CN113997238A

CN113997238A - Helicopter blade pull rod gap adjusting method and adjusting tool

Info

Publication number: CN113997238A
Application number: CN202111178947.8A
Authority: CN
Inventors: 李奕锋; 卓伟伟; 陈强; 孙欢欢; 张晶鑫; 曹永辉; 丁忠伟; 宋永巍; 唐驭傲; 罗太明
Original assignee: Chengdu Guoying Jinjiang Machine Factory
Current assignee: Chengdu Guoying Jinjiang Machine Factory
Priority date: 2021-10-08
Filing date: 2021-10-08
Publication date: 2022-02-01

Abstract

A helicopter blade pull rod gap adjusting method and adjusting tool belong to the technical field of helicopter maintenance, wherein the adjusting method comprises four steps of troubleshooting and determining main assembly parts causing faults, carrying out gap adjustment and detection experiments on blade pull rods with different part sizes, re-calibrating the size range of the main assembly parts causing the blade pull rod faults, and carrying out surface treatment on parts which do not meet requirements; the adjustment frock includes the bottom plate, and the both ends of bottom plate are equipped with spout and fixed axle subassembly respectively, are equipped with the sliding shaft in the spout, and the both ends of paddle pull rod are fixed in respectively on sliding shaft and the fixed axle subassembly. The invention can simulate the working environment on the machine, directly measure the clearance on the ground, reduce the process repetition and improve the working efficiency; meanwhile, the main factor causing the failure of the paddle pull rod can be determined to be the ball bearing, the matching standard of the ball bearing is determined, the one-time assembly qualification rate of the paddle pull rod is improved, and the failure removal of the paddle pull rod is effectively guaranteed.

Description

Helicopter blade pull rod gap adjusting method and adjusting tool

Technical Field

The invention belongs to the technical field of helicopter overhauling, relates to gap adjustment of a helicopter blade pull rod, and particularly relates to a gap adjustment method and an adjustment tool for the helicopter blade pull rod.

Background

The helicopter blade pull rod is used for connecting the automatic tilter rotating disk and the rotor hub axial joint variable-pitch rocker arm, and transmitting a steering rod operation instruction to change the blade attack angle so as to meet the requirement of helicopter flight control. Clearance out-of-tolerance faults often occur in the use process of the blade pull rod, so that the vibration of components is increased, the abrasion is aggravated, and the normal operation and the flight quality of the helicopter are influenced.

The existing blade pull rod adjusting technology is not deep enough for key part cognition, and the adjusting method is not convenient enough. There are mainly the following problems:

1. the working environment simulation and adjustment tool for the blade pull rod is lacked, and the blade pull rod can be detected only after being installed;

2. the dimensional tolerance of the key parts is not accurate enough, and the condition of out-of-tolerance can occur after assembly;

3. the adjusting method is single, and a part adjusting and matching process method is lacked.

Therefore, key parts influencing clearance out-of-tolerance need to be found out through analysis of the blade pull rod fault phenomenon and product structures and assembling relations, a blade pull rod working environment simulation adjusting tool is designed, multiple times of assembling data acquisition and comparison are carried out, the size tolerance of the parts is determined, and processing and adjusting methods are used for guaranteeing that the blade pull rod clearance is qualified.

Disclosure of Invention

In view of the above disadvantages of the prior art, an object of the present invention is to provide a method for adjusting a gap between tie rods of a helicopter blade, which is used to solve the technical problems of the prior art that the method for adjusting a tie rod of a blade is single, the tolerance accuracy of key parts is poor, and an out-of-tolerance condition may occur after assembly.

