阅读说明：本技术 一种气流致声发电机弹载能量采集检测装置 (Detection device for acquiring missile-borne energy of airflow sound-generating motor ) 是由 陈荷娟 李京昊 李智鹏 张建铭 沈嫣秋 于 2021-08-24 设计创作，主要内容包括：一种气流致声发电机弹载能量采集检测装置,本发明属于引信电源技术领域。利用弹丸发射后迎面气流作用于弹体,气流入气流致声发电机的入流调制结构,在空腔内气流诱发生成边棱音,产生一个稳定的激励声波,该声波通过共振腔结构传播到达底部,压电换能元件感受到声波后引起谐振并将振动能转换成电能,通过能量采集电路将压电换能元件输出的交流电压转换成直流电压并加在负载两端,数字信号采集与存储电路中的A/D转换电路将负载两端的直流电压信号转换为数字信号,存储电路的单片机采集该数字信号并存储在了闪存芯片中,从而实现弹载发电能量的实时采集与存储功能,由此实现气流致声发电机发电能量利用和控制。(The invention discloses an airflow sound-generating motor missile-borne energy acquisition and detection device, and belongs to the technical field of fuse power supplies. The projectile is used for launching the head-on airflow to act on a projectile body, the airflow enters an inflow modulation structure of an airflow sound-generating motor, the airflow in a cavity induces and generates edge tones to generate stable excitation sound waves, the sound waves are transmitted to the bottom through a resonant cavity structure, a piezoelectric transduction element induces resonance after sensing the sound waves and converts vibration energy into electric energy, alternating current voltage output by the piezoelectric transduction element is converted into direct current voltage through an energy acquisition circuit and is applied to two ends of a load, an A/D conversion circuit in a digital signal acquisition and storage circuit converts direct current voltage signals at two ends of the load into digital signals, a single chip of the storage circuit acquires the digital signals and stores the digital signals in a flash memory chip, and therefore the real-time acquisition and storage functions of missile-borne power generation energy are achieved, and utilization and control of power generation energy of the airflow sound-generating motor are achieved.)

1. The utility model provides an air current sound-generating motor missile-borne energy acquisition detection device which characterized in that: the device comprises an airflow sound-generating motor and a missile-borne energy acquisition circuit with an energy acquisition circuit and a digital signal acquisition and storage circuit; the airflow sound-generating motor consists of an inflow modulation structure and a resonant cavity structure which are arranged at the head part of the fuse, and the inflow modulation structure and the resonant cavity structure are connected into a whole through threaded connection between a shell with steps and a metal cover, wherein the inflow modulation structure is positioned at the upper end of the shell and faces an inflow inlet; the resonant cavity structure is positioned at the lower end of the shell, a cavity is reserved between the resonant cavity structure and the inflow modulation structure, and the distance between the resonant cavity structure and the inflow modulation structure is kept; the metal cover compresses a piezoelectric transduction element of an energy acquisition circuit in the missile-borne energy acquisition circuit at the bottom of the resonant cavity structure, and two output ends of the piezoelectric transduction element are connected with two poles of the energy acquisition circuit; the output ends of the alternating current-direct current conversion circuit of the energy acquisition circuit are connected with the two ends of the load; the load is connected with the A/D conversion circuit of the digital signal acquisition and storage circuit, and then the load is connected with the storage circuit of the digital signal acquisition and storage circuit and connected with the computer PC to read data and display a signal curve.

2. The airborne energy collection and detection device of claim 1, characterized in that: the air inlet end of the airflow sound-generating motor is connected with the shell through threads, the inflow modulation structure is tightly pressed on the shell, and a narrow side gap is formed between the inflow modulation structure and the shell. The metal cover and the shell are also in threaded connection, and the resonant cavity structure and the piezoelectric transduction element are sequentially and tightly pressed on the shell; the inflow modulation structure, the resonant cavity structure and the fuse are coaxial, sharp edges in the resonant cavity structure are opposite to side gaps of the inflow modulation structure, a cavity is reserved between the inflow modulation structure and the resonant cavity structure, external head-on airflow passes through the inflow modulation structure, sound waves are induced in the cavity, and the sound waves act on the piezoelectric transduction element through the resonant cavity structure; the shell is evenly provided with a plurality of inclined exhaust ports in the circumferential direction of the cavity.

