CN114701663A - Aircraft testing method and related equipment - Google Patents

Aircraft testing method and related equipment Download PDF

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Publication number
CN114701663A
CN114701663A CN202210632101.5A CN202210632101A CN114701663A CN 114701663 A CN114701663 A CN 114701663A CN 202210632101 A CN202210632101 A CN 202210632101A CN 114701663 A CN114701663 A CN 114701663A
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Prior art keywords
spoiler
undercarriage
vibration
landing gear
frequency spectrum
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CN114701663B (en
Inventor
孙超
马晨阳
曹朋亮
王露露
刘海立
夏慧
谢飞
周庚涛
刘可
李详
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Industrial Fulian Hangzhou Data Technology Co ltd
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Industrial Fulian Hangzhou Data Technology Co ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
    • G01B21/22—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
    • G01H1/00—Measuring characteristics of vibrations in solids by using direct conduction to the detector
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M13/00—Testing of machine parts
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
    • G06F17/10—Complex mathematical operations
    • G06F17/14—Fourier, Walsh or analogous domain transformations, e.g. Laplace, Hilbert, Karhunen-Loeve, transforms
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
    • G06F17/10—Complex mathematical operations
    • G06F17/18—Complex mathematical operations for evaluating statistical data, e.g. average values, frequency distributions, probability functions, regression analysis
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

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  • Pure & Applied Mathematics (AREA)
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  • Aviation & Aerospace Engineering (AREA)
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  • Manufacturing & Machinery (AREA)
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  • Bioinformatics & Computational Biology (AREA)
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  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

An aircraft testing method and related equipment are applied to a master control server, and the method comprises the following steps: receiving a test command of the undercarriage and/or the spoiler sent by the mobile control end; sending a test command to an edge controller corresponding to the undercarriage and/or the spoiler, enabling the edge controller to collect the offset angle and the vibration amplitude of the undercarriage and/or the spoiler within a preset time, and performing Fourier transform on the vibration amplitude of the undercarriage and/or the spoiler to obtain a vibration frequency spectrum of the undercarriage and/or the spoiler; receiving the offset angle and the vibration frequency spectrum of the landing gear and/or the spoiler sent by the edge controller; judging whether the offset angle and the vibration frequency spectrum of the undercarriage and/or the spoiler are abnormal or not to obtain a test result of the undercarriage and/or the spoiler; and sending the test result of the undercarriage and/or the spoiler to the mobile control end. The landing gear and/or spoiler of the airplane can be efficiently tested.

Description

Aircraft testing method and related equipment
Technical Field
The application relates to the technical field of equipment detection, in particular to an aircraft testing method and related equipment.
Background
Landing gear and spoilers are important components of the airframe structure of an aircraft. In order to ensure the safe operation of the airplane, the undercarriage and the spoiler of the airplane need to be tested.
Disclosure of Invention
The embodiment of the application provides an aircraft testing method and related equipment, which can be used for efficiently testing an undercarriage and/or a spoiler of an aircraft.
In a first aspect, the present application provides an aircraft testing method, which is applied to a master control server, and the method includes:
receiving a test command of the undercarriage and/or the spoiler sent by the mobile control end;
sending the test command to an edge controller corresponding to the undercarriage and/or the spoiler, so that the edge controller collects the offset angle and the vibration amplitude of the undercarriage and/or the spoiler within a preset time, and performs Fourier transform on the vibration amplitude of the undercarriage and/or the spoiler to obtain a vibration frequency spectrum of the undercarriage and/or the spoiler;
receiving the offset angle and the vibration frequency spectrum of the undercarriage and/or the spoiler sent by the edge controller;
judging whether the offset angle and the vibration frequency spectrum of the undercarriage and/or the spoiler are abnormal or not to obtain a test result of the undercarriage and/or the spoiler;
and sending the test result of the undercarriage and/or the spoiler to the mobile control end.
According to the aircraft testing method, a user sends a testing command through the mobile control end, the main control server obtains testing data of the undercarriage and the spoiler according to the testing command, and whether the undercarriage and the spoiler work normally or not is judged according to the testing data, so that efficient testing of the undercarriage and the spoiler is achieved.
