WO2023216353A1 - 一种基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法 - Google Patents

一种基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法 Download PDF

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WO2023216353A1
WO2023216353A1 PCT/CN2022/097849 CN2022097849W WO2023216353A1 WO 2023216353 A1 WO2023216353 A1 WO 2023216353A1 CN 2022097849 W CN2022097849 W CN 2022097849W WO 2023216353 A1 WO2023216353 A1 WO 2023216353A1
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array
ultrasonic
bolt
measure
film sensor
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PCT/CN2022/097849
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English (en)
French (fr)
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王川
焦光明
李文生
程全士
夏斌宏
郑鹏飞
杨保建
李崇源
杨兵
张俊
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航天精工股份有限公司
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Publication of WO2023216353A1 publication Critical patent/WO2023216353A1/zh

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
    • G01L5/24—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for determining value of torque or twisting moment for tightening a nut or other member which is similarly stressed
    • G01L5/246—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for determining value of torque or twisting moment for tightening a nut or other member which is similarly stressed using acoustic waves
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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  • the invention belongs to the technical field of bolt stress ultrasonic measurement, and in particular relates to a bolt shear force circumferential distribution measurement method based on array film rotation calibration.
  • Bolt connection is an important connection technology for large-scale key equipment in the aerospace field.
  • the external vibration load on the bolted connection structure can generally be divided into four situations: axial tension, radial shear force, axial torque parallel to the bolt axis and radial bending moment perpendicular to the bolt axis. Compared with the other three loads, lateral dynamic loads are more capable of loosening bolted connections.
  • the propagation speed of ultrasonic waves in bolts is related to the stress of the bolts.
  • Observing the propagation time of ultrasonic waves in bolts can know the propagation speed of ultrasonic waves, the functional relationship between the propagation time of shear ultrasonic waves and the axial stress of the bolts, and through calibration tests. Once the correlation coefficient in the functional relationship is obtained, the bolt stress value can be quantitatively measured by measuring the propagation time of ultrasonic waves in the bolt, thereby judging the health of the bolt connection.
  • the patch-type ultrasonic stress detection method has been used for many years, but because the piezoelectric chip is generally bonded to the bolt with epoxy resin or adhesive, it is easy to fall off. Moreover, since the thickness of the adhesive layer cannot be measured, it has a great impact on the detection accuracy.
  • NASA in the United States uses ultrasonic waves to carry out research on bending stress measurement of shear joints.
  • Koshit constructed the ultrasonic propagation path equation of the bolt structure in the bending state, and simulated and calculated the sound path changes under different bending stresses. Time delay.
  • Both theoretical research and experimental results show that there is a linear relationship between ultrasonic acoustic delay and bending stress.
  • the piezoelectric film can be controlled to overlap with the position of the maximum shear force.
  • the piezoelectric film can be controlled to overlap with the position of the maximum shear force.
  • the randomness of the bolt tightening process there is a random angle between the direction of the maximum shear force and the orientation of the piezoelectric film. The offset results in a large deviation in the calibration coefficient used during the load measurement process, making it impossible to obtain accurate shear force measurement results.
  • the present invention aims to propose a method for measuring the circumferential distribution of bolt shear force based on array film rotation calibration to achieve accurate measurement and direction positioning of shear force on bolt fasteners and devices to be inspected under shear loads. , thereby improving the accuracy of measurement results.
  • a method for measuring the circumferential distribution of bolt shear force based on array film rotation calibration including the following steps:
  • Step S2 Fix the array probe and the array ultrasonic film sensor in one-to-one correspondence, and the array probe is electrically connected to the ultrasonic instrument;
  • Step S3 Fixedly connect the standard bolt to the stretching fixture, and then connect the stretching fixture to the stretching machine.
  • the direction of the line connecting the center of mass point of the array ultrasonic film sensor numbered E1 and the center of the standard bolt is connected to the stretching machine. In the same direction, record the ultrasonic flight time tb 0 of each array ultrasonic film sensor when the shear load is 0;
  • Step S8 Prepare an array ultrasonic film sensor with N array elements arranged in a circumferential direction on the top surface of the bolt to be tested by physical vapor deposition, and fix the array probe and the array ultrasonic film sensor in one-to-one correspondence. Electrically connected to the ultrasonic instrument, the bolt to be tested is fixedly connected to the tensile fixture, and then the tensile fixture is connected to the tensile machine. Measure the ultrasonic flight time tb of each array ultrasonic film sensor when the shear load is 0.
