CN109506914A - Tail slurry displacement fatigue experimental device - Google Patents
Tail slurry displacement fatigue experimental device Download PDFInfo
- Publication number
- CN109506914A CN109506914A CN201811340594.5A CN201811340594A CN109506914A CN 109506914 A CN109506914 A CN 109506914A CN 201811340594 A CN201811340594 A CN 201811340594A CN 109506914 A CN109506914 A CN 109506914A
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- China
- Prior art keywords
- experimental device
- pedestal
- fatigue experimental
- tail slurry
- convex platform
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
This application provides a kind of tail slurry displacement fatigue experimental device, including monaural component, support base and pedestal, monaural component includes support arm and auricle interconnected, offers connecting hole on auricle, is used for joint test part；Support base includes integrally formed convex platform and lower convex platform, and for fixing testpieces, lower convex platform is connect convex platform with pedestal；Angle between pedestal and the side and the other side corresponding thereto of support base connection is in predetermined angle.
Description
Technical field
This application involves Helicopter Technology fields, specifically provide a kind of tail slurry displacement fatigue experimental device.
Background technique
Tail-rotor is the middle important component of helicopter structure, and the torque that main balancing helicopter rotor generates leads to simultaneously
It crosses and generates variable torque to the posture of helicopter, ensure that steady during helicopter flight, tail-rotor operating system passes through
In tail-rotor displacement ring transmission force to tail-rotor, thus control aircraft posture and have a smooth flight, and the fatigue behaviour pair of tail-rotor displacement ring
It is had an important influence in the state of flight of helicopter.
The tail-rotor displacement ring fatigue experimental device for being primarily present unmanned helicopter in the prior art lacks and fatigue behaviour is difficult
With determining problem.
Summary of the invention
At least one in order to solve the above-mentioned technical problem, this application provides a kind of tail slurry displacement fatigue experimental device, packets
Monaural component, support base and pedestal are included, the monaural component includes support arm and auricle interconnected, is offered on the auricle
Connecting hole is used for joint test part；The support base includes integrally formed convex platform and lower convex platform, and the convex platform is for solid
The fixed testpieces, the lower convex platform are connect with the pedestal, and the support base is connect with the pedestal；The pedestal with it is described
Angle between the side and the other side of support base connection is in predetermined angle.
According at least one embodiment of the application, the center line of the center line of the support arm and the auricle is located at same
On straight line.
According at least one embodiment of the application, multiple first mounting holes are offered on the convex platform, it is convex under described
Multiple second mounting holes are offered on platform, for connecting the testpieces, second mounting hole is used for first mounting hole
It is connect with the pedestal.
According at least one embodiment of the application, the center of second mounting hole and the support base is formed by directly
Angle between line and adjacent nearest first mounting hole is 4.84 °.
According at least one embodiment of the application, the pedestal is hexahedron structure, and the hexahedral front-back is flat
Row, left and right face are parallel, and following face is parallel to the horizontal plane, and the front-back, left and right face are vertical with the lower surface；It is described
It is in predetermined angle between upper surface and the lower surface.
According at least one embodiment of the application, the predetermined angle is 8.73 °.
According at least one embodiment of the application, the upper surface of the pedestal offers multiple threaded holes, the multiple
Second mounting hole is connect with the multiple threaded hole by fixing bolt.
According at least one embodiment of the application, multiple pilot holes are provided on the upper surface of the pedestal.
According at least one embodiment of the application, the quantity of the pilot hole is four.
According at least one embodiment of the application, the quantity of second mounting hole and the quantity of the threaded hole are
8.
Tail slurry displacement fatigue experimental device provided by the embodiments of the present application, energy accurate simulation tail-rotor displacement ring fatigue test exist
Installation state on helicopter effectively examines the fatigue properties of tail-rotor displacement ring fatigue test.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of tail slurry displacement fatigue experimental device provided by the embodiments of the present application；
Fig. 2 is the structural schematic diagram of auricle component provided by the embodiments of the present application；
Fig. 3 is the structural schematic diagram of support base provided by the embodiments of the present application；
Fig. 4 is the structural schematic diagram of pedestal provided by the embodiments of the present application；
Fig. 5 is the structural schematic diagram of testpieces provided by the embodiments of the present application.
Wherein:
10, monaural component；11, support arm；12, auricle；13, connecting hole；20, support base；21, convex platform；22, lower convex platform；
23, the first mounting hole；24, the second mounting hole；30, pedestal；31, threaded hole；32, pilot hole；40, testpieces.
