Displacement monitoring device and method for slender aircraft test
By installing a monitor and a controller on the elongated body aircraft, real-time accurate monitoring and automatic termination of axial twitching are achieved, which solves the problem of inaccurate monitoring in the prior art and improves the safety and reliability of the test.
Patent Information
- Application Number
- CN202510626991.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-15
- Publication Date
- 2025-08-01
AI Technical Summary
The prior art is difficult to accurately monitor the axial movement of the slender body aircraft in the comprehensive temperature, humidity and vibration test, resulting in the inability to take timely measures, affecting the accuracy of the test data and the safety of the aircraft structure.
The device combined with a monitor and a controller is adopted, including a displacement recording module and a tamper warning and termination module. The displacement is monitored in real time through sensors and automatically cut off the vibration excitation source when the warning value is exceeded, achieving accurate monitoring and automatic termination test.
The monitoring accuracy and safety of the elongated aircraft test are improved, structural damage and human negligence caused by squirming are reduced, and the reliability and efficiency of the test are enhanced.
Smart Images
Figure CN120397291A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the technical field of slender aircraft test equipment, and in particular, to a crosstalk monitoring device and method for slender aircraft tests. Background Art
[0002] During the life cycle of a slender aircraft, it has to experience temperature, humidity, and vibration coupling environments. Therefore, during the development process, ground temperature, humidity, and vibration comprehensive tests need to be carried out to evaluate its reliability. Currently, most tests rely on locking clamping rings to install and fix it, and rely on friction to prevent axial crosstalk. During the comprehensive test, due to the effects of temperature, humidity, and vibration, the fixture may become loose, and the test article may experience axial crosstalk. Currently, the monitoring method for this phenomenon mainly relies on manual monitoring through a small observation window of the temperature chamber during the test process. However, it is difficult to observe the subtle crosstalk of the slender aircraft manually, so measures cannot be taken in time for the crosstalk of the slender aircraft. Summary of the Invention
[0003] In view of this, the purpose of the present application is to propose a crosstalk monitoring device and method for slender aircraft tests to solve the problem that the crosstalk of the slender aircraft cannot be accurately observed during vibration tests.
[0004] Based on the above purpose, the present application provides a crosstalk monitoring device for slender aircraft tests, including:
[0005] A monitor, installed on the slender aircraft and / or the fixture, for monitoring the displacement of the slender aircraft;
[0006] A controller, including a displacement recording module and a crosstalk warning termination module. The displacement recording module is connected to the monitor, for recording the displacement and generating displacement data. The crosstalk warning termination module is connected to the displacement recording module. When the displacement data exceeds a preset warning value, the crosstalk warning termination module triggers a warning signal. When the displacement data exceeds a preset safety value, the crosstalk warning termination module automatically cuts off the vibration excitation source of the slender aircraft to terminate the test.
[0007] Optionally, the monitor includes acceleration sensors. Two acceleration sensors are provided, respectively installed on the slender aircraft and the fixture, for obtaining the relative acceleration data between the slender aircraft and the fixture to obtain the displacement of the slender aircraft.
[0008] Optionally, the monitor includes a displacement sensor, which is installed on the slender aircraft to monitor the displacement of the slender aircraft.
[0009] Optionally, the controller further includes a data transmission module, which is connected to the displacement recording module and is used to transmit the displacement data to a remote monitoring terminal.
[0010] Optionally, the controller further includes a vibration control module, which is used to control the output parameters of the vibration excitation source of the slender body aircraft to achieve the required vibration conditions for the test; the vibration control module is connected to the creep warning termination module. When the displacement data exceeds the preset safety value, the creep warning termination module automatically cuts off the vibration excitation source of the slender body aircraft through the vibration control module to terminate the test.
[0011] Based on the same inventive concept, the present disclosure also provides a method for monitoring creep during the test of a slender body aircraft, which is applied to the above-mentioned device for monitoring creep during the test of a slender body aircraft, and includes:
[0012] Install the monitor at a preset position on the slender body aircraft and / or the fixture;
[0013] Set the preset warning value and the preset safety value in the creep warning termination module;
[0014] The test of the slender body aircraft starts. The monitor collects the displacement during the test of the slender body aircraft and transmits the displacement to the displacement recording module. The displacement recording module records the displacement and generates the displacement data;
[0015] The creep warning termination module obtains the displacement data and compares it with the preset warning value and the preset safety value; when the displacement data exceeds the preset warning value, the creep warning termination module triggers a warning signal; when the displacement data exceeds the preset safety value, the creep warning termination module automatically cuts off the vibration excitation source of the slender body aircraft to terminate the test.
