CN110654568A - Hub couple loading device - Google Patents
Hub couple loading device Download PDFInfo
- Publication number
- CN110654568A CN110654568A CN201910931893.4A CN201910931893A CN110654568A CN 110654568 A CN110654568 A CN 110654568A CN 201910931893 A CN201910931893 A CN 201910931893A CN 110654568 A CN110654568 A CN 110654568A
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- mounting plate
- screw
- small
- hanging
- large screw
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automatic Assembly (AREA)
- Apparatuses For Generation Of Mechanical Vibrations (AREA)
Abstract
The invention discloses a hub couple loading device, wherein a sliding guide rail (4) and a mounting beam (3) are connected into a whole; a large screw fixing mounting plate (1) is mounted on the mounting beam (3), a large screw (2) is mounted on the large screw fixing mounting plate (1), two ends of a moving adjusting beam (7) are freely mounted on the two sliding guide rails (4), a middle threaded hole is mounted on the large screw (2), and two small screw fixing mounting plates (6) are mounted at two ends of the moving adjusting beam (7); the small screw (5) is arranged on the small screw fixing mounting plate (6); the vibration exciter hanging beam (12) is movably hung on the small screw (5), and the two hanging lugs (13) are connected with the vibration exciter hanging beam (12); the lower end of the hanging lug (13) is provided with a lock screw buckle (14), an elastic rope (15), a vibration exciter (16), a vibration exciting rod (17) and a vibration exciting position connecting block (18) in sequence. The hub couple loading device can quickly and accurately realize the butt joint positioning of the loading equipment and the loading point.
Description
Technical Field
The invention belongs to a helicopter transfer function test technology, and relates to a helicopter hub couple loading device.
Background
The transfer function dynamic characteristic test is an important link for researching vibration analysis and control of the helicopter, and almost all new models need to be developed and finished. The most key technology of the test is that excitation force is simulated and applied to excitation sources such as the hub center and the like; in the flight process of a common helicopter, excitation borne by the center of a hub can be decoupled and decomposed into course, lateral, vertical, pitching moment and rolling moment couples, wherein the moment couples are loaded by two independent excitation sources, and the loading process is the most complicated. Mainly faces the problems of time-varying property, poor repeatability and the like existing at the position of a loading point. At this time, a set of mechanism needs to be designed, and the function of adjusting the position of the loading device, which is accurately butted with the loading point, can be realized. The couple loading device used in the existing laboratory is mainly adjusted manually, has poor butt joint precision and low working efficiency, and is difficult to meet the requirements of the current test task. In order to meet the requirements of new-trend scientific research work and improve the test level, a novel hub couple loading device is urgently needed to be developed.
Disclosure of Invention
In view of the above situation in the prior art, an object of the present invention is to provide a hub couple loading device, which can quickly and accurately realize the butt joint positioning between the loading device and the loading point position, and can be used to complete the helicopter transfer function dynamic characteristic test.
The above object of the present invention is achieved by the following technical solutions:
a hub couple loading device comprising: the vibration exciter comprises a large screw fixing and mounting plate, a large screw, mounting beams, sliding guide rails, a small screw fixing and mounting plate, a traveling adjusting beam, a vibration exciter hanging beam and hanging lugs, wherein the two sliding guide rails and the two mounting beams are connected into a whole; the mounting beams are respectively provided with a large screw fixing mounting plate, two ends of the large screw are mounted on the large screw fixing mounting plate, through holes at two ends of the moving adjusting beam are freely mounted on the two sliding guide rails, a middle threaded hole is mounted on the large screw, and two small screw fixing mounting plates are respectively mounted at two ends of the moving adjusting beam; two ends of the small screw are arranged on the small screw fixing and mounting plate; the vibration exciter hanging beam is movably hung on the small screw rod, and the two hanging lugs are connected with the vibration exciter hanging beam; the lower end of the suspension loop is provided with a lock screw buckle, an elastic rope, a vibration exciter, a vibration exciting rod and a vibration exciting position connecting block in sequence.
The vibration exciter hanging beam is hung on the small screw rod through the square-head stud, the middle threaded hole of the square-head stud is installed on the small screw rod, the lower surface of the square-head stud is freely placed on the moving adjusting beam, the square-head stud is connected with the vibration exciter hanging beam through the locking nut, and the rotation position of the vibration exciter hanging beam in the hanging beam plane can be adjusted before locking.
The large screw fixing and mounting plate and the mounting beam can be integrated or separated, the large screw fixing and mounting plate is fixedly connected with the mounting beam, and the situation of the small screw fixing and mounting plate is similar.
