CN106516174B - Method and system for monitoring space debris impact on in-orbit spacecraft - Google Patents
Method and system for monitoring space debris impact on in-orbit spacecraft Download PDFInfo
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Abstract
The invention discloses a method and a system for monitoring space debris impact on an in-orbit spacecraft, wherein the method comprises the following steps: respectively acquiring corresponding target ultrasonic signals through a plurality of ultrasonic sensors, and performing amplification gain processing to obtain ultrasonic monitoring data; when any ultrasonic monitoring data is judged to exceed a preset trigger threshold value, acquiring and storing specific ultrasonic monitoring data, wherein the specific ultrasonic monitoring data are ultrasonic monitoring data of all ultrasonic sensors within a preset trigger time; and when all the ultrasonic monitoring data are judged not to reach the preset triggering threshold value, reading the stored specific ultrasonic monitoring data, and analyzing and calculating according to the specific ultrasonic monitoring data to obtain the impact position and the impact strength of the in-orbit spacecraft. The invention realizes the acoustic emission monitoring and positioning generated by the space debris impact structure in a passive ultrasonic monitoring mode.
Description
Technical Field
The invention belongs to the technical field of satellite communication, and particularly relates to a method and a system for monitoring space debris impact on an in-orbit spacecraft.
Background
With the densification of human space activities, the space debris is continuously increased to cause the space environment to be increasingly deteriorated, and due to the increase of the space debris, an event that the space debris collides with the in-orbit spacecraft is often easy to occur, which poses a serious threat to the safe operation of the in-orbit spacecraft and the life safety of the spacecraft and becomes an important risk factor which is not negligible, so that the condition that the in-orbit spacecraft is impacted by the space debris needs to be monitored to evaluate the damage and the structural health condition of the in-orbit spacecraft and provide data support for the in-orbit maintenance and the like of the spacecraft.
At present, the existing spacecraft structure health monitoring method usually adopts data analysis through an active vibration sensor or ultrasonic active flaw detection, and although the ultrasonic active flaw detection is successfully applied to nondestructive testing means in some industrial and military fields, the ultrasonic active flaw detection method needs to actively emit ultrasonic waves, is only suitable for active flaw detection, cannot be applied to monitoring of unmanned spacecraft structure damage, and cannot use acoustic emission signals generated by space debris impact structures to carry out passive impact monitoring and positioning.
Disclosure of Invention
In view of this, embodiments of the present invention provide a method and a system for monitoring an on-orbit spacecraft from space debris impact based on ultrasonic signal processing, and solve the technical problem of directly using an acoustic emission signal generated by a space debris impact structure to perform passive impact monitoring and positioning.
In order to solve the technical problem, in one aspect, the invention provides a method for monitoring an on-orbit spacecraft from being hit by space debris, which includes the following steps:
respectively acquiring corresponding target ultrasonic signals through a plurality of ultrasonic sensors, wherein the target ultrasonic signals are ultrasonic signals which are generated when an in-orbit spacecraft is impacted by space debris and are transmitted along the structure of the in-orbit spacecraft;
amplifying and gain processing is carried out on each target ultrasonic signal to obtain ultrasonic monitoring data;
when any ultrasonic monitoring data is judged to exceed a preset trigger threshold value, acquiring and storing specific ultrasonic monitoring data, wherein the specific ultrasonic monitoring data are ultrasonic monitoring data of all ultrasonic sensors within a preset trigger time;
and when all the ultrasonic monitoring data are judged not to reach the preset triggering threshold value, reading the stored specific ultrasonic monitoring data, and analyzing and calculating according to the specific ultrasonic monitoring data to obtain the impact position and the impact strength of the in-orbit spacecraft.
Preferably, the step of performing amplification gain processing on each target ultrasound signal to obtain ultrasound monitoring data includes:
converting each target ultrasonic signal into a voltage signal, and carrying out primary amplification on the voltage signal to a preset voltage value;
adjusting the voltage signal after the first-stage amplification to an analog signal of which the center zero position is at a preset zero value;
performing primary filtering on the analog signal after zero setting;
performing secondary amplification on the filtered analog signal according to a preset gain coefficient;
and carrying out voltage following on the analog signal subjected to secondary amplification and then converting the analog signal into a digital signal to obtain ultrasonic monitoring data.