[0016] Optionally, the displacement recording module records the displacement and generates the displacement data, including: the displacement recording module preprocesses the generated displacement data, including filtering and outlier rejection. The data transmission module transmits the preprocessed displacement data to a remote monitoring terminal and displays a displacement-time curve on the remote monitoring terminal.
[0017] Optionally, before the test of the slender body aircraft starts, the output parameters of the vibration excitation source are set through the vibration control module; when the displacement data exceeds the preset safety value, the creep warning termination module automatically cuts off the vibration excitation source of the slender body aircraft through the vibration control module to terminate the test.
[0018] Based on the same inventive concept, the present disclosure also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable by the processor. When the processor executes the computer program, the above-mentioned method is implemented.
[0019] Based on the same inventive concept, the present disclosure also provides a non-transitory computer-readable storage medium storing computer instructions for causing a computer to execute the above-mentioned method.
[0020] Based on the same inventive concept, the present disclosure also provides a computer program product including computer program instructions. When the computer program instructions run on a computer, the computer is caused to execute the above-mentioned method.
[0021] As can be seen from the above, a crosstalk monitoring device for slender body aircraft tests provided by the present application installs sensors on the slender body aircraft and / or fixtures. The sensors can achieve real-time displacement monitoring of the slender body aircraft. Compared with traditional manual monitoring, the monitoring accuracy is greatly improved, effectively avoiding damage to the aircraft structure caused by increased crosstalk, greatly reducing the test risk, and improving the test accuracy. The displacement recording module and crosstalk warning termination module on the controller increase the intelligent decision-making performance of the monitoring device, enabling the monitoring device to automatically take corresponding treatment measures according to the severity of the crosstalk of the slender body aircraft, without the need for testers to closely monitor the test process at all times. This not only reduces the workload of testers but also avoids test accidents caused by human negligence or misjudgment, significantly improving the safety and reliability of the test. Description of the Drawings
[0022] In order to more clearly illustrate the technical solutions in the present application or related technologies, the following will briefly introduce the drawings required for use in the description of the embodiments or related technologies. Obviously, the drawings in the following description are only embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.
[0023] Figure 1 Schematic diagram showing the crosstalk monitoring device in the embodiment of the present application;
[0024] Figure 2 Flowchart showing the crosstalk monitoring method in the embodiment of the present application;
[0025] Figure 3 Schematic diagram of the hardware structure of an electronic device provided in the embodiment of the present application.
[0026] Reference numerals: 1, monitor; 11, slender aircraft; 12, fixture; 2, controller; 21, displacement recording module; 22, creep warning termination module; 23, data transmission module; 24, vibration control module; 3, vibration sensor; 4, vibration table; 5, power amplifier; 6, test chamber. Detailed implementation manners
[0027] To make the objectives, technical solutions and advantages of the present application clearer and more understandable, the following further elaborates on the present application in detail with reference to specific embodiments and the accompanying drawings.
[0028] It should be noted that, unless otherwise defined, the technical terms or scientific terms used in the embodiments of the present application should have the ordinary meanings understood by those with ordinary skills in the field to which the present application belongs. The "first", "second" and similar terms used in the embodiments of the present application do not indicate any order, quantity or importance, but are only used to distinguish different components. The terms such as "including" or "comprising" mean that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects. The terms such as "connected" or "coupled" are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. The terms such as "upper", "lower", "left" and "right" are only used to represent relative positional relationships, and when the absolute position of the object being described changes, the relative positional relationship may also change accordingly.
[0029] Based on the background described above, in the fields of aerospace, national defense and military industry, slender aircraft play an irreplaceable role in tasks such as high-speed flight and long-distance detection due to their unique aerodynamic shape design. However, during their entire life cycle, such aircraft inevitably have to undergo multiple tests of extreme temperature, high humidity environment and severe vibration. The sharp change in temperature may cause the material to expand and contract thermally, leading to structural deformation; the fluctuation of humidity will accelerate the corrosion of metal components and reduce the material properties; while vibration may exacerbate structural fatigue and even cause loosening of the connection parts. To ensure the reliability and safety of the aircraft in complex service environments, the ground temperature-humidity-vibration comprehensive test has become an essential key link in the development process.
