Adjusting method and device for trailing edge flap type active control rotor wing flap deflection angle difference

Abstract

The invention provides a method and a device for adjusting a trailing edge flap type active control rotor wing flap deflection angle difference. The method comprises the following steps: arranging a sensor for measuring the output displacement of a piezoelectric actuator in a driving mechanism of a trailing edge flap type active control rotor wing blade; in a non-rotating state, synchronously measuring the output displacement of the piezoelectric actuator and the deflection angle of the flap of each blade under voltage excitation; establishing a corresponding relation between the output displacement of the piezoelectric actuator and the deflection angle of the flap; calculating an actual value of a force arm of each paddle driving mechanism; calculating the number of shims, needing to be compensated, of each paddle; and a corresponding number of shims capable of being shifted are added at the driving force arm position of each paddle for adjustment. According to the invention, the problem of adjusting the deflection angle difference of each blade flap is solved from the structural perspective, command signals input by the piezoelectric drivers are not influenced, and the safe use of the drivers in each blade is ensured.

Description

Technical Field

[0001] This invention belongs to the field of rotor testing technology, and particularly relates to a method and device for adjusting the difference in flap deflection angle of an active control rotor with trailing edge flaps. Background Technology

[0002] Active control rotors with trailing edge flaps address vibration and noise issues at the rotor itself, representing a key direction for future intelligent helicopter rotor development. By controlling the dynamic deflection of the trailing edge flaps, additional high-order harmonic aerodynamic forces are generated on the blade's lifting surface. Appropriate control of the amplitude, frequency, and phase of these high-order harmonic aerodynamic forces effectively counteracts the corresponding high-order harmonic components in the blade's distributed load, thus achieving vibration reduction. Because the trailing edge flaps are located at the outer end of blades with high dynamic pressure, even a small deflection angle can cause significant aerodynamic load changes. However, differences in the performance of the piezoelectric actuators of each blade and tolerances in the lever arm of the drive mechanism during blade manufacturing lead to variations in the flap deflection angles of each blade, resulting in a reduction in the vibration and noise reduction effect of the active control rotor with trailing edge flaps.

[0003] Currently, for large-sized trailing-edge flap-type active control rotors, the difference in flap deflection angles among the blades can be reduced by designing a larger drive mechanism lever arm. However, due to the limitations of the blade space structure, the effectiveness of this approach is limited. For model-level rotors, the drive mechanism lever arm is relatively small, and therefore greatly affected by manufacturing tolerances, making adjustment more difficult. Currently, the only way to adjust it is by adjusting the command signal of the piezoelectric actuator. This makes the control of the piezoelectric actuator command signal complex, and the command signal of the piezoelectric actuator of individual blades may exceed the allowable voltage range, which may lead to damage to the piezoelectric actuator. Summary of the Invention

[0004] To address the issue of flap deflection angle differences among the blades of an active control rotor with trailing edge flaps, this invention provides a method and apparatus for adjusting these differences. From a structural perspective, it compensates for the driving force arm, reducing the flap deflection angle differences among the blades. The technical solution is as follows:

[0005] In a first aspect, a method for adjusting the flap deflection angle difference of an active control rotor with trailing edge flaps is provided, characterized by comprising:

[0006] Step 1: Install a sensor in the drive mechanism of the trailing edge flap type active control rotor blade to measure the output displacement of the piezoelectric actuator;

[0007] Step 2: In a non-rotating state, simultaneously measure the output displacement of the piezoelectric actuator and the deflection angle of the flaps for each blade under voltage excitation;

[0008] Step 3: Establish the correspondence between the output displacement of the piezoelectric actuator and the deflection angle of the flap;

[0009] Step 4: Calculate the actual value of the lever arm of each blade drive mechanism;

[0010] Step 5: Calculate the number of adjustable shims required to compensate for each blade;

[0011] Step 6: Adjust the blades by adding the appropriate number of adjustable shims to the drive arm position.

