CN114537705B - Airplane flaring conduit assembly method and device with errors, storage medium and equipment - Google Patents
Airplane flaring conduit assembly method and device with errors, storage medium and equipmentDownload PDFInfo
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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
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
Description
Technical Field
The application relates to the technical field of airplane assembly, in particular to an airplane flaring conduit assembling method and device with errors, a storage medium and equipment.
Background
The flaring guide pipe is a key connecting piece of an airplane system and is widely applied to hydraulic systems, environmental control systems, fuel oil systems and engine systems of airplanes. In the current assembly and manufacturing links of domestic airplanes, the leakage problem of a flared conduit system is very common, and particularly the leakage of the flared conduit at the assembly joint is particularly common. The leakage problem at the flared conduit fitting connection is mainly caused by the angle error during conduit fitting, the existing research generally considers reducing the fitting angle error as much as possible or adopts other methods to compensate the angle error, the compensation fitting mode can increase the production cost, the assembly with error is particularly dependent on the experience of an operator, the required fitting torque is difficult to accurately control, and the fitting quality is low.
Disclosure of Invention
The application mainly aims to provide an airplane flaring conduit assembling method and device with errors, a storage medium and electronic equipment, and aims to solve the problem that in the prior art, the quality of airplane flaring conduit assembling with errors is low.
In order to achieve the above purpose, the embodiments of the present application adopt the following technical solutions:
in a first aspect, an embodiment of the present application provides an airplane flared conduit band error assembly method, including the following steps:
establishing a target library, wherein the step of establishing the target library comprises the following steps:
obtaining an equivalent straight catheter model of a target catheter;
obtaining the critical sealing pressure of the equivalent straight conduit model under the critical installation torque according to the equivalent straight conduit model;
obtaining the critical installation torque of the equivalent straight guide pipe model under different angle errors according to the critical sealing pressure under the critical installation torque of the equivalent straight guide pipe model;
establishing a target library according to the critical installation torque of the equivalent straight conduit model under different angle errors;
acquiring an angle error when a target guide pipe is installed;
matching a target critical mounting moment under the angle error from a target library according to the angle error; the target library stores critical mounting moments under different angle errors;
obtaining an actual mounting moment according to a target critical mounting moment;
and assembling the target guide pipe according to the actual installation moment.
In one possible implementation manner of the first aspect, before the step of obtaining the critical sealing pressure of the equivalent straight conduit model at the critical installation torque according to the equivalent straight conduit model, the method further comprises:
and carrying out an air tightness test according to the equivalent straight guide pipe model to obtain the critical installation torque of the equivalent straight guide pipe model.
In one possible implementation manner of the first aspect, the step of obtaining the critical sealing pressure of the equivalent straight conduit model at the critical installation torque according to the equivalent straight conduit model comprises:
obtaining an end face sealing line of the equivalent straight guide pipe model under the critical installation torque according to the equivalent straight guide pipe model;
and obtaining the critical sealing pressure of the equivalent straight conduit model under the critical installation torque according to the end face sealing line.
In one possible implementation manner of the first aspect, the step of obtaining the critical installation torque of the equivalent straight conduit model under different angle errors according to the critical sealing pressure of the equivalent straight conduit model under the critical installation torque comprises:
applying mounting torque to the equivalent straight conduit model under different angle errors according to the critical sealing pressure of the equivalent straight conduit model under the critical mounting torque so as to obtain the sealing pressure of the equivalent straight conduit model under different angle errors;
adjusting the mounting torque to obtain the critical mounting torque of the equivalent straight guide pipe model under different angle errors; wherein the critical seating torque is obtained when a difference between the sealing pressure and the critical sealing pressure is within an error range.
In one possible implementation manner of the first aspect, the step of obtaining an equivalent straight catheter model of the target catheter comprises:
acquiring characteristic parameters of a target catheter; wherein the characteristic parameter comprises a diameter;
establishing an equivalent straight catheter model according to the characteristic parameters of the target catheter; wherein the length of the equivalent straight conduit model is not less than five times the diameter.
