CN113602536B - Dynamic stiffness on-orbit monitoring device and method for space inflatable expandable support structure - Google Patents
Dynamic stiffness on-orbit monitoring device and method for space inflatable expandable support structure Download PDFInfo
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Abstract
The invention discloses a dynamic stiffness on-orbit monitoring device and method of a space inflatable expandable support structure, wherein the device comprises a top cover, a circuit board and a box body; the circuit board is arranged in the box body; the top cover is arranged on the top surface of the box body to seal the box body; the circuit board comprises a signal generation module, a signal acquisition module, a microprocessor module, a serial port communication module, a data storage module and a power management module; the microprocessor module controls the signal sending module to generate a sine sweep frequency signal with a designated frequency and enables the signal acquisition module to acquire data; after the signal acquisition module is used for acquiring, the microprocessor module respectively performs short-time Fourier transform on the acquired excitation signal and response signal, obtains dynamic stiffness data of the inflatable expandable support structure by calculating the ratio of the excitation signal to the response signal, and then transmits the dynamic stiffness data to the SD card for storage. The device has the characteristics of miniaturization, modularization and low power consumption, saves the load space of the spacecraft and saves the energy.
Description
Technical Field
The invention belongs to the technical field of aerospace, and particularly relates to an on-orbit monitoring device and method for dynamic stiffness.
Background
The space inflatable expandable structure has the remarkable advantages of small folding volume, light weight, easiness in expansion, easiness in storage, low cost and the like, and has a wide application prospect in aerospace engineering. The space-inflatable deployable structure is generally composed of a membrane and a support structure, wherein the support structure mainly comprises an inflatable deployable support bar and a support ring. In a space-based large-scale inflatable deployment antenna system, the inflatable deployment support rods and support rings are used for deployment and maintenance of the reflective surfaces in the antenna system; in solar sails, inflatable deployable support struts are used to deploy and support the sail face. The inflatable expandable support structure mainly realizes expansion of the space inflatable structure in an inflatable mode, provides power for structural expansion, and plays a role in keeping the appearance of the structure by keeping inflation pressure to form certain rigidity. After the inflatable expandable support structure is expanded, the dynamic stiffness characteristic of the inflatable expandable support structure on the track has important influences on the vibration characteristic of the whole inflatable structure, the attitude control of a spacecraft platform and the like, and the dynamic stiffness characteristic of the inflatable expandable support structure is measured in situ on the track and monitored in real time, so that the inflatable expandable support structure has very important engineering value.
At present, some research has been focused on testing the dynamic stiffness of a space-inflated expandable support structure at the ground. The Slade is excited by an electromagnetic vibrator, and a laser oscillator is used for collecting signals to obtain dynamic stiffness characteristics of the inflatable structure (Slade K N. Dynamic characterization of thin-film inflatable structures [ M ]. Durham: duke University, 2000.). Thomas excites the inflatable rod by using an electromagnetic vibrator and a piezoelectric sheet sensor, and acquires vibration signals by using an acceleration sensor and a laser vibration meter respectively to obtain dynamic stiffness characteristics of the inflatable structure (Single T G.Experimental vibration analysis of inflatable beams for an AFIT space shuttle experiment [ R ]. Ohio: air University, 2002.). Yu Jianxin and the like dynamically test the structure of the inflatable ring on the ground by a force hammer impact method, select a single built-in circuit piezoelectric sheet sensor to measure response, collect data by a commercial dynamic data analysis instrument, and extract modal parameters to obtain a frequency response function of internal and external vibration of the inflatable ring surface of the film (Yu Jianxin, wei Jianzheng, tan Huifeng. Test study [ J ] on dynamic characteristics of the inflatable ring of the film, vibration and impact, 2013,32 (7): 11-11.). However, it should be noted that these studies have all been conducted on the ground using commercially available structural dynamics testing equipment of relatively high volume and power consumption to perform dynamic stiffness testing of inflatable expandable support structures. Due to the limitation of volume and power consumption and the complexity of the system, the equipment and the method cannot be used for testing the space on-orbit state, and do not have continuous real-time dynamic stiffness monitoring capability.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a dynamic stiffness on-orbit monitoring device and method of a space inflatable expandable support structure, wherein the device comprises a top cover, a circuit board and a box body; the circuit board is arranged in the box body; the top cover is arranged on the top surface of the box body to seal the box body; the circuit board comprises a signal generation module, a signal acquisition module, a microprocessor module, a serial port communication module, a data storage module and a power management module; the microprocessor module controls the signal sending module to generate a sine sweep frequency signal with a designated frequency and enables the signal acquisition module to acquire data; after the signal acquisition module is used for acquiring, the microprocessor module respectively performs short-time Fourier transform on the acquired excitation signal and response signal, obtains dynamic stiffness data of the inflatable expandable support structure by calculating the ratio of the excitation signal to the response signal, and then transmits the dynamic stiffness data to the SD card for storage. The device has the characteristics of miniaturization, modularization and low power consumption, saves the load space of the spacecraft and saves the energy.