In some alternative embodiments, the landing gear offset angle includes an angle between the landing gear and the wheels, and the spoiler offset angle includes an angle at which the spoiler is raised and deployed.
In some optional embodiments, determining whether the vibration spectrum of the landing gear and/or the spoiler is abnormal comprises:
judging whether the frequency of a resonance point of a vibration frequency spectrum of the undercarriage and/or the spoiler is within a preset frequency range;
and if the frequency of the resonance point of the vibration frequency spectrum of the undercarriage and/or the spoiler is not within the preset range, the vibration frequency spectrum of the undercarriage and/or the spoiler is abnormal.
In some optional embodiments, the method further comprises:
sampling data for the amplitude of vibration of the landing gear and/or spoiler;
and sending the vibration amplitude of the undercarriage and/or the spoiler after data sampling to the movement control end.
In a second aspect, the present application provides an aircraft testing method, applied to an edge controller, the method including:
receiving a test command of the undercarriage and/or the spoiler sent by the main control server;
acquiring the offset angle and the vibration amplitude of the undercarriage and/or the spoiler within preset time;
carrying out Fourier transform on the vibration amplitude of the undercarriage and/or the spoiler to obtain a vibration frequency spectrum of the undercarriage and/or the spoiler;
and sending the offset angle and the vibration frequency spectrum of the undercarriage and/or the spoiler to the main control server, so that the main control server judges whether the offset angle and the vibration frequency spectrum of the undercarriage and/or the spoiler are abnormal or not, and a test result of the undercarriage and/or the spoiler is obtained.
According to the aircraft testing method, the edge controller acquires the testing data of the undercarriage and the spoiler according to the testing command, so that the main control server can judge whether the undercarriage and the spoiler work normally or not according to the testing data, and efficient testing of the undercarriage and the spoiler is realized.
In some alternative embodiments, the landing gear offset angle includes an angle between the landing gear and the wheels, and the spoiler offset angle includes an angle at which the spoiler is raised and deployed.
In some optional embodiments, the method further comprises:
and after receiving the test command, sending a starting instruction to a motion controller corresponding to the falling frame and/or the spoiler so as to start the falling frame and/or the spoiler.
In some optional embodiments, determining whether the vibration spectrum of the landing gear and/or the spoiler is abnormal comprises:
judging whether the frequency of a resonance point of a vibration frequency spectrum of the undercarriage and/or the spoiler is within a preset frequency range;
and if the frequency of the resonance point of the vibration frequency spectrum of the undercarriage and/or the spoiler is not in the preset range, the vibration frequency spectrum of the undercarriage and/or the spoiler is abnormal.
A third aspect of the present application provides a computer readable storage medium comprising computer instructions which, when run on a computing device, cause the computing device to perform the aircraft testing method of the first or second aspect.
A fourth aspect of the present application provides a computing device comprising a processor and a memory, the memory for storing instructions, the processor for invoking the instructions in the memory to cause the computing device to perform an aircraft testing method according to the first or second aspect.
It should be understood that the computer-readable storage medium of the third aspect and the computing device of the fourth aspect provided above both correspond to the method of the first aspect and the method of the second aspect, and therefore, the beneficial effects achieved by the computer-readable storage medium of the third aspect and the computing device of the fourth aspect may refer to the beneficial effects in the corresponding method provided above, and are not described herein again.
Drawings
Fig. 1 is a schematic diagram of an aircraft testing system provided in an embodiment of the present application.
Fig. 2 is a flowchart of an aircraft testing method according to an embodiment of the present application.
Fig. 3 is a schematic diagram of a computing device provided by an embodiment of the present application.
Detailed Description
For ease of understanding, some descriptions of concepts related to the embodiments of the present application are given by way of illustration and reference.
In the present application, "at least one" means one or more, "and" a plurality "means two or more. "and/or" describes an association relationship of associated objects, meaning that three relationships may exist, e.g., A and/or B may represent: a exists alone, A and B exist simultaneously, and B exists alone, wherein A and B can be singular or plural. The terms "first," "second," "third," "fourth," and the like in the description and in the claims and drawings of the present application, if any, are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order.
Fig. 1 is a schematic diagram of an aircraft testing system provided in an embodiment of the present application.
