A trailing edge flap type intelligent rotor and a flap hinge torque estimation method thereof

Abstract

The application provides a trailing edge flap type intelligent rotor and a flap hinge torque estimation method thereof, and the method comprises the following steps: step 1: obtaining the flap deflection angle φ 襟翼 and the simulated aerodynamic force F 气动力 of the flap through intelligent rotor flap driving mechanism bench test 气动力 ; step 2: calculating the hinge torque N of the flap in the bench test according to the simulated aerodynamic force F 气动力 of the flap and the force arm r of the spring load application point to the flap rotation shaft 襟翼 ; step 3: establishing the mapping relationship between the hinge torque N and the flap deflection angle φ 襟翼 ; step 4: carrying out the rotation test of the intelligent rotor to obtain the flap deflection angle θ0 in the flight state; and step 5: substituting the flap deflection angle θ0 in the flight state into the mapping relationship N=F(Φ) to obtain the flap hinge torque load N=F(θ0) of the trailing edge flap type intelligent rotor in the rotation motion.

Description

Technical Field

[0001] This invention belongs to the field of rotor design technology, and in particular relates to a trailing edge flap type intelligent rotor and a method for predicting the flap hinge torque. Background Technology

[0002] Trailing-edge flap-type intelligent rotors are a promising new rotor system that addresses vibration and noise at the rotor itself, the source of helicopter vibration and noise. By controlling the deflection of the trailing-edge flaps, additional high-order harmonic aerodynamic forces are generated on the blade's lifting surface. By appropriately controlling the amplitude, frequency, and phase of these high-order harmonic aerodynamic forces, the corresponding high-order harmonic components in the blade's distributed load can be effectively counteracted, thus achieving vibration reduction. Because the trailing-edge flaps are located at the outer end of the blades with high dynamic pressure, a small deflection angle can cause a significant change in aerodynamic load. However, for model rotors, especially those with a diameter of less than 4 meters, the space constraints of the blades make it difficult to measure the hinge moment load of the flaps during rotation and motion.

[0003] Current research often uses theoretical calculations to predict the flap hinge moment load of trailing edge flap-type smart rotors during rotation. However, this method has low load prediction accuracy and cannot accurately reflect the flap load of the trailing edge flap-type smart rotor under actual rotation. Summary of the Invention

[0004] This application provides a trailing edge flap type smart rotor and a method for predicting the flap hinge torque, which can improve the prediction accuracy of flap load.

[0005] In a first aspect, this application provides a method for predicting the hinge torque of a trailing-edge flap-type smart rotor flap, the method comprising:

[0006] Step 1: Obtain the flap deflection angle φ in the drive mechanism through bench testing of the intelligent rotor flap drive mechanism. 襟翼 Simulated aerodynamic force F of the flaps 气动力 ;

[0007] Step 2: Based on the simulated aerodynamic force F of the flap 气动力 Calculate the hinge torque N of the flap during the bench test, taking the lever arm r from the point of application of the spring load to the flap rotation axis.

[0008] Step 3: Establish the flap hinge torque N and flap deflection angle φ 襟翼 The mapping relationship;

[0009] Step 4: Conduct rotational tests on the intelligent rotor to obtain the flap deflection angle θ0 during flight.

[0010] Step 5: Substitute the flap deflection angle θ0 in flight into the mapping relationship N=F(Φ) to obtain the flap hinge moment load N=F(θ0) of the trailing edge flap type smart rotor in rotational motion.

[0011] Specifically, step 1 includes:

[0012] Step 11: Conduct a bench test on the flap drive mechanism of the intelligent rotor separately. The simulated centrifugal force of the flap is applied by a tension spring or mass block connected to the side of the flap. Determine the simulated centrifugal force F on the flap based on the test rotational speed of the rotor and the mass of the flap. L ;

[0013] Step 12: Apply simulated aerodynamic force to the flaps using springs connected to the upper and lower surfaces of the flaps, and measure the spring force using a force sensor connected in series with the springs to obtain the simulated aerodynamic force F of the flaps. 气动力 ;

[0014] Step 13: Apply a quasi-static voltage excitation to the driver and measure the flap deflection angle φ in the drive mechanism. 襟翼 .

[0015] Specifically, step 11 includes:

[0016] Using formula F L =mR0Ω 2 Calculate the simulated centrifugal force on the flap, where m is the mass of the flap, R0 is the distance from the center of the flap to the center of the rotor rotation, and Ω is the test rotational speed of the rotor.

[0017] Specifically, step 3 includes:

[0018] Step 31: Use springs of different stiffness to simulate aerodynamic forces F of different magnitudes. 气动力 Repeat steps 1 and 2 to obtain n sets of different simulated aerodynamic forces F. 气动力 The hinge torque N and flap deflection angle φ 襟翼 :(Nn,Φn);

[0019] Step 32: Obtain the flap hinge torque N and flap deflection angle φ by fitting using the least squares method. 襟翼 The mapping relationship is N = F(Φ).