In a second aspect, the present application provides an aircraft flared conduit with error assembly apparatus, including:
the first acquisition module is used for acquiring the angle error of the target guide pipe during installation;
the matching module is used for matching a target critical mounting moment under the angle error from a target library according to the angle error; the target library stores critical mounting moments under different angle errors;
the second acquisition module is used for acquiring an actual mounting moment according to the target critical mounting moment;
and the execution module is used for assembling the target guide pipe according to the actual mounting moment.
In a third aspect, an embodiment of the present application provides a computer-readable storage medium, which stores a computer program, and when the computer program is loaded and executed by a processor, the method for assembling an aircraft flared conduit with an error is implemented as provided in any one of the first aspect.
In a fourth aspect, an embodiment of the present application provides an electronic device, including a processor and a memory, wherein,
the memory is used for storing a computer program;
the processor is configured to load and execute the computer program to cause the electronic device to perform the method for assembling the airplane flared conduit with the error.
Compared with the prior art, the beneficial effects of this application are:
the embodiment of the application provides an airplane flaring conduit assembling method with errors, a device, a storage medium and electronic equipment, wherein the method comprises the following steps: acquiring an angle error when a target guide pipe is installed; matching a target critical mounting moment under the angle error from a target library according to the angle error; the target library stores critical mounting moments under different angle errors; obtaining an actual mounting moment according to a target critical mounting moment; and assembling the target guide pipe according to the actual installation moment. The method of the application matches the angle error value in a target library established in advance by obtaining the angle error when the guide pipe is installed, the target library is established by summarizing the existing assembly data and test simulation data, the angle errors correspond to the critical assembly torques one by one, the critical assembly torques under different error angles can be rapidly acquired, the critical assembly torques are critical point values of the assembly torques obtained by long-term assembly data accumulation and test simulation, the critical assembly torques exceed the critical assembly torques, the assembly airtightness can be ensured, the critical assembly torques are lower than the critical assembly torques, and the leakage risk exists, and adjusting according to the critical mounting moment to obtain an actual mounting moment so as to ensure air tightness, and then carrying out error assembly on the airplane flaring guide pipe under the actual mounting moment, so that the quality of error assembly of the airplane flaring guide pipe can be greatly improved.
Drawings
Fig. 1 is a schematic structural diagram of an electronic device in a hardware operating environment according to an embodiment of the present application;
fig. 2 is a schematic flow chart of an airplane flared conduit error assembly method according to an embodiment of the present application;
FIG. 3 is a functional block diagram of an aircraft flared conduit with error assembly apparatus according to an embodiment of the present disclosure;
fig. 4 is a schematic diagram of establishing an equivalent straight conduit model in the method for assembling an airplane flared conduit with an error according to the embodiment of the present application;
fig. 5 is a schematic view of an assembly structure of an equivalent straight duct model in an airplane flared duct belt error assembly method according to an embodiment of the present application during an airtight test;
the labels in the figure are: 101-processor, 102-communication bus, 103-network interface, 104-user interface, 105-memory, 1-target catheter, 2-equivalent straight catheter model, 3-flat nozzle, 4-outer nut, 5-pipe joint, 6-plugging end.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
The main solution of the embodiment of the application is as follows: the method comprises the steps of providing an airplane flaring conduit assembling method with errors, a device, a storage medium and equipment, and obtaining an angle error when a target conduit is installed; matching a target critical mounting moment under the angle error from a target library according to the angle error; the target library stores critical mounting moments under different angle errors; obtaining an actual mounting moment according to a target critical mounting moment; and assembling the target guide pipe according to the actual installation moment.