The technical scheme adopted for solving the technical problems is as follows:
an on-orbit monitoring device for dynamic stiffness of a space inflatable expandable support structure comprises a top cover, a circuit board, a micro rectangular connector and a box body; the circuit board is arranged in the box body; the top cover is arranged on the top surface of the box body to seal the box body; the bottom surface of the box body is provided with a plurality of bolt holes for installing the dynamic stiffness on-orbit monitoring device on the aircraft wall plate through bolts; the micro rectangular connector is arranged on the inner side wall of the box body, the inner pin end of the micro rectangular connector is electrically connected with the circuit board, and the interface end of the micro rectangular connector can be electrically connected with the inflatable expandable support structure;
the circuit board comprises a signal generation module, a signal acquisition module, a microprocessor module, a serial port communication module, a data storage module and a power management module;
the signal generation module generates a sine sweep frequency signal, and outputs an excitation signal to the inflatable expandable support structure through the excitation output channel after amplification, so that the inflatable expandable support structure vibrates; the signal acquisition module synchronously acquires an excitation signal output by the signal generation module and a response signal generated by vibration of the inflatable expandable support structure; the microprocessor module is used for controlling each module of the dynamic stiffness on-orbit monitoring device and calculating dynamic stiffness data; the serial port communication module is used for converting serial port into USB, and realizing command transmission and data transmission between the satellite-borne computer and the dynamic stiffness on-orbit monitoring device by connecting USB wires; the data storage module is used for storing dynamic stiffness data; the power management module is used for supplying power to other modules of the dynamic stiffness on-orbit monitoring device.
Further, the signal generation module comprises a signal generation circuit, a channel selection circuit and a program-controlled amplifying circuit; the signal generating circuit adopts an AD9834 DDS chip, and can output 2 paths of sine sweep frequency signals with the frequency of 100KHz at the same time; the channel selection circuit consists of two BL1551 single-pole double-throw analog switch chips, and the microprocessor module realizes the selection of an excitation output channel by enabling an EN pin of the BL1551 chip; the program-controlled amplifying circuit amplifies the peak value of the excitation signal to 24V at maximum.
Further, the signal acquisition module realizes synchronous acquisition of 6 paths of response signals and 2 paths of excitation signals at a sampling rate of 200KHz, and the acquired signals are read by the microprocessor module through SPI serial communication.
Further, the microprocessor module adopts an STM32F103ZFT6 chip as a processor chip.
Further, the serial port communication module adopts a CH340G chip to realize serial port to USB conversion, and realizes command transmission and data transmission between the satellite-borne computer and the dynamic stiffness on-orbit monitoring device by connecting USB wires, wherein the data transmission rate is 2Mbps at the highest.
Further, the data storage module adopts an SD card as storage equipment and supports SDIO protocol for data communication.
Further, the power management module is responsible for supplying power to other modules of the dynamic stiffness on-orbit monitoring device, the power management module inputs 5V voltage through USB, and after the voltage is converted through an AMS117-3.3 power chip and an MAX743 power chip, the voltages of +3.3V and +12V are obtained, and the provided voltages are +5V, +3.3V and +12V.
Further, the dynamic stiffness on-track monitoring device can simultaneously monitor the dynamic stiffness of the 2-path inflatable expandable support structure on-track, each path comprises an excitation and sensor system formed by 1 piezoelectric patch driver and 2 piezoelectric patch sensors which are arranged on an inflatable film of the inflatable expandable support structure, wherein the piezoelectric patch driver is driven by the dynamic stiffness on-track monitoring device to apply a sinusoidal sweep signal to excite the inflatable expandable support structure, and the piezoelectric patch sensors are used for sensing vibration of the inflatable expandable support structure and generating charge signals.