  • the array ultrasonic film sensor corresponding to the maximum ultrasonic flight time is numbered E -measure 1
  • the other array ultrasonic film sensors are numbered clockwise as E -measure 2 , E -measure 3 ...E -measure N ;
  • Step S10 Apply a shear load F measure to the bolt to be tested through a tensile machine, measure the ultrasonic flight time tb measure i of each array ultrasonic film sensor when the shear load is F measure , and subtract tb measure 0 to obtain the ultrasonic
  • the stretching fixture includes a base, a mounting plate, and a stretching rod.
  • the base is provided with two opposite mounting plates.
  • the mounting plate is provided with through holes for fixing bolts.
  • the stretching rod is located on Between the two mounting plates, one end of the stretching rod is sleeved on the bolt, and the other end is connected to the stretching machine.
  • the number of array elements of the array ultrasonic thin film sensor is N>8.
  • the array ultrasonic thin film sensor includes a protective layer, a piezoelectric layer and an electrode layer; preferably, the shape of the array ultrasonic thin film sensor includes one of a circle, a square or a sector.
  • the standard bolts are zero-stress bolts after annealing.
  • the maximum shear load applied by the tensile machine to the standard bolt and the bolt to be tested is less than the shear strength of the standard bolt and the bolt to be tested.
  • the bolt shear force circumferential distribution measurement method based on array film rotation calibration according to the present invention has the following advantages:
  • the measurement method of the present invention no longer uses the original conventional ultrasonic stress detection method, but uses physical vapor deposition technology to prepare piezoelectric films and electrode arrays with acoustic and electrical conversion properties, and transmits ultrasonic waves through the center and receives ultrasonic waves through the array. signal, thereby achieving high-precision measurement of shear stress and positioning of load distribution, avoiding random angular deviation between the direction of maximum shear force and the orientation of the piezoelectric film, and improving the accuracy of measurement results;
  • the measurement method of the present invention prepares a piezoelectric sensing coating on the surface of the fastener, and then prepares an array electrode, conducts a calibration experiment that simulates the actual working environment, records different loads, and collects data from each electrode at different angles of action.
  • the received acoustic time signals form a database, which can monitor the changes in shear force and load distribution in real time during actual work, which is highly practical;
  • the measurement method described in the present invention can be used for, but is not limited to, high-precision measurement of shear stress of bolt fasteners to achieve normal and stable operation under harsh conditions such as high stress and high temperature environments, such as aircraft engine fastening. Bolts, boiler vessel fastening bolts, etc., to achieve high-precision measurement and distribution positioning of fastener shear force.
  • Figure 1 is a schematic diagram of the distribution structure of the array ultrasonic film sensor on the top surface of the bolt according to the embodiment of the present invention
  • Figure 2 is a schematic structural diagram of a stretching clamp according to an embodiment of the present invention.
  • Figure 3 is a relationship curve between ultrasonic flight time and shear load measured by the E1 sensor according to the embodiment of the present invention
  • Figure 4 is the calibration coefficient fitting result of the ultrasonic flight time-angle curve in the range of -180° to 180° measured in the embodiment of the present invention
  • Figure 5 shows the shear force distribution in the circumferential direction of the bolt to be tested measured according to the embodiment of the present invention.
  • test reagents used in the following examples are all conventional biochemical reagents, unless otherwise stated; the experimental methods, unless otherwise stated, are all conventional methods.
  • the bolt shear force circumferential distribution measurement method based on array film rotation calibration in the present invention includes the following steps:
  • the standard bolt in this embodiment is jointly acted by three layers of mezzanine.
  • the tensile fixture is designed as shown in Figure 2. It is fixed through the base. The three layers The tension rod in the middle of the mezzanine applies tension, and the two mounting plates on both sides are bolted, so that the bolts as a whole bear shear force, which is a simulation of actual working conditions;

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  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • General Physics & Mathematics (AREA)
  • Force Measurement Appropriate To Specific Purposes (AREA)

Abstract

本发明提供了一种基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法，通过在标样螺栓上沉积制备阵列超声薄膜传感器，测量超声飞行时间，得到应力标定系数与转动角度的标定函数，之后对待测螺栓上的阵列超声薄膜传感器进行编号；测量基准阵列超声薄膜传感器与剪切载荷方向的夹角，利用标定函数计算对应的标定系数以及圆周方向的应力分布。本发明所述的测量方法不再采用原有的常规超声应力检测方法，而是利用物理气相沉积技术制备具有声电转换性能的压电薄膜与电极阵列，通过中心发射、阵列接收超声波信号，从而实现对剪切应力的高精度测量与载荷分布定位，避免最大剪切力方向与压电薄膜方位存在的随机角度偏移，提高测量结果的准确性。