In the prior art, generally, the mounting angle error is reduced as much as possible or the angle error is compensated by adopting other methods for assembling the flaring guide pipe of the airplane, but in the actual production of a manufacturing enterprise, in order to take production cost and benefit into consideration, the smaller angle error is generally not compensated, but the sealing performance of the connection part of the guide pipe is ensured by adopting larger mounting torque, but the control of the mounting torque is mostly dependent on the experience of operators, the obtained mounting torque is inaccurate, so that the assembly quality is lower, and the high-quality batch production of products of the manufacturing enterprise is restricted.
Therefore, the method provides a solution, the angle error which is easy to obtain during installation of the guide pipe is directly obtained, the critical installation torque under the angle error is matched in the target library according to the angle error, the critical installation torque correspondingly required under different angle errors is stored in the target library, the actual installation torque is obtained according to the adjustment of the critical installation torque, and finally the guide pipe is assembled with errors. The speed and the precision of the installation moment can be improved, and the quality of the airplane flaring guide pipe with error assembly in the prior art is improved.
Referring to fig. 1, fig. 1 is a schematic structural diagram of an electronic device in a hardware operating environment according to an embodiment of the present application, where the electronic device may include: aprocessor 101, such as a Central Processing Unit (CPU), acommunication bus 102, auser interface 104, anetwork interface 103, and amemory 105. Wherein thecommunication bus 102 is used for enabling connection communication between these components. Theuser interface 104 may comprise a Display screen (Display), an input unit such as a Keyboard (Keyboard), and theoptional user interface 104 may also comprise a standard wired interface, a wireless interface. Thenetwork interface 103 may optionally include a standard wired interface, a WIreless interface (e.g., a WIreless-FIdelity (WI-FI) interface). TheMemory 105 may optionally be a storage device independent of theprocessor 101, and theMemory 105 may be a Random Access Memory (RAM) Memory, or a Non-Volatile Memory (NVM), such as at least one disk Memory; theprocessor 101 may be a general-purpose processor including a central processing unit, a network processor, etc., and may also be a digital signal processor, an application specific integrated circuit, a field programmable gate array or other programmable logic device, discrete gate or transistor logic, discrete hardware components.
Those skilled in the art will appreciate that the configuration shown in fig. 1 does not constitute a limitation of the electronic device and may include more or fewer components than those shown, or some components may be combined, or a different arrangement of components.
As shown in fig. 1, thememory 105, which is a storage medium, may include therein an operating system, a data storage module, a network communication module, a user interface module, and an electronic program.
In the electronic device shown in fig. 1, thenetwork interface 103 is mainly used for data communication with a network server; theuser interface 104 is mainly used for data interaction with a user; theprocessor 101 and thememory 105 in the present invention may be disposed in an electronic device, and the electronic device invokes the airplane flare conduit error assembling apparatus stored in thememory 105 through theprocessor 101, and executes the airplane flare conduit error assembling method provided in the embodiment of the present application.
Referring to fig. 2, based on the hardware device of the foregoing embodiment, an embodiment of the present application provides an airplane flared conduit misassembly method, including the following steps:
s20: acquiring an angle error when the target guide pipe 1 is installed;
in the concrete implementation, the target conduit 1 is a conduit to be assembled, and the angle error during installation refers to the degree of angular deviation of the installation angle during actual installation from the installation angle during theoretical installation, for example: the target conduit 1 and the other connecting piece theoretically need to be coaxial, but when the target conduit and the other connecting piece are actually installed, the axes of the target conduit and the other connecting piece form an included angle of 0.3 degrees, and the degree of the included angle is an angle error; the angle error can be obtained by scanning the structure of the target catheter 1 by scanning equipment to obtain the angle deviation, or by measuring the levelness of the target catheter 1 and the connecting piece, and calculating the angle error by the difference of the levelness obtained under the same reference. The angle error can be known according to actual use requirements, the control is within an error range, the error range is determined according to actual requirements, if the assembly quality requirement is high, the error range needs to be controlled within 1 degree, the error range can be properly enlarged to within 1.5 degrees or 2 degrees for general assembly, when the obtained angle error is not within the range searched by the user, the problem exists in the installation process, and the installation needs to be carried out after adjustment, so that the installation in the embodiment refers to correct installation within the error range.