In order to achieve the above objects and other related objects, the present invention provides a method for adjusting a gap between tie rods of a helicopter blade, which mainly comprises the following steps:

the method comprises the following steps that firstly, fault elimination is carried out on a blade pull rod, and main assembly parts causing the blade pull rod fault are determined;

step two, assembling the blade pull rods with different sizes based on the main assembling parts causing the blade pull rod faults determined in the step one, carrying out multi-group secondary blade pull rod gap adjustment and detection experiments, and collecting experiment data;

step three, carrying out comparative analysis according to the test data obtained in the step two, re-calibrating the size range of the main assembly parts causing the blade pull rod fault, and improving the primary assembly qualified rate;

and step four, performing surface treatment on the main assembly parts which cause the blade pull rod fault and have unqualified first-time assembly qualified rate, so that the main assembly parts meet the use requirement.

In any of the above schemes, preferably, in the step one, the method for troubleshooting the blade drag link includes: and (3) carrying out an assembly test by adopting a method of measuring and counting the sizes and the matching sizes of all parts of the fault part, adjusting the parts to be replaced and replacing the assembly torque, and verifying and discharging item by item to determine the main assembly parts causing the fault.

Preferably, in any of the above schemes, in the second step, the gap adjustment and the detection test of the blade pull rod are performed by using a gap adjustment tool.

In any of the above schemes, preferably, in the fourth step, the method for performing surface treatment on the main assembly parts causing the blade pull rod failure includes: and carrying out surface copper plating treatment on the assembly parts.

In any of the above schemes, preferably, the thickness of the single side of the copper plating layer after the surface copper plating treatment of the assembly part is between 0.01mm and 0.015 mm.

In any of the above schemes, preferably, after the blade pull rod is assembled on the surface-treated assembly part, the interference is greater than 0.02mm, and then the copper plating layer of the assembly part is polished.

The utility model provides a helicopter paddle pull rod clearance adjustment frock, includes the bottom plate, the spout has been seted up on its length direction to the one end of bottom plate, and the other end of bottom plate is connected with fixed axle subassembly, be equipped with in the spout and follow spout length direction and control the sliding shaft that removes, the cover is equipped with the sliding block on the sliding shaft, and the one end of paddle pull rod is fixed in on the sliding shaft through set nut and the paddle pull rod is located between set nut and the sliding block, the other end of paddle pull rod is fixed in on the fixed axle subassembly through set nut.

In any one of the above schemes, preferably, the lower end of the sliding block is sleeved with a scale ring.

Preferably in any one of the above schemes, the fixed shaft assembly comprises a fixed block, an inclined plane is arranged at the top of the fixed block, a connecting hole which penetrates through the fixed block and is perpendicular to the inclined plane is formed in the inclined plane, a fixed shaft is arranged in the connecting hole, and the fixed shaft penetrates through the connecting hole and then is matched with the positioning nut to fix the end part of the blade pull rod.

Preferably in any one of the above schemes, the connecting hole includes first through-hole and second through-hole that communicate each other, the mounting hole with the second through-hole intercommunication is seted up to the lateral wall of fixed block, the one end of fixed axle is located the mounting hole, and the other end is fixed with the end of set nut cooperation behind running through mounting hole, second through-hole and the first through-hole in proper order to the paddle pull rod.

As described above, the helicopter blade tie rod gap adjusting method and adjusting tool of the present invention have the following beneficial effects:

1. according to the invention, the adjusting tool can simulate the working environment on the aircraft, the blade pull rod gap measurement after the assembling on the aircraft is avoided, the gap measurement can be directly carried out on the ground workbench, the rapid adjustment of a rotor system and a control system is realized, the process repetition is reduced, and the working efficiency is improved.

2. In the invention, when the war wound is rush-repaired, due to the convenience of adjusting the tool, the parts can be selected and assembled in advance, and the requirements of field maneuvering repair and war wound rush-repair are met.

3. According to the invention, the main assembly parts causing the blade pull rod fault can be determined, and the matching standard of the parts is determined, so that the one-time assembly qualification rate of the blade pull rod is improved, the fault elimination of the blade pull rod is effectively ensured, and the working efficiency is improved.

Drawings

FIG. 1 is a schematic view of the present invention.

Fig. 2 is a schematic structural view of the positioning nut.

Fig. 3 is a schematic view showing the structure of the sliding shaft.

FIG. 4 is a schematic diagram of a slider.

