Tailing edge flap type intelligent rotor wing and method for estimating flap hinge moment of trailing edge flap type intelligent rotor wing

Abstract

The invention provides a trailing edge flap type intelligent rotor wing and a flap hinge moment estimation method thereof, and the method comprises the steps: 1, obtaining a flap deflection angle phi flap in a driving mechanism and simulated aerodynamic force F of the flap in the driving mechanism through a bench test of the flap driving mechanism of the intelligent rotor wing; 2, according to the simulated aerodynamic force F of the flap and the force arm r from the spring load applying point to the flap rotating shaft, the hinge moment N of the flap in the bench test is calculated. 3, establishing a mapping relation between the flap hinge moment N and the flap deflection angle phi flap; 4, a rotation test of the intelligent rotor wing is carried out, and the flap deflection angle theta 0 in the flight state is obtained. And 5, substituting the flap deflection angle theta0 in the flight state into the mapping relation N = F (phi) to obtain the flap hinge moment load N = F (theta0) of the trailing edge flap type intelligent rotor in rotational motion.

Description

Technical Field

[0001] The invention belongs to the technical field of rotor design, and in particular relates to a trailing edge flap type intelligent rotor and a method for estimating a flap hinge torque thereof. Background Art

[0002] The trailing edge flap type smart rotor is a very promising new rotor system. It takes measures to reduce vibration and noise from the rotor, the source of helicopter vibration noise. It generates additional high-order harmonic aerodynamic forces on the blade lift surface by controlling the deflection of the blade trailing edge flap. By properly controlling the amplitude, frequency and phase of these high-order harmonic aerodynamic forces, it can effectively offset the corresponding high-order harmonic components in the blade distributed load to achieve the purpose of vibration reduction. Since the trailing edge flap is arranged at the outer end of the blade with higher dynamic pressure, a small angle deflection can cause a large change in aerodynamic load. However, for model rotors, especially model rotors with a diameter of less than 4m, it is difficult to measure the hinge moment load of the flap in a rotating state and in motion due to the space limitation of the blade.

[0003] At present, theoretical calculation methods are often used in research to estimate the flap hinge moment load of the trailing edge flap type smart rotor in rotational motion. However, the load estimation accuracy of this method is low and it cannot accurately reflect the flap load condition of the trailing edge flap type smart rotor in the actual rotation state. Summary of the invention

[0004] The present application provides a method for estimating a trailing edge flap type intelligent rotor and a flap hinge torque thereof, which can improve the estimation accuracy of the flap load.

[0005] In a first aspect, the present application provides a method for estimating 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 the bench test of the intelligent rotor flap drive mechanism 襟翼 and the simulated aerodynamic force F of the flap 气动力 ;

[0007] Step 2: Based on the simulated aerodynamic force F of the flap 气动力 and the moment arm r from the spring load application point to the flap rotation axis, calculate the hinge moment N of the flap in the bench test.

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

[0009] Step 4: Carry out a rotation test of the smart rotor to obtain the flap deflection angle θ0 in the flight state.

[0010] Step 5: Substitute the flap deflection angle θ0 in the flight state 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: The flap drive mechanism in the smart rotor is subjected to a separate bench test. The simulated centrifugal force of the flap is loaded through a tension spring or mass block connected to the side of the flap. The simulated centrifugal force F on the flap is determined based on the test speed of the rotor and the mass of the flap. L ;

[0013] Step 12: Apply the simulated aerodynamic force of the flap by connecting the springs on the upper and lower wing surfaces of the flap, and measure the spring force by the force sensor connected in series to the spring to obtain the simulated aerodynamic force F of the flap. 气动力 ;

[0014] Step 13: Apply 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 between the center of the flap and the center of rotation of the rotor, and Ω is the test rotation speed of the rotor.

[0017] Specifically, step 3 includes:

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

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

[0020] Specifically, N = F (Φ) is: flap hinge moment N and 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) is: flap hinge moment N and flap deflection angle φ 襟翼 The relationship is taken as a quadratic relationship, that is, N = c1*φ2 +c2*φ+c0, where c1, c2, c0 are the quadratic relationship fitting coefficients.

[0022] Specifically, step 2 includes:

[0023] Using the formula N = F 气动力 *r, calculate the hinge moment N of the flap in the bench test.

[0024] Specifically, step 4 includes:

[0025] According to the rotation test of the intelligent rotor, when a preset quasi-static voltage is applied to the piezoelectric driver in a flight state, the 1 / 2 peak-to-peak value of the angle of the flap in the rotation state is measured, and the flap deflection angle θ0 in the flight state is obtained.

[0026] In a second aspect, the present application provides a trailing edge flap type smart rotor, which is implemented by using the method for estimating the flap hinge torque of the trailing edge flap type smart rotor as described above.

[0027] In summary, the present application provides a method for estimating the hinge torque of a trailing edge flap type intelligent rotor flap, firstly, a bench test of the actual external load is simulated by a piezoelectric drive mechanism, and the relationship between the deflection angle of the flap drive mechanism and the hinge torque of the flap is established, and then the actual angle is obtained by a rotation test of the rotor, and the hinge torque of the flap is obtained by comparing with the bench test data. The hinge torque load of the flap obtained by this method is closer to the actual value. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 A flow chart of a method for estimating hinge torque of a trailing edge flap type intelligent rotor flap provided in this application. DETAILED DESCRIPTION

[0029] like Figure 1 As shown, the present application provides a method for estimating hinge torque of a trailing edge flap type intelligent rotor flap, comprising:

[0030] Step 1: Obtain the flap deflection angle φ in the drive mechanism through the bench test of the intelligent rotor flap drive mechanism 襟翼 and the simulated aerodynamic force F of the flap 气动力 ;

[0031] Specifically, step 1 includes:

[0032] Step 11: The flap drive mechanism in the smart rotor is subjected to a bench test separately. The simulated centrifugal force of the flap is loaded through a tension spring or a mass block connected to the side of the flap. The simulated centrifugal force on the flap is determined according to the test rotation 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 between the center of the flap and the center of rotation of the rotor, and Ω is the test rotation speed of the rotor.