[0030] At present, when installing and fixing slender aircraft in the comprehensive temperature, humidity and vibration test, most of them use locking clamp rings. This kind of fixture fastens the aircraft to the test platform through a mechanical structure. Its core principle is to rely on the friction force between the clamp ring and the surface of the aircraft to resist the axial movement force that may occur during the test. Under ideal conditions, this fixture can meet the fixing requirements at the initial stage of the test, but the actual test process is far more complex than the theoretical assumption. The cyclic change of temperature and humidity will change the physical properties of the fixture and aircraft materials. For example, the brittleness of metal materials increases at low temperatures, and corrosion intensifies in high-temperature and high-humidity environments. These changes will directly affect the stability of the friction force. The superposition of vibration loads will further disrupt the static friction balance between the fixture and the aircraft, causing the fixture to gradually loosen, and finally resulting in axial movement of the test article.
[0031] The existing means for monitoring axial movement mainly rely on manual visual monitoring by test personnel through a small observation window on the temperature chamber. This traditional monitoring method has obvious drawbacks: on the one hand, the internal space of the temperature chamber is limited, the field of view of the observation window is narrow, and it is restricted by the lighting conditions of the test environment, making it difficult to comprehensively and clearly observe the state of the aircraft; on the other hand, the axial movement of the slender aircraft is often relatively subtle, and it is difficult for the naked eye to capture displacement changes at the millimeter level or even sub-millimeter level. When the test personnel discover the movement, the aircraft may have undergone a large displacement, missing the best intervention opportunity, which not only affects the accuracy of the test data, but may also cause irreversible damage to the aircraft structure, and even lead to safety accidents. Therefore, developing a technology that can monitor the axial movement of slender aircraft in real time and accurately has become an urgent need to ensure the smooth progress of the comprehensive temperature, humidity and vibration test and the successful development of the aircraft.
[0032] The following will Figures 1-3 describe the embodiments of the present application in detail with reference to the accompanying
[0033] A monitoring device for axial movement of a slender aircraft during a test, comprising:
[0034] A monitor 1, installed on the slender aircraft 11 and / or the fixture 12, for monitoring the displacement of the slender aircraft 11;
[0035] A controller 2, including a displacement recording module 21 and a movement warning termination module 22. The displacement recording module 21 is connected to the monitor 1 for recording the displacement and generating displacement data. The movement warning termination module 22 is connected to the displacement recording module 21. When the displacement data exceeds a preset warning value, the movement warning termination module 22 triggers a warning signal. When the displacement data exceeds a preset safety value, the movement warning termination module 22 automatically cuts off the vibration excitation source of the slender aircraft 11 to terminate the test.
[0036] Specifically, the displacement recording module 21 uses a high-speed data acquisition card and is equipped with a multi-channel analog / digital conversion (A / D) chip. It can simultaneously receive analog signals transmitted by multiple monitors 1 and quickly convert them into digital signals. The displacement recording module 21 also uses a high-performance microprocessor, providing powerful data processing and logical judgment capabilities for the displacement recording module 21 and the crosstalk warning termination module 22. For the convenience of subsequent data analysis, this module also has data compression and classification functions, and can automatically sort the data according to conditions such as the test stage and displacement change trend. The crosstalk warning termination module 22 receives the displacement data transmitted by the displacement recording module 21 through a high-speed communication interface (such as Ethernet, USB, etc.) and uses a digital signal processor (DSP) to analyze the data in real time. When the displacement data generated by the displacement recording module 21 exceeds the preset warning value, the audible and visual alarm device on the crosstalk warning termination module 22 will immediately trigger an audible and visual warning signal, and at the same time send a warning text message to the mobile terminal of the test personnel to remind the test personnel to closely monitor the state of the aircraft. If the displacement data continues to rise and exceeds the preset safety value, this module will automatically cut off the vibration excitation source of the slender aircraft 11 through a relay, and at the same time turn off the temperature and humidity adjustment system, making the test environment enter a safe shutdown state. In addition, the crosstalk warning termination module 22 is also provided with a manual intervention interface, and the test personnel can manually control the termination and restart of the test through this interface under special circumstances.
