CN119197919A - On-orbit leak detection method and equipment for spacecraft cabin - Google Patents
On-orbit leak detection method and equipment for spacecraft cabin Download PDFInfo
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Abstract
本发明提供航天器舱段在轨检漏方法及设备，应用于航天器舱段在轨检漏装置，该方法包括：将航天器舱段在轨检漏装置设置于目标位置；获取每个阵列面的每个传感器在第一预设时间段内采集到的数据，并对每个传感器采集到的数据进行短时傅里叶变换，得到每个阵列面的初始正常数据；基于每个阵列面的初始正常数据获取每个阵列面在不同频带下的幅值随时间变化的本底数据；每隔预定时间基于每个阵列面的初始正常数据获取在第二预设时间段内的每个阵列面在不同频带下的幅值随时间变化的实时信号特征；将本底数据与实时信号特征进行对比得到对比结果，并基于对比结果确定航天器舱段的泄露位置，从而实现对航天器舱段泄露状态的实时监测及泄漏位置的准确定位。
The present invention provides a method and equipment for on-orbit leakage detection of spacecraft cabins, which are applied to an on-orbit leakage detection device for spacecraft cabins. The method comprises: setting the on-orbit leakage detection device for spacecraft cabins at a target position; acquiring data collected by each sensor of each array surface within a first preset time period, and performing short-time Fourier transform on the data collected by each sensor to obtain initial normal data of each array surface; acquiring background data of amplitude variation over time of each array surface in different frequency bands based on the initial normal data of each array surface; acquiring real-time signal characteristics of amplitude variation over time of each array surface in different frequency bands within a second preset time period based on the initial normal data of each array surface at predetermined intervals; comparing the background data with the real-time signal characteristics to obtain a comparison result, and determining the leakage position of the spacecraft cabin based on the comparison result, thereby achieving real-time monitoring of the leakage state of the spacecraft cabin and accurate positioning of the leakage position.
Description
Technical Field
The embodiment of the specification relates to the technical field of spacecraft leakage detection, in particular to a method and equipment for on-orbit leakage detection of a spacecraft cabin.
Background
Aiming at the problems that large spacecrafts such as space stations and the like are extremely easy to be influenced by space fragments and space environment during the on-orbit running process, the cabin body is damaged to leak, and the life safety of astronauts is directly threatened.
The on-orbit leakage detection method is implemented for large-scale long-term on-orbit resident multi-cabin sections such as space stations, cargo ships, manned spacecraft and the like. The method is mainly characterized in that the cabin body is complex in internal structure, a plurality of layers, cargoes and the like are piled to block the cabin wall and block the transmission and characteristic frequency of effective signals, meanwhile, the detected continuous and weak signals of broadband leakage sound signals have frequency shift phenomena when leakage of different holes, audible sound and ultrasonic parts exist, the audible sound signals are influenced by background noise in a sealed cabin, the ultrasonic signals are accumulated and blocked by cargoes and the like to attenuate and influence the penetrability and the characteristic frequency of the cabin, meanwhile, 360-degree monitoring is needed in real time, so that after the long-term on-orbit resident multi-cabin-section butt joint is carried out, the cabin section is simultaneously and simultaneously, if the on-orbit leakage occurs, the specific failed cabin section or cabin body cannot be judged quickly, and the complex structure, the multi-layer fabric cargo pile blocking, the noise of instruments and equipment in the complex cabin and the like are faced, so that the on-orbit leakage judgment of the cabin section is difficult to realize.
Thus, a better solution is needed.
Disclosure of Invention
In view of this, embodiments of the present disclosure provide a method for on-orbit leak detection of a spacecraft cabin. One or more embodiments of the present specification are also directed to an on-orbit leak detection apparatus for a spacecraft cabin, a computing device, a computer readable storage medium, and a computer program, which address the technical deficiencies of the prior art.
According to a first aspect of embodiments of the present disclosure, an on-orbit leakage detection method for a spacecraft cabin is provided, and the on-orbit leakage detection method is applied to an on-orbit leakage detection device for a spacecraft cabin, where the device at least includes an empty-coupled broadband acoustic cube, 8 empty-coupled broadband acoustic sensors are disposed on each array surface of the empty-coupled broadband acoustic cube, and 8 empty-coupled broadband acoustic sensors on the same array surface are arranged in an equally-divided annular manner for one week, and the method includes:
when the spacecraft is in a cabin leak detection stage, arranging the on-orbit leak detection device of the spacecraft cabin at a target position;
acquiring data acquired by each sensor of each array surface in a first preset time period, and performing short-time Fourier transform on the data acquired by each sensor to obtain initial normal data of each array surface;
Acquiring background data of amplitude values of each array surface under different frequency bands, which change with time, based on the initial normal data of each array surface;
Acquiring real-time signal characteristics of amplitude values of each array surface in different frequency bands in a second preset time period according to the initial normal data of each array surface at intervals of preset time;
and comparing the background data with the real-time signal characteristics to obtain a comparison result, and determining the leakage position of the spacecraft cabin based on the comparison result.