Preferably, the preset trigger threshold includes an upper limit value and a lower limit value centered on a central zero position.
Preferably, the specific ultrasound monitoring data is acquired and stored by a cross-memory array.
Preferably, the step of analyzing and calculating the impact position and the impact strength of the in-orbit spacecraft according to the specific ultrasonic monitoring data specifically includes:
carrying out target ultrasonic signal feature identification and impact occurrence time point confirmation according to the specific ultrasonic monitoring data;
calculating the impact position of the in-orbit spacecraft by a time difference positioning method according to the characteristics of the target ultrasonic signal, the impact occurrence time point and the distribution position of the ultrasonic sensor;
and estimating the impact strength of the in-orbit spacecraft according to the energy analysis of the specific ultrasonic monitoring data.
In another aspect, the present invention also provides a system for monitoring the impact of an in-orbit spacecraft on space debris, the system comprising:
the system comprises a plurality of ultrasonic sensors, a plurality of ultrasonic sensors and a controller, wherein the ultrasonic sensors are used for acquiring corresponding target ultrasonic signals, and the target ultrasonic signals are ultrasonic signals generated when an in-orbit spacecraft is impacted by space debris and propagated along the structure of the in-orbit spacecraft;
the amplification gain module is used for performing amplification gain processing on each target ultrasonic signal to obtain ultrasonic monitoring data;
the judging module is used for judging whether any ultrasonic monitoring data exceeds a preset triggering threshold value;
the acquisition and storage module is used for acquiring and storing specific ultrasonic monitoring data when judging that any ultrasonic monitoring data exceeds a preset trigger threshold, wherein the specific ultrasonic monitoring data is ultrasonic monitoring data within a preset trigger time;
and the analysis and calculation module is used for reading the stored specific ultrasonic monitoring data when judging that all the ultrasonic monitoring data do not reach the preset trigger threshold value, and analyzing and calculating the impact position and the impact strength of the in-orbit spacecraft according to the specific ultrasonic monitoring data.
Preferably, the amplification gain module further comprises:
the primary amplification submodule is used for converting each target ultrasonic signal into a voltage signal and performing primary amplification on the voltage signal to a preset voltage value;
the zero adjustment submodule is used for adjusting the voltage signal after the primary amplification to an analog signal of which the center zero is at a preset zero value;
the filtering submodule is used for carrying out primary filtering on the analog signal after the zero setting;
the second-stage amplification submodule is used for carrying out second-stage amplification on the filtered analog model;
and the signal following and analog-to-digital conversion submodule is used for carrying out voltage following on the analog signal after secondary amplification and then converting the analog signal into a digital signal to obtain ultrasonic monitoring data.
Preferably, the preset trigger threshold includes an upper limit value and a lower limit value centered on a central zero position.
Preferably, the acquisition and storage module is a cross storage array.
Preferably, the analysis calculation module further comprises:
the identification and confirmation submodule is used for identifying the characteristics of the target ultrasonic signal and confirming the impact occurrence time point according to the specific ultrasonic monitoring data;
the position calculation submodule is used for calculating the impact position of the in-orbit spacecraft by a time difference positioning method according to the characteristics of the target ultrasonic signal, the impact occurrence time point and the distribution position of the ultrasonic sensor;
and the intensity estimation submodule is used for estimating the impact intensity of the in-orbit spacecraft according to the energy analysis of the specific ultrasonic monitoring data.
By adopting the technical scheme, the invention can at least obtain the following technical effects:
the method and the system for monitoring the space debris impact on the in-orbit spacecraft adopt the passive ultrasonic sensor as an ultrasonic signal acquisition sensitive device, can perform corresponding signal identification mode adjustment, gain adjustment and system expansion aiming at the requirements of rigid structures of different in-orbit spacecrafts, realize the acoustic emission monitoring and positioning generated by the space debris impact structure, and provide the method for monitoring the space debris impact on the in-orbit spacecraft based on the passive monitoring mode.
