Rotor wing test device blade total pitch angle debugging method

Abstract

The invention discloses a method for debugging the total pitch angle of blades of a rotor test device, belongs to the field of icing wind tunnel tests, and aims to solve the problem that the total pitch angle of an existing rotor test device is difficult to debug. The method comprises the following steps: firstly, adjusting inclination angles of a fixed support and a rotor main shaft, then establishing random data consisting of random rotor positions of a blade angle driving motor and a blade angle arithmetic mean value, selecting the random data as a boundary of an interpolation rotor position, obtaining the interpolation rotor position corresponding to a target total pitch angle through interpolation operation, and if a deviation meets an error requirement, judging whether the deviation meets the error requirement. And if not, taking the interpolated rotor position as a theoretical rotor position to obtain corresponding relation data between the target total distance angle and the theoretical rotor position. Through the method, the corresponding relation between the blade total pitch angle and the theoretical rotor position of the blade angle driving motor can be quickly obtained, and the debugging time is greatly shortened.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of icing wind tunnel test, and particularly relates to a rotor test device blade total pitch angle debugging method. BACKGROUND

[0002] The wind tunnel test is widely used as an aerodynamics research method, and provides necessary guarantee for the development of the fields of aviation, spaceflight, railway transportation and the like. The rotor is a main component for providing lift for a helicopter, and rotor blade icing can cause problems such as blade vibration and torque increase, which has a great influence on safe flight of the helicopter. Compared with helicopter flight test under real icing weather conditions, rotor icing characteristics can be researched through development of icing wind tunnel test, which can greatly reduce research cost and test risk. In part rotor blade icing test research, the rotor test device blade does not have a cyclic pitch function, and each blade total pitch angle is uniformly adjusted, so as to research blade icing characteristics of the rotor blade under a certain blade total pitch angle condition. The test device blade total pitch angle precision and consistency of each blade angle all affect the icing characteristics. Before the wind tunnel test is developed, the angle control precision of the rotor test device blade total pitch angle needs to be debugged, so as to obtain accurate icing characteristics of different blade total pitch angles. The existing rotor test device is a rotor test device with uniformly adjusted each blade total pitch angle and without a cyclic pitch function, and the blade angle cannot be measured after installation. The total pitch angle debugging of the test device has great difficulty and a long period. SUMMARY

[0003] The application aims to provide a rotor test device blade total pitch angle debugging method, so as to solve the problem of great difficulty in total pitch angle debugging of the existing rotor test device. The technical solution adopted by the application is as follows.

[0004] A rotor test device blade total pitch angle debugging method comprises the following steps.

[0005] Step one, fix and level the fixed support of the test device;

[0006] Step two, adjust the inclination angle of the rotor main shaft to a vertical state;

[0007] Step three, measure the blade angle of the blades in real time;

[0008] Step four, establish random data composed of the random rotor position of the blade angle driving motor and the arithmetic average value of the blade angle;

[0009] Step five, calculate the deviation between each blade angle in the random data and the corresponding blade angle arithmetic average value, if the deviation is greater than the error requirement, adjust the mechanism gap, and then perform step four again;

[0010] Step six, first according to the target total angle of the test required, select the range of interpolation rotor position in random data, through the difference operation, get the interpolation rotor position, then measure the interpolation blade angle of each blade in the interpolation rotor position state, and calculate the arithmetic mean of the interpolation blade angle;

[0011] Step seven, calculate the deviation between the arithmetic mean of the interpolation blade angle and the target total angle, if the deviation is greater than the error requirement, then the interpolation rotor position greater than the error requirement and the corresponding arithmetic mean of the interpolation blade angle are taken as new random data, and step six is repeated to obtain new interpolation rotor position and new arithmetic mean of the interpolation blade angle, until the final arithmetic mean of the interpolation blade angle and the target total angle deviation meet the requirements, the final interpolation rotor position is taken as the theoretical rotor position, and the corresponding relationship data of the theoretical rotor position and the target total angle is recorded;

[0012] Step eight, repeat steps six and seven to complete all the theoretical rotor positions required by the test and the test relationship data of the corresponding target total angle;

[0013] Step nine, select part of the typical data in all test relationship data, and test the data repeatability deviation of the target total angle, if the deviation exceeds the error requirement, adjust the mechanism gap, and re-perform step four;

[0014] Step ten, the debugging is completed, the blades are reassembled, and the test relationship data obtained by step eight can be used to quickly obtain the target total angle required by the test through the theoretical rotor position.