In one possible implementation manner, when a spacecraft is in a cabin leak detection stage, the on-orbit leakage detection device for the spacecraft cabin is arranged at a target position, and the on-orbit leakage detection device comprises:
Based on the shapable spring, the spacecraft cabin on-orbit leakage detection device is hung into a cabin to be detected of a spacecraft, and the hanging height of the spacecraft cabin on-orbit leakage detection device is adjusted, so that the spacecraft cabin on-orbit leakage detection device is located at the center position of the cabin to be detected, one end of the shapable spring is connected with the spacecraft cabin on-orbit leakage detection device through plugs of 3 locating pins, and the other end of the shapable spring is adhered to the cabin to be detected through nylon sticking buckles.
In one possible implementation manner, obtaining background data of amplitude variation of each array surface under different frequency bands with time based on the initial normal data of each array surface includes:
carrying out short-time Fourier transform on each channel signal in the initial normal data of each array surface to obtain first change data of each channel, wherein each channel signal is the initial normal data corresponding to each sensor;
And averaging the sum of the first change data of each channel on the same array surface to obtain a first average value, and taking the first average value as background data of the amplitude of each array surface, which changes with time, under different frequency bands.
In one possible implementation manner, comparing the background data with the real-time signal features to obtain a comparison result, and determining the leakage position of the spacecraft cabin based on the comparison result, including:
When the amplitude value in the real-time signal characteristic is higher than the amplitude average value of the background data, the real-time signal characteristic comprises new frequency which does not exist in the background data, and the duration of the new frequency exceeds the first duration, taking the real-time signal characteristic of the frequency band where the new frequency is positioned as a target signal characteristic;
if the signal characteristics in the preset ground verification database are consistent with the frequency characteristics of the target signal characteristics, the real-time signal characteristics of the array surface corresponding to the new frequency are collected again;
if the new frequency still exists in the re-acquired real-time signal characteristics, leakage exists in the array surface corresponding to the new frequency, and the leakage position is determined based on the first change data of each channel in the array surface with the leakage.
In one possible implementation, determining the location of the leak based on the first variation data for each channel in the array face where the leak exists includes:
And comparing the first variation data of each channel in the array surface with the leakage, and taking the channel with the largest first variation data as the leakage direction.
In one possible implementation manner, the signal characteristics in the preset ground verification database and the target signal characteristics are obtained based on the following formula, including:
Wherein, For the target signal feature, an is a weight, pi (j) (fn, t) is first variation data, j is a sensor number on each array face, f is a frequency, t is a time,And verifying the signal characteristics in the database for the preset ground.
In one possible implementation, the method further includes:
When the frequency band misalignment exists between the signal characteristics in the preset ground verification database and the target signal characteristics, continuously and repeatedly acquiring the real-time signal characteristics of the array surface corresponding to the new frequency, and writing the frequency band characteristic points and the amplitude in the target signal characteristics into the preset ground verification database.
According to a second aspect of embodiments of the present disclosure, there is provided an on-orbit leakage detection device for a spacecraft cabin, the device at least includes an empty-coupled wideband acoustic cube, 8 empty-coupled wideband acoustic sensors are disposed on each array surface of the empty-coupled wideband acoustic cube, and 8 empty-coupled wideband acoustic sensors on the same array surface are arranged in an equally-divided annular shape for one week, the device includes:
the device setting module is used for setting the on-orbit leakage detection device of the spacecraft cabin at a target position when the spacecraft is in the cabin leakage detection stage;
The initial transformation module is used for acquiring data acquired by each sensor of each array surface in a first preset time period, and performing short-time Fourier transformation on the data acquired by each sensor to acquire initial normal data of each array surface;
the background data acquisition module is used for acquiring background data of amplitude values of each array surface under different frequency bands, which change with time, based on the initial normal data of each array surface;
the real-time signal characteristic acquisition module is used for acquiring real-time signal characteristics of amplitude values of each array surface in different frequency bands in a second preset time period along with time based on the initial normal data of each array surface at intervals of preset time;
and the leakage position determining module is used for comparing the background data with the real-time signal characteristics to obtain a comparison result and determining the leakage position of the spacecraft cabin based on the comparison result.
According to a third aspect of embodiments of the present specification, there is provided a computing device comprising:
A memory and a processor;
The memory is used for storing computer executable instructions, and the processor is used for executing the computer executable instructions, and the computer executable instructions realize the steps of the on-orbit leakage detection method for the spacecraft cabin when being executed by the processor.
According to a fourth aspect of embodiments of the present description, there is provided a computer-readable storage medium storing computer-executable instructions which, when executed by a processor, implement the steps of the above-described spacecraft cabin on-orbit leak detection method.
According to a fifth aspect of embodiments of the present specification, there is provided a computer program, wherein the computer program, when executed in a computer, causes the computer to perform the steps of the above-described spacecraft cabin on-orbit leak detection method.
