CN220625121U - Helicopter main reducer radome fairing locking reliability inspection tool - Google Patents
Helicopter main reducer radome fairing locking reliability inspection tool Download PDFInfo
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- CN220625121U CN220625121U CN202322388323.XU CN202322388323U CN220625121U CN 220625121 U CN220625121 U CN 220625121U CN 202322388323 U CN202322388323 U CN 202322388323U CN 220625121 U CN220625121 U CN 220625121U
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- scale
- measuring rod
- sleeve
- indicating
- sliding
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- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 16
- 238000007689 inspection Methods 0.000 title claims abstract description 15
- 210000004907 gland Anatomy 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 4
- 238000005259 measurement Methods 0.000 abstract description 22
- 238000006073 displacement reaction Methods 0.000 abstract description 2
- 230000007246 mechanism Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000002674 ointment Substances 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000035515 penetration Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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- Length-Measuring Instruments Using Mechanical Means (AREA)
Abstract
The utility model belongs to the technical field of displacement measurement, and particularly relates to a helicopter main reducer fairing locking reliability inspection tool, which comprises a sleeve, a measuring rod and an indicating assembly, wherein a piston is arranged at one end of the measuring rod, a sliding hole is arranged in the sleeve, the piston slides closely to the sliding hole, and the measuring rod can extend out of the sleeve; the inner wall of the sliding hole is connected with the piston through a spring; the side wall of the sleeve is provided with a mounting groove which is communicated with the sliding hole, and the mounting groove is provided with a graduated scale; the indicating assembly comprises a sliding part and an indicating scale arranged on the sliding part, wherein the sliding part is tightly clung to the sliding hole and is arranged in a sliding manner, and the indicating end of the indicating scale is opposite to the graduated scale. The tool can quickly finish the length measurement of the extension amount of the lock pin, can directly read, has high measurement accuracy, and does not need to repeatedly measure to ensure the measurement effectiveness.
Description
Technical Field
The utility model belongs to the technical field of displacement measurement, and particularly relates to a helicopter main reducer fairing locking reliability inspection tool.
Background
A helicopter of helicopter series X is developed on the basis of a simulation method to produce a superwasp helicopter, a large accessory openable fairing mechanism for ensuring aerodynamic shape requirement and convenient maintenance and daily maintenance inspection is designed on an upper member platform, during ground test and flying, a fairing is buckled and reliable locking is required, wherein the locking mode of a main speed reducer (hereinafter referred to as main reduction) fairing is locking mode that a lock pin on the fairing locking mechanism enters a lock hole of a fuselage structure, the locking reliability directly influences flight safety, so the reliability inspection of fairing locking is indispensable during helicopter repair and daily maintenance, the locking reliability inspection technical inspection index is the extension amount of the lock pin entering the lock hole, and the extension amount of the lock pin is not less than 10mm according to technical requirements. The primary minus fairing locking arrangement is shown in fig. 9.
Objective drawbacks of the prior art:
when the locking pin extending amount is checked, the main reducing fairing is buckled on the machine body completely and locked, the universal measuring tool cannot be used for measuring and checking outside, the locking pin extending amount is generally measured in a marking method mode in the prior art, namely, before the fairing is buckled, the inner edge of a lock hole of the machine body is coated with grease, then the fairing is buckled and locked, after the fairing locking pin enters the lock hole of the machine body, the ointment is driven to leave an ointment trace in the lock hole, the fairing is opened, and then the length of the ointment trace in the lock hole is measured, so that the actual extending amount of the locking pin is obtained.
The extending amount of the lock pin can be measured by a mark method after the hatch cover is buckled and locked, and according to the technical requirement, the extending amount of the lock pin is not less than 10mm, although the requirement on the measuring precision is not high, a certain measuring error exists due to the error of the mark, so that the objective defect in the prior art is mainly represented by insufficient measuring precision and the measurement is required to be repeatedly performed to ensure the measuring effectiveness.
Disclosure of Invention
Aiming at the technical problems in the background technology, the utility model provides a helicopter main reducer fairing locking reliability checking tool.