3. The airborne energy collection and detection device of claim 1, characterized in that: the shell is preferably provided with eight inclined exhaust ports at the periphery of the cavity position.

4. The airborne energy collection and detection device of claim 1, characterized in that: the missile-borne energy acquisition circuit consists of an energy acquisition circuit and a digital signal acquisition and storage circuit, wherein one surface of a piezoelectric energy conversion element in the energy acquisition circuit faces the bottom of the resonant cavity structure and directly senses sound waves induced by the head-on airflow.

5. The airborne energy collection and detection device of claim 1, characterized in that: the energy acquisition circuit consists of a piezoelectric transduction element and an alternating current-direct current conversion circuit, and the alternating current-direct current conversion circuit is directly connected with a load.

6. The airborne energy collection and detection device of claim 1, characterized in that: the piezoelectric transduction element is pressed in a cavity with a step end outside the bottom of the resonant cavity structure by a metal cover, the edge of the piezoelectric transduction element is a copper sheet and is in direct contact with the shell to form a rigid wall surface, the center of the piezoelectric transduction element is made of ceramic, a lead is welded at the center and is directly connected with one end of the alternating current-direct current conversion circuit, a lead is also welded on the copper sheet, a small hole with the diameter of 6mm is formed in the metal cover, and the lead is led out through the small hole to be connected with the energy acquisition circuit.

7. The airborne energy collection and detection device of claim 1, characterized in that: the AC-DC conversion circuit consists of a GaN rectifier bridge, a filter capacitor and a voltage stabilizing diode, wherein the GaN rectifier bridge is a full-bridge rectifier circuit consisting of four GaN diodes; one input end of the GaN rectifier bridge is connected with a lead led out from the center of the piezoelectric transduction element, the other input end of the GaN rectifier bridge is welded to a lead welded on a copper sheet in a small hole of the metal cover, and the output end of the GaN rectifier bridge is directly connected with two ends of the filter capacitor; the output end of the filter capacitor is connected with two ends of the voltage stabilizing diode; the voltage stabilizing diode is directly connected with a load.

8. The airborne energy collection and detection device of claim 1, characterized in that: the load is a series resistor of a large resistor and a small resistor, two ends of the small resistor are connected with the A/D conversion circuit in parallel to form a voltage divider, the large resistor =8.2k omega, the small resistor =1k omega, when the voltage of the voltage stabilizing diode is 30V, the voltage of two ends of the small resistor is ensured to be less than 3.3V, and the digital signal acquisition and storage circuit can be protected from being burnt out.

9. The airborne energy collection and detection device of claim 1, characterized in that: the digital signal acquisition and storage circuit comprises an A/D conversion circuit and a storage circuit, wherein the input end of the A/D conversion circuit is respectively connected with two ends of a small resistor, the output end of the A/D conversion circuit is connected with the storage circuit in parallel, and the output end of the storage circuit can be directly connected with a computer when detection data need to be read.

10. The airborne energy collection and detection device of claim 1, characterized in that: the A/D conversion circuit is an analog/digital converter, and the storage circuit is composed of an 8051 singlechip and a FLASH FLASH memory chip.

Technical Field

The invention belongs to the technical field of fuse power supplies, relates to a dynamic power generation energy detection technology, and particularly relates to a bullet-loaded energy acquisition and detection device for an airflow sound-generating motor, which is used as the output power of a special power supply for fuses, can adapt to the projectile launching and flying environment and acquires and detects the power generation energy of the airflow sound-generating motor for fuses.

Background

The power supply for the fuse generally uses a disposable chemical battery or a physical power supply, and is different from a civil battery and a power supply in that the power supply does not generate and supply power at ordinary times, and only is excited to generate and supply power in the normal flying process of the projectile in the launching environment. An airflow sound-generating motor is a novel power supply in the field of current fuses, and meets the use environment of the fuses. The generator is excited by unstable head-on airflow outside the projectile in the projectile flight, and has the characteristic of more stable output power and voltage signals. In order to meet the use requirement of the fuze, a detection means for detecting the generated power and the stored energy in real time and rapidly is needed in engineering development and product production.