Fig. 5 shows a schematic diagram of the structure of the scale ring.

Fig. 6 is a schematic structural view of the base plate.

Fig. 7 shows a schematic view of the structure of the fixed shaft.

Fig. 8 is a schematic view showing the connection of the fixed shaft assembly to the base plate.

Fig. 9 is a perspective view showing a fixing block.

Fig. 10 is a schematic structural view of the fixing block.

Description of the element reference numerals

1-a positioning nut, 2-a sliding shaft, 2.1-a base, 2.2-a sliding shaft section, 2.3-a second transition section, 2.4-a first threaded shaft section, 2.5-a third transition section, 2.6-a connection section, 2.7-a second threaded shaft section, 3-a sliding block, 3.1-a first cylindrical section, 3.2-a second cylindrical section, 3.3-a connection groove, 3.4-a mating axial diameter section, 3.5-a first transition section, 3.6-a threaded hole section, 4-a scale ring, 4.1-a groove line, 5-a bottom plate, 5.1-a sliding groove, 5.2-a fixing hole, 5.3-a first pin hole, 6-a fixing shaft, 7-a fixing block, 7.1-a connection hole, 7.11-a first through hole, 7.12-a second through hole, 7.2-a mounting hole, 7.3-a connection pin hole, 7.4-a second cylinder, 8-dowel.

Detailed Description

The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure.

Please refer to fig. 1 to 10. It should be understood that the structures, ratios, sizes, and the like shown in the drawings and described in the specification are only used for matching with the disclosure of the specification, so as to be understood and read by those skilled in the art, and are not used to limit the conditions under which the present invention can be implemented, so that the present invention has no technical significance, and any structural modification, ratio relationship change, or size adjustment should still fall within the scope of the present invention without affecting the efficacy and the achievable purpose of the present invention. In addition, the terms "upper", "lower", "left", "right", "middle" and "one" used in the present specification are for clarity of description, and are not intended to limit the scope of the present invention, and the relative relationship between the terms and the terms is not to be construed as a scope of the present invention.

Example 1

The blade pull rod assembly connects the automatic tilter rotating disk with the rotor hub axial joint variable-pitch rocker arm, when the steering column is pushed and pulled, the blade pull rod assembly generates axial displacement through the transmission of the pull rod, the rocker arm and the longitudinal hydraulic booster, the automatic tilter rotating disk tilts to cause the change of the rotor blade attack angle, the change of the front and back blade pitches, the front and back tilting of the rotor cone causes the front and back tilting of the rotor pulling force, thereby changing the flight state. When the automatic inclinator changes the total distance, the rotating disc moves up and down along the guide cylinder, the rotating disc drives five blade pull rod assemblies and the variable-distance rocker arm simultaneously, so that the rotor blade arranged on the axial joint shell rotates around the axis of the corresponding support arm, and the installation angle of the blade changes, thereby increasing or reducing the tension of the rotor wing. The damage of the abnormal clearance of the blade pull rod can cause the working part of the blade pull rod assembly to vibrate greatly in the flying process of the helicopter, the working environment is severe, and according to the working state analysis of parts, the damage of parts can be accelerated due to the large movable clearance, and the service life of the parts can be shortened; in addition, if the gaps of the five blade pull rod assemblies are different from each other greatly, the normal operation of the helicopter is influenced. Therefore, in order to adjust the movable clearance of the blade pull rod, reduce the damage of parts and prolong the service life of the blade pull rod, the invention provides a method for adjusting the clearance of the blade pull rod of the helicopter, which mainly comprises the following steps:

the key factors causing the faults are found out by analyzing the fault phenomena of the blade pull rod, the structural composition of the product, the installation relation on the machine, the work bearing load and other factors.