In order to achieve the above purpose, the technical scheme provided by the utility model is as follows:
a helicopter main reducer fairing locking reliability checking tool comprises a sleeve, a measuring rod and an indicating assembly, wherein a piston is arranged at one end of the measuring rod, a sliding hole is formed in the sleeve, the piston slides tightly against the sliding hole, and the measuring rod can extend out of the sleeve; the inner wall of the sliding hole is connected with the piston through a spring; the side wall of the sleeve is provided with a mounting groove which is communicated with the sliding hole, and the mounting groove is provided with a graduated scale; the indicating assembly comprises a sliding part and an indicating scale arranged on the sliding part, wherein the sliding part is tightly clung to the sliding hole and is arranged in a sliding manner, and the indicating end of the indicating scale is opposite to the graduated scale.
Optionally, the sliding part includes collar and elastic rubber ring, the elastic rubber ring is established in the annular draw-in groove of collar, and the outer wall of elastic rubber ring is hugged closely the slide hole inner wall and is set up.
Optionally, the mounting ring is provided with a first threaded hole, the indication scale is fixed in the first threaded hole of the mounting ring through a locking screw, and the indication scale extends out of the mounting groove and slides against the surface of the graduated scale.
Optionally, one graduated scale is provided, and two groups of different graduated numerical values are arranged on the same graduated scale; one group of the scale values gradually decrease from the measuring rod to the direction of the mounting groove, and the other group of scale values gradually increase from the measuring rod to the direction of the mounting groove.
Optionally, two graduation scales are arranged on two sides of the mounting groove respectively; one of the graduated scales gradually reduces the graduated value from the measuring rod to the direction of the installation groove, and the other graduated scale gradually increases the graduated value from the measuring rod to the direction of the installation groove; the indication staff gauge is provided with two indication ends, and the two indication ends respectively correspond to the two graduation staff gauges.
Optionally, in the initial state, the measuring rod extends out of the sleeve, and the extending amount of the measuring rod is the same as the total length of the measured lock hole; and two numerical values indicated by the indication scale, wherein one numerical value is the extension amount of the measuring rod, and the other numerical value is the extension amount of the lock pin.
Optionally, a gland is screwed at one end of the sleeve, an adjusting screw is screwed in the gland, and the adjusting screw is used for adjusting the position of the indicating assembly in the sliding hole.
The utility model has the following advantages and beneficial effects:
in the utility model, after the lock pin is inserted into the lock hole for locking, the measuring rod is inserted into the other side of the lock hole, the sleeve is pressed until the sleeve is tightly attached to the main rear wall of the helicopter, the indication scale moves backwards along with the sleeve when the sleeve moves relative to the sleeve, and the floating pointer stops moving along with the sleeve and stays on a certain scale when the sleeve stops moving, so that the extension quantity of the indication measuring rod and the extension quantity of the lock pin can be directly read. After the sleeve is taken out, the measuring rod automatically returns to the zero position under the action of spring force, so that one-step convenient measurement can be realized, the indicating assembly is unchanged, the scale value is unchanged, the measuring rod can be taken out for reading after the measurement is finished, and the indicating assembly is manually pushed to reset after the reading is finished. The tool can rapidly finish the length measurement of the extension amount of the lock pin, has high measurement accuracy, and does not need repeated measurement to ensure the measurement effectiveness.
Drawings
FIG. 1 is a front view of a measuring tool provided by the utility model;
FIG. 2 is a half-sectional view of the measuring tool provided by the utility model;
FIG. 3 is a schematic view of a metering rod according to the present utility model received within a sleeve;
FIG. 4 is a block diagram of the bi-directional indicator scale provided by the utility model mounted on a cylinder;
FIG. 5 is a block diagram of the cartridge provided by the present utility model;
FIG. 6 is a first schematic view of the measuring tool provided by the utility model for measuring the penetration of the lock pin;
FIG. 7 is a second schematic diagram of the measuring tool provided by the utility model for measuring the penetration of the lock pin;
FIG. 8 is a schematic illustration of the indication scale and the graduated scale provided by the present utility model;
FIG. 9 is a schematic view of a helicopter main debulking fairing and locking mechanism provided by the utility model;
icon: 1-sleeve, 11-limiting hole, 12-sliding hole, 13-mounting groove, 2-measuring rod, 21-piston, 3-mounting ring, 31-threaded hole, 4-elastic rubber ring, 5-spring, 6-adjusting screw, 61-gland, 7-indicating scale, 8-scale, 81-locking screw, 9-helicopter main cabin-reducing back wall structure, 91-helicopter main cabin-reducing back wall lock hole structure, 92-main cabin-reducing cover locking mechanism lock pin.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments of the present utility model.
