CN112182932A - Method for predicting deflection angle of trailing edge flap of rotor wing in rotation state model - Google Patents

Method for predicting deflection angle of trailing edge flap of rotor wing in rotation state model Download PDF

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CN112182932A
CN112182932A CN202011022137.9A CN202011022137A CN112182932A CN 112182932 A CN112182932 A CN 112182932A CN 202011022137 A CN202011022137 A CN 202011022137A CN 112182932 A CN112182932 A CN 112182932A
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flap
trailing edge
deflection angle
piezoelectric
excitation voltage
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高乐
魏武雷
胡和平
张仕明
邓旭东
周云
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China Helicopter Research and Development Institute
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Abstract

The invention belongs to the technical field of rotor wing design, and discloses a method for predicting the deflection angle of a rotor wing trailing edge flap of a rotation state model. The parameters of the piezoelectric material in the simulation model are corrected through displacement performance data of the intelligent rotor piezoelectric driver, and the input voltage amplitude in the simulation model is corrected through a hysteresis performance test of the piezoelectric driver with spring load, so that the established finite element simulation model of the flap driving mechanism is closer to a test model, and the estimated flap deflection angle is higher in precision.

Description

Method for predicting deflection angle of trailing edge flap of rotor wing in rotation state model
Technical Field
The invention belongs to the technical field of rotor wing design, and relates to a method for predicting the deflection angle of a rotor wing trailing edge flap of a rotation state model.
Background
The trailing edge flap type intelligent rotor wing is a novel potential rotor wing system, and measures are taken from a helicopter vibration noise source rotor wing to realize vibration reduction and noise reduction. The method can generate additional high-order harmonic aerodynamic force on the lifting surface of the blade by controlling the deflection of the trailing edge flap of the blade, and can effectively counteract corresponding high-order harmonic components in the distributed load of the blade by properly controlling the amplitude, the frequency and the phase of the high-order harmonic aerodynamic force so as to achieve the aim of vibration reduction. Since the trailing edge flaps are arranged at the outer ends of the blades where the dynamic pressure is high, a smaller angular deflection can cause a larger aerodynamic load variation. However, the model rotor, especially the model rotor below 4m in diameter, is limited by the space limitation of the blades, and it is difficult to install a sensor for measuring the deflection angle of the trailing edge flap, so that the vibration and noise reduction control of the trailing edge flap type intelligent rotor becomes a "black box", and the flap deflection angle, which is a key parameter in the control process, cannot be obtained.
In the prior art, two methods are used for predicting the deflection angle of the flap in a rotating state, one is a method for indirectly measuring variables in the force transmission process of a flap driving mechanism and converting the variables into the flap angle, and the other is a method for directly adopting a linear elastic piezoelectric constitutive equation to carry out trailing edge flap driving modeling analysis and simulating to obtain the flap deflection angle without adopting any correction mode. The indirect measurement method has two disadvantages, namely, when the intermediate variable measurement in the force transmission process of the flap drive mechanism is carried out in a rotating state, the risk of interference between test equipment such as a lead and the like and the flap drive mechanism of a movable part exists; secondly, when the measured indirect quantity is converted into the angle of the flap, the measured indirect quantity can be amplified or reduced due to the force transmission rod system, and the precision is not high. And the precision of the deviation angle of the flap estimated by adopting a simulation model without any correction is poor.
Disclosure of Invention
The invention aims to provide a rotary state trailing edge flap deflection angle estimation simulation method with correction, which can improve estimation precision of flap deflection angle.
The technical scheme of the invention is as follows:
a method for predicting the deflection angle of a trailing edge flap of a rotor of a rotating state model comprises the following steps:
the first step is as follows: testing the driving performance of the piezoelectric driver;
the second step is that: establishing a finite element simulation model of the piezoelectric actuator, and correcting parameters of the piezoelectric material by adopting the displacement performance of the piezoelectric actuator;
the third step: calculating the moment load of the flap;