[0037] In this embodiment, by installing sensors on the slender aircraft 11 and / or the fixture 12, the sensors can realize real-time displacement monitoring of the slender aircraft 11. Compared with traditional manual monitoring, the monitoring accuracy is greatly improved, effectively avoiding the damage of the aircraft structure caused by the aggravation of crosstalk, and greatly reducing the test risk. The displacement recording module 21 and the crosstalk warning termination module 22 on the controller 2 enhance the intelligent decision-making performance of the monitoring device, enabling the monitoring device to automatically take corresponding treatment measures according to the severity of the crosstalk of the slender aircraft 11, without the need for the test personnel to closely monitor the test process at all times. This not only reduces the work burden of the test personnel but also avoids test accidents caused by human negligence or misjudgment, significantly improving the safety and reliability of the test.
[0038] In some embodiments, the monitor 1 includes acceleration sensors. Two acceleration sensors are provided and are respectively installed on the slender aircraft 11 and the fixture 12 to obtain relative acceleration data between the slender aircraft 11 and the fixture 12, so as to obtain the displacement amount of the slender aircraft 11.
[0039] Specifically, when using the acceleration sensors for monitoring, the first acceleration sensor is fixed on the surface of the slender body aircraft 11, and the second acceleration sensor is fixed on the surface of the fixture 12. The acceleration data a1 of the slender body aircraft 11 and the acceleration data a2 of the fixture 12 are collected in real time respectively. The acceleration difference Δa between the two is calculated by the high-performance microprocessor on the displacement recording module 21. The calculation formula is Δa = a1 - a2. Based on the kinematic principle, the acceleration difference Δa is integrated with respect to time t once to obtain the velocity expression: Δv = ∫Δadt + C1, where C1 is the integration constant. By detrending the velocity data to eliminate the influence of the integration constant C1, the relative velocity Δv between the slender body aircraft 11 and the fixture 12 is obtained. Further, the relative velocity Δv is integrated with respect to time t twice to obtain the displacement expression Δx = ∫Δvdt + C2, where C2 is the integration constant. By removing the offset from the displacement data to eliminate the influence of the integration constant C2, the actual displacement Δx of the slender body aircraft 11 relative to the fixture 12 is finally obtained, thereby achieving accurate measurement of the creep displacement of the slender body aircraft 11.
[0040] In this embodiment, in the combined temperature, humidity and vibration test, the vibration environment is relatively complex and intense. Ordinary sensors may generate false signals due to vibration interference, resulting in inaccurate measurement results. However, the acceleration sensor has good seismic performance, can effectively resist the influence of vibration, accurately obtain the acceleration data of the slender body aircraft 11 and the fixture 12, accurately calculate the relative acceleration between the two, and then obtain the accurate displacement through integral operation, providing accurate data support for evaluating the creep situation of the aircraft and helping to more accurately judge the reliability of the aircraft in the test.
[0041] In some embodiments, the monitor 1 includes a displacement sensor, and the displacement sensor is installed on the slender body aircraft 11 to monitor the displacement of the slender body aircraft 11.
[0042] In this embodiment, the displacement sensor is directly installed on the slender body aircraft 11, which can directly obtain the displacement information of the slender body aircraft 11, avoiding errors and uncertainties that may be brought by other indirect methods, thereby providing more accurate and reliable displacement data and helping to accurately evaluate the position change of the aircraft during the test.
[0043] In some embodiments, the monitor 1 can be a travel switch. The travel switch is at a preset position on the slender body aircraft 11. The distance between this preset position and the fixture 12 is a preset distance. When the slender body aircraft 11 creeps the preset distance, the fixture 12 triggers the travel switch to automatically cut off the excitation source of the slender body aircraft 11.
[0044] In this embodiment, when the slender body aircraft 11 experiences unexpected crosstalk, the travel switch operates in a timely manner to cut off the excitation source, preventing the aircraft from continuing abnormal movement and preventing more serious faults or accidents that may be caused. The travel switch has a simple structure and low cost. Compared with sensors, it has a high cost performance while realizing the basic crosstalk monitoring function.
[0045] In some embodiments, the controller 2 further includes a data transmission module 23. The data transmission module 23 is connected to the displacement recording module 21 and is used to transmit the displacement data to a remote monitoring terminal.
[0046] In addition, the controller 2 further includes a vibration control module 24. The vibration control module 24 is used to control the output parameters of the vibration excitation source of the slender body aircraft 11 to achieve the vibration conditions required for the test. The vibration control module 24 is connected to the crosstalk warning termination module 22. When the displacement data exceeds the preset safety value, the crosstalk warning termination module 22 automatically cuts off the vibration excitation source of the slender body aircraft 11 through the vibration control module 24 to terminate the test.
