CN111947904A - Micro-vibration-based on-orbit health monitoring method, system, medium and equipment for spacecraft structure - Google Patents
Micro-vibration-based on-orbit health monitoring method, system, medium and equipment for spacecraft structure Download PDFInfo
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
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- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H11/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties
- G01H11/06—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties by electric means
- G01H11/08—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties by electric means using piezoelectric devices
Abstract
The invention provides a micro-vibration-based on-orbit health monitoring method, a system, a medium and equipment for a spacecraft structure. Micro-vibration signals of the spacecraft during on-orbit running are collected by high-frequency piezoelectric acceleration sensors which are distributed and installed on a spacecraft structure. The sensor network is connected with the preamplifier, the micro-vibration signal data is input into the data acquisition and storage unit, the data acquisition and storage unit outputs data signals to the computer, and the computer processes the input signals according to the stored micro-vibration data signals and then determines whether the working state of the accelerator is normal or not and gives out possible fault parts. The invention solves the problems of real-time monitoring and fault analysis of the spacecraft structure in the in-orbit working process, and makes up the defects of the prior art.
Description
Technical Field
The invention relates to the field of on-orbit health monitoring, in particular to a micro-vibration-based on-orbit health monitoring method, system, medium and equipment for a spacecraft structure.
Background
At present, the cost of developing and launching the spacecraft is high, the on-orbit service time is long, the working conditions and the load conditions are high, the structure of the spacecraft is also inevitably easy to generate specific damage in the working state, and the damage causes comprise impact, continuous load, corrosion aging, change of the working environment and the like. It is therefore desirable for certain spacecraft that operate in orbit for extended periods of time to be able to monitor the health of the structure.
Patent document CN102809423 discloses a satellite in-orbit micro-vibration measurement system, which can comprehensively master the vibration states of the active section and the in-orbit section of the satellite, provide basis for later-stage satellite structure optimization, and make a proper vibration control strategy and environment assessment indexes, but does not further apply the system to spacecraft in-orbit structure health monitoring. The method used in this patent has significant limitations.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a micro-vibration-based on-orbit health monitoring method, system, medium and equipment for a spacecraft structure.
According to the invention, the micro-vibration-based on-orbit health monitoring method for the spacecraft structure comprises the following steps: step S1: installing high-frequency piezoelectric acceleration sensors on monitoring parts of a spacecraft structure in a distributed manner; a sensor network is formed by high-frequency piezoelectric acceleration sensors to acquire sensor signal information; step S2: according to the signal information of the sensor, the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage; step S3: the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage; step S4: the data acquisition and storage unit outputs data signals to the vibration monitoring computer; step S5: the vibration monitoring computer carries out fast Fourier transform on the input signal according to the vibration signal recorded periodically to obtain a micro-vibration signal frequency spectrum; step S6: and analyzing the frequency spectrum of the micro-vibration signal, comparing the frequency spectrum with a set threshold value to obtain whether the sensor signal is normal or not, and acquiring the information of an abnormal presumed occurrence area or the structural on-orbit health result information.
Preferably, the step S1 includes: and S1.1, acquiring a micro-vibration signal generated by normal periodic motion of movable parts such as flywheels, solar wings, refrigerators and the like on the on-orbit spacecraft by using a high-frequency piezoelectric acceleration sensor network.
Preferably, the step S1 further includes: and S1.2, acquiring signal information of the sensor according to a micro-vibration signal generated by normal periodic motion of a movable part on the in-orbit spacecraft.
Preferably, the step S6 includes: s6.1, analyzing the spectrum of the micro-vibration signal through a neural network algorithm, and comparing the spectrum with a set threshold value to obtain whether the sensor signal is normal or not; the information of the abnormality presumed occurrence region or the information of the structural on-track health result is acquired, and the region where the abnormality is likely to occur is given as a damage portion.
According to the invention, the micro-vibration based on-orbit health monitoring system for the spacecraft structure comprises: module S1: installing high-frequency piezoelectric acceleration sensors on monitoring parts of a spacecraft structure in a distributed manner; a sensor network is formed by high-frequency piezoelectric acceleration sensors to acquire sensor signal information; module S2: according to the signal information of the sensor, the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage; module S3: the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage; module S4: the data acquisition and storage unit outputs data signals to the vibration monitoring computer; module S5: the vibration monitoring computer carries out fast Fourier transform on the input signal according to the vibration signal recorded periodically to obtain a micro-vibration signal frequency spectrum; module S6: and analyzing the frequency spectrum of the micro-vibration signal, comparing the frequency spectrum with a set threshold value to obtain whether the sensor signal is normal or not, and acquiring the information of an abnormal presumed occurrence area or the structural on-orbit health result information.
Preferably, the module S1 includes: and a module S1.1, acquiring a micro-vibration signal generated by normal periodic motion of a movable part on the in-orbit spacecraft by a high-frequency piezoelectric acceleration sensor network.
