CN215262313U - Propeller blade rigidity testing mechanism - Google Patents
Propeller blade rigidity testing mechanism Download PDFInfo
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- CN215262313U CN215262313U CN202121195518.7U CN202121195518U CN215262313U CN 215262313 U CN215262313 U CN 215262313U CN 202121195518 U CN202121195518 U CN 202121195518U CN 215262313 U CN215262313 U CN 215262313U
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Abstract
The utility model discloses a rigidity testing mechanism for propeller blades, which comprises a test bed frame, a blade fixing seat, a propeller hub, a clamping hub, a measuring tool fixing seat, a measuring tool, a rigidity testing clamp and a weight assembly; the paddle fixing seat is fixed on the top of the test bed; the hub is horizontally fixed at one end of the blade fixing seat, the clamping hub is detachably arranged at the mounting end of the hub, and the measuring tool is fixed on the ground and is positioned at the front side of the mounting end of the hub; the blade root of the propeller blade is fixed on the hub, the measuring tool is installed on the measuring tool fixing seat and corresponds to the measuring point of the propeller blade, the rigidity testing clamp is detachably fixed at the measuring point position, the weight component is installed on the rigidity testing clamp, the waving rigidity and the torsional rigidity of the propeller blade can be systematically and perfectly measured by the method for testing by using the mechanism, and the preloading operation is carried out by searching for a proper measuring point, so that the accuracy and the authenticity of data are ensured.
Description
Technical Field
The utility model relates to a paddle test field, more specifically the mechanism for testing propeller blade rigidity data that says so relates to.
Background
Currently, propeller products require blade stiffness testing. The measured stiffness includes flapping stiffness and torsional stiffness of the propeller blade, the flapping stiffness measurement requires the truest measurement of the stiffness value of each section, and the torsional stiffness measurement is that the blade of the propeller blade is twisted by applying a load, so that the torsional stiffness is measured.
However, the prior art lacks a measuring mode, is not systematic and has larger error.
Therefore, how to provide a perfect and systematic propeller blade stiffness measuring mechanism is a problem to be solved urgently by those skilled in the art.
SUMMERY OF THE UTILITY MODEL
In view of the above, the present invention is directed to a method for testing stiffness of a propeller blade, so as to solve at least one of the above technical problems in the prior art to a certain extent.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a propeller blade stiffness testing mechanism comprising: the device comprises a test rack, a blade fixing seat, a propeller hub, a clamping hub, a measuring tool fixing seat, a measuring tool, a rigidity test clamp and a weight assembly; the paddle fixing seat is fixed on the top of the test bed; the hub is horizontally fixed at one end of the blade fixing seat, the clamping hub is detachably arranged at the mounting end of the hub, and the measuring tool is fixed on the ground and is positioned at the front side of the mounting end of the hub;
the blade root of the propeller blade is fixed on the propeller hub, the measuring tool is installed on the measuring tool fixing seat and corresponds to the measuring point of the propeller blade, the rigidity testing clamp is detachably fixed at the position of the measuring point, and the weight component is installed on the rigidity testing clamp.
Preferably, in the above mechanism for testing stiffness of a propeller blade, when the flapping stiffness is measured, a measurement tangent plane is selected, an intersection point of the measurement tangent plane and the axis of the propeller blade is a measurement point, and the measurement tool is mounted on the measurement tool holder.
Preferably, in the above mechanism for testing stiffness of a propeller blade, when measuring torsional stiffness, a measurement tangent plane is selected, the intersection point of the measurement tangent plane and the axis of the propeller blade and the position where the measurement tangent plane is 100mm away from the axis of the propeller blade are measurement points, and the measurement tool is correspondingly mounted on the measurement tool fixing base.
Preferably, in the above-mentioned one of the screw blade rigidity testing mechanisms, the measuring tool is a dial indicator.