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In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments of the present invention will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the contents of the embodiments of the present invention and the drawings without creative efforts.
FIG. 1 is a schematic flow chart of a method for monitoring the impact of space debris on an in-orbit spacecraft according to the invention;
FIG. 2 is a diagram of a hardware implementation of the method for monitoring the impact of space debris on an in-orbit spacecraft of the present invention;
FIG. 3 is a schematic illustration of a monitoring trigger for the ultrasound monitoring data of FIG. 1;
fig. 4 is a schematic structural diagram of a system for monitoring the impact of space debris on an in-orbit spacecraft.
Detailed Description
In order to make the technical problems solved, technical solutions adopted and technical effects achieved by the present invention clearer, the technical solutions of the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention provides a method for monitoring space debris impact on an in-orbit spacecraft, which comprises the following steps: respectively acquiring corresponding target ultrasonic signals through a plurality of ultrasonic sensors, wherein the target ultrasonic signals are ultrasonic signals which are generated when an in-orbit spacecraft is impacted by space debris and are transmitted along the structure of the in-orbit spacecraft; amplifying and gain processing is carried out on each target ultrasonic signal to obtain ultrasonic monitoring data; when any ultrasonic monitoring data is judged to exceed a preset trigger threshold value, acquiring and storing specific ultrasonic monitoring data, wherein the specific ultrasonic monitoring data are ultrasonic monitoring data of all ultrasonic sensors within a preset trigger time; and when all the ultrasonic monitoring data are judged not to reach the preset triggering threshold value, reading the stored specific ultrasonic monitoring data, and analyzing and calculating according to the specific ultrasonic monitoring data to obtain the impact position and the impact strength of the in-orbit spacecraft.
Referring to fig. 1 and fig. 2, fig. 1 is a schematic flow chart of a method for monitoring an in-orbit spacecraft from space debris impact according to the present invention, and fig. 2 is a structural diagram of a hardware implementation of the method for monitoring the in-orbit spacecraft from space debris impact according to the present invention. The method for monitoring the space debris impact on the in-orbit spacecraft, which is described in the embodiment, comprises the following steps:
step 101: the method comprises the steps of respectively acquiring corresponding target ultrasonic signals through a plurality of ultrasonic sensors, wherein the target ultrasonic signals are ultrasonic signals which are generated when an in-orbit spacecraft is impacted by space debris and are transmitted along the structure of the in-orbit spacecraft.
In the specific implementation, the passive ultrasonic sensor is used as an ultrasonic signal acquisition sensitive device, when the in-orbit spacecraft is impacted by space debris, ultrasonic signals transmitted along the structure of the in-orbit spacecraft can be generated, the plurality of ultrasonic sensors are arranged at different positions on the structure of the in-orbit spacecraft, and therefore target ultrasonic signals generated at a plurality of specific positions can be acquired through the plurality of ultrasonic sensors, and the acquired target ultrasonic signals are converted into charge signals to be output. In this embodiment, four ultrasonic sensors are used, which are mounted on an in-orbit spacecraft structure.
Step 102: and carrying out amplification gain processing on each target ultrasonic signal to obtain ultrasonic monitoring data.
In specific implementation, after a plurality of target ultrasonic signals corresponding to a plurality of ultrasonic sensors are acquired, the target ultrasonic signals are charge signals and need to be converted into voltage signals and subjected to amplification gain, and meanwhile, the voltage signals are also subjected to adjustment filtering. Namely, the step of performing amplification gain processing on each target ultrasonic signal to obtain ultrasonic monitoring data comprises the following steps:
converting each target ultrasonic signal into a voltage signal, and carrying out primary amplification on the voltage signal to a preset voltage value;
adjusting the voltage signal after the first-stage amplification to an analog signal of which the center zero position is at a preset zero value;
performing primary filtering on the analog signal after zero setting;
performing secondary amplification on the filtered analog signal according to a preset gain coefficient;
and carrying out voltage following on the analog signal subjected to secondary amplification and then converting the analog signal into a digital signal to obtain ultrasonic monitoring data.