[0012] Optionally, in the second step, in a non-rotating state, for each blade, the output displacement Ui of the piezoelectric actuator during one stable operation cycle is measured using the displacement sensor set in the first step, and the deflection angle Φi of the flap is simultaneously measured using an tilt sensor or a laser displacement sensor; during measurement, the actuator uses quasi-static excitation or static excitation, and the excitation amplitude is consistent with the excitation voltage amplitude during actual operation; one cycle refers to the excitation voltage of the piezoelectric actuator including a boost phase and a buck phase. During the boost phase, the excitation voltage monotonically increases from the lowest voltage to the highest voltage, and during the buck phase, the excitation voltage monotonically decreases from the highest voltage to the lowest voltage.

[0013] Optionally, in the third step, for each blade, the output displacement Ui of the piezoelectric actuator and the deflection angle Φi of the flap, obtained from the synchronous measurement in the second step, are fitted using the least squares method to establish the relationship between the piezoelectric actuator displacement u and the flap deflection angle. Relationship curve: Where k and b are coefficients obtained by least squares fitting.

[0014] Optionally, in the fourth step, the piezoelectric actuator displacement u of each blade and the flap deflection angle obtained in the third step are used as the basis for the calculation. The coefficient k in the relationship curve is used to calculate the actual value of the lever arm of each blade drive mechanism, r = 180 / π / k, using the following formula.

[0015] Optionally, in step five, the blade with the largest lever arm in the drive mechanism among all blades is selected as the reference blade for flap deflection adjustment. This blade is not adjusted, and the number of adjustable shims n = (r) required for compensation of other blades is calculated. max -r) / d, where d is the thickness of a single-layer removable pad; n is a positive integer, rounded to the nearest integer.

[0016] Optionally, in step six, based on the results calculated in step five, a corresponding number of movable shims are added to the driving arm position of each blade to complete the adjustment of the flap deflection angle of each blade.

[0017] Furthermore, the method also includes:

[0018] Step 7: Conduct rotational tests on the trailing edge flap type active control rotor to obtain the piezoelectric actuator output displacement Vi measured by the sensor under a certain flight state;

[0019] Step 8: Substitute the piezoelectric actuator output displacement Vi obtained in step 7 into the relationship curve established in step 3 to obtain the flap deflection angle θi = k*Vi.

[0020] In a second aspect, an adjustment device is provided for performing the adjustment method for the trailing edge flap type active control rotor flap angle difference as described in any of the first aspects, comprising:

[0021] The module is used to set up a sensor for measuring the output displacement of the piezoelectric actuator in the drive mechanism of the trailing edge flap type active control rotor blade.

[0022] The measurement module is used to synchronously measure the output displacement of each blade under voltage excitation and the deflection angle of the flaps in a non-rotating state.

[0023] A module is established to establish the correspondence between the output displacement of the piezoelectric actuator and the deflection angle of the flap;

[0024] The calculation module is used to calculate the actual value of the lever arm of each blade drive mechanism;

[0025] Calculate the number of adjustable shims required to compensate for each blade;

[0026] The setting module is also used to add a corresponding number of adjustable shims to the drive arm position of each blade for adjustment.

[0027] The beneficial effects of this invention are at least as follows:

[0028] By employing the measured relationship between the displacement of the piezoelectric actuator and the flap deflection angle of an actively controlled rotor blade with trailing edge flaps, the actual equivalent driving force arm of each blade is calculated due to factors such as differences in piezoelectric actuator performance and tolerances in the drive mechanism lever arm during blade manufacturing. Furthermore, by adjusting the driving force arm, the difference in flap deflection angle among each blade is adjusted. This invention solves the problem of adjusting the difference in flap deflection angle among blades from a structural perspective without affecting the command signal input to the piezoelectric actuator, ensuring the safe operation of the actuator in each blade. Attached Figure Description

[0029] Figure 1 A flowchart illustrating the adjustment method for the difference in flap deflection angle of an active control rotor with trailing edge flaps.

[0030] Figure 2 This is a schematic diagram of the fitting relationship between the displacement of the piezoelectric actuator and the deflection angle of the flap. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0032] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0033] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited from each other.

[0034] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0035] An embodiment of the present invention provides a method for adjusting the flap deflection angle difference of an active control rotor with trailing edge flaps, which mainly includes the following steps:

[0036] Step 1: Set up the sensor to measure the displacement output of the piezoelectric actuator.

[0037] A sensor is arranged in the drive mechanism of the trailing-edge flap-type actively controlled rotor blade to measure the output displacement u of the piezoelectric actuator. i .