[0015] Further, the specific method of step one is that the four corners of the fixing support of the test device are threadedly connected with jacking screws, so that the fixing support is supported on the mounting seat through the jacking screws, the fixing support is leveled by screwing the jacking screws, the plane of the fixing support is measured using an angle measuring instrument, until the horizontalities of two perpendicular directions on the plane of the fixing support meet the requirements, and then the fixing support and the mounting seat are fastened through fastening screws.

[0016] Further, the specific method of step two is to remove the upper piece of the hub, the plurality of blades, the plurality of cranks and the variable pitch box, install a main shaft inclination measuring platform on the lower piece of the hub, and place an angle measuring instrument on the main shaft inclination measuring platform, adjust the inclination of the rotor shaft through the inclination motor, and observe the reading of the angle measuring instrument until the rotor shaft is in a vertical state.

[0017] Further, the specific method of step three is to make a plurality of blade angle measuring platforms with the same connection conditions as the blades, remove the main shaft inclination measuring platform, reassemble the upper piece of the hub, and use the plurality of blade angle measuring platforms to replace the plurality of blades installed between the lower piece of the hub and the upper piece of the hub, the angle measuring instrument is placed on the blade angle measuring platform to display the blade angle of the corresponding blade in real time.

[0018] Furthermore, the specific method of step 4 is as follows: within the blade angle range required for the test, randomly select i blade angles to drive the rotor rotation angles of the motor as random rotor positions, and mark them as 、 、……、 , measure the blade angle of each blade under each random rotor position state, calculate the arithmetic mean of the random blade angle corresponding to each random rotor position, and mark them as 、 、……、 , mark the jth random blade angle arithmetic mean as , where j is any number in i, then Calculated by the following formula:

[0019] ;

[0020] Where:

[0021] n is the number of blades;

[0022] is the blade angle measurement of the nth blade at the jth random rotor position;

[0023] The arithmetic mean of i random rotor positions and corresponding i blade angles is used as random data, where i is a natural number greater than or equal to 2.

[0024] Furthermore, the specific method of step five is: under the j-th random rotor position state, the blade angle of the n-th blade and the corresponding arithmetic mean The deviation is ,like If the error is greater than the error index, adjust the gap between the blade, crank and pitch sleeve. If it is less than the error index, it is considered Equal to the blade collective pitch angle corresponding to the random rotor position state .

[0025] Furthermore, the specific method of step six is: first, according to the target total distance angle required by any test Size, select two adjacent random rotor positions and the corresponding blade angle arithmetic mean in the random data, set the selected two random positions to be and , the arithmetic mean values ​​of the two blade angles are and , assuming the arithmetic mean of the target blade angle Can be considered equal to , then < < ,exist and Set the interpolated rotor position between , Through interpolation operation, we get:

[0026] ;

[0027] Rotate the rotor of the blade angle drive motor to the interpolated rotor position , measure the blade angle of each blade at this time, and calculate the arithmetic mean of the interpolated blade angle .

[0028] Furthermore, the specific method of step seven is: if If the error is greater than the requirement, Relabeled as ,Will Relabeled as , and then and As new random data, repeat step 6;

[0029] until If the error requirement is met, As the theoretical rotor position ,think is the target collective angle The corresponding blade angle drives the rotor rotation angle position of the motor.

[0030] Furthermore, in steps 4 to 8, when adjusting the blade angle, in order to avoid the influence of mechanical clearance, each blade is made to move in one direction to change the blade angle.

[0031] Furthermore, in step 2, when adjusting the inclination angle of the rotor main shaft, in order to avoid the influence of mechanical clearance, the rotor main shaft is made to move in one direction to change the inclination angle.