Description

一种基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法 技术领域
本发明属于螺栓应力超声测量技术领域，尤其是涉及一种基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法。
背景技术
螺栓连接是航空航天领域大型关键装备的重要连接技术。螺栓连接结构所受到的外部振动载荷一般可分为四种情况：轴向拉力、径向剪切力、平行于螺栓轴线的轴向扭矩和垂直于螺栓轴线的径向弯矩。相比于其它三种载荷，横向动态载荷更能够使得螺栓连接结构松动。
国内外开展较早的螺栓应力测量研究工作，其中大部分的研究工作是以轴向应力(预紧力)测量为主。根据声弹性原理，超声波在螺栓中的传播速度与螺栓应力有关，观测超声波在螺栓中的传播时间可知道超声波的传播速度，剪力超声波传播时间与螺栓轴向应力的函数关系，并通过标定试验得到函数关系式中的相关系数，则可以通过测量超声波在螺栓中的传播时间进而定量测量出螺栓应力值，从而判断螺栓联接的健康状况。目前贴片式的超声波应力检测方法已经应用多年，但由于压电晶片一般采用环氧树脂或者胶粘剂粘接在螺栓上，容易出现脱落。而且由于胶层的厚度无法测量，对检测精度造成了较大的影响。
德国开发了基于PMTS(Permanent Mounted Transducer System)传感器的预紧力测量方法，其主要通过在螺栓上制备永久型压电传感器，然后利用传感器的逆压电效应在螺栓内产生超声波信号，通过标定不同载荷、温度与超声波在螺栓内的飞行时间差关系，来实现螺栓内载荷的测量，是螺栓载荷的直接、原位测量方法。但在剪切力测量方面，尚且没有深入的进展或者将剪切力测量与压电薄膜相结合的技术方法。
美国NASA采用超声波开展剪切接头的弯曲应力测量研究工作，Koshit基于超声传播的声束追踪模型，构建了弯曲状态下螺栓结构的超声传播路径方程，模拟计算了不同弯曲应力作用下的声程变化及声延时。理论研究和实验结果均表明，超声的声延时与弯曲应力呈线性关系，但是在一些如探头晶片与反射体对应关系较差的区域，还存在超声信号畸变严重的问题。
现有技术的方法至少存在如下技术问题：
(1)使用传统超声波方法，使用耦合剂等会导致应力检测存在较大的误差，而传统的粘贴压电晶片也对粘接剂要求很高，经常导致超声波信号比较杂乱，而且容易磨损和脱落；
(2)使用压电薄膜进行应力检测时，由于剪力作用的角度往往在紧固件周向非均匀分布，常规的超声测量方法只能确定单点剪力大小，无法得出非均匀的剪力分布；
(3)在标定过程中，可以控制压电薄膜与最大剪切力的位置重叠，但是在实际测量过程中，由于螺栓拧紧过程的随机性，最大剪切力方向与压电薄膜方位存在随机角度偏移，导致在载荷测量过程中所使用的标定系数存在较大的偏差，无法得到精确的剪力测量结果。
发明内容
有鉴于此，本发明旨在提出一种基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法，以实现螺栓紧固件以及受剪切载荷作用待检器件的剪力精确测量与作用方向定位，从而提高测量结果准确性。
为达到上述目的，本发明的技术方案是这样实现的：
一种基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法，包括以下步骤：
步骤S1：在标样螺栓顶面通过物理气相沉积法制备呈周向排列的阵元数为N的阵列超声薄膜传感器，并按顺时针方向依次编号为E i(i＝1,2…N)；
步骤S2：将阵列探针与阵列超声薄膜传感器一一对应固定，所述阵列探针与超声仪器电性连接；
步骤S3：将标样螺栓与拉伸夹具固定连接，之后将拉伸夹具与拉伸机相连，编号为E 1的阵列超声薄膜传感器的质心点与标样螺栓中心连线方向与拉伸机加载方向相同，记录每个阵列超声薄膜传感器在剪切载荷为0时的超声飞行时间tb 0；
