WO2016037400A1 - 基于能量加权因子的复合材料结构冲击区域定位方法 - Google Patents

基于能量加权因子的复合材料结构冲击区域定位方法 Download PDF

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WO2016037400A1
WO2016037400A1 PCT/CN2014/088641 CN2014088641W WO2016037400A1 WO 2016037400 A1 WO2016037400 A1 WO 2016037400A1 CN 2014088641 W CN2014088641 W CN 2014088641W WO 2016037400 A1 WO2016037400 A1 WO 2016037400A1
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impact
monitoring
energy weighting
sensors
sensor
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PCT/CN2014/088641
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English (en)
French (fr)
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袁慎芳
邱雷
任元强
梅寒飞
高尚
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南京航空航天大学
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Priority to US14/767,467 priority Critical patent/US20160252438A1/en
Publication of WO2016037400A1 publication Critical patent/WO2016037400A1/zh

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/30—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
    • G01D5/00—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable
    • G01D5/02—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using mechanical means
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/02—Details
    • G—PHYSICS
    • G08—SIGNALLING
    • G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
    • G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
    • G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/02—Details not specific for a particular testing method
    • G01N2203/0202—Control of the test
    • G01N2203/0212—Theories, calculations
    • G01N2203/0218—Calculations based on experimental data

Definitions

  • the invention relates to a method for positioning a composite structure impact region, and belongs to the technical field of structural health monitoring.
  • composite materials Compared with conventional metal materials, composite materials have the advantages of high specific stiffness, strong resistance to fatigue and corrosion, and flexible design, so they are widely used in aircraft structures.
  • the low resistance of the composite to impact is likely to result in a significant drop in its mechanical properties.
  • impact can occur during manufacturing, service, and maintenance, and is almost inevitable throughout its life cycle. Therefore, it is important to carry out on-board and on-line impact monitoring of aircraft composite structures.
  • the digital impact monitoring node directly converts the impact response signal of the impact sensor into a digital sequence, and extracts corresponding characteristic parameters therefrom to realize the positioning of the impact region, thereby greatly simplifying the system, having the advantages of small size, light weight, low power consumption, and the like. Meet the requirements of on-board online monitoring.
  • the impact occurring in one area may trigger other nodes to perform impact detection. If each node separately locates the impact, it will cause positioning conflict. Therefore, in actual applications, the impact localization algorithm is needed to eliminate such conflicts, and the impact records of multiple nodes are combined to determine the correct impact occurrence area.
  • the technical problem to be solved by the present invention is to overcome technical deficiencies and provide a composite based on energy weighting factors.
  • the material structure impact region localization method can effectively solve the positioning conflict problem existing in the impact monitoring technology of the existing multi-monitoring node network and the problem that the intermediate region is difficult to accurately locate, and perform fast and accurate regional positioning on the impact generating region.
  • a method for locating a composite structure impact region based on an energy weighting factor wherein at least two sets of impact sensor arrays are disposed in the impact monitoring area of the composite structure surface, and each set of impact sensor arrays is respectively connected with a monitoring node signal, and each monitoring node Both are connected to the same monitoring center signal; the impact area positioning method includes the following steps:
  • Step A meshing the impact monitoring area by using a position of each impact sensor disposed on the surface of the composite structure as a mesh apex;
  • Step B When an impact occurs, each of the n monitored nodes that are triggered receives a digital sequence of impulse response signals of each of the impact sensors connected thereto, and selects the first of the digital sequences of the impulse response signals therefrom.
  • the first M impact sensors that arrive at the first rising edge of the signal, M is the number of vertices of a single grid unit divided by step A; then calculate the energy weighting factors of each of the M impact sensors, and send the calculation result to the monitoring center
  • the energy weighting factor of the impact sensor is calculated according to the following formula:
  • EWF is an energy weighting factor of the impact sensor
  • IFRE is a sequence number of arrival times of the first signal rising edge in the digital sequence of the impulse response signal of the impact sensor in the M impact sensors
  • DR is The sum of the durations of the rising edges of all signals in the digital sequence of the impulse response signal of the impact sensor
  • Step C The monitoring center selects the top M with the largest energy weighting factor value from the n ⁇ M impact sensors, keeps the energy weighting factor values of the M impact sensors unchanged, and increases the energy weighting factors of all the remaining impact sensors.
  • the values are all set to 0;
  • Step D The monitoring center determines an area where the impact occurs according to the sum of the energy weighting factors of the impact sensors at the M vertices of each grid unit in the impact monitoring area: the grid unit with the largest value of the sum of the energy weighting factors is The area where the impact occurs.
  • the invention provides a multi-node joint positioning method for network monitoring of multiple impact monitoring nodes, solves the problem of positioning conflicts when multiple node monitoring areas are adjacent, and can accurately perform impact positioning on the intermediate area;
  • the algorithm is simple, the positioning speed is fast, and the software and hardware requirements are low.
  • FIG. 1 is a schematic flow chart of a method for positioning a composite structure impact region according to the present invention
  • Figure 2 is a schematic diagram of the first rising edge and the rising edge duration of the digital sequence
  • Figure 3 is a schematic view showing the arrangement of the impact monitoring system of the wing structure of the UAV composite material
  • Figure 4 is an energy weighting factor distribution diagram of the first eight sensors arriving at the first rising edge
  • Figure 5 is a distribution plot of the sum of the energy weighting factors for each of the 25 monitored sub-regions.
  • the basic idea of the invention is to define a characteristic parameter called energy weighting factor according to the characteristic that the sensor located in the impact generating area is closest to the impact position and is most affected by the impact, and each sensor is characterized by the entire impact monitoring range. The extent of the impact of the impact, and then the extent of the impact of each sub-area within the monitoring range, and finally determine the sub-area that is most affected is the impact sub-area.
