CN106828973B - Propeller centrifugal load test device - Google Patents
Propeller centrifugal load test device Download PDFInfo
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- CN106828973B CN106828973B CN201710073452.6A CN201710073452A CN106828973B CN 106828973 B CN106828973 B CN 106828973B CN 201710073452 A CN201710073452 A CN 201710073452A CN 106828973 B CN106828973 B CN 106828973B
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Abstract
The invention provides a propeller centrifugal load test device which comprises a load applying device and a force bearing mechanism, wherein the load applying device is arranged in a propeller hub and is in a regular polygon shape, the axis of each blade is perpendicular to the side wall, closest to the blade, of the load applying device, an oil cavity is formed in each side wall of the polygon of the load applying device, a rodless piston is arranged in each oil cavity, an oil inlet and an oil inlet channel are formed in the load applying device, and the oil cavity is communicated with the oil inlet through the oil inlet channel; the bearing mechanism comprises a first bearing component and a second bearing component, the first bearing component is arranged in the propeller hub, one end of the first bearing component, which is far away from the propeller blade, is contacted with the rodless piston, the other end of the first bearing component is contacted with the second bearing component, the end surface of one point of the two ends is a spherical surface, the second bearing component is fixed in the propeller blade, and the second bearing component is provided with a strain gauge.
Description
Technical Field
The invention relates to the technical field of propeller tests, in particular to a propeller centrifugal load test device.
Background
In order to test the static force and the fatigue strength of the propeller hub of the airplane propeller, the static force and the fatigue test of the propeller hub are required. The rotor hub is subjected to centrifugal forces from the blades during operation and also to aerodynamic loads generated by the blades. In order to ensure the safety of the airplane, the load is simulated under the test condition for testing, and the safety life is given.
In structural static force and fatigue tests, in order to simulate the centrifugal force load generated by the propeller blades in the rotating process, a radial load is generally applied to the simulated blades in the centrifugal force load direction, and a load applying device is connected with a loading actuator at the radial outer side of the simulated blades.
The prior art centrifugal load test apparatus has the following disadvantages:
1. the centrifugal load and the pneumatic load can be mutually interfered, and because the load acted on the propeller hub has the pneumatic load besides the centrifugal load and the loading position is close, if the mutual interference is generated, the applied load error is large, and the load needs to be repeatedly calibrated for many times before the test;
2. when one side of the test piece is damaged and can not bear centrifugal load continuously, the hub is fixed on the base platform through the connecting piece, so that the load on the other side can not be unloaded immediately, and the centrifugal load can cause secondary damage to the test piece.
Disclosure of Invention
In order to overcome at least one defect in the prior art, the invention provides a propeller centrifugal load test device, wherein the propeller comprises a propeller hub, a plurality of blades are circumferentially arranged on the outer side of the propeller hub, and the blades are connected with the propeller hub through propeller sleeves;
the centrifugal load test device comprises a load applying device and a force bearing mechanism;
the load applying device is arranged in the propeller hub, the load applying device is in a regular polygon shape, the axis of each blade is perpendicular to the side wall, closest to the blade, of the load applying device, when the propeller has two blades, the load applying device preferably adopts a quadrilateral shape, each side wall corresponds to one blade in two opposite side walls in the quadrilateral shape, when the propeller has three or more blades, the number of the sides of the load applying device is the same as that of the blades, and the axis of each blade is perpendicular to the polygonal side wall corresponding to the blade; each side wall of the polygonal side wall of the load applying device is provided with an oil cavity, each oil cavity is equivalent to a groove on the side wall, each oil cavity is internally provided with a rodless piston, an oil inlet and an oil inlet channel are arranged in the load applying device, the oil inlet is communicated with the oil inlet, the oil cavity is communicated with the oil inlet through the oil inlet channel, oil at the oil inlet is conveyed to the oil cavity through the oil inlet channel, and the rodless piston is extruded to serve as a load applying source;
the force-bearing mechanism comprises a first force-bearing member and a second force-bearing member, the first force-bearing member is arranged in the propeller hub, one end of the first force-bearing member, which is far away from the blade, is contacted with the rodless piston, one end of the first force-bearing member, which is close to the blade, is contacted with the second force-bearing member, the end surface of the first force-bearing member, which is far away from one end of the blade or close to one end of the blade, is a spherical surface, the spherical surface allows the second force-bearing member and the load applying device to slightly rotate, and the first force-bearing member is used for transmitting the centrifugal load from the load applying source to the blade; the second bearing component is fixed inside the paddle and provided with a strain gauge, and the magnitude of the applied load is adjusted through data fed back by the strain gauge.