In this embodiment, the preset voltage value is 10mV to 200 mV. After the analog signal after zero adjustment is primarily filtered, the input noise of the secondary amplified signal can be reduced.
In this embodiment, the preset zero value is 2.5V, and certainly, the preset zero value may also be a certain value in 0-5V (i.e., the level range of the system to the sensor input signal), as long as the secondary amplification of the subsequent signal is not affected.
The two-stage amplification can realize controllable gain of input signals, namely, the signals can be set with gain coefficients according to command words, and the signals are amplified to a proper standard when being input to the rear-end AD signals, so that the on-orbit spacecraft fragment impact sensing requirements of different structures are met.
It should be noted that, in the present invention, the functions of the first-stage amplification, the filtering and the second-stage amplification of the target ultrasonic signal may be integrated in the ultrasonic sensor (the analog signal conditioning function is integrated), and the function of the digital-to-analog conversion after the second-stage amplification is completed by the signal processing unit, that is, the small signal output by the ultrasonic sensor is transmitted to the signal processing unit through the coaxial shielded cable, and the impedance of the ultrasonic sensor and the signal processing unit is matched by the signal following.
In this embodiment, a multi-channel AD parallel sampling mode is adopted for the analog signal after the second-stage amplification, the acquisition rate is 6MHz, and the sampling precision is 14 bits.
Step 103: judging whether any ultrasonic monitoring data exceeds a preset trigger threshold value, if so, executing step 104; if not, go to step 105.
Step 104: and acquiring and storing specific ultrasonic monitoring data, wherein the specific ultrasonic monitoring data are ultrasonic monitoring data of all ultrasonic sensors within a preset trigger time.
During specific implementation, each ultrasonic sensor outputs ultrasonic monitoring data to the signal processing unit for processing, namely, a plurality of ultrasonic monitoring channels are formed, and the ultrasonic monitoring data are continuously output within monitoring time. The signal processing unit needs to buffer the data of the multiple ultrasonic monitoring channels in real time to output 1ms data before judging the ultrasonic monitoring data, buffer the data of each ultrasonic monitoring channel in real time in the running process of software, and judge the ultrasonic monitoring data output by each ultrasonic sensor.
Referring to fig. 3, fig. 3 is a schematic diagram illustrating triggering of monitoring of the ultrasound monitoring data in fig. 1. When ultrasonic monitoring data output by a certain ultrasonic sensor is cached by a signal processing unit, a judgment module (such as an FPGA) in the signal processing unit reads the ultrasonic monitoring data and judges whether a trigger threshold value is preset or not, and because an ultrasonic input signal vibrates up and down by taking a central zero position O as a center, two threshold values of an upper limit value A and a lower limit value B need to be set for carrying out super-threshold monitoring judgment.
In this embodiment, the preset trigger time may be from 1ms before the trigger time to 1ms after the trigger condition is not satisfied, or from 100us before the trigger time to about 1ms after the trigger condition is not satisfied, and may be specifically set and adjusted as needed. In fig. 2, T1 and T5 are the time 1ms before the trigger time meeting the recording requirement, and T2 and T6 are the trigger times meeting the recording requirement; t3, T7: the trigger time which does not meet the recording requirement is T4 and T8 which are 1ms after the trigger time which does not meet the recording requirement, so the recording time of the specific ultrasonic monitoring data is T1-T4 and T5-T8.
The signal processing unit needs to perform trigger threshold judgment on the ultrasonic monitoring data of all the ultrasonic sensors, and as long as any one of the ultrasonic monitoring data exceeds a preset trigger threshold, the specific ultrasonic monitoring data of all the ultrasonic monitoring channels within a preset trigger time (from 1ms before the trigger time to 1ms after the trigger condition is not met) needs to be acquired and stored. In this embodiment, the acquisition and storage of the specific ultrasound monitoring data of all the ultrasound monitoring channels are realized in a FIFO (First Input First Output) manner.