  • the invention uniformly evaluates the magnitude of the impact of each impact monitoring sub-region by the impact from a global, not limited to a single node monitoring range, and displays the phases of multiple impact monitoring nodes during large-scale network monitoring.
  • the neighboring node positioning conflict and the intermediate area positioning problem are uniformly restored to the problem of the impact degree of the sub-area affected by the impact, which effectively solves both problems.
  • each of the monitoring nodes is respectively connected with a sensor array composed of a plurality of impact sensors, and each monitoring node is Information can be exchanged with the monitoring center.
  • the whole monitoring area is divided into a series of non-overlapping sub-areas by meshing in advance, that is, each shock sensor is located as a mesh vertice, and the impact monitoring area is meshed.
  • the specific division of the grid can be flexibly selected according to the actual arrangement of the sensor. For example, a triangular mesh, a quadrilateral mesh, a hexagonal mesh, etc. can be used. When the triangular meshing mode is adopted, every 3 adjacent impacts are used.
  • the sensor is a vertex of a grid unit, and its corresponding grid unit is a sub-area. Similarly, when a quadrilateral grid is used, each grid unit has 4 vertices.
  • the positioning process of the entire impact area is as shown in FIG. 1 , and specifically includes the following steps:
  • each monitored node is triggered to convert the response signals of the respective connected impact sensors into a digital sequence, and each triggered monitoring node obtains a set Shock response signal digital sequence.
  • the 1, 2, ..., n monitoring nodes respectively select the first 4 digital sequences of the first rising edge from the digital sequence of the impulse response signals obtained by them (for the sake of description, the quadrilateral mesh is used here)
  • the number of selected digital sequences also changes.
  • the first digital sequence of the first rising edge of the three paths is selected. And calculate the sum of the durations of all their respective rising edges.
  • the definition of the first rising edge and the rising edge duration of the digital sequence is shown in Figure 2.
  • the monitoring nodes of 1, 2, ..., n respectively calculate the energy weighting factors of the four piezoelectric sensors and upload them to the monitoring center.
  • the monitoring center receives 4 ⁇ n energy weighting factors, corresponding to 4 ⁇ n impacts. sensor.
  • the energy weighting factor of the impact sensor is calculated according to the following formula:
  • EWF is the energy weighting factor of the impact sensor
  • IFRE is the order of the arrival time of the rising edge of the first signal in the digital sequence of the impulse response signal of the impact sensor in the selected four impact sensors, The impact sensor that arrives first at the rising edge of a signal has an IFRE value of 1, the second arrives with an IFRE value of 2, and so on
  • DR is the entire signal in the digital sequence of the impulse response signal of the impact sensor.
  • the sum of the durations of the rising edges, where the unit of measurement of the duration can be seconds, milliseconds, subtle, etc., as long as it is uniform, the invention preferably uses milliseconds.
  • the monitoring center selects the four values from the energy weighting factors of the 4 ⁇ n piezoelectric sensors to maximize the energy weighting factor values of the four impact sensors and weights the energy of all other piezoelectric sensors.
  • the factor values are all set to zero.
  • the monitoring center calculates the sum of the energy weighting factors of the four impact sensors at the apex of each sub-area (ie, the grid unit) divided in the entire impact monitoring area, and takes the largest sub-area as the impact generating sub-area.
  • a piezoelectric sensor and an impact monitoring node are arranged on the wing of the UAV composite material, and the monitoring network is configured to perform impact monitoring on the wing, thereby explaining the specific implementation process of the method of the present invention.
  • the size of the UAV composite wing is 2000mm ⁇ 1200mm, and 36 piezoelectric sensors are arranged on the inner surface of the wing composite skin, which are recorded as No. 1 to No. 36 sensors.
  • sensors No. 1 to No. 18 are connected to No. 1 wireless shock monitoring node.
  • sensors No. 1 to No. 18 form 10 impact monitoring sub-areas, which are recorded as sub-areas No. 1 to No. 10; sensor connections No. 19 to No. 36
  • the No. 2 wireless shock monitoring node also constitutes 10 impact monitoring sub-areas, which are recorded as sub-areas 11 to 20.
  • Each sub-area is surrounded by four piezoelectric sensors with an area of 170 x 150 mm 2 .
  • the sub-area belongs to the middle area, so the impact monitoring nodes No. 1 and No. 2 are triggered.
  • the workflow of the entire monitoring network is as follows:
  • Node 1 is triggered, and the response signals of the 18 piezoelectric sensors connected thereto are converted into digital sequences, totaling 18 digital sequences, and the length of each digital sequence is set to 1000 points.
  • Node 1 selects the first four digit sequences of the first rising edge from the 18 digital sequences and calculates the sum of their respective rising edge durations.
  • the first sensors that arrive at the first rising edge of the digital sequence are 9, 12, 6, and 11 in sequence.
  • Node 1 calculates the energy weighting factors of the four piezoelectric sensors and uploads them to the monitoring center wirelessly, with values of 2.92, 1.53, 0.71, and 0.49, respectively.
  • Node 2 performs the above steps of node 1 at the same time, and the first sensors that arrive at the first rising edge of the digital sequence in all sensors connected to node 2 are 28, 25, 29, and 26, respectively.
  • the energy weighting factors of the four sensors are 3.05, 1.47, 0.79, and 0.52, respectively.
  • the monitoring center selects the four largest among the energy weighting factors of the eight piezoelectric sensors.
  • Figure 4 lists the energy weighting factors of the eight sensors. It can be seen from the figure that the energy weighting factor is the largest.
  • the sensors are 28, 9, 12, and 25 respectively. Keeping the energy weighting factor values of sensors No. 28, 9, 12, and 25 unchanged, the monitoring center sets the energy weighting factor values of the other 32 piezoelectric sensors to zero.
  • the invention defines an energy weighting factor to measure the degree of impact of each sensor in the monitoring range, and then uniformly evaluates the impact degree of all sub-areas affected by the impact and finally locates the impact generating sub-area, and solves the multi-node monitoring area phase.
  • the problem of positioning conflict and the problem of intermediate sub-area appearing in the neighboring time can quickly and accurately locate the impact of all sub-areas within the monitoring range.
  • the invention can meet the airborne application requirements of the large-area online impact monitoring of the composite material structure, and can promote the application and development of the structural health monitoring and management system in China.