[0032] Compared with the prior art, the present invention has the following beneficial effects:

[0033] The present invention eliminates the influence of installation and main shaft inclination on the measurement of blade angle by adjusting the fixed support and the inclination angle of the rotor main shaft; processes a blade angle measurement platform parallel to the chord line of the characteristic section of the blade, thereby solving the problem that the angle of the blade cannot be measured after installation; angle measurement platforms are installed for all blade positions, and the arithmetic mean of the blade angle is used as the nominal collective pitch angle of the blade, which effectively ensures the consistency of the angles of each blade and can obtain more accurate icing characteristics during high-speed rotation of the blade; there is a nonlinear relationship between the blade collective pitch angle and the rotor position of the blade angle drive motor. The corresponding relationship between the blade collective pitch angle and the theoretical rotor position of the blade angle drive motor is quickly obtained through interpolation operation, which can greatly shorten the debugging time. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 is a flow chart of the method of the present application;

[0035] Figure 2 is a schematic diagram of the overall structure of the test device of the present application;

[0036] Figure 3 is an A-A sectional view of Figure 2

[0037] Figure 4 is a schematic diagram of the overall structure of the total angle adjustment assembly;

[0038] Figure 5 is an E-E sectional view of Figure 4

[0039] Figure 6 is a partial enlarged view of C in Figure 5

[0040] Figure 7 is a partial enlarged view of D in Figure 5

[0041] Figure 8 is a B-B sectional view of Figure 4

[0042] Figure 9 is a schematic diagram of the connection of the variable-pitch box and the paddle;

[0043] Figure 10 is a schematic diagram of the sliding arrangement of the variable-pitch sliding sleeve on the variable-pitch box;

[0044] Figure 11 is a schematic diagram of the structure of the paddle;

[0045] Figure 12 is a schematic diagram of the structure of the crank;

[0046] Figure 13 is a schematic diagram of the connection of the main shaft inclination measurement platform and the lower piece of the hub;

[0047] Figure 14 is a schematic diagram of the connection of the paddle angle measurement platform and the hub.

[0048] ​​​​​In the figure, 1. Propeller blade, 2. Propeller hub upper plate, 3. Propeller hub lower plate, 4. Rotor main shaft, 5. Guide key, 6. Static ring gland, 7. Static ring, 8. Anti-torque arm, 9. Six-component balance, 10. Base, 11. Commutator, 12. Propeller motor, 13. Pitch control push rod, 14. Electric cylinder, 15. Bearing seat, 16. Speed ​​encoder, 17. Coupling, 18. Torque sensor, 19. Rotary ring gland, 20. Collective pitch adjustment bearing, 21. Rotary ring, 22. Push rod pin, 23. Bearing gland, 24. Main shaft bearing, 25. Lock nut, 26. Propeller blade bearing, 27. Crank, 28. Clamping ring, 29. Pitch control box upper plate, 30. Pitch control sleeve, 31. Pitch change box lower plate, 32. Slideway, 33. Square socket, 34. Circular plate, 35. Square bump, 36. Rocker, 37. Double-sided milled flat section, 38. Fixed support, 39. Fastening screw, 40. Jacking screw, 41. Pitch motor, 42. Pitch driving shaft, 43. Pitch driven shaft, 100. Collective pitch angle adjustment assembly, 200. Pitch adjustment assembly, 300. Mounting base, 400. Spindle pitch angle measurement platform, 500. Blade angle measurement platform. DETAILED DESCRIPTION

[0049] To make the objectives, technical solutions, and advantages of the present invention more clearly apparent, the present invention is described below using specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely illustrative and are not intended to limit the scope of the present invention. In addition, in the following description, descriptions of well-known structures and technologies are omitted to avoid unnecessary confusion of the concepts of the present invention.

