape, and bottom and testing table base plate 3 place plane are fixed.The journal stirrup of actuator 8 one end and non rotating ring 1 is hinged, and the other end is hinged on described hold-down support 7.It should be noted that, the load angle (α in Fig. 1) of actuator 8 can adjust guarantee in the installation site of hold-down support 5 on installed surface, to simulate the Impact direction of non rotating ring 1 as far as possible, improves test accuracy.
Further, actuator 8 can be hinged by the journal stirrup of multiple applicable mode and non rotating ring 1.In the present embodiment, connected by crossover sub assembly, specifically as shown in Figure 3 and Figure 4, crossover sub assembly comprises oscillating bearing 9, the journal stirrup of oscillating bearing 9 one end and non rotating ring 1 is hinged, oscillating bearing 9 other end is connected with large joint 10 one end, and the other end of large joint 10 is connected with adapter 11 one end by fastening screw nut 13 again, and adapter 9 other end is connected with one end away from hold-down support 7 of actuator 8 again.
Actuator load topworks also comprises force snesor 12 and corresponding control device.
Force snesor 12 is connected with actuator 8, and for detecting the load that actuator 8 exports, certain force snesor 12 also can other positions be applicable to.Control device controllably regulates actuator 8 to apply power load to non rotating ring 1, and judges the size of the load exported according to the data that force snesor 12 feeds back, and ensures magnitude of load and coordinates phase place, improving test accuracy.
During installation, first by fashion of extrusion by non rotating ring 1 testpieces press-in seat ring 5, and to ensure on the ears center line of non rotating ring 1 three support arms and seat ring 56
the center line of hole (not shown) is mutually 30 ° of angles, and error must be less than 1 °.Non rotating ring 1 is fixed on seat ring 5, then by seat ring 5 being bolted on testing table top board 4 by 6 M24 by the bolt of two circle M10 and M8 on fixed head 6 again.Test-bed 2 is bolted on testing table base plate 3 by circle 6 M24's.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, do not departing under the original prerequisite of the present invention; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (7)
1. an auto-bank unit non rotating ring fatigue experimental device, is characterized in that, comprising:
Erecting device, for fixedly mounting non rotating ring (1);
Actuator load topworks, is connected with the journal stirrup of described non rotating ring (1), for helicopter simulating booster control loads and described control loads is applied to described non rotating ring (1).
2. auto-bank unit non rotating ring fatigue experimental device according to claim 1, it is characterized in that, described erecting device comprises:
Test-bed (2), cylindrically;
Testing table base plate (3), rounded, be fixedly installed on described test-bed (2) bottom, the axis of described test-bed (2) passes the center of circle of described testing table base plate (3);
Testing table top board (4), rounded, be fixedly installed on described test-bed (2) top, the axis of described test-bed (2) passes the center of circle of described testing table top board (4);
Seat ring (5), cylindrically, bottom is fixedly connected with described testing table top board (4), the axis of described seat ring (5) and the dead in line of described test-bed (2), described non rotating ring (1) is fixedly installed on described seat ring (5) top.
3. auto-bank unit non rotating ring fatigue experimental device according to claim 2, it is characterized in that, described seat ring (5) bottom end face offers a coaxial annular recess, described in described groove, the internal diameter of seat ring (5) equals the diameter of described groove, and the bottom surface of the described seat ring (5) in described groove and the bottom surface of described non rotating ring (1) are positioned at same level;
Be provided with a circular fixed head (6) in described groove, the diameter of described fixed head (6) equals the diameter of described groove, for being connected with described seat ring (5) and described non rotating ring (1) simultaneously.
4. auto-bank unit non rotating ring fatigue experimental device according to claim 1, is characterized in that, described actuator load topworks comprises:
Hold-down support (7);
Actuator (8), the journal stirrup of one end and described non rotating ring (1) is hinged, and the other end is hinged on described hold-down support (7).