Preferably, in the above-mentioned propeller blade rigidity testing mechanism, the rigidity testing jig includes a flapping rigidity jig assembly and a torsional rigidity jig assembly;
the flapping rigidity clamp assembly comprises a first flapping clamp body and a second flapping clamp body, two ends of the first flapping clamp body and the second flapping clamp body are detachably connected, fixing grooves corresponding to the external contour of the propeller blade are formed in the opposite side faces of the first flapping clamp body and the second flapping clamp body, and the propeller blade is clamped in the fixing grooves; the weight assembly is arranged on the lower side of the second waving clamp body;
the torsional rigidity clamp assembly comprises a first torsional clamp body and a second torsional clamp body, and one ends of the first torsional clamp body and the second torsional clamp body extend outwards to form cantilever beams; two ends of the first torsion clamp body and the second torsion clamp body are detachably connected, and fixing grooves corresponding to the outer contour of the propeller blade are formed in opposite side faces of the first torsion clamp body and the second torsion clamp body; clamping the propeller blade in the fixing groove; one end of the cantilever beam is detachably fixed on one side of the first torsion clamp body and one side of the second torsion clamp body, and the other end of the cantilever beam is provided with the weight component.
Preferably, in the above mechanism for testing the rigidity of the propeller blade, two ends of the first waving clamp body and the second waving clamp body are provided with corresponding fixing holes which can be detachably fixed by bolts, and the bottom of the second waving clamp body is provided with a weight mounting hole;
twist reverse the anchor clamps body one with twist reverse the fixed slot both ends of the anchor clamps body two and all set up the fixed orifices, can dismantle fixedly through the bolt, and the tip of cantilever all sets up the weight mounting hole.
Can know via foretell technical scheme, compare with prior art, the utility model discloses a propeller blade rigidity accredited testing organization is provided, its advantage lies in satisfying all needs that propeller blade rigidity was measured, more system, and measured data is more accurate, true.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a middle stiffness testing mechanism according to the present invention;
FIG. 2 is a schematic structural view of a fixture assembly for flapping stiffness according to the present invention;
fig. 3 is a schematic structural diagram of the torsional rigidity clamp assembly according to the present invention.
Reference numerals
The test bed frame 1, the blade fixing seat 2, the hub 3, the clamping hub 4, the measuring tool fixing seat 5, the measuring tool, the waving rigidity clamp component 60, the waving clamp body I601, the waving clamp body II 602, the weight mounting hole 603, the torsional rigidity clamp component 61, the torsional clamp body I611, the torsional clamp body II 612, the weight component 7 and the propeller blade 8.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
Example 1
Please refer to fig. 1-3, which illustrate a mechanism for testing stiffness of a propeller blade according to the present invention, comprising: the device comprises a test bench 1, a blade fixing seat 2, a propeller hub 3, a clamping hub 4, a measuring tool fixing seat 5, a measuring tool, a rigidity testing clamp and a weight component 7; the paddle fixing seat 2 is fixed on the top of the test bed 1; the hub 3 is horizontally fixed at one end of the blade fixing seat 2, the clamping hub 4 is detachably arranged at the mounting end of the hub 3, and the measuring tool is fixed on the ground and is positioned at the front side of the mounting end of the hub 3;
the blade root of propeller blade 8 is fixed on propeller hub 3, and measuring tool installs and corresponds with the measuring point of propeller blade 8 on measuring tool fixing base 5, and rigidity test fixture detachable fixes in the measuring point position, and weight subassembly 7 is installed on rigidity test fixture.
In order to further optimize the technical scheme, when the flapping rigidity is measured, a measuring tangent plane is selected, the intersection point of the measuring tangent plane and the axis of the blade is a measuring point, and a measuring tool is installed on the measuring tool fixing seat 5.
In order to further optimize the technical scheme, when the torsional rigidity is measured, a measuring tangent plane is selected, the intersection point of the measuring tangent plane and the axis of the propeller blade 8 and the position 100mm away from the axis of the propeller blade 8 are measuring points, and a measuring tool is correspondingly installed on the measuring tool fixing seat 5.
In order to further optimize the technical scheme, the measuring tool is a dial indicator.