An on-orbit monitoring method for dynamic stiffness of a space-inflated expandable support structure, comprising the following steps:
step1: after the inflatable expandable support structure is expanded, the spaceborne computer sends a measurement starting instruction to the dynamic stiffness on-orbit monitoring device;
step2: the microprocessor module initializes the signal generation module, the signal acquisition module and the data storage module every other appointed period, starts 2 excitation channels, and starts a timer TIM3 and a timer TIM4 in the microprocessor module;
step3: the microprocessor module transmits a frequency control word corresponding to the designated frequency to the signal transmission module in an interrupt function generated by the timer TIM3 in an SPI communication mode, so that the signal transmission module generates a sinusoidal sweep frequency signal of the designated frequency according to the frequency control word, and the signal acquisition module is enabled to acquire data in the interrupt function generated by the timer TIM4;
step4: after the signal acquisition module is used for acquiring the excitation signals and the response signals, the microprocessor module respectively performs short-time Fourier transform, obtains dynamic stiffness data of the inflatable expandable support structure by calculating the ratio of the excitation signals to the response signals, and then transmits the dynamic stiffness data to the SD card for storage;
step5: after the data storage is completed, the microprocessor module enables the signal generating module, the signal collecting module and the data storage module to enter a sleep mode, and the next measurement is waited to start.
An on-orbit monitoring data transmission method for dynamic stiffness of a space inflatable expandable support structure comprises the following steps:
step1: the satellite-borne computer sends a data transmission instruction to the dynamic stiffness on-orbit monitoring device;
step2: the microprocessor module initializes the data storage module and the serial port communication module;
step3: the microprocessor module reads data in the SD card and sends the data to the satellite-borne computer through the USB;
step4: after the data transmission task is finished, enabling the data storage module and the serial port communication module to enter a sleep mode by the microprocessor module;
step5: and after receiving the dynamic stiffness data, the satellite-borne computer transmits the data to the ground.
The beneficial effects of the invention are as follows:
1. the device only occupies a small spacecraft loading space. The circuit board in the device adopts a modularized design, and the layout among the modules is orderly and compact, so that the load space of the spacecraft is greatly saved.
2. The power consumption of the device is only 1.25W when the device performs the measurement task on the track, so that the energy is greatly saved.
3. The device has the data storage function, does not occupy the storage space of the spaceborne computer, and only needs to transmit dynamic stiffness data to the spaceborne computer according to the data transmission instruction sent by the spaceborne computer.
4. The device has the characteristics of miniaturization, modularization and low power consumption, is easy to integrate with a spacecraft, and can be used for in-situ measurement on the track and real-time monitoring of the dynamic stiffness characteristic of the inflatable expandable support structure.
Drawings
Fig. 1 is a general construction diagram of the device of the present invention.
Fig. 2 is a schematic view of the apparatus of the present invention.
Fig. 3 is a circuit board diagram of the device of the present invention.
FIG. 4 is a J30J-15ZK micro rectangular connector of the device of the present invention.
FIG. 5 is a schematic view of the arrangement of piezoelectric patches in a space-inflatable deployable support bar structure in an apparatus of the invention.
Figure 6 is a graph showing the dynamic stiffness characteristics of a spatial inflatable deployable support bar structure in an apparatus of the invention.
The device comprises a 1-top cover, a 2-circuit board, a 3-box body, 4-M3 bolt holes, a 5-SMA interface, a 6-J30J-15ZK micro rectangular connector interface, a 7-USB interface, an 8-4X 1 reverse bend pin header interface, a 9-SD card holder, a 10-USB female holder, an 11-SMA connector, a 12-4X 1 reverse bend pin header, a 13-6X 2 straight pin header, a 14-J30J-15ZK micro rectangular connector inner pin, a 15-J30J-15ZK micro rectangular connector, a 16-piezoelectric driver, a 17-piezoelectric sensor, an 18-top holder, a 19-base and a 20-polyimide film.
Detailed Description
The invention will be further described with reference to the drawings and examples.
The invention provides a miniaturized, integrated and low-power-consumption dynamic stiffness on-orbit monitoring device applied to a space inflatable expandable support structure, and aims to realize on-orbit in-situ measurement and real-time monitoring of dynamic stiffness characteristics of the space inflatable expandable support structure in a service process, so as to provide guarantee for safe operation of a spacecraft.
