CN113155335B - Two-stage type micro-flying piece impact stress testing device and testing method - Google Patents
Two-stage type micro-flying piece impact stress testing device and testing method Download PDFInfo
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Abstract
本发明公开一种两级式微飞片冲击应力测试装置及测试方法,其中,一种两级式微飞片冲击应力测试装置,包括固定底座,固定底座的一侧安装点火装置,固定底座上依次安装有激发装置、飞片靶材、前级压电感知单元、加速膛和后级压电感知单元,固定底座的一侧安装电荷转换单元,前级压电感知单元和后级压电感知单元均与电荷转换单元通信连接。本发明在微飞片穿孔时,利用前级压电薄膜感知层的去极化效应所形成的电信号可以准确获得微飞片的等效面积,便于评估换能元激发作用下微飞片形态,同时有利于准确测量微飞片的冲击应力;通过增置前级压电薄膜感知层等效换算微飞片接触面积则会显著增加后级压电薄膜感知层的测量精度。
The invention discloses a two-stage micro-flyer impact stress test device and a test method. The two-stage micro-flyer impact stress test device includes a fixed base, an ignition device is installed on one side of the fixed base, and an ignition device is installed on the fixed base in sequence. There are excitation device, flyer target, front-stage piezoelectric sensing unit, acceleration chamber and rear-stage piezoelectric sensing unit, and a charge conversion unit is installed on one side of the fixed base, and both the front-stage piezoelectric sensing unit and the rear-stage piezoelectric sensing unit are Communicatively connected to the charge conversion unit. When the micro-flyer is perforated, the electric signal formed by the depolarization effect of the sensing layer of the front-stage piezoelectric film can be used to accurately obtain the equivalent area of the micro-flyer, which is convenient for evaluating the shape of the micro-flyer under the excitation of the transducer element At the same time, it is beneficial to accurately measure the impact stress of the micro-flyer; the equivalent conversion of the contact area of the micro-flyer by adding the front-stage piezoelectric film sensing layer will significantly increase the measurement accuracy of the subsequent piezoelectric film sensing layer.
Description
技术领域Technical Field
本发明属于爆炸和冲击测试领域,具体涉及一种两级式微飞片冲击应力测试装置及测试方法。The invention belongs to the field of explosion and impact testing, and in particular relates to a two-stage micro-flyer impact stress testing device and a testing method.
背景技术Background Art
冲击片雷管不含敏感性起爆药,具有高安全、高可靠以及抗电磁干扰等优势,可广泛应用于智能武器以及民用爆破等诸多领域。在冲击片雷管的设计与制造过程中,测量微飞片在电爆炸箔等换能元激发作用下所获得的冲击应力是评估其起爆性能的关键参数之一。目前,对冲击应力的测量主要通过实时采集高灵敏度压电薄膜在微飞片加速撞击下的电荷输出信号推算获得,该方法具有测试成本低,可适用多种不同测量场合等优势。具体测试时,冲击应力的大小为压电电荷输出与飞片撞击面积所决定,显然,微飞片的形态尺寸以及撞击压电薄膜时的作用面积是测定应力的关键所在。然而,在实际测量中,由于无法准确确定电爆炸产生的微飞片尺寸,往往利用压电薄膜的敏感面积等效代替,导致其测量得到的微飞片冲击应力存在较大误差,无法满足实际需求。Impact piece detonators do not contain sensitive explosives, and have the advantages of high safety, high reliability and anti-electromagnetic interference. They can be widely used in many fields such as intelligent weapons and civilian blasting. In the design and manufacturing process of impact piece detonators, measuring the impact stress obtained by the microfly sheet under the excitation of transducers such as electric explosion foil is one of the key parameters for evaluating its detonation performance. At present, the measurement of impact stress is mainly obtained by real-time acquisition of the charge output signal of the highly sensitive piezoelectric film under the accelerated impact of the microfly sheet. This method has the advantages of low testing cost and applicability to a variety of different measurement occasions. In the specific test, the magnitude of the impact stress is determined by the piezoelectric charge output and the impact area of the fly sheet. Obviously, the shape and size of the microfly sheet and the area of action when it impacts the piezoelectric film are the key to measuring stress. However, in actual measurement, since it is impossible to accurately determine the size of the microfly sheet generated by the electric explosion, the sensitive area of the piezoelectric film is often used as an equivalent substitute, resulting in a large error in the impact stress of the microfly sheet measured, which cannot meet actual needs.