步骤S4：通过拉伸机以梯度为ΔF的剪切载荷对标样螺栓施加剪切载荷F＝n*ΔF(n＝1,2,3,4,5)，依次记录每个剪切载荷下每个阵列超声薄膜传感器对应的超声飞行时间tb ni(n＝1,2,3,4,5；i＝1,2…N)，并减去tb 0，得到超声飞行时间差数组Δtb ni(n＝1,2,3,4,5；i＝1,2…N)；
步骤S5：通过超声飞行时间差数组与剪切载荷进行线性拟合分别得到每个阵列超声薄膜传感器剪切载荷与超声飞行时间的关系式：F＝A i0*Δtb+B i0，i＝1,2…N，Δtb为超声飞行时间差，A i0、B i0均为常系数；
步骤S6：以梯度为Δθ依次转动标样螺栓至相较初始角度为θ＝m*Δθ，重复步骤S4-S5，分别计算得到不同角度时的A im及B im，m为转动次数；
步骤S7：通过θ、A im及B im拟合得到关系式：A i＝f i1(θ)，Bi＝f i2(θ)；
步骤S8：在待测螺栓顶面通过物理气相沉积法制备呈周向排列的阵元数为N的阵列超声薄膜传感器，将阵列探针与阵列超声薄膜传感器一一对应固定，所述阵列探针与超声仪器电性连接，将待测螺栓与拉伸夹具固定连接，之后将拉伸夹具与拉伸机相连，测量在剪切载荷为0时每个阵列超声薄膜传感器的超声飞行时间tb 测0，最大超声飞行时间所对应的阵列超声薄膜传感器编号为E 测1，其他阵列超声薄膜传感器按顺时针依次编号为E 测2、E 测3…E 测N；
步骤S9：测量编号为E 测1的超声薄膜传感器与待测螺栓中心点连线方向与剪切载荷方向之间的夹角θ 测，将θ 测代入步骤S7得到的关系式，分别得到每个阵列超声薄膜传感器对应的系数A 测i及B 测i，i＝1,2…N；
步骤S10：通过拉伸机向待测螺栓施加剪切载荷F 测，测量在剪切载荷为F 测时每个阵列超声薄膜传感器的超声飞行时间tb 测i，并减去tb 测0，得到超声飞行时间差数组Δtb 测i，i＝1,2…N，通过公式F 测i＝A 测i*Δtb 测i+B 测i得到待测螺栓圆周方向的剪力分布。
进一步地，所述拉伸夹具包括底座、安装板、拉伸杆，所述底座在安装板上相对设有两个，安装板上设有用于固定螺栓的通孔，所述拉伸杆设于两个安装板之间，拉伸杆的一端套设于螺栓上，另一端与拉伸机相连。
进一步地，所述阵列超声薄膜传感器的阵元数N＞8。
进一步地，所述阵列超声薄膜传感器包括保护层、压电层及电极层；优选地，所述阵列超声薄膜传感器的形状包括圆形、方形或扇形中的一种。
进一步地，所述标样螺栓为退火处理后的零应力螺栓。
进一步地，所述拉伸机向标样螺栓及待测螺栓施加的最大剪切载荷小于标样螺栓及待测螺栓的剪切强度。
相对于现有技术，本发明所述的基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法具有以下优势：
(1)本发明所述的测量方法不再采用原有的常规超声应力检测方法，而是利用物理气相沉积技术制备具有声电转换性能的压电薄膜与电极阵列，通过中心发射、阵列接收超声波信号，从而实现对剪切应力的高精度测量与载荷分布定位，避免最大剪切力方向与压电薄膜方位存在的随机角度偏移， 提高测量结果的准确性；
(2)本发明所述的测量方法在紧固件表面制备压电传感涂层，而后制备阵列电极，进行拟照实际工作环境的标定实验，记录不同载荷，不同作用角度下每个电极采集到的声时信号，形成数据库，即可在实际工作时，实时监测剪力的变化与载荷的分布，实用性强；
(3)本发明所述的测量方法可用于但不仅限于螺栓紧固件的剪切应力高精度测量，实现在高应力、高温度环境等严苛条件下的正常稳定工作，如飞机发动机紧固螺栓、锅炉容器紧固螺栓等，实现对紧固件剪力的高精度测量与分布定位。
附图说明
构成本发明的一部分的附图用来提供对本发明的进一步理解，本发明的示意性实施例及其说明用于解释本发明，并不构成对本发明的不当限定。在附图中：
图1为本发明实施例所述的阵列超声薄膜传感器在螺栓顶面的分布结构示意图；
图2为本发明实施例所述的拉伸夹具的结构示意图；
图3为本发明实施例通过E1传感器测得的超声飞行时间与剪切载荷关系曲线；
图4为本发明实施例测得的-180°到180°范围内超声飞行时间-角度曲线的标定系数拟合结果；