As shown in fig. 1, an aircraft testing system 10 provided in the embodiment of the present application includes a mobile control end 11, a main control server 12, a landing gear testing subsystem 13, and a spoiler testing subsystem 14. The landing gear testing subsystem 13 is used to obtain test data for a landing gear 15 of the aircraft and the spoiler testing subsystem 14 is used to obtain test data for a spoiler 16 of the aircraft.
In the embodiment of the present application, the landing gear testing subsystem 13 and the spoiler testing subsystem 14 each include an edge controller, an analog-to-digital converter, and a sensor. Referring to fig. 1, the landing gear testing subsystem 13 includes an edge controller 131, an analog-to-digital converter 132, and a sensor 133, and the spoiler testing subsystem 14 includes an edge controller 141, an analog-to-digital converter 142, and a sensor 143. Sensor 133 is used to collect data from landing gear 15 and sensor 143 is used to collect data from spoiler 16. The sensors 133 and 143 collect analog signals, the analog-to-digital converter 132 converts the analog signals collected by the sensor 133 into digital signals, and the analog-to-digital converter 142 converts the analog signals collected by the sensor 143 into digital signals. The edge controllers 131 and 141 are respectively in communication with the main control server 12, and respectively process digital signals corresponding to the landing gear 15 and the spoiler 16.
In the embodiment of the present application, the sensors 133 and 143 each include an angle sensor and a vibration sensor. Referring to fig. 1, the sensors 133 include an angle sensor 1331 and a vibration sensor 1332, and the sensors 143 include an angle sensor 1431 and a vibration sensor 1432. The angle sensor 1331 is used to acquire the offset angle of the landing gear 15, and the angle sensor 1431 is used to acquire the offset angle of the spoiler 16. Vibration sensor 1332 is used to collect the amplitude of vibration of landing gear 15 and vibration sensor 1432 is used to collect the amplitude of vibration of spoiler 16.
The mobile control terminal 11 may be a mobile phone, a tablet computer, an intelligent watch, an intelligent bracelet, a notebook computer, an intelligent sound box, an on-board computer, or the like. The mobile control terminal 11 can perform man-machine interaction with a user through a keyboard, a mouse, a remote controller, a touch panel or a voice control device.
By using the aircraft testing system 10 shown in fig. 1, a user can send a test command through the mobile control terminal 11, the main control server 12 controls the landing gear testing subsystem 13 and the spoiler testing subsystem 14 to acquire test data according to the test command, and judges whether the landing gear 15 and the spoiler 16 work normally according to the test data, so that efficient testing of the landing gear 15 and the spoiler 16 is realized.
In other embodiments of the present application, the aircraft testing system 10 may also include other testing subsystems. For example, the aircraft testing system 10 further includes an atmospheric temperature and humidity testing subsystem for testing the atmospheric temperature and humidity of the environment in which the aircraft is located. As another example, the aircraft testing system 10 may further include an atmospheric dust testing subsystem for testing the environment in which the aircraft is located for atmospheric dust. The atmospheric temperature and humidity testing subsystem comprises a temperature and humidity sensor, and the atmospheric dust testing subsystem comprises a dust sensor.
Fig. 2 is a flowchart of an aircraft testing method according to an embodiment of the present application. The aircraft testing method may use an aircraft testing system (e.g., the aircraft testing system 10 shown in fig. 1) to test the landing gear and spoilers of an aircraft. The order of the steps in the flow chart may be changed and some steps may be omitted according to different needs.
201, the mobile control end issues a test command of the landing gear and the spoiler to the main control server.
For example, referring to fig. 1, the mobile control terminal 11 issues a test command for the landing gear 15 and the spoiler 16 to the main control server 12.
The test command issued by the mobile control end can include enabling signals and sampling frequencies corresponding to the undercarriage and the spoiler. The enable signal is used to cause the landing gear testing subsystem and the spoiler testing subsystem to begin testing the landing gear and the spoiler. The sampling frequency is the frequency at which the offset angle and vibration amplitude of the landing gear and spoiler are collected. In one embodiment of the present application, the sampling frequency of the vibration amplitude is greater than the sampling frequency of the offset angle. The frequency of the offset angle may be several kHz (e.g., 8 kHz) and the sampling frequency of the vibration amplitude may be several tens of kHz (e.g., 28kHz or 56 kHz).