Specific embodiment
The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining related application, rather than the restriction to this application.It also should be noted that in order to
Convenient for description, part relevant to the application is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The application is described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
It should be noted that in the description of the present application, term " center ", "upper", "lower", "left", "right", " preceding ",
The direction of instructions such as " rear " or the term of positional relationship are direction based on the figure or positional relationship, this is just for the sake of just
In description, rather than indication or suggestion described device or element must have a particular orientation, constructed and grasped with specific orientation
Make, therefore should not be understood as the limitation to the application.In addition, term " first ", " second " are used for description purposes only, and cannot manage
Solution is indication or suggestion relative importance.
In addition it is also necessary to explanation, in the description of the present application unless specifically defined or limited otherwise, term " peace
Dress ", " setting ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.To those skilled in the art, it can understand that above-mentioned term exists as the case may be
Concrete meaning in the application.
Fig. 1 shows tail slurry displacement fatigue experimental device provided by the embodiments of the present application, and Fig. 5 shows the embodiment of the present application
The testpieces of offer, as shown in Figure 1 and Figure 5, tail slurry displacement fatigue experimental device include monaural component 10, support base 20 and pedestal
30, support base 20 is connect with pedestal 30, and testpieces 40 is set on support base 20, and connects monaural component 10, to simulate
The true installation position of testpieces 40 simultaneously carries out fatigue test to testpieces 40.
Fig. 2 shows auricle components 10 provided by the embodiments of the present application, as shown in Fig. 2, monaural component 10 includes mutually interconnecting
The support arm 11 and auricle 12 connect, optionally, the center line of the center line and auricle 12 of support arm 11 is located along the same line.
Connecting hole 13 is offered on auricle 12, and joint optionally is set in connecting hole 13 for joint test part 40
Bearing is connect by oscillating bearing with testpieces 40.
External screw thread has can be set in the other end of support arm 11, for connecting the system for generating active force.
Fig. 3 shows support base 20 provided by the embodiments of the present application, as shown in figure 3, support base 20 includes integrally formed
Convex platform 21 and lower convex platform 22 offer multiple first mounting holes 23 on convex platform 21, convex under for fixing testpieces 40
Multiple second mounting holes 24 are offered on platform 22, for connecting with pedestal 30.
Optionally, the center of the second mounting hole 24 and support base 20 is formed by straight line and adjacent the first nearest mounting hole
Angle between 23 includes but is not limited to 4.84 °, can also be that other angles, specific value can be come true according to actual needs
It is fixed.
Fig. 4 shows pedestal 30 provided by the embodiments of the present application, as shown in figure 4,30 hexahedron structures of pedestal, six face
The front-back of body is parallel, left and right face is parallel, and following face is parallel to the horizontal plane, and front-back, left and right face are vertical with lower surface.
It optionally, is in predetermined angle between upper surface and lower surface, which includes but is not limited to 8.73 °, may be used also
To be other angles, specific value can determine according to actual needs.
Offer multiple threaded holes 31 and multiple pilot holes 32 on the upper surface of pedestal 30, multiple second mounting holes 24 with
Multiple threaded holes 31 are connected by fixing bolt.Optionally, the quantity of the second mounting hole 24 and the quantity of threaded hole 31 are 8
It is a.Optionally, the quantity of pilot hole 32 is four, and is distributed in the four corners of 30 upper surface of pedestal.
The above, the only specific embodiment of the application, it is apparent to those skilled in the art that,
For convenience of description and succinctly, the system, module of foregoing description and the specific work process of unit can refer to preceding method
Corresponding process in embodiment, details are not described herein.It should be understood that the protection scope of the application is not limited thereto, it is any to be familiar with
Those skilled in the art within the technical scope of the present application, can readily occur in various equivalent modifications or substitutions,
These modifications or substitutions should all cover within the scope of protection of this application.
Claims (10)
1. a kind of tail slurry displacement fatigue experimental device, which is characterized in that including monaural component (10), support base (20) and pedestal
(30),
The monaural component (10) includes support arm interconnected (11) and auricle (12), offers connection on the auricle (12)
Hole (13) is used for joint test part (40)；
The support base (20) includes integrally formed convex platform (21) and lower convex platform (22), and the convex platform (21) is for fixing
The testpieces (40), the lower convex platform (22) connect with the pedestal (30)；
Angle between side that the pedestal (20) connect with the support base (20) and the other side corresponding thereto is in default
Angle.
2. tail slurry displacement fatigue experimental device according to claim 1, which is characterized in that the center line of the support arm (11)
It is located along the same line with the center line of the auricle (12).
3. tail slurry displacement fatigue experimental device according to claim 1, which is characterized in that opened up on the convex platform (21)
There are multiple first mounting holes (23), multiple second mounting holes (24), first mounting hole are offered on the lower convex platform (22)
(23) for connecting the testpieces (40), second mounting hole (24) with the pedestal (30) for connecting.
