WO2017067034A1 - 基于二极管阵列数字化的微小型超低功耗冲击监测系统 - Google Patents

基于二极管阵列数字化的微小型超低功耗冲击监测系统 Download PDF

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WO2017067034A1
WO2017067034A1 PCT/CN2015/094667 CN2015094667W WO2017067034A1 WO 2017067034 A1 WO2017067034 A1 WO 2017067034A1 CN 2015094667 W CN2015094667 W CN 2015094667W WO 2017067034 A1 WO2017067034 A1 WO 2017067034A1
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module
array
micro
unit
diode array
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PCT/CN2015/094667
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English (en)
French (fr)
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邱雷
袁慎芳
郑倩云
梅寒飞
任元强
鲍峤
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南京航空航天大学
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Priority to US15/513,857 priority Critical patent/US10145746B2/en
Publication of WO2017067034A1 publication Critical patent/WO2017067034A1/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
    • G01L5/0052—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes measuring forces due to impact
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
    • G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
    • 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
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B2219/00—Program-control systems
    • G05B2219/20—Pc systems
    • G05B2219/25—Pc structure of the system
    • G05B2219/25145—I-O communicates with local bus at one end and with fieldbus at other end

Definitions

  • the invention relates to a micro-miniature ultra-low power impact monitoring system based on digitization of a diode array, and belongs to the technical field of aircraft structural health monitoring.
  • the impact of the structure of the aircraft is a random transient event that must be monitored at the moment the impact occurs. Therefore, the impact monitoring system must be installed as an airborne device on the aircraft to perform online real-time uninterrupted impact monitoring.
  • the current conventional impact monitoring system achieves accurate impact localization and evaluation in order to obtain an impulse response signal, and includes an analog circuit composed of a signal amplifier, a filter, and a digital-to-analog converter, and a microprocessor and peripheral devices supporting a complex monitoring algorithm.
  • the digital circuit in addition to large-scale structure large-area monitoring, due to the large number of channels required, resulting in a large system, large weight, large power consumption, and reliability is difficult to ensure, it is difficult to achieve low-power on-board , small size and high reliability requirements.
  • a miniaturized digital large-scale sensor array impact monitoring system which replaces the digital-to-analog converter in a conventional impact monitoring system with a high-speed voltage comparator array and replaces it with a programmable logic gate array.
  • a digital circuit consisting of a microprocessor and peripheral devices.
  • the high speed voltage comparator is capable of directly converting an analog form of the impulse response signal into an impact digital sequence.
  • the programmable logic gate array acquires the digital sequence and realizes the recording of the impact event and the location of the impact region by the impact region localization algorithm based on the digital sequence.
  • the system has the characteristics of small size, light weight and real-time online real-time impact monitoring, which provides a space for the impact monitoring system. A feasible and effective implementation.
  • the high-speed voltage comparator array used in the above-mentioned miniaturized digital large-scale sensor array impact monitoring system for digitizing the impulse response signal is an active array, and each comparator in the array is implemented by a comparator chip.
  • the comparator chip is often bulky and has high power consumption, which increases the volume and power consumption of the entire impact monitoring system to a certain extent, which is not conducive to achieving micro-miniature and ultra-low power consumption.
  • the aerodynamic noise that the real aircraft will experience during flight will interfere with the noise generated by the engine vibration, and this low frequency and high frequency vibration will interfere with the acquisition of the impulse response signal by the piezoelectric element, resulting in the acquired digital sequence not being correct.
  • the ground characterizes the impact information, thereby reducing the accuracy of the judgment of the real impact. Therefore, it is necessary to filter the low frequency noise and the high frequency noise signal through signal conditioning before digitizing the impulse response signal, thereby fundamentally eliminating the interference of the low frequency noise and the high frequency noise on the impulse response signal.
  • the above-mentioned miniaturized digital large-scale sensor array impact monitoring system does not consider the interference problem in this respect.
  • the occurrence of the impact is a random event. It is not only necessary to monitor the impact during the flight. Even when the aircraft is grounded, powered off or maintained, there will be an impact event. Therefore, the impact monitoring is An online real-time uninterrupted process. At this point, the impact monitoring system is required to be self-powered, so that all the impacts on the structure can be monitored as much as possible, providing timely maintenance.