图5为本发明实施例测得的待测螺栓圆周方向的剪力分布。
附图标记说明：
1、底座；2、安装板；3、拉伸杆；4、螺栓；5、阵列超声薄膜传感器。
具体实施方式
除有定义外，以下实施例中所用的技术术语具有与本发明所属领域技术人员普遍理解的相同含义。以下实施例中所用的试验试剂，如无特殊说明，均为常规生化试剂；所述实验方法，如无特殊说明，均为常规方法。
下面结合实施例及附图来详细说明本发明。
本发明中基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法，包括以下步骤：
S1.在标样螺栓顶面使用物理气相沉积方法制备周向排列的阵元数为16的阵列超声薄膜传感器，使用物理气相沉积方法制备压电陶瓷传感器涂层与保护层，在传感器涂层表面制备电极，电极使用银等贴合性好、耐腐蚀且不易脱落的材料，得到带传感器螺栓，本实施例中使用的螺栓为高温环境下使用的镍基合金抗扭螺栓，通过直接物理气相沉积成型或激光切割等方法加工成具有圆周方向16个的阵列超声薄膜传感器的阵列,形成扇形阵列，扇形阵列示意图如图1所示，对圆周上每个的阵列超声薄膜传感器按顺时针顺序编号为E 1、E 2、E 3、……E 16；
S2.根据标样螺栓顶部阵列超声薄膜传感器的阵列排布和数量，制作用于超声仪器与的阵列超声薄膜传感器之间信号传递的阵列探针，探针与阵列超声薄膜传感器的中心一一对应固定；
S3.根据使用标样螺栓实际工作环境所受的剪切力作用，本实施例中的标样螺栓受三层夹层联合作用，设计拉伸夹具如图2所示，通过底座进行固定，三层夹层中部的拉伸杆施加拉力、两侧的两个安装板进行螺栓固定，使得螺栓整体承受剪切力，即实际使用工况的模拟；
S4.将标样螺栓及拉伸夹具固定于标准拉伸机上，并保证编号为E 1的阵列超声薄膜传感器的质心点与螺栓中心点连线方向与拉伸机加载方向一致， 即夹角为0，，记录每个阵列超声薄膜传感器在剪切载荷为0时的超声飞行时间tb 0；
S5.利用拉伸机以梯度5000N设置不同大小的剪切载荷n*2000N(n＝1，2，3，4，5)进行加载，设置的最大剪切载荷值为25kN；
S6.依次记录每个载荷下的每个阵列超声薄膜传感器对应的超声飞行时间tb ni(n＝1,2,3,4,5；i＝1,2,……16),并减去零应力下的时间tb 0,得到飞行时间数组Δtb ni(n＝1,2,3,4,5；i＝1,2,……16)；
S7.利用每个阵列超声薄膜传感器对应的载荷数据和飞行时间数据进行线性拟合，从而得到每个阵列超声薄膜传感器对应的应力标定系数，记录为A i0和B i0；
S8.将标样螺栓旋转5°，即编号E1阵列超声薄膜传感器的质心点与螺栓中心点连线方向与拉伸机加载方向的夹角为5°，重复S5-S7步骤，得到θ＝5°对应的应力标定系数A i1和B i1；
S9.再依次将标样螺栓旋转35倍Δθ＝10°，记录角度和标定系数数组，拟合获得角度与应力标定系数的函数如图3与图4所示。
S10.进行服役螺栓剪切力的实际测量，利用多通道超声仪器，并行测量16个阵列超声薄膜传感器的超声飞行时间，以飞行时间最大的阵列超声薄膜传感器编号为E 1，其他阵列超声薄膜传感器按照顺时针进行编号；
S11.测量E 1阵列超声薄膜传感器的质心点与螺栓中心点连线方向与剪切载荷方向的夹角θ,将夹角按照S9拟合得到的公式，计算出各个阵列超声薄膜传感器对应的标定系数A 测i(i＝1,2,……16)和B 测i(i＝1,2,……16)；
S12.并行测量和记录服役螺栓的N个阵列超声薄膜传感器在剪切载荷为F 测时的超声飞行时间，记录数组t 测i(i＝1,2,……16),并减去服役螺栓零应 力状态时的飞行时间tb 0,得到所有阵列超声薄膜传感器的超声飞行时间数组Δt 测i(i＝1,2,……16)，利用公式计算得到圆周方向的剪力分布如图5所示。
以上所述仅为本发明的较佳实施例而已，并不用以限制本发明，凡在本发明的精神和原则之内，所作的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。