The embodiment of the specification provides an on-orbit leakage detection method and equipment for a spacecraft cabin, wherein the on-orbit leakage detection method for the spacecraft cabin is applied to an on-orbit leakage detection device for the spacecraft cabin, the device at least comprises an empty coupling broadband acoustic cube, 8 empty coupling broadband acoustic sensors are arranged on each array surface of the empty coupling broadband acoustic cube, the 8 empty coupling broadband acoustic sensors on the same array surface are arrayed for a circle according to an equally-divided annular mode, the method comprises the steps of setting the on-orbit leakage detection device for the spacecraft cabin at a target position when the spacecraft is in a cabin leakage detection stage, acquiring data acquired by each sensor of each array surface in a first preset time period, performing short-time Fourier transform on the data acquired by each sensor to obtain initial normal data of each array surface, acquiring data of each array surface changing with time under different frequency bands based on the initial normal data of each array surface, comparing the acquired amplitude value of each array surface with the background signal in different frequency bands based on the preset time period every preset time period with the initial normal data of each array surface, and comparing the obtained amplitude value with the real-time signal of each array surface to obtain a real-time comparison result. Through the steps, the real-time monitoring of the leakage state of the spacecraft cabin and the accurate positioning of the leakage position are realized.
Drawings
FIG. 1 is a flow chart of a method for on-orbit leak detection of a spacecraft cabin according to an embodiment of the present disclosure;
Fig. 2 is a schematic structural diagram of an on-orbit leakage detection device for a spacecraft cabin according to an embodiment of the present disclosure;
fig. 3 is a schematic circuit configuration diagram of a power panel according to an embodiment of the present disclosure;
Fig. 4 is a schematic structural diagram of an on-orbit leakage detection device for a spacecraft cabin according to an embodiment of the disclosure;
FIG. 5 is a block diagram of a computing device provided in one embodiment of the present description.
Detailed Description
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present description. This description may be embodied in many other forms than described herein and similarly generalized by those skilled in the art to whom this disclosure pertains without departing from the spirit of the disclosure and, therefore, this disclosure is not limited by the specific implementations disclosed below.
The terminology used in the one or more embodiments of the specification is for the purpose of describing particular embodiments only and is not intended to be limiting of the one or more embodiments of the specification. As used in this specification, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used in one or more embodiments of the present specification refers to and encompasses any or all possible combinations of one or more of the associated listed items.
It should be understood that, although the terms first, second, etc. may be used in one or more embodiments of this specification to describe various information, these information should not be limited by these terms. These terms are only used to distinguish one type of information from another. For example, a first may also be referred to as a second, and similarly, a second may also be referred to as a first, without departing from the scope of one or more embodiments of the present description. The term "if" as used herein may be interpreted as "at..once" or "when..once" or "in response to a determination", depending on the context.
In this specification, an on-orbit leakage detection method for a spacecraft cabin is provided, and the specification relates to an on-orbit leakage detection device for a spacecraft cabin, a computing device and a computer readable storage medium, and is described in detail in the following examples one by one.
Referring to fig. 1, fig. 1 shows a flowchart of an on-orbit leakage detection method for a spacecraft cabin, which is provided according to an embodiment of the present disclosure, and the method is applied to an on-orbit leakage detection device for a spacecraft cabin, where the device at least includes an empty-coupled broadband acoustic cube, 8 empty-coupled broadband acoustic sensors are disposed on each array surface of the empty-coupled broadband acoustic cube, and the 8 empty-coupled broadband acoustic sensors on the same array surface are arranged in an equally-divided annular form for one week, and specifically includes the following steps.
Step 101, when the spacecraft is in a cabin leak detection stage, setting the on-orbit leak detection device of the spacecraft cabin at a target position.
In one possible implementation manner, when a spacecraft is in a cabin leak detection stage, the on-orbit leakage detection device for the spacecraft cabin is arranged at a target position, and the on-orbit leakage detection device comprises:
Based on the shapable spring, the spacecraft cabin on-orbit leakage detection device is hung into a cabin to be detected of a spacecraft, and the hanging height of the spacecraft cabin on-orbit leakage detection device is adjusted, so that the spacecraft cabin on-orbit leakage detection device is located at the center position of the cabin to be detected, one end of the shapable spring is connected with the spacecraft cabin on-orbit leakage detection device through plugs of 3 locating pins, and the other end of the shapable spring is adhered to the cabin to be detected through nylon sticking buckles.
In practical application, referring to fig. 2, the on-orbit leakage detection device for the spacecraft cabin section at least comprises an empty coupling broadband acoustic cube, the cube is composed of 6 array surfaces, 8 empty coupling broadband acoustic sensors are arranged on each array surface, and are uniformly and uniformly arranged on the surface of the array surface in a mode shown in fig. 2, and a circle is formed, so that all-dimensional perception of leakage acoustic signals along air propagation is realized.