In the prior art, the reason and the elimination method of the blade pull rod fault are not determined, and only the processing standard is met after the fault occurs. However, when the blade tension rod fails, the blade tension rod still generates a clearance out-of-tolerance fault phenomenon randomly after the blade tension rod assembly is assembled on the helicopter and used for a short time after the blade tension rod assembly is correctly executed according to a specified processing standard. Therefore, the main cause causing the failure of the blade pull rod needs to be determined, and corresponding troubleshooting processing is carried out according to the main cause causing the failure so as to improve the failure processing efficiency and the yield of the blade pull rod. The specific method for determining the main assembly parts causing the blade pull rod fault comprises the following steps:

the method comprises the steps of measuring and counting the sizes and the matching sizes of all parts of a fault part, adjusting the parts to be replaced and replacing the assembly torque, and the like to carry out an assembly test, and determining the main assembly parts causing the fault after verification and discharge item by item. The specific test procedures and test data are as follows:

1. assembly moment analysis

In the whole blade pull rod assembling process, 4 assembling moments are provided, wherein an upper pull rod joint is connected with a moment A, a lower pull rod joint is connected with a moment B, a bearing inner ring fixing moment C and a bearing outer ring fixing moment D. According to engineering experience, adjustment tests were carried out in the range between 85% of the specified minimum tightening torque value and 115% of the specified maximum tightening torque value, the specific test results being shown in table 1:

TABLE 1 units N.m

2. Fit size analysis

When the blade pull rod is assembled, 3 matching dimension requirements are met, tests are respectively carried out according to the specified dimension of a new part and the repair limit dimension of an old part summarized according to the repair experience, and the specific test results are shown in table 2:

TABLE 2 units mm

3. Double-row ball bearing

The double-row ball bearing is a finished part on the paddle pull rod, except for the matching requirement of other parts, the bearing has the range requirement of bearing play when being produced and delivered from a factory, the upper limit and the lower limit of production qualified standards are taken as the range, the bearing is replaced for testing, and the specific test result is shown in table 3:

TABLE 3 units mm

	Lower limit of play	Median value	Upper limit of play
				Bearing size	0.015	0.022	0.03
Test results	Disappearance of failure	With slight change	The fault condition is obvious

Through analysis of test data, main assembly parts causing the failure of the paddle pull rod are ball bearings on the paddle pull rod. Namely, the ball bearing selected according to the original qualified standard still has faults after being assembled.

After the reason that the ball bearing standard is incorrect, the fault is found out, and in order to increase a new ball bearing matching standard, a large amount of assembly data needs to be collected as a basis, so that an assembly simulation adjustment tool needs to be designed, test data collection is convenient to carry out, meanwhile, the fault is used as an improved new process method to ensure the product quality, and the qualification rate is improved.

The simulation adjustment tool can simulate the assembly working environment on the helicopter, and is convenient for accurate, convenient and rapid detection and adjustment of the blade pull rod gap.

And step two, assembling the blade pull rods with different sizes based on the main assembling parts causing the blade pull rod faults determined in the step one, carrying out multi-group secondary blade pull rod gap adjustment and detection experiments, and collecting experimental data.

The specific test method comprises the following steps: and adjusting the gap of the blade pull rod and performing a detection test by using a gap adjusting tool. The blade pull rod provided with the ball bearings with different sizes is installed on an assembly simulation adjusting tool, a specified tightening torque is applied to the positioning nut 1 for fixing, the tool can ensure that the angles of two ends of the blade pull rod are kept unchanged, and the full-stroke simulation of the length of the blade pull rod is realized through the movement of the sliding shaft 2 in the sliding groove 5.1 of the bottom plate 5. And (4) carrying out clearance measurement by using a dial indicator in the full-stroke adjustment process of the blade pull rod, and recording the size of the ball bearing used in the qualified state of the full stroke of the clearance of the blade pull rod. Test results are shown in table 4:

TABLE 4 units mm

in the prior art, the selection size requirement of the ball bearing assembled on the blade pull rod is not specified, and the blade pull rod is assembled by simply using a product manufactured by a bearing manufacturer according to a production standard. However, in terms of actual use, the assembly yield of the ball bearing directly used in production is only about 80%, and once a failure occurs, the ball bearing needs to be disassembled and adjusted again, and the failure cannot be guaranteed to be eliminated, so that the assembly selection standard of the ball bearing needs to be increased.