202, the main control server sends the test command to the edge controllers corresponding to the landing gear and the spoiler.
For example, referring to fig. 1, the main control server 12 sends a test command corresponding to the landing gear 15 to the edge controller 131, and sends a test command corresponding to the spoiler 16 to the edge controller 141.
The main control server and the edge controllers corresponding to the undercarriage and the spoiler can be connected through a service bus, and the main control server can send a test command to the edge controllers corresponding to the undercarriage and the spoiler through the service bus.
203, after the edge controllers corresponding to the undercarriage and the spoiler receive the test command, the angle sensors acquire the offset angles of the undercarriage and the spoiler within the first preset time, and the vibration sensors acquire the vibration amplitudes of the undercarriage and the spoiler within the second preset time.
For example, referring to fig. 1, after receiving a test command for undercarriage 15, edge controller 131 collects an offset angle of undercarriage 15 according to a sampling frequency corresponding to undercarriage 15; after receiving the test command of the spoiler 16, the edge controller 141 acquires the offset angle of the spoiler 16 according to the sampling frequency corresponding to the spoiler 16.
The data collected by the angle sensor and the vibration sensor are analog signals.
The first preset time is greater than or equal to the movement period of the undercarriage, and the second preset time is greater than or equal to the movement period of the spoiler. The first preset time and the second preset time may be the same or different. For example, the movement period of the landing gear is 1-2 minutes, the movement period of the spoiler is 1-3 minutes, and the first and second preset times may be set to 5 minutes.
In the embodiment of the present application, the offset angle of the landing gear includes an angle between the landing gear and the wheel, and an angle between the landing gear and the fuselage, and the offset angle of the spoiler includes an angle at which the spoiler is lifted and deployed.
In one embodiment of the present application, a user may manually activate the landing gear and spoiler to initiate movement thereof before the test command is received by the respective edge controllers of the landing gear and spoiler. The manual actuation of the landing gear and spoiler provides greater safety. The landing gear and the spoiler are provided with corresponding motion controllers respectively, and the landing gear and the spoiler are controlled through the corresponding motion controllers.
In another embodiment of the present application, after the edge controller corresponding to the landing gear and the spoiler receives the test command, an activation command may be sent to the motion controller corresponding to the landing gear and the spoiler to activate the landing gear and the spoiler. The automatic start of the landing gear and the spoiler has higher test automation degree.
And 204, carrying out Fourier transform on the vibration amplitude of the landing gear and the spoiler by the edge controller to obtain the vibration frequency spectrum of the landing gear and the spoiler.
For example, referring to FIG. 1, edge controller 131 performs a Fourier transform on the amplitude of the vibration of landing gear 15 to obtain a frequency spectrum of the vibration of landing gear 15; the edge controller 141 performs fourier transform on the vibration amplitude of the spoiler 16, and obtains a vibration spectrum of the spoiler 16.
In one embodiment of the present application, the edge controller may pre-process the amplitude of the vibration of the landing gear and spoiler prior to fourier transforming the amplitude of the vibration of the landing gear and spoiler. The preprocessing of the vibration amplitude may include filling missing values in the vibration amplitude.
The K-nearest neighbor algorithm may be used to determine K data nearest to the missing value (e.g., determine K data nearest to the missing value according to the euclidean distance), and the missing value may be estimated by averaging the values of the K data in a weighted manner.
Other methods may also be used to fill in the missing values. For example, the missing values may be filled in by a method of regression fitting or interpolation.
The preprocessing of the vibration amplitude may also include correcting for outliers in the vibration amplitude. Outliers are values that deviate significantly from other data.
The method of correcting the abnormal value for the vibration amplitude may be the same as the method of filling the missing value. For example, a K-nearest neighbor algorithm may be used to determine K data nearest to the outlier (e.g., determine K data nearest to the outlier according to the euclidean distance), and estimate the correction value of the outlier by weighted averaging the values of the K data. Or correcting the abnormal value by a regression fitting method or an interpolation method.
The method of correcting the abnormal value for the vibration amplitude may also be different from the method of filling the missing value.
The edge controller sends the offset angle and vibration spectrum of the landing gear and spoiler to the master server 205.