Furthermore, the on-orbit leakage detection device for the spacecraft cabin can further comprise 1 FPGA core signal processing module, 1 power supply module, 1 switch, 1 external electric connector, 4 lithium battery packs, 1 spiral semi-flexible suspension deformable spring with 3 fixed positions, 6 wifi communication modules and 6 alarm lamps, as shown in fig. 2, and is different from the traditional ADC analog sampling operation mechanism, and the sensor is fixed on a circuit board. The array signal line, the power line and the ground line are led out by adopting custom plugs, and power supply and signal transmission are realized through a data bus. The surface of the circuit board is covered with a layer of plastic board with the same height as the sensor, the surface is flush, the circuit board is embedded into the mounting template and can be integrally mounted on the measuring model, and independently output signals and power supply are connected to the FPGA core signal processing module through flexible flat cables for signal processing.
The 6 array surfaces are arranged on a structural plate with pick-up holes, a circuit fixing support is added on the structural plate, the 6 structural plates form 1 cube, an FPGA core signal processing module is arranged in the 6 structural plates, and a power supply module and a wifi communication module are arranged in the 6 structural plates. The lithium battery pack comprises a structural switch, 1 external electric connector, 4 lithium battery packs, a spiral semi-flexible fixable spring suspension with 1 fixing position 3 and 6 alarm lamps, wherein the 1 alarm lamps are arranged on a shell of the lithium battery packs and are arranged in the centers of four side faces of a cube structure in a direct plug-in mode, and the 1 alarm lamps are respectively arranged on the top face and the bottom face. The electrical connector is then placed on the bottom structural panel, the switch is arranged on the side face panel, and the semi-flexible settable spring is suspended on the top panel of the cube structure.
As shown in fig. 3, the FPGA core signal processing module in the device mainly uses 7020FPGA of the siren as a core processing unit, the output plug is connected to the FPGA processor to demodulate the signal, the data analysis and processing are performed through the ARM core in the FPGA, the data can be tested and analyzed through the upper computer of the internet access, and the ARM controls the IO port to drive the lamp on the central plane to alarm and flash after exceeding the alarm threshold, and controls the wifi module to transmit.
The wifi circuit module transmits the original data, the analyzed interpretation data and the alarm signal to the relay through the WI FI chip under the control of the FPGA and the ARM, and then alarms through an alarm lamp on the relay. The host module adopts a wifi chip of AW859A, supports I EEE 802.11a/b/g/n/ac, carries out signal transmission, and increases alarm data switching value transmission, as shown in figure 3.
The main functions of the power supply module comprise the steps of converting a 9-12V power supply of the lithium battery into a 5V/+/-12V power supply required by the FPGA board and the sensor board, collecting the battery voltage and the battery temperature telemetry of the lithium battery, and simultaneously completing AD collection of ultrasonic signals output by the sensor board and DA conversion output of audio signals. The power panel mainly comprises a fuse protection circuit, a surge suppression circuit, a power conversion circuit, an AD conversion circuit, an audio conversion circuit and a battery voltage/temperature telemetry circuit, and the schematic block diagram of the power panel is shown in fig. 3.
The power supply conversion circuit adopts an LTM4644 voltage regulator manufactured by LINEAR company to convert 9-12V power supply into +5V and +3.3V power supply, and adopts an LT3582 power supply converter to convert +5V power supply output by the LTM4644 into +12V power supply to supply power to the FPGA board and the sensor board respectively. The input voltage range of the LTM4644 is +4-14V, the output voltage is +5V, the rated working current is 4A, the actual working current is not more than 2A, and the working temperature range is-40 to +125 ℃. The input voltage range of LT3582 is +3~12V, the output voltage is + -12V, rated working current is 300mA, actual working current is not more than 20mA, working temperature range is-40 to +125 ℃. The interface design of the power supply part mainly relates to a self battery power supply interface, an external power supply interface, a power panel input/output interface and the like. The battery power supply interface adopts a two-pin positive and negative direct current power supply mode and adopts a pin mode, and the power panel is powered by a battery and externally powered, realizes voltage conversion through a conversion circuit and transmits the voltage conversion to other circuits.
The battery pack adopts 18650 lithium battery packs, supplies 12VDC, has a capacity superior to that of 3000mAh and 3 strings, and is connected by adopting Y36A. During charging, the side slotted hole is removed and replaced, and the outside is charged, and the charger adopts an on-rail leak detector charger. The battery monomer is a cylindrical full-sealing structure, and the whole battery is composed of an anode, a cathode, a diaphragm, a safety valve, a Positive Temperature Control (PTC) terminal, a battery shell and the like. The design of the storage battery adopts the design of a negative electrode lap shell, and the battery shell is the negative electrode. An insulating measure is adopted between the anode and the shell. The external dimension of the 18650 battery is 18mm in diameter, 65mm in height and 45-49 g in weight.
The shapable spring is hung by bending a hard single-core thick copper cable with the diameter of 3mm, can be directly stretched and compressed by a human hand, keeps the shape and the position, realizes the position adjustment, has a nylon sticking buckle at the top end, and can be directly stuck. The plugs with 3 positioning pins at the bottoms are directly inserted into the positioning grooves at the top ends of the devices to be fixed, and then hanging and fixing can be completed.