5. auto-bank unit non rotating ring fatigue experimental device according to claim 4, is characterized in that, described actuator (8) is hinged by the journal stirrup of crossover sub assembly and described non rotating ring (1).
6. auto-bank unit non rotating ring fatigue experimental device according to claim 5, it is characterized in that, described crossover sub assembly comprises oscillating bearing (9), and described oscillating bearing (9) is connected with one end away from described hold-down support (7) of described actuator (8) with adapter (11) by the large joint (10) connected successively.
7. auto-bank unit non rotating ring fatigue experimental device according to claim 4, is characterized in that, described actuator load topworks also comprises:
Force snesor (12), is connected with described actuator (8), for detecting the load that described actuator (8) exports;
Control device, controllably regulates described actuator (8) to apply power load to described non rotating ring (1), and judges the size of the load exported according to the data that described force snesor (12) feeds back.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510160862.5A CN104729846A (en) | 2015-04-07 | 2015-04-07 | Automatic inclinator nonrotating ring fatigue test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510160862.5A CN104729846A (en) | 2015-04-07 | 2015-04-07 | Automatic inclinator nonrotating ring fatigue test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104729846A true CN104729846A (en) | 2015-06-24 |
Family
ID=53453945
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510160862.5A Pending CN104729846A (en) | 2015-04-07 | 2015-04-07 | Automatic inclinator nonrotating ring fatigue test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104729846A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181333A (en) * | 2015-08-18 | 2015-12-23 | 鹰领航空高端装备技术秦皇岛有限公司 | Helicopter tail rotor system supporting combination joint bearing test machine |
| CN108489723A (en) * | 2018-04-23 | 2018-09-04 | 中国航发哈尔滨东安发动机有限公司 | Master subtracts casing component booster bearing fatigue experimental device |
| CN108552154A (en) * | 2018-02-24 | 2018-09-21 | 南京工业职业技术学院 | A kind of aviation scarecrow device |
| CN109187019A (en) * | 2018-10-31 | 2019-01-11 | 燕山大学 | Oscillating oil cylinder loaded type main rotor ball socket bearing comprehensive test machine |
| CN109506914A (en) * | 2018-11-12 | 2019-03-22 | 中国直升机设计研究所 | Tail slurry displacement fatigue experimental device |
| CN109506911A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Load testing machine |
| CN110954342A (en) * | 2019-12-18 | 2020-04-03 | 东风(武汉)实业有限公司 | Angle-variable strength tester |
| CN112485135A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Fatigue test device and verification method for rigid rotor wing composite material long pull rod |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202994453U (en) * | 2012-12-25 | 2013-06-12 | 中国直升机设计研究所 | An operation matching mechanism of a rotor testing platform |
| CN103162963A (en) * | 2013-02-06 | 2013-06-19 | 燕山大学 | Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine |
| KR101368070B1 (en) * | 2012-12-28 | 2014-02-27 | 현대위아 주식회사 | Fatigue evaluation device of rotating swashplate of helicopter main rotor control system |
| CN104511857A (en) * | 2013-09-30 | 2015-04-15 | 哈尔滨飞机工业集团有限责任公司 | Fixed ring detection tool |
| CN104697754A (en) * | 2013-12-04 | 2015-06-10 | 中国直升机设计研究所 | Blade root section fatigue test device |
-
2015
- 2015-04-07 CN CN201510160862.5A patent/CN104729846A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202994453U (en) * | 2012-12-25 | 2013-06-12 | 中国直升机设计研究所 | An operation matching mechanism of a rotor testing platform |
| KR101368070B1 (en) * | 2012-12-28 | 2014-02-27 | 현대위아 주식회사 | Fatigue evaluation device of rotating swashplate of helicopter main rotor control system |
| CN103162963A (en) * | 2013-02-06 | 2013-06-19 | 燕山大学 | Helicopter automatic inclinator spherical hinge bearing comprehensive fatigue testing machine |
