CN104236880A - Fatigue test device for torque arm assembly - Google Patents
Fatigue test device for torque arm assembly Download PDFInfo
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- CN104236880A CN104236880A CN201410424579.4A CN201410424579A CN104236880A CN 104236880 A CN104236880 A CN 104236880A CN 201410424579 A CN201410424579 A CN 201410424579A CN 104236880 A CN104236880 A CN 104236880A
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Abstract
The invention discloses a fatigue test device for a torque arm assembly and belongs to the fatigue test technology for torque arm assemblies. The fatigue test device for the torque arm assembly is characterized in that two opposite semicircular holes are formed in one end of a shaft body of an artificial main shaft, the outer diameter of the shaft body of the artificial main shaft is matched with the inner diameter of a clamping ring, the two semicircular holes in the shaft body and two opposite semicircular holes in the clamping ring are aligned, and the other end of the artificial main shaft is fixed to a test stand rack; a first actuator is connected with a first force transducer and is connected with a first torque arm through a first loading connector, a second actuator is connected with a second force transducer and is connected with a second torque arm through a second loading connector, the first actuator and the second actuator are symmetrical about the artificial main shaft, a pair of loads which are opposite in direction are exerted on the first loading connector and the second loading connector respectively in the tangential directions of the torque arms, and the fixed end of the first actuator and the fixed end of the second actuator are fixed to the test stand rack. According to the fatigue test device for the torque arm assembly, the loading structure and the load characteristics can be simulated more truly, and results are more accurate and more credible. When the fatigue test device is used for testing, the overall testing error can be controlled below 3%.
Description
Technical field
The invention belongs to torsional arm component fatigue test technology, relate to a kind of torsional arm component fatigue experimental device.
Background technology
In helicopter structure, toggle is generally all mounted in pairs, and one end is connected with rotating ring, and the other end is connected with mast by snap ring or is connected with center piece by ring flange, mainly bears the contrary circumferential load in a pair direction that rotating ring transmits.For ensureing the reliability of its good performance and use, its load should be simulated and design feature carries out torture test examination, for determining that its serviceable life provides foundation.
Prior art adopts single toggle charger to test, can not real simulation dynamic changes process relation, there is larger engineering simplification, and test total error can reach about 10%.
Summary of the invention
The technical problem to be solved in the present invention: a kind of torsional arm component fatigue experimental device is provided, can more real simulation installation structure and Load Characteristics, can determine true fatigue behaviour and the weak part of torsional arm component more accurately, for determining that its serviceable life provides foundation, result is more accurately credible.
Technical scheme of the present invention: a kind of torsional arm component fatigue experimental device, torsional arm component comprises snap ring 6, toggle 4 and No. two toggles 7, by the assembling of aircraft installation state, square arm 4-1 one end of a toggle 4 is fixedly connected with Triangular Arm 4-2 by bolt, and the other end is fixedly connected with snap ring 6 by bolt; Square arm 7-1 one end of No. two toggles 7 is fixedly connected with Triangular Arm 7-2 by bolt, and the other end is fixedly connected with snap ring 6 by bolt.It is characterized in that, comprising: main shaft bogusware 5, actuator 1, a force cell 2, a loading joint 3, No. two actuator 10, No. two force cells 9, No. two loading joints 8, coordinated loading control system 11, main shaft bogusware 5 one end axis body is provided with two relative semicircle orifices, main shaft bogusware 5 axis body external diameter and snap ring 6 internal diameter adaptation, align with two relative semicircle orifices on snap ring 6, main shaft bogusware 5 other end is fixed on test-bed; An actuator 1 is connected a force cell 2 and is connected with a toggle 4 by a loading joint 3, No. two actuator 10 are connected No. two force cells 9 and are connected with No. two toggles 7 by No. two loading joints 8, an actuator 1 and No. two actuator 10 are arranged symmetrically with relative to main shaft bogusware 5, apply that a pair direction is contrary respectively and along the load of toggle tangential direction, an actuator 1, No. two actuator 10 stiff ends and test-bed are fixed at a loading joint 3 and No. two loading joints 8.