[0050] The connections mentioned in the present invention are divided into fixed connections and detachable connections. The fixed connection refers to a non-detachable connection, including but not limited to conventional fixed connection methods such as hem connection, rivet connection, adhesive connection, and welding connection. The detachable connection refers to but not limited to conventional detachable connection methods such as bolt connection, snap connection, pin connection, and hinge connection. When the specific connection method is not clearly specified, it is assumed that at least one connection method can be found among the existing connection methods to achieve the function. Those skilled in the art can choose according to their needs. For example, a welded connection is selected for a fixed connection, and a bolted connection is selected for a detachable connection.

[0051] The present invention will be further described in detail below with reference to the accompanying drawings. The following embodiments are provided to explain the present invention, but the present invention is not limited to the following embodiments.

[0052] Example: Figures 1-14 As shown, the test device is a prior art, including a collective pitch angle adjustment assembly 100 and a pitch angle adjustment assembly 200. The collective pitch angle adjustment assembly 100 includes a plurality of blades 1, a rotor main shaft 4, a six-component balance 9, a base 10, a rotor motor 12, a pitch control push rod 13, a bearing seat 15, a torque sensor 18, a crank 27 and a pitch control sleeve 30.

[0053] The bearing seat 15, the six-component balance 9 and the base 10 are sequentially connected from top to bottom, the lower part of the rotor main shaft 4 is rotationally connected with the bearing seat 15 through two main shaft bearings 24, the collective pitch control rod 13 is axially and circumferentially connected with the upper part of the rotor main shaft 4, the lower end of the rotor main shaft 4 penetrates the six-component balance 9 and is connected with one end of the torque sensor 18, the other end of the torque sensor 18 is connected with the output shaft of the rotor motor 12 through the commutator 11, the bearing seat 15 is provided with a lifting mechanism, and the output end of the lifting mechanism is connected with the collective pitch control rod 13.

[0054] The hub is arranged at the top end of the rotor main shaft 4, the hub is composed of the upper hub piece 2 and the lower hub piece 3 which are connected in sequence, the hub is internally provided with a collective pitch control cavity, a plurality of connecting holes are arranged on the circumferential wall of the hub, the roots of the plurality of blades 1 are rotationally connected with the plurality of connecting holes in one-to-one correspondence, the root end face of the blade 1 is provided with a square insertion hole 33, the top end of the collective pitch control rod 13 is sleeved with a collective pitch control box, the collective pitch control box is located in the collective pitch control cavity, a plurality of sliding grooves 32 are arranged on the outer periphery of the collective pitch control box, a collective pitch control sliding sleeve 30 is slidably arranged in the sliding groove 32, the crank 27 comprises a circular plate body 34 at the middle part, a square protruding block 35 is arranged on one side end face of the circular plate body 34, a rocker 36 is eccentrically arranged on the other side end face of the circular plate body 34, the square protruding blocks 35 of the plurality of cranks 27 are insertedly connected with the square insertion holes 33 of the plurality of blades 1 in one-to-one correspondence, the rockers 36 of the plurality of cranks 27 are hingedly connected with the plurality of collective pitch control sliding sleeves 30 in one-to-one correspondence, and the sliding groove 32 is perpendicular to the corresponding blade 1.

[0055] The collective pitch control box comprises a collective pitch control box upper piece 29 and a collective pitch control box lower piece 31 which are connected in sequence, a plurality of sliding grooves 32 are arranged on the outer periphery of the collective pitch control box lower piece 31 and penetrate the collective pitch control box lower piece 31 upwards, the collective pitch control box upper piece 29 blocks the upper openings of the plurality of sliding grooves 32, the top end of the collective pitch control rod 13 is provided with a double-face milling flat section 37, the collective pitch control box upper piece 29 and the collective pitch control box lower piece 31 are sleeved on the double-face milling flat section 37, and a compression ring 28 is connected with the top end of the collective pitch control rod 13.

[0056] The base 10 is provided with a rotational speed encoder 16, and a measurement rotating ring of the rotational speed encoder 16 is connected with the rotor main shaft 4.

[0057] The upper part of the rotor main shaft 4 is provided with an inner hole, and the collective pitch control rod 13 is slidably arranged in the inner hole of the rotor main shaft 4.