Further, after the leak detection device is hung, the self-locking switch can be pressed, the equipment is turned on, monitoring is started, the power supply lamp is observed to be green, the power supply lamp is normal, and if the power supply lamp is not green, the leak detection device needs to be overhauled.
Step 102, acquiring data acquired by each sensor of each array surface in a first preset time period, and performing short-time Fourier transform on the data acquired by each sensor to obtain initial normal data of each array surface.
Specifically, starting from the start of the power-on, 1min is the start of noise floor test, each sensor of each array surface is detected, data are stored in each address in a memory, the data of 8 sensors of each array surface are analyzed, the time spectrum data obtained by the real-time short-time Fourier transform of 1min are stored in the memory and serve as initial normal data of each array surface, meanwhile, each channel signal is recorded as Fi (j), i is an array surface number, the value range is 0-5;j is the sensor number on each array surface, and the value range is 0-7.
Step 103, obtaining background data of amplitude values of each array surface under different frequency bands, which change with time, based on the initial normal data of each array surface.
In one possible implementation manner, obtaining background data of amplitude variation of each array surface under different frequency bands with time based on the initial normal data of each array surface includes:
carrying out short-time Fourier transform on each channel signal in the initial normal data of each array surface to obtain first change data of each channel, wherein each channel signal is the initial normal data corresponding to each sensor;
And averaging the sum of the first change data of each channel on the same array surface to obtain a first average value, and taking the first average value as background data of the amplitude of each array surface, which changes with time, under different frequency bands.
In practical application, short-time Fourier transform is performed on each channel signal Fi (j) in initial normal data of each array surface, frequency amplitude conditions of time variation can be obtained through the short-time Fourier transform, data obtained after the short-time Fourier transform of each channel are used as first variation data and are calculated as Pi (j) (f, t), wherein i and j are consistent with a sensor channel recording method, f is frequency, and t is time. After the time information is introduced, the amplitude and duration reflected on each primary frequency can be recorded. At the same time, the first change data of 8 channels are added and averaged to be calculated asAnd serves as a background for amplitude variation over time at different frequency bands of the array plane.
Step 104, acquiring real-time signal characteristics of amplitude changes of each array surface in different frequency bands with time in a second preset time period based on the initial normal data of each array surface at intervals of preset time.
Specifically, considering that long-term monitoring of the cabin of the spacecraft is required, detecting for 10min every 30min for controlling the electric quantity, wherein the detection of the real-time signal characteristics of the amplitude of each array surface under different frequency bands is consistent with the mode of acquiring the first change data, and the detected real-time signal characteristics of the amplitude of each array surface under different frequency bands are as follows
And 105, comparing the background data with the real-time signal characteristics to obtain a comparison result, and determining the leakage position of the spacecraft cabin based on the comparison result.
In one possible implementation manner, comparing the background data with the real-time signal features to obtain a comparison result, and determining the leakage position of the spacecraft cabin based on the comparison result, including:
When the amplitude value in the real-time signal characteristic is higher than the amplitude average value of the background data, the real-time signal characteristic comprises new frequency which does not exist in the background data, and the duration of the new frequency exceeds the first duration, taking the real-time signal characteristic of the frequency band where the new frequency is positioned as a target signal characteristic;
if the signal characteristics in the preset ground verification database are consistent with the frequency characteristics of the target signal characteristics, the real-time signal characteristics of the array surface corresponding to the new frequency are collected again;
if the new frequency still exists in the re-acquired real-time signal characteristics, leakage exists in the array surface corresponding to the new frequency, and the leakage position is determined based on the first change data of each channel in the array surface with the leakage.
In one possible implementation, determining the location of the leak based on the first variation data for each channel in the array face where the leak exists includes:
And comparing the first variation data of each channel in the array surface with the leakage, and taking the channel with the largest first variation data as the leakage direction.
In one possible implementation manner, the signal characteristics in the preset ground verification database and the target signal characteristics are obtained based on the following formula, including:
Wherein, For the target signal feature, an is a weight, pi (j) (fn, t) is first variation data, j is a sensor number on each array face, f is a frequency, t is a time,And verifying the signal characteristics in the database for the preset ground.
In one possible implementation, the method further includes:
When the frequency band misalignment exists between the signal characteristics in the preset ground verification database and the target signal characteristics, continuously and repeatedly acquiring the real-time signal characteristics of the array surface corresponding to the new frequency, and writing the frequency band characteristic points and the amplitude in the target signal characteristics into the preset ground verification database.
In practical application, willAnd (3) withComparing, and recording the situation that the new frequency appears and the duration exists or exists after the occurrence asNamely, the real-time signal characteristics of the array surface corresponding to the new frequency are preliminarily judged that suspicious leakage situations possibly occur, and then the data situations are compared with the signal characteristics in a preset ground verification databaseAnd comparing, namely, if the frequency characteristics are consistent, classifying the signals as target signal characteristics and further checking the target signal characteristics as key suspicious signals.