[0047] Specifically, the data transmission module 23 can adopt a three-channel redundant architecture of 4G / 5G wireless communication, industrial Ethernet, and fiber optic transmission to ensure the reliability of displacement data transmission. Two vibration tables 4 respectively clamp both ends of the slender body aircraft 11 through fixtures 12 and place it in a test chamber 6 that simulates the temperature and humidity environment. The vibration control module 24 adopts an adaptive PID control algorithm to monitor and dynamically adjust the output parameters of the vibration table 4 in real time to ensure that the aircraft bears the vibration load that meets the test requirements. At the same time, a power amplifier 5 connected in series between the vibration control module 24 and the vibration table 4 can amplify the control signal and provide stable and sufficient driving energy for the vibration table 4 to ensure the power output under complex vibration conditions. Under the influence of interference factors such as temperature and humidity fluctuations and dynamic changes in the aircraft structure, the adaptive PID control algorithm can still respond quickly and continuously and stably simulate the vibration conditions in the actual service environment of the aircraft, providing real and accurate test data support for the reliability evaluation of the aircraft, effectively improving the credibility and effectiveness of the test results, and reducing the test risks and repeated costs caused by inaccurate vibration control.
[0048] In this embodiment, the data transmission module 23 transmits the displacement data of the displacement recording module 21 to the remote monitoring terminal, enabling the test personnel to obtain the displacement information of the slender body aircraft 11 in real time even when they are not at the test site, thereby improving the data acquisition efficiency and facilitating the test personnel to timely understand the displacement change of the aircraft during the test, providing strong support for making decisions in a timely manner. The vibration control module 24 can control the output parameters of the vibration excitation source of the slender body aircraft 11 to achieve the vibration conditions required for the test, so as to ensure that the test can simulate various vibration conditions that the aircraft may encounter in actual use, improving the authenticity and effectiveness of the test.
[0049] Based on the same inventive concept, the present application also provides a method for monitoring the crosstalk of a slender body aircraft during a test, which is applied to the above-mentioned device for monitoring the crosstalk of a slender body aircraft during a test, and includes:
[0050] S = 101: Install the monitor 1 at a preset position on the slender body aircraft 11 and / or the fixture 12;
[0051] Specifically, the installation position of the monitor 1 is selected according to the type of the monitor 1. For example, when the monitor 1 is an acceleration sensor, two monitors 1 are set and installed on the slender body aircraft 11 and the fixture 12 respectively, and the displacement of the slender body aircraft 11 is obtained through the accelerations of the slender body aircraft 11 and the fixture 12; when the monitor 1 is a displacement sensor, the displacement sensor is installed on the slender body aircraft 11, and the crosstalk amount is determined through the displacement amount of the slender body aircraft. The monitor 1 can adopt a mechanical locking fixing method to ensure that the monitor 1 does not displace in a vibrating environment. For a high-temperature test environment, a high-temperature resistant epoxy resin adhesive can be used for secondary reinforcement, and at the same time, heat sinks are designed on the shell of the monitor 1 to ensure the normal operation of the monitor 1.
[0052] S = 102: Set the preset warning value and the preset safety value in the crosstalk warning termination module 22;
[0053] Specifically, two fixtures 12 clamp the slender body aircraft 11, and the relative distance between the two fixtures 12 is the clamping width, which is a key dimensional parameter used to determine the preset warning value and the preset safety value of the crosstalk to judge whether the displacement of the slender body aircraft 11 during the test is within a safe range. Exemplarily, when the displacement amount of the slender body aircraft 11 reaches 3% of the clamping width, the preset warning value is triggered; when the displacement amount reaches 10% of the clamping width, the preset safety value is reached.
[0054] S103: The slender aircraft 11 starts the test. The monitor 1 collects the displacement during the test of the slender aircraft 11 and transmits the displacement to the displacement recording module 21. The displacement recording module 21 records the displacement and generates the displacement data.