[0058] The lifting mechanism comprises several electric cylinders 14 and an automatic tilting device, the automatic tilting device comprises a static ring gland 6, a static ring 7, a dynamic ring 21, a dynamic ring gland 19 and a total pitch adjusting bearing 20, two through long circular holes are arranged on the inner hole side wall of the rotor main shaft 4, the long circular holes are vertically arranged, the bottom of the variable pitch push rod 13 is provided with a push rod pin 22, the static ring gland 6 and the static ring 7 are clamped on the two sides of the outer ring of the total pitch adjusting bearing 20, the dynamic ring 21 and the dynamic ring gland 19 are clamped on the two sides of the inner ring of the total pitch adjusting bearing 20 respectively, the dynamic ring 21 is sleeved on the rotor main shaft 4, the two ends of the push rod pin 22 pass through the two long circular holes respectively and are connected with the dynamic ring 21, the push rod pin 22 is in sliding fit with the two long circular holes respectively, the rear cylinder cover of the electric cylinder 14 is connected with the bearing seat 15, the outer periphery of the static ring 7 is uniformly provided with several connecting ears, the piston rods of the several electric cylinders 14 are connected with the several connecting ears one by one.

[0059] The driving motor of the electric cylinder 14 is named as a blade angle driving motor, the blade angle driving motor drives the piston rod of the electric cylinder 14 to stretch and retract, so as to drive the automatic tilting device to slide up and down, and then adjust the blade angle of each blade 1, the blade angle driving motor is provided with an encoder, the rotation angle of the rotor of the blade angle driving motor can be identified and measured through the encoder, and the rotation angle of the rotor has a one-to-one correspondence with the blade angle of each blade 1.

[0060] The outer periphery of the rotor main shaft 4 is provided with two guide keys 5, the inner periphery of the dynamic ring 21 is vertically provided with two key grooves, and the two guide keys 5 are in sliding fit with the two key grooves.

[0061] The bearing seat 15 and the static ring 7 are connected through the anti-twist arm 8.

[0062] The inclination angle adjusting assembly 200 comprises a fixed support 38 and an inclination angle motor 41, the left and right ends of the base 10 are rotatably installed on the fixed support 38 through an inclination angle driving shaft 42 and an inclination angle driven shaft 43 respectively, the fixed support 38 is provided with the inclination angle motor 41, the output end of the inclination angle motor 41 is connected with the inclination angle driving shaft 42, and the base 10 is provided with an inclination angle sensor.

[0063] A blade total pitch angle debugging method of a rotor test device, comprising the following steps:

[0064] Step one, fix and level the fixed support 38 of the test device;

[0065] Step two, adjust the inclination angle of the rotor main shaft 4 to a vertical state;

[0066] Step three, measure the blade angle of the several blades 1 in real time;

[0067] Step four, establish random data composed of the random rotor position of the blade angle driving motor and the arithmetic average value of the blade angle;

[0068] Step five, calculate the deviation between each blade angle in random data and the corresponding arithmetic mean of blade angle, if the deviation is greater than the error requirement, adjust the mechanism gap, and re-perform step four;

[0069] Step six, first select the range of interpolation rotor position in random data according to the target total distance angle required by the test, obtain the interpolation rotor position through difference operation, then measure the interpolation blade angle of each blade 1 in the interpolation rotor position state, and calculate the arithmetic mean of interpolation blade angle;

[0070] Step seven, calculate the deviation between the arithmetic mean of interpolation blade angle and the target total distance angle, if the deviation is greater than the error requirement, take the interpolation rotor position greater than the error requirement and the corresponding arithmetic mean of interpolation blade angle as new random data, and repeat step six to obtain new interpolation rotor position and new arithmetic mean of interpolation blade angle, until the final arithmetic mean of interpolation blade angle and the target total distance angle meet the requirement, take the final interpolation rotor position as the theoretical rotor position, and record the corresponding relationship data of the theoretical rotor position and the target total distance angle;

[0071] Step eight, repeat steps six and seven to complete all theoretical rotor positions and test relationship data of corresponding target total distance angles required by the test;

[0072] Step nine, select part of the typical data in all test relationship data, and test the data repeatability deviation of the target total distance angle, if the deviation exceeds the error requirement, adjust the mechanism gap, and re-perform step four;

[0073] Step ten, the debugging is completed, the blades 1 are reassembled, and through the test relationship data obtained in step eight, the target total distance angle required by the test can be quickly obtained through the theoretical rotor position.