Preferably, the second force-bearing component comprises a top rod and a locking rod, one end of the top rod, which is close to the hub, is in contact with the first force-bearing component, one end of the top rod, which is far from the hub, is in contact with the locking rod, and the locking rod is fixed with the blade, i.e., the load is sequentially transmitted to the top rod and the locking rod through the first force-bearing component and finally transmitted to the blade through the locking rod; the strain gauge is arranged on the side wall of the ejector rod.
Preferably, the locking rod is fixed with the blade in a threaded connection mode.
Preferably, the first force-bearing member is spherical as a whole, that is, both the end of the first force-bearing member close to the blade and the end of the first force-bearing member far from the blade are spherical, so that the relative rotation between the load applying device and the blade can be allowed to the maximum extent, that is, the influence of the aerodynamic load on the centrifugal load can be eliminated to the maximum extent.
The invention provides a propeller centrifugal load test device, which has the following beneficial effects:
1. the centrifugal load loading point is changed into loading inside the hub, and the load applying device can simultaneously load and unload a plurality of paddle sleeve directions.
2. The centrifugal load loading point is far away from the pneumatic load loading point, and the centrifugal load and the pneumatic load are not influenced mutually.
3. The bearing ball enables the rodless piston to only bear centrifugal load, and the influence of bending moment formed by pneumatic load on the centrifugal load test device is eliminated.
4. When the propeller is damaged and one direction can not continuously bear the centrifugal load, the centrifugal load applied in other directions can be immediately unloaded, and secondary damage to the test piece can not be caused.
Drawings
FIG. 1 is a schematic structural diagram of a propeller centrifugal load test device;
fig. 2 is a schematic structural view of a load applying device in the propeller centrifugal load test device.
Reference numerals: the structure comprises a propeller hub 1, a propeller sleeve 2, blades 3, a load applying device 4, an oil inlet 5, an oil inlet channel 6, an oil cavity 7, a rodless piston 8, a first force bearing component 9, a top rod 10, a locking rod 11 and a strain gauge 12.
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. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings, which are used for convenience in describing the invention and for simplicity in description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the scope of the invention.
The following describes a propeller centrifugal load test device provided by the invention with reference to the accompanying drawings.
As shown in FIG. 1, the invention provides a centrifugal load test device for a propeller, wherein the propeller comprises a hub 1, a plurality of blades 3 are circumferentially arranged on the outer side of the hub 1, and the blades 3 are connected with the hub 1 through sleeves 2;
the centrifugal load test device comprises a load applying device 4 and a bearing mechanism;
as shown in fig. 2, the load applying devices 4 are arranged inside the hub 1, the load applying devices 4 are in the shape of a regular polygon, the axis of each blade 3 is perpendicular to the side wall of the load applying device 4 closest to the blade 3, when the propeller has two blades 3, the load applying devices 4 preferably take the shape of a quadrangle, of two opposite side walls in the quadrangle, each side wall corresponds to one blade 3, when the propeller has three or more blades 3, the number of sides of the load applying devices 4 is the same as the number of blades 3, and the axis of each blade 3 is perpendicular to the corresponding polygonal side wall; an oil cavity 7 is formed in each side wall of the polygonal side wall of the load applying device 4, the oil cavity 7 is equivalent to a groove in the side wall, a rodless piston 8 is arranged in each oil cavity 7, an oil inlet 5 and an oil inlet channel 6 are arranged in the load applying device 4, the oil inlet 5 is communicated with the oil inlet channel 6, the oil cavity 7 is communicated with the oil inlet 5 through the oil inlet channel 6, oil at the oil inlet 5 is conveyed to the oil cavity 7 through the oil inlet channel 6, and the rodless piston 8 is extruded to serve as a load applying source;
the bearing mechanism comprises a first bearing component 9 and a second bearing component.