In order to further optimize the above technical solution, the stiffness test fixture comprises a flap stiffness fixture assembly 60 and a torsional stiffness fixture assembly 61;
the flapping stiffness clamp assembly 60 comprises a first flapping clamp body 601 and a second flapping clamp body 602, wherein two ends of the first flapping clamp body 601 and the second flapping clamp body 602 are detachably connected, fixing grooves corresponding to the external contour of the propeller blade 8 are formed in the opposite side surfaces of the first flapping clamp body 601 and the second flapping clamp body 602, and the propeller blade 8 is clamped in the fixing grooves; the weight component 7 is arranged on the lower side of the second flapping clamp body 602;
the torsional rigidity clamp assembly 61 comprises a first torsional clamp body 611 and a second torsional clamp body 612, and one ends of the first torsional clamp body 611 and the second torsional clamp body 612 extend outwards to form cantilever beams; two ends of the first torsion clamp body 611 and the second torsion clamp body 612 are detachably connected, and opposite side surfaces are provided with fixing grooves corresponding to the outer contour of the propeller blade 8; and the screw propeller blade 8 is clamped in the fixing groove; one end of the cantilever beam is detachably fixed at one side of the first torsion clamp body 611 and the second torsion clamp body 612, and the other end is provided with a weight component 7.
Specifically, the both ends of waving the anchor clamps body one 601 and waving the anchor clamps body two 602 set up corresponding fixed orifices, can dismantle fixedly through the bolt, and wave the bottom of the anchor clamps body two 602 and set up weight mounting hole 603.
Specifically, the two ends of the fixing grooves of the first twisting clamp body 611 and the second twisting clamp body 612 are respectively provided with a fixing hole, the fixing holes can be detached and fixed through bolts, and the end portions of the cantilever beams are respectively provided with a weight mounting hole.
Specifically, the first waving clamp 601, the second waving clamp 602, the first twisting clamp 611 and the second twisting clamp 612 are all made of hard wood.
Specifically, the hardwood can be pine, the profile dimension is cut by an electric saw, and then the profile of the propeller blade is ground on a clamp by comparing the profile of the propeller blade, so that the ground profile completely fits the outer profile of the propeller blade.
Specifically, the application method of the scheme comprises the following steps:
the propeller blade takes a JL-4 series propeller product as an example and comprises the following steps:
the method comprises the following steps: assembling a test device, fixing a blade rigidity fixing seat on a test bench, and then fixing a propeller hub on the blade rigidity fixing seat; arranging a dial indicator fixing seat at one side of the propeller hub, and installing a dial indicator;
step two: installing a propeller blade, taking a metal outer sleeve of a blade root as a clamping surface, penetrating the metal outer sleeve through the dial indicator fixing seat and fixing the metal outer sleeve on the propeller hub to enable the propeller blade to become a cantilever beam;
step three: selecting a loading point, wherein on the axis of the propeller blade, a tangent plane at a position 1400mm away from the rotation center of the propeller is selected as a selected tangent plane, and the intersection point of the tangent plane and the axis of the propeller blade is selected as the loading point;
step four: installing a rigidity measuring clamp, and clamping and fixing the rigidity measuring clamp at a loading point;
step five: loading the waving stiffness weight, adding the weight at the loading point position, preloading the load 400N twice in the blade waving direction, eliminating the installation gap, and standing for 3 minutes each time; formal loading, wherein each stage loads 100N, the stop time between each stage is 1 minute, and after the loading is finished, the load is unloaded to zero;
step five: testing waving rigidity, starting equipment to test waving rigidity, and recording data;
step six: dismantling weights, and dismantling weights loaded during the waving rigidity test;
step seven: loading a torsional rigidity weight, namely loading the weight at the position of a loading point, preloading the load at the loading point for 150 N.m twice, and standing for 3 minutes each time; formal loading, each stage is loaded with 50 N.m, the two stages are stopped for 1 minute, and after the loading is finished, the load is unloaded to zero;
step eight: testing waving rigidity, starting equipment to test waving rigidity, and recording data;
step nine: and (5) dismantling the test equipment to finish the rigidity test.
In order to further optimize the technical scheme, after the weights are unloaded after the test is finished, the secondary test can be carried out after 3-5 minutes.