Step 105: and reading the stored specific ultrasonic monitoring data, and analyzing and calculating according to the specific ultrasonic monitoring data to obtain the impact position and the impact strength of the in-orbit spacecraft.
During specific implementation, when all the ultrasonic monitoring data are judged not to reach the preset trigger threshold value, the system is idle at the moment, the signal processing unit reads back the specific ultrasonic monitoring data of each ultrasonic sensor channel before, and the impact position and the impact strength of the in-orbit spacecraft are obtained through CPU analysis and calculation.
The step of analyzing and calculating the impact position and the impact strength of the in-orbit spacecraft according to the specific ultrasonic monitoring data specifically comprises the following steps:
carrying out target ultrasonic signal feature identification and impact occurrence time point confirmation according to the specific ultrasonic monitoring data;
calculating the impact position of the in-orbit spacecraft by a time difference positioning method according to the characteristics of the target ultrasonic signal, the impact occurrence time point and the distribution position of the ultrasonic sensor;
and estimating the impact strength of the in-orbit spacecraft according to the energy analysis of the specific ultrasonic monitoring data.
It should be noted that in the present invention, the storage array is used to improve the data storage efficiency, that is, the data cross storage mode is used to implement the high-speed sampling data storage of the multi-channel ultrasonic sensor, and in fig. 2, the four cross storage arrays of the cross storage array 1, the cross storage array 2, the cross storage array 3, and the cross storage array 4 are used to store data in this embodiment. The ultrasonic monitoring data is managed through the data cross storage array and the address pointer, meanwhile, the storage array supports multi-time trigger data partition storage, the problem that a data storage array bus is occupied and analysis data cannot be read due to the fact that a threshold value trigger recording event occurs in the data resolving period is solved, and the working efficiency of the system is improved.
After the impact position and the impact strength of the in-orbit spacecraft are obtained through analysis and calculation, the invention sends remote measurement information such as impact time, impact positioning and the like to the satellite through the bus, and monitors the original ultrasonic data through the storage abnormal time of a downlink system of a high-speed data downlink. The invention supports 16-channel (channel) ultrasonic sensor signal monitoring and supports channel expansion.
In addition, referring to fig. 4, the present invention further provides a system for monitoring an on-orbit spacecraft from being hit by space debris, the system comprising:
a plurality of ultrasonic sensors 10 for acquiring corresponding target ultrasonic signals, wherein the target ultrasonic signals are ultrasonic signals generated when the in-orbit spacecraft is impacted by space debris and propagated along the in-orbit spacecraft structure;
the amplification gain module 20 is configured to perform amplification gain processing on each target ultrasonic signal to obtain ultrasonic monitoring data;
the judging module 30 is configured to judge whether any one of the ultrasonic monitoring data exceeds a preset trigger threshold;
the acquisition and storage module 40 is configured to acquire and store specific ultrasonic monitoring data when it is determined that any one of the ultrasonic monitoring data exceeds a preset trigger threshold, where the specific ultrasonic monitoring data is ultrasonic monitoring data of all ultrasonic sensors in a preset trigger duration;
and the analysis and calculation module 50 is configured to, when it is determined that all the ultrasonic monitoring data do not reach the preset trigger threshold, read the specific ultrasonic monitoring data, and analyze and calculate the impact position and the impact strength of the in-orbit spacecraft according to the specific ultrasonic monitoring data.
It should be noted that, in this embodiment, the preset trigger time may be from 1ms before the trigger time to 1ms after the trigger condition is not satisfied, or from 100us before the trigger time to about 1ms after the trigger condition is not satisfied, and may be specifically set and adjusted as needed.