And analyzing the test data in the second step, wherein the key standard of the ball bearing matching is that the axial clearance of the ball bearing needs to be less than 0.020 mm. The paddle pull rod of the ball bearing with the axial clearance smaller than 0.020mm is reassembled, the adjustment and detection test of the clearance of the paddle pull rod with multiple groups of words is carried out, test data are collected, and the test result is shown in a table 5:

TABLE 5 units mm

By analyzing the above data it can be concluded that: the assembly qualification rate can be ensured to be 100 percent after the assembly is selected according to the new standard.

Therefore, the ball bearing with the axial clearance smaller than 0.020mm can effectively improve the one-time assembly yield of the blade pull rod.

In conclusion, the selection criteria of the ball bearing causing the blade pull rod fault are as follows: the axial clearance of the ball bearing is less than 0.020 mm.

Step four, carry out surface treatment to the main assembly part that causes paddle pull rod trouble that once assembles the qualification rate and does not meet the requirements, make it satisfy the user demand, specifically do:

the original ball bearing standard is the production standard of a bearing manufacturer, and in order to meet the assembly requirement of a product, a ball bearing with the axial clearance less than 0.020mm needs to be selected and screened according to the new assembly standard determined in the third step for use. In order to improve the utilization rate of parts and reduce waste, the surface treatment needs to be carried out on the ball bearing which has the axial clearance larger than 0.020mm after screening and meets the production standard, so that the ball bearing meets the assembly requirement.

The surface treatment method of the ball bearing with the axial clearance larger than 0.020mm comprises the following steps: the bearing outer ring cylindrical surface of the ball bearing is subjected to copper plating treatment, the copper plating layer has medium hardness, the passivated copper plating layer is bright light red, the copper plating layer is easy to polish and has high binding force with other metals, and the copper plating thickness is controlled according to the unilateral thickness of 0.01-0.015 mm. Meanwhile, the fit clearance is controlled in the assembly, the ball bearing is guaranteed to rotate flexibly and has no clamping stagnation after being assembled, and the copper plating layer of the ball bearing with the interference magnitude of more than 0.02mm is polished. The processed ball bearing meets the assembly requirement, can be directly used for assembly, improves the one-time assembly qualification rate, and eliminates the fault of the blade pull rod.

The specific processing methods and steps of the copper plating treatment and the grinding and polishing treatment of the surface of the ball bearing belong to the prior art, and those skilled in the art can know the prior art, so further details are not described in this embodiment.

Example 2

In the prior art, a method for measuring the clearance of a blade pull rod of a helicopter is to assemble the blade pull rod assembly, and connect the blade pull rod to measure the clearance when an automatic tilter and a rotor hub are installed on the helicopter. The measurement mode needs to be carried out after the paddle pull rod is installed, and the working efficiency is low. In order to reduce the process repetition, improve the working efficiency, optimize the working process and carry out the clearance measurement on the ground workbench in advance so as to meet the requirement of quick adjustment of a rotor system and a control system, the invention designs the tool for simulating the adjustment of the environment on the helicopter. The method specifically comprises the following steps:

referring to fig. 1-10, the invention provides a gap adjustment tool for a helicopter blade pull rod, which comprises a bottom plate 5, wherein one end of the bottom plate 5 is provided with a sliding groove 5.1 along the length direction of the bottom plate, the other end of the bottom plate 5 is connected with a fixed shaft assembly, a sliding shaft 2 capable of moving left and right along the length direction of the sliding groove 5.1 is arranged in the sliding groove 5.1, a sliding block 3 is sleeved on the sliding shaft 2, one end of the blade pull rod is fixed on the sliding shaft 2 through a positioning nut 1, the blade pull rod is located between the positioning nut 1 and the sliding block 3, and the other end of the blade pull rod is fixed on the fixed shaft assembly through the positioning nut 1.