  • the present invention proposes a micro-miniature ultra-low power impact monitoring system based on diode array digitization.
  • the system is suitable for on-board use, and has the characteristics of supporting a large number of sensors, small volume, ultra-light quality, ultra-low power consumption, self-power supply, and can be used for network monitoring. It can realize online real-time uninterrupted impact on the structure of the aircraft. Monitoring to improve the safety and maintenance efficiency of the aircraft structure.
  • a micro-miniature ultra-low power impact monitoring system based on diode array digitization including micro sensor array interface, passive band pass filter array, diode array, digital conversion and management module, airborne bus communication module, monitoring data storage module Self-powered module and micro-miniature communication interface, wherein micro-miniature sensor array interface, passive band-pass filter array, diode array and digital conversion and management module are sequentially connected, digital conversion and management module and airborne bus communication module are bidirectionally connected, digital Two-way connection between conversion and management module and monitoring data storage module, two-way connection between on-board bus communication module and micro-miniature communication interface, on-board bus communication module, monitoring data storage module and digital
  • the conversion and management modules are respectively connected to the self-power supply module, and the self-power supply module and the micro-miniature communication interface are connected.
  • the diode array is composed of n diode units, where n is a natural number greater than or equal to 1, and each diode unit is implemented by a passive transient suppression diode or a passive Zener diode circuit.
  • the passive band pass filter array is composed of n band pass filter units, each band pass filter unit is composed of an m-th order high-pass circuit and an m-th order low-pass circuit, wherein n and m are both greater than or equal to 1. Natural number.
  • the m-th order high-pass circuit is a passive filter composed of m capacitors and m resistors connected in series, one end of the m resistors are uniformly grounded, and the m-th order low-pass circuit is composed of m resistors and m capacitors connected in series.
  • the passive filter has one end of m capacitors uniformly grounded, wherein m is a natural number greater than or equal to 1.
  • the self-power supply module is composed of a power protection unit, a first-level conditioning unit, a charging management unit, an aeronautical rechargeable battery, a power switching unit, a secondary conditioning unit, and three linear conversion units, wherein the power protection unit, the first-level conditioning unit, The charging management unit, the aeronautical rechargeable battery, the power switching unit and the secondary conditioning unit are sequentially connected, the first conditioning unit and the power switching unit are sequentially connected, and the first linear conversion unit, the second linear conversion unit and the third linear conversion unit are respectively The secondary conditioning unit is connected.
  • the system of the present invention has the characteristics of supporting a large number of sensors, a small volume, an ultra-light quality, an ultra-low power consumption, a self-power supply, and a networkable monitoring.
  • the system of the present invention is suitable for on-board use, enabling online real-time uninterrupted impact monitoring of large-scale aircraft structures, thereby improving the safety and maintenance efficiency of the aircraft structure.
  • 1 is a schematic diagram of the hardware architecture of the system of the present invention.
  • FIG. 2 is a schematic diagram of a passive band pass filter array of the present invention.
  • Figure 3 is a schematic illustration of a diode array of the present invention.
  • FIG. 4 is a schematic diagram of a self-powered module of the system of the present invention.
  • FIG. 5 is a schematic diagram of a hardware integration structure of the system of the present invention.
  • the system hardware architecture of the present invention is shown in FIG.
  • the system consists of micro-miniature sensor array interface, passive band-pass filter array, diode array, digital conversion and management module, airborne bus communication module, monitoring data storage module, self-powered module and micro-miniature communication interface.
  • the airborne bus communication module and the micro-miniature communication interface are bidirectionally connected, and the onboard bus communication module, the monitoring data storage module and the digital conversion and management module are respectively connected with the self-power supply module, and the self-power supply module and the micro-miniature communication interface are connected.
  • the passive bandpass filter array consists of n bandpass filter units, as shown in Figure 2.
  • Each band pass filter unit is composed of an m-th order high-pass circuit and an m-th order low-pass circuit.
  • the m-th order high-pass circuit is a passive filter composed of m capacitors and m resistors in series. One end of the m resistors is grounded uniformly.
  • the m-th order low-pass circuit is a passive filter composed of m resistors and m capacitors connected in series, and one end of the m capacitors is uniformly grounded.
  • n is 32
  • m is a natural number greater than or equal to 1.