发明内容Summary of the invention
本发明的主要目的在于提供一种两级式微飞片冲击应力测试装置及测试方法,克服现有压电薄膜微飞片冲击应力测试存在较大误差的问题。The main purpose of the present invention is to provide a two-stage micro-flyer impact stress testing device and testing method, so as to overcome the problem of large error in the existing piezoelectric film micro-flyer impact stress testing.
为了实现上述目的,根据本发明的一个方面,提供了一种两级式微飞片冲击应力测试装置,包括固定底座,所述固定底座的一侧安装点火装置,所述固定底座上依次安装有激发装置、飞片靶材、前级压电感知单元、加速膛和后级压电感知单元,所述固定底座的另一侧安装电荷转换单元,所述前级压电感知单元和所述后级压电感知单元均与所述电荷转换单元通信连接,所述电荷转换单元依次通信连接有电荷放大单元、多通道数据采集单元以及数据信息存储单元,将来自前级压电感知单元和后级压电感知单元的电荷信号存储到数据信息存储单元。In order to achieve the above-mentioned purpose, according to one aspect of the present invention, a two-stage micro-flyer impact stress testing device is provided, comprising a fixed base, an ignition device is installed on one side of the fixed base, an excitation device, a flying chip target, a front-stage piezoelectric sensing unit, an acceleration chamber and a rear-stage piezoelectric sensing unit are sequentially installed on the fixed base, a charge conversion unit is installed on the other side of the fixed base, the front-stage piezoelectric sensing unit and the rear-stage piezoelectric sensing unit are both communicatively connected with the charge conversion unit, the charge conversion unit is communicatively connected with a charge amplification unit, a multi-channel data acquisition unit and a data information storage unit in sequence, and the charge signals from the front-stage piezoelectric sensing unit and the rear-stage piezoelectric sensing unit are stored in the data information storage unit.
上述结构中,所述前级压电感知单元具有前级压电薄膜感知层,所述前级压电薄膜感知层通过多次溶液旋涂集成于所述飞片靶材的背面与所述飞片靶材形成一个整体,且所述前级压电薄膜感知层平行布置于所述加速膛的前端面。In the above structure, the front-stage piezoelectric sensing unit has a front-stage piezoelectric film sensing layer, which is integrated on the back side of the flying chip target through multiple solution spin coating to form a whole with the flying chip target, and the front-stage piezoelectric film sensing layer is arranged parallel to the front end face of the acceleration chamber.
上述结构中,所述前级压电薄膜感知层包括采用高速旋涂工艺结合为一体的前级上电极层、前级压电薄膜层以及前级下电极层,所述前级上电极层和所述前级下电极层均采用非金属导电墨水旋涂而成。In the above structure, the front piezoelectric film sensing layer includes a front upper electrode layer, a front piezoelectric film layer and a front lower electrode layer integrated into one by a high-speed spin coating process, and the front upper electrode layer and the front lower electrode layer are both spin-coated with non-metallic conductive ink.
上述结构中,所述后级压电感知单元具有后级压电薄膜感知层,所述后级压电薄膜感知层平行布置于所述加速膛的后端面。In the above structure, the rear-stage piezoelectric sensing unit has a rear-stage piezoelectric film sensing layer, and the rear-stage piezoelectric film sensing layer is arranged in parallel to the rear end surface of the acceleration chamber.
上述结构中,所述后级压电薄膜感知层包括依次设置的后级上封装层、后级上电极层、后级压电薄膜层、后级下电极层和后级柔性基底层,所述后级上封装层和所述后级柔性基底层均采用薄质柔性的高分子薄膜材料,所述后级上电极层和所述后级下电极层均采用导电良好的金属溅射而成,所述后级压电薄膜层采用柔性高分子压电薄膜材料。In the above structure, the rear-stage piezoelectric film sensing layer includes a rear-stage upper packaging layer, a rear-stage upper electrode layer, a rear-stage piezoelectric film layer, a rear-stage lower electrode layer and a rear-stage flexible substrate layer which are arranged in sequence, the rear-stage upper packaging layer and the rear-stage flexible substrate layer are both made of thin and flexible polymer film materials, the rear-stage upper electrode layer and the rear-stage lower electrode layer are both formed by sputtering metal with good conductivity, and the rear-stage piezoelectric film layer is made of flexible polymer piezoelectric film material.