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Abstract

一种基于能量加权因子的复合材料结构冲击区域定位方法，属于结构健康监测技术领域。根据位于冲击发生区域内的传感器距离冲击位置最近、受冲击影响最大的特点，定义了能量加权因子特征参数，在整个冲击监测范围内表征每个传感器受冲击影响程度的大小，进而计算监测范围内每个子区域受冲击影响程度的大小，并最终判定受影响程度最大的子区域为冲击发生子区域。解决了现有多节点大规模组网监测时出现的相邻节点定位冲突以及中间区域定位盲区问题；该方法通过组网联合多个节点共同进行冲击监测，能够快速、准确地对网络监测范围内的所有子区域进行冲击定位。

Description

基于能量加权因子的复合材料结构冲击区域定位方法 技术领域
本发明涉及一种复合材料结构冲击区域定位方法，属于结构健康监测技术领域。
背景技术
复合材料相比于常规金属材料具有比刚度大、对疲劳和腐蚀抵抗力强以及设计灵活等优点，因此被大量应用于飞行器结构。然而，复合材料对冲击的低抗性容易导致其机械性能的大幅下降。对于飞行器复合材料结构而言，冲击可能发生在制造、服役和维护过程中，在其整个寿命周期中几乎是不可避免的。因此，对飞行器复合材料结构进行机载、在线冲击监测是很重要的。
传统的结构健康监测系统在进行冲击监测时，由于追求高定位精度，因此系统对软、硬件配置往往具有很高的要求，导致系统体积大、功耗高，不能满足航空机载的要求。数字式冲击监测节点将冲击传感器的冲击响应信号直接转换为数字序列，并从中提取相应特征参数以实现冲击区域的定位，从而大大简化了系统，具有体积小、重量轻、功耗低等优点，满足机载在线监测的要求。
真实飞行器往往存在多个大面积复合材料结构需要进行冲击监测，例如机翼、机身和垂尾等，因此往往需要用多个冲击监测节点进行组网监测。然而当多个监测节点对同一结构进行大规模组网冲击监测时，存在如下两个问题：
(1)当多个监测节点的监测区域相邻时，发生在一个区域的冲击可能会触发其它节点也进行冲击检测，如果每个节点均单独对冲击进行定位，则会导致定位冲突。因此在实际应用中需要冲击定位算法能够消除这种冲突，联合多个节点的冲击记录共同判断出正确的冲击发生区域。
(2)相邻的监测区域之间往往存在中间区域，这些中间区域不属于任何一个节点的监测范围，但也同样需要进行冲击监测。工作在单个节点内的定位算法只能对该节点监测范围内的区域进行冲击监测定位，无法定位这些中间区域。故需要新的冲击定位算法来对发生在这些中间区域上的冲击进行识别和定位。
发明内容
本发明所要解决的技术问题在于克服技术不足，提供一种基于能量加权因子的复合 材料结构冲击区域定位方法，可有效解决现有多监测节点组网的冲击监测技术所存在的定位冲突问题以及中间区域难以准确定位的问题，对冲击发生区域进行快速准确的区域定位。
本发明具体采用以下技术方案：
基于能量加权因子的复合材料结构冲击区域定位方法，所述复合材料结构表面的冲击监测区域内设置有至少两组冲击传感器阵列，每一组冲击传感器阵列分别与一个监测节点信号连接，各监测节点均与同一个监测中心信号连接；所述冲击区域定位方法包括以下步骤：
步骤A、以复合材料结构表面所设置的每一个冲击传感器所在位置分别作为一个网格顶点，对所述冲击监测区域进行网格划分；
步骤B、当冲击发生时，被触发的n个监测节点中的每一个监测节点接收与其连接的每一个冲击传感器的冲击响应信号数字序列，并从中选出其冲击响应信号数字序列中的第一个信号上升沿最先到达的前M个冲击传感器，M为步骤A所划分的单个网格单元的顶点数；然后计算这M个冲击传感器各自的能量加权因子，并将计算结果发送给监测中心；所述冲击传感器的能量加权因子按照下式计算：