[0074] The specific method of step one is that the four corners of the fixed support 38 of the test device are threadedly connected with jacking screws 40, so that the fixed support 38 is supported on the mounting seat 300 through the jacking screws 40, the fixed support 38 is leveled by screwing each jacking screw 40, the plane of the fixed support 38 is measured using an angle measuring instrument, until the horizontalities of two perpendicular directions on the plane of the fixed support 38 meet the requirements, and then the fixed support 38 and the mounting seat 300 are fastened through the fastening screws 39.

[0075] The specific method of step two is that the upper piece of the hub 2, the plurality of blades 1, the plurality of cranks 27 and the variable pitch box are removed, the main shaft inclination measuring platform 400 is installed on the lower piece of the hub 3, and the angle measuring instrument is placed on the main shaft inclination measuring platform 400, the inclination of the rotor shaft 4 is adjusted through the inclination motor 41, and the indication of the angle measuring instrument is observed until the rotor shaft 4 is in the vertical state.

[0076] The specific method of step three is: making a blade angle measuring platform 500 with the same connection condition as the blade 1, disassembling the main shaft inclination angle measuring platform 400, reassembling the upper blade hub piece 2, and using a plurality of blade angle measuring platforms 500 to replace a plurality of blades 1 and install them between the lower blade hub piece 3 and the upper blade hub piece 2, and placing an angle measuring instrument on the blade angle measuring platform 500 to display the blade angle of the corresponding blade 1 in real time.

[0077] The specific method of step four is: within the range of blade angles required for the test, randomly selecting i blade angle rotor rotation angles as random rotor positions, and sequentially marking them as 、 、……、 , measuring the blade angle of each blade 1 in each random rotor position state, calculating the random blade angle arithmetic mean corresponding to each random rotor position, and sequentially marking them as 、 、……、 , marking the jth random blade angle arithmetic mean in the plurality of random blade angle arithmetic means as , where j is any number in i, then is calculated by the following formula:

[0078] ;

[0079] In the formula:

[0080] n is the number of blades 1;

[0081] is the blade angle measurement value of the nth blade 1 at the jth random rotor position;

[0082] The i random rotor positions and the i blade angle arithmetic means corresponding thereto are used as random data, wherein the measurement data of the blade angle needs to include the minimum blade angle and the maximum blade angle required for the test conditions, and therefore i is a natural number greater than or equal to 2.

[0083] The specific method of step five is: the deviation of the blade angle of the nth blade 1 at the jth random rotor position state from the corresponding arithmetic mean is , if is greater than the error index, the gap between the blade 1, the crank 27, and the variable pitch sliding sleeve 30 is adjusted, and if is less than the error index, it is considered that is equal to the total pitch angle of the blades under the corresponding random rotor position state .

[0084] The specific method of step six is: first, according to the target total pitch angle required for any test Size, in random data to select the adjacent two random rotor position and the corresponding blade angle arithmetic mean, set the selected two random position is and , the corresponding two blade angle arithmetic mean is and , assuming the target blade angle arithmetic mean may be considered equal to , so that < < , between and set interpolation rotor position , by interpolation operation:

[0085] ;

[0086] the blade angle drive motor rotor to the interpolation rotor position , the measurement at this time each blade 1 blade angle, and calculate the interpolation blade angle arithmetic mean .

[0087] Step seven is the specific method: if greater than the error requirement, will relabel , will relabel , and and as the new random data, and repeat step six;

[0088] until satisfy the error requirement, will as the theoretical rotor position , think is the target total distance angle corresponding to the blade angle drive motor rotor angle position.