Preferably, the module S1 further includes: and a module S1.2 for acquiring signal information of the sensor according to a micro-vibration signal generated by normal periodic motion of active parts such as an upper flywheel, a solar wing, a refrigerator and the like on the on-orbit spacecraft.
Preferably, the module S6 includes: a module S6.1, analyzing the micro-vibration signal frequency spectrum through a neural network algorithm, and comparing the frequency spectrum with a set threshold value to obtain whether the sensor signal is normal or not; the information of the abnormality presumed occurrence region or the information of the structural on-track health result is acquired, and the region where the abnormality is likely to occur is given as a damage portion.
According to the present invention, a computer-readable storage medium is provided having a computer program stored thereon, which, when being executed by a processor, carries out the steps of the micro-vibration based on-orbit health monitoring method for a spacecraft structure.
According to the invention, the micro-vibration based on-orbit health monitoring equipment for the spacecraft structure comprises: a controller;
the controller comprises a computer readable storage medium storing a computer program which, when executed by a processor, implements the steps of a micro-vibration based on-orbit health monitoring method for a spacecraft structure; alternatively, the controller comprises a micro-vibration based on-orbit health monitoring system for the spacecraft structure.
Compared with the prior art, the invention has the following beneficial effects:
the invention provides an on-orbit health monitoring system of a spacecraft structure based on micro-vibration, which is characterized in that micro-vibration signals generated by periodic motion of movable parts such as a flywheel, a solar wing and a refrigerator on the spacecraft are collected, the signals are amplified and then processed by using an artificial neural network, and whether the micro-vibration signals are normal or not is judged, so that the purpose of on-orbit monitoring of the health condition of the spacecraft structure is achieved. The process does not influence the normal in-orbit work of the spacecraft, and can realize the in-orbit health monitoring of the spacecraft. The design concept is likely to become a breakthrough direction for the development of on-orbit health monitoring of the spacecraft in the future.
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Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic diagram of an in-orbit health monitoring system of a micro-vibration-based spacecraft structure provided by the invention.
In the figure:
data acquisition and storage unit 3 of sensor network 1
Preamplifier 2 vibration monitoring computer 4
Detailed Description
The present invention will be described in detail with reference to specific examples. The following 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 it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, the method for monitoring the on-orbit health of a micro-vibration-based spacecraft structure provided by the invention comprises the following steps: step S1: installing high-frequency piezoelectric acceleration sensors on monitoring parts of a spacecraft structure in a distributed manner; a sensor network is formed by high-frequency piezoelectric acceleration sensors to acquire sensor signal information; step S2: according to the signal information of the sensor, the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage; step S3: the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage; step S4: the data acquisition and storage unit outputs data signals to the vibration monitoring computer; step S5: the vibration monitoring computer carries out fast Fourier transform on the input signal according to the vibration signal recorded periodically to obtain a micro-vibration signal frequency spectrum; step S6: and analyzing the frequency spectrum of the micro-vibration signal, comparing the frequency spectrum with a set threshold value to obtain whether the sensor signal is normal or not, and acquiring the information of an abnormal presumed occurrence area or the structural on-orbit health result information.
Preferably, the step S1 includes: and S1.1, acquiring a micro-vibration signal generated by normal periodic motion of movable parts such as flywheels, solar wings, refrigerators and the like on the on-orbit spacecraft by using a high-frequency piezoelectric acceleration sensor network.
Preferably, the step S1 further includes: and S1.2, acquiring signal information of the sensor according to a micro-vibration signal generated by normal periodic motion of a movable part on the in-orbit spacecraft.
Preferably, the step S6 includes: s6.1, analyzing the spectrum of the micro-vibration signal through a neural network algorithm, and comparing the spectrum with a set threshold value to obtain whether the sensor signal is normal or not; the information of the abnormality presumed occurrence region or the information of the structural on-track health result is acquired, and the region where the abnormality is likely to occur is given as a damage portion.
According to the invention, the micro-vibration based on-orbit health monitoring system for the spacecraft structure comprises: module S1: installing high-frequency piezoelectric acceleration sensors on monitoring parts of a spacecraft structure in a distributed manner; a sensor network is formed by high-frequency piezoelectric acceleration sensors to acquire sensor signal information; module S2: according to the signal information of the sensor, the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage; module S3: the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage; module S4: the data acquisition and storage unit outputs data signals to the vibration monitoring computer; module S5: the vibration monitoring computer carries out fast Fourier transform on the input signal according to the vibration signal recorded periodically to obtain a micro-vibration signal frequency spectrum; module S6: and analyzing the frequency spectrum of the micro-vibration signal, comparing the frequency spectrum with a set threshold value to obtain whether the sensor signal is normal or not, and acquiring the information of an abnormal presumed occurrence area or the structural on-orbit health result information.
