CN108100302B - Experimental excitation device of heart characteristic in helicopter tail-rotor hub - Google Patents
Experimental excitation device of heart characteristic in helicopter tail-rotor hub Download PDFInfo
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- CN108100302B CN108100302B CN201711256529.XA CN201711256529A CN108100302B CN 108100302 B CN108100302 B CN 108100302B CN 201711256529 A CN201711256529 A CN 201711256529A CN 108100302 B CN108100302 B CN 108100302B
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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
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- Aviation & Aerospace Engineering (AREA)
- Measuring Pulse, Heart Rate, Blood Pressure Or Blood Flow (AREA)
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Abstract
The invention relates to a test excitation device for the cardiac characteristics in a helicopter tail rotor hub, which belongs to the technical field of helicopter tests. The device for testing the central dynamic characteristics of the helicopter tail rotor hub can simulate centrifugal exciting force to carry out steady-state sinusoidal exciting loading on the tail rotor hub, and can carry out free adjustment in three directions of course direction, lateral direction and vertical direction in the loading process so as to meet the requirement of the central exciting loading position of the tail rotor hub. Through a test of the central cardiac characteristics of the hub of the tail rotor, the vibration frequency mode and the response of the tail beam can be measured, and through the analysis of the central frequency response characteristics of the tail rotor, each order mode of the tail beam is obtained.
Description
Technical Field
The invention belongs to a helicopter tail rotor hub center dynamic characteristic test technology, and relates to a design of a helicopter tail rotor hub center excitation loading test device.
Background
In the test of the central cardiac characteristics of the tail rotor hub, the central course and the vertical mode of the tail rotor hub of the helicopter are obtained by measuring the dynamic characteristics at the center of the tail rotor hub of the helicopter, so that a test basis is provided for the ground and ship surface resonance analysis of the helicopter. The ground and ship surface resonance is caused because of the existence of two vibration systems: a rotor system and a vibration system of the body on the undercarriage. The two vibration systems are combined through the center of the propeller hub, and ground and ship surface resonance can occur under certain conditions. Under the general condition, the plane shimmy rigid rotor does not generate ground and ship surface resonance, and only the plane internal shimmy soft rotor helicopter has the ground and ship surface resonance problem. Then, only after the tail rotor is designed into a shimmy soft rotor, the tail rotor is coupled with a tail beam in a low-order mode, and the ground and ship surface resonance problem also exists.
At present, a tail rotor of a certain helicopter is a shimmy soft rotor, and the technical research of the cardiac characteristic test in a tail rotor hub of the helicopter is needed to analyze whether the helicopter has ground and ship surface resonance problems. At present, a finite element simulation analysis method is adopted for researching the cardiac characteristics in the tail rotor hub, and no relevant test device or method exists.
Disclosure of Invention
The invention aims to provide a device for exciting a test of the cardiac characteristics in a helicopter tail rotor hub, which is used for solving the problems.
In order to achieve the purpose, the invention adopts the technical scheme that: a test excitation device for cardiac characteristics in a helicopter tail rotor hub is used for simulating steady-state excitation loading of centrifugal excitation force on the tail rotor hub, and comprises:
the upper end and the lower end of the frame are respectively provided with an upper guide plane and a lower guide plane which can be guided, the upper guide plane and the lower guide plane are parallel, the upper guide plane and the lower guide plane are respectively provided with an upper guide part and a lower guide part which are parallel to each other, and the arrangement direction of the upper guide part and the lower guide part is a side direction;
the course sliding beam is arranged on the upper guide plane and can be adjusted along the upper guide part, the sliding beam is provided with a sliding groove, the opening direction of the sliding groove is the course, and the course is vertical to the lateral direction;
a lateral sliding plate which is arranged on the lower guide plane and can be adjusted along the lower guide part, wherein the upper surface of the lateral sliding plate is provided with a lateral sliding part;
a course sliding plate which is arranged on the upper surface of the lateral sliding plate and can be adjusted along the sliding part;
the actuator is vertically arranged in the frame, the upper end of the actuator is connected with the course sliding beam and is connected with the sliding groove through a hoop, the hoop can be adjusted along the sliding groove, and the lower end of the actuator is fixedly arranged on the course sliding plate so as to realize the adjustment of the actuator in the lateral direction and the course direction; and
the screw thread adjusting rod and the sensor are arranged between the actuator and the blade test piece, and the length of the screw thread adjusting rod in the axial direction can be adjusted by the screw thread adjusting rod.