For example, referring to fig. 1, the edge controller 131 transmits the offset angle and vibration spectrum of the landing gear 15 to the main control server 12, and the edge controller 141 transmits the offset angle and vibration spectrum of the spoiler 16 to the main control server 12.
As described above, the main control server and the edge controller may be connected via a service bus, and the edge controller may transmit the offset angle and the vibration spectrum of the undercarriage and the spoiler to the main control server via the service bus.
And 206, judging whether the offset angle and the vibration frequency spectrum of the undercarriage and the spoiler are abnormal or not by the main control server to obtain the test result of the undercarriage and the spoiler.
Whether the offset angle of the landing gear and the spoiler is abnormal or not is judged, namely whether the movement of the landing gear and the spoiler (namely the movement of the landing gear relative to the wheels and the body and the lifting and unfolding of the spoiler) is abnormal or not is judged. In an embodiment of the present application, the main control server determines whether an offset angle of the undercarriage and the spoiler is within a preset angle range, and if the offset angle of the undercarriage and the spoiler is within the preset angle range, the offset angle of the undercarriage and the spoiler is normal (i.e., the movement of the undercarriage and the spoiler is normal). Otherwise, if the offset angle of the landing gear or the spoiler is not within the preset angle range, the offset angle of the landing gear or the spoiler is abnormal (i.e., the movement of the landing gear or the spoiler is abnormal).
For example, the predetermined angle range of the spoiler is [38, 42] (in degrees), the main control server determines whether the offset angle of the spoiler is within the predetermined angle range, and if the offset angle of the spoiler is within the predetermined angle range, the offset angle of the spoiler is normal. Otherwise, if the offset angle of the spoiler is not within the preset angle range, the offset angle of the spoiler is abnormal.
And judging whether the vibration frequency spectrums of the undercarriage and the spoiler are abnormal or not, namely judging whether the vibration frequency spectrums of the undercarriage and the spoiler are abnormal or not. In an embodiment of the present application, the main control server determines whether the frequency of the resonance point of the vibration spectrum of the undercarriage and the spoiler is within a preset frequency range, and if the frequency of the resonance point of the vibration spectrum of the undercarriage and the spoiler is within the preset frequency range, the vibration spectrum of the undercarriage and the spoiler is normal (that is, the vibration of the undercarriage and the spoiler is normal). Otherwise, if the frequency of the resonance point of the vibration spectrum of the landing gear or the spoiler is within the preset range, the vibration spectrum of the landing gear or the spoiler is abnormal (namely the vibration of the landing gear or the spoiler is abnormal).
In one embodiment of the present application, the master control server may sample the vibration amplitude of the landing gear and spoiler. The vibration amplitude sampling rate that the vibration sensor gathered is higher, and data bulk is great, in order to can see the vibration waveform better at the mobile control end, need carry out sampling process to the vibration amplitude who gathers.
And 207, the main control server sends the test results of the undercarriage and the spoiler to the mobile control end.
In one embodiment of the application, if the offset angle or the vibration spectrum of the landing gear or the spoiler is abnormal, the main control server outputs an abnormal prompt message.
The main control server can send abnormal prompt information to a preset user through mails, short messages and instant communication tools.
The master control server can send out abnormal prompt information in the modes of voice, characters and the like.
In an embodiment of the present application, if the offset angle or the vibration spectrum of the landing gear or the spoiler is abnormal, the main control server may send a stop command to an edge controller corresponding to the landing gear or the spoiler, and after receiving the stop command, the edge controller sends a stop command to a motion controller corresponding to the landing gear or the spoiler, so as to stop the landing gear or the spoiler.
In one embodiment of the application, the main control server sends the vibration amplitudes of the sampled undercarriage and spoiler to the mobile control terminal.
And 208, after the mobile control end receives the test results of the undercarriage and the spoiler, displaying the test results of the undercarriage and the spoiler at the mobile control end.
In one embodiment of the application, the main control server further sends the sampled vibration amplitudes of the undercarriage and the spoiler to the mobile control terminal. And after the mobile control end receives the vibration amplitudes of the undercarriage and the spoiler after sampling processing, displaying the vibration waveforms of the undercarriage and the spoiler at the mobile control end according to the vibration amplitudes of the undercarriage and the spoiler after sampling processing.