  • the function of the passive band-pass filter array is to suppress the low-frequency and high-frequency noise interference of the impulse response signal, and improve the accuracy of discriminating the real impact region.
  • the diode array consists of n diode cells, as shown in Figure 3. Each diode unit is implemented by a passive TVS diode or a Zener diode circuit. The number n of diode units is the same as the number of band pass filter units. After the impulse response signal after the passive band pass filter array passes through the diode array, the amplitude of the impulse response signal is controlled within the clamp voltage range of the diode under the premise of retaining the characteristics of the impulse response signal, thereby ensuring safe entry into the digital conversion. And management module. A first level of digitization of the impulse response signal is achieved.
  • the digital conversion and management module is composed of micro-miniature ultra-low power field programmable logic gate array and its peripheral circuits, realizes the second set digitization of the impulse response signal, and processes the shock response digital signal to realize the impact area monitoring. And storing the monitoring result and the collected digital sequence in the monitoring data storage module.
  • the digital conversion and management module is also responsible for controlling the communication between the onboard bus communication module and the onboard area level manager, and transmitting the stored monitoring results and the collected digital sequence to the onboard regional level manager and accepting the onboard Control of the regional level manager.
  • the monitoring system uses a diode array to control the amplitude of the impulse response signal within the clamping voltage range of the diode to achieve the first level of digitization; digital conversion and management consisting of a micro-miniature ultra-low power field programmable logic gate array The module implements a second level of digitization of the impulse response signal.
  • the self-power supply module is composed of a power protection unit, a first-level conditioning unit, a charging management unit, an aeronautical rechargeable battery, a power switching unit, a secondary conditioning unit, and three linear conversion units.
  • the power switching unit of the self-power supply module turns on the first-level conditioning unit to directly supply power to other modules, and simultaneously charges the aviation rechargeable battery; when the aviation power is turned off, the power switching unit turns on the aviation rechargeable battery. Powering other modules to achieve self-powering of the entire system ensures that the system will continue to operate uninterrupted when the aircraft is grounded.
  • the impulse response signal generated by the external piezoelectric sensor array of the system is input to the inside of the system through the micro sensor array interface.
  • the onboard bus communication and the input of the aeronautical power supply share a micro-miniature communication power supply interface to connect with the external airborne area level manager and aviation power.
  • the passive band-pass filter array and diode array in the system are implemented in small package devices, all of which are passive devices and have no power consumption.
  • the digital conversion and management module, the onboard bus communication module, the monitoring data storage module and the self-powered module are all implemented with low power consumption and small package components.
  • the overall power consumption of the system is less than 30mW.
  • the structure of the system hardware integration is shown in Figure 5, which is realized by a two-layer board stack structure.
  • the top board is provided with a micro sensor array interface, a passive band pass filter array and a self-powered module, and the bottom board is placed by a diode array, a digital conversion and management module, a monitoring data storage module and an onboard bus communication module.
  • the two layers are connected by micro-miniature plugs.
  • the aeronautical rechargeable battery is mounted below the backplane and connected to the self-powered module in the top panel by jumpers.
  • the whole system hardware is packaged in an aluminum casing to achieve isolation and electromagnetic shielding from the external environment.
  • the volume after system packaging (including two interfaces) is less than 45mm ⁇ 35mm ⁇ 25mm (length ⁇ width ⁇ height).