Furthermore, the threaded adjusting rod has a bidirectional adjusting function.
Further, the sensor is a force sensor and is used for measuring the exciting force of the actuator on the blade test piece.
Further, the actuator is a hydraulic cylinder.
Further, the sliding groove is a rectangular groove.
The helicopter tail rotor hub central characteristic test excitation device can effectively simulate centrifugal excitation force to carry out steady-state sinusoidal excitation loading on the tail rotor hub, can be freely adjusted in three directions of course direction, lateral direction and vertical direction in the loading process to meet the requirement of a tail rotor hub central excitation loading position, and has the advantages of simple structure, complete functions and accurate simulation.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.
Fig. 1 is a schematic diagram of a test excitation device for the cardiac characteristics of a helicopter tail rotor hub.
FIG. 2 is a schematic view of the connection between the frame and the course sliding beam according to the present invention.
FIG. 3 is a schematic view of the frame of the present invention coupled to a course slide and a lateral slide.
Fig. 4 is a schematic view of the connection of the excitation device for testing the cardiac characteristics of the helicopter tail hub and the helicopter tail hub.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention.
The invention provides an excitation device for a test of the central cardiac characteristics of a helicopter tail rotor hub, which can effectively simulate centrifugal exciting force to carry out steady-state sinusoidal excitation loading on the tail rotor hub and can be used for completing the test of the central cardiac characteristics of the helicopter tail rotor hub.
The invention relates to a test excitation device for the cardiac characteristics of a helicopter tail rotor hub, which is used for simulating the steady-state excitation loading of centrifugal excitation force on the tail rotor hub, and comprises the following components:
the frame 1, the upper and lower both ends of frame 1 have upper guide plane 11 and lower guide plane 12 that can lead respectively, and upper guide plane 11 and lower guide plane 12 are parallel and upper guide plane 11 and lower guide plane are last 12 respectively to be equipped with parallel upper guide part 110 and lower guide part 120, and the direction of setting up of upper guide part 110 and lower guide part 120 is side direction X.
Specifically, in the embodiment, the upper guide portion 110 is two sliding groove ribs laterally adjusted, the lower guide portion 120 is a sliding groove plate provided with a lateral sliding adjustment, the sliding groove ribs, the sliding groove plate and the frame plate form an integrated frame 1 in a welding mode, so as to ensure the strength of the frame 1, and the frame 1 can be fixed on the ground through anchor bolts and the like.
The device comprises a course sliding beam 2, wherein the course sliding beam 2 is arranged on an upper guide plane 11, the course sliding beam 2 can be adjusted in a sliding mode along an upper guide part 110, a sliding groove 21 is formed in the sliding beam 2, the opening direction of the sliding groove 21 is a course Y, and the course Y is perpendicular to the lateral direction X.
In the embodiment, the sliding groove 21 may be a rectangular groove, which facilitates installation.
And the lateral sliding plate 3, the lateral sliding plate 3 is arranged on the lower guide plane 120, the lateral sliding plate 3 can be slidably adjusted along the lower guide part 120, and the upper surface of the lateral sliding plate 3 is provided with a sliding part 31 with a heading Y.
And a course sliding plate 4, wherein the course sliding plate 4 is arranged on the upper surface of the lateral sliding plate 3 and can be adjusted along the sliding part 31.
Specifically, in the present invention, the lower guide portion 120 and the sliding portion 31 may be grooves or sliding ribs, and the portions engaged with the grooves or sliding ribs are protrusions or sliding grooves.
The length of the screw thread adjusting rod 6 in the axial direction can be adjusted by the screw thread adjusting rod 6, the sensor 7 and the screw thread adjusting rod 6 are arranged between the actuator 5 and the blade test piece 10, and the length of the screw thread adjusting rod 6 in the axial direction can be adjusted. In an embodiment, the sensor 7 may be a force sensor or a displacement sensor, preferably a force sensor. And the thread adjusting rod 6 is a threaded rod which can be adjusted in two directions, and after the installation is finished according to the connection state shown in the figure, the position of the excitation device in the vertical direction can be adjusted by adjusting the thread adjusting rod 6.
In addition, a rotating joint 8 is arranged between the sensor 7 and the blade test piece 10, and the rotating joint 8 is a rolling bearing rotating joint and has certain load transfer capacity and good degree of freedom.
The invention is also provided with a handle 9 for adjustment, the handle 9 is respectively connected with the lateral sliding plate 3 and the heading sliding plate 4, the transmission rod part of the handle 4 can be a rod with screw threads, and a nut is welded on the frame 1 and can be matched with the transmission rod part of the handle 4 to control the lateral sliding plate 3 and the heading sliding plate 4 to respectively slide along the sliding chutes.
