Aircraft release emergency processing method and device, storage medium and equipment

Abstract

The invention discloses an aircraft release emergency processing method and device, a storage medium and equipment. A to-be-tested aircraft is determined based on first tipping decision information and a tipping bearable coefficient; determining second tipping decision information of the aircraft to be subjected to flight test based on the real crop material list of the aircraft, and binding the second tipping decision information and the first tipping decision information to obtain third tipping decision information; based on the third connection decision information and the test flight requirement, generating test flight approval process information of the to-be-tested flight aircraft; according to the method, whether the airplane is received or not is judged by utilizing the connection bearable coefficient, so that the connection efficiency is improved; based on the received airplane, the airplane emergency release application and the examination and approval result of the airplane emergency release application are determined, rapid processing and efficient cooperation of the airplane release application are achieved, and the technical problems that the airplane connection and installation inspection efficiency is low, and the release application examination and verification process is complex and long in period are solved.

Description

Technical Field

[0001] This application relates to the technical field of aircraft flight test management and control, and particularly relates to an aircraft release emergency handling method, device, storage medium, and equipment. Background Art

[0002] After the aircraft successfully passes the assembly and integration tests and the ground station tests, the flight test execution unit initiates an aircraft release application, and the flight test can only be carried out after obtaining the consent of departments such as process, design, and quality. During the aircraft development and production process, due to the dispersion of the management departments of aircraft testing, process, design, and quality, traditional aircraft release applications mainly use paper documents and are processed through manual filling and in-person countersigning, resulting in high labor costs, high time costs, and low processing efficiency. Especially in cases of urgent tasks or document re-signing, the above methods have poor adaptability and immediacy. In the situation where the requirements for aircraft development cycle, quality, and cost are getting higher and higher, there is an urgent need to explore new methods for aircraft release application emergency handling in combination with the needs of aircraft release operations by using information technology facilities. Summary of the Invention

[0003] The main purpose of this application is to provide an aircraft release emergency handling method, device, storage medium, and equipment, aiming to solve the technical problems of low efficiency of aircraft installation inspection and complex and long-cycle review process of release applications.

[0004] To achieve the above object, this application provides an aircraft release emergency handling method, including: determining installation concern information based on configuration items of a pre-constructed whole-aircraft integration material decomposition clue model for installation, where the installation concern information includes first installation decision information and installation tolerance coefficient; determining the aircraft to be flight-tested based on the first installation decision information and the installation tolerance coefficient; obtaining the actual aircraft material list during the manufacturing process of the aircraft to be flight-tested, and determining the second installation decision information of the aircraft to be flight-tested based on the actual aircraft material list, binding the second installation decision information with the first installation decision information to obtain the third installation decision information; generating flight test approval process information for the aircraft to be flight-tested based on the third installation decision information and flight test requirements; obtaining the approval result of the aircraft to be flight-tested based on the flight test approval process information, and sending the approval result of the aircraft to be flight-tested to the flight test applicant.

[0005] Optionally, the configuration items of the aircraft to be installed include a first-level decomposition system to a third-level decomposition system. Among them, the first-level decomposition system is the logical subsystem of the aircraft to be installed, the second-level decomposition system is the physical system included in each logical subsystem, and the third-level decomposition system is the physical components included in each physical system. Determining the aircraft to be test-flown based on the first installation decision information and the installation tolerance coefficient includes: comprehensively evaluating the first installation decision information of the third-level decomposition system to obtain a first quantization value, where the categories of the first installation decision information include: items of concern in installation inspection, prominent problems existing in installation inspection, reasons for problems, and solutions to problems; determining a second quantization value of the second-level decomposition system based on the average value of the first quantization value; determining a third quantization value of the first-level decomposition system based on the average value of the second quantization value; determining the installation tolerance coefficient of the aircraft to be installed based on the average value of the third quantization value; and determining the test-flown aircraft based on the installation tolerance coefficient.

[0006] Optionally, generating the test-flight approval process information of the aircraft to be test-flown based on the third installation decision information and test-flight requirements includes: obtaining the test-flight requirements, creating a test-flight task for the test-flown aircraft based on the test-flight requirements, where the test-flight requirements include: test-flight type requirements, test-flight subject requirements; generating the test-flight approval process information based on the test-flight type requirements, the test-flight subject requirements, and the third installation decision information, and the approvers and approval process of the test-flight approval process information, where the approvers include: the responsible persons of the production management department, the process management department, the design department, the inspection management department, the project general manager, and the user representative.

[0007] Optionally, obtaining the approval result of the aircraft to be test-flown based on the test-flight approval process information includes: generating a release application form for the aircraft to be test-flown based on the test-flight task and the test-flight application test-flight approval process information, and the content of the release application form includes the third installation decision information; sending the release application form to each approver; receiving the approved release application form and sending the approved release application form to the applicant.

[0008] Optionally, obtaining the approval result of the aircraft to be test-flown based on the test-flight approval process information further includes: generating a first test-flight status based on the test-flight task; generating a second test-flight status based on the submitted release application form; generating a third test-flight status based on the approved release application form; generating a fourth test-flight status based on the release application form agreed by all approvers.