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  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Manufacturing & Machinery (AREA)
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Abstract

一种基于二极管阵列数字化的微小型超低功耗冲击监测系统，属于飞行器结构健康监测技术领域。该监测系统由微小型传感器阵列接口、无源带通滤波阵列、二极管阵列、数字转换及管理模块、机载总线通讯模块、监测数据存储模块、自供电模块和微小型通讯接口组成。该监测系统采用二极管阵列将冲击响应信号的幅值控制在二极管的钳位电压范围内，实现第一级数字化；采用由微小型超低功耗的现场可编程逻辑门阵列组成的数字转换及管理模块实现冲击响应信号的第二级数字化。该系统能够实现对大尺度飞行器结构的在线实时不间断的冲击监测，从而提高结构的安全性和维护效率。

Description

基于二极管阵列数字化的微小型超低功耗冲击监测系统 技术领域
本发明涉及一种基于二极管阵列数字化的微小型超低功耗冲击监测系统，属于飞行器结构健康监测技术领域。
背景技术
飞行器在服役的过程中不可避免的要承受各种能量的冲击，例如飞机起飞时的碎石碰撞、飞行过程中飞鸟撞击、停飞维护时工具的掉落砸伤等，又例如航天器在进入外层空间后受到的轨道碎片等太空垃圾的撞击。近年来，随着航空工业技术的迅速发展，复合材料结构已经逐渐成为飞行器的重要承力结构，然后复合材料结构遭受冲击后容易在其内部产生表面不可见的损伤，这些损伤会随着结构的服役而逐渐扩展，给飞机的正常运行带来安全隐患。所以，对飞行器结构实施冲击监测对提高飞行器结构的安全性和维护效率非常重要。
飞行器结构的冲击是一种随机的瞬态事件，必须在冲击发生的时刻对其进行监测。所以冲击监测系统必须作为一种机载设备，被安装在飞行器上，实施在线实时不间断的冲击监测。然而，目前常规的冲击监测系统为了获取冲击响应信号实现精确的冲击定位与评估，包含由信号放大器、滤波器和数模转换器组成的模拟电路以及支持复杂监测算法的微处理器及外围器件组成的数字电路，再加之在大尺度结构大面积监测时，由于所需通道数多，导致系统整体的体积大、重量大和功耗大，并且可靠性难保证，所以很难达到机载低功耗、小体积和高可靠性的要求。
针对上述这些问题，一种小型化数字式的大规模传感器阵列冲击监测系统被提出，该系统使用高速电压比较器阵列替代常规冲击监测系统中的数模转换器，并采用可编程逻辑门阵列替代微处理器及外围器件组成的数字电路。高速电压比较器能够直接将模拟量形式的冲击响应信号转换为冲击数字序列。可编程逻辑门阵列采集数字序列并通过基于数字序列的冲击区域定位算法实现冲击事件的记录和冲击区域定位。该系统具有体积小、质量轻、能够实现在线实时冲击监测的特点，为冲击监测系统的机载化提供了一个 可行且有效的实现方案。
但上述小型化数字式的大规模传感器阵列冲击监测系统在实现冲击响应信号数字化时采用的高速电压比较器阵列是有源阵列，阵列中的每一个比较器都是用一个比较器芯片来实现的，而比较器芯片往往体积大、功耗高，在一定程度上增加了整个冲击监测系统的体积和功耗，不利于实现微小型和超低功耗。
此外，真实飞行器在飞行过程中会受到的气动噪声与发动机振动产生的噪声等干扰，而这种低频和高频振动将会干扰压电元件对冲击响应信号的采集，导致获取的数字序列无法正确地表征冲击的信息，从而降低对真实冲击判断的准确性。所以需要在冲击响应信号数字化之前要先经过信号调理将低频噪声和高频噪声信号滤除，从根本上消除低频噪声和高频噪声对冲击响应信号的干扰。上述小型化数字式的大规模传感器阵列冲击监测系统没有考虑这方面的干扰问题。
另外，冲击的发生是一个随机事件，不仅仅是在飞行的过程中需要对冲击进行监测，即使在飞机落地断电停飞或是维护时，也会有冲击事件的发生，因此，冲击监测是一个在线实时不间断的过程。此时，要求冲击监测系统能够实现自供电，从而最大可能的监测出结构遭受到的所有冲击，为及时的维护提供保障。
发明内容