An on-orbit monitoring device for dynamic stiffness of a space inflatable expandable support structure comprises a top cover, a circuit board, a micro rectangular connector and a box body; the circuit board is arranged in the box body; the top cover is arranged on the top surface of the box body to seal the box body; the bottom surface of the box body is provided with a plurality of bolt holes for installing the dynamic stiffness on-orbit monitoring device on the aircraft wall plate through bolts; the micro rectangular connector is arranged on the inner side wall of the box body, the inner pin end of the micro rectangular connector is electrically connected with the circuit board, and the interface end of the micro rectangular connector can be electrically connected with the inflatable expandable support structure;
the circuit board comprises a signal generation module, a signal acquisition module, a microprocessor module, a serial port communication module, a data storage module and a power management module;
the signal generation module generates a sine sweep frequency signal, and outputs an excitation signal to the inflatable expandable support structure through the excitation output channel after amplification, so that the inflatable expandable support structure vibrates; the signal acquisition module synchronously acquires an excitation signal output by the signal generation module and a response signal generated by vibration of the inflatable expandable support structure; the microprocessor module is used for controlling each module of the dynamic stiffness on-orbit monitoring device and calculating dynamic stiffness data; the serial port communication module is used for converting serial port into USB, and realizing command transmission and data transmission between the satellite-borne computer and the dynamic stiffness on-orbit monitoring device by connecting USB wires; the data storage module is used for storing dynamic stiffness data; the power management module is used for supplying power to other modules of the dynamic stiffness on-orbit monitoring device.
Further, the signal generation module comprises a signal generation circuit, a channel selection circuit and a program-controlled amplifying circuit; the signal generating circuit adopts an AD9834 DDS chip, and can output 2 paths of sine sweep frequency signals with the frequency of 100KHz at the same time; the channel selection circuit consists of two BL1551 single-pole double-throw analog switch chips, and the microprocessor module realizes the selection of an excitation output channel by enabling an EN pin of the BL1551 chip; the program-controlled amplifying circuit amplifies the peak value of the excitation signal to 24V at maximum.
Further, the signal acquisition module realizes synchronous acquisition of 6 paths of response signals and 2 paths of excitation signals at a sampling rate of 200KHz, and the acquired signals are read by the microprocessor module through SPI serial communication.
Further, the microprocessor module adopts an STM32F103ZFT6 chip as a processor chip.
Further, the serial port communication module adopts a CH340G chip to realize serial port to USB conversion, and realizes command transmission and data transmission between the satellite-borne computer and the dynamic stiffness on-orbit monitoring device by connecting USB wires, wherein the data transmission rate is 2Mbps at the highest.
Further, the data storage module adopts an SD card as storage equipment and supports SDIO protocol for data communication.
Further, the power management module is responsible for supplying power to other modules of the dynamic stiffness on-orbit monitoring device, the power management module inputs 5V voltage through USB, and after the voltage is converted through an AMS117-3.3 power chip and an MAX743 power chip, the voltages of +3.3V and +12V are obtained, and the provided voltages are +5V, +3.3V and +12V.
Further, the dynamic stiffness on-track monitoring device can simultaneously monitor the dynamic stiffness of the 2-path inflatable expandable support structure on-track, each path comprises an excitation and sensor system formed by 1 piezoelectric patch driver and 2 piezoelectric patch sensors which are arranged on an inflatable film of the inflatable expandable support structure, wherein the piezoelectric patch driver is driven by the dynamic stiffness on-track monitoring device to apply a sinusoidal sweep signal to excite the inflatable expandable support structure, and the piezoelectric patch sensors are used for sensing vibration of the inflatable expandable support structure and generating charge signals.
An on-orbit monitoring method for dynamic stiffness of a space-inflated expandable support structure, comprising the following steps:
step1: after the inflatable expandable support structure is expanded, the spaceborne computer sends a measurement starting instruction to the dynamic stiffness on-orbit monitoring device;
step2: the microprocessor module initializes the signal generation module, the signal acquisition module and the data storage module every other appointed period, starts 2 excitation channels, and starts a timer TIM3 and a timer TIM4 in the microprocessor module;
step3: the microprocessor module transmits a frequency control word corresponding to the designated frequency to the signal transmission module in an interrupt function generated by the timer TIM3 in an SPI communication mode, so that the signal transmission module generates a sinusoidal sweep frequency signal of the designated frequency according to the frequency control word, and the signal acquisition module is enabled to acquire data in the interrupt function generated by the timer TIM4;
step4: after the signal acquisition module is used for acquiring the excitation signals and the response signals, the microprocessor module respectively performs short-time Fourier transform, obtains dynamic stiffness data of the inflatable expandable support structure by calculating the ratio of the excitation signals to the response signals, and then transmits the dynamic stiffness data to the SD card for storage;
step5: after the data storage is completed, the microprocessor module enables the signal generating module, the signal collecting module and the data storage module to enter a sleep mode, and the next measurement is waited to start.