S30: matching a target critical mounting moment under the angle error from a target library according to the angle error; the target library stores critical mounting moments under different angle errors;
in the specific implementation process, the critical installation torque is a critical value of the installation torque between sealing and leakage when the guide pipe is assembled, namely if the torque of the guide pipe during assembly is smaller than the critical installation torque, leakage can occur after assembly, and if the torque is larger than the critical installation torque, the sealing effect is achieved after assembly. The critical installation torque information required by the assembly of each different type of target guide pipe 1 is stored in the target library, and the critical installation torque information required by the assembly of each different type of guide pipe under different angle errors is also stored in the target library, so that the adjustment when required is convenient, the source of the critical installation torque information can be empirical data in the prior assembly, and can also be obtained after experimental analysis, for example: for the existing same-type conduit assembly, critical installation moment information can be obtained after various empirical data in the previous assembly are collected, no empirical data can be provided for a newly-researched project, but because products are manufactured in batches, the critical installation moment of the newly-researched product can be obtained through steps of manual modeling, simulation analysis, data processing and the like and is supplemented to a target library as an information source, the time is only consumed on one test for the promotion of the newly-researched project, the subsequent mass production assembly time can be greatly saved, the target library contains more and more comprehensive information along with the time lapse and the development of enterprises, and the assembly quality and the production efficiency are greatly improved.
S40: obtaining an actual mounting moment according to a target critical mounting moment;
in the specific implementation process, the target critical installation torque is the target critical installation torque required by the target conduit 1 under the angle error of the target conduit 1, and according to the target critical installation torque, if sealing assembly is to be realized, the actual installation torque needs to be adjusted, so that the actual installation torque of the target conduit 1 is larger than the critical installation torque, and the larger the difference is, the higher the tightness degree of assembly is; although theoretically actual installation moment is bigger, sealed effect is better, but after actual installation moment increases to certain extent, increase moment size again and be little to the promotion meaning of leakproofness, the random installation is the while and the inseparable great installation moment of pursuit, guarantee under the prerequisite of leakproofness suitable increase in order to promote assembly stability can.
S50: assembling the target guide pipe 1 according to the actual mounting moment;
in the specific implementation process, after the actually required installation torque is determined, the target catheter 1 can be assembled with errors according to the installation torque, the assembly can be completed through the control of a mechanical arm, a workbench and the like, the torque output can be set in advance through a program, and the assembly is realized through the output of the torque by an assembly tool.
According to the method for assembling the error-carrying flared conduit of the airplane, the obtained angle error of the target conduit 1 during installation is matched in a target library to obtain the target critical installation torque of the target conduit 1 under the angle error, the installation torque required during actual assembly is adjusted according to the critical installation torque to ensure the sealing performance, and finally, the assembly is carried out according to the actual installation torque obtained through adjustment. According to the method, through the steps, the critical installation torque and the actual installation torque of the target catheter 1 under any angle error can be rapidly acquired, the critical installation torque corresponds to the angle error one to one, the accuracy of the acquired installation torque is improved, and high assembly quality can still be ensured under the condition of realizing convenient assembly with errors.
In one embodiment, at step S20: before the step of acquiring the angle error of the target conduit 1 during installation, the method further comprises:
s10: and establishing a target library.
In the specific implementation process, a target library is established in advance so as to be used repeatedly in the following process, and the expression forms of data in the established target library are various, such as: in a table form, the data of the type, the angle error and the critical installation torque of the guide pipe correspond one to one; the coordinate form can be more visual and accurate than the table form reaction, the points reflecting critical mounting moments corresponding to different angle errors are connected into a line in a coordinate system, the two sides of the line respectively represent a sealing area and a leakage area, and the change trend can be judged according to the trend of the line so as to determine the more appropriate actual mounting moment.