Wherein the amplification gain module 20 further comprises:
the primary amplification submodule 201 is used for converting each target ultrasonic signal into a voltage signal and performing primary amplification on the voltage signal to a preset voltage value;
the zero adjustment submodule 202 is configured to adjust the voltage signal after the first-stage amplification to an analog signal with a center zero at a preset zero value;
the filtering submodule 203 is used for performing primary filtering on the analog signal after the zero setting;
the secondary amplification sub-module 204 is used for performing secondary amplification on the filtered analog signal;
and the signal following and analog-to-digital conversion sub-module 205 is used for performing voltage following on the secondarily amplified analog signal and then converting the secondarily amplified analog signal into a digital signal to obtain ultrasonic monitoring data.
The preset trigger threshold comprises an upper limit value and a lower limit value which take a central zero position as a center; the collection and storage module 40 is a cross storage array.
The analysis calculation module 50 further includes:
the recognition and confirmation submodule 501 is configured to perform target ultrasonic signal feature recognition and impact occurrence time point confirmation according to the specific ultrasonic monitoring data;
the position calculation submodule 502 is used for calculating the impact position of the in-orbit spacecraft by a time difference positioning method according to the characteristics of the target ultrasonic signal, the impact occurrence time point and the distribution position of the ultrasonic sensor;
and the intensity estimation submodule 503 is used for estimating the impact intensity of the in-orbit spacecraft according to the energy analysis of the specific ultrasonic monitoring data.
Compared with the prior art, the method and the system for monitoring the space debris impact on the in-orbit spacecraft have the following beneficial effects:
1. a passive ultrasonic sensor is used as an ultrasonic signal acquisition sensitive device, and an ultrasonic signal is not actively transmitted to monitor structural damage, so that acoustic emission monitoring and positioning generated by space debris impacting a structure can be realized;
2. the method can perform corresponding signal identification mode adjustment, gain adjustment and system expansion aiming at the rigid structure body requirements of different in-orbit spacecrafts such as satellites, manned/carried spacecrafts, space vehicles, space/extraterrestrial immigration cabins and the like, provides data support such as structural health monitoring, damage assessment, in-orbit maintenance and the like, and has wide popularization prospect and application value.
In summary, the method and the system for monitoring the space debris impact on the in-orbit spacecraft adopt the passive ultrasonic sensor as an ultrasonic signal acquisition sensitive device, can perform corresponding signal identification mode adjustment, gain adjustment and system expansion aiming at the requirements of rigid structures of different in-orbit spacecrafts, and realize acoustic emission monitoring and positioning generated by the space debris impact structure through a passive ultrasonic monitoring mode.
It is to be noted that the foregoing is only illustrative of the preferred embodiments of the present invention and the technical principles employed. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.
Claims (8)
1. A method for monitoring an in-orbit spacecraft from space debris impact, the method comprising the steps of:
respectively acquiring corresponding target ultrasonic signals through a plurality of ultrasonic sensors, wherein the target ultrasonic signals are ultrasonic signals which are generated when an in-orbit spacecraft is impacted by space debris and are transmitted along the structure of the in-orbit spacecraft;
amplifying and gain processing is carried out on each target ultrasonic signal to obtain ultrasonic monitoring data;
when any ultrasonic monitoring data is judged to exceed a preset trigger threshold value, acquiring and storing specific ultrasonic monitoring data, wherein the specific ultrasonic monitoring data are ultrasonic monitoring data of all ultrasonic sensors within a preset trigger time;
when all the ultrasonic monitoring data are judged to not reach a preset triggering threshold value, reading the stored specific ultrasonic monitoring data, and analyzing and calculating according to the specific ultrasonic monitoring data to obtain the impact position and the impact strength of the in-orbit spacecraft; wherein,
the step of obtaining ultrasonic monitoring data by performing amplification gain processing on each target ultrasonic signal comprises the following steps:
converting each target ultrasonic signal into a voltage signal, and carrying out primary amplification on the voltage signal to a preset voltage value, wherein the preset voltage value is 10 mV-200 mV;
adjusting the voltage signal after the first-stage amplification to an analog signal of which the center zero position is at a preset zero value;
performing primary filtering on the analog signal after zero setting;
performing secondary amplification on the filtered analog signal according to a preset gain coefficient;
and carrying out voltage following on the analog signal subjected to secondary amplification and then converting the analog signal into a digital signal to obtain ultrasonic monitoring data.