[0038] Step 2: In a non-rotating state, simultaneously measure the output displacement of the piezoelectric actuator and the deflection angle of the flaps for each blade under voltage excitation.

[0039] In the non-rotating state, for each blade, the output displacement Ui of the piezoelectric actuator during one stable operation cycle is measured using the displacement sensor arranged in the first step. Simultaneously, the deflection angle Φi of the flap is measured using an tilt sensor or laser displacement sensor. During measurement, the actuator uses quasi-static or static excitation, with the excitation amplitude consistent with the actual operating excitation voltage amplitude. One cycle refers to the excitation voltage of the piezoelectric actuator including a boost phase and a buck phase. During the boost phase, the excitation voltage monotonically increases from the lowest voltage to the highest voltage, and during the buck phase, the excitation voltage monotonically decreases from the highest voltage to the lowest voltage.

[0040] Step 3: Establish the relationship curve between the displacement of the piezoelectric actuator and the deflection angle of the flap.

[0041] For each blade, the output displacement Ui of the piezoelectric actuator and the deflection angle Φi of the flap, obtained from the second step of synchronous measurement, are fitted using the least squares method to establish the relationship between the piezoelectric actuator displacement u and the flap deflection angle. Relationship curve: Where k and b are coefficients obtained by least squares fitting.

[0042] Step 4: Calculate the actual value of the lever arm of each blade drive mechanism.

[0043] Based on the piezoelectric actuator displacement u of each blade and the flap deflection angle obtained in step three... The coefficient k of the relationship curve is used to calculate the actual value of the lever arm of each blade drive mechanism, r = 180 / π / k, using the following formula.

[0044] When the piezoelectric actuator in the drive mechanism is displaced by u, it causes the flap to generate... The deflection angle, since the displacement u of the piezoelectric actuator is a micro-displacement, can be equivalently considered as the flap rotation axis as the rotation center and the drive mechanism lever arm r as the rotation radius, the flap deflects by [value missing]. When the angle is angular, the corresponding arc length is the displacement u of the piezoelectric actuator. Therefore, the relationship between the actuator displacement u and the flap deflection angle can be established as follows:

[0045]

[0046] Based on the piezoelectric actuator displacement u of each blade and the flap deflection angle obtained in step three... Based on the coefficient k of the relationship curve, the actual value of the lever arm of each blade drive mechanism, r = 180 / π / k, is calculated.

[0047] Step 5: Calculate the number of adjustable shims required to compensate for each blade.

[0048] Select the blade with the largest lever arm in the drive mechanism among all blades as the reference blade for flap deflection adjustment. This blade will not be adjusted. Calculate the number of adjustable shims n = (r... max -r) / d, where d is the thickness of a single-layer removable pad; n is a positive integer, rounded to the nearest integer.

[0049] Based on step four, the lever arms of each blade drive mechanism are calculated to be r. j The driving lever arm of the largest blade is r. max The blade with the largest lever arm in the drive mechanism among all blades is selected as the reference blade for flap deflection adjustment; this blade is not adjusted. The number n of adjustable shims required for compensation of the j-th blade is calculated. j =(r max -r j ) / d, where d is the thickness of a single removable shim; n j If the result is a positive integer, it will be rounded to the nearest integer.

[0050] Step 6: Adjust the blades by adding the appropriate number of adjustable shims to the drive arm position.

[0051] Based on the calculation results in step 5, add a corresponding number of adjustable shims at the driving arm position of each blade to complete the adjustment of the flap deflection angle of each blade.

[0052] Furthermore, in another embodiment, the calculation results from the third step can also solve the problem of flap angle measurement when model rotors with a diameter of 3m or less cannot be equipped with flap angle sensors, or when large rotors have flap angle sensors that are damaged during missions. Specifically:

[0053] Step 7: Conduct a rotation test on the trailing edge flap type active control rotor to obtain the output displacement Vi of the piezoelectric actuator under a certain flight state.

[0054] Rotational tests were conducted on a trailing-edge flap-type active control rotor to obtain the output displacement Vi of the piezoelectric actuator measured by sensors under a certain flight condition.

[0055] Step 8: Measurement of flap deflection angle.

[0056] Substituting the piezoelectric actuator output displacement Vi obtained in step seven into the relationship curve established in step three, we can obtain the flap deflection angle θi = k*Vi.

