CN207570942U - A kind of tail undercarriage damper leg erection joint fatigue experimental device - Google Patents
A kind of tail undercarriage damper leg erection joint fatigue experimental device Download PDFInfo
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- CN207570942U CN207570942U CN201721655113.0U CN201721655113U CN207570942U CN 207570942 U CN207570942 U CN 207570942U CN 201721655113 U CN201721655113 U CN 201721655113U CN 207570942 U CN207570942 U CN 207570942U
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- connector
- erection joint
- load maintainer
- damper leg
- hold
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Abstract
The utility model is related to a kind of tail undercarriage damper leg erection joint fatigue experimental devices, belong to helicopter experimental technique field, including：It is fixed for simulating installing plate, the testpieces hold-down support, the load maintainer hold-down support for fixing load maintainer, the simulation connector for simulating the damper leg erection joint in real structure for fixed mounting plate of the installation state of connector test part for simulating the connector test part of mounting base at the tail undercarriage damper leg erection joint in actual airplane and connector test part, the load maintainer being set between simulation connector and load maintainer hold-down support, for generating the load for loading on simulation connector and connector test part.The fatigue experimental device of the utility model is simple and practical, processing and maintenance cost are relatively low, and can installation and stress of the accurate simulation tail undercarriage damper leg erection joint on helicopter, effectively examine the fatigue properties of tail undercarriage damper leg erection joint.
Description
Technical field
The utility model belongs to helicopter experimental technique field more particularly to a kind of tail undercarriage damper leg erection joint
Fatigue experimental device.
Background technology
Tail undercarriage is the important component of helicopter fuselage structure, it may ensure that the stabilization of helicopter ground taxi
Property, helicopter landing Impact energy is absorbed, reduces bump stroke, improves the safety of helicopter landing.Helicopter tail undercarriage
It is mainly made of components such as damper leg, distance-variable rocker arm and wheels, wherein damper leg is connect with distance-variable rocker arm by installation
Head is connect with body.Helicopter during landing, tail undercarriage stand under load change greatly, moment impact greatly, especially tail undercarriage
The stability of damper leg erection joint structural strength decides the length of helicopter tail undercarriage service life.Therefore, in order to
It determines the fatigue behaviour of tail undercarriage damper leg erection joint, so as to effective and rapid judges the use of helicopter tail undercarriage
Service life and time between overhauls(TBO), it is necessary to fatigue test be carried out to the erection joint of helicopter tail undercarriage damper leg, obtain its fatigue
Dangerous position and fatigue rupture pattern, the service life to determine tail undercarriage damper leg erection joint provide foundation.
At present, mainly exist not in boundary condition simulation etc. in tail undercarriage damper leg erection joint fatigue test
Foot, it is that there are no corresponding tail undercarriage damper leg erection joint fatigue experimental devices to trace it to its cause, it is impossible to it be carried out tired
Labor is tested.
Utility model content
The purpose of this utility model is to provide a kind of tail undercarriage damper leg erection joint fatigue experimental device, for solving
The certainly above problem.
In order to achieve the above objectives, the technical solution adopted in the utility model is：A kind of tail undercarriage damper leg installation connects
Head fatigue experimental device, including
Connector test part, the connector test part are used to simulate the tail undercarriage damper leg erection joint in actual airplane
Mounting base；
Installing plate, the installing plate have the grid beam identical with the grid beam of the erection joint installed position in actual airplane
Structure, connector test part are fixed for simulating the installation state of connector test part with installing plate；
Testpieces hold-down support, the hold-down support have and the matched stationary plane of the installing plate, the installing plate
It is fixed on hold-down support；
Load maintainer hold-down support, the load maintainer hold-down support are used to fix load maintainer；
Connector is simulated, simulation connector is used to simulate the damper leg erection joint in real structure, and simulation connector is connected to
Testpieces, simulation connector are connected to connector test part；
Load maintainer, load maintainer are set between simulation connector and load maintainer hold-down support, are loaded on for generating
Simulate the load of connector and connector test part.
Further, the installing plate includes upper mounting plate and lower installation board, and upper mounting plate and lower installation board are respectively with connecing
Head testpieces is fixed in two mounting surfaces at β angles.
Further, the load maintainer is applied to the active force of connector test part and the upper installation of anchor tip testpieces
Plate is in α angles.
Further, the load maintainer hold-down support has a regulating tank on the force direction, leads to
The bolt in secured adjusted slot is overregulated to adjust the angle of load maintainer.
Further, support device is further included, the support device is in the load maintainer, by adjusting support dress
It puts, the height of load maintainer hold-down support and testpieces hold-down support is applied to the active force angle of connector test part to adjust.
Further, it is described simulation connector in be equipped with oscillating bearing, for prevent loading play caused by simulation connector with
Connector test part is interfered.