2. The method according to claim 1, wherein the preset trigger threshold comprises an upper limit value and a lower limit value centered on a central zero position.
3. A method of monitoring exposure of an in-orbit spacecraft to space debris impact as claimed in claim 2 wherein the specific ultrasound monitoring data is collected and stored by a cross-memory array.
4. The method for monitoring the collision of the in-orbit spacecraft with the space debris according to claim 1, wherein the step of analyzing and calculating the collision position and the collision strength of the in-orbit spacecraft according to the specific ultrasonic monitoring data specifically comprises the following steps:
carrying out target ultrasonic signal feature identification and impact occurrence time point confirmation according to the specific ultrasonic monitoring data;
calculating the impact position of the in-orbit spacecraft by a time difference positioning method according to the characteristics of the target ultrasonic signal, the impact occurrence time point and the distribution position of the ultrasonic sensor;
and estimating the impact strength of the in-orbit spacecraft according to the energy analysis of the specific ultrasonic monitoring data.
5. An in-orbit spacecraft space debris impact monitoring system, the system comprising:
the system comprises a plurality of ultrasonic sensors, a plurality of ultrasonic sensors and a controller, wherein the ultrasonic sensors are used for acquiring corresponding target ultrasonic signals, and the target ultrasonic signals are ultrasonic signals generated when an in-orbit spacecraft is impacted by space debris and propagated along the structure of the in-orbit spacecraft;
the amplification gain module is used for performing amplification gain processing on each target ultrasonic signal to obtain ultrasonic monitoring data;
the judging module is used for judging whether any ultrasonic monitoring data exceeds a preset triggering threshold value;
the acquisition and storage module is used for acquiring and storing specific ultrasonic monitoring data when judging that any ultrasonic monitoring data exceeds a preset trigger threshold, wherein the specific ultrasonic monitoring data are ultrasonic monitoring data of all ultrasonic sensors in a preset trigger time;
the analysis and calculation module is used for reading the stored specific ultrasonic monitoring data when judging that all the ultrasonic monitoring data do not reach the preset trigger threshold value, and analyzing and calculating the impact position and the impact strength of the in-orbit spacecraft according to the specific ultrasonic monitoring data; wherein,
the amplification gain module further comprises:
the primary amplification submodule is used for converting each target ultrasonic signal into a voltage signal and performing primary amplification on the voltage signal to a preset voltage value, wherein the preset voltage value is 10 mV-200 mV;
the zero adjustment submodule is used for adjusting the voltage signal after the primary amplification to an analog signal of which the center zero is at a preset zero value;
the filtering submodule is used for carrying out primary filtering on the analog signal after the zero setting;
the second-stage amplification submodule is used for carrying out second-stage amplification on the filtered analog signal;
and the signal following and analog-to-digital conversion submodule is used for carrying out voltage following on the analog signal after secondary amplification and then converting the analog signal into a digital signal to obtain ultrasonic monitoring data.
6. The in-orbit spacecraft space debris impact monitoring system of claim 5, wherein the preset trigger threshold comprises an upper limit value and a lower limit value centered at a central zero position.
7. The in-orbit spacecraft space debris impact monitoring system of claim 6, wherein the acquisition storage module is a crossbar storage array.
8. The in-orbit spacecraft space debris impact monitoring system of claim 5, wherein the analytical computation module further comprises:
the identification and confirmation submodule is used for identifying the characteristics of the target ultrasonic signal and confirming the impact occurrence time point according to the specific ultrasonic monitoring data;
the position calculation submodule is used for calculating the impact position of the in-orbit spacecraft by a time difference positioning method according to the characteristics of the target ultrasonic signal, the impact occurrence time point and the distribution position of the ultrasonic sensor;
and the intensity estimation submodule is used for estimating the impact intensity of the in-orbit spacecraft according to the energy analysis of the specific ultrasonic monitoring data.
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