上述结构中,所述电荷转换单元包括外接电容和外接电阻,所述电荷转换单元采用前级电缆与所述前级压电薄膜感知层连接,所述电荷转换单元采用后级电缆与所述后级压电薄膜感知层连接,所述外接电阻的阻值与所述前级电缆的等效电阻相等,所述外接电阻的阻值与所述后级电缆的等效电阻相等。In the above structure, the charge conversion unit includes an external capacitor and an external resistor. The charge conversion unit is connected to the front-stage piezoelectric film sensing layer using a front-stage cable. The charge conversion unit is connected to the rear-stage piezoelectric film sensing layer using a rear-stage cable. The resistance value of the external resistor is equal to the equivalent resistance of the front-stage cable, and the resistance value of the external resistor is equal to the equivalent resistance of the rear-stage cable.
为了实现上述目的,根据本发明的另一方面,一种两级式微飞片冲击应力测试方法,包括:In order to achieve the above object, according to another aspect of the present invention, a two-stage microflyer impact stress testing method comprises:
a.启动点火装置;a. Start the ignition device;
b.记录前级压电薄膜感知层输出的电荷信号的峰值V1max,同时记录下该电荷信号的上升时间ts1,根据压电薄膜传感特性可以换算得到剪切微飞片的实际有效面积A1,具体如下:b. Record the peak value V 1max of the charge signal output by the front-stage piezoelectric film sensing layer, and record the rise time t s1 of the charge signal. According to the sensing characteristics of the piezoelectric film, the actual effective area A 1 of the sheared microfly can be calculated, as follows:
式中,K1为前级压电薄膜感知层的极化强度;Where K1 is the polarization strength of the front-stage piezoelectric film sensing layer;
c.记录后级压电薄膜感知层输出的另一电荷信号的峰值V2max,同时记录下该电荷信号的上升时间ts2;c. Record the peak value V 2max of another charge signal output by the subsequent piezoelectric film sensing layer, and record the rise time t s2 of the charge signal;
微飞片在加速膛内的平均速度v可以用式(2)计算得到;The average velocity v of the microfly in the acceleration chamber can be calculated using formula (2);
微飞片的冲击应力峰值Pmax则可计算如下:The peak value P max of the impact stress of the microfly can be calculated as follows:
式中,K2为后级压电薄膜感知层的灵敏度系数;K2通过霍普金森杆压力装置进行动态标定;Where, K2 is the sensitivity coefficient of the subsequent piezoelectric film sensing layer; K2 is dynamically calibrated by the Hopkinson bar pressure device;
将(1)式带入(3)式,得到微飞片的冲击应力峰值为:Substituting equation (1) into equation (3), we can obtain the peak impact stress of the microfly:
与现有技术相比本发明的有益效果在于:Compared with the prior art, the present invention has the following beneficial effects:
1.在微飞片穿孔时,利用前级压电薄膜感知层的去极化效应所形成的电信号可以准确获得微飞片的等效面积,便于评估换能元激发作用下微飞片形态,同时有利于准确测量微飞片的冲击应力;1. When the microflyer is perforated, the electrical signal formed by the depolarization effect of the front-stage piezoelectric film sensing layer can accurately obtain the equivalent area of the microflyer, which is convenient for evaluating the morphology of the microflyer under the excitation of the transducer, and is also conducive to accurately measuring the impact stress of the microflyer;
2.利用前级压电薄膜感知层的电荷信号、后级压电薄膜感知层的电荷信号所获得的上升时间差,结合加速膛尺寸在测量微飞片冲击应力的同时,还可以获得微飞片在加速膛内的平均速度;2. Using the rise time difference obtained by the charge signal of the front-stage piezoelectric film sensing layer and the charge signal of the rear-stage piezoelectric film sensing layer, combined with the acceleration chamber size, the average speed of the micro-flyer in the acceleration chamber can be obtained while measuring the impact stress of the micro-flyer;
3.针对前级压电薄膜感知层,采用非金属导电墨水作为上电极层、下电极层可以大大降低前级压电薄膜感知层对微飞片穿孔时的力学影响。3. For the front-stage piezoelectric film sensing layer, using non-metallic conductive ink as the upper electrode layer and the lower electrode layer can greatly reduce the mechanical influence of the front-stage piezoelectric film sensing layer on the micro-flyer sheet during perforation.
附图说明BRIEF DESCRIPTION OF THE DRAWINGS
构成本申请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:The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:
图1为本发明两级式微飞片冲击应力测试装置原理图;FIG1 is a schematic diagram of a two-stage microflyer impact stress testing device according to the present invention;
图2是前级压电薄膜感知层结构组成;Figure 2 shows the structure of the front-stage piezoelectric film sensing layer;
图3为后级压电薄膜感知层结构组成;Figure 3 shows the structure of the subsequent piezoelectric film sensing layer;
图4为电荷转换电路结构示意图;FIG4 is a schematic diagram of the structure of a charge conversion circuit;
图5为冲击应力和电荷面密度表。FIG5 is a table of impact stress and charge surface density.