the fourth step: testing the hysteresis performance of the piezoelectric driver with spring load;
the fifth step: establishing a finite element simulation model of the flap driving mechanism, and estimating the deflection angle of the flap at the trailing edge in a rotating state by taking the corrected piezoelectric material parameters and the excitation voltage signal corrected by the hysteresis characteristic as correction input.
Further, the testing the driving performance of the piezoelectric driver in the first step includes: applying 1Hz excitation voltage U ═ A to the piezoelectric actuator in the clamped-free state0+ Asin (t) to obtain the output displacement u of the piezoelectric driver0Maximum value u of0maxAnd the minimum value u0min。
Further, in the second step, a finite element simulation model of the piezoelectric actuator under the condition of a fixed support-free boundary is established, and the applied 1Hz excitation voltage U is obtained through simulation0Output displacement u 'of piezoelectric actuator at + Asin (t)'0U's maximum value'0maxAnd minimum value u'0minBy correcting the piezoelectric material parameter S in the simulation model11、S12、S13、S33、S44、d15、d31、d33And are such that u'0max＝u0max、u'0min＝u0min。
Further, in the third step, the formula for calculating the flap moment is as follows:
Figure BDA0002700974400000031
where ρ is the air density, Ω is the rotor speed, cfIs the chord length of the flap, ChIs the moment coefficient of the flap hinge, R2、R1With flaps at the outer and inner ends of the blade, respectivelyThe station of the end.
Further, in the fourth step, testing the hysteresis performance of the piezoelectric driver with the spring load comprises:
one end of the driver is fixed, and the other end is connected with a spring load with the rigidity of
Figure BDA0002700974400000032
In the formula, H is the moment of the flap hinge in the third step, e is the moment arm of the flap and is the deflection angle of the flap;
applying a 1Hz excitation voltage U-A0+ Asin (t) to obtain the static value u of the driver's output displacementstAnd the dynamic amplitude u of the displacementdy(ii) a Applying the excitation voltage U-A of omega Hz0+ Asin (ω t), obtaining the static value u 'of the output displacement of the driver'stAnd displacement dynamic amplitude u'dy。
Further, the hysteresis characteristics of the piezoelectric driver with spring load during ω Hz excitation include: the static amplitude scaling system and the dynamic amplitude scaling coefficient of the excitation voltage have the following calculation formula:
static amplitude scaling coefficient of excitation voltage:
Figure BDA0002700974400000033
dynamic amplitude scaling coefficient of excitation voltage
Figure BDA0002700974400000034
Further, in the fifth step, the calculation process of the deflection angle of the trailing edge flap comprises the following steps:
using the corrected parameters S of the piezoelectric material11、S12、S13、S33、S44、d15、d31、d33Establishing a finite element simulation model of the intelligent rotor blade flap driving mechanism in a rotating state, wherein the load of the flap is the flap moment load obtained by the third step of calculation;
the exciting voltage signal input in the simulation model is corrected by using the hysteresis characteristic test result
Thereby obtaining the exciting voltage U-A applied to the omega Hz in the rotating state0+ Asin (ω t) is the angle of deflection of the trailing edge flap.
Further, the excitation voltage signal input in the simulation model is corrected by using the following formula:
Umodel＝A0*kst+A*kdy sin(ωt)。
the key points of the invention are as follows:
1) correcting parameters of the piezoelectric material in the simulation model through displacement performance data of the piezoelectric actuator;
2) and correcting the input voltage amplitude in the simulation model through a hysteresis performance test of the piezoelectric driver with spring load.
The invention has the beneficial effects that: according to the method for estimating the deflection angle of the wing flap at the trailing edge of the rotor wing of the rotating state model, the parameters of a piezoelectric material in the simulation model are corrected through the displacement performance data of a piezoelectric driver, and the input voltage amplitude in the simulation model is corrected through the hysteresis performance test of the piezoelectric driver with spring load, so that the established finite element simulation model of the wing flap driving mechanism is closer to a test model, and the estimated deflection angle of the wing flap is higher in precision.
Drawings
FIG. 1 is a flow chart of a method for predicting a flap deflection angle of a rotor trailing edge of a model rotor in a rotating state.
Detailed Description
The method for estimating the flap deflection angle of the rotor trailing edge of the model in a rotating state according to the present invention is further described in detail with reference to the accompanying drawings.