In one embodiment, as shown in FIG. 4, an implementation of creating a target library is provided, comprising the steps of:
s101: obtaining an equivalentstraight catheter model 2 of a target catheter 1;
in a specific implementation process, if the target conduit 1 has a bent pipe portion, the bent portion of the target conduit 1 having the bent pipe is eliminated and is equivalent to a straight conduit model to improve the universality of the assembly method, as shown in fig. 4, interference of different conduit shapes is avoided, wherein an implementation manner is provided, the equivalentstraight conduit model 2 is established by extracting key parameters of the target conduit 1 to ensure that the equivalentstraight conduit model 2 can maximally simulate the assembly requirement of the original conduit under the condition of eliminating the shape interference, and accordingly, the step S101: obtaining an equivalentstraight catheter model 2 of a target catheter 1, comprising the steps of:
s1011: acquiring characteristic parameters of the target catheter 1; wherein the characteristic parameter comprises a diameter;
in a specific implementation process, the characteristic parameter refers to a parameter that can reflect the size of the conduit most, and the most important component for the conduit class is the diameter, and in other embodiments, the characteristic parameter may further include a wall thickness, a flaring angle, and the like.
S1012: establishing an equivalentstraight catheter model 2 according to the characteristic parameters of the target catheter 1; wherein, the length of the equivalentstraight conduit model 2 is not less than five times of the diameter;
in the concrete implementation process, because the bent pipe part is eliminated in the process of establishing the equivalent straight conduit, the effective length of the horizontal part of the conduit is relatively shortened, and if the length is reduced relative to the diameter of the conduit, the accuracy of subsequent simulation tests and parameter acquisition is inevitably caused, so that the length of the equivalentstraight conduit model 2 is required to be set to be not less than five times of the diameter, and when the length is less than five times of the diameter, the length compensation is carried out to meet the condition.
S102: obtaining the critical sealing pressure of the equivalentstraight conduit model 2 under the critical installation torque according to the equivalentstraight conduit model 2;
in the specific implementation process, because the effect of the installation torque will directly bring about the pressure change, the simulation can be performed by a mode of establishing a finite element model, in the established finite element model, in order to facilitate subsequent parameter acquisition, assembling parts such as theflat nozzle 3, the outer nut 4 and the pipe joint 5 can be added, and the critical installation torque is accurately converted into the form of critical sealing pressure to be expressed, but it should be noted that no angle error exists during the installation of the equivalent straight conduit at this time, that is, the angle of the coaxial assembly connection error of the flat conduit is zero, and thus, the step S102: according to the equivalentstraight conduit model 2, the critical sealing pressure of the equivalentstraight conduit model 2 under the critical installation torque is obtained, and the method comprises the following steps:
s1021: according to the equivalentstraight conduit model 2, obtaining an end face sealing line of the equivalentstraight conduit model 2 under the critical installation torque;
in the specific implementation process, under the established finite element model, the obtained critical installation moment is used as an input condition, the pressure distribution of the end face of thepipe joint 5 under the critical installation moment, namely the pressure distribution of the assembly end face, is obtained through finite element calculation, and the points with the maximum pressure are connected together along the circumference of the end face of the pipe joint 5 to form a ring, namely an end face sealing line.
S102: obtaining the critical sealing pressure of the equivalentstraight conduit model 2 under the critical installation torque according to the end face sealing line;
in the specific implementation process, because the end face sealing lines are obtained in the state without the error angle, the end face sealing lines are uniformly distributed, and the corresponding pressure distribution is also uniform, at this time, the critical sealing pressure can be obtained and used as a comparison judgment object of parameters obtained in the subsequent process with the error angle.