Further, based on step S104, after repeating the test for 10 minutes, it may be determined that there is a leak in the direction on the acoustic array surface, and the channel with the largest first variation data is used as the leak direction.
Further, after the leak detection is completed, if the frequency band misalignment exists between the signal characteristics in the preset ground verification database and the target signal characteristics, the continuous repeated detection times are increased, and the frequency band characteristic points and the amplitude in the target signal characteristics are written into the preset ground verification database to serve as a basic database for subsequent learning and training.
The embodiment of the specification provides an on-orbit leakage detection method and equipment for a spacecraft cabin, wherein the on-orbit leakage detection method for the spacecraft cabin is applied to an on-orbit leakage detection device for the spacecraft cabin, the device at least comprises an empty coupling broadband acoustic cube, 8 empty coupling broadband acoustic sensors are arranged on each array surface of the empty coupling broadband acoustic cube, the 8 empty coupling broadband acoustic sensors on the same array surface are arrayed for a circle according to an equally-divided annular mode, the method comprises the steps of setting the on-orbit leakage detection device for the spacecraft cabin at a target position when the spacecraft is in a cabin leakage detection stage, acquiring data acquired by each sensor of each array surface in a first preset time period, performing short-time Fourier transform on the data acquired by each sensor to obtain initial normal data of each array surface, acquiring data of each array surface changing with time under different frequency bands based on the initial normal data of each array surface, comparing the acquired amplitude value of each array surface with the background signal in different frequency bands based on the preset time period every preset time period with the initial normal data of each array surface, and comparing the obtained amplitude value with the real-time signal of each array surface to obtain a real-time comparison result. Through the steps, the real-time monitoring of the leakage state of the spacecraft cabin and the accurate positioning of the leakage position are realized.
Corresponding to the above method embodiment, the present disclosure further provides an embodiment of an on-orbit leakage detection device for a spacecraft cabin, and fig. 4 shows a schematic structural diagram of an on-orbit leakage detection device for a spacecraft cabin according to an embodiment of the present disclosure. The device is applied to an on-orbit leakage detection device for a spacecraft cabin, the device at least comprises an empty coupling broadband acoustic cube, 8 empty coupling broadband acoustic sensors are arranged on each array surface of the empty coupling broadband acoustic cube, and 8 empty coupling broadband acoustic sensors on the same array surface are arranged for a circle according to an equally-divided annular shape, as shown in fig. 4, the device comprises:
The device setting module 401 is configured to set the on-orbit leakage detection device for the spacecraft cabin at a target position when the spacecraft is in the cabin leakage detection stage;
The initial transformation module 402 is configured to obtain data collected by each sensor of each array surface in a first preset time period, and perform short-time fourier transformation on the data collected by each sensor to obtain initial normal data of each array surface;
a background data obtaining module 403, configured to obtain background data of amplitude values of each array surface under different frequency bands according to time variation based on the initial normal data of each array surface;
a real-time signal feature acquiring module 404, configured to acquire, at intervals of a predetermined time, real-time signal features of amplitude values of each array surface in different frequency bands in a second predetermined time period, which change with time, based on the initial normal data of each array surface;
The leakage position determining module 405 is configured to compare the background data with the real-time signal feature to obtain a comparison result, and determine a leakage position of the spacecraft cabin based on the comparison result.
The above is a schematic scheme of the on-orbit leakage detection device for the spacecraft cabin in the embodiment. It should be noted that, the technical scheme of the on-orbit leakage detection device for the spacecraft cabin section and the technical scheme of the on-orbit leakage detection method for the spacecraft cabin section belong to the same conception, and the details of the technical scheme of the on-orbit leakage detection device for the spacecraft cabin section, which are not described in detail, can be referred to the description of the technical scheme of the on-orbit leakage detection method for the spacecraft cabin section.
Fig. 5 illustrates a block diagram of a computing device 400 provided in accordance with one embodiment of the present description. The components of the computing device 400 include, but are not limited to, a memory 410 and a processor 420. Processor 420 is coupled to memory 410 via bus 430 and database 450 is used to hold data.
Computing device 400 also includes access device 440, access device 440 enabling computing device 400 to communicate via one or more networks 460. Examples of such networks include public switched telephone networks (PSTN, public Switched Telephone Network), local area networks (LAN, local Area Network), wide area networks (WAN, wide Area Network), personal area networks (PAN, personal Area Network), or combinations of communication networks such as the internet. The access device 440 may include one or more of any type of network interface, wired or wireless, such as a network interface card (NIC, network interface controller), such as an IEEE802.11 wireless local area network (WLAN, wireless Local Area Network) wireless interface, a worldwide interoperability for microwave access (Wi-MAX, worldwide Interoperability for Microwave Access) interface, an ethernet interface, a universal serial bus (USB, universal Serial Bus) interface, a cellular network interface, a bluetooth interface, near Field Communication (NFC).