In the embodiment shown in fig. 2, a user sends a test command through the mobile control end, the main control server obtains test data of the undercarriage and the spoiler according to the test command, and whether the undercarriage and the spoiler work normally is judged according to the test data, so that efficient testing of the undercarriage and the spoiler is realized.
The embodiment shown in fig. 2 is illustrated for the case of simultaneous landing gear and spoiler testing. In other embodiments of the present application, the landing gear or the spoiler may be tested separately, and the testing method refers to the related description of fig. 2, which is not described herein again.
Fig. 3 is a schematic diagram of a computing device (a master server or an edge controller) according to an embodiment of the present application.
The computing device 30 includes a memory 301, a processor 302, and a computer program 303, such as an aircraft test program, stored in the memory 301 and executable on the processor 302. The steps in the above described embodiments of the aircraft testing method are implemented when processor 302 executes computer program 303. Illustratively, the computer program 303 may be partitioned into one or more modules that are stored in the memory 301 and executed by the processor 302 to perform the aircraft testing method described above. The one or more modules may be a series of computer program instruction segments capable of performing certain functions that are used to describe the execution of computer program 303 in computing device 30.
Computing device 30 may be a desktop computer, a laptop computer, a server, etc. Those skilled in the art will appreciate that the schematic diagram 3 is merely an example of the computing device 30 and does not constitute a limitation of the computing device 30 and may include more or less components than shown, or combine certain components, or different components, e.g., the computing device 30 may also include input-output devices, network access devices, buses, etc.
The Processor 302 may be a Central Processing Unit (CPU), other general purpose Processor, a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field Programmable Gate Array (FPGA) or other Programmable logic device, discrete Gate or transistor logic, discrete hardware components, etc. The general purpose processor may be a microprocessor or the processor 302 may be any conventional processor or the like, the processor 302 being the control center for the computing device 30 and connecting the various parts of the overall computing device 30 using various interfaces and lines.
Memory 301 may be used to store computer programs 303, and processor 302 may implement various functions of computing device 30 by running or executing computer programs or modules stored in memory 301, as well as by invoking data stored in memory 301. The memory 301 may mainly include a storage program area and a storage data area, wherein the storage program area may store an operating system, an application program required by at least one function (such as a sound playing function, an image playing function, etc.), and the like; the storage data area may store data created according to use of the computing device 30. Further, the memory 301 may include a non-volatile memory, such as a hard disk, a memory, a plug-in hard disk, a Smart Media Card (SMC), a Secure Digital (SD) Card, a Flash memory Card (Flash Card), at least one magnetic disk storage device, a Flash memory device, or other non-volatile solid state storage device.
The modules integrated by the computing device 30 may be stored in a storage medium if implemented in the form of software functional modules and sold or used as separate products. Based on such understanding, all or part of the flow in the method of the embodiments described above may be implemented by a computer program, which is stored in a storage medium and used for instructing related hardware to implement the steps of the embodiments of the methods described above when being executed by a processor. Wherein the computer program comprises computer program code, which may be in the form of source code, object code, an executable file or some intermediate form, etc. The computer readable medium may include: any entity or device capable of carrying computer program code, recording medium, usb disk, removable hard disk, magnetic disk, optical disk, computer Memory, Read-Only Memory (ROM).
In the several embodiments provided in the present application, it should be understood that the disclosed system, apparatus and method may be implemented in other manners.
The modules described as separate parts may or may not be physically separate, and parts displayed as modules may or may not be physical modules, may be located in one place, or may be distributed on a plurality of network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment.
In addition, functional modules in the embodiments of the present application may be integrated into one processing module, or each of the modules may exist alone physically, or two or more modules are integrated into one module. The integrated module can be realized in a hardware mode, and can also be realized in a mode of hardware and a software functional module.
The integrated module implemented in the form of a software functional module may be stored in a storage medium. The software functional module is stored in a storage medium and includes several instructions to enable a computing device (which may be a personal computer, a server, or a network device) or a processor (processor) to execute some steps of the methods according to the embodiments of the present application.