| CN104511857A (en) * | 2013-09-30 | 2015-04-15 | 哈尔滨飞机工业集团有限责任公司 | Fixed ring detection tool |
| CN104697754A (en) * | 2013-12-04 | 2015-06-10 | 中国直升机设计研究所 | Blade root section fatigue test device |
Non-Patent Citations (2)
| Title |
|---|
| 梅卫胜，焦昌富: "悬停状态下旋翼模型桨叶气弹稳定性试验研究", 《南京航空航天大学学报》 * |
| 王建: "直升机旋翼系统工程强度设计方法", 《直升机技术》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181333A (en) * | 2015-08-18 | 2015-12-23 | 鹰领航空高端装备技术秦皇岛有限公司 | Helicopter tail rotor system supporting combination joint bearing test machine |
| CN108552154A (en) * | 2018-02-24 | 2018-09-21 | 南京工业职业技术学院 | A kind of aviation scarecrow device |
| CN108489723A (en) * | 2018-04-23 | 2018-09-04 | 中国航发哈尔滨东安发动机有限公司 | Master subtracts casing component booster bearing fatigue experimental device |
| CN109187019A (en) * | 2018-10-31 | 2019-01-11 | 燕山大学 | Oscillating oil cylinder loaded type main rotor ball socket bearing comprehensive test machine |
| CN109187019B (en) * | 2018-10-31 | 2019-07-26 | 燕山大学 | Oscillating oil cylinder loaded type main rotor ball socket bearing comprehensive test machine |
| CN109506911A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Load testing machine |
| CN109506914A (en) * | 2018-11-12 | 2019-03-22 | 中国直升机设计研究所 | Tail slurry displacement fatigue experimental device |
| CN110954342A (en) * | 2019-12-18 | 2020-04-03 | 东风(武汉)实业有限公司 | Angle-variable strength tester |
| CN112485135A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Fatigue test device and verification method for rigid rotor wing composite material long pull rod |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104729846A (en) | Automatic inclinator nonrotating ring fatigue test device | |
| US9708982B2 (en) | Method for mounting an aircraft engine on a pylon, and engine fastener for implementing said method | |
| US20110041624A1 (en) | Wind turbine gearbox testing system | |
| CN104697754A (en) | Blade root section fatigue test device | |
| CN207570942U (en) | A kind of tail undercarriage damper leg erection joint fatigue experimental device | |
| CN101905414A (en) | Installation device | |
| CN204439326U (en) | A kind of test rudder face actuator simulator | |
| CN112444415B (en) | Test device and test method for axle steering system | |
| CN104236880B (en) | A kind of torsional arm component fatigue experimental device | |
| CN112485108A (en) | Three-dimensional loading test device for double-elastic-bearing main-propeller central part | |
| CN210549664U (en) | Automatic centering device for blade | |
| CN110285024B (en) | Floating type fan tower drum scaling model for simulating tower shadow effect and yaw error | |
| CN102922444A (en) | Fixed clamping device for detecting complex blade vibration performance | |
| CN109533387A (en) | A kind of Helicopter Main Hub support arm restraint lock fatigue experimental device | |
| CN107651214A (en) | Multi-rotor unmanned aerial vehicle overall test device and its test method | |
| CN104176269B (en) | A kind of rotor system anchor fitting improving depopulated helicopter engines ground experiment safety | |
| CN109506915A (en) | A kind of tail-rotor steering assembly fatigue experimental device | |
| CN107322051A (en) | A kind of drill bit installing mechanism | |
| CN209400326U (en) | A kind of shield tunnel screwed joint tensile property multifunction test device | |
| CN209280444U (en) | Leaf assay device | |
| CN207328860U (en) | Multi-rotor unmanned aerial vehicle overall test device | |
| CN203719756U (en) | Double shear beam type weighing sensor | |
| CN205379725U (en) | Novel drum strainer wheel hub | |
| CN219687614U (en) | Small-load helicopter full-aircraft static test lifting system simulation part | |
| CN101761893B (en) | Wind-resistance fixing device and runway guard light |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150624 |
|
| RJ01 | Rejection of invention patent application after publication |