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A blade clamping mechanism
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A clamping mechanism and blade technology, applied in workpiece clamping devices, manufacturing tools, etc., to achieve the effect of compact structure
Active Publication Date: 2017-03-01
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology
[0004] The invention provides a paddle clamping mechanism, which can solve the problem that the swing ratio can be locally and continuously adjustable in the process of clamping large-size paddles
Method used
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Embodiment 1
[0024] Such as figure 1 and figure 2 As shown, the blade clamping mechanism of the present invention includes a loading rod 1 , a carrier 2 , a pin shaft 3 , an upper template 4 , a lower template 5 , a front screw assembly 6 , a rear screw assembly 7 , and blades 8 and other components.
[0025] The transmission carrier 2 is movably arranged on the upper template 4, and can be moved along the chord direction of the blade cavity on the upper template 4 ( figure 1 The direction indicated by the middle arrow F) reciprocates in the horizontal direction, the loading rod 1 is hinged on the carrier 2, and the axis of the hinge point is perpendicular to the chord direction of the blade cavity.
[0026] The lower end of the loading rod 1 (in the figure) can be installed on the transmission body 2 by installing suitable bearing components such as joint bearings or radial ball bearings, so as to adapt to the free deformation of the blade when it is loaded. The upper end of the loading...
Embodiment 2
[0032] Such as image 3 As shown, the difference between this embodiment and the above-mentioned embodiment 1 lies in that the structure of the carrier 2 is different.
[0033] In this embodiment, the transmission carrier 2 is composed of a pressure plate 21, an upper slider 23, a lower slider 29, and several bolt assemblies 24; the middle of the upper slider 23 protrudes upwards with lugs, and the inside of the lugs is parallel to the blade. An installation through hole 30 is opened in the direction of the axis 81, and the pin shaft 3 passes through the installation through hole 30 to realize the hinge between the loading rod 1 and the upper slider 23, and the upper end of the loading rod 1 is connected with the actuator.
[0034] The pressing plate 21 is fixed above the upper template 4, and there is a chute 25 with a "convex" cross section in the middle of the pressing plate 21. The upper slider 23 is placed above the pressing plate 21, and the lower slider 29 is placed in ...
Embodiment 3
[0036] Such as Figure 4 As shown, the difference with the above-mentioned embodiment 1 and embodiment 2 is that in this embodiment, a cushion 10 can be installed on the contact surface of the upper template 4 and the lower template 5 with the paddle 8 to prevent direct contact with the paddle 8. The blade 8 constitutes damage.
[0037] In addition, a pressing plate 21 can be installed under the lower template 5 to increase the strength of the lower template 5 . And between the pressing plate 21 and the upper template 4 and between the pressing plate 21 and the lower template 5, a bolt assembly 9 and a briquetting block 23 are respectively installed to increase the rigidity of the whole clamping mechanism.
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Abstract
The invention belongs to the experimental technique of a helicopter blade, relates to a blade clamping mechanism, and solves the problem that the swing ratio of a large-sized blade is continuously adjustable in a clamping process. The blade clamping mechanism provided by the invention comprises an upper template and a lower template, wherein a blade cavity, a carrier and a loading rod are formed between the upper template and the lower template, the loading rod is hinged on the carrier, and the carrier can move back and forth in a horizontal direction on the upper template along a chordwise direction of the blade cavity. The blade clamping mechanism provided by the invention is compact in structure; furthermore, when an external load is applied to the blade by the loading rod, the applied load can pass through the axis of the blade all the time by adjusting the position of the loading rod, an additional torque cannot be generated on the blade, and the demand of adjusting the swing ratio can be met.
Description
technical field [0001] The invention belongs to the experimental technology of helicopter blades, in particular to a blade clamping mechanism. Background technique [0002] The loads to be applied in the blade test usually include flapping moment, shimmy bending moment and centrifugal force. Commonly used load application methods include resonance loading method and actuator forced loading method. During the test using the forced loading method, when the test piece rotates around its axis, the loading axis still needs to pass through the blade axis to meet the realization of the swing ratio (the ratio of the swing bending moment and the swing bending moment on the test piece). Proportion) needs to be continuously adjustable, otherwise additional torque will be generated during the application of bending moment. [0003] For small blade test pieces, the disk mechanism whose center coincides with the blade axis can be used for clamping, and the external load applied in the ra...
Claims
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Application Information
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