[0057] This invention calculates the actual equivalent driving force arm of each blade by using the measured relationship between the displacement of the piezoelectric actuator of the trailing edge flap-type active control rotor blade and the flap deflection angle, and then adjusts the difference in flap deflection angle of each blade by adjusting the driving force arm.

[0058] For example, in one embodiment, the adjustment of the difference in rotor flap deflection angle by actively controlling the trailing edge flap type is specifically implemented as follows:

[0059] (1) Arrange a sensor for measuring the displacement output of the piezoelectric actuator in the drive mechanism of the trailing edge flap type active control rotor blade, and attach strain gauges to the piezoelectric actuator stack.

[0060] (2) In the non-rotating state, apply the following static excitation voltages sequentially to the piezoelectric drive: Ui = 0V, 10V, 20V, ..., 120V, 130V, 120V, ..., 0V. Use the displacement sensor arranged in the first step to measure the output displacement Wi of the piezoelectric drive during one cycle of stable operation. Use the tilt sensor or laser displacement sensor attached to the flap to synchronously measure the deflection angle of the blade flap. Taking a certain blade as an example, the test results are shown in Table 1.

[0061] Table 1. Output displacement of a piezoelectric actuator and deflection angle of flaps for a certain blade under excitation voltage.

[0062]

[0063] (3) Taking a certain blade as an example, such as Figure 2 As shown, the least squares method is used to fit the data obtained in the table in the second step to obtain the piezoelectric actuator displacement w and the flap deflection angle. The relationship curve is as follows: Where k = 0.0255° / μm.

[0064] (4) Taking a certain blade as an example, using the k = 0.0255° / μm obtained in the second step, and using the formula r = 180 / π / k, the actual value of the lever arm of the blade drive mechanism can be calculated as r = 2.247mm.

[0065] (5) Taking two blades as an example, the actual values ​​of the driving force arm of the two blades calculated in step four are r1 = 2.247 mm and r2 = 2.162 mm, respectively. When using movable shims with a single layer thickness of 0.05 mm for force arm compensation, the blade with a driving force arm of r1 = 2.247 mm does not need to be adjusted, while the blade with a driving force arm of r2 = 2.162 mm needs to have n = 2 movable shims added at the force arm position.

[0066] (6) Add n=2 movable shims at the blade lever arm position where the lever arm is r2=2.162mm, so as to complete the adjustment of the difference in the flap deflection angle of each blade.

[0067] Example 2: Flap angle measurement under specific circumstances, specifically implemented as follows:

[0068] (1) Arrange a sensor for measuring the displacement output of the piezoelectric actuator in the drive mechanism of the trailing edge flap type active control rotor blade, and attach strain gauges to the piezoelectric actuator stack.

[0069] (2) In the non-rotating state, the following static excitation voltages are applied to the piezoelectric drive in sequence: Ui = 0V, 10V, 20V, ..., 120V, 130V, 120V, ..., 0V. The output displacement Wi of the piezoelectric drive during one cycle of stable operation is measured using the displacement sensor arranged in the first step. The deflection angle i of the blade flap is measured synchronously using the tilt sensor or laser displacement sensor attached to the flap. Taking a certain blade as an example, the test results are shown in Table 1.

[0070] (3) Taking a certain blade as an example, such as Figure 2 As shown, the least squares method is used to fit the data obtained in the table in the second step to obtain the piezoelectric actuator displacement w and the flap deflection angle. The relationship curve is as follows: Where k = 0.0255° / μm.

[0071] (4) Conduct rotational tests on the trailing edge flap type active control rotor and obtain the output displacement V = 263 μm of the piezoelectric actuator measured by the sensor under a certain flight state.

[0072] (5) Substituting the piezoelectric actuator output displacement Vi obtained in step four into the relationship curve established in step three, the flap deflection angle θ = 6.49° can be obtained.

[0073] This invention employs a measured relationship between the displacement of the piezoelectric actuator and the flap deflection angle of an actively controlled rotor blade with trailing edge flaps. It calculates the actual equivalent driving force arm of each blade due to factors such as differences in piezoelectric actuator performance and tolerances in the drive mechanism's lever arm during blade manufacturing. By adjusting the driving force arm, the difference in flap deflection angle among the blades is adjusted. This structurally solves the problem of adjusting the flap deflection angle difference among the blades without affecting the command signal input to the piezoelectric actuator, thus ensuring the safe operation of the actuators in each blade.