As shown in fig. 1, the first force-bearing member 9 is spherical as a whole, i.e. a force-bearing ball, the first force-bearing member 9 is arranged inside the hub 1, one end of the first force-bearing member 9 away from the blade 3 contacts with the rodless piston 8, one end of the first force-bearing member 9 close to the blade 3 contacts with the second force-bearing member, i.e. both the end of the first force-bearing member 9 close to the blade 3 and the end of the first force-bearing member away from the blade 3 are spherical, so that the relative rotation between the load applying device 4 and the blade 3 can be allowed to the maximum extent, i.e. the influence of the aerodynamic load on the centrifugal load can be eliminated to the maximum extent, and the first force-bearing member 9 is used for transmitting the centrifugal load from the load applying source to the blade 3;
the second force-bearing component is fixed inside the blade 3 and comprises a top rod 10 and a locking rod 11, one end of the top rod 10 close to the hub 1 is in contact with the first force-bearing component 9, one end of the top rod 10 far away from the hub 1 is in contact with the locking rod 11, the locking rod 11 is fixed with the blade 3 in a threaded connection mode, and the locking rod 11 moves together with the blade 3 in the axial direction of the blade 3, namely, the load is sequentially transmitted to the top rod 10 and the locking rod 11 through the first force-bearing component 9 and finally transmitted to the blade 3 through the locking rod 11; the second force bearing component is provided with a strain gauge 12, the strain gauge 12 is arranged on the side wall of the ejector rod 10, and the magnitude of the applied load is adjusted through data fed back by the strain gauge 12.
The present invention is described in further detail below by way of specific examples.
The specific embodiment is as follows:
as shown in fig. 1 and 2, when a propeller centrifugal load test device is installed, firstly, load applying devices 4 matched with the number of propeller blades are selected, in this embodiment, a propeller with six blades 3 is selected, the load applying devices 4 are in a regular hexagon shape, each side wall of each load applying device is perpendicular to the axis of one blade 3, an oil inlet 5 is arranged at the center of the bottom surface of each load applying device 4, oil inlet channels 6 are circumferentially arranged at the oil inlet 5, six blades 3 are arranged in this embodiment, therefore, six oil inlet channels 6 are arranged, each oil inlet channel 6 is coincident with the axis of the corresponding blade 3, each oil inlet channel 6 is perpendicular to the corresponding rodless piston 8, and the load applying devices 4 are installed in a propeller hub 1;
then, a locking rod 11 is screwed in each blade 3, a mandril 10 is arranged behind the locking rod 11, and the mandril 10 and the locking rod 11 can be integrally formed rod-shaped devices or can be split-type devices as adopted in the embodiment;
the strain gauges 12 are arranged on the ejector rods 10, the strain gauge 12 can be arranged on only one ejector rod 10, or the strain gauges 12 can be arranged on all the ejector rods 10, and then the values fed back by all the strain gauges 12 are averaged, so that the value of the applied load can be set more accurately;
finally, a first force-bearing component 9 is arranged between the top rod 10 and the rodless piston 8, the surface of the first force-bearing component 9, which is contacted with the rodless piston 8, can be a spherical surface, at the moment, the first force-bearing component 9 can be integrally formed with the rodless piston 8, the surface of the first force-bearing component 9, which is contacted with the top rod 10, can also be a spherical surface, at the moment, the first force-bearing component 9 can be integrally formed with the top rod 10, and the first force-bearing component 9 in the embodiment adopts a force-bearing ball which is integrally spherical, so that the force-bearing ball exists as an independent component;
after installation, the locking lever 11 is tightened to eliminate play and prevent rotation.
During testing, the oil inlet 5 is connected with the pressurizing oil cylinder, the pressurizing oil cylinder conveys oil into the oil inlet 5, the oil extrudes the rodless piston 8 and the bearing ball, and the bearing ball extrudes the ejector rod 10 and the locking rod 11, so that the paddle 3 is subjected to oil pressure to realize application of centrifugal load, and the magnitude of the applied centrifugal load is detected through the strain gauge 12; the centrifugal load is applied simultaneously with the pneumatic load, which is directed as indicated by the arrow in fig. 1 and whose magnitude can be measured by means of a tension meter.
The pneumatic load and the centrifugal load are applied simultaneously, so that the pneumatic load can influence the test of the centrifugal load, and when the paddle 3 is twisted due to the application of the pneumatic load, the bearing ball is point-to-face applied load and is not influenced, so that the influence of the pneumatic load on the centrifugal load is eliminated;
when the propeller cannot bear load and is damaged and cannot continuously bear centrifugal load in one direction, the rodless piston 8 in the direction can be ejected out by oil pressure, and the purpose of immediate unloading is achieved. The centrifugal load test device is a self-balancing system, centrifugal forces in multiple directions are the same at any time, and when one direction cannot continuously bear the centrifugal load, the centrifugal loads in other directions cannot cause secondary damage to the propeller.