[0089] In step four to step eight, adjust the blade angle, in order to avoid the influence of mechanical clearance, each blade 1 unidirectional motion change blade angle.

[0090] In step two, adjust the tilt angle of the rotor main shaft 4, in order to avoid the influence of mechanical clearance, the rotor main shaft 4 unidirectional motion change tilt angle.

[0091] The application eliminates the influence of installation and rotor main shaft 4 inclination on the measurement of blade angle by adjusting the fixed support 38 and the inclination of the rotor main shaft 4; the blade angle measurement platform 500 parallel to the chord line of the characteristic section of the blade 1 solves the problem that the blade 1 cannot be measured after installation; the angle measurement platform is installed at all blade positions, and the arithmetic average of the blade angle is used as the nominal total distance angle of the blade, which effectively ensures the consistency of the angles of the blades, and more accurate icing characteristics of the blades during high-speed rotation can be obtained; the total distance angle of the blade and the rotor position of the blade angle driving motor are in a nonlinear relationship, and the corresponding relationship between the total distance angle of the blade and the theoretical rotor position of the blade angle driving motor is quickly obtained through interpolation operation, which can greatly shorten the debugging time. The blade total distance angle debugging method of the rotor test device provided by the application is conducive to standardizing the debugging process of subsequent test devices without periodic pitch adjustment function and unified adjustment of the total distance angle of the blades.

[0092] The above examples are only illustrative of the application and do not limit the protection scope thereof, and a person skilled in the art can also make changes to part of it, as long as the spirit and substance of the application are not exceeded, and it is within the protection scope of the application.

Claims

1. A method for debugging the collective pitch angle of blades of a rotor test device, characterized in that: The following steps are involved: Step 1, fixing and leveling the fixed support (38) of the test device; Step 2: Adjust the inclination angle of the rotor main shaft (4) to a vertical state; Step 3: measuring the blade angles of the plurality of blades (1) in real time; Step 4: Create random data consisting of the random rotor position of the blade angle drive motor and the arithmetic mean of the blade angle; Step 5: Calculate the deviation between each blade angle in the random data and the arithmetic mean of the corresponding blade angle. If the deviation is greater than the error requirement, adjust the mechanism clearance and repeat step 4. Step 6: First, according to the target collective pitch angle required by the test, select the range of the interpolated rotor position in the random data, obtain the interpolated rotor position through difference calculation, then measure the interpolated blade angle of each blade (1) under the interpolated rotor position state, and calculate the arithmetic mean of the interpolated blade angle; Step 7: Calculate the deviation between the arithmetic mean of the interpolated blade angles and the target collective pitch angle. If the deviation is greater than the error requirement, use the interpolated rotor position greater than the error requirement and the corresponding arithmetic mean of the interpolated blade angle as new random data, and repeat step 6 to obtain a new interpolated rotor position and a new arithmetic mean of the interpolated blade angle until the final deviation between the arithmetic mean of the interpolated blade angle and the target collective pitch angle meets the requirement. Use the final interpolated rotor position as the theoretical rotor position, and record the corresponding relationship data between the theoretical rotor position and the target collective pitch angle. Step 8: Repeat steps 6 and 7 to complete all the test relationship data of the theoretical rotor positions and the corresponding target collective pitch angles required for the test; Step 9: Select some typical data from all the test relationship data and test the data repeatability deviation of the target total distance angle. If the deviation exceeds the error requirement, adjust the mechanism clearance and repeat step 4. Step 10: After debugging is completed, the blade (1) is reinstalled. The target collective pitch angle required for the test can be quickly obtained through the theoretical rotor position using the test relationship data obtained in step 8.

2. The method for adjusting the blade collective pitch angle of a rotor test device according to claim 1, characterized in that: The specific method of step one is as follows: the four corners of the fixed support (38) of the test device are all threadedly connected with jacking screws (40), so that the fixed support (38) is supported on the mounting base (300) by the jacking screws (40), the fixed support (38) is leveled by screwing each jacking screw (40), and the plane of the fixed support (38) is measured using an angle measuring instrument until the horizontality of the two vertical directions on the plane of the fixed support (38) meets the requirements, and then the fixed support (38) and the mounting base (300) are fastened by tightening screws (39).