[0074] The above description merely illustrates embodiments of the present invention and is quite specific and detailed; however, it should not be construed as limiting the scope of the patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Furthermore, any parts of the present invention not described in detail are conventional techniques.

Claims

1. A method of adjusting a difference in flap angle of a trailing edge flap type active control rotor flap, characterized by, The method comprises: First step: setting a sensor for measuring the output displacement of the piezoelectric driver in the driving mechanism of the rotor blade of the trailing edge flap type active control rotor; Second step: synchronously measuring the output displacement of the piezoelectric driver and the deflection angle of the flap under voltage excitation in a non-rotating state; Third step: establishing the corresponding relationship between the output displacement of the piezoelectric driver and the deflection angle of the flap; Fourth step: calculating the actual value of the driving force arm of each blade; Fifth step: calculating the number of shiftable shims required for compensation of each blade; Sixth step: adding the corresponding number of shiftable shims to the driving force arm position of each blade for adjustment.

2. The method of claim 1, wherein, In the second step, for each blade, the displacement sensor set in the first step is used to measure the output displacement Ui of the piezoelectric driver in a stable operation cycle, and the tilt angle sensor or laser displacement sensor is used to synchronously measure the deflection angle Φi of the flap in a non-rotating state; the driver uses quasi-static excitation or static excitation during measurement, and the excitation amplitude is consistent with the excitation voltage amplitude in actual work; one cycle refers to that the excitation voltage of the piezoelectric driver includes a voltage rising stage and a voltage falling stage; in the voltage rising stage, the excitation voltage monotonously rises from the lowest voltage to the highest voltage, and in the voltage falling stage, the excitation voltage monotonously falls from the highest voltage to the lowest voltage.

3. The method of claim 1, wherein, In the third step, for each blade, the least square method is used to fit the output displacement Ui of the piezoelectric driver and the deflection angle Φi of the flap obtained in the second step, to establish the relationship curve between the piezoelectric driver displacement u and the flap deflection angle : wherein k and b are both coefficients obtained by the least square method.

4. The method of claim 1, wherein, In the fourth step, the actual value of the force arm of the driving mechanism of each blade is calculated by using the following formula according to the coefficient k in the relationship curve between the piezoelectric driver displacement u of each blade obtained in the third step and the flap deflection angle r = 180 / π / k.

5. The method of claim 1, wherein, In the fifth step, the blade with the largest force arm in the driving mechanism is selected as the reference blade for the flap angle adjustment, and the blade is not adjusted. The number of compensating shims n required by other blades is calculated as follows: n = (r max -r) / d, where d is the thickness of a single layer of compensating shims; n is a positive integer, rounded to the nearest whole number.

6. The method of claim 1, wherein, In the sixth step, according to the calculation result of the fifth step, the corresponding number of shiftable shims is added to the driving force arm position of each blade, so that the adjustment of the flap deflection angle of each blade is completed.

7. The method of claim 3, wherein, The method further comprises: Seventh step: carrying out a rotating test of the trailing edge flap type active control rotor to obtain the output displacement Vi of the piezoelectric driver measured by the sensor in a certain flight state; Eighth step: substituting the output displacement Vi of the piezoelectric driver obtained in the seventh step into the relationship curve established in the third step to obtain the deflection angle θi=k*Vi of the flap.

8. An adjustment device for performing the adjustment method of the difference in the flap angle of a trailing edge flap type active control rotor flap according to any one of claims 1 to 7, characterized in that, The method comprises: A setting module for setting a sensor for measuring the output displacement of the piezoelectric driver in the driving mechanism of the rotor blade of the trailing edge flap type active control rotor; A measuring module for synchronously measuring the output displacement of the piezoelectric driver and the deflection angle of the flap under voltage excitation in a non-rotating state; An establishing module for establishing the corresponding relationship between the output displacement of the piezoelectric driver and the deflection angle of the flap; A calculating module for calculating the actual value of the driving force arm of each blade; A calculating module for calculating the number of shiftable shims required for compensation of each blade; The setting module is further used for adding the corresponding number of shiftable shims to the driving force arm position of each blade for adjustment.

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