[0055] Specifically, the displacement recording module 21 uses a high-precision data acquisition card and is equipped with a multi-channel analog / digital conversion (A / D) chip, which can receive analog signals transmitted by multiple monitors 1 simultaneously and quickly convert them into digital signals. The displacement recording module 21 also uses a high-performance microprocessor to provide strong data processing and logical judgment capabilities for the displacement recording module 21 and the crosstalk warning termination module 22. For the convenience of subsequent data analysis, this module also has data compression and classification functions, and can automatically sort the data according to conditions such as the test stage and the displacement change trend.
[0056] S104: The crosstalk warning termination module 22 obtains the displacement data and compares it with the preset warning value and the preset safety value. When the displacement data exceeds the preset warning value, the crosstalk warning termination module 22 triggers a warning signal. When the displacement data exceeds the preset safety value, the crosstalk warning termination module 22 automatically cuts off the vibration excitation source of the slender aircraft 11 to terminate the test.
[0057] Specifically, in addition to the displacement data, the warning decision is made by comprehensively considering the displacement change rate (speed) and acceleration parameters. Exemplarily, when the displacement value does not exceed the threshold but the change rate continues to increase, a warning signal is triggered in advance to achieve early prediction of potential crosstalk risks. The crosstalk warning termination module 22 can push the warning signal to the remote monitoring terminal in real time through the data transmission module 23, such as: devices such as the computers of the test personnel. The remote monitoring terminal will receive a push notification containing the warning type, the test equipment number, and the displacement data, which is convenient for remote personnel to timely understand the test status and make a quick response even if they are not on site.
[0058] In this embodiment, by installing sensors on the slender aircraft 11 and / or the fixture 12, the sensors can realize real-time displacement monitoring of the slender aircraft 11. Compared with traditional manual monitoring, the monitoring accuracy is greatly improved, effectively avoiding the damage of the aircraft structure caused by the aggravation of crosstalk, greatly reducing the test risk, and improving the test accuracy. The displacement recording module 21 and the crosstalk warning termination module 22 on the controller 2 increase the intelligent decision-making performance of the monitoring device, enabling the monitoring device to automatically take corresponding treatment measures according to the severity of the crosstalk of the slender aircraft 11, without the need for test personnel to closely monitor the test process all the time, which not only reduces the work burden of the test personnel, but also avoids test accidents caused by human negligence or judgment errors, and significantly improves the safety and reliability of the test.
[0059] In some embodiments, the displacement recording module 21 records the displacement amount and generates the displacement data, including:
[0060] S1031: The displacement recording module 21 preprocesses the generated displacement data, including filtering and outlier removal. The data transmission module 23 transmits the preprocessed displacement data to the remote monitoring terminal and displays the displacement-time curve on the remote monitoring terminal.
[0061] Specifically, in the filtering process, high-frequency noise can be removed and short-term fluctuations can be smoothed, and outliers can be removed. The removed outliers are filled by linear interpolation or ARIMA model prediction to ensure data continuity, so as to obtain an accurate displacement-time curve.
[0062] In this embodiment, the data transmission module 23 transmits the preprocessed data to the remote monitoring terminal, which facilitates the experimenter to obtain the displacement data in real time and improves the flexibility and convenience of monitoring. Displaying the displacement-time curve on the remote monitoring terminal can intuitively present the displacement change trend of the slender body aircraft 11 during the experiment, enabling the experimenter to more quickly and accurately understand the experimental situation and timely discover potential problems.
[0063] In some embodiments, before the slender body aircraft 11 starts the experiment, the output parameters of the vibration excitation source are set through the vibration control module 24; when the displacement data exceeds the preset safety value, the crosstalk warning termination module 22 automatically cuts off the vibration excitation source of the slender body aircraft 11 through the vibration control module 24 to terminate the experiment.
[0064] In this embodiment, the slender body aircraft 11 realizes parameter setting and automatic processing of faults through the vibration control module 24, reducing manual intervention and thus improving the efficiency of the experiment.
[0065] Based on the same inventive concept, corresponding to the method of any of the above embodiments, the present application also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, it implements the crosstalk monitoring method described in any of the above embodiments.
[0066] Figure 3 FIG. shows a more specific schematic diagram of the hardware structure of the electronic device provided in this embodiment. The device may include: a processor 1010, a memory 1020, an input / output interface 1030, a communication interface 1040, and a bus 1050. Among them, the processor 1010, the memory 1020, the input / output interface 1030, and the communication interface 1040 are communicatively connected to each other inside the device through the bus 1050.