An on-orbit monitoring data transmission method for dynamic stiffness of a space inflatable expandable support structure comprises the following steps:
step1: the satellite-borne computer sends a data transmission instruction to the dynamic stiffness on-orbit monitoring device;
step2: the microprocessor module initializes the data storage module and the serial port communication module;
step3: the microprocessor module reads data in the SD card and sends the data to the satellite-borne computer through the USB;
step4: after the data transmission task is finished, enabling the data storage module and the serial port communication module to enter a sleep mode by the microprocessor module;
step5: and after receiving the dynamic stiffness data, the satellite-borne computer transmits the data to the ground.
Specific examples:
as shown in FIG. 1, the dynamic stiffness on-orbit monitoring device comprises a top cover, a circuit board and a box body. The circuit board is tightly connected with the box body, and the top cover is tightly connected with the box body by 4M 3 bolts. After connection is completed, the dynamic stiffness on-orbit monitoring device has the size of 150mm multiplied by 30mm, the mass of 350g and occupies very small space for loading the spacecraft. The bottom surface of the dynamic stiffness on-orbit monitoring device is a plane with M3 bolt holes at four corners, the device has good operability, and the device can be tightly connected to the spacecraft wallboard by using 4M 3 bolts, so that the integration of the spacecraft is very easy.
The circuit board in the dynamic stiffness on-orbit monitoring device adopts a modularized design, and the layout among the modules is orderly and compact, so that the size of the circuit board is greatly reduced, the volume of the dynamic stiffness on-orbit monitoring device is optimized, and the occupied load space of the spacecraft is reduced. The circuit board functionally integrates a signal generation module, a signal acquisition module, a microprocessor module, a serial port communication module, a data storage module and a power management module, and the principle implementation of each module is shown in fig. 2.
The signal generating module comprises a signal generating circuit, a channel selecting circuit and a program-controlled amplifying circuit. The signal generating circuit adopts an AD9834 DDS chip, an external clock of the chip adopts an active crystal oscillator of 1MHz, the output frequency resolution reaches 0.004Hz, and 2 paths of sine sweep signals with the frequency as high as 100KHz can be simultaneously output; the channel selection circuit consists of two BL1551 single-pole double-throw analog switch chips, and the microprocessor module realizes the selection of an excitation output channel by enabling an EN pin of the BL1551 chip; the program-controlled amplifying circuit is used for respectively setting 1 AD623 operational amplifier chip, 1 MCP1100 digital potentiometer chip and 1 3296W resistor with resistance value of 100KΩ for 2 paths of excitation signals, the AD623 operational amplifier chip adopts +/-12V power supply, the peak-peak value of the excitation signals can be maximally amplified to 24V, the MCP1110 chip is controlled by the processor chip through analog IIC communication and used for determining amplifying gain, and the 3296W resistor is used for eliminating direct current bias existing in the output excitation signals through manually adjusting the resistance value of the resistor.
The signal acquisition module adopts an AD7606 chip to realize the analog-to-digital conversion function, the module can realize synchronous acquisition of 6 paths of response signals and 2 paths of excitation signals at a sampling rate of up to 200KHz, and the acquired signals can be read by the microprocessor module through SPI serial communication.
The microprocessor module adopts a STM32F103ZFT6 chip with low power consumption as a processor chip, and the peripheral circuit comprises a high/low frequency crystal oscillator circuit, a reset circuit and a program downloading circuit. Wherein the processor chip has flash memory up to 768KB and 96KB SRAM; the high/low frequency crystal oscillator circuit adopts 8MHz and 32.768KHz passive crystal oscillator respectively to provide two external clocks for the processor chip; the reset circuit can reset the dynamic stiffness on-orbit monitoring device to start executing a program; the program downloading circuit adopts an SWD downloading mode, only needs four wires, and occupies 2 interface resources of the processor chip.
The serial port communication module adopts a CH340G chip to realize serial port to USB, and realizes command transmission and data transmission between the satellite-borne computer and the dynamic stiffness on-orbit monitoring device by connecting USB wires, wherein the highest data transmission rate can reach 2Mbps.
The data storage module adopts the SD card as the storage device thereof, the storage space of the spaceborne computer is not required to be occupied, the SD card supports the SDIO protocol to carry out data communication, and the capacity size of the SD card can be freely selected according to the on-orbit running time of the spacecraft.