When the embodiment is used, in order to reduce the process repetition and improve the working efficiency, an assembly simulation tool is necessary to be designed, the existing process flow is optimized, and the gap measurement is carried out on the ground workbench in advance, so that the requirement for quick adjustment of a rotor system and a control system is met. Specifically, when the helicopter blade pull rod needs to be assembled, simulated and adjusted, the installation environment of the helicopter blade pull rod on the helicopter is simulated, and the helicopter blade pull rod is installed on the assembly simulation adjusting tool and fixed. Specifically, two ends of a blade pull rod are respectively placed on a sliding shaft 2 and a fixed shaft assembly, positioning nuts 1 are arranged on the sliding shaft 2 and the fixed shaft assembly, and a specified tightening torque is applied to the positioning nuts 1 to ensure that the angles of the two ends of the blade pull rod are kept unchanged; the simulation of the full length stroke of the blade link is then carried out by the displacement of the sliding shaft 2 in the sliding groove 5.1 of the base plate 5. In the full-stroke adjustment process of the blade pull rod, the dial indicator is used for measuring the blade pull rod, so that the blade pull rod can still meet the use requirement after being adjusted arbitrarily during on-machine installation.

In this embodiment, a sliding groove 5.1 for connecting the sliding shaft 2 is formed in one end of the bottom plate 5, a fixing hole 5.2 and a first pin hole 5.3 for connecting the fixing shaft assembly are formed in the other end of the bottom plate 5, two sets of scale marks (not shown in the figure) are arranged on the bottom plate 5 along the length direction of the bottom plate 5, and the two sets of scale marks are symmetrically arranged along the horizontal center line of the bottom plate 5.

In this embodiment, the sliding block 3 includes a first cylindrical section 3.1 and a second cylindrical section 3.2 that are integrally formed, a diameter of the first cylindrical section 3.1 is larger than a diameter of the second cylindrical section 3.2, and a junction of the first cylindrical section 3.1 and the second cylindrical section 3.2 is chamfered. The upper surface of the first cylindrical section 3.1 is recessed inwards to form a connecting groove 3.3 matched with the shape of the blade pull rod joint, and a scale ring 4 is sleeved outside the second cylindrical section 3.2.

The middle of the first cylindrical section 3.1 is provided with a matching shaft diameter section 3.4 used for matching with the sliding shaft 2 and penetrating through the center of the blade pull rod joint, the upper end of the matching shaft diameter section 3.4 is communicated with a connecting groove 3.3, the lower end of the matching shaft diameter section 3.4 is communicated with a first transition section 3.5, and the lower end of the first transition section 3.5 is communicated with a threaded hole section 3.6. The first transition section 3.5 is arranged between the first cylindrical section 3.1 and the second cylindrical section 3.2, and the threaded hole section 3.6 is arranged in the middle of the second cylindrical section 3.2. The threaded hole section 3.6 is used for being in threaded connection with the sliding shaft 2 to form a bolt and nut matching structure, and the sliding shaft 2 is controlled to move or be fixed by adjusting the tightness degree of connection between the sliding shaft 2 and the threaded hole section 3.6 through rotation. The first transition section 3.5 is arranged to facilitate machining.

In this embodiment, the sliding shaft 2 includes a base 2.1, and a sliding shaft section 2.2, a second transition section 2.3, a first threaded shaft section 2.4, a third transition section 2.5, a connecting section 2.6 and a second threaded shaft section 2.7 which are sequentially arranged on the base 2.1 from bottom to top. The sliding shaft 2 penetrates through the bottom plate 5 from bottom to top and then is installed, and the size of a base 2.1 at the bottom of the sliding shaft 2 is larger than that of a slotted hole in the bottom plate 5, so that the sliding shaft 2 cannot be separated from the bottom plate 5 upwards. The sliding shaft section 2.2 is matched with a sliding groove 5.1 of the bottom plate 5. The second transition section 2.3 is provided for ease of manufacture. The first threaded shaft section 2.4 cooperates with the threaded hole section 3.6 of the sliding block 3 to form a fixing and tightening torque. The diameter of the third transition section 2.5 may be the same as the diameter of the connecting section 2.6, but will typically be designed with a different diameter to distinguish between the working section and the transition section, e.g. the working face shaft section of the working section typically has surface treatment requirements and higher roughness requirements, whereas the transition section does not. The connecting section 2.6 is connected with the blade tie rod joint. The second threaded shaft section 2.7 is matched with the positioning nut 1 and used for fixing the blade pull rod.