本发明为克服上述小型化数字式的大规模传感器阵列冲击监测系统存在的问题，提出了一种基于二极管阵列数字化的微小型超低功耗冲击监测系统。该系统适于机载使用，具有支持传感器数目多、微小体积、超轻质量、超低功耗、可自供电、可用于组网监测的特点，能够实现对飞行器结构的在线实时不间断的冲击监测，从而提高飞行器结构的安全性和维护效率。
本发明为解决其技术问题采用如下技术方案：
一种基于二极管阵列数字化的微小型超低功耗冲击监测系统，包括微小型传感器阵列接口、无源带通滤波阵列、二极管阵列、数字转换及管理模块、机载总线通讯模块、监测数据存储模块、自供电模块和微小型通讯接口，其中微小型传感器阵列接口、无源带通滤波阵列、二极管阵列和数字转换及管理模块顺序连接，数字转换及管理模块和机载总线通讯模块双向连接，数字转换及管理模块和监测数据存储模块双向连接，机载总线通讯模块和微小型通讯接口双向连接，机载总线通讯模块、监测数据存储模块和数字 转换及管理模块分别与自供电模块连接，自供电模块和微小型通讯接口连接。
所述二极管阵列由n个二极管单元组成，其中n为大于等于1的自然数，每个二极管单元由无源瞬态抑制二极管或无源稳压二极管电路实现。
所述无源带通滤波阵列由n个带通滤波单元组成，每个带通滤波单元是由一个m阶高通电路和一个m阶低通电路组成，其中，n和m都为大于等于1的自然数。
所述m阶高通电路是由m个电容和m个电阻串联组成的无源滤波器，m个电阻的一端统一接地，所述m阶低通电路是由m个电阻和m个电电容串联组成的无源滤波器，m个电容的一端统一接地，其中，m都为大于等于1的自然数。
所述自供电模块由电源保护单元、一级调理单元、充电管理单元、航空可充电电池、电源切换单元、二级调理单元和3个线性转换单元组成，其中电源保护单元、一级调理单元、充电管理单元、航空可充电电池、电源切换单元和二级调理单元顺序连接，一级调理单元和电源切换单元顺序连接，第一线性转换单元、第二线性转换单元和第三线性转换单元分别与二级调理单元连接。
本发明有益效果如下：
(1)本发明的系统具有支持传感器数目多、微小体积、超轻质量、超低功耗、可自供电、可组网监测的特点。
(2)本发明的系统适于机载使用，能够实现对大尺度飞行器结构的在线实时不间断的冲击监测，从而提高飞行器结构的安全性和维护效率。
附图说明
图1是本发明系统的硬件架构示意图。
图2是本发明无源带通滤波阵列示意图。
图3是本发明二极管阵列示意图。
图4是本发明系统自供电模块示意图。
图5是本发明系统硬件集成结构示意图。
具体实施方式
下面结合附图对本发明创造做进一步详细说明。
本发明的系统硬件架构如图1所示。该系统由微小型传感器阵列接口、无源带通滤波阵列、二极管阵列、数字转换及管理模块、机载总线通讯模块、监测数据存储模块、自供电模块和微小型通讯接口组成。微小型传感器阵列接口、无源带通滤波阵列、二极管阵列和数字转换及管理模块顺序连接，数字转换及管理模块和机载总线通讯模块双向连接，数字转换及管理模块和监测数据存储模块双向连接，机载总线通讯模块和微小型通讯接口双向连接，机载总线通讯模块、监测数据存储模块和数字转换及管理模块分别与自供电模块连接，自供电模块和微小型通讯接口连接。
无源带通滤波阵列由n个带通滤波单元组成，如图2所示。每个带通滤波单元是由一个m阶高通电路和一个m阶低通电路组成，m阶高通电路是由m个电容和m个电阻串联组成的无源滤波器，m个电阻的一端统一接地，m阶低通电路是由m个电阻和m个电容串联组成的无源滤波器，m个电容的一端统一接地。其中，其中n＝32，m为大于等于1的自然数。无源带通滤波阵列的功能是抑制冲击响应信号的低频和高频噪声干扰，提高对真实冲击区域判别的准确性。
二极管阵列由n个二极管单元组成，如图3所示。每个二极管单元由无源瞬态抑制二极管或是稳压二极管电路来实现。二极管单元的个数n同带通滤波单元的个数一致。经过无源带通滤波阵列之后的冲击响应信号通过二极管阵列后，在保留冲击响应信号特性的前提下，将冲击响应信号的幅值控制在二极管的钳位电压范围内，确保安全的进入数字转换及管理模块。实现冲击响应信号的第一级数字化。