The exciting airflow of the airflow sound-generating motor induces a sound wave signal after flowing through the pipeline, which can cause structural vibration, and the head-on airflow encountered in the flying process of the projectile is converted into electric energy by utilizing the piezoelectric transduction principle. Since the output of such a generator is an ac voltage signal and a dc power supply is required for a circuit to be applied in practice, ac/dc conversion is required. The typical fuze power ac-dc conversion circuit is a simple diode half-wave or full-wave rectifier circuit. The airflow sound-generating motor outputs micro power and energy which fluctuate along with the head-on airflow, and a common diode type alternating current-direct current conversion circuit cannot meet the requirement of maximum efficiency conversion, so that a novel synchronous charge acquisition and storage circuit is designed for the airflow sound-generating motor.

The common AC/DC conversion circuit adopts a standard energy acquisition circuit and consists of a full-bridge rectification circuit and a filter capacitor, wherein the full-bridge rectification circuit completes AC-DC conversion, and the filter capacitor completes charge storage. The full-bridge rectifier bridge converts alternating current output by the piezoelectric element into direct current with larger ripple, and the filter capacitor with larger parallel connection ensures output voltage with smaller ripple. The standard energy acquisition circuit has a simple topological structure, continuous output voltage and low energy acquisition efficiency. A method for acquiring and storing analog quantity by using an FPGA is introduced in China, after power is supplied, an acquisition coding module controls to code and write digital signals sent back by an AD acquisition circuit into an FIFO module, the digital signals are circulated continuously, and after a takeoff mark is received, a FLASH read-write control module reads data from the FIFO module and stores the data into a FLASH chip. The other method is that after the flight process is finished, an external control instruction is received, the FLASH read-write control module reads the data in the FLASH chip and writes the data into FIFO, and then the data of the FIFO module is read through the communication interface and sent to the outside. The method of utilizing FPGA control is complex to operate. The projectile space is limited, the modules in the methods occupy more volume and cannot be adopted, and the FPGA has high energy consumption and is not suitable for being used in fuzes.

In the technical field of fuze power supplies, no device for collecting real-time energy specially used for fuze work in pellet flight exists. The airflow sound-generating motor is arranged on the bullet for use, the randomness of the head-on airflow in the flight is very high, and the flying speed of the bullet is high, which causes the difficulty of the design of the rapid energy acquisition and storage circuit. Therefore, a device for rapidly detecting and storing the missile-borne energy is provided, which is necessary for the application of the airflow sound-generating motor to a fuse, can also provide a technology for design and commercialization, and has important application significance.

Disclosure of Invention

The invention aims to overcome the defect of power supply in the existing fuze system and provides a detection device for collecting missile-borne energy of an airflow sound-generating motor.

The invention is realized by the following technical scheme: an airborne energy acquisition and detection device of an airflow sound-generating motor comprises the airflow sound-generating motor and an airborne energy acquisition circuit with an energy acquisition circuit and a digital signal acquisition and storage circuit; the airflow sound-generating motor consists of an inflow modulation structure and a resonant cavity structure which are arranged at the head part of the fuse, and the inflow modulation structure and the resonant cavity structure are connected into a whole through threaded connection between a shell with steps and a metal cover, wherein the inflow modulation structure is positioned at the upper end of the shell and faces an inflow inlet; the resonant cavity structure is positioned at the lower end of the shell, a cavity is reserved between the resonant cavity structure and the inflow modulation structure, and the distance between the resonant cavity structure and the inflow modulation structure is kept; the metal cover compresses a piezoelectric transduction element of an energy acquisition circuit in the missile-borne energy acquisition circuit at the bottom of the resonant cavity structure, and two output ends of the piezoelectric transduction element are connected with two poles of the energy acquisition circuit; the output ends of the alternating current-direct current conversion circuit of the energy acquisition circuit are connected with the two ends of the load; the load is connected with the A/D conversion circuit of the digital signal acquisition and storage circuit, and then the load is connected with the storage circuit of the digital signal acquisition and storage circuit and connected with the computer PC to read data and display a signal curve.