[0009] To achieve the above object, the present application further provides an aircraft release emergency processing device, which is characterized by including: an information acquisition module, configured to determine the installation concern information based on the configuration items of the pre-constructed whole-machine integrated material decomposition clue model for installation, where the installation concern information includes the first installation decision information and the installation tolerance coefficient; a flight test determination module, configured to determine the aircraft to be flight-tested based on the first installation decision information and the installation tolerance coefficient; a binding module, configured to obtain the actual aircraft material list during the manufacturing process of the aircraft to be flight-tested, and determine the second installation decision information of the aircraft to be flight-tested based on the actual aircraft material list, and bind the second installation decision information with the first installation decision information to obtain the third installation decision information; a process generation module, configured to generate the flight test approval process information of the aircraft to be flight-tested based on the third installation decision information and the flight test requirements; obtain the approval result of the aircraft to be flight-tested based on the flight test approval process information, and send the approval result of the aircraft to be flight-tested to the flight test applicant.

[0010] Optionally, the aircraft release emergency processing device further includes: a factory-institute collaboration module, configured to receive and parse the release application form, and the factory-institute collaboration module adopts a message format and content described in extensible markup language, and the factory-institute collaboration module includes a data packet layer, a file layer, and a data item layer.

[0011] Optionally, the factory-institute collaboration module includes a data packet layer, a file layer, and a data item layer, and each layer uses extensible markup language to describe the message format and content.

[0012] To achieve the above object, the present application further provides a computer-readable storage medium, which includes instructions that, when running on a computer, cause the computer to execute the aircraft release emergency processing method in any of the above embodiments.

[0013] To achieve the above object, the present application further provides an aircraft release emergency processing device, where the aircraft release emergency processing device includes: at least one processor, a memory, and an input / output unit; wherein, the memory is used to store a computer program, and the processor is used to call the computer program stored in the memory to execute the aircraft release emergency processing method in any of the above embodiments.

[0014] An aircraft release emergency handling method, device, storage medium, and equipment proposed in an embodiment of the present application determine the installation concern information through configuration items based on a pre-constructed whole-machine integrated material decomposition clue model for installation, where the installation concern information includes first installation decision information and an installation tolerance coefficient; determine the aircraft to be test-flown based on the first installation decision information and the installation tolerance coefficient; obtain the actual aircraft material list during the manufacturing process of the aircraft to be test-flown, and determine the second installation decision information of the aircraft to be test-flown based on the actual aircraft material list, and bind the second installation decision information with the first installation decision information to obtain the third installation decision information; generate the test flight approval process information of the aircraft to be test-flown based on the third installation decision information and the test flight requirements; obtain the approval result of the aircraft to be test-flown based on the test flight approval process information, and send the approval result of the aircraft to be test-flown to the test flight applicant. The present application uses the installation tolerance coefficient to judge whether to receive the aircraft, thereby improving the installation efficiency; determining the aircraft emergency release application and the approval result of the aircraft emergency release application based on the received aircraft, realizing the rapid processing and efficient collaboration of the aircraft release application, and solving the technical problems of low efficiency of aircraft installation inspection and complex and long cycle in the review process of the release application. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic structural diagram of a computer device for the hardware operating environment involved in an embodiment of the present application;

[0016] Figure 2 It is a flowchart of the aircraft release emergency handling method provided in an embodiment of the present application;

[0017] Figure 3 It is a schematic block diagram of the aircraft release emergency handling device provided in an embodiment of the present application;

[0018] Figure 4 It is a schematic block diagram of the installation module provided in an embodiment of the present application;

[0019] Figure 5 It is a schematic diagram of the storage medium provided in an embodiment of the present application;

[0020] Figure 6 It is a schematic structural diagram of the equipment provided in an embodiment of the present application.

[0021] The realization, functional features, and advantages of the purpose of the present application will be further described with reference to the embodiments and the accompanying drawings. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0022] It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0023] In the prior art, aircraft development units mainly build information systems around the manufacturing and assembly processes of aircraft components to support the control of the aircraft manufacturing process and improve the efficiency of aircraft development. Aircraft flight test, as a key task that must be carried out before the aircraft completes ground tests and is delivered to users, its execution efficiency is crucial for the efficiency of aircraft development. Since aircraft design institutes and assembly plants are usually different units, and the aircraft manufacturing process involves cooperation between different professional branch plants and production management departments, it leads to low efficiency in aircraft acceptance inspection and a complex and long cycle in the review process of flight release applications. The traditional method of manual document review and signature can no longer meet the development requirements of high quality, low cost, and short cycle in aircraft development.

[0024] This application provides an aircraft flight release emergency handling method. By constructing a Bill of Materials as Delivered (DBOM) for the whole aircraft integrated with material decomposition clues for acceptance and defining the configuration items of the DBOM, it uses the acceptance tolerance coefficient of the whole aircraft to determine whether the aircraft can be accepted, improving the acceptance efficiency; based on the Bill of Materials as Built of the aircraft, it clarifies the remaining work of the aircraft; constructs an aircraft integrated flight test task for multi-business collaboration; generates a flight release application form for the aircraft integrated flight test task for multi-business collaboration through the aircraft model / batch number to integrate the aircraft integrated flight test task for multi-business collaboration and the DBOM; and approves and automatically distributes according to the integrated flight test type, integrated flight test subjects, and remaining work of aircraft acceptance in the flight release