[0067] The processor 1010 can be implemented in the form of a general-purpose CPU (Central Processing Unit), a microprocessor, an application-specific integrated circuit (ASIC), or one or more integrated circuits, etc., and is used to execute relevant programs to implement the technical solutions provided in the embodiments of this specification.
[0068] The memory 1020 can be implemented in the form of a ROM (Read Only Memory), a RAM (Random Access Memory), a static storage device, a dynamic storage device, etc. The memory 1020 can store an operating system and other application programs. When implementing the technical solutions provided in the embodiments of this specification through software or firmware, the relevant program codes are stored in the memory 1020 and are called and executed by the processor 1010.
[0069] The input / output interface 1030 is used to connect to the input / output module to achieve information input and output. The input / output module can be configured as a component in the device (not shown in the figure) or can be externally connected to the device to provide corresponding functions. Among them, the input device can include a keyboard, a mouse, a touch screen, a microphone, various sensors, etc., and the output device can include a display, a speaker, a vibrator, an indicator light, etc.
[0070] The communication interface 1040 is used to connect to a communication module (not shown in the figure) to achieve communication interaction between this device and other devices. Among them, the communication module can achieve communication in a wired manner (such as USB, network cable, etc.).
[0071] The bus 1050 includes a path for transmitting information between various components of the device (such as the processor 1010, the memory 1020, the input / output interface 1030, and the communication interface 1040).
[0072] It should be noted that although the above device only shows the processor 1010, the memory 1020, the input / output interface 1030, the communication interface 1040, and the bus 1050, in the specific implementation process, the device may also include other components necessary for normal operation. In addition, those skilled in the art can understand that the above device may also only include the components necessary to implement the solutions of the embodiments of this specification, and does not necessarily include all the components shown in the figure.
[0073] The electronic device in the above embodiment is used to implement the corresponding crosstalk monitoring method in any of the foregoing embodiments, and has the beneficial effects of the corresponding method embodiments, which will not be elaborated here.
[0074] Based on the same inventive concept, corresponding to the method of any of the above embodiments, the present application further provides a non-transitory computer-readable storage medium storing computer instructions for causing the computer to execute the crosstalk monitoring method as described in any one of the above embodiments.
[0075] The computer-readable medium of this embodiment includes permanent and non-permanent, removable and non-removable media, and information storage can be implemented by any method or technology. The information can be computer-readable instructions, data structures, program modules, or other data. Examples of computer storage media include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, compact disc read-only memory (CD-ROM), digital versatile disc (DVD) or other optical storage, magnetic cassette tapes, magnetic disk storage or other magnetic storage devices, or any other non-transmission medium that can be used to store information accessible by a computing device.
[0076] The computer instructions stored in the storage medium of the above embodiment are used to cause the computer to execute the crosstalk monitoring method as described in any one of the above embodiments, and have the beneficial effects of the corresponding method embodiments, which will not be elaborated here.
[0077] Those of ordinary skill in the art should understand that the discussion of any of the above embodiments is only exemplary and is not intended to imply that the scope of the present application is limited to these examples; under the concept of the present application, the technical features in the above embodiments or different embodiments can also be combined, the steps can be implemented in any order, and there are many other variations in different aspects of the embodiments of the present application as described above, which are not provided in detail for the sake of brevity.
[0078] In addition, for simplicity of explanation and discussion, and so as not to make the embodiments of the present application difficult to understand, well-known power / ground connections to integrated circuit (IC) chips and other components may or may not be shown in the provided drawings. Further, the devices may be shown in block diagram form in order to avoid making the embodiments of the present application difficult to understand, and this also takes into account the fact that details of the implementation of these block diagram devices are highly dependent on the platform on which the embodiments of the present application are to be implemented (i.e., these details should be entirely within the understanding of those skilled in the art). In cases where specific details (such as circuits) are set forth to describe exemplary embodiments of the present application, it will be apparent to those skilled in the art that the embodiments of the present application may be practiced without these specific details or with variations of these specific details. Accordingly, these descriptions should be considered illustrative rather than restrictive.
[0079] Although the present application has been described in connection with specific embodiments thereof, many alternatives, modifications, and variations of these embodiments will be apparent to those of ordinary skill in the art in light of the foregoing description. For example, other memory architectures (such as dynamic RAM (DRAM)) may be used with the embodiments discussed.