The power management module is responsible for supplying power to other modules of the dynamic stiffness on-orbit monitoring device, the module inputs 5V voltage by USB, and the voltage of +3.3V and +12V is obtained after the voltage is converted by AMS117-3.3 power chip and MAX743 power chip, and the voltage which can be provided by the module is +5V, +3V and +12V.
The circuit board in the dynamic stiffness on-track monitoring device is provided with 1 SD card seat, 1 USB female seat, 2 SMA connectors, 1 4X 1 reverse bent pin header and 1 6X 2 straight pin header, as shown in figure 3. The USB female seat, the SMA connector and the 4X 1 reverse bending pin header are respectively and directly connected with a USB interface, an SMA interface and a 4X 1 reverse bending pin header interface on the surface of the box body, the 6X 2 direct inserting pin header is connected to an inner pin of the J30J-15ZK micro rectangular connector through a wire, and then the J30J-15ZK micro rectangular connector is connected to the J30J-15ZK micro rectangular connector interface on the surface of the box body. The structure of the J30J-15ZK micro rectangular connector is shown in FIG. 4.
The assembly process of the dynamic stiffness on-orbit monitoring device comprises the following steps:
firstly, installing an SD card with a selected size in an SD card seat on a circuit board; secondly, tightly connecting a circuit board with a box body through 4M 3 bolts, mounting a J30J-15ZK micro-rectangular connector on a J30J-15ZK micro-rectangular connection interface on the box body, and connecting pins in the J30J-15ZK micro-rectangular connector with 6X 2 direct contact pins by using wires; and finally, tightly connecting the top cover and the box body by using 4M 3 bolts.
Interface connection of dynamic stiffness on-orbit monitoring device:
firstly, connecting a JTAG simulator on a 4 multiplied by 1 reverse bending pin header, burning a program in a dynamic stiffness on-orbit monitoring device, and pulling out the JTAG simulator after the program is burnt; then, the dynamic stiffness on-orbit monitoring device is installed on a wall plate of the spacecraft by using 4M 3 bolts, and is connected with the spacecraft by using a USB wire through a USB interface, so that electric connection and communication connection are realized; finally, the excitation signal output from the SMA interface is connected to a piezoelectric driver on the inflatable expandable support structure, and then the piezoelectric sensor on the inflatable expandable support structure is connected to a J30J-15ZK micro rectangular connector interface, so that the dynamic stiffness on-orbit monitoring device can monitor the dynamic stiffness of the 2-path inflatable expandable support structure at the same time. Taking an inflatable expandable support rod shown in fig. 5 as an example for illustration, the inflatable expandable support rod is formed by bonding polyimide films with the thickness of 0.5mm, upper and lower footstands and bases are formed by printing PLA materials, the height of the rod is 700mm, the outer diameter of the rod is 100mm, 1 piezoelectric plate driver and 2 piezoelectric plate sensors are arranged on the films, the piezoelectric plate driver is used for receiving sine sweep signals output by a dynamic stiffness on-orbit monitoring device so as to excite the inflatable expandable support rod, the piezoelectric plate sensors are used for converting vibration of the inflatable expandable support rod into charge signals, the piezoelectric plate driver on the inflatable expandable support rod uses the dynamic stiffness on-orbit monitoring device to output sine sweep signals of 1-10Hz, and the sine sweep signals and charge signals generated by the 2 piezoelectric plate sensors are acquired with the resolution of 100Hz, and then the signals are respectively subjected to short-time Fourier transformation and the ratio is calculated, so that the dynamic stiffness curve of the inflatable expandable support rod is shown in fig. 6. From the figure, the inflatable expandable support rod has uneven structural mass distribution due to the fact that the top of the inflatable expandable support rod is provided with a tightening hoop for tightly binding the film and the top seat, 2 first-order natural frequencies exist, and the dynamic stiffness value of the inflatable expandable support rod is minimum at the first-order natural frequencies of 4.98Hz and 5.81 Hz.