In one embodiment of the present description, the above-described components of computing device 400, as well as other components not shown in FIG. 5, may also be connected to each other, such as by a bus. It should be understood that the block diagram of the computing device shown in FIG. 5 is for exemplary purposes only and is not intended to limit the scope of the present description. Those skilled in the art may add or replace other components as desired.
Computing device 400 may be any type of stationary or mobile computing device, including a mobile computer or mobile computing device (e.g., tablet, personal digital assistant, laptop, notebook, netbook, etc.), mobile phone (e.g., smart phone), wearable computing device (e.g., smart watch, smart glasses, etc.), or other type of mobile device, or a stationary computing device such as a desktop computer or personal computer (PC, personal Computer). Computing device 400 may also be a mobile or stationary server.
The processor 420 is configured to execute computer-executable instructions that, when executed by the processor, implement the steps of the above-described method for on-orbit leakage detection of a spacecraft cabin. The foregoing is a schematic illustration of a computing device of this embodiment. It should be noted that, the technical solution of the computing device and the technical solution of the above-mentioned on-orbit leakage detection method for the spacecraft cabin belong to the same concept, and details of the technical solution of the computing device, which are not described in detail, can be referred to the description of the technical solution of the above-mentioned on-orbit leakage detection method for the spacecraft cabin.
An embodiment of the present disclosure also provides a computer-readable storage medium storing computer-executable instructions that, when executed by a processor, implement the steps of the above-described spacecraft cabin on-orbit leak detection method.
The above is an exemplary version of a computer-readable storage medium of the present embodiment. It should be noted that, the technical scheme of the storage medium and the technical scheme of the on-orbit leakage detection method for the spacecraft cabin section belong to the same conception, and details of the technical scheme of the storage medium which are not described in detail can be referred to the description of the technical scheme of the on-orbit leakage detection method for the spacecraft cabin section.
An embodiment of the present disclosure further provides a computer program, where the computer program, when executed in a computer, causes the computer to perform the steps of the above-mentioned method for on-orbit leakage detection of a spacecraft cabin.
The above is an exemplary version of a computer program of the present embodiment. It should be noted that, the technical scheme of the computer program and the technical scheme of the on-orbit leakage detection method for the spacecraft cabin section belong to the same conception, and details of the technical scheme of the computer program, which are not described in detail, can be referred to the description of the technical scheme of the on-orbit leakage detection method for the spacecraft cabin section.
The foregoing describes specific embodiments of the present disclosure. Other embodiments are within the scope of the following claims. In some cases, the actions or steps recited in the claims can be performed in a different order than in the embodiments and still achieve desirable results. In addition, the processes depicted in the accompanying figures do not necessarily require the particular order shown, or sequential order, to achieve desirable results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.
The computer instructions include computer program code that may be in source code form, object code form, executable file or some intermediate form, etc. The computer readable medium may include any entity or device capable of carrying the computer program code, a recording medium, a U disk, a removable hard disk, a magnetic disk, an optical disk, a computer Memory, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), an electrical carrier signal, a telecommunications signal, a software distribution medium, and so forth. It should be noted that the computer readable medium contains content that can be appropriately scaled according to the requirements of jurisdictions in which such content is subject to legislation and patent practice, such as in certain jurisdictions in which such content is subject to legislation and patent practice, the computer readable medium does not include electrical carrier signals and telecommunication signals.
It should be noted that, for simplicity of description, the foregoing method embodiments are all expressed as a series of combinations of actions, but it should be understood by those skilled in the art that the embodiments are not limited by the order of actions described, as some steps may be performed in other order or simultaneously according to the embodiments of the present disclosure. Further, those skilled in the art will appreciate that the embodiments described in the specification are all preferred embodiments, and that the acts and modules referred to are not necessarily all required for the embodiments described in the specification.
In the foregoing embodiments, the descriptions of the embodiments are emphasized, and for parts of one embodiment that are not described in detail, reference may be made to the related descriptions of other embodiments.
The preferred embodiments of the present specification disclosed above are merely used to help clarify the present specification. Alternative embodiments are not intended to be exhaustive or to limit the invention to the precise form disclosed. Obviously, many modifications and variations are possible in light of the teaching of the embodiments. The embodiments were chosen and described in order to best explain the principles of the embodiments and the practical application, to thereby enable others skilled in the art to best understand and utilize the invention. This specification is to be limited only by the claims and the full scope and equivalents thereof.
Claims (10)
1. The on-orbit leakage detection method for the spacecraft cabin is characterized by being applied to an on-orbit leakage detection device for the spacecraft cabin, wherein the device at least comprises an empty-coupling broadband acoustic cube, 8 empty-coupling broadband acoustic sensors are arranged on each array surface of the empty-coupling broadband acoustic cube, and 8 empty-coupling broadband acoustic sensors on the same array surface are arranged for one circle according to an equally-divided annular shape, and the method comprises the following steps:
when the spacecraft is in a cabin leak detection stage, arranging the on-orbit leak detection device of the spacecraft cabin at a target position;
acquiring data acquired by each sensor of each array surface in a first preset time period, and performing short-time Fourier transform on the data acquired by each sensor to obtain initial normal data of each array surface;
Acquiring background data of amplitude values of each array surface under different frequency bands, which change with time, based on the initial normal data of each array surface;
Acquiring real-time signal characteristics of amplitude values of each array surface in different frequency bands in a second preset time period according to the initial normal data of each array surface at intervals of preset time;
and comparing the background data with the real-time signal characteristics to obtain a comparison result, and determining the leakage position of the spacecraft cabin based on the comparison result.