Thus, the following detailed description of the embodiments of the utility model, as presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Examples
As shown in fig. 1-5, a helicopter main reducer fairing locking reliability inspection tool comprises a sleeve 1, a measuring rod 2 and an indicating assembly, wherein a piston 21 is arranged at one end of the measuring rod 2, a limiting hole 11 and a sliding hole 12 are sequentially arranged in the sleeve 1, and the diameter of the limiting hole 11 is smaller than that of the sliding hole 12. The piston 21 slides against the slide hole 12, the measuring rod 2 slides against the limit hole 11, and the measuring rod 2 can extend to the outer side of the sleeve 1. The inner wall of the sliding hole 12 is connected with the piston 21 through the spring 5, namely one end of the spring 5 is fixedly connected with the inner wall of the sleeve 1, and the other end is fixedly connected with the piston 21. The side wall of the sleeve 1 is provided with a mounting groove 13, the mounting groove 13 is communicated with the sliding hole 12, and the mounting groove 13 is provided with a graduated scale 8; the indicating assembly comprises a sliding part and an indicating scale 7 arranged on the sliding part, the sliding part is arranged in a sliding manner by clinging to the sliding hole 12, and the indicating end of the indicating scale 7 is arranged on the graduation scale 8.
As a preferable mode of the utility model, the sliding part comprises a mounting ring 3 and an elastic rubber ring 4, the elastic rubber ring 4 is sleeved in an annular clamping groove of the mounting ring 3, and the outer wall of the elastic rubber ring 4 is tightly attached to the inner wall of the sliding hole 12. The elastic rubber ring 4 is tightly clung to the inner wall of the slide hole 12 through the elastic resistance, and has certain friction force. When the sleeve 1 slides relative to the measuring rod 2, the elastic rubber ring 4 is tightly clung to the inner wall of the sliding hole 12 to slide, and when the measuring rod 2 is reset after the measurement is finished, the elasticity of the elastic rubber ring 4 is tightly clung to the inner wall of the sliding hole 12 and cannot move, so that the indication scale 7 cannot move, and the measurement precision is ensured.
Further, a first threaded hole 31 is formed in the mounting ring 3, the indication scale 7 is fixed in the threaded hole 31 of the mounting ring 3 through a locking screw, the locking screw penetrates through a through hole of the indication scale 7 and then penetrates through the elastic rubber ring 4 to be screwed into the threaded hole 31 for fixation, and therefore the indication scale 7, the elastic rubber ring 4 and the mounting ring 3 can be fixed into a whole. The indication scale 7 extends from the inside of the slide hole 12 to the outside of the mounting groove 13 and slides against the surface of the graduation scale 8, so that reading can be performed according to the graduation indicated by the indication scale 7.
As shown in fig. 1 and 3, in a preferred embodiment of the present utility model, one of the scale plates 8 is provided, the scale plate 8 is fixed to one side of the mounting groove 13, and the scale plate 8 is fixed to the mounting groove 13 by a lock screw 81. Two groups of different scale values are arranged on the same scale 8; one group of graduation values from the measuring rod 2 to the mounting groove 13 gradually decrease, the graduation values in the figure are from 23mm to 0mm in sequence from left to right, and the other group of graduation values from the measuring rod 2 to the mounting groove 13 gradually increase, and the graduation values in the figure are from 0mm to 23mm in sequence from left to right. The number of scales is not limited to this, and the design of the present utility model is such that the maximum scale is set to 23mm because the total depth H of the measured lock hole is 23mm.