The experimental excitation of the invention can realize free adjustment in three directions of course, side direction and vertical direction so as to meet the requirement of the central excitation loading position of the tail rotor hub.
As shown in FIG. 4, the blade dummy 10 is installed at the center of the tail rotor of the helicopter, and the excitation loading of the cardiac characteristic test in the tail rotor hub of the helicopter can be completed by outputting a steady-state sinusoidal load through a hydraulic actuating cylinder.
The device for testing the central dynamic characteristics of the helicopter tail rotor hub can simulate centrifugal exciting force to carry out steady-state sinusoidal exciting loading on the tail rotor hub, and can carry out free adjustment in three directions of course direction, lateral direction and vertical direction in the loading process so as to meet the requirement of the central exciting loading position of the tail rotor hub. Through a test of the cardiac characteristics in the hub of the tail rotor, the vibration frequency vibration mode and the response of the tail beam can be measured, and through the analysis of the central frequency response characteristics of the tail rotor, the effective amount of each order mode of the tail beam in the center of the hub of the tail rotor is obtained, so that a test basis is provided for the ground and ship surface resonance analysis.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (5)
1. A test excitation device for cardiac characteristics in a tail rotor hub of a helicopter, which is used for simulating steady-state excitation loading of centrifugal excitation force on the tail rotor hub, and is characterized by comprising:
the upper end and the lower end of the frame are respectively provided with an upper guide plane and a lower guide plane which can be guided, the upper guide plane and the lower guide plane are parallel, the upper guide plane and the lower guide plane are respectively provided with an upper guide part and a lower guide part which are parallel to each other, and the arrangement direction of the upper guide part and the lower guide part is a side direction;
the course sliding beam is arranged on the upper guide plane and can be adjusted along the upper guide part, the sliding beam is provided with a sliding groove, the opening direction of the sliding groove is the course, and the course is vertical to the lateral direction;
a lateral sliding plate which is arranged on the lower guide plane and can be adjusted along the lower guide part, wherein the upper surface of the lateral sliding plate is provided with a lateral sliding part;
a course sliding plate which is arranged on the upper surface of the lateral sliding plate and can be adjusted along the sliding part;
the actuator is vertically arranged in the frame, the upper end of the actuator is connected with the course sliding beam and is connected with the sliding groove through a hoop, the hoop can be adjusted along the sliding groove, and the lower end of the actuator is fixedly arranged on the course sliding plate so as to realize the adjustment of the actuator in the lateral direction and the course direction; and
the screw thread adjusting rod and the sensor are arranged between the actuator and the blade test piece, and the length of the screw thread adjusting rod in the axial direction can be adjusted by the screw thread adjusting rod.
2. The helicopter tail rotor hub cardiogenic characteristic test excitation device of claim 1, characterized in that the threaded adjustment rod has a bidirectional adjustment function.
3. A test excitation device for cardiac characteristics in a helicopter tail rotor hub according to claim 1 wherein said sensor is a force sensor for measuring the magnitude of the excitation force of said actuator on said blade test piece.
4. A helicopter tail rotor hub according to claim 1 wherein said actuator is a hydraulic cylinder.
5. A helicopter tail rotor hub according to claim 1 wherein said sliding slots are rectangular slots.
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 |
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| 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 |
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| CN108100302A CN108100302A (en) | 2018-06-01 |
| CN108100302B true CN108100302B (en) | 2021-06-11 |
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| CN201711256529.XA Active CN108100302B (en) | 2017-12-03 | 2017-12-03 | Experimental excitation device of heart characteristic in helicopter tail-rotor hub |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110654568B (en) * | 2019-09-29 | 2022-09-06 | 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 |
| CN112478192B (en) * | 2020-10-30 | 2022-10-18 | 中国直升机设计研究所 | Full-mechanical static test loading rack of small-load helicopter |
| CN113173261B (en) * | 2021-04-20 | 2022-10-18 | 中国直升机设计研究所 | Composite loading field checking device and method for rotor wing balance loading test bed |
| 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 |
| CN114166489B (en) * | 2021-11-23 | 2023-06-27 | 中国直升机设计研究所 | Loading test device for rigid main hub connector |
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| 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 |
| 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 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
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- 2017-12-03 CN CN201711256529.XA patent/CN108100302B/en active Active
Patent Citations (6)
| 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 |
| 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 |
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