The air inlet end of the airflow sound-generating motor is connected with the shell through threads, the inflow modulation structure is tightly pressed on the shell, and a narrow side gap is formed between the inflow modulation structure and the shell. The metal cover and the shell are also in threaded connection, and the resonant cavity structure and the piezoelectric transduction element are sequentially and tightly pressed on the shell; the inflow modulation structure, the resonant cavity structure and the fuse are coaxial, sharp edges in the resonant cavity structure are opposite to side gaps of the inflow modulation structure, a cavity is reserved between the inflow modulation structure and the resonant cavity structure, external head-on airflow passes through the inflow modulation structure, sound waves are induced in the cavity, and the sound waves act on the piezoelectric transduction element through the resonant cavity structure; the shell is evenly provided with a plurality of inclined exhaust ports in the circumferential direction of the cavity.

The shell is preferably provided with eight inclined exhaust ports at the periphery of the cavity position.

The missile-borne energy acquisition circuit consists of an energy acquisition circuit and a digital signal acquisition and storage circuit, wherein one surface of a piezoelectric energy conversion element in the energy acquisition circuit faces the bottom of the resonant cavity structure and directly senses sound waves induced by the head-on airflow.

The energy acquisition circuit consists of a piezoelectric transduction element and an alternating current-direct current conversion circuit, and the alternating current-direct current conversion circuit is directly connected with a load.

The piezoelectric transduction element is pressed in a cavity with a step end outside the bottom of the resonant cavity structure by a metal cover, the edge of the piezoelectric transduction element is a copper sheet and is in direct contact with the shell to form a rigid wall surface, the center of the piezoelectric transduction element is made of ceramic, a lead is welded at the center and is directly connected with one end of the alternating current-direct current conversion circuit, a lead is also welded on the copper sheet, a small hole with the diameter of 6mm is formed in the metal cover, and the lead is led out through the small hole to be connected with the energy acquisition circuit.

The AC-DC conversion circuit consists of a GaN rectifier bridge, a filter capacitor and a voltage stabilizing diode, wherein the GaN rectifier bridge is a full-bridge rectifier circuit consisting of four GaN diodes; one input end of the GaN rectifier bridge is connected with a lead led out from the center of the piezoelectric transduction element, the other input end of the GaN rectifier bridge is welded to a lead welded on a copper sheet in a small hole of the metal cover, and the output end of the GaN rectifier bridge is directly connected with two ends of the filter capacitor; the output end of the filter capacitor is connected with two ends of the voltage stabilizing diode; the voltage stabilizing diode is directly connected with a load.

The load is a series resistor of a large resistor and a small resistor, two ends of the small resistor are connected with the A/D conversion circuit in parallel to form a voltage divider, the large resistor =8.2k omega, the small resistor =1k omega, when the voltage of the voltage stabilizing diode is 30V, the voltage of two ends of the small resistor is ensured to be less than 3.3V, and the digital signal acquisition and storage circuit can be protected from being burnt out.

The digital signal acquisition and storage circuit comprises an A/D conversion circuit and a storage circuit, wherein the input end of the A/D conversion circuit is respectively connected with two ends of a small resistor, the output end of the A/D conversion circuit is connected with the storage circuit in parallel, and the output end of the storage circuit can be directly connected with a computer when detection data need to be read.

The A/D conversion circuit is an analog/digital converter.

The storage circuit is composed of an 8051 singlechip and a FLASH FLASH memory chip.

After the projectile is launched, the projectile in the air flies at a reduced acceleration, head-on air flow acts on the projectile body, at the moment, the air flow enters an inflow modulation structure of an air flow sound generation motor through an air inlet channel of a fuse positioned at the head of the projectile body, edge sound is induced and generated in a cavity through the air flow, stable excitation sound waves are generated and are propagated to the bottom through a resonant cavity structure, a piezoelectric transduction element senses the sound waves to cause resonance and convert vibration energy into electric energy (electric charge), alternating current voltage output by the piezoelectric transduction element is converted into direct current voltage through an energy acquisition circuit and is applied to two ends of a load, a direct current voltage signal at two ends of the load is converted into a digital signal through an A/D conversion circuit in a digital signal acquisition and storage circuit, a singlechip of the storage circuit acquires the digital signal and stores the digital signal in a flash memory chip, after analog test or shooting recovery in a laboratory, the data of the storage circuit can be read out or drawn by a computer PC (personal computer) or used by other devices in a fuse, so that the real-time acquisition and storage functions of missile-borne power generation energy are realized, and the utilization and control of the power generation energy of the airflow sound-generating motor are realized.