As shown in fig. 4, as another preferable mode of the present utility model, the two graduation marks 8 are provided on both sides of the mounting groove 13, and the graduation marks 8 are fixed in the mounting groove 13 by the locking screw 81. Wherein, the scale values of one scale 8 from the measuring rod 2 to the mounting groove 13 gradually decrease, the scales in the figure are from 23mm to 0mm in turn from left to right, the scale values of the other scale 8 from the measuring rod 2 to the mounting groove 13 gradually increase, and the scales in the figure are from 0mm to 23mm in turn from left to right. The number of scales is not limited to this, and the design of the present utility model is to set the maximum scale to 23mm because the total depth of the measured lock hole is 23mm. The indication scale 7 is provided with two indication ends, which correspond to the two graduation scales 8, respectively.
As shown in fig. 1 and 2, in the initial state, the measuring rod 2 is protruded to the outside of the sleeve 1, and the protruded amount of the measuring rod 2 is the same as the total length of the measured lock hole, and the total length of the lock hole is 23mm, so that the protruded amount is 23mm when the measuring rod 2 is completely protruded. The graduated scale 8 now indicates two values simultaneously, 23mm and 0mm respectively. Two numerical values indicated by the indication scale 7, one of which is the extension amount of the measuring rod 2, namely 23mm, and the other of which is the extension amount of the lock pin, namely 0mm.
Referring to fig. 6 and 7, the locking pin extending amount h1=the total length of the locking hole H-the extending amount H2 of the measuring rod 2, and the total length of the locking hole structure of the machine body is 23mm, so that the indicating scale value of the measuring rod 2 at the initial position (zero position) is designed to be 23mm, namely, the extending amount of the measuring rod 2 is recorded to be 23mm at the initial time; and assuming that the measuring rod 2 is fully extended into the lock catch, the extension amount of the lock pin is recorded as 0mm, so that the same indicating position simultaneously indicates two groups of data, one group is the extension amount of the measuring rod 2, and the other group is the extension amount of the lock pin. The design can directly read and measure the extending amount of the lock pin.
One end of the sleeve 1 is in threaded connection with a gland 61, the gland 61 is in threaded connection with an adjusting screw 6, the adjusting screw 6 is used for adjusting the position of the indicating assembly in the sliding hole 12, after measurement is completed, the adjusting screw 6 pushes the indicating assembly (the mounting ring 3, the elastic rubber ring 4 and the indicating scale 7) to slide by rotating the adjusting screw, so that the mounting ring 3 is clung to the piston 21, and the position is reset to the zero point position (measurement in situ).
Measuring working principle:
step one: before measurement, the helicopter main reducing fairing is buckled and locked. As shown in fig. 1 and 2, in the initial position, the measuring rod 2 is fully extended, and one of the values indicated by the scale values is 23mm, that is, the extending amount of the measuring rod 2 is 23mm.
Step two: as shown in fig. 6, the measuring rod 2 is extended into the lock hole from behind the lock hole of the helicopter main cabin reduction rear wall structure 9 through the space gap between the fairing and the main speed reducer until the measuring rod 2 is tightly attached to the lock pin.
Step three: as shown in fig. 7 and 8, the sleeve 1 is pressed, the sleeve 1 slides relative to the measuring rod 2, the indication scale 7 moves relative to the graduation scale 8 until the sleeve 1 is tightly attached to the side wall of the main cabin reduction rear wall structure 9 of the helicopter; then extract measuring rod 2 and take out measurement frock, measuring rod 2 receives spring 5's effect to reset to normal position, can realize "one step" convenient measurement, but instruct scale 7 motionless, consequently can take out from the lockhole and take out again and read.
Step four: as shown in fig. 8, the scale values are two groups, wherein one group of the scale values is sequentially reduced from 23mm to 14mm, and the 14mm is the protrusion of the measuring rod 2 with h2=14mm; one set of readings increases in sequence from 0mm to 9mm, and the 9mm is the extension of the lock pin is h1=9mm.