The dynamic stiffness monitoring device can continuously measure the dynamic stiffness of the inflatable expandable support structure at intervals of a fixed period, and the specific measuring process is as follows:
step1: after the inflatable expandable support structure is expanded, the spaceborne computer sends a measurement starting instruction to the dynamic stiffness on-orbit monitoring device;
step2: the microprocessor module initializes the signal generation module, the signal acquisition module and the data storage module every other appointed period, starts 2 excitation channels, and starts a timer TIM3 and a timer TIM4;
step3: the microprocessor module sends a frequency control word corresponding to the designated frequency to the signal sending module in an interrupt function generated by the timer TIM3 in an SPI communication mode, so that the microprocessor module generates a sinusoidal signal with the designated frequency according to the frequency control word, and the signal collecting module is enabled to collect data in the interrupt function generated by the timer 4;
step4: after the acquisition is completed, the microprocessor module respectively performs short-time Fourier transform on the acquired excitation signals and response signals, obtains dynamic stiffness data of the inflatable expandable support structure by calculating the ratio of the excitation signals and the response signals, and then transmits the dynamic stiffness data to the SD card for storage;
step5: after the data storage is completed, the microprocessor module enables the signal generating module, the signal collecting module and the data storage module to enter a sleep mode, and the next measurement is waited to start.
The dynamic stiffness on-orbit monitoring device has a data storage function, does not occupy the storage space of a satellite-borne computer, and only needs to transmit dynamic stiffness data to the on-orbit monitoring device according to a data transmission instruction sent by the satellite-borne computer, wherein the specific data transmission process is as follows:
step1: the satellite-borne computer sends a data transmission instruction to the dynamic stiffness on-orbit monitoring device;
step2: the microprocessor module initializes the data storage module and the serial port communication module;
step3: the microprocessor module reads data in the SD card and sends the data to the satellite-borne computer through the USB;
step4: after the data transmission task is finished, enabling the data storage module and the serial port communication module to enter a sleep mode by the microprocessor module;
step5: and the computer transmits the data to the ground after receiving the dynamic stiffness data.
Claims (10)
1. The dynamic stiffness on-orbit monitoring device of the space inflatable expandable support structure is characterized by comprising a top cover, a circuit board, a micro rectangular connector and a box body; the circuit board is arranged in the box body; the top cover is arranged on the top surface of the box body to seal the box body; the bottom surface of the box body is provided with a plurality of bolt holes for installing the dynamic stiffness on-orbit monitoring device on the aircraft wall plate through bolts; the micro rectangular connector is arranged on the inner side wall of the box body, the inner pin end of the micro rectangular connector is electrically connected with the circuit board, and the interface end of the micro rectangular connector can be electrically connected with the inflatable expandable support structure;
the circuit board comprises a signal generation module, a signal acquisition module, a microprocessor module, a serial port communication module, a data storage module and a power management module;
the signal generation module generates a sine sweep frequency signal, and outputs an excitation signal to the inflatable expandable support structure through the excitation output channel after amplification, so that the inflatable expandable support structure vibrates; the signal acquisition module synchronously acquires an excitation signal output by the signal generation module and a response signal generated by vibration of the inflatable expandable support structure; the microprocessor module is used for controlling each module of the dynamic stiffness on-orbit monitoring device and calculating dynamic stiffness data; the serial port communication module is used for converting serial port into USB, and realizing command transmission and data transmission between the satellite-borne computer and the dynamic stiffness on-orbit monitoring device by connecting USB wires; the data storage module is used for storing dynamic stiffness data; the power management module is used for supplying power to other modules of the dynamic stiffness on-orbit monitoring device.
2. The dynamic stiffness on-orbit monitoring device for a space-inflated deployable support structure of claim 1, wherein the signal generation module comprises a signal generation circuit, a channel selection circuit and a program-controlled amplification circuit; the signal generating circuit adopts an AD9834 DDS chip, and can output 2 paths of sine sweep frequency signals with the frequency of 100KHz at the same time; the channel selection circuit consists of two BL1551 single-pole double-throw analog switch chips, and the microprocessor module realizes the selection of an excitation output channel by enabling an EN pin of the BL1551 chip; the program-controlled amplifying circuit amplifies the peak value of the excitation signal to 24V at maximum.
3. The dynamic stiffness on-orbit monitoring device of the spatial inflatable expandable support structure according to claim 1, wherein the signal acquisition module is used for synchronously acquiring 6 paths of response signals and 2 paths of excitation signals at a sampling rate of 200KHz, and the acquired signals are read by the microprocessor module through SPI serial communication.
4. The device for on-orbit monitoring of dynamic stiffness of a spatially inflatable expandable support structure according to claim 1, wherein the microprocessor module employs STM32F103ZFT6 chips as the processor chip.