[0020] Specifically, N = F(Φ) represents the flap hinge torque N and the flap deflection angle φ. 襟翼 The relationship is taken as a linear relationship, that is, N=a0*φ+b0, where a0 and b0 are linear fitting coefficients.

[0021] Specifically, N = F(Φ) represents the flap hinge torque N and the flap deflection angle φ. 襟翼 The relation is taken as a quadratic relation, i.e., N = c1 * φ2 +c2*φ+c0, where c1, c2, and c0 are the quadratic relationship fitting coefficients.

[0022] Specifically, step 2 includes:

[0023] Using the formula N = F 气动力 *r, calculates the hinge torque N of the flap during the bench test.

[0024] Specifically, step 4 includes:

[0025] Based on the rotation test of the smart rotor, the flap deflection angle θ0 in the flight state is obtained by measuring the peak-to-peak value of the flap angle 1 / 2 in the rotation state when a preset quasi-static voltage is applied to the piezoelectric actuator under a certain flight state.

[0026] Secondly, this application provides a trailing edge flap type smart rotor, which is implemented using the aforementioned method for estimating the flap hinge torque of a trailing edge flap type smart rotor.

[0027] In summary, this application provides a method for predicting the flap hinge torque of a trailing-edge flap-type smart rotor. First, a bench test simulating an actual external load is conducted using a piezoelectric drive mechanism to establish the relationship between the deflection angle of the flap drive mechanism and the flap hinge torque. Then, the actual angle is obtained through rotor rotation tests, and the flap hinge torque is obtained by comparing the results with the bench test data. The flap hinge torque load obtained using this method is closer to the actual value. Attached Figure Description

[0028] Figure 1 A flowchart illustrating a method for predicting the hinge torque of a trailing edge flap-type smart rotor, as provided in this application. Detailed Implementation

[0029] like Figure 1 As shown, this application provides a method for predicting the hinge torque of the trailing edge flap type smart rotor flap, including:

[0030] Step 1: Obtain the flap deflection angle φ in the drive mechanism through bench testing of the intelligent rotor flap drive mechanism. 襟翼 Simulated aerodynamic force F of the flaps 气动力 ;

[0031] Specifically, step 1 includes:

[0032] Step 11: Conduct a bench test on the flap drive mechanism in the smart rotor. The simulated centrifugal force of the flap is applied by a tension spring or mass block connected to the side of the flap. The simulated centrifugal force on the flap is determined according to the test speed of the rotor and the mass of the flap.

[0033] Specifically, step 11 includes: using formula F L =mR0Ω 2 Calculate the simulated centrifugal force on the flap, where m is the mass of the flap, R0 is the distance from the center of the flap to the center of the rotor rotation, and Ω is the test rotational speed of the rotor.

[0034] Step 12: Apply simulated aerodynamic force to the flaps using springs connected to the upper and lower surfaces of the flaps, and measure the spring force using a force sensor connected in series with the springs to obtain the simulated aerodynamic force F of the flaps. 气动力 ;

[0035] Step 13: Apply a quasi-static voltage excitation to the driver and measure the flap deflection angle φ in the drive mechanism. 襟翼 .

[0036] In practical applications, a quasi-static voltage excitation U = 75 + 75s in(2π*1*t)V is applied to the actuator. The angle of the flaps and the force on the spring in the drive mechanism are measured, and half of their dynamic peak-to-peak values ​​are taken, which are φ respectively. 襟翼 F 气动力 .

[0037] Step 2: Based on the simulated aerodynamic force F of the flap 气动力 Calculate the hinge torque N of the flap during the bench test, taking the lever arm r from the point of application of the spring load to the flap rotation axis.

[0038] Specifically, step 2 includes: using the formula N = F 气动力 *r, calculates the hinge torque N of the flap during the bench test.

[0039] Step 3: Establish the flap hinge torque N and flap deflection angle φ 襟翼 The mapping relationship;

[0040] Specifically, step 3 includes:

[0041] Step 31: Use springs of different stiffness to simulate aerodynamic forces F of different magnitudes. 气动力 Repeat steps 1 and 2 to obtain n sets of different simulated aerodynamic forces F. 气动力 The hinge torque N and flap deflection angle φ 襟翼 :(Nn,Φn).

[0042] Step 32: Obtain the flap hinge torque N and flap deflection angle φ by fitting using the least squares method. 襟翼 The mapping relationship is N = F(Φ).

[0043] Specifically, N = F(Φ) represents the flap hinge torque N and the flap deflection angle φ. 襟翼The relationship is taken as a linear relationship, that is, N=a0*φ+b0, where a0 and b0 are linear fitting coefficients.

[0044] Specifically, N = F(Φ) represents the flap hinge torque N and the flap deflection angle φ. 襟翼 The relation is taken as a quadratic relation, i.e., N = c1 * φ 2 +c2*φ+c0, where c1, c2, and c0 are the quadratic relationship fitting coefficients.