In this embodiment, the arrangement of the scale ring 4 can facilitate observation of the moving distance of the sliding shaft 2.2 groove lines 4.1 are symmetrically arranged on the scale ring 4 along the vertical central line of the scale ring, the groove lines 4.1 can be matched with length scale lines marked on the bottom plate 5, and the moving distance of the sliding shaft 2 and the length of the whole paddle pull rod can be visually observed. When the 2 groove lines 4.1 are aligned with the scribed lines on both sides of the base plate 5, the center of the 2 groove lines 4.1 is at the center of all the axes and is parallel to the fixed axis 6 on the other end, and the corresponding dimension of the scribed line on the base plate 5 is the length of the blade pull rod.

As a further description of the above embodiment, the fixed shaft assembly includes a fixed block 7, the fixed block 7 is connected to the bottom plate 5 through a pin 8, the top of the fixed block 7 is provided with an inclined plane, a connection hole 7.1 penetrating through the fixed block 7 and perpendicular to the inclined plane is formed in the inclined plane, a mounting hole 7.2 communicated with the connection hole 7.1 is formed in the side wall of the fixed block 7, a fixed shaft 6 is arranged in the connection hole 7.1, one end of the fixed shaft 6 is located in the mounting hole 7.2, and the other end of the fixed shaft 6 is matched with the positioning nut 1 to fix the end of the blade pull rod after penetrating through the connection hole 7.1.

When the blade drag link is used in the embodiment, the connecting hole 7.1 comprises a first through hole 7.11 and a second through hole 7.12 which are communicated with each other, and the first through hole 7.11 is used for installing the blade drag link. One end of the fixing shaft 6 is located in the mounting hole 7.2, and the other end of the fixing shaft penetrates through the second through hole 7.12 and the first through hole 7.11 in sequence and then is matched with the positioning nut 1 to fix the blade pull rod, so that the end angle of the blade pull rod is not changed when the length of the pull rod is adjusted.

In this embodiment, the fixing block 7 is a cylindrical block, the bottom center of the fixing block 7 protrudes outward to form a connecting cylinder 7.3, and the connecting cylinder 7.3 is inserted into the fixing hole 5.2 for positioning. The outer diameter of the connecting cylinder 7.3 is equal to the inner diameter of the fixing hole 5.2. An L-shaped opening is formed in the side wall of one side of the fixing block 7, a second pin hole 7.4 is formed in the bottom of the L-shaped opening, and the pin 8 penetrates through the first pin hole 5.3 and the second pin hole 7.4 in sequence and then connects the fixing block 7 with the bottom plate 5.

In this embodiment, for the convenience of troubleshooting, the fixed angle design that adopts of paddle pull rod in this embodiment, if promote with other helicopter paddle pull rods, but adjustable frock design becomes the structure of rotatable angle, satisfies the fixed operation that two sections of different model paddle pull rods connect the angle change requirement. The structure of the rotatable angle can be obtained by those skilled in the art by performing corresponding adjustment according to the prior art, and therefore, the specific structure thereof will not be further described in this embodiment. Both fixed angle and rotatable angle configurations are within the scope of the present application.

In conclusion, the assembly simulation adjusting tool can be used for rapidly realizing multi-group word assembly tests of different part sizes, comparison and analysis are carried out according to test data, and the matching standard range of pipe parts is stipulated again, so that the one-time assembly qualified rate is improved, and the working efficiency is further improved.