In order to further optimize the technical scheme, the intersection point of the tangent plane and the axis of the propeller blade is selected as a flapping stiffness measuring point;
the point of intersection of the propeller blade axis and the selected tangent plane and the point of 100mm away from the propeller blade axis on the selected tangent plane are all torsional rigidity measuring points.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (6)
1. A propeller blade stiffness testing mechanism comprising: the device comprises a test bench (1), a blade fixing seat (2), a hub (3), a clamping hub (4), a measuring tool fixing seat (5), a measuring tool, a rigidity testing clamp and a weight component (7); the paddle fixing seat (2) is fixed at the top of the test bench (1); the hub (3) is horizontally fixed at one end of the blade fixing seat (2), the clamping hub (4) is detachably arranged at the mounting end of the hub (3), and the measuring tool is fixed on the ground and is positioned at the front side of the mounting end of the hub (3);
the blade root of the propeller blade (8) is fixed on the propeller hub (3), the measuring tool is installed on the measuring tool fixing seat (5) and corresponds to the measuring point of the propeller blade (8), the rigidity testing clamp is detachably fixed at the position of the measuring point, and the weight component (7) is installed on the rigidity testing clamp.
2. The propeller blade stiffness testing mechanism according to claim 1, wherein when measuring flapping stiffness, a measuring tangent plane is selected, the intersection point of the measuring tangent plane and the blade axis is a measuring point, and the measuring tool is mounted on the measuring tool fixing base (5).
3. The propeller blade stiffness testing mechanism according to claim 2, wherein when measuring torsional stiffness, a measuring tangent plane is selected, and the intersection point of the measuring tangent plane and the axis of the propeller blade (8) and the position 100mm away from the axis of the propeller blade (8) are measuring points, and the measuring tool is correspondingly installed on the measuring tool fixing seat (5).
4. A mechanism according to claim 3, wherein the measuring means is a dial gauge.
5. A propeller blade stiffness testing mechanism according to claim 4 wherein the stiffness testing clamp includes a flap stiffness clamp assembly (60) and a torsional stiffness clamp assembly (61);
the flapping rigidity clamp assembly (60) comprises a first flapping clamp body (601) and a second flapping clamp body (602), wherein two ends of the first flapping clamp body (601) and the second flapping clamp body (602) are detachably connected, opposite sides of the first flapping clamp body are provided with fixing grooves corresponding to the external contour of the propeller blade (8), and the propeller blade (8) is clamped in the fixing grooves; the weight component (7) is arranged on the lower side of the second waving clamp body (602);
the torsional rigidity clamp assembly (61) comprises a first torsional clamp body (611) and a second torsional clamp body (612), and one ends of the first torsional clamp body (611) and the second torsional clamp body (612) extend outwards to form cantilever beams; two ends of the first torsion clamp body (611) and the second torsion clamp body (612) are detachably connected, and fixing grooves corresponding to the outer contour of the propeller blade (8) are formed in opposite side surfaces of the first torsion clamp body and the second torsion clamp body; and clamping the propeller blades (8) in the fixing grooves; one end of the cantilever beam is detachably fixed on one side of the first torsion clamp body (611) and one side of the second torsion clamp body (612), and the other end of the cantilever beam is provided with the weight component (7).
6. The mechanism for testing the rigidity of the propeller blade is characterized in that two ends of the first flapping clamp body (601) and the second flapping clamp body (602) are provided with corresponding fixing holes which can be detachably fixed through bolts, and the bottom of the second flapping clamp body (602) is provided with a weight mounting hole (603);
fixing holes are formed in two ends of the fixing grooves of the first torsion clamp body (611) and the second torsion clamp body (612) and can be detachably fixed through bolts, and weight mounting holes (603) are formed in the end portions of the cantilever beams.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121195518.7U CN215262313U (en) | 2021-05-31 | 2021-05-31 | Propeller blade rigidity testing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121195518.7U CN215262313U (en) | 2021-05-31 | 2021-05-31 | Propeller blade rigidity testing mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215262313U true CN215262313U (en) | 2021-12-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121195518.7U Active CN215262313U (en) | 2021-05-31 | 2021-05-31 | Propeller blade rigidity testing mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215262313U (en) |
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2021
- 2021-05-31 CN CN202121195518.7U patent/CN215262313U/en active Active
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