Figure PCTCN2014088641-appb-000001
式中，EWF为冲击传感器的能量加权因子，IFRE为该冲击传感器的冲击响应信号数字序列中的第一个信号上升沿的到达时间在所述M个冲击传感器中的先后次序号，DR为该冲击传感器的冲击响应信号数字序列中的全部信号上升沿的持续时间之和；
步骤C、监测中心从这n×M个冲击传感器中选出能量加权因子值最大的前M个，保持这M个冲击传感器的能量加权因子值不变，并将其余所有冲击传感器的能量加权因子值均设为0；
步骤D、监测中心根据所述冲击监测区域中每一个网格单元的M个顶点处的冲击传感器的能量加权因子之和确定冲击发生的区域：能量加权因子之和的值最大的网格单元即为冲击发生的区域。
相比现有技术，本发明技术方案具有以下有益效果：
本发明为多个冲击监测节点组网监测提供了一种多节点联合定位方法，解决了多个节点监测区域相邻时出现的定位冲突问题，并能够准确的对中间区域进行冲击定位；本发明算法简单，定位速度快，对软件硬件要求低。
附图说明
图1为本发明的复合材料结构冲击区域定位方法的流程示意图；
图2为数字序列第一个上升沿及上升沿持续时间的示意图；
图3无人机复合材料机翼结构冲击监测系统布置示意图；
图4为第一个上升沿最先到达的8个传感器的能量加权因子分布图；
图5为25个监测子区域各自的能量加权因子之和的分布图。
具体实施方式
下面结合附图对本发明的技术方案进行详细说明：
本发明的基本思路是根据位于冲击发生区域内的传感器距离冲击位置最近、受冲击影响最大的特点，定义了一种称为能量加权因子的特征参数，在整个冲击监测范围内表征每个传感器受冲击影响程度的大小，进而计算监测范围内每个子区域受冲击影响程度的大小，并最终判定受影响程度最大的子区域为冲击发生子区域。本发明通过上述方式从一个全局的、不局限于单个节点监测范围的角度统一评判各个冲击监测子区域受冲击影响程度的大小，将多个冲击监测节点在进行大规模组网监测时出现的相邻节点定位冲突以及中间区域定位问题统一还原为求冲击发生子区域受冲击影响程度大小的问题，有效的解决了这两种问题。
假定待监测复合材料结构中布置了多个冲击监测节点组成监测网络，对整个监测区域进行冲击监测；其中每个监测节点均分别连接一个由多个冲击传感器所组成的传感器阵列，各监测节点均可与监测中心进行信息交互。
预先通过网格划分的方式将整个监测区域划分为一系列互不重叠的子区域，即以每一个冲击传感器所在位置分别作为一个网格顶点，对所述冲击监测区域进行网格划分。网格的具体划分方式可结合传感器的实际布置情况灵活选取，例如可采用三角网格、四边形网格、六边形网格等，当采用三角网格划分方式时，每3个相邻的冲击传感器作为一个网格单元的顶点，其所对应的网格单元即为一个子区域，类似地，当采用四边形网格时，每个网格单元既具有4个顶点。
当冲击发生时，整个冲击区域的定位流程如图1所示，具体包括以下步骤：
(1)1,2，…，n号监测节点被触发，被触发的每个监测节点分别将各自连接的各冲击传感器的响应信号转换为数字序列，每个被触发的监测节点都获得一组冲击响应信号数字序列。
(2)1,2，…，n号监测节点分别从其获得的冲击响应信号数字序列中挑选出第一个上升沿最先到达的4路数字序列(为便于描述，此处以四边形网格划分方式为例，当采用其它网格划分方式时，所挑选的数字序列数目也随之变化，例如，当采用三角网格时，则挑选3路第一个上升沿最先到达的数字序列)，并计算它们各自的全部上升沿的持续时间之和。数字序列第一个上升沿和上升沿持续时间的定义如图2所示。
(3)1,2，…，n号监测节点分别计算这4个压电传感器的能量加权因子并上传给监测中心，监测中心共收到4×n个能量加权因子，对应4×n个冲击传感器。所述冲击传感器的能量加权因子按照下式计算：
Figure PCTCN2014088641-appb-000002