Further, the load maintainer is loading actuator, and the loading actuator can export the loading of sine wave
Power.
The fatigue experimental device of the utility model is simple and practical, processing and maintenance cost are relatively low, and can accurate simulation tail rise
Installation and stress of the frame damper leg erection joint on helicopter are fallen, the installation of tail undercarriage damper leg is effectively examined to connect
The fatigue properties of head.
Description of the drawings
Attached drawing herein is incorporated into specification and forms the part of this specification, shows and meets the utility model
Embodiment, and for explaining the principle of the utility model together with specification.
Fig. 1 is the fatigue experimental device schematic diagram of the utility model.
Fig. 2 is the connector test part assembling schematic diagram of the utility model.
Fig. 3 is the load maintainer hold-down support schematic diagram schematic diagram of the utility model.
Specific embodiment
To make the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Attached drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the utility model.
Referring to shown in Fig. 1~Fig. 3, the tail undercarriage damper leg erection joint fatigue experimental device of this utility model connects
Fishplate bar 1, connector test part 7, simulation connector 2, load maintainer 5, testpieces hold-down support 4 and load maintainer hold-down support 3.
Connector test part 7 has two mounting surfaces, therefore connecting plate 1 includes upper junction plate 11 and lower connecting plate 12, connector examination
It tests part 1 to carry out riveting fixed composition connector test part component by rivet and upper junction plate 11 and lower connecting plate 12, be vertically connected with
Plate is formed similar to the grid beam structure on aircraft so as to the installation state of simulation test piece.
Connector test part 1 and upper junction plate 11 and lower connecting plate 12 assemble after component by multiple fixing bolts by connector
Testpieces assembling assembly is fixed on testpieces hold-down support 4.It is needed above testpieces hold-down support 4 with inclined-plane angle
Design it is at an angle β, it is identical with the angle on 8 two sides of upper junction plate 1 and lower connecting plate.Testpieces hold-down support 4 is fixed by bearing
Bolt assembly is fixed on comprehensive component fatigue testing stand.
Connector test part component is connected with simulating one end of connector 2, and the endoporus of simulation connector 2 places oscillating bearing, connector
For the outer diameter of testpieces component with oscillating bearing to matching, oscillating bearing can prevent the junction of simulation connector and connector test part
Stuck that structure is caused to be destroyed, the other end of simulation connector 2 is connected with load maintainer 5, and load maintainer 5 is by load maintainer hold-down support
3 are fixed in comprehensive component platform.Load maintainer is adjusted by the fixture accuracy of manufacture and vertical direction of testpieces hold-down support 4
The mounting height of load maintainer fixing bolt on hold-down support 3 eliminates fixture manufacturing process error, ensures that load maintainer adds
The end face for carrying direction and upper junction plate is at an angle, to meet experiment loading direction requirement.In addition, it also needs to add by test fixture
Work technique ensures that connector test part 7 is at an angle β with the assembling assembly bottom surface of upper junction plate 11 and lower connecting plate 12, and testpieces fixes branch
Above seat 4 and inclined-plane angle is β angles.Finally ensure that test load is accurately applied on damper leg erection joint testpieces.
In test, test load size is applied by load maintainer, and load maintainer can be actuator, by MTS
Coordinated loading control system is controlled, and exportable sine wave is loaded, and realizes feedback wave the methods of by adjusting PID
Shape and the preferable of target waveform coincide, and accurately apply load.In addition, it also needs to ensure that connector test part realizes that rigidity connects with each load maintainer
It connects, ensures the accuracy of posting.
The fatigue experimental device of the utility model is simple and practical, processing and maintenance cost are relatively low, and can accurate simulation tail rise
Installation and stress of the frame damper leg erection joint on helicopter are fallen, the installation of tail undercarriage damper leg is effectively examined to connect
The fatigue properties of head through result of the test verification and test data analyzer, obtain good effect.
The optimal specific embodiment of the above, only the utility model, but the scope of protection of the utility model is not
This is confined to, in the technical scope that any one skilled in the art discloses in the utility model, can be readily occurred in
Change or replacement, should be covered within the scope of the utility model.Therefore, the scope of protection of the utility model should be with
Subject to the scope of the claims.
Claims (7)
1. a kind of tail undercarriage damper leg erection joint fatigue experimental device, which is characterized in that the experimental rig includes
Connector test part, the connector test part are used to simulate the peace of the tail undercarriage damper leg erection joint in actual airplane
Fill seat；
Installing plate, the installing plate have the grid beam knot identical with the grid beam of the erection joint installed position in actual airplane
Structure, connector test part are fixed for simulating the installation state of connector test part with installing plate；
Testpieces hold-down support, the hold-down support has to be fixed with the matched stationary plane of the installing plate, the installing plate
In hold-down support；
Load maintainer hold-down support, the load maintainer hold-down support are used to fix load maintainer；
Connector is simulated, simulation connector is used to simulate the damper leg erection joint in real structure, and simulation connector is connected to experiment
Part, simulation connector are connected to connector test part；
Load maintainer, load maintainer are set between simulation connector and load maintainer hold-down support, and simulation is loaded on for generating
The load of connector and connector test part.