Description of the drawings:

FIG. 1 is a schematic diagram of energy collection missile-borne detection of an airflow sound-generating motor;

FIG. 2 is a schematic diagram of energy collection missile-borne detection of an airflow sound-generating motor;

FIG. 3 is a schematic structural diagram of an airflow sound-generating motor;

fig. 4 is a schematic diagram of a missile-borne energy harvesting circuit.

In the figure, 1, an airflow sound-generating motor; 2. a missile-borne energy acquisition circuit; y, a fuse at the head of the projectile; B. a fuse inlet channel; a. the₁An inflow modulation structure; a. the₂A resonant cavity structure; a. the₃A piezoelectric transduction element; a. the₄The alternating current-direct current conversion circuit; a. the₅An A/D conversion circuit; a. the₆A memory circuit; z, load; e. A cavity; 11. a housing; 12. a metal cover; 13. an exhaust port; 21. an energy harvesting circuit; 22. a digital signal acquisition and storage circuit; d1, D2, D3, D4, GaN diode; c1, a filter capacitor; ZD, zener diode; r1, large resistance; r2, small resistance; PC, computer.

The specific implementation mode is as follows:

referring to the attached drawings 1-4, the missile-borne energy acquisition and detection device for the airflow sound-generating motor comprises an airflow sound-generating motor 1 and a missile-borne energy acquisition circuit 2 with an energy acquisition circuit 21 and a digital signal acquisition and storage circuit 22; the airflow sound-generating motor 1 is composed of an inflow modulation structure A arranged at the head part of a fuse₁And a resonant cavity structure A₂Formed by connecting a stepped housing 11 and a metal cover 12 into a whole by a screw connection therebetween, wherein the inflow modulation structure A₁At the upper end of the housing 11, facing the inflow inlet; resonant cavity structure A₂At the lower end of the housing 11, with an inflow modulation structure A₁A cavity is left between the two parts to keep the distance of the cavityE; the metal cover 12 will load the piezoelectric transducer element A of the energy collection circuit 21 in the energy collection circuit 2₃Is tightly pressed on the resonant cavity structure A₂Bottom, piezoelectric transducer element A₃The two output ends are connected with the two poles of the energy acquisition circuit 21; AC-DC conversion circuit A of energy acquisition circuit 21₄The two output ends are connected with the two ends of the load Z; a/D conversion circuit a of load Z and digital signal acquisition and storage circuit 22₅A storage circuit A connected with and then accessed into the digital signal acquisition and storage circuit 22₆And the computer PC reads data and displays a signal curve.

The air inlet end of the airflow sound-generating motor 1 is connected with the shell 11 through threads, and an inflow modulation structure A is formed₁Pressed against the housing 11, and flowing into the flow-modulating structure A₁Forming a narrow side gap with the housing 11. The metal cover 12 and the housing 11 are also connected by screw threads to form a resonant cavity structure A₂And a piezoelectric transducing element A₃Which in turn press against the housing 11. Inflow modulation structure A₁The resonant cavity structure A₂Coaxial with the fuse, a resonant cavity structure A₂The inner sharp edge faces the inflow modulation structure A₁With a cavity E left between them, the external oncoming airflow passing through the inflow modulation structure a₁Inducing acoustic waves in the cavity E through the resonant cavity structure A₂Applying the acoustic wave to the piezoelectric transducer element A₃. The housing 11 is provided with a plurality of inclined exhaust ports 13 uniformly along the circumference at the position of the cavity E.

The casing 11 preferably has eight circumferentially inclined exhaust ports 13 at the location of the cavity E.