式中，EWF为冲击传感器的能量加权因子；IFRE为该冲击传感器的冲击响应信号数字序列中的第一个信号上升沿的到达时间在所选出的4个冲击传感器中的先后次序号，第一个信号上升沿最先到达的冲击传感器，其IFRE值则为1，第二个到达的，其IFRE值为2，依此类推；DR为该冲击传感器的冲击响应信号数字序列中的全部信号上升沿的持续时间之和，此处持续时间的度量单位可采用秒、毫秒、微妙等，只要统一即可，本发明优选采用毫秒。
(4)监测中心从这4×n个压电传感器的能量加权因子中挑选出4个值最大的，保持这4个冲击传感器的能量加权因子值不变并将所有其它压电传感器的能量加权因子值均设为0。
(6)监测中心计算整个冲击监测区域中所划分的每个子区域(即网格单元)顶点处的4个冲击传感器的能量加权因子之和，取和最大的子区域作为冲击发生子区域。
为了更好地说明本发明的技术方案，在无人机复合材料机翼上布置压电传感器以及冲击监测节点，组成监测网络对机翼进行冲击监测，以此来说明本发明方法的具体实施过程。
如图3所示，无人机复合材料机翼的尺寸为2000mm×1200mm，在机翼复合材料蒙皮内表面共布置了36个压电传感器，记为1号到36号传感器。其中1号到18号传感器连接1号无线冲击监测节点，如图所示，1号到18号传感器组成10个冲击监测子区域，记为1号到10号子区域；19到36号传感器连接2号无线冲击监测节点，也组成10个冲击监测子区域，记为11到20号子区域。此外，1号节点和2号节点的监测区域 间还存在5个中间子区域，记为21到25号子区域。每个子区域由4个压电传感器围成，面积为170×150mm2。
以在23号子区域施加冲击为例，该子区域属于中间区域，故1号、2号冲击监测节点都会被触发。
按照图1所示的冲击区域定位算法执行机制，整个监测网络的工作流程如下：
(1)1号节点被触发，将其连接的18个压电传感器的响应信号均转换为数字序列，共计18路数字序列，设定每路数字序列的长度为1000个点。
(2)1号节点从这18路数字序列中挑选出第一个上升沿最先到达的4路数字序列，并计算它们各自的上升沿持续时间之和。本实施例中1号节点连接的所有传感器中数字序列第一个上升沿最先到达的4个传感器依次为9、12、6、11号。
(3)1号节点分别计算这4个压电传感器的能量加权因子并通过无线方式上传给监测中心，值分别为2.92、1.53、0.71和0.49。
(4)2号节点同时执行1号节点的上述步骤，且2号节点连接的所有传感器中数字序列第一个上升沿最先到达的4个传感器依次为28、25、29、26号，这4个传感器的能量加权因子分别为3.05、1.47、0.79、0.52。
(5)监测中心从这8个压电传感器的能量加权因子中挑选出4个最大的，图4列出了这8个传感器的能量加权因子，从图中可以看出能量加权因子最大的4个传感器分别为28、9、12、25号。保持28、9、12、25号传感器的能量加权因子值不变，监测中心将其它32个压电传感器的能量加权因子值均设为0。
(6)计算监测范围内全部25个子区域中每个子区域的4个压电传感器的能量加权因子之和，取和最大的作为冲击发生子区域。图5显示了每个监测子区域的能量加权因子和值的分布情况，从图中可以看出23号子区域的4个传感器的能量加权因子之和最大，被判断是冲击发生子区域，与实际吻合。
本发明通过定义一种能量加权因子来度量监测范围内每个传感器受冲击影响程度，进而对所有子区域受冲击影响程度进行统一评判并最终定位冲击发生子区域，解决了多个节点监测区域相邻时出现的定位冲突问题和中间子区域定位问题，能够快速准确地对监测范围内的所有子区域进行冲击定位。本发明能够满足复合材料结构大面积在线冲击监测的机载应用需求，可以促进我国结构健康监测与管理系统的应用和发展。