A method for estimating the deflection angle of a trailing edge flap of a rotor of a rotating state model, as shown in FIG. 1, comprises the following steps:
the first step is as follows: and testing the driving performance of the piezoelectric actuator. The piezoelectric driver is used for driving a rotor wing trailing edge flap.
Applying 1Hz excitation voltage U to the piezoelectric driver in the clamped-free stateA0+ Asin (t), the output displacement u of the piezoelectric actuator is obtained0Maximum value u of0maxAnd the minimum value u0min. The clamped-free state is that one end of the piezoelectric driver is fixedly constrained, and the other end of the piezoelectric driver is used as an output end and is not constrained.
The second step is that: and establishing a finite element simulation model of the piezoelectric actuator, and correcting parameters of the piezoelectric material by adopting the displacement performance of the piezoelectric actuator. The piezoelectric actuator consists of a piezoelectric stack and an amplifying frame which are made of piezoelectric materials, and the parameters of the piezoelectric materials comprise: sijAnd dkl(ii) a Wherein SijThe index i represents the generation direction of the strain of the piezoelectric material, and the index j represents the direction of the stress applied to the piezoelectric material; dklThe piezoelectric material is a piezoelectric material strain constant, a subscript k represents an external field voltage direction, a subscript l represents a direction of generating strain under the action of an electric field, k takes values of 1,2 and 3 and respectively corresponds to an X \ Y \ Z direction under a coordinate system, and i, j and l take values of 1,2, … … and 6; wherein 1,2 and 3 respectively correspond to X \ Y \ Z direction under a coordinate system, and 4,5 and 6 respectively correspond to shear strain yz, zx and xy.
Establishing a finite element simulation model of the piezoelectric actuator under the condition of a fixed support-free boundary, and simulating to obtain an excitation voltage U (equal to A) applied with 1Hz0Output displacement u 'of piezoelectric actuator at + Asin (t)'0U's maximum value'0maxAnd minimum value u'0minBy correcting the parameters S of the piezoelectric material in the simulation model11、S12、S13、S33、S44、d15、d31、d33So that u'0max＝u0max、u'0min＝u0min。
The third step: and calculating the moment load of the flap.
Calculating flap hinge moment using the formula
Figure BDA0002700974400000061
Where ρ is the air density, Ω is the rotor speed, cfIs the chord length of the flap, ChBeing flapsCoefficient of moment of hinge, R2、R1The positions of the flaps at the outer end and the inner end of the blade are respectively.
The fourth step: hysteresis performance test of piezoelectric driver with spring load
One end of the driver is fixedly supported, and the other end of the driver is connected with a spring load with the rigidity of
Figure BDA0002700974400000062
In the formula, H is the flap hinge moment in the third step, e is the moment arm of the flap and is the flap deflection angle.
Applying a 1Hz excitation voltage U-A0When + Asin (t), obtaining the output displacement static value u of the driverstAnd the dynamic amplitude u of the displacementdy(ii) a Applying the excitation voltage U-A of omega Hz0At + Ash (ω t), the static value u 'of the output displacement of the actuator is obtained'stAnd displacement dynamic amplitude u'dyThus, the hysteresis characteristic of the excitation of the omega Hz is obtained: static amplitude scaling coefficient of excitation voltage
Figure BDA0002700974400000063
And dynamic amplitude scaling factor
Figure BDA0002700974400000064
The fifth step: establishing a finite element simulation model of the flap driving mechanism, and estimating the deflection angle of the flap at the trailing edge in a rotating state by taking the corrected piezoelectric material parameters and the excitation voltage signal corrected by the hysteresis characteristic as correction input.
Using the corrected parameters S of the piezoelectric material in the second step11、S12、S13、S33、S44、d15、d31、d33And establishing a finite element simulation model of the intelligent rotor blade flap driving mechanism in a rotating state, wherein the load of the flap adopts the flap moment load obtained by the third step of calculation. Exciting electricity input in simulation modelThe voltage signal is corrected U by adopting the hysteresis characteristic test result of the fourth stepmodel＝A0*kst+A*kdy sin(ωt)，
Thereby obtaining the exciting voltage U-A applied to the omega Hz in the rotating state0+ Asin (ω t) is the angle of deflection of the trailing edge flap.
The invention provides a method for estimating the deflection angle of a wing flap at the trailing edge of a model rotor in a rotating state, which solves the problem that a wing flap angle sensor cannot be installed on a model-level trailing edge wing flap type intelligent rotor to measure the deflection angle of the wing flap. The flap deflection angle estimated by the method is higher in precision and closer to the true angle of the rotation test.