A described loading joint 3 is monaural chip architecture, monaural sheet has a dead eye, a built-in joint ball bearing, one end of a loading joint 3 is fixedly connected with a force cell 2, and the Triangular Arm axle head of a toggle 4 is fixedly connected with a loading joint 3 through dead eye.
Described No. two loading joints 8 are monaural chip architecture, monaural sheet has a dead eye, a built-in joint ball bearing, one end of No. two loading joints 8 is fixedly connected with No. two force cells 9, and the Triangular Arm axle head of No. two toggles 7 is fixedly connected with a loading joint 8 through dead eye.
The angle of the square arm 4-1 of described snap ring 6 and a toggle 4 is 5 °-45 °, and the angle of the Triangular Arm 4-2 of square arm 4-1 and No. one toggle 4 of a toggle 4 is 60 °-135 °.
The angle of the square arm 7-1 of described snap ring 6 and No. two toggles 7 is 5 °-45 °, and the angle of the Triangular Arm 7-2 of square arm 7-1 and No. two toggle 7 of No. two toggles 7 is 60 °-135 °.
Coupling bolt is connected main shaft bogusware 5 and snap ring 6 by described main shaft bogusware 5 with the semicircle orifice on snap ring 6, is fixed on main shaft bogusware 5 by snap ring 6 by tightening coupling bolt.
Beneficial effect of the present invention:
The torsional arm component fatigue experimental device of the present invention's design, simulation installation structure and Load Characteristics, adopt two to load actuator and apply a pair contrary tangential direction load in direction at two toggles and rotating ring tie point respectively, can more real simulation installation structure and Load Characteristics, result is more accurately credible.By adopting apparatus of the present invention to test, test total error can control within 3%.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is vertical view of the present invention.
Fig. 3 is A-A cut-open view of the present invention.
Fig. 4 is B-B cut-open view of the present invention.
Embodiment
Below the present invention is described in further details.
As shown in Figure 1, Figure 2, Figure 3, Figure 4, the present invention is a kind of torsional arm component fatigue experimental device, comprising:
Main shaft bogusware 5, an actuator 1, a force cell 2, a loading joint 3, No. two actuator 10, No. two force cells 9, No. two loading joints 8, coordinated loading control system 11, main shaft bogusware 5 axis body is provided with two relative semicircle orifices, and main shaft bogusware 5 axis body external diameter and snap ring 6 internal diameter are adaptive, aligns with two relative semicircle orifices on snap ring 6, coupling bolt is connected main shaft bogusware and snap ring by described main shaft bogusware with the semicircle orifice on snap ring, is fixed on main shaft bogusware by snap ring by tightening coupling bolt.An actuator 1 is connected a force cell 2 and is connected with a toggle 4 by a loading joint 3.No. two actuator 10 are connected No. two force cells 9 and are connected with No. two toggles 7 by No. two loading joints 8.An actuator 1 and No. two actuator 10 are arranged symmetrically with relative to main shaft bogusware 5, apply a pair direction respectively contrary and along the load of toggle tangential direction at a loading joint 3 and No. two loading joints 8.Main shaft bogusware 5, actuator 1, No. two actuator 10 stiff ends and test-bed are fixed.
A loading joint 3 is monaural chip architecture, monaural sheet has a dead eye, a built-in joint ball bearing, one end of a loading joint 3 is fixedly connected with a force cell 2, and the Triangular Arm axle head of a toggle 4 is fixedly connected with a loading joint 3 through dead eye.
No. two loading joints 8 are monaural chip architecture, monaural sheet has a dead eye, a built-in joint ball bearing, one end of No. two loading joints 8 is fixedly connected with No. two force cells 9, and the Triangular Arm axle head of No. two toggles 7 is fixedly connected with a loading joint 8 through dead eye.
The angle of the square arm 4-1 of described snap ring 6 and a toggle 4 is 5 °-45 °, and the angle of the Triangular Arm 4-2 of square arm 4-1 and No. one toggle 4 of a toggle 4 is 60 °-135 °.