S103: obtaining the critical installation torque of the equivalent straightguide pipe model 2 under different angle errors according to the critical sealing pressure under the critical installation torque of the equivalent straightguide pipe model 2;
in the specific implementation process, the finite element model is adjusted so that an angle error exists between the equivalentstraight conduit model 2 and thepipe joint 5, each angle error is uniformly increased or decreased, such as 0.3 degree, 0.6 degree, 0.9 degree, 1.2 degree and 1.5 degree, the end face sealing line under the angle error is obtained by referring to the previous steps, and step S103: according to the critical sealing pressure under the critical installation torque of the equivalent straightguide pipe model 2, the critical installation torque of the equivalent straightguide pipe model 2 under different angle errors is obtained, and the method comprises the following steps:
s1031: applying mounting torque to the equivalentstraight conduit model 2 under different angle errors according to the critical sealing pressure under the critical mounting torque of the equivalentstraight conduit model 2 to obtain the sealing pressure of the equivalentstraight conduit model 2 under different angle errors;
in the specific implementation process, the actual assembly with errors is simulated, an installation moment is applied in advance, the sealing pressure at the moment can be determined after the corresponding end face sealing line is obtained, and a basis is provided for the adjustment of the next installation moment.
S1032: adjusting the mounting torque to obtain the critical mounting torque of the equivalent straightguide pipe model 2 under different angle errors; wherein the critical mounting torque is obtained when the difference between the sealing pressure and the critical sealing pressure is within an error range
In the specific implementation process, due to the existence of the angle error, the end face sealing line is not necessarily overlapped with the end face sealing line when the error angle is zero, the size of the installation torque is adjusted at the moment until the difference between the minimum pressure on the end face sealing line under the existence of the angle error and the pressure on the end face sealing line under the zero error is less than two percent, and the obtained installation torque at the moment is the critical installation torque under the error angle.
S104: establishing a target library according to the critical installation torque of the equivalent straightguide pipe model 2 under different angle errors;
in the specific implementation process, after the critical installation moments of the guide pipe under different angle errors are obtained in the previous steps, a target library can be established, the angle errors and the critical installation moments form corresponding relations in the target library, and the critical installation moments can be quickly matched according to the angle errors.
In one embodiment, in step S102: before obtaining the critical sealing pressure of the equivalentstraight conduit model 2 under the critical installation torque according to the equivalentstraight conduit model 2, the method for assembling the flaring conduit of the airplane with the error further comprises the following steps:
carrying out an air tightness test according to the equivalent straightguide pipe model 2 to obtain the critical installation torque of the equivalent straightguide pipe model 2;
in the specific implementation process, as the critical installation moment is a critical value of sealing and leakage, in order to obtain the critical installation moment, an air tightness test is adopted to directly obtain related parameters, as shown in figure 5, the equivalentstraight conduit model 2 is assembled with theflat nozzle 3, the outer nut 4 and the pipe joint 5 with corresponding specifications, no angle error exists between the equivalentstraight conduit model 2 and thepipe joint 5, one end of thepipe joint 5 is plugged to form a plugging end, the other end of thepipe joint 5 is connected with equipment for the air tightness test, certain air pressure is applied and kept for a certain time, whether leakage occurs at the assembly connection part is observed, if leakage occurs, the installation moment is increased, the air tightness test is carried out again until no leakage occurs, and the installation moment at this time is the critical installation moment when no angle error exists; if the leakage does not occur, the mounting torque is reduced, the minimum mounting torque without the leakage is obtained, namely the critical mounting torque, the obtained data can represent the basic sealing performance of the guide pipe through the air tightness test, and the obtained test structure is more reliable.
Referring to fig. 3, based on the same inventive concept as that in the previous embodiment, the embodiment of the present application further provides an airplane flared conduit belt error assembly device, including:
the first acquisition module is used for acquiring the angle error of the target catheter 1 during installation;
the matching module is used for matching a target critical mounting moment under the angle error from a target library according to the angle error; the target library stores critical mounting moments under different angle errors;
the second acquisition module is used for acquiring an actual mounting moment according to the target critical mounting moment;
and the execution module is used for assembling the target guide pipe 1 according to the actual installation moment.