[0034] Step 12: Apply the simulated aerodynamic force of the flap by connecting the springs on the upper and lower wing surfaces of the flap, and measure the spring force by the force sensor connected in series to the spring to obtain the simulated aerodynamic force F of the flap. 气动力 ;

[0035] Step 13: Apply 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 driver, and the angle of the flap in the drive mechanism and the force on the spring are measured. The 1 / 2 peak-to-peak value of the dynamic value is taken, which is φ 襟翼 、F 气动力 .

[0037] Step 2: Based on the simulated aerodynamic force F of the flap 气动力 and the moment arm r from the spring load application point to the flap rotation axis, calculate the hinge moment N of the flap in the bench test.

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

[0039] Step 3: Establish the flap hinge moment 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 different sizes of simulated aerodynamic forces F 气动力 Repeat steps 1 and 2 to obtain n groups of different simulated aerodynamic forces F 气动力 The hinge moment N and flap deflection angle φ under 襟翼 :(Nn,Φn).

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

[0043] Specifically, N = F (Φ) is: flap hinge moment N and 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) is: flap hinge moment N and flap deflection angle φ 襟翼 The relationship is taken as a quadratic relationship, that is, N = c1*φ 2 +c2*φ+c0, where c1, c2, c0 are the quadratic relationship fitting coefficients.

[0045] Step 4: Carry out a rotation test of the smart rotor to obtain the flap deflection angle θ0 in the flight state.

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

[0047] Step 5: Substitute the flap deflection angle θ0 in the flight state 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, the present application provides a trailing edge flap type smart rotor, which is implemented by using the above-mentioned method for estimating the flap hinge torque of the trailing edge flap type smart rotor.

[0049] The present invention provides a method for estimating the hinge torque of a trailing edge flap type intelligent rotor flap, which solves the problem that the hinge torque load of a moving flap cannot be measured in a rotating model rotor. The hinge torque load of the flap estimated by this method has higher accuracy and is closer to the actual value of the rotation test.

Claims

1. A method for estimating hinge torque of a trailing edge flap type intelligent rotor flap, characterized in that: The method comprises: Step 1: Obtain the flap deflection angle φ in the drive mechanism through the bench test of the intelligent rotor flap drive mechanism 襟翼 and the simulated aerodynamic force F of the flap 气动力 ; Step 2: Based on the simulated aerodynamic force F of the flap 气动力 and the moment arm r from the spring load application point to the flap rotation axis, calculate the hinge moment N of the flap in the bench test. Step 3: Establish the flap hinge moment N and flap deflection angle φ 襟翼 The mapping relationship; Step 4: Carry out a rotation test of the smart rotor to obtain the flap deflection angle θ0 in the flight state. Step 5: Substitute the flap deflection angle θ0 in the flight state 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 estimation method according to claim 1, characterized in that: Step 1 includes: Step 11: The flap drive mechanism in the smart rotor is subjected to a separate bench test. The simulated centrifugal force of the flap is loaded through a tension spring or mass block connected to the side of the flap. The simulated centrifugal force F on the flap is determined based on the test speed of the rotor and the mass of the flap. L ; Step 12: Apply the simulated aerodynamic force of the flap by connecting the springs on the upper and lower wing surfaces of the flap, and measure the spring force by the force sensor connected in series to the spring to obtain the simulated aerodynamic force F of the flap. 气动力 ; Step 13: Apply quasi-static voltage excitation to the driver and measure the flap deflection angle φ in the drive mechanism 襟翼 .

3. The estimation 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 between the center of the flap and the center of rotation of the rotor, and Ω is the test rotation speed of the rotor.

4. The estimation method according to claim 1, characterized in that: Step 3 includes: Step 31: Use springs of different stiffness to simulate different sizes of simulated aerodynamic forces F 气动力 Repeat steps 1 and 2 to obtain n groups of different simulated aerodynamic forces F 气动力 The hinge moment N and flap deflection angle φ under 襟翼 :(Nn,Φn); Step 32: Obtain the flap hinge moment N and flap deflection angle φ by least squares fitting. 襟翼 The mapping relationship N=F(Φ).

5. The estimation method according to claim 4, characterized in that: Flap hinge moment N and flap deflection angle φ 襟翼 The relationship is a linear relationship, that is, N=a0*φ+b0, where a0 and b0 are both linear fitting coefficients.

6. The estimation method according to claim 4, characterized in that: Flap hinge moment N and flap deflection angle φ 襟翼 The relationship is a quadratic relationship, that is, N = c1*φ 2 +c2*φ+c0, where c1, c2, c 0均 is the quadratic relationship fitting coefficient.

7. The estimation method according to claim 1, characterized in that: Step 2 includes: Using the formula N = F 气动力 *r, calculate the hinge moment N of the flap in the bench test.

8. The estimation method according to claim 1, characterized in that: Step 4 includes: According to the rotation test of the intelligent rotor, when a preset quasi-static voltage is applied to the piezoelectric driver in a flight state, the 1 / 2 peak-to-peak value of the angle of the flap in the rotation state is measured, and the flap deflection angle θ0 in the flight state is obtained.

9. A trailing edge flap type intelligent rotor, characterized in that: The trailing edge flap type smart rotor is implemented by using the method for estimating the flap hinge torque of the trailing edge flap type smart rotor as described in any one of claims 1 to 8.

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