[0080] Embodiments of the present application are intended to cover all such alternatives, modifications, and variations that fall within the broad scope of the claims of the present application. Accordingly, any omissions, modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the embodiments of the present application shall be included within the protection scope of the present application.
Claims
1. A slender aircraft test motion monitoring device, characterized in that: Comprising: A monitor (1), installed on the slender body aircraft (11) and / or the fixture (12), for monitoring the displacement of the slender body aircraft (11); A controller (2), including a displacement recording module (21) and a creep warning termination module (22), the displacement recording module (21) is connected to the monitor (1), for recording the displacement and generating displacement data, the creep warning termination module (22) is connected to the displacement recording module (21), when the displacement data exceeds a preset warning value, the creep warning termination module (22) triggers a warning signal, when the displacement data exceeds a preset safety value, the creep warning termination module (22) automatically cuts off the vibration excitation source of the slender body aircraft (11) to terminate the test.
2. The crosstalk monitoring device for slender body aircraft tests according to claim 1, characterized in that, The monitor (1) includes acceleration sensors, two acceleration sensors are provided, and are respectively installed on the slender body aircraft (11) and the fixture (12), for obtaining the relative acceleration data between the slender body aircraft (11) and the fixture (12), so as to obtain the displacement of the slender body aircraft (11).
3. The crosstalk monitoring device for slender body aircraft test according to claim 1, characterized in that, The monitor (1) includes a displacement sensor, the displacement sensor is installed on the slender body aircraft (11), to monitor the displacement of the slender body aircraft (11).
4. The crosstalk monitoring device for slender aircraft test according to claim 1, characterized in that, The controller (2) further includes a data transmission module (23), the data transmission module (23) is connected to the displacement recording module (21), for transmitting the displacement data to a remote monitoring terminal.
5. The crosstalk monitoring device for slender body aircraft test according to claim 1, characterized in that, The controller (2) further includes a vibration control module (24), the vibration control module (24) is used to control the output parameters of the vibration excitation source of the slender body aircraft (11), to achieve the vibration conditions required for the test; the vibration control module (24) is connected to the creep warning termination module (22), when the displacement data exceeds the preset safety value, the creep warning termination module (22) automatically cuts off the vibration excitation source of the slender body aircraft (11) through the vibration control module (24) to terminate the test.
6. A method for monitoring the longitudinal movement of a slender aircraft during tests, which is applied to the longitudinal movement monitoring device for a slender aircraft during tests according to any one of claims 1-5, characterized in that, Comprising: Install the monitor (1) at a preset position on the slender body aircraft (11) and / or the fixture (12); Set the preset warning value and the preset safety value in the creep warning termination module (22); The slender body aircraft (11) starts the test, the monitor (1) collects the displacement during the test of the slender body aircraft (11), and transmits the displacement to the displacement recording module (21), the displacement recording module (21) records the displacement and generates the displacement data; The creep warning termination module (22) obtains the displacement data, and compares it with the preset warning value and the preset safety value; When the displacement data exceeds the preset warning value, the creep warning termination module (22) triggers a warning signal; When the displacement data exceeds the preset safety value, the creep warning termination module (22) automatically cuts off the vibration excitation source of the slender body aircraft (11) to terminate the test.
7. The crosstalk monitoring method according to claim 6, wherein The displacement recording module (21) records the displacement amount and generates the displacement data, including: the displacement recording module (21) preprocesses the generated displacement data, including filtering and outlier rejection, and the data transmission module (23) transmits the preprocessed displacement data to a remote monitoring terminal and displays a displacement-time curve on the remote monitoring terminal.
8. A method for monitoring the movement back and forth, as claimed in claim 6, wherein Before the start of the test of the slender body aircraft (11), the output parameters of the vibration excitation source are set through the vibration control module (24); when the displacement data exceeds a preset safety value, the creep warning termination module (22) automatically cuts off the vibration excitation source of the slender body aircraft (11) through the vibration control module (24) to terminate the test.
9. An electronic device, comprising a memory, a processor, and a computer program stored on the memory and running on the processor, characterized in that, When the processor executes the program, it implements the method according to any one of claims 6 to 8.
10. A non-transitory computer-readable storage medium storing computer instructions, characterized in that, The computer instructions are used to cause a computer to execute the method according to any one of claims 6 to 8.
11. A computer program product, comprising computer program instructions, characterized in that, When the computer program instructions run on a computer, the computer is caused to execute the method according to any one of claims 6 - 8.