The invention discloses a micro-vibration-based spacecraft structure on-orbit health monitoring system, which comprises a sensor network consisting of a plurality of high-frequency piezoelectric acceleration sensors, a preamplifier and a data acquisition and storage unit which are connected through a cable network, and vibration data are input into a vibration monitoring computer to form a complete system. Micro-vibration signals of the spacecraft during on-orbit running are collected by high-frequency piezoelectric acceleration sensors which are distributed and installed on a spacecraft structure. The sensor network is connected with the preamplifier, the micro-vibration signal data is input into the data acquisition and storage unit, the data acquisition and storage unit outputs data signals to the computer, and the computer processes the input signals according to the stored micro-vibration data signals and then determines whether the working state of the accelerator is normal or not and gives out possible fault parts. The invention solves the problems of real-time monitoring and fault analysis of the spacecraft structure in the in-orbit working process, and makes up the defects of the prior art.
Preferably, the module S1 includes: and a module S1.1, acquiring a micro-vibration signal generated by normal periodic motion of a movable part on the in-orbit spacecraft by a high-frequency piezoelectric acceleration sensor network.
Preferably, the module S1 further includes: and a module S1.2 for acquiring signal information of the sensor according to a micro-vibration signal generated by normal periodic motion of active parts such as an upper flywheel, a solar wing, a refrigerator and the like on the on-orbit spacecraft.
Preferably, the module S6 includes: a module S6.1, analyzing the micro-vibration signal frequency spectrum through a neural network algorithm, and comparing the frequency spectrum with a set threshold value to obtain whether the sensor signal is normal or not; the information of the abnormality presumed occurrence region or the information of the structural on-track health result is acquired, and the region where the abnormality is likely to occur is given as a damage portion.
Specifically, in one embodiment, the microvibration-based on-orbit health monitoring system for a spacecraft structure comprises the steps of cabling high-frequency piezoelectric acceleration sensors disposed on the spacecraft structure into a sensor network 1. The sensor network 1 is connected with the preamplifier 2 by a cable and is used for outputting a micro-vibration signal of a spacecraft structure. The preamplifier 2 is connected with the data acquisition and storage unit 3 and transmits and stores the micro-vibration signals. The data acquisition and storage unit 3 outputs micro-vibration signal data to the vibration monitoring computer 4. The vibration monitoring computer 4 performs fast Fourier transform on the input signal according to the vibration signal data recorded periodically to obtain the micro-vibration signal frequency spectrum. And finally, analyzing the spectrum of the micro-vibration signal by using a neural network algorithm, comparing the spectrum with a set threshold value to obtain whether the sensor signal is normal or not, and giving an area where the abnormality is likely to occur.
When the method is applied, various normal or abnormal spacecraft structure micro-vibration signal data are required to be collected according to the typical working conditions of the on-orbit operation of the spacecraft and stored in the vibration monitoring computer. Then, using the acquired typical signal, fast fourier transform is performed to acquire the spectrum of the micro-vibration signal. And then, training the acquired micro-vibration signal frequency spectrum by using a neural network algorithm, and establishing a data feature library. After training is completed, health monitoring on the typical working condition of the on-orbit operation of the spacecraft can be realized through the artificial neural network. In the training process, the number of input nodes of the artificial neural network is equal to the number of characteristic frequency bands in the micro-vibration signal frequency spectrum, and the number of output nodes is the number of normal working conditions plus one, and the input nodes respectively correspond to the normal states of various spacecrafts. And when the abnormality is diagnosed, inputting the characteristic frequency band numerical value into the neural network, wherein the output of the neural network gives the signal state of each high-frequency piezoelectric acceleration sensor and the membership degree of the high-frequency piezoelectric acceleration sensor to the normal state or the abnormal state. If the membership degree of a certain abnormal state is greater than a preset threshold value, the abnormal fault occurs in the area near the high-frequency piezoelectric acceleration sensor, and the computer gives an alarm.
According to the present invention, a computer-readable storage medium is provided having a computer program stored thereon, which, when being executed by a processor, carries out the steps of the micro-vibration based on-orbit health monitoring method for a spacecraft structure.
According to the invention, the micro-vibration based on-orbit health monitoring equipment for the spacecraft structure comprises: a controller;
the controller comprises a computer readable storage medium storing a computer program which, when executed by a processor, implements the steps of a micro-vibration based on-orbit health monitoring method for a spacecraft structure; alternatively, the controller comprises a micro-vibration based on-orbit health monitoring system for the spacecraft structure.