Claims (6)

  1. 一种基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法，其特征在于，包括以下步骤：
    步骤S1：在标样螺栓顶面通过物理气相沉积法制备呈周向排列的阵元数为N的阵列超声薄膜传感器，并按顺时针方向依次编号为E i(i＝1,2…N)；
    步骤S2：将阵列探针与阵列超声薄膜传感器一一对应固定，所述阵列探针与超声仪器电性连接；
    步骤S3：将标样螺栓与拉伸夹具固定连接，之后将拉伸夹具与拉伸机相连，编号为E 1的阵列超声薄膜传感器的质心点和标样螺栓中心连线方向与拉伸机加载方向相同，记录每个阵列超声薄膜传感器在剪切载荷为0时的超声飞行时间tb 0；
    步骤S4：通过拉伸机以梯度为ΔF的剪切载荷对标样螺栓施加剪切载荷F＝n*ΔF(n＝1,2,3,4,5)，依次记录每个剪切载荷下每个阵列超声薄膜传感器对应的超声飞行时间tb ni(n＝1,2,3,4,5；i＝1,2…N)，并减去tb 0，得到超声飞行时间差数组Δtb ni(n＝1,2,3,4,5；i＝1,2…N)；
    步骤S5：通过超声飞行时间差数组与剪切载荷进行线性拟合分别得到每个阵列超声薄膜传感器剪切载荷与超声飞行时间的关系式：F＝A i0*Δtb+B i0，i＝1,2…N，Δtb为超声飞行时间差，A i0、B i0均为常系数；
    步骤S6：以梯度为Δθ依次转动标样螺栓至相较初始角度为θ＝m*Δθ，重复步骤S4-S5，分别计算得到不同角度时的A im及B im，m为转动次数；
    步骤S7：通过θ、A im及B im拟合得到关系式：A i＝f i1(θ)，B i＝f i2(θ)；
    步骤S8：在待测螺栓顶面通过物理气相沉积法制备呈周向排列的阵元数为N的阵列超声薄膜传感器，将阵列探针与阵列超声薄膜传感器一一对应固定，所述阵列探针与超声仪器电性连接，将待测螺栓与拉伸夹具固定连接， 之后将拉伸夹具与拉伸机相连，测量在剪切载荷为0时每个阵列超声薄膜传感器的超声飞行时间tb 测0，最大超声飞行时间所对应的阵列超声薄膜传感器编号为E 测1，其他阵列超声薄膜传感器按顺时针依次编号为E 测2、E 测3…E 测N；
    步骤S9：测量编号为E 测1的超声薄膜传感器与待测螺栓中心点连线方向和剪切载荷方向之间的夹角θ 测，将θ 测代入步骤S7得到的关系式，分别得到每个阵列超声薄膜传感器对应的系数A 测i及B 测i，i＝1,2…N；
    步骤S10：通过拉伸机向待测螺栓施加剪切载荷F 测，测量在剪切载荷为F 测时每个阵列超声薄膜传感器的超声飞行时间tb 测i，并减去tb 测0，得到超声飞行时间差数组Δtb 测i，i＝1,2…N，通过公式F 测i＝A 测i*Δtb 测i+B 测i得到待测螺栓圆周方向的剪力分布。
  2. 根据权利要求1所述的基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法，其特征在于：所述拉伸夹具包括底座、安装板、拉伸杆，所述底座在安装板上相对设有两个，安装板上设有用于固定螺栓的通孔，所述拉伸杆设于两个安装板之间，拉伸杆的一端套设于螺栓上，另一端与拉伸机相连。
  3. 根据权利要求1所述的基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法，其特征在于：所述阵列超声薄膜传感器的阵元数N＞8。
  4. 根据权利要求1所述的基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法，其特征在于：所述阵列超声薄膜传感器包括保护层、压电层及电极层；优选地，所述阵列超声薄膜传感器的形状包括圆形、方形或扇形中的一种。
  5. 根据权利要求1所述的基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法，其特征在于：所述标样螺栓为退火处理后的零应力螺栓。
  6. 根据权利要求1所述的基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法，其特征在于：所述拉伸机对标样螺栓及待测螺栓施加的最大剪切载荷小于标样螺栓及待测螺栓的剪切强度。
PCT/CN2022/097849 2022-05-09 2022-06-09 一种基于阵列薄膜旋转标定的螺栓剪力周向分布测量方法 WO2023216353A1 (zh)

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