The angle of the square arm 7-1 of described snap ring 6 and No. two toggles 7 is 5 °-45 °, and the angle of the Triangular Arm 7-2 of square arm 7-1 and No. two toggle 7 of No. two toggles 7 is 60 °-135 °.
During test, control an actuator 1, No. two actuator 10 by coordinated loading control system 11 and apply a pair load contrary with Helicopter Main rotor wing rotation direction, real simulation installation structure and Load Characteristics, tested by accumulation cycle, obtain true fatigue behaviour and the weak part of testpieces, for determining that the serviceable life of testpieces provides foundation.
In one embodiment of the invention, snap ring 6 is 20 ° with the angle of the square arm 4-1 of the toggle 4 and square arm 7-1 of toggle 7, the Triangular Arm 4-2 of the square arm 4-1 of toggle 4 and the square arm 7-1 of toggle 7 and toggle 4 and toggle 7 the angle of Triangular Arm 7-2 be 98 °.
Claims (6)
1. a torsional arm component fatigue experimental device, it is characterized in that, comprise main shaft bogusware (5), an actuator (1), a force cell (2), a loading joint (3), No. two actuator (10), No. two force cells (9), No. two loading joints (8) and coordinated loading control system (11), main shaft bogusware (5) one end axis body is provided with two relative semicircle orifices, main shaft bogusware (5) axis body external diameter and snap ring (6) internal diameter adaptation, align with upper two the relative semicircle orifices of snap ring (6), main shaft bogusware (5) other end is fixed on test-bed, an actuator (1) is connected a force cell (2) and is connected with a toggle (4) by a loading joint (3), No. two actuator (10) are connected No. two force cells (9) and are connected with No. two toggles (7) by No. two loading joints (8), an actuator (1) is arranged symmetrically with relative to main shaft bogusware (5) with No. two actuator (10), a pair direction is applied respectively contrary and along the load of toggle tangential direction a loading joint (3) and No. two loading joints (8), an actuator (1), No. two actuator (10) stiff ends and test-bed are fixed.
2. torsional arm component fatigue experimental device according to claim 1, it is characterized in that, a loading joint (3) is monaural chip architecture, monaural sheet has a dead eye, a built-in joint ball bearing, one end of a loading joint (3) is fixedly connected with a force cell (2), and the Triangular Arm axle head of a toggle (4) is fixedly connected with a loading joint (3) through dead eye.
3. torsional arm component fatigue experimental device according to claim 1, it is characterized in that, No. two loading joints (8) are monaural chip architecture, monaural sheet has a dead eye, a built-in joint ball bearing, one end of No. two loading joints (8) is fixedly connected with No. two force cells (9), and the Triangular Arm axle head of No. two toggles (7) is fixedly connected with a loading joint (8) through dead eye.
4. torsional arm component fatigue experimental device according to claim 1, it is characterized in that, described snap ring (6) is 5 °-45 ° with the angle of the square arm (4-1) of a toggle (4), and the square arm (4-1) of a toggle (4) is 60 °-135 ° with the angle of the Triangular Arm (4-2) of a toggle (4).
5. torsional arm component fatigue experimental device according to claim 1, it is characterized in that, described snap ring (6) is 5 °-45 ° with the angle of the square arm (7-1) of No. two toggles (7), and the square arm (7-1) of No. two toggles (7) is 60 °-135 ° with the angle of the Triangular Arm (7-2) of No. two toggles (7).