It will be evident to those skilled in the art that the present application is not limited to the details of the foregoing illustrative embodiments, and that the present application may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the application being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference signs in the claims shall not be construed as limiting the claim concerned. Furthermore, it is to be understood that the word "comprising" does not exclude other modules or steps, and the singular does not exclude the plural. A plurality of modules or means recited in the system claims may also be implemented by one module or means in software or hardware. The terms first, second, etc. are used to denote names, but not any particular order.

Claims (10)

1. An aircraft testing method is applied to a master control server, and is characterized by comprising the following steps:
receiving a test command of the undercarriage and/or the spoiler sent by the mobile control end;
sending the test command to an edge controller corresponding to the undercarriage and/or the spoiler, so that the edge controller collects the offset angle and the vibration amplitude of the undercarriage and/or the spoiler within a preset time, and performs Fourier transform on the vibration amplitude of the undercarriage and/or the spoiler to obtain a vibration frequency spectrum of the undercarriage and/or the spoiler;
receiving the offset angle and the vibration frequency spectrum of the landing gear and/or the spoiler sent by the edge controller;
judging whether the offset angle and the vibration frequency spectrum of the undercarriage and/or the spoiler are abnormal or not to obtain a test result of the undercarriage and/or the spoiler;
and sending the test result of the undercarriage and/or the spoiler to the mobile control end.
2. An aircraft testing method according to claim 1, wherein the landing gear offset angle comprises an angle between the landing gear and a wheel, and an angle between the landing gear and a fuselage, and the spoiler offset angle comprises an angle at which the spoiler is raised and deployed.
3. An aircraft testing method according to claim 1, wherein determining whether the vibration spectrum of the landing gear and/or spoiler is abnormal comprises:
judging whether the frequency of a resonance point of a vibration frequency spectrum of the undercarriage and/or the spoiler is within a preset frequency range;
and if the frequency of the resonance point of the vibration frequency spectrum of the undercarriage and/or the spoiler is not in the preset range, the vibration frequency spectrum of the undercarriage and/or the spoiler is abnormal.
4. An aircraft testing method according to claim 1, wherein the method further comprises:
sampling data for the amplitude of vibration of the landing gear and/or spoiler;
and sending the vibration amplitude of the undercarriage and/or the spoiler after data sampling to the movement control end.
5. An aircraft testing method applied to an edge controller, the method comprising:
receiving a test command of the undercarriage and/or the spoiler sent by the main control server;
acquiring the offset angle and the vibration amplitude of the undercarriage and/or the spoiler within a preset time;
carrying out Fourier transform on the vibration amplitude of the undercarriage and/or the spoiler to obtain a vibration frequency spectrum of the undercarriage and/or the spoiler;
and sending the offset angle and the vibration frequency spectrum of the undercarriage and/or the spoiler to the main control server, so that the main control server judges whether the offset angle and the vibration frequency spectrum of the undercarriage and/or the spoiler are abnormal or not, and a test result of the undercarriage and/or the spoiler is obtained.
6. An aircraft testing method according to claim 5, wherein the landing gear offset angle comprises an angle between the landing gear and a wheel, and an angle between the landing gear and a fuselage, and the spoiler offset angle comprises an angle at which the spoiler is raised and deployed.
7. An aircraft testing method according to claim 5, wherein the method further comprises:
and after receiving the test command, sending a starting instruction to a motion controller corresponding to the falling frame and/or the spoiler so as to start the falling frame and/or the spoiler.
8. An aircraft testing method according to claim 5, wherein determining whether the vibration spectrum of the landing gear and/or spoiler is abnormal comprises:
judging whether the frequency of a resonance point of a vibration frequency spectrum of the undercarriage and/or the spoiler is within a preset frequency range;
and if the frequency of the resonance point of the vibration frequency spectrum of the undercarriage and/or the spoiler is not in the preset range, the vibration frequency spectrum of the undercarriage and/or the spoiler is abnormal.
9. A computer readable storage medium comprising computer instructions which, when executed on a computing device, cause the computing device to perform the aircraft testing method of any of claims 1 to 4, or 5 to 8.
10. A computing device, comprising a processor and a memory, the memory to store instructions, the processor to invoke the instructions in the memory, causing the computing device to perform the aircraft testing method of any of claims 1 to 4, or 5 to 8.
CN202210632101.5A 2022-06-07 2022-06-07 Aircraft testing method and related equipment Active CN114701663B (en)

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