It should be understood by those skilled in the art that the division of each module in the embodiment is only a division of a logic function, and all or part of the modules may be integrated onto one or more actual carriers in actual application, and all of the modules may be implemented in a form called by a processing unit through software, may also be implemented in a form of hardware, or implemented in a form of combination of software and hardware.
Based on the same inventive concept as that in the foregoing embodiments, embodiments of the present application further provide a computer-readable storage medium, which stores a computer program, and when the computer program is loaded and executed by a processor, the method for assembling an airplane flared conduit with an error is implemented as provided in the embodiments of the present application.
In addition, based on the same inventive concept as the foregoing embodiments, the embodiments of the present application further provide an electronic device, which at least includes a processor and a memory, wherein,
the memory is used for storing a computer program;
the processor is used for loading and executing a computer program to enable the electronic device to execute the airplane flaring conduit assembling method with errors.
In some embodiments, the computer-readable storage medium may be memory such as FRAM, ROM, PROM, EPROM, EEPROM, flash, magnetic surface memory, optical disk, or CD-ROM; or may be various devices including one or any combination of the above memories. The computer may be a variety of computing devices including intelligent terminals and servers.
In some embodiments, executable instructions may be written in any form of programming language (including compiled or interpreted languages), in the form of programs, software modules, scripts or code, and may be deployed in any form, including as a stand-alone program or as a module, component, subroutine, or other unit suitable for use in a computing environment.
By way of example, executable instructions may correspond, but do not necessarily have to correspond, to files in a file system, and may be stored in a portion of a file that holds other programs or data, such as in one or more scripts in a hypertext Markup Language (HTML) document, in a single file dedicated to the program in question, or in multiple coordinated files (e.g., files that store one or more modules, sub-programs, or portions of code).
By way of example, executable instructions may be deployed to be executed on one computing device or on multiple computing devices at one site or distributed across multiple sites and interconnected by a communication network.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or system. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or system that comprises the element.
The sequence of the embodiments of the present application is merely for description, and does not represent the advantages and disadvantages of the embodiments.
Through the above description of the embodiments, those skilled in the art will clearly understand that the method of the above embodiments can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware, but in many cases, the former is a better embodiment. Based on such understanding, the technical solutions of the present application may be embodied in the form of a software product, which is stored in a storage medium (e.g., a rom/ram, a magnetic disk, an optical disk) and includes instructions for enabling a multimedia terminal (e.g., a mobile phone, a computer, a television receiver, or a network device) to execute the method of the embodiments of the present application.
In summary, the method, the device, the storage medium and the equipment for assembling the airplane flaring conduit with the error are used for obtaining the angle error when the target conduit 1 is installed; matching a target critical mounting moment under the angle error from a target library according to the angle error; the target library stores critical mounting moments under different angle errors; obtaining an actual mounting moment according to a target critical mounting moment; according to the actual installation torque, the target guide pipe 1 is assembled, the determination precision and the obtaining efficiency of the installation torque required by the airplane flaring guide pipe during assembly are improved, and the assembly quality during assembly with errors is improved.
The above description is only exemplary of the present application and should not be taken as limiting the present application, as any modification, equivalent replacement, or improvement made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (8)
1. An airplane flared conduit belt error assembly method is characterized by comprising the following steps:
establishing a target library, wherein the step of establishing the target library comprises the following steps:
obtaining an equivalent straight catheter model of a target catheter;
obtaining the critical sealing pressure of the equivalent straight guide pipe model under the critical installation torque according to the equivalent straight guide pipe model;
obtaining the critical installation torque of the equivalent straight guide pipe model under different angle errors according to the critical sealing pressure under the critical installation torque of the equivalent straight guide pipe model;
establishing the target library according to the critical installation torque of the equivalent straight conduit model under different angle errors;
acquiring an angle error when the target guide pipe is installed;
matching a target critical mounting moment under the angle error from the target library according to the angle error; the target library stores critical mounting moments under different angle errors;
obtaining an actual mounting moment according to the target critical mounting moment;
and assembling the target guide pipe according to the actual mounting moment.