3. The method for adjusting the blade collective pitch angle of a rotor test device according to claim 2, characterized in that: The specific method of step 2 is: remove the propeller hub upper plate (2), a plurality of blades (1), a plurality of cranks (27) and the pitch box, install the main shaft inclination angle measuring platform (400) on the propeller hub lower plate (3), and place an angle measuring instrument on the main shaft inclination angle measuring platform (400), adjust the inclination angle of the rotor main shaft (4) by the inclination motor (41), and observe the reading of the angle measuring instrument until the rotor main shaft (4) is in a vertical state.

4. The method for adjusting the blade collective pitch angle of a rotor test device according to claim 3, characterized in that: The specific method of step three is: making a blade angle measuring platform (500) with connection conditions consistent with the blade (1), disassembling the main shaft inclination angle measuring platform (400), reinstalling the hub upper piece (2), and using a plurality of blade angle measuring platforms (500) to replace a plurality of blades (1) and install them between the hub lower piece (3) and the hub upper piece (2), and placing an angle measuring instrument on the blade angle measuring platform (500) for real-time display of the blade angle of the corresponding blade (1).

5. The method for adjusting the blade collective pitch angle of a rotor test device according to claim 1, characterized in that: The specific method of step 4 is: within the blade angle range required for the test, randomly select i blade angles to drive the rotor rotation angles of the motor as random rotor positions, and mark them in turn as 、 、……、 , measure the blade angle of each blade (1) under each random rotor position state, calculate the arithmetic mean of the random blade angle corresponding to each random rotor position, and mark them as 、 、……、 , mark the jth random blade angle arithmetic mean as , where j is any number in i, then Calculated by the following formula: ； Where: n is the number of blades (1); is the blade angle measurement of the nth blade (1) at the jth random rotor position; The arithmetic mean of i random rotor positions and corresponding i blade angles is used as random data, where i is a natural number greater than or equal to 2.

6. The method for adjusting the blade collective pitch angle of a rotor test device according to claim 5, characterized in that: The specific method of step 5 is: the blade angle of the nth blade (1) under the jth random rotor position state is and the corresponding arithmetic mean The deviation is ,like If the error is greater than the error index, adjust the gap between the blade (1), crank (27) and pitch sleeve (30). If it is less than the error index, it is considered Equal to the blade collective pitch angle corresponding to the random rotor position state .

7. The method for adjusting the blade collective pitch angle of a rotor test device according to claim 6, characterized in that: The specific method of step six is: first, according to the target total angle required by any test Size, select two adjacent random rotor positions and the corresponding blade angle arithmetic mean in the random data, set the selected two random positions to be and , the arithmetic mean values ​​of the two blade angles are and , assuming the arithmetic mean of the target blade angle Can be considered equal to , then < < ,exist and Set the interpolated rotor position between , Through interpolation operation, we get: ； Rotate the rotor of the blade angle drive motor to the interpolated rotor position , measure the blade angle of each blade (1) at this time, and calculate the arithmetic mean of the interpolated blade angle .

8. The method for adjusting the blade collective pitch angle of a rotor test device according to claim 7, characterized in that: The specific method of step seven is: If the error is greater than the requirement, Relabeled as ,Will Relabeled as , and then and As new random data, repeat step 6; until If the error requirement is met, As the theoretical rotor position ,think is the target collective angle The corresponding blade angle drives the rotor rotation angle position of the motor.

9. The method for adjusting the blade collective pitch angle of a rotor test device according to claim 8, characterized in that: In steps 4 to 8, when adjusting the blade angle, in order to avoid the influence of mechanical clearance, each blade (1) is made to move in one direction to change the blade angle.

10. The method for adjusting the blade collective pitch angle of a rotor test device according to claim 3, characterized in that: In step 2, when adjusting the inclination angle of the rotor main shaft (4), in order to avoid the influence of mechanical clearance, the rotor main shaft (4) is made to move in one direction to change the inclination angle.

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