具体实施方式DETAILED DESCRIPTION
需要说明的是,在不冲突的情况下,本申请中的实施例及实施例中的特征可以相互组合。It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application may be combined with each other.
为了使本技术领域的人员更好地理解本申请方案,下面将结合本申请实施例,对本申请实施例中的技术方案进行清楚、完整地描述,显然,所描述的实施例仅仅是本申请一部分的实施例,而不是全部的实施例。基于本申请中的实施例,本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例,都应当属于本申请保护的范围。In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiment of the present application will be clearly and completely described below in combination with the embodiment of the present application. Obviously, the described embodiment is only a part of the embodiment of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work should fall within the scope of protection of the present application.
如图1-4所示,一种两级式微飞片冲击应力测试装置,包括固定底座1,所述固定底座1的一侧安装点火装置2,所述固定底座1上依次安装有激发装置3、飞片靶材4、前级压电感知单元5、加速膛6和后级压电感知单元7,所述固定底座1的另一侧安装电荷转换单元8,所述前级压电感知单元5和所述后级压电感知单元7均与所述电荷转换单元8通信连接,所述电荷转换单元8依次通信连接有电荷放大单元9、多通道数据采集单元10以及数据信息存储单元11,将来自前级压电感知单元5和后级压电感知单元7的电荷信号存储到数据信息存储单元11。As shown in Figures 1-4, a two-stage micro-flyer impact stress testing device includes a fixed base 1, an ignition device 2 is installed on one side of the fixed base 1, an excitation device 3, a flying chip target 4, a front-stage piezoelectric sensing unit 5, an acceleration chamber 6 and a rear-stage piezoelectric sensing unit 7 are installed on the fixed base 1 in sequence, and a charge conversion unit 8 is installed on the other side of the fixed base 1, the front-stage piezoelectric sensing unit 5 and the rear-stage piezoelectric sensing unit 7 are both communicatively connected to the charge conversion unit 8, and the charge conversion unit 8 is communicatively connected to a
所述前级压电感知单元5具有前级压电薄膜感知层,所述前级压电薄膜感知层通过多次溶液旋涂集成于所述飞片靶材4的背面与所述飞片靶材4形成一个整体,且所述前级压电薄膜感知层平行布置于所述加速膛6的前端面。The front-stage piezoelectric sensing unit 5 has a front-stage piezoelectric thin film sensing layer, which is integrated on the back side of the flying chip target 4 through multiple solution spin coating to form a whole with the flying chip target 4, and the front-stage piezoelectric thin film sensing layer is arranged in parallel to the front end surface of the acceleration chamber 6.
所述前级压电薄膜感知层包括采用高速旋涂工艺结合为一体的前级上电极层501、前级压电薄膜层502以及前级下电极层503,所述前级上电极层501和所述前级下电极层503均采用非金属导电墨水旋涂而成。The front-stage piezoelectric film sensing layer includes a front-stage
所述后级压电感知单元7具有后级压电薄膜感知层,所述后级压电薄膜感知层平行布置于所述加速膛6的后端面。The rear-stage piezoelectric sensing unit 7 has a rear-stage piezoelectric film sensing layer, and the rear-stage piezoelectric film sensing layer is arranged in parallel to the rear end surface of the acceleration chamber 6 .