[0045] Step 4: Conduct rotational tests on the intelligent rotor to obtain the flap deflection angle θ0 during flight.

[0046] Specifically, step 4 includes: conducting a rotation test of the smart rotor to obtain the peak-to-peak value θ0 of the flap angle 1 / 2 under a certain flight state when a preset quasi-static voltage is applied to the piezoelectric actuator.

[0047] Step 5: Substitute the flap deflection angle θ0 in flight into the mapping relationship N=F(Φ) to obtain the flap hinge moment load N=F(θ0) of the trailing edge flap type smart rotor in rotational motion.

[0048] In addition, this application provides a trailing edge flap type smart rotor, which is implemented using the aforementioned method for estimating the flap hinge torque of the trailing edge flap type smart rotor.

[0049] This invention provides a method for predicting the hinge torque of a trailing-edge flap-type intelligent rotor, solving the problem of the inability to measure the hinge torque load on the flap during rotation in a rotating rotor model. The flap hinge torque load predicted by this method has higher accuracy and is closer to the actual value in the rotation test.

Claims

1. A method for predicting the hinge torque of a trailing-edge flap-type intelligent rotor flap, characterized in that, The method includes: Step 1: Obtain the flap deflection angle φ in the drive mechanism through bench testing of the intelligent rotor flap drive mechanism. 襟翼 Simulated aerodynamic force F of the flaps 气动力 ; Step 2: Based on the simulated aerodynamic force F of the flap 气动力 Calculate the hinge torque N of the flap during the bench test, taking the lever arm r from the point of application of the spring load to the flap rotation axis. Step 3: Establish the flap hinge torque N and flap deflection angle φ 襟翼 The mapping relationship; Step 3 includes: Step 31: Using springs of different stiffness to simulate aerodynamic forces F of different magnitudes. 气动力 Repeat steps 1 and 2 to obtain n sets of different simulated aerodynamic forces F. 气动力 The hinge torque N, i.e., Nn, and the flap deflection angle φ 襟翼 That is, Φn; Step 32: Obtain the flap hinge torque N and flap deflection angle φ by least squares fitting. 襟翼 The mapping relationship N=F(Φ); Step 4: Conduct rotation tests on the intelligent rotor to obtain the flap deflection angle θ0 during flight; Step 5: Substitute the flap deflection angle θ0 in flight into the mapping relationship N=F(Φ) to obtain the flap hinge moment load N'=F(θ0) of the trailing edge flap type smart rotor in rotational motion.

2. The prediction method according to claim 1, characterized in that, Step 1 includes: Step 11: Conduct a bench test on the flap drive mechanism of the intelligent rotor separately. The simulated centrifugal force of the flap is applied by a tension spring or mass block connected to the side of the flap. Determine the simulated centrifugal force F on the flap based on the test rotational speed of the rotor and the mass of the flap. L ; Step 12: Apply simulated aerodynamic force to the flaps using springs connected to the upper and lower surfaces of the flaps, and measure the spring force using a force sensor connected in series with the springs to obtain the simulated aerodynamic force F of the flaps. 气动力 ; Step 13: Apply a quasi-static voltage excitation to the driver and measure the flap deflection angle φ in the drive mechanism. 襟翼 .

3. The prediction method according to claim 2, characterized in that, Step 11 includes: Using formula F L =mR0Ω 2 Calculate the simulated centrifugal force on the flap, where m is the mass of the flap, R0 is the distance from the center of the flap to the center of the rotor rotation, and Ω is the test rotational speed of the rotor.

4. The prediction method according to claim 1, characterized in that, flap hinge torque N and flap deflection angle φ 襟翼 The relationship is linear, i.e., N = a0 * φ 襟翼 +b0, where a0 and b0 are linear fitting coefficients.

5. The prediction method according to claim 1, characterized in that, flap hinge torque N and flap deflection angle φ 襟翼 The relationship is a quadratic relationship, i.e., N = c1 * φ 襟翼 2 +c2*φ 襟翼 +c0, where c1, c2, and c0 are all quadratic relationship fitting coefficients.

6. The prediction method according to claim 1, characterized in that, Step 2 includes: Using the formula N = F 气动力 *r, calculates the hinge torque N of the flap during the bench test.

7. The prediction method according to claim 1, characterized in that, Step 4 includes: Based on the rotation test of the smart rotor, the flap deflection angle θ0 in the flight state is obtained by measuring the peak-to-peak value of the flap angle 1 / 2 in a certain flight state when a preset quasi-static voltage is applied to the piezoelectric actuator.

8. A trailing-edge flap type intelligent rotor, characterized in that, The trailing edge flap type intelligent rotor is implemented using the method for predicting the flap hinge torque of the trailing edge flap type intelligent rotor as described in any one of claims 1 to 7.

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