Footstep bearings can be installed at two ends of the large screw rod, and the footstep bearings are installed on the large screw rod fixing and installing plate in an embedded mode, so that time and labor are saved during operation. In addition, one end of the big screw rod and one end of the small screw rod are respectively connected with a big handle and a small handle.
The invention relates to a propeller hub couple loading device, which belongs to the helicopter transfer function test technology, realizes the front-back left-right position adjustment in a plane through a large and small adjusting screw rod, realizes the position adjustment in the vertical direction through a lock turnbuckle, and can freely rotate and adjust a vibration exciter hanging beam in the plane, thereby being capable of quickly and accurately realizing the butt joint positioning of loading equipment and the position of a loading point; the device overcomes the defects of poor butting precision and low working efficiency of the loading equipment and the loading point of the current laboratory. The operation workers are reduced from two to one, the working time is shortened from half an hour to about several minutes, and the butt joint precision is greatly improved.
Drawings
Figure 1 is an isometric view of a hub couple loading apparatus of the present invention.
Fig. 2 is an isometric view of a exciter hanger and its accessories in the hub couple loading apparatus of the present invention.
Detailed Description
The technical scheme of the invention is clearly and completely described in combination with the embodiment of the invention by referring to the attached drawings.
Fig. 1 is an isometric view of a hub couple loading device of the present invention, and fig. 2 is an isometric view of a vibration exciter hanger and its accessories therein. As shown in the figure, the propeller hub couple loading device comprises a large screw fixing and mounting plate 1, a large screw 2, a mounting beam 3, a sliding guide rail 4, a small screw 5, a small screw fixing and mounting plate 6, a traveling adjusting beam 7, a large handle 8, a small handle 9, a square stud 10, a locking nut 11, a vibration exciter hanging beam 12 and a hanging lug 13. Wherein the large screw fixing mounting plate 1 is fixedly connected with the mounting beam 3, and the two sliding guide rails 4 are connected with the two mounting beams 3 into a whole; thrust bearings are arranged at two ends of the large screw rod 2, and the thrust bearings are embedded and arranged on the large screw rod fixing and mounting plate 1; through holes at two ends of the traveling adjusting beam 7 are freely arranged on the two sliding guide rails 4, a middle threaded hole is arranged on the large screw rod 2, and one end of the large screw rod 2 is connected with the large handle 8; the two small screw fixing and mounting plates 6 are respectively and fixedly connected with two ends of the traveling adjusting beam 7; thrust bearings are arranged at two ends of the small screw 5 and are embedded and arranged on the small fixed screw mounting plate 6; a middle threaded hole of the square-head stud 10 is arranged on the small screw rod 5, the lower surface of the square head is freely placed on the moving adjusting beam 7, and one end of the small screw rod 5 is connected with the small handle 9; the square stud 10 is connected with a vibration exciter hanging beam 12 through a locking nut 11; the two hanging lugs 13 are connected with a vibration exciter hanging beam 12; the lower end of the hanging lug 13 is provided with a lock screw buckle 14, an elastic rope 15, a vibration exciter 16, a vibration exciting rod 17, a vibration exciting position connecting block 18 and the like in sequence to form a complete couple loading adjusting mechanism.
During assembly, the method comprises the following steps:
1. the traveling adjusting beam 7 is arranged on two sliding guide rails 4, and then two ends of the sliding guide rails 4 are connected with the mounting beams 3 to form a whole;
2. the small screw 5 is connected with a square stud 10 and is simultaneously connected with two small screw fixing and mounting plates 6, the small screw fixing and mounting plates 6 are screwed on the moving adjusting beam 7, and a small handle 9 is simultaneously mounted;
3. connecting the large screw 2 with the traveling adjusting beam 7, connecting the two large screw fixing and mounting plates 1 at the same time, screwing the large screw fixing and mounting plates 1 on the mounting beam 3, and mounting a large handle 8 at the same time;
4. mounting and connecting a square stud 10, a lock nut 11, a vibration exciter hanging beam 12, a hanging lug 13 and a lock screw buckle 14, and then mounting the above assembly into a preset position at the top end of the rack;
5. the elastic rope 15, the vibration exciter 16, the vibration exciting rod 17, the vibration exciting position connecting block 18 and other parts are connected on the ground, then the whole body is hoisted by the hoisting device to be connected with the lock screw buckle 14, and the lock screw buckle 14 can realize the up-and-down position adjustment of a loading point;
6. before the test is started, an operator rotates the large screw rod 2 and the small screw rod 5, the large handle 8 and the small handle 9 are adjusted through rotation, the front-back and left-right adjustment of the excitation position is achieved, the excitation point height adjustment is achieved through adjusting the lockset turnbuckle 14, the excitation point position is controlled accurately, and when the pitching and rolling couple is switched, the locking nut 11 is loosened, and the vibration exciter hanging beam 12 is rotated by 90 degrees, so that the vibration exciter hanging beam can be achieved.