6. torsional arm component fatigue experimental device according to claim 1, it is characterized in that, coupling bolt is connected main shaft bogusware (5) and snap ring (6) by described main shaft bogusware (5) with the semicircle orifice on snap ring (6), is fixed on main shaft bogusware (5) by snap ring (6) by tightening coupling bolt.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410424579.4A CN104236880B (en) | 2014-08-26 | 2014-08-26 | A kind of torsional arm component fatigue experimental device |
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| CN201410424579.4A CN104236880B (en) | 2014-08-26 | 2014-08-26 | A kind of torsional arm component fatigue experimental device |
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| CN104236880A true CN104236880A (en) | 2014-12-24 |
| CN104236880B CN104236880B (en) | 2018-02-23 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104833493A (en) * | 2015-04-07 | 2015-08-12 | 中国直升机设计研究所 | Fatigue test loading device for tail rotor hub central component |
| CN109506914A (en) * | 2018-11-12 | 2019-03-22 | 中国直升机设计研究所 | Tail slurry displacement fatigue experimental device |
| CN110095265A (en) * | 2018-01-27 | 2019-08-06 | 蒋盼盼 | A kind of torsional arm component fatigue experimental device |
| CN112179787A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Torsion test device for main paddle central part and support arm limited lock |
| CN112213101A (en) * | 2020-10-16 | 2021-01-12 | 中国直升机设计研究所 | Durability test bed for torsion arm swing-proof bearing of helicopter |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1818599A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Apparatus for testing fatigue strength of axial hinge bearing of helicopter |
| CN1818598A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Externally swing joint-bearing fatigue experimental apparatus of automatic rotor oblique device for helicopter |
| CN101368874A (en) * | 2008-09-26 | 2009-02-18 | 成都发动机（集团）有限公司 | Testing device for implementing main torque and vibrating torque to high speed rotary main shaft |
| CN102628744A (en) * | 2012-04-17 | 2012-08-08 | 长春轨道客车股份有限公司 | Double-way loading force transmission unit of simulation fatigue test device |
| 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 |
| CN203688373U (en) * | 2013-12-02 | 2014-07-02 | 北京乐冶液压气动设备技术有限公司 | Tension compression and torsional vibration fatigue test device |
-
2014
- 2014-08-26 CN CN201410424579.4A patent/CN104236880B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1818599A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Apparatus for testing fatigue strength of axial hinge bearing of helicopter |
| CN1818598A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Externally swing joint-bearing fatigue experimental apparatus of automatic rotor oblique device for helicopter |
| CN101368874A (en) * | 2008-09-26 | 2009-02-18 | 成都发动机（集团）有限公司 | Testing device for implementing main torque and vibrating torque to high speed rotary main shaft |
| CN102628744A (en) * | 2012-04-17 | 2012-08-08 | 长春轨道客车股份有限公司 | Double-way loading force transmission unit of simulation fatigue test device |
| 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 |
| CN203688373U (en) * | 2013-12-02 | 2014-07-02 | 北京乐冶液压气动设备技术有限公司 | Tension compression and torsional vibration fatigue test device |
Non-Patent Citations (1)
| Title |
|---|
| 李清蓉等: "直升机尾桨轴疲劳试验技术研究", 《直升机技术》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104833493A (en) * | 2015-04-07 | 2015-08-12 | 中国直升机设计研究所 | Fatigue test loading device for tail rotor hub central component |
| CN104833493B (en) * | 2015-04-07 | 2017-07-07 | 中国直升机设计研究所 | A kind of tail-rotor hub center piece fatigue test loading device |
| CN110095265A (en) * | 2018-01-27 | 2019-08-06 | 蒋盼盼 | A kind of torsional arm component fatigue experimental device |
| CN110095265B (en) * | 2018-01-27 | 2021-02-19 | 江苏锡华铸造有限公司 | Torsion arm assembly fatigue test device |
| CN109506914A (en) * | 2018-11-12 | 2019-03-22 | 中国直升机设计研究所 | Tail slurry displacement fatigue experimental device |
| CN112179787A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Torsion test device for main paddle central part and support arm limited lock |
| CN112213101A (en) * | 2020-10-16 | 2021-01-12 | 中国直升机设计研究所 | Durability test bed for torsion arm swing-proof bearing of helicopter |
| CN112213101B (en) * | 2020-10-16 | 2022-06-17 | 中国直升机设计研究所 | Durability test bed for torsion arm swing-proof bearing of helicopter |
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| CN104236880B (en) | 2018-02-23 |
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