5. The dynamic stiffness on-orbit monitoring device of the space inflatable expandable support structure according to claim 1, wherein the serial port communication module adopts a CH340G chip to realize serial port to USB, and realizes command transmission and data transmission between a satellite-borne computer and the dynamic stiffness on-orbit monitoring device through connecting USB wires, wherein the data transmission rate is up to 2Mbps.
6. The dynamic stiffness on-orbit monitoring device of the space inflatable expandable support structure according to claim 1, wherein the data storage module adopts an SD card as a storage device and supports SDIO protocol for data communication.
7. The device for monitoring the dynamic stiffness of the spatial inflatable and expandable support structure on the track according to claim 1, wherein the power management module is responsible for supplying power to other modules of the device for monitoring the dynamic stiffness on the track, the power management module inputs 5V voltage by USB, and the voltage of +3.3V and +/-12V is obtained after the voltage is converted by an AMS117-3.3 power chip and a MAX743 power chip, and the provided voltage is +5V, +3.3V and +/-12V.
8. An on-track monitoring device for the dynamic stiffness of a space inflatable deployable support structure according to claim 1, wherein the on-track monitoring device is capable of simultaneously monitoring the dynamic stiffness of a 2-way inflatable deployable support structure on-track, each of the two ways comprising an excitation and sensor system comprising 1 piezoelectric patch driver and 2 piezoelectric patch sensors disposed on an inflatable membrane of the inflatable deployable support structure, wherein the piezoelectric patch driver passive stiffness on-track monitoring device applies a sinusoidal sweep signal to excite the inflatable deployable support structure, and the piezoelectric patch sensors are configured to sense vibrations of the inflatable deployable support structure and generate a charge signal.
9. An on-orbit monitoring method for dynamic stiffness of a space-inflated expandable support structure is characterized by comprising the following steps:
step1: after the inflatable expandable support structure is expanded, the spaceborne computer sends a measurement starting instruction to the dynamic stiffness on-orbit monitoring device;
step2: the microprocessor module initializes the signal generation module, the signal acquisition module and the data storage module every other appointed period, starts 2 excitation channels, and starts a timer TIM3 and a timer TIM4 in the microprocessor module;
step3: the microprocessor module transmits a frequency control word corresponding to the designated frequency to the signal transmission module in an interrupt function generated by the timer TIM3 in an SPI communication mode, so that the signal transmission module generates a sinusoidal sweep frequency signal of the designated frequency according to the frequency control word, and the signal acquisition module is enabled to acquire data in the interrupt function generated by the timer TIM4;
step4: after the signal acquisition module is used for acquiring the excitation signals and the response signals, the microprocessor module respectively performs short-time Fourier transform, obtains dynamic stiffness data of the inflatable expandable support structure by calculating the ratio of the excitation signals to the response signals, and then transmits the dynamic stiffness data to the SD card for storage;
step5: after the data storage is completed, the microprocessor module enables the signal generating module, the signal collecting module and the data storage module to enter a sleep mode, and the next measurement is waited to start.
10. The method for transmitting the on-orbit monitoring data of the dynamic stiffness of the space inflatable expandable support structure is characterized by comprising the following steps of:
step1: the satellite-borne computer sends a data transmission instruction to the dynamic stiffness on-orbit monitoring device;
step2: the microprocessor module initializes the data storage module and the serial port communication module;
step3: the microprocessor module reads data in the SD card and sends the data to the satellite-borne computer through the USB;
step4: after the data transmission task is finished, enabling the data storage module and the serial port communication module to enter a sleep mode by the microprocessor module;
step5: and after receiving the dynamic stiffness data, the satellite-borne computer transmits the data to the ground.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012021911A1 (en) * | 2010-08-16 | 2012-02-23 | Ruag Space Gmbh | Device for the securing and commanded release of an element to be released of a spacecraft |
| CN207638661U (en) * | 2017-12-18 | 2018-07-20 | 中国科学院西安光学精密机械研究所 | A kind of small-sized laser space communication terminal rough tracking device |
-
2021
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012021911A1 (en) * | 2010-08-16 | 2012-02-23 | Ruag Space Gmbh | Device for the securing and commanded release of an element to be released of a spacecraft |
| CN207638661U (en) * | 2017-12-18 | 2018-07-20 | 中国科学院西安光学精密机械研究所 | A kind of small-sized laser space communication terminal rough tracking device |
Non-Patent Citations (1)
| Title |
|---|
| 充气展开反射面天线动态特性试验研究;余建新;谭惠丰;卫剑征;;载人航天(第04期);84-89 * |
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