所述后级压电薄膜感知层包括依次设置的后级上封装层704、后级上电极层701、后级压电薄膜层702、后级下电极层703和后级柔性基底层705,所述后级上封装层704和所述后级柔性基底层705均采用薄质柔性的高分子薄膜材料,所述后级上电极层701和所述后级下电极层703均采用导电良好的金属溅射而成,所述后级压电薄膜层702采用柔性高分子压电薄膜材料。The rear-stage piezoelectric film sensing layer includes a rear-stage
所述电荷转换单元8包括外接电容801和外接电阻802,所述电荷转换单元采用前级电缆与所述前级压电薄膜感知层连接,所述电荷转换单元采用后级电缆与所述后级压电薄膜感知层连接,所述外接电阻802的阻值与所述前级电缆的等效电阻相等,所述外接电阻802的阻值与所述后级电缆的等效电阻相等。The charge conversion unit 8 includes an
如图1所示,结合工作原理具体说明一种两级式微飞片冲击应力测试方法,包括:As shown in FIG1 , a two-stage micro-flyer impact stress test method is specifically described in combination with the working principle, including:
a.启动点火装置,电爆炸炸箔产生冲击力;a. Start the ignition device, and the electric explosion foil will produce impact force;
b.冲击力经过所述激发装置产生剪切力,剪切力对飞片靶材剪切破坏,形成一定尺寸的微飞片;b. The impact force generates shear force through the excitation device, and the shear force shears and destroys the target material to form micro-flying pieces of a certain size;
c.微飞片对前级压电薄膜感知层进行穿孔;c. The micro-flying sheet perforates the front-stage piezoelectric film sensing layer;
d.前级压电薄膜感知层输出一定的电荷信号,峰值大小为V1max,同时,记录下该电荷信号的上升时间ts1,根据压电薄膜传感特性可以换算得到剪切微飞片的实际有效面积A1,具体如下:d. The front-stage piezoelectric film sensing layer outputs a certain charge signal with a peak value of V 1max . At the same time, the rise time t s1 of the charge signal is recorded. According to the sensing characteristics of the piezoelectric film, the actual effective area A 1 of the sheared micro-flyer can be calculated, as follows:
式中,K1为前级压电薄膜感知层的极化强度;Where K1 is the polarization strength of the front-stage piezoelectric film sensing layer;
e.微飞片穿孔前级压电薄膜感知层后,经过长度为L的加速膛,动能进一步增加,并惯性撞击位于加速膛后端面的后级压电薄膜感知层,相应地,后级压电薄膜感知层输出另一电荷信号,同时,记录下该电荷信号峰值V2max,以及电荷信号的上升时间ts2;e. After the micro-flyer perforates the front-stage piezoelectric film sensing layer, it passes through the acceleration chamber of length L, and its kinetic energy is further increased, and it inertially impacts the rear-stage piezoelectric film sensing layer located at the rear end surface of the acceleration chamber. Accordingly, the rear-stage piezoelectric film sensing layer outputs another charge signal. At the same time, the peak value V 2max of the charge signal and the rise time t s2 of the charge signal are recorded;
此时,微飞片在加速膛内的平均速度v可以用式(2)计算得到;At this time, the average velocity v of the microfly in the acceleration chamber can be calculated using formula (2);
而微飞片的冲击应力峰值Pmax则可计算如下:The peak value P max of the impact stress of the microfly can be calculated as follows:
式中,K2为后级压电薄膜感知层的灵敏度系数;K2通过霍普金森杆压力装置进行动态标定;Where, K2 is the sensitivity coefficient of the subsequent piezoelectric film sensing layer; K2 is dynamically calibrated by the Hopkinson bar pressure device;
将(1)式带入(3)式,得到微飞片的冲击应力峰值为:Substituting equation (1) into equation (3), we can obtain the peak impact stress of the microfly:
事实上,该微飞片冲击前级压电薄膜形成的穿孔面积与微飞片大小相当。In fact, the area of the perforation formed by the microflyer impacting the front-stage piezoelectric film is comparable to the size of the microflyer.
由图5可以看出,后级压电薄膜感知层的电荷面密度输出大小与加载压力成正比,因此,可以测量微飞片的冲击应力。同时,该电荷面密度又与标定实验中加载物与后级压电薄膜感知层的接触面积密切相关。As can be seen from Figure 5, the charge surface density output of the subsequent piezoelectric film sensing layer is proportional to the loading pressure, so the impact stress of the microfly can be measured. At the same time, the charge surface density is closely related to the contact area between the load and the subsequent piezoelectric film sensing layer in the calibration experiment.
表1不同接触面积的压电感知层灵敏度系数统计值Table 1 Statistical values of sensitivity coefficients of piezoelectric sensing layers with different contact areas
结合表1可知,当与加载物的接触面积显著小于后级压电薄膜感知层的敏感面积时,即:面积比小于1时,灵敏度K2也会迅速下降,通过增置前级压电薄膜感知层等效换算微飞片接触面积则会显著增加后级压电薄膜感知层的测量精度。Combined with Table 1, it can be seen that when the contact area with the load is significantly smaller than the sensitive area of the subsequent piezoelectric film sensing layer, that is, when the area ratio is less than 1, the sensitivity K2 will also drop rapidly. By adding the front-stage piezoelectric film sensing layer to convert the contact area of the micro-flyer into an equivalent, the measurement accuracy of the subsequent piezoelectric film sensing layer will be significantly increased.
以上所述仅为本发明的优选实施例而已,并不用于限制本发明,对于本领域的技术人员来说,本发明可以有各种更改和变化。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、部件拆分或组合等,均应包含在本发明的保护范围之内。The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, component splitting or combination, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.
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