4. tail slurry displacement fatigue experimental device according to claim 3, which is characterized in that second mounting hole (24) with
The angle that the center of the support base (20) is formed by between straight line and adjacent nearest first mounting hole (23) is
4.84°。
5. tail slurry displacement fatigue experimental device according to claim 3, which is characterized in that the pedestal (30) is hexahedron
Structure, the hexahedral front-back is parallel, left and right face is parallel, and following face is parallel to the horizontal plane, and the front-back, left and right
Face is vertical with the lower surface；It is in predetermined angle between the upper surface and the lower surface.
6. tail slurry displacement fatigue experimental device according to claim 5, which is characterized in that the predetermined angle is 8.73 °.
7. tail slurry displacement fatigue experimental device according to claim 5, which is characterized in that the upper surface of the pedestal (30)
It offers multiple threaded holes (31), the multiple second mounting hole (24) and the multiple threaded hole (31) are connected by fixing bolt
It connects.
8. tail slurry displacement fatigue experimental device according to claim 7, which is characterized in that the upper surface of the pedestal (30)
On be provided with multiple pilot holes (32).
9. tail slurry displacement fatigue experimental device according to claim 8, which is characterized in that the quantity of the pilot hole (32)
It is four.
10. tail slurry displacement fatigue experimental device according to claim 7, which is characterized in that second mounting hole (24)
Quantity and the quantity of the threaded hole (31) be 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811340594.5A CN109506914B (en) | 2018-11-12 | 2018-11-12 | Tail stock pitch-changing fatigue test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811340594.5A CN109506914B (en) | 2018-11-12 | 2018-11-12 | Tail stock pitch-changing fatigue test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109506914A true CN109506914A (en) | 2019-03-22 |
| CN109506914B CN109506914B (en) | 2020-12-29 |
Family
ID=65748069
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811340594.5A Active CN109506914B (en) | 2018-11-12 | 2018-11-12 | Tail stock pitch-changing fatigue test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109506914B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110589025A (en) * | 2019-09-29 | 2019-12-20 | 中国直升机设计研究所 | Rotor transition shaft fixing device |
Citations (6)
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|---|---|---|---|---|
| CN104236880A (en) * | 2014-08-26 | 2014-12-24 | 中国直升机设计研究所 | Fatigue test device for torque arm assembly |
| CN104729846A (en) * | 2015-04-07 | 2015-06-24 | 中国直升机设计研究所 | Automatic inclinator nonrotating ring fatigue test device |
| CN106441857A (en) * | 2016-11-29 | 2017-02-22 | 中国直升机设计研究所 | Fatigue testing apparatus for mounting joint of damper post of main gear |
| CN207570917U (en) * | 2017-12-01 | 2018-07-03 | 中国直升机设计研究所 | Main hub branch brachiostrophosis load testing machine |
| CA3004224A1 (en) * | 2017-07-27 | 2018-07-11 | Airbus Helicopters Deutschland GmbH | A control transfer member for a pitch control device of a ducted rotorcraft tail rotor |
| CN108528737A (en) * | 2018-03-28 | 2018-09-14 | 合肥工业大学 | A kind of helicopter electric drive tail-rotor control system and method |
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2018
- 2018-11-12 CN CN201811340594.5A patent/CN109506914B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104236880A (en) * | 2014-08-26 | 2014-12-24 | 中国直升机设计研究所 | Fatigue test device for torque arm assembly |
| CN104729846A (en) * | 2015-04-07 | 2015-06-24 | 中国直升机设计研究所 | Automatic inclinator nonrotating ring fatigue test device |
| CN106441857A (en) * | 2016-11-29 | 2017-02-22 | 中国直升机设计研究所 | Fatigue testing apparatus for mounting joint of damper post of main gear |
| CA3004224A1 (en) * | 2017-07-27 | 2018-07-11 | Airbus Helicopters Deutschland GmbH | A control transfer member for a pitch control device of a ducted rotorcraft tail rotor |
| CN207570917U (en) * | 2017-12-01 | 2018-07-03 | 中国直升机设计研究所 | Main hub branch brachiostrophosis load testing machine |
| CN108528737A (en) * | 2018-03-28 | 2018-09-14 | 合肥工业大学 | A kind of helicopter electric drive tail-rotor control system and method |
Non-Patent Citations (1)
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| 张涛: "直升机重要改装设计疲劳评定符合性验证方法研究", 《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110589025A (en) * | 2019-09-29 | 2019-12-20 | 中国直升机设计研究所 | Rotor transition shaft fixing device |
| CN110589025B (en) * | 2019-09-29 | 2022-09-06 | 中国直升机设计研究所 | Rotor transition shaft fixing device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109506914B (en) | 2020-12-29 |
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