2. tail undercarriage damper leg erection joint fatigue experimental device according to claim 1, which is characterized in that described
Installing plate includes upper mounting plate and lower installation board, and upper mounting plate and lower installation board are in respectively two installations at β angles with connector test part
Face is fixed.
3. tail undercarriage damper leg erection joint fatigue experimental device according to claim 2, which is characterized in that described
The upper mounting plate of active force and anchor tip testpieces that load maintainer is applied to connector test part is in α angles.
4. tail undercarriage damper leg erection joint fatigue experimental device according to claim 3, which is characterized in that described
Load maintainer hold-down support has a regulating tank on the force direction, by adjusting the spiral shell in secured adjusted slot
Bolt adjusts the angle of load maintainer.
5. tail undercarriage damper leg erection joint fatigue experimental device according to claim 3, which is characterized in that also wrap
Include support device, the support device in the load maintainer, by adjusting supporting device, load maintainer hold-down support and
The height of testpieces hold-down support is applied to the active force angle of connector test part to adjust.
6. tail undercarriage damper leg erection joint fatigue experimental device according to claim 1, which is characterized in that described
It is interior equipped with oscillating bearing to simulate connector, for preventing from simulating connector and the interference of connector test part caused by loading play.
7. tail undercarriage damper leg erection joint fatigue experimental device according to claim 1, which is characterized in that described
Load maintainer is loading actuator, and the loading actuator can export the loading force of sine wave.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721655113.0U CN207570942U (en) | 2017-12-03 | 2017-12-03 | A kind of tail undercarriage damper leg erection joint fatigue experimental device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721655113.0U CN207570942U (en) | 2017-12-03 | 2017-12-03 | A kind of tail undercarriage damper leg erection joint fatigue experimental device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207570942U true CN207570942U (en) | 2018-07-03 |
Family
ID=62689677
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721655113.0U Active CN207570942U (en) | 2017-12-03 | 2017-12-03 | A kind of tail undercarriage damper leg erection joint fatigue experimental device |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109283042A (en) * | 2018-11-08 | 2019-01-29 | 上海赛飞航空线缆制造有限公司 | A kind of flexible cable is test bed |
| CN109506908A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test horizontal tail load charger |
| CN109506909A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test tail undercarriage load charger |
| CN109506911A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Load testing machine |
| CN112182756A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Fatigue test design method for main landing gear buffer strut joint |
| CN112591137A (en) * | 2020-11-13 | 2021-04-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Horizontal tail large shaft test device for airplane |
| CN114674548A (en) * | 2022-05-30 | 2022-06-28 | 中国飞机强度研究所 | Local vibration load applying system for airplane fatigue strength test and design method thereof |
-
2017
- 2017-12-03 CN CN201721655113.0U patent/CN207570942U/en active Active
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109283042B (en) * | 2018-11-08 | 2022-02-22 | 上海赛飞航空线缆制造有限公司 | Flexible cable test bench |
| CN109283042A (en) * | 2018-11-08 | 2019-01-29 | 上海赛飞航空线缆制造有限公司 | A kind of flexible cable is test bed |
| CN109506908A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test horizontal tail load charger |
| CN109506909A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test tail undercarriage load charger |
| CN109506911A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Load testing machine |
| CN109506909B (en) * | 2018-11-09 | 2020-08-14 | 中国直升机设计研究所 | Tail landing gear load loading device for fatigue test of tail section test piece |
| CN109506908B (en) * | 2018-11-09 | 2020-10-23 | 中国直升机设计研究所 | Tail end load loading device for fatigue test of tail section test piece |
| CN112182756A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Fatigue test design method for main landing gear buffer strut joint |
| CN112182756B (en) * | 2020-09-25 | 2022-09-06 | 中国直升机设计研究所 | Fatigue test design method for main landing gear buffer strut joint |
| CN112591137A (en) * | 2020-11-13 | 2021-04-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Horizontal tail large shaft test device for airplane |
| CN112591137B (en) * | 2020-11-13 | 2023-11-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane horizontal tail large shaft test device |
| CN114674548A (en) * | 2022-05-30 | 2022-06-28 | 中国飞机强度研究所 | Local vibration load applying system for airplane fatigue strength test and design method thereof |
| CN114674548B (en) * | 2022-05-30 | 2022-08-26 | 中国飞机强度研究所 | Local vibration load applying system for airplane fatigue strength test and design method thereof |
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