The above description is only for the specific embodiment 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 (4)
1. The utility model provides a screw centrifugal load test device, the screw includes propeller hub (1), and propeller hub (1) outside circumference is equipped with a plurality of paddles (3), and paddle (3) are connected with propeller hub (1) through oar sleeve (2), its characterized in that, centrifugal load test device includes:
the load applying device (4) is arranged inside the propeller hub (1), the load applying device (4) is in a regular polygon shape, the axis of each blade (3) is perpendicular to the side wall, closest to the blade (3), of the load applying device (4), an oil cavity (7) is formed in each side wall of the polygon of the load applying device (4), a rodless piston (8) is arranged in each oil cavity (7), an oil inlet (5) and an oil inlet channel (6) are formed in the load applying device (4), and the oil cavities (7) are communicated with the oil inlet (5) through the oil inlet channel (6);
the force-bearing mechanism comprises a first force-bearing component (9) and a second force-bearing component, wherein the first force-bearing component (9) is arranged inside the propeller hub (1), one end, far away from the propeller blade (3), of the first force-bearing component (9) is contacted with the rodless piston (8), one end, close to the propeller blade (3), of the first force-bearing component (9) is contacted with the second force-bearing component, the end face, far away from one end of the propeller blade (3), of the first force-bearing component (9) or the end face, close to one end of the propeller blade (3), of the first force-bearing component is a spherical surface, the second force-bearing component is fixed inside the propeller blade (3), and the second force-bearing component is provided with a strain gauge (12).
2. The propeller centrifugal load test device according to claim 1, wherein the second force-bearing component comprises a top rod (10) and a locking rod (11), one end of the top rod (10) close to the hub (1) is in contact with the first force-bearing component (9), one end of the top rod (10) far away from the hub (1) is in contact with the locking rod (11), the locking rod (11) is fixed with the blade (3), and the strain gauge (12) is arranged on the side wall of the top rod (10).
3. A propeller centrifugal load test device according to claim 2, characterized in that the locking bar (11) is fixed to the blade (3) by means of a threaded connection.
4. A propeller centrifugal load test device according to claim 1, wherein the first force-bearing member (9) is spherical in shape as a whole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710073452.6A CN106828973B (en) | 2017-02-10 | 2017-02-10 | Propeller centrifugal load test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710073452.6A CN106828973B (en) | 2017-02-10 | 2017-02-10 | Propeller centrifugal load test device |
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| Publication Number | Publication Date |
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| CN106828973A CN106828973A (en) | 2017-06-13 |
| CN106828973B true CN106828973B (en) | 2020-02-07 |
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| CN201710073452.6A Active CN106828973B (en) | 2017-02-10 | 2017-02-10 | Propeller centrifugal load test device |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107727375A (en) * | 2017-08-30 | 2018-02-23 | 江西昌河航空工业有限公司 | Motion loading device and method is used in a kind of propeller hub detection |
| CN109720602B (en) * | 2019-01-25 | 2024-01-30 | 重庆苏试广博环境可靠性技术有限公司 | Test device for simulating torque conversion test of working state of propeller |
| CN115420478A (en) * | 2021-05-31 | 2022-12-02 | 惠阳航空螺旋桨有限责任公司 | Hub centrifugal load test device |
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| CN1019657B (en) * | 1987-12-21 | 1992-12-30 | 联合工艺公司 | Aircraft propeller blade retention device |
| CN102673802A (en) * | 2012-05-23 | 2012-09-19 | 北京理工大学 | *-shaped reaction torque rudder structure layout method |
| CN104973244A (en) * | 2014-04-04 | 2015-10-14 | 波音公司 | Modular rotor craft rotor hub system |
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| EP3109481A2 (en) * | 2015-06-23 | 2016-12-28 | General Electric Company | Trunnion retention for a turbine engine |
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2017
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1019657B (en) * | 1987-12-21 | 1992-12-30 | 联合工艺公司 | Aircraft propeller blade retention device |
| CN102673802A (en) * | 2012-05-23 | 2012-09-19 | 北京理工大学 | *-shaped reaction torque rudder structure layout method |
| CN104973244A (en) * | 2014-04-04 | 2015-10-14 | 波音公司 | Modular rotor craft rotor hub system |
| EP3109481A2 (en) * | 2015-06-23 | 2016-12-28 | General Electric Company | Trunnion retention for a turbine engine |
| CN106143949A (en) * | 2016-07-06 | 2016-11-23 | 西安交通大学 | A kind of unmanned vehicle testboard and method of testing thereof |
Non-Patent Citations (1)
| Title |
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| 螺旋桨桨毂疲劳试验加载方法;杨雷等;《航空动力学报》;20150630;第30卷(第6期);第1492-1497页 * |
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