Claims (8)
1. A propeller hub couple loading device comprises a large screw fixing mounting plate (1), a large screw (2), mounting beams (3), sliding guide rails (4), small screws (5), small screw fixing mounting plates (6), a traveling adjusting beam (7), a vibration exciter hanging beam (12) and hanging lugs (13), wherein the two sliding guide rails (4) are connected with the two mounting beams (3) into a whole; the mounting beam (3) is respectively provided with a large screw fixing mounting plate (1), two ends of a large screw (2) are mounted on the large screw fixing mounting plate (1), through holes at two ends of a moving adjusting beam (7) are freely mounted on two sliding guide rails (4), a middle threaded hole is mounted on the large screw (2), and two small screw fixing mounting plates (6) are respectively mounted at two ends of the moving adjusting beam (7); two ends of the small screw (5) are arranged on the small screw fixing and mounting plate (6); the vibration exciter hanging beam (12) is movably hung on the small screw (5), and the two hanging lugs (13) are connected with the vibration exciter hanging beam (12); the lower end of the hanging lug (13) is provided with a lock screw buckle (14), an elastic rope (15), a vibration exciter (16), a vibration exciting rod (17) and a vibration exciting position connecting block (18) in sequence.
2. The hub couple loading device according to claim 1, wherein the exciter hanging beam (12) is hung on the small screw rod (5) through a square stud (10), a middle threaded hole of the square stud (10) is installed on the small screw rod (5), the lower surface of the square stud (10) is freely placed on the traveling adjusting beam (7), the square stud (10) is connected with the exciter hanging beam (12) through a locking nut (11), and before locking, the rotation position of the exciter hanging beam in the hanging beam plane can be adjusted.
3. The hub couple loading unit of claim 1 wherein the large screw anchor mounting plate (1) is integral with the mounting beam (3).
4. The hub couple loading unit of claim 1 wherein the large screw anchor mounting plate (1) is fixedly attached to the mounting beam (3).
5. The hub couple loading unit of claim 1 wherein the small screw anchor mounting plate (6) is integral with the fly-adjustment beam (7).
6. The hub couple loading unit of claim 1 wherein the small screw anchor mounting plate (6) is fixedly attached to the fly-adjustment beam (7).
7. The hub couple loading device of claim 1, wherein thrust bearings are mounted at both ends of the large screw (2), and the thrust bearings are mounted on the large screw fixing mounting plate (1) in an embedded manner.
8. The hub couple loading device of claim 1, wherein one end of the large screw (2) and one end of the small screw (5) are respectively connected with a large handle (8) and a small handle (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910931893.4A CN110654568B (en) | 2019-09-29 | 2019-09-29 | Hub couple loading device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910931893.4A CN110654568B (en) | 2019-09-29 | 2019-09-29 | Hub couple loading device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110654568A true CN110654568A (en) | 2020-01-07 |
| CN110654568B CN110654568B (en) | 2022-09-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910931893.4A Active CN110654568B (en) | 2019-09-29 | 2019-09-29 | Hub couple loading device |
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Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0199317A2 (en) * | 1985-04-25 | 1986-10-29 | Bayerische Motoren Werke Aktiengesellschaft, Patentabteilung AJ-3 | Test stand for investigating the reliability of motor vehicle components |
| JP2004126488A (en) * | 2002-10-02 | 2004-04-22 | Koichi Kameoka | Chaos vibration generating device |
| JP2007138627A (en) * | 2005-11-21 | 2007-06-07 | Geotop Corp | Pile dynamic horizontal loading test equipment |
| CN102183363A (en) * | 2010-12-30 | 2011-09-14 | 南京理工大学 | Dynamic characteristic parameter test device and method of sliding guide rail junction surface |
| US20120151768A1 (en) * | 2010-07-30 | 2012-06-21 | Linda Swadling | Trammel Assembly for Rotor Pitch Links and Method of Using Same |
| CN103063392A (en) * | 2012-12-31 | 2013-04-24 | 浙江工业大学 | Ultra-low frequency modal test gravitational equilibrium system |
