Device for rapidly dismounting damper bolts
A damper and bolt technology, applied in the field of helicopter design and test, can solve the problems of small surrounding space, unable to meet the requirement of regular disassembly of damper bolts, large operating space, etc., and achieve the effect of simple structure
Active Publication Date: 2015-06-10
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology
[0013] Both the screw-out method and the ejection method require a large operating space. The device structure of the screw-out method is complex and is only suitable for the threaded pair structure. The ejection method needs to apply force on the threaded end of the bolt.
In the fatigue test of the central part of the main propeller hub of the helicopter, due to the layout and structural characteristics of the damper lugs, the space around the threaded end of the bolt is small, and the above two methods cannot meet the requirement of regular disassembly of the damper bolt
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[0024] The present invention will be described in further detail below.
[0025] Such as figure 1 , 2 As shown, the present invention is a device for quickly disassembling damper bolts, including: a driving bolt 1 , a driving gear 21 , a driven bolt 4 , a driven gear 22 , a clip 5 , a backing plate 6 , and a spacer 7 .
[0026] Wherein, the spacer 7 is located between the nut 10 and the body of the central part 8, the upper surface of the spacer 7 is closely attached to the bottom of the nut 10, and the lower surface of the spacer 7 is closely attached to the inner wall of the central part 8 body.
[0027] The bolt body parts of the driving bolt 1 and the driven bolt 4 are, from top to bottom, a non-cylindrical part, a polished rod part, and a threaded part; the major diameters and pitches of the threaded parts of the driving bolt 1 and the driven bolt 4 are the same, but the direction of rotation is opposite; The non-cylindrical part of the driving bolt 1 passes through the...
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The invention provides a device for rapidly dismounting damper bolts. The damper bolts can be rapidly dismounted in a small space. According to the technical scheme, the device is characterized in that each of bolt portions of a driving bolt and a driven bolt is sequentially divided into a non-cylindrical portion, a smooth portion and a thread portion from top to bottom, and the thread portion of the driving bolt and the thread portion of the driven bolt are the same in large diameter and pitch but opposite in screwing direction; the non-cylindrical portion of the driving bolt penetrates a driving gear, and the thread portion of the driving bolt is screwed in a first thread hole of a clamping block to abut against the upper surface of a base plate; and the non-cylindrical portion of the driven bolt penetrates a driven gear, and the thread portion of the driven bolt is screwed into a second thread hole in the clamping block to abut against the upper surface of the base plate. The driving bolt and the driven bolt rotate coaxially, and the driving gear and the driven gear are meshed for transmission; the driven gear and the driven bolt coaxially rotate; and the driving gear and the driven gear are the same in size and shape.
Description
technical field [0001] The invention relates to the field of helicopter design tests, in particular to a device for quickly disassembling damper bolts. Background technique [0002] In the fatigue test of the central part of the main propeller hub of the helicopter, it is necessary to regularly check the use condition of the damper bolts (dimensions and tolerances, surface wear, extrusion deformation, etc.). [0003] The implementation steps are as follows: [0004] 1. Disassemble the test piece and loading fixture; [0005] 2. Take out the bolts; [0006] 3. Observe the wear state of the bolt surface; [0007] 4. Measure the external dimensions and tolerances of bolts; [0008] 5. Decide whether to replace the bolts; [0009] 6. Reinstall bolts, test pieces and fixtures. [0010] In the fatigue test, the damper lugs and the damper loading handle of the central part are hingedly connected, and the damper bolts are subjected to a large shear force, which will produce ob...
Claims
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IPC IPC(8): B25B27/00
CPCB25B27/00
Inventor 姚海涛刘红艳王利鹏
Owner CHINA HELICOPTER RES & DEV INST