Step five: after the measurement is finished, the adjusting screw 6 is rotated, the adjusting screw 6 pushes the indicating assembly (the mounting ring 3, the elastic rubber ring 4 and the indicating scale 7) to slide until the mounting ring 3 is clung to the piston 21 and is reset to the zero position (the measurement original position), the next measurement is convenient, and after the adjustment of the adjusting screw 6 is finished, the adjusting screw needs to be reset to reserve a space for the sliding of the measuring rod 2.
The above is only a preferred embodiment of the present utility model, and is not intended to limit the present utility model, but various modifications and variations can be made to the present utility model by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.
Claims (7)
1. The helicopter main speed reducer fairing locking reliability checking tool is characterized by comprising a sleeve, a measuring rod and an indicating assembly, wherein one end of the measuring rod is provided with a piston, a sliding hole is formed in the sleeve, the piston slides tightly against the sliding hole, and the measuring rod can extend out of the sleeve; the inner wall of the sliding hole is connected with the piston through a spring; the side wall of the sleeve is provided with a mounting groove which is communicated with the sliding hole, and the mounting groove is provided with a graduated scale; the indicating assembly comprises a sliding part and an indicating scale arranged on the sliding part, wherein the sliding part is tightly clung to the sliding hole and is arranged in a sliding manner, and the indicating end of the indicating scale is opposite to the graduated scale.
2. The helicopter main reducer fairing locking reliability inspection tool of claim 1, wherein: the sliding part comprises a mounting ring and an elastic rubber ring, the elastic rubber ring is sleeved in an annular clamping groove of the mounting ring, and the outer wall of the elastic rubber ring is tightly attached to the inner wall of the sliding hole.
3. The helicopter main reducer fairing locking reliability inspection tool of claim 2, wherein: the mounting ring is provided with a first threaded hole, the indication scale is fixed in the first threaded hole of the mounting ring through a locking screw, and the indication scale extends out of the mounting groove and slides against the surface of the graduation scale.
4. The helicopter main reducer fairing locking reliability inspection tool of claim 1, wherein: the scale is provided with one scale, and the same scale is provided with two groups of different scale values; one group of graduation values from the measuring rod to the direction of the mounting groove gradually decrease to indicate the extension amount of the measuring rod, and the other group of graduation values from the measuring rod to the direction of the mounting groove gradually increase to indicate the extension amount of the lock pin.
5. The helicopter main reducer fairing locking reliability inspection tool of claim 1, wherein: the two graduated scales are respectively arranged at two sides of the mounting groove; one of the graduated scales gradually reduces the graduated value from the measuring rod to the direction of the installation groove, and the other graduated scale gradually increases the graduated value from the measuring rod to the direction of the installation groove; the indication staff gauge is provided with two indication ends, and the two indication ends respectively correspond to the two graduation staff gauges.
6. The helicopter main reducer fairing locking reliability inspection tool of claim 4 or 5, wherein: in the initial state, the measuring rod extends out of the sleeve, and the extending amount of the measuring rod is the same as the total length of the measured lock hole; and two numerical values indicated by the indication scale, wherein one numerical value is the extension amount of the measuring rod, and the other numerical value is the extension amount of the lock pin.
7. The helicopter main reducer fairing locking reliability inspection tool of claim 1, wherein: one end of the sleeve is in threaded connection with a gland, an adjusting screw is in threaded connection with the gland, and the adjusting screw is used for adjusting the position of the indicating assembly in the sliding hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322388323.XU CN220625121U (en) | 2023-09-04 | 2023-09-04 | Helicopter main reducer radome fairing locking reliability inspection tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322388323.XU CN220625121U (en) | 2023-09-04 | 2023-09-04 | Helicopter main reducer radome fairing locking reliability inspection tool |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220625121U true CN220625121U (en) | 2024-03-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322388323.XU Active CN220625121U (en) | 2023-09-04 | 2023-09-04 | Helicopter main reducer radome fairing locking reliability inspection tool |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220625121U (en) |
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2023
- 2023-09-04 CN CN202322388323.XU patent/CN220625121U/en active Active
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