| FR3027830A1 (en) * | 2014-11-05 | 2016-05-06 | Mbh Dev | SUSPENSION DEVICE FOR SURFACING TOOL |
| CN206436203U (en) * | 2017-01-18 | 2017-08-25 | 杭州为一自动化设备有限公司 | A kind of workbench |
| CN107651216A (en) * | 2017-10-23 | 2018-02-02 | 重庆通用航空产业集团有限公司 | Engine loading device and method applied to single-shot fixed wing aircraft slow test |
| CN108088672A (en) * | 2017-11-29 | 2018-05-29 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel suspension joint slow test fixture |
| CN108100302A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter tail rotor hub center dynamic response test exciting bank |
| CN108163228A (en) * | 2017-12-03 | 2018-06-15 | 中国直升机设计研究所 | A kind of full machine flexibility trapeze test device of helicopter |
| CN207712320U (en) * | 2017-12-13 | 2018-08-10 | 中国航空工业集团公司成都飞机设计研究所 | A kind of ground microgravity simulation system based on constant force spring |
| JP2018173380A (en) * | 2017-03-31 | 2018-11-08 | 日鐵住金建材株式会社 | Object holding device for drop test and method of drop test |
| CN108910080A (en) * | 2018-06-26 | 2018-11-30 | 中国直升机设计研究所 | A kind of helicopter tail rotor aerodynamic loading environmental simulation test device |
| CN109540486A (en) * | 2018-11-12 | 2019-03-29 | 中国直升机设计研究所 | A kind of height-adjustable excitation loading device |
| CN109855984A (en) * | 2018-12-05 | 2019-06-07 | 中国建筑股份有限公司 | A kind of unidirectional compression shear loading device and its application method |
| US20190176281A1 (en) * | 2017-12-07 | 2019-06-13 | The Boeing Company | Automated Apparatus for Moving an End Effector Over a Surface of an Airfoil-Shaped Body |
-
2019
- 2019-09-29 CN CN201910931893.4A patent/CN110654568B/en active Active
Patent Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0199317A2 (en) * | 1985-04-25 | 1986-10-29 | Bayerische Motoren Werke Aktiengesellschaft, Patentabteilung AJ-3 | Test stand for investigating the reliability of motor vehicle components |
| JP2004126488A (en) * | 2002-10-02 | 2004-04-22 | Koichi Kameoka | Chaos vibration generating device |
| JP2007138627A (en) * | 2005-11-21 | 2007-06-07 | Geotop Corp | Pile dynamic horizontal loading test equipment |
| US20120151768A1 (en) * | 2010-07-30 | 2012-06-21 | Linda Swadling | Trammel Assembly for Rotor Pitch Links and Method of Using Same |
| CN102183363A (en) * | 2010-12-30 | 2011-09-14 | 南京理工大学 | Dynamic characteristic parameter test device and method of sliding guide rail junction surface |
| CN103063392A (en) * | 2012-12-31 | 2013-04-24 | 浙江工业大学 | Ultra-low frequency modal test gravitational equilibrium system |
| FR3027830A1 (en) * | 2014-11-05 | 2016-05-06 | Mbh Dev | SUSPENSION DEVICE FOR SURFACING TOOL |
| CN206436203U (en) * | 2017-01-18 | 2017-08-25 | 杭州为一自动化设备有限公司 | A kind of workbench |
| JP2018173380A (en) * | 2017-03-31 | 2018-11-08 | 日鐵住金建材株式会社 | Object holding device for drop test and method of drop test |
| CN107651216A (en) * | 2017-10-23 | 2018-02-02 | 重庆通用航空产业集团有限公司 | Engine loading device and method applied to single-shot fixed wing aircraft slow test |
| CN108088672A (en) * | 2017-11-29 | 2018-05-29 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel suspension joint slow test fixture |
| CN108100302A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter tail rotor hub center dynamic response test exciting bank |
| CN108163228A (en) * | 2017-12-03 | 2018-06-15 | 中国直升机设计研究所 | A kind of full machine flexibility trapeze test device of helicopter |
| US20190176281A1 (en) * | 2017-12-07 | 2019-06-13 | The Boeing Company | Automated Apparatus for Moving an End Effector Over a Surface of an Airfoil-Shaped Body |
| CN207712320U (en) * | 2017-12-13 | 2018-08-10 | 中国航空工业集团公司成都飞机设计研究所 | A kind of ground microgravity simulation system based on constant force spring |
| CN108910080A (en) * | 2018-06-26 | 2018-11-30 | 中国直升机设计研究所 | A kind of helicopter tail rotor aerodynamic loading environmental simulation test device |
| CN109540486A (en) * | 2018-11-12 | 2019-03-29 | 中国直升机设计研究所 | A kind of height-adjustable excitation loading device |
| CN109855984A (en) * | 2018-12-05 | 2019-06-07 | 中国建筑股份有限公司 | A kind of unidirectional compression shear loading device and its application method |
Non-Patent Citations (2)
| Title |
|---|
| 方宇等: "移动质量载荷作用下的悬臂梁振动计算方法", 《机械设计与制造》 * |
| 贵忠东等: "CPP桨毂机构电液伺服加载试验台", 《农业机械学报》 * |
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| CN110654568B (en) | 2022-09-06 |
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