Claims (5)

  1. 基于能量加权因子的复合材料结构冲击区域定位方法，所述复合材料结构表面的冲击监测区域内设置有至少两组冲击传感器阵列，每一组冲击传感器阵列分别与一个监测节点信号连接，各监测节点均与同一个监测中心信号连接；其特征在于，所述冲击区域定位方法包括以下步骤：
    步骤A、以复合材料结构表面所设置的每一个冲击传感器所在位置分别作为一个网格顶点，对所述冲击监测区域进行网格划分；
    步骤B、当冲击发生时，被触发的n个监测节点中的每一个监测节点接收与其连接的每一个冲击传感器的冲击响应信号数字序列，并从中选出其冲击响应信号数字序列中的第一个信号上升沿最先到达的前M个冲击传感器，M为步骤A所划分的单个网格单元的顶点数；然后计算这M个冲击传感器各自的能量加权因子，并将计算结果发送给监测中心；所述冲击传感器的能量加权因子按照下式计算：
    Figure PCTCN2014088641-appb-100001
    式中，EWF为冲击传感器的能量加权因子，IFRE为该冲击传感器的冲击响应信号数字序列中的第一个信号上升沿的到达时间在所述M个冲击传感器中的先后次序号，DR为该冲击传感器的冲击响应信号数字序列中的全部信号上升沿的持续时间之和；
    步骤C、监测中心从这n×M个冲击传感器中选出能量加权因子值最大的前M个，保持这M个冲击传感器的能量加权因子值不变，并将其余所有冲击传感器的能量加权因子值均设为0；
    步骤D、监测中心根据所述冲击监测区域中每一个网格单元的M个顶点处的冲击传感器的能量加权因子之和确定冲击发生的区域：能量加权因子之和的值最大的网格单元即为冲击发生的区域。
  2. 如权利要求1所述复合材料结构冲击区域定位方法，其特征在于，所述冲击传感器为压电传感器。
  3. 如权利要求1所述复合材料结构冲击区域定位方法，其特征在于，对所述冲击监测区域进行四边形网格划分。
  4. 如权利要求1所述复合材料结构冲击区域定位方法，其特征在于，所述监测中心与监测节点之间通过无线方式信号连接。
  5. 如权利要求1所述复合材料结构冲击区域定位方法，其特征在于，在能量加权因子 计算公式中，该冲击传感器的冲击响应信号数字序列中的全部信号上升沿的持续时间之和DR的单位为毫秒。
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