The missile-borne energy acquisition circuit 2 consists of an energy acquisition circuit 21 and a digital signal acquisition and storage circuit 22, wherein a piezoelectric transducer element A in the energy acquisition circuit 21₃One surface of the first electrode faces the resonant cavity structure A₂The bottom, directly sensitive to the acoustic waves induced by the oncoming airflow.

The energy acquisition circuit 21 is composed of a piezoelectric transduction element A₃And AC-DC conversion circuit A₄Two parts, AC-DC conversion circuit A₄Is directly connected to the load Z.

The piezoelectric transduction element A₃Is pressed in the resonant cavity structure A by the metal cover 12₂In the cavity with the step end outside the bottom, the copper sheet is arranged at the edge and is in direct contact with the shell 11 to form a rigid wall surface, the ceramic is arranged at the center, and a lead is welded at the center and is directly connected with the AC-DC conversion circuit A₄One end of the copper sheet is connected, a lead is also welded on the copper sheet, a small hole with the diameter of 6mm is arranged on the metal cover 12, and the lead is led out through the small hole and connected with the energy acquisition circuit 21.

The AC-DC conversion circuit A₄The GaN-based LED constant current source comprises a GaN rectifier bridge, a filter capacitor C1 and a voltage stabilizing diode ZD, wherein the GaN rectifier bridge is a full-bridge rectifier circuit formed by four GaN diodes D1, D2, D3 and D4; one input end of the GaN rectifier bridge is connected with the piezoelectric transduction element A₃The other input end of the lead wire led out from the center is welded to the lead wire welded on the copper sheet in the small hole of the metal cover 12, and the output end of the lead wire is directly connected with the two ends of the filter capacitor C1; the output end of the filter capacitor C1 is connected with two ends of the voltage stabilizing diode ZD; the zener diode ZD is directly connected to the load Z.

The load Z is a series resistor of a large resistor R1 and a small resistor R2, and two ends of the small resistor R2 are connected with the A/D conversion circuit A in parallel₅The voltage divider is formed, the large resistor R1=8.2k Ω, the small resistor R2=1k Ω, and when the voltage of the zener diode ZD is 30V, the voltage at two ends of the small resistor R2 is ensured to be less than 3.3V, so that the digital signal acquisition and storage circuit 22 can be protected from being burnt out.

The digital signal acquisition and storage circuit 22 comprises an A/D conversion circuit A₅And a memory circuit A₆Two-part, A/D converter circuit A₅The input ends of the two resistors are respectively connected with the two ends of a small resistor R2, and the output ends of the two resistors are connected with a storage circuit A in parallel₆The memory circuit A can be used when the read detection data is needed₆The output is directly connected to the computer PC.

The A/D conversion circuit A₅Is an analog/digital converter.

The memory circuit A₆Is composed of an 8051 single chip microcomputer and a FLASH FLASH memory chip.

After the projectile is launched, the projectile flies at a reduced acceleration in the air, the head-on airflow acts on the projectile, and the airflow passes through an air inlet channel of a fuse Y positioned at the head of the projectileB entering the inflow modulation structure A of the airflow sound-generating motor 1₁The air flow in the cavity E induces the generation of edge tones, producing a stable acoustic excitation wave which passes through the resonant cavity structure A₂Propagating to the bottom, piezoelectric transducing element A₃The piezoelectric transduction element A is induced to resonate and converts vibration energy into electric energy (electric charge) by sensing sound waves, and is connected with an energy acquisition circuit 21₃The output AC voltage passes through an AC-DC conversion circuit A₄An A/D conversion circuit A in the digital signal acquisition and storage circuit 22 for converting the voltage into DC voltage and applying the DC voltage to both ends of the load Z₅Converting DC voltage signals at two ends of load Z into digital signals, and storing circuit A₆The single chip microcomputer collects the digital signal and stores the digital signal in a FLASH FLASH memory chip, and after a laboratory simulation test or a shooting is recovered, the storage circuit A can be used₆The data of (A) can be read out by a computer PC and plotted, or the memory circuit A can be used₆The data of the data are utilized by other devices in the fuse, so that the real-time acquisition and storage functions of missile-borne power generation energy are realized, and the utilization and control of the power generation energy of the airflow sound-generating motor are realized.

The above examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.