In conclusion, the invention can simulate the working environment on the aircraft, avoid blade pull rod gap measurement after assembly on the aircraft, and directly measure the gap on the ground workbench, thereby realizing the rapid adjustment of the rotor system and the control system, reducing the process repetition and improving the working efficiency; meanwhile, the main factor causing the failure of the paddle pull rod can be determined to be the ball bearing, and the matching standard of the ball bearing is determined, so that the one-time assembly qualification rate of the paddle pull rod is improved, the failure removal of the paddle pull rod is effectively guaranteed, and the working efficiency is improved. Therefore, the invention effectively overcomes various defects in the prior art and has high industrial utilization value.

The foregoing embodiments are merely illustrative of the principles and utilities of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or change the above-mentioned embodiments without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which can be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.

Claims

1. A helicopter blade pull rod gap adjusting method is characterized by mainly comprising the following steps:

2. The method for adjusting the clearance of the blade link of the helicopter of claim 1 wherein in step one, the method for troubleshooting the blade link comprises: and (3) carrying out an assembly test by adopting a method of measuring and counting the sizes and the matching sizes of all parts of the fault part, adjusting the parts to be replaced and replacing the assembly torque, and verifying and discharging item by item to determine the main assembly parts causing the fault.

3. The method for adjusting the clearance of the blade link of the helicopter according to claim 1, wherein in the second step, the clearance adjustment and the detection test of the blade link are performed by using a clearance adjustment tool.

4. The method for adjusting the clearance of the blade link of the helicopter according to claim 1, wherein in the fourth step, the method for performing surface treatment on the main assembly parts causing the failure of the blade link comprises the following steps: and carrying out surface copper plating treatment on the assembly parts.

5. The method for adjusting the clearance of the helicopter blade tie rod according to claim 4, wherein the thickness of the single side of the copper plating layer after the copper plating treatment on the surface of the fitting part is between 0.01mm and 0.015 mm.

6. The method for adjusting the clearance of the helicopter blade tie rod according to claim 4, wherein the interference after the blade tie rod is assembled on the surface-treated assembly part is greater than 0.02mm, and then the copper plating layer of the assembly part is polished.

7. The utility model provides a helicopter paddle pull rod clearance adjustment frock which characterized in that: including bottom plate (5), spout (5.1) have been seted up on the one end of bottom plate (5) along its length direction, and the other end of bottom plate (5) is connected with fixed axle subassembly, be equipped with in spout (5.1) and follow spout (5.1) length direction and remove sliding shaft (2), the cover is equipped with sliding block (3) on sliding shaft (2), and the one end of paddle pull rod is fixed in on sliding shaft (2) through set nut (1) and the paddle pull rod is located between set nut (1) and sliding block (3), the other end of paddle pull rod is fixed in on the fixed axle subassembly through set nut (1).

8. The helicopter blade tie rod clearance adjustment frock of claim 7 characterized in that: the lower pot head of sliding block (3) is equipped with scale circle (4).

9. The helicopter blade tie rod clearance adjustment frock of claim 7 characterized in that: the fixed shaft assembly comprises a fixed block (7), an inclined plane is arranged at the top of the fixed block (7), a connecting hole (7.1) which penetrates through the fixed block (7) and is perpendicular to the inclined plane is formed in the inclined plane, a fixed shaft (6) is arranged in the connecting hole (7.1), and the end portion of the paddle pull rod is fixed by the aid of the fixed shaft (6) after the fixed shaft (6) penetrates through the connecting hole (7.1) and is matched with the positioning nut (1).

10. The helicopter blade tie rod clearance adjustment frock of claim 9 characterized in that: connecting hole (7.1) are including first through-hole (7.11) and second through-hole (7.12) that communicate each other, mounting hole (7.2) with second through-hole (7.12) intercommunication are seted up to the lateral wall of fixed block (7), the one end of fixed axle (6) is located mounting hole (7.2), and the other end runs through mounting hole (7.2), second through-hole (7.12) and behind first through-hole (7.11) in proper order and fixes the tip of paddle pull rod with set nut (1) cooperation.