2. The aircraft flared conduit mismatching method of claim 1, wherein prior to said step of obtaining a critical sealing pressure of said equivalent straight conduit model at a critical installation torque based on said equivalent straight conduit model, said method further comprises:
and carrying out an airtight test according to the equivalent straight guide pipe model so as to obtain the critical mounting torque of the equivalent straight guide pipe model.
3. The method for assembling airplane flared conduit with errors according to claim 1, wherein the step of obtaining the critical sealing pressure of the equivalent straight conduit model at the critical installation torque according to the equivalent straight conduit model comprises:
obtaining an end face sealing line of the equivalent straight guide pipe model under the critical installation torque according to the equivalent straight guide pipe model;
and obtaining the critical sealing pressure of the equivalent straight conduit model under the critical installation torque according to the end face sealing line.
4. The method for assembling airplane flared conduit with errors according to claim 1, wherein the step of obtaining the critical installation torques of the equivalent straight conduit model under different angle errors according to the critical sealing pressure under the critical installation torque of the equivalent straight conduit model comprises:
applying installation torque to the equivalent straight conduit model under different angle errors according to the critical sealing pressure of the equivalent straight conduit model under the critical installation torque so as to obtain the sealing pressure of the equivalent straight conduit model under different angle errors;
adjusting the mounting torque to obtain the critical mounting torque of the equivalent straight guide pipe model under different angle errors; wherein the critical seating torque is obtained when a difference between the sealing pressure and the critical sealing pressure is within an error range.
5. The aircraft flared conduit mismatching method of claim 1, wherein said step of obtaining an equivalent straight conduit model of said target conduit comprises:
acquiring characteristic parameters of the target catheter; wherein the characteristic parameter comprises a diameter;
establishing the equivalent straight catheter model according to the characteristic parameters of the target catheter; wherein the length of the equivalent straight conduit model is not less than five times the diameter.
6. An aircraft flared conduit with error assembly device, comprising:
the first acquisition module is used for acquiring the angle error of the target guide pipe during installation;
the matching module is used for matching a target critical mounting moment under the angle error from a target library according to the angle error; the target library stores critical mounting moments under different angle errors;
the second acquisition module is used for acquiring an actual mounting torque according to the target critical mounting torque;
an execution module for assembling the target conduit according to the actual installation torque.
7. A computer-readable storage medium storing a computer program which, when loaded and executed by a processor, implements the method of assembling aircraft flared conduit with errors as set forth in any one of claims 1-5.
8. An electronic device comprising a processor and a memory, wherein,
the memory is used for storing a computer program;
the processor is configured to load and execute the computer program to cause the electronic device to perform the method of assembling an aircraft flared conduit with errors as set forth in any one of claims 1-5.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210436685.9ACN114537705B (en) | 2022-04-25 | 2022-04-25 | Airplane flaring conduit assembly method and device with errors, storage medium and equipment |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210436685.9ACN114537705B (en) | 2022-04-25 | 2022-04-25 | Airplane flaring conduit assembly method and device with errors, storage medium and equipment |
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| CN114537705A CN114537705A (en) | 2022-05-27 |
| CN114537705Btrue CN114537705B (en) | 2022-08-12 |
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| CN202210436685.9AActiveCN114537705B (en) | 2022-04-25 | 2022-04-25 | Airplane flaring conduit assembly method and device with errors, storage medium and equipment |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114954997B (en)* | 2022-07-14 | 2022-12-13 | 成都飞机工业（集团）有限责任公司 | Method, device, equipment and medium for controlling assembly step of cabin door |
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| CN114537705A (en) | 2022-05-27 |
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