The invention provides an on-orbit health monitoring system of a spacecraft structure based on micro-vibration, which is characterized in that micro-vibration signals generated by periodic motion of movable parts such as a flywheel, a solar wing and a refrigerator on the spacecraft are collected, the signals are amplified and then processed by using an artificial neural network, and whether the micro-vibration signals are normal or not is judged, so that the purpose of on-orbit monitoring of the health condition of the spacecraft structure is achieved. The process does not influence the normal in-orbit work of the spacecraft, and can realize the in-orbit health monitoring of the spacecraft. The design concept is likely to become a breakthrough direction for the development of on-orbit health monitoring of the spacecraft in the future.
Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A micro-vibration-based spacecraft structure on-orbit health monitoring method is characterized by comprising the following steps:
step S1: installing high-frequency piezoelectric acceleration sensors on monitoring parts of a spacecraft structure in a distributed manner; a sensor network is formed by high-frequency piezoelectric acceleration sensors to acquire sensor signal information;
step S2: according to the signal information of the sensor, the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage;
step S3: the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage;
step S4: the data acquisition and storage unit outputs data signals to the vibration monitoring computer;
step S5: the vibration monitoring computer carries out fast Fourier transform on the input signal according to the vibration signal recorded periodically to obtain a micro-vibration signal frequency spectrum;
step S6: and analyzing the frequency spectrum of the micro-vibration signal, comparing the frequency spectrum with a set threshold value to obtain whether the sensor signal is normal or not, and acquiring the information of an abnormal presumed occurrence area or the structural on-orbit health result information.
2. A micro-vibration based spacecraft structure in-orbit health monitoring method according to claim 1, wherein the step S1 comprises:
and S1.1, acquiring a micro-vibration signal generated by normal periodic motion of a movable part on the in-orbit spacecraft by using a high-frequency piezoelectric acceleration sensor network.
3. The micro-vibration based spacecraft structure in-orbit health monitoring method of claim 1, wherein the step S1 further comprises:
and S1.2, acquiring signal information of the sensor according to a micro-vibration signal generated by normal periodic motion of a movable part on the in-orbit spacecraft.
4. A micro-vibration based spacecraft structure in-orbit health monitoring method according to claim 1, wherein the step S6 comprises:
s6.1, analyzing the spectrum of the micro-vibration signal through a neural network algorithm, and comparing the spectrum with a set threshold value to obtain whether the sensor signal is normal or not; and acquiring information of the abnormal presumed occurrence area or structural on-track health result information.
5. A micro-vibration based on-orbit health monitoring system for a spacecraft structure, comprising:
module S1: installing high-frequency piezoelectric acceleration sensors on monitoring parts of a spacecraft structure in a distributed manner; a sensor network is formed by high-frequency piezoelectric acceleration sensors to acquire sensor signal information;
module S2: according to the signal information of the sensor, the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage;
module S3: the preamplifier amplifies the acquired micro-vibration signal and transfers the amplified micro-vibration signal to a data acquisition and storage unit for storage;
module S4: the data acquisition and storage unit outputs data signals to the vibration monitoring computer;
module S5: the vibration monitoring computer carries out fast Fourier transform on the input signal according to the vibration signal recorded periodically to obtain a micro-vibration signal frequency spectrum;
module S6: and analyzing the frequency spectrum of the micro-vibration signal, comparing the frequency spectrum with a set threshold value to obtain whether the sensor signal is normal or not, and acquiring the information of an abnormal presumed occurrence area or the structural on-orbit health result information.
6. A micro-vibration based spacecraft structural in-orbit health monitoring system of claim 5, wherein the module S1 comprises:
and a module S1.1, acquiring a micro-vibration signal generated by normal periodic motion of a movable part on the in-orbit spacecraft by a high-frequency piezoelectric acceleration sensor network.
7. A micro-vibration based spacecraft structural in-orbit health monitoring system of claim 5, wherein the module S1 further comprises: and a module S1.2 for acquiring signal information of the sensor according to a micro-vibration signal generated by normal periodic motion of a movable part on the in-orbit spacecraft.
8. A micro-vibration based spacecraft structural in-orbit health monitoring system of claim 5, wherein the module S6 comprises:
a module S6.1, analyzing the micro-vibration signal frequency spectrum through a neural network algorithm, and comparing the frequency spectrum with a set threshold value to obtain whether the sensor signal is normal or not; and acquiring information of the abnormal presumed occurrence area or structural on-track health result information.
9. A computer-readable storage medium storing a computer program, wherein the computer program, when executed by a processor, performs the steps of the micro-vibration based spacecraft structure in-orbit health monitoring method of any of claims 1 to 4.
10. A micro-vibration based on-orbit health monitoring device for a spacecraft structure, comprising: a controller;
the controller comprising a computer readable storage medium of claim 9 having a computer program stored thereon, which when executed by a processor implements the steps of the micro-vibration based spacecraft structure in-orbit health monitoring method of any of claims 1 to 4; alternatively, the controller comprises the micro-vibration based spacecraft structure in-orbit health monitoring system of any of claims 5 to 8.
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