Claims (8)

1. The utility model provides a method for predicting the deflection angle of a rotor trailing edge flap of a rotating state model, which is characterized in that: the method comprises the following steps:
the first step is as follows: testing the driving performance of the piezoelectric driver; the piezoelectric driver is used for driving a rotor wing trailing edge flap;
the second step is that: establishing a finite element simulation model of the piezoelectric actuator, and correcting parameters of the piezoelectric material by adopting the displacement performance of the piezoelectric actuator;
the third step: calculating the moment load of the flap;
the fourth step: testing the hysteresis characteristic of the piezoelectric driver with spring load according to the flap moment load;
the fifth step: establishing a finite element simulation model of the flap driving mechanism, and estimating the deflection angle of the flap at the trailing edge in a rotating state by taking the corrected piezoelectric material parameters and the excitation voltage signal corrected by the hysteresis characteristic as correction input.
2. The method for estimating the deflection angle of the trailing edge flap of the rotor based on the rotating state model according to claim 1, wherein the method comprises the following steps:
the testing the driving performance of the piezoelectric driver in the first step comprises the following steps: applying 1Hz excitation voltage U ═ A to the piezoelectric actuator in the clamped-free state0+ A sin (t) to obtain the output displacement u of the piezoelectric actuator0Maximum value u of0maxAnd the minimum value u0min。
3. The method for estimating the deflection angle of the trailing edge flap of the rotor based on the rotating state model according to claim 2, wherein the method comprises the following steps: in the second step, a piezoelectric driver finite element simulation model of the fixed support-free boundary condition is established, and the applied 1Hz excitation voltage U is obtained through simulation0Output displacement u 'of piezoelectric actuator at + A sin (t)'0U's maximum value'0maxAnd minimum value u'0minBy correcting the piezoelectric material parameter S in the simulation model11、S12、S13、S33、S44、d15、d31、d33And make it possible to
u’0max＝u0max、u’0min＝u0min。
4. The method for estimating the deflection angle of the trailing edge flap of the rotor based on the rotating state model according to claim 3, wherein the method comprises the following steps: in the third step, the formula for calculating the flap moment is as follows:
Figure FDA0002700974390000021
where ρ is the air density, Ω is the rotor speed, cfIs the chord length of the flap, ChIs the moment coefficient of the flap hinge, R2、R1The positions of the flaps at the outer end and the inner end of the blade are respectively.
5. The method for estimating the deflection angle of the trailing edge flap of the rotor based on the rotating state model according to claim 4, wherein the method comprises the following steps: in the fourth step, testing the hysteresis performance of the piezoelectric driver with the spring load comprises:
one end of the piezoelectric driver is fixed, and the other end of the piezoelectric driver is connected with a spring load with the rigidity of
Figure FDA0002700974390000022
In the formula, H is the moment of the flap in the third step, e is the moment arm of the flap and is the deflection angle of the flap;
applying a 1Hz excitation voltage U-A0+ A sin (t) to obtain the static value u of the output displacement of the piezoelectric actuatorstAnd the dynamic amplitude u of the displacementdy(ii) a Applying the excitation voltage U-A of omega Hz0+ A sin (ω t) to obtain static value u 'of output displacement of the piezoelectric actuator'stAnd displacement dynamic amplitude u'dy。
6. The method for estimating the deflection angle of the trailing edge flap of the rotor based on the rotating state model according to claim 5, wherein the method comprises the following steps: the hysteresis characteristics of the piezoelectric driver with the spring load in the excitation of the omega Hz comprise: the static amplitude scaling coefficient and the dynamic amplitude scaling coefficient of the excitation voltage are calculated according to the following formulas:
static amplitude scaling coefficient of excitation voltage:
Figure FDA0002700974390000031
dynamic amplitude scaling coefficient of excitation voltage
Figure FDA0002700974390000032
7. The method for estimating the deflection angle of the trailing edge flap of the rotor based on the rotating state model according to claim 6, wherein the method comprises the following steps: in the fifth step, the calculation process of the deflection angle of the trailing edge flap comprises the following steps:
using the corrected parameters S of the piezoelectric material11、S12、S13、S33、S44、d15、d31、d33Establishing a finite element simulation model of the rotor blade flap driving mechanism in a rotating state, wherein the load of the flap is the flap moment load obtained by the third step of calculation;
excitation voltage signal input in simulation model is adopted lateCorrecting the hysteresis characteristic test result to obtain the excitation voltage U (A) applied to the omega Hz in the rotating state0+ A sin (ω t) is the angle of deflection of the trailing edge flap.
8. The method for estimating the deflection angle of the trailing edge flap of the rotor based on the rotating state model according to claim 7, wherein the method comprises the following steps: correcting an excitation voltage signal input in a finite element simulation model of a rotor blade flap driving mechanism by using the following formula:
Umodel＝A0*kst+A*kdy sin(ωt)。
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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020141867A1 (en) * 2001-04-03 2002-10-03 Eurocopter Deutschland Gmbh Method and control arrangement for adjusting a flap that is pivotally supported in a rotor blade of a helicopter
CN107600389A (en) * 2017-09-04 2018-01-19 江西洪都航空工业集团有限责任公司 A kind of slide guide posture trailing edge flap movement technique
CN110162933A (en) * 2019-06-26 2019-08-23 上海交通大学 The coaxial more rotor emulation modes of one kind and system

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020141867A1 (en) * 2001-04-03 2002-10-03 Eurocopter Deutschland Gmbh Method and control arrangement for adjusting a flap that is pivotally supported in a rotor blade of a helicopter
CN107600389A (en) * 2017-09-04 2018-01-19 江西洪都航空工业集团有限责任公司 A kind of slide guide posture trailing edge flap movement technique
CN110162933A (en) * 2019-06-26 2019-08-23 上海交通大学 The coaxial more rotor emulation modes of one kind and system

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
张仕明等: "基于集中参数模型的后缘小翼驱动机构分析", 《压电与声光》, no. 03, 15 June 2018 (2018-06-15), pages 110 - 115 *
高乐等: "后缘襟翼型智能旋翼驱动力臂的设计方法", 《航空科学技术》, no. 05, 15 May 2018 (2018-05-15), pages 47 - 53 *

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