2. The method of claim 1, wherein positioning the spacecraft cabin on-orbit leak detection device at a target location while the spacecraft is in a cabin leak detection phase comprises:
Based on the shapable spring, the spacecraft cabin on-orbit leakage detection device is hung into a cabin to be detected of a spacecraft, and the hanging height of the spacecraft cabin on-orbit leakage detection device is adjusted, so that the spacecraft cabin on-orbit leakage detection device is located at the center position of the cabin to be detected, one end of the shapable spring is connected with the spacecraft cabin on-orbit leakage detection device through plugs of 3 locating pins, and the other end of the shapable spring is adhered to the cabin to be detected through nylon sticking buckles.
3. The method of claim 1, wherein obtaining background data for each array plane over time in amplitude at different frequency bands based on the initial normal data for each array plane comprises:
carrying out short-time Fourier transform on each channel signal in the initial normal data of each array surface to obtain first change data of each channel, wherein each channel signal is the initial normal data corresponding to each sensor;
And averaging the sum of the first change data of each channel on the same array surface to obtain a first average value, and taking the first average value as background data of the amplitude of each array surface, which changes with time, under different frequency bands.
4. A method according to claim 3, wherein comparing the background data with the real-time signal features yields a comparison result, and determining the position of the leak in the spacecraft cabin based on the comparison result comprises:
When the amplitude value in the real-time signal characteristic is higher than the amplitude average value of the background data, the real-time signal characteristic comprises new frequency which does not exist in the background data, and the duration of the new frequency exceeds the first duration, taking the real-time signal characteristic of the frequency band where the new frequency is positioned as a target signal characteristic;
if the signal characteristics in the preset ground verification database are consistent with the frequency characteristics of the target signal characteristics, the real-time signal characteristics of the array surface corresponding to the new frequency are collected again;
if the new frequency still exists in the re-acquired real-time signal characteristics, leakage exists in the array surface corresponding to the new frequency, and the leakage position is determined based on the first change data of each channel in the array surface with the leakage.
5. The method of claim 4, wherein determining the location of the leak based on the first change data for each channel in the array face where the leak exists comprises:
And comparing the first variation data of each channel in the array surface with the leakage, and taking the channel with the largest first variation data as the leakage direction.
6. The method of claim 4, wherein the signal characteristics in the pre-determined ground verification database and the target signal characteristics are obtained based on the following formula, comprising:
Wherein, For the target signal feature, an is a weight, pi (j) (fn, t) is first variation data, j is a sensor number on each array face, f is a frequency, t is a time,And verifying the signal characteristics in the database for the preset ground.
7. The method according to claim 4, wherein the method further comprises:
When the frequency band misalignment exists between the signal characteristics in the preset ground verification database and the target signal characteristics, continuously and repeatedly acquiring the real-time signal characteristics of the array surface corresponding to the new frequency, and writing the frequency band characteristic points and the amplitude in the target signal characteristics into the preset ground verification database.
8. The utility model provides a spacecraft cabin on-orbit leak hunting equipment, its characterized in that is applied to spacecraft cabin on-orbit leak hunting device, the device includes an empty wide band sound cube at least, all be provided with 8 empty wide band acoustic sensor of coupling on every array face of empty wide band sound cube, and 8 on same array face empty wide band acoustic sensor of coupling is arranged a week according to the annular of equipartition, the equipment includes:
the device setting module is used for setting the on-orbit leakage detection device of the spacecraft cabin at a target position when the spacecraft is in the cabin leakage detection stage;
The initial transformation module is used for acquiring data acquired by each sensor of each array surface in a first preset time period, and performing short-time Fourier transformation on the data acquired by each sensor to acquire initial normal data of each array surface;
the background data acquisition module is used for acquiring background data of amplitude values of each array surface under different frequency bands, which change with time, based on the initial normal data of each array surface;
the real-time signal characteristic acquisition module is used for acquiring real-time signal characteristics of amplitude values of each array surface in different frequency bands in a second preset time period along with time based on the initial normal data of each array surface at intervals of preset time;
and the leakage position determining module is used for comparing the background data with the real-time signal characteristics to obtain a comparison result and determining the leakage position of the spacecraft cabin based on the comparison result.
9. A computing device, comprising:
A memory and a processor;
The memory is configured to store computer executable instructions that, when executed by the processor, implement the steps of the spacecraft cabin on-orbit leak detection method of any one of claims 1 to 7.
10. A computer readable storage medium storing computer executable instructions which when executed by a processor perform the steps of the spacecraft cabin on-orbit leak detection method of any one of claims 1 to 7.
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