数字转换及管理模块是由微小型超低功耗的现场可编程逻辑门阵列及其外围电路来组成，实现冲击响应信号的第二集数字化，并对冲击响应数字信号进行处理，实现冲击区域监测，并将监测结果和采集到的数字序列存储在监测数据存储模块中。此外，数字转换及管理模块也负责控制机载总线通讯模块实现与机载区域级管理器的通讯，将存储的监测结果和采集到的数字序列发送给机载区域级管理器，并接受机载区域级管理器的控制。
该监测系统采用二极管阵列将冲击响应信号的幅值控制在二极管的钳位电压范围内，实现第一级数字化；采用由微小型超低功耗的现场可编程逻辑门阵列组成的数字转换及管理模块实现冲击响应信号的第二级数字化。
自供电模块如图4所示，由电源保护单元、一级调理单元、充电管理单元、航空可充电电池、电源切换单元、二级调理单元和3个线性转换单元组成。当航空电源开启时，自供电模块的电源切换单元接通一级调理单元，直接对其它模块供电，同时为航空可充电电池充电；当航空电源关闭时，电源切换单元接通航空可充电电池，为其它模块供电，从而实现整个系统的自供电，确保在飞机停飞时，该系统也能不间断的正常工作。
系统外部压电传感器阵列产生的冲击响应信号经过微小型传感器阵列接口输入至系统内部。机载总线通讯及航空电源的输入共用一个微小型通讯供电接口实现与外部机载区域级管理器和航空电源的连接。
系统中的无源带通滤波阵列、二极管阵列采用小封装器件实现，均为无源器件，没有功耗。数字转换及管理模块、机载总线通讯模块、监测数据存储模块和自供电模块均使用低功耗、小封装的元器件实现。系统整体功耗小于30mW。
系统硬件集成的结构如图5所示，采用两层板堆叠结构来实现。顶层板放置微小型传感器阵列接口、无源带通滤波阵列和自供电模块，底层板放置由二极管阵列、数字转换及管理模块、监测数据存储模块和机载总线通讯模块。两层板之间通过微小型排插进行连接。航空可充电电池安装在底层板的下方并与顶层板中的自供电模块通过跳线进行连接。整个系统硬件整体封装在铝质机壳内实现与外界环境的隔离和电磁屏蔽。系统封装后的体积(含两个接口)小于45mm×35mm×25mm(长×宽×高)。

Claims (5)

  1. 一种基于二极管阵列数字化的微小型超低功耗冲击监测系统，其特征在于，包括微小型传感器阵列接口、无源带通滤波阵列、二极管阵列、数字转换及管理模块、机载总线通讯模块、监测数据存储模块、自供电模块和微小型通讯接口，其中微小型传感器阵列接口、无源带通滤波阵列、二极管阵列和数字转换及管理模块顺序连接，数字转换及管理模块和机载总线通讯模块双向连接，数字转换及管理模块和监测数据存储模块双向连接，机载总线通讯模块和微小型通讯接口双向连接，机载总线通讯模块、监测数据存储模块和数字转换及管理模块分别与自供电模块连接，自供电模块和微小型通讯接口连接。
  2. 如权利要求1所述的基于二极管阵列数字化的微小型超低功耗冲击监测系统，其特征在于，所述二极管阵列由n个二极管单元组成，其中n为大于等于1的自然数，每个二极管单元由无源瞬态抑制二极管或无源稳压二极管电路实现。
  3. 如权利要求1所述的基于二极管阵列数字化的微小型超低功耗冲击监测系统，其特征在于，所述无源带通滤波阵列由n个带通滤波单元组成，每个带通滤波单元是由一个m阶高通电路和一个m阶低通电路组成，其中，n和m都为大于等于1的自然数。
  4. 如权利要求3所述的基于二极管阵列数字化的微小型超低功耗冲击监测系统，其特征在于，所述m阶高通电路是由m个电容和m个电阻串联组成的无源滤波器，m个电阻的一端统一接地，所述m阶低通电路是由m个电阻和m个电电容串联组成的无源滤波器，m个电容的一端统一接地，其中，m都为大于等于1的自然数。
  5. 如权利要求1所述的基于二极管阵列数字化的微小型超低功耗冲击监测系统，其特征在于，所述自供电模块由电源保护单元、一级调理单元、充电管理单元、航空可充电电池、电源切换单元、二级调理单元和3个线性转换单元组成，其中电源保护单元、一级调理单元、充电管理单元、航空可充电电池、电源切换单元和二级调理单元顺序连接，一级调理单元和电源切换单元顺序连接，第一线性转换单元、第二线性转换单元和第三线性转换单元分别与二级调理单元连接。
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