CN108100302A - A kind of helicopter tail rotor hub center dynamic response test exciting bank - Google Patents
A kind of helicopter tail rotor hub center dynamic response test exciting bank Download PDFInfo
- Publication number
- CN108100302A CN108100302A CN201711256529.XA CN201711256529A CN108100302A CN 108100302 A CN108100302 A CN 108100302A CN 201711256529 A CN201711256529 A CN 201711256529A CN 108100302 A CN108100302 A CN 108100302A
- Authority
- CN
- China
- Prior art keywords
- course
- rotor hub
- tail
- sliding
- hub center
- 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.)
- Granted
Links
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Measuring Pulse, Heart Rate, Blood Pressure Or Blood Flow (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention relates to a kind of helicopter tail rotor hub center dynamic response test exciting banks, belong to helicopter experimental technique field, blade bogusware 10 is installed on to the tail-rotor center of helicopter by the present invention, exporting steady-state sine load by hydraulic actuation cylinder can be completed the dynamic response test excitation loading of helicopter tail rotor hub center.The helicopter tail rotor hub center test installation for dynamic characteristics of the present invention can simulate centrifugation exciting force and steady-state sine excitation loading is carried out to tail-rotor hub, and course can be carried out in loading procedure, lateral, vertical three direction freely adjusts to meet tail-rotor hub center-driven loading position requirement.By tail propeller hub center dynamic response test, shake frequency vibration type and the response of tail boom can be measured, by the analysis to tail-rotor center Frequency Response, draws each rank mould of tail boom.
Description
Technical field
The invention belongs to helicopter tail rotor hub center dynamic response test technologies, are related to a kind of helicopter tail rotor hub center-driven
Load testing machine designs.
Background technology
Tail propeller hub center dynamic response test goes straight up to tail by measuring the dynamic characteristics at helicopter tail rotor hub center, acquisition
Propeller hub center course and vertical mode provide test basis for helicopter ground and ship resonance analysis.Ground and warship face are total to
The Producing reason that shakes is that there are two vibrational systems due to it：The vibrational system of rotor system and body on undercarriage.This two
A vibrational system is combined by propeller hub center, and ground and ship resonance may occur under certain condition.Ordinary circumstance
Ground and ship resonance do not occur for the shimmy firm type rotor of lower plane, and there are ground for shimmy softness heligyro only in plane
And ship resonance problem.So, only after tail-rotor is designed to shimmy soft rotor, it coupled with tail boom lower mode there is also
Ground and ship resonance problem.
At present, certain helicopter tail rotor is shimmy soft rotor, is needed to analyze it with the presence or absence of ground and ship resonance problem
Tail propeller hub center dynamic response test technical research is carried out to helicopter.And tail propeller hub center dynamic analysis is used more at this stage
The method of Finite Element Simulation Analysis does not have correlation test device and method.
The content of the invention
It is above-mentioned for solving the object of the present invention is to provide a kind of helicopter tail rotor hub center dynamic response test exciting bank
Problem.
In order to achieve the above objectives, the technical solution adopted by the present invention is：A kind of helicopter tail rotor hub center dynamic response test
Exciting bank loads the steady stimulation of tail-rotor hub for simulating centrifugation exciting force, including：
Frame, the frame upper and lower ends are respectively provided with the upper guide surface that can be oriented to and lower guide surface, it is described on
Guide surface is parallel with lower guide surface and upper guide surface and lower guide surface on be respectively equipped with the upper guide part being mutually parallel
With lower guide part, the setting direction of the upper guide part and lower guide part is lateral；
Course sliding beam, the course sliding beam is arranged in the upper guide surface and the course sliding beam being capable of edge
The upper guide part to adjust, and the sliding beam is equipped with sliding groove, the sliding groove opens up direction as course, the course
With it is described laterally horizontal；
Course sliding panel, the course sliding panel is arranged at the lower guide surface and the course sliding panel can be along
The lower guide part is adjusted, and the course sliding panel upper surface is equipped with lateral sliding part；
Lateral sliding plate, the lateral sliding plate are arranged at the course sliding panel upper surface and can be along the slips
Portion is adjusted；
Actuator, the actuator are vertically arranged in the frame, and actuator upper end is connected and leads to course sliding beam
It crosses anchor ear and is connected to the sliding groove, the anchor ear can be adjusted along the sliding groove and actuator lower end is fixed at
On the lateral sliding plate, to realize adjusting of the actuator on the lateral and course direction；And
Threaded adjusting bar and sensor, the adjusting rod and sensor be arranged at the actuator and blade testpieces it
Between, the threaded adjusting bar can be adjusted along the length on the threaded adjusting rod axis direction.
Further, the threaded adjusting bar has two-way regulating function.
Further, the sensor is force snesor, for measuring exciting force of the actuator to blade testpieces
Size.
Further, the actuator is hydraulic actuation cylinder.
Further, the sliding groove is rectangular channel.
The helicopter tail rotor hub central characteristics experiment exciting bank of the present invention can effectively simulate centrifugation exciting force to tail-rotor
Hub carries out steady-state sine excitation loading, can freely adjust to meet tail in course, lateral, vertical three direction in loading procedure
Propeller hub center excitation loading position requirement, has the advantages that simple in structure, multiple functional, simulation is accurate.
Description of the drawings
Attached drawing herein is merged in specification and forms the part of this specification, shows the implementation for meeting the present invention
Example, and the principle for explaining the present invention together with specification.
Fig. 1 is the helicopter tail rotor hub center dynamic response test exciting bank schematic diagram of the present invention.
Fig. 2 is frame and course sliding beam connection diagram in the present invention.
Fig. 3 is frame and course sliding panel and lateral sliding plate connection diagram in the present invention.
Fig. 4 is the helicopter tail rotor hub center dynamic response test exciting bank of the present invention and helicopter tail rotor hub connection signal
Figure.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.
The present invention, which provides a kind of helicopter tail rotor hub center dynamic response test exciting bank, can effectively simulate centrifugation exciting
Power carries out tail-rotor hub steady-state sine excitation loading, can be used for completing helicopter tail rotor hub center dynamic response test.
The helicopter tail rotor hub center dynamic response test exciting bank of the present invention centrifuges exciting force to tail-rotor hub for simulating
Steady stimulation loading, including：
Frame 1, the upper and lower ends of frame 1 are respectively provided with the upper guide surface 11 that can be oriented to and lower guide surface 12, on
Guide surface 11 is parallel with lower guide surface 12 and upper guide surface 11 and lower guide surface on 12 be respectively equipped with what is be mutually parallel
The setting direction of upper guide part 110 and lower guide part 120, upper guide part 110 and lower guide part 120 is lateral X.
Specific in embodiment, upper guide part 110 is the sliding slot muscle of two lateral adjustments, and lower guide part 120 is equipped with side
To the coulisse of slidable adjustment, sliding slot muscle, coulisse and frame plate are made up of the frame 1 of integral type welding manner, to protect
Demonstrate,prove the intensity of frame 1, frame 1 is logical can be crossed foundation bolt etc. and fix on the ground.
Course sliding beam 2, course sliding beam 2 is arranged in guide surface 11 and course sliding beam 2 can be along above leading
To 110 slidable adjustment of portion, and sliding beam 2 is equipped with sliding groove 21, and sliding groove 21 opens up direction as course Y, course Y and lateral X
Vertically.
Specific in embodiment, sliding groove 21 can be rectangular channel, facilitate installation.
Lateral sliding plate 3, lateral sliding plate 3 is arranged at lower guide surface 120 and lateral sliding plate 3 can be along lower guiding
120 slidable adjustment of portion, 3 upper surface of lateral sliding plate are equipped with the sliding part 31 of course Y.
Course sliding panel 4, course sliding panel 4 are arranged at the upper surface of lateral sliding plate 3 and can be adjusted along sliding part 31
Section.
Specific in the present invention, lower guide part 120 and sliding part 31 can be groove or slide muscle, portion with matching
Divide and be then changed to protrusion or sliding slot.
Actuator 5, actuator 5 are vertically arranged in frame 1, and the upper end of actuator 5 is connected and passes through with course sliding beam 2
Anchor ear is connected on sliding groove 21, and anchor ear can be fixed at boat along the lower end of 21 slidable adjustment of sliding groove and actuator 5
On sliding panel 4, to realize adjusting of the actuator 5 on lateral X and course Y-direction.Specific in embodiment, actuator is liquid
Press the exportable larger load of cylinder, and the sine of hydraulic actuation cylinder exportable stable state after connecting signal source in the present invention
Excitation load.
Threaded adjusting bar 6 and sensor 7, threaded adjusting bar 6 and sensor 7 are arranged at actuator 5 and blade testpieces 10
Between, threaded adjusting bar 6 can adjust the length on threadingly adjusting rod axis direction.In embodiment, sensor 7 can be
Force snesor or displacement sensor, it is therefore preferable to force snesor.And threaded adjusting bar 6 is a kind of bilaterally adjustable threaded rod,
After installation is complete according to connection status shown in figure, adjust threaded adjusting bar 6 and exciting bank can be realized in vertical direction
Position it is adjustable.
In addition, being equipped with swivel 8 between sensor 7 and blade testpieces 10, swivel 8 is forwarded dynamic for rolling fiducial axis
Connector, with certain posting ability and with preferable degree of freedom.
The handle 9 of adjusting is additionally provided in the present invention, and handle 9 is connected to lateral sliding plate 3 and course sliding panel
4, the transmission bar part of handle 4 can be equipped with threaded bar, and welding sets a nut on frame 1, and nut can be with handle 4
The cooperation of transmission bar part completed control lateral sliding plate 3 and course sliding panel 4 is slided respectively along sliding slot.
The experiment excitation of the present invention can be achieved to realize that course, lateral, vertical three direction freely adjust to meet tail-rotor
The requirement of hub center-driven loading position.
As shown in figure 4, blade bogusware 10 is installed on the tail-rotor center of helicopter, steady-state sine is exported by hydraulic actuation cylinder
The dynamic response test excitation loading of helicopter tail rotor hub center can be completed in load.
The helicopter tail rotor hub center test installation for dynamic characteristics of the present invention can simulate centrifugation exciting force and tail-rotor hub is carried out
Steady-state sine excitation loading, and course can be carried out in loading procedure, lateral, vertical three direction freely adjusts to meet tail-rotor
The requirement of hub center-driven loading position.By tail propeller hub center dynamic response test, shake frequency vibration type and the response of tail boom can be measured,
By the analysis to tail-rotor center Frequency Response, effective quantity of each rank mode of tail boom in tail propeller hub center is drawn, so as to be ground
And ship resonance analysis provides test basis.
The above is only the optimal specific embodiment of the present invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Subject to enclosing.
Claims (5)
1. a kind of helicopter tail rotor hub center dynamic response test exciting bank, for simulating stable state of the centrifugation exciting force to tail-rotor hub
Excitation loading, which is characterized in that the exciting bank includes：
Frame, the frame upper and lower ends are respectively provided with the upper guide surface that can be oriented to and lower guide surface, the upper guiding
Plane is parallel with lower guide surface and upper guide surface and lower guide surface on be respectively equipped with the upper guide part that is mutually parallel and under
The setting direction of guide part, the upper guide part and lower guide part is lateral；
Course sliding beam, the course sliding beam is arranged in the upper guide surface and the course sliding beam can be along institute
Guide part adjusting is stated, and the sliding beam is equipped with sliding groove, the sliding groove opens up direction as course, the course and institute
It states laterally horizontal；
Course sliding panel, the course sliding panel is arranged at the lower guide surface and the course sliding panel can be along described
Lower guide part is adjusted, and the course sliding panel upper surface is equipped with lateral sliding part；
Lateral sliding plate, the lateral sliding plate are arranged at the course sliding panel upper surface and can be along the sliding part tune
Section；
Actuator, the actuator are vertically arranged in the frame, and actuator upper end is connected with course sliding beam and by embracing
Hoop is connected to the sliding groove, and the anchor ear can be fixed at described along sliding groove adjusting and actuator lower end
On lateral sliding plate, to realize adjusting of the actuator on the lateral and course direction；And
Threaded adjusting bar and sensor, the adjusting rod and sensor are arranged between the actuator and blade testpieces, institute
Stating threaded adjusting bar can be adjusted along the length on the threaded adjusting rod axis direction.
2. helicopter tail rotor hub center dynamic response test exciting bank according to claim 1, which is characterized in that the spiral shell
Line adjusting rod has two-way regulating function.
3. helicopter tail rotor hub center dynamic response test exciting bank according to claim 1, which is characterized in that the biography
Sensor is force snesor, for measuring size of the actuator to the exciting force of blade testpieces.
4. helicopter tail rotor hub center dynamic response test exciting bank according to claim 1, which is characterized in that the work
Dynamic device is hydraulic actuation cylinder.
5. helicopter tail rotor hub center dynamic response test exciting bank according to claim 1, which is characterized in that the cunning
Dynamic slot is rectangular channel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711256529.XA CN108100302B (en) | 2017-12-03 | 2017-12-03 | Experimental excitation device of heart characteristic in helicopter tail-rotor hub |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711256529.XA CN108100302B (en) | 2017-12-03 | 2017-12-03 | Experimental excitation device of heart characteristic in helicopter tail-rotor hub |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108100302A true CN108100302A (en) | 2018-06-01 |
| CN108100302B CN108100302B (en) | 2021-06-11 |
Family
ID=62209013
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711256529.XA Active CN108100302B (en) | 2017-12-03 | 2017-12-03 | Experimental excitation device of heart characteristic in helicopter tail-rotor hub |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108100302B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110654568A (en) * | 2019-09-29 | 2020-01-07 | 中国直升机设计研究所 | Hub couple loading device |
| CN110884682A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Ground test system for actively controlling multidirectional vibration reduction efficiency by helicopter vibration |
| CN112478192A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Full-mechanical static test loading rack of small-load helicopter |
| CN113173261A (en) * | 2021-04-20 | 2021-07-27 | 中国直升机设计研究所 | Composite loading field checking device and method for rotor wing balance loading test bed |
| CN113310695A (en) * | 2021-05-28 | 2021-08-27 | 中国商用飞机有限责任公司 | Aircraft engine windmill load ground simulation method and system |
| CN114166489A (en) * | 2021-11-23 | 2022-03-11 | 中国直升机设计研究所 | Loading test device of rigid main propeller hub connecting piece |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203178051U (en) * | 2012-12-31 | 2013-09-04 | 浙江工业大学 | Ultralow-frequency modal test gravitational equilibrium system |
| CN104034501A (en) * | 2014-06-24 | 2014-09-10 | 中国飞机强度研究所 | Aircraft rear body dynamic load follow-up loading testing device |
| FR2987348B1 (en) * | 2012-02-24 | 2014-11-21 | Airbus Operations Sas | DEVICE FOR SUSPENSION ABOVE THE FLOOR OF AN AIRCRAFT LANDING TRAIN AND SUSPENSION SYSTEM ABOVE THE GROUND OF AN AIRCRAFT COMPRISING SUCH A DEVICE. |
| CN104765976A (en) * | 2015-04-27 | 2015-07-08 | 中国直升机设计研究所 | Carrier-based helicopter ship surface propeller hub center dynamic characteristic modeling method |
| CN205449501U (en) * | 2016-03-31 | 2016-08-10 | 中航商用航空发动机有限责任公司 | Wing excitation analogue means |
| CN106596023A (en) * | 2016-11-29 | 2017-04-26 | 中国直升机设计研究所 | Helicopter real vibration environment simulation test system |
| CN206258238U (en) * | 2016-12-19 | 2017-06-16 | 华东交通大学 | A kind of three coordinate adjustable exciting experiment porch |
-
2017
- 2017-12-03 CN CN201711256529.XA patent/CN108100302B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2987348B1 (en) * | 2012-02-24 | 2014-11-21 | Airbus Operations Sas | DEVICE FOR SUSPENSION ABOVE THE FLOOR OF AN AIRCRAFT LANDING TRAIN AND SUSPENSION SYSTEM ABOVE THE GROUND OF AN AIRCRAFT COMPRISING SUCH A DEVICE. |
| CN203178051U (en) * | 2012-12-31 | 2013-09-04 | 浙江工业大学 | Ultralow-frequency modal test gravitational equilibrium system |
| CN104034501A (en) * | 2014-06-24 | 2014-09-10 | 中国飞机强度研究所 | Aircraft rear body dynamic load follow-up loading testing device |
| CN104765976A (en) * | 2015-04-27 | 2015-07-08 | 中国直升机设计研究所 | Carrier-based helicopter ship surface propeller hub center dynamic characteristic modeling method |
| CN205449501U (en) * | 2016-03-31 | 2016-08-10 | 中航商用航空发动机有限责任公司 | Wing excitation analogue means |
| CN106596023A (en) * | 2016-11-29 | 2017-04-26 | 中国直升机设计研究所 | Helicopter real vibration environment simulation test system |
| CN206258238U (en) * | 2016-12-19 | 2017-06-16 | 华东交通大学 | A kind of three coordinate adjustable exciting experiment porch |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110654568A (en) * | 2019-09-29 | 2020-01-07 | 中国直升机设计研究所 | Hub couple loading device |
| CN110884682A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Ground test system for actively controlling multidirectional vibration reduction efficiency by helicopter vibration |
| CN112478192A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Full-mechanical static test loading rack of small-load helicopter |
| CN113173261A (en) * | 2021-04-20 | 2021-07-27 | 中国直升机设计研究所 | Composite loading field checking device and method for rotor wing balance loading test bed |
| CN113310695A (en) * | 2021-05-28 | 2021-08-27 | 中国商用飞机有限责任公司 | Aircraft engine windmill load ground simulation method and system |
| CN113310695B (en) * | 2021-05-28 | 2023-01-31 | 中国商用飞机有限责任公司 | Aircraft engine windmill load ground simulation method and system |
| CN114166489A (en) * | 2021-11-23 | 2022-03-11 | 中国直升机设计研究所 | Loading test device of rigid main propeller hub connecting piece |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108100302B (en) | 2021-06-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108100302A (en) | A kind of helicopter tail rotor hub center dynamic response test exciting bank | |
| CN102680215B (en) | Wind turbine blade tester | |
| CN105606357B (en) | A kind of aircraft test of static strength loading device | |
| CN101726401A (en) | Scale measuring device for pitching dynamic derivative experiment | |
| CN101561339B (en) | System for dynamically detecting stiffness parameters of closed-loop diagonal-bracing type vehicle bogies | |
| CN207570917U (en) | Main hub branch brachiostrophosis load testing machine | |
| CN204831774U (en) | Loading device | |
| CN104266910A (en) | Method and device for loading fatigue test force | |
| CN109359321A (en) | A kind of lightweight connecting hinge optimization method of topological optimization in conjunction with lattice structure | |
| CN105190284A (en) | Resonance generating apparatus with reduced side loads for a blade's fatigue testing | |
| CN105216998B (en) | A kind of marine propeller for reducing noise | |
| CN109737168A (en) | A kind of quasi-zero stiffness vibration isolators | |
| CN203798658U (en) | High-voltage servo true three-axis testing machine | |
| CN102991725A (en) | Pole restraint device | |
| CN106768816A (en) | A kind of pitching dynamic derivative experimental provision of tail vibration | |
| CN106568583A (en) | Foldable strut flexibility measurement device and method for airplane main undercarriage | |
| CN205719460U (en) | A kind of Ship Structure impact test system | |
| CN108680961B (en) | Unmanned aerial vehicle transient electromagnetic probe carrying device and carrying method | |
| CN109094815A (en) | Aircraft vertical stabilization and fuselage bonding strength test support system | |
| CN204530480U (en) | Faulting of slab ends adjusting device | |
| CN108036916B (en) | A kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model | |
| CN206648802U (en) | A kind of pitching dynamic derivative experimental provision of tail vibration | |
| CN204964311U (en) | Synchronous loading device of multiple spot of vertical curvature effect of multi -chambered case roof beam | |
| CN104792490A (en) | External store side-sway frequency and yaw frequency decoupling device of wind tunnel flutter model | |
| CN206373635U (en) | A kind of gear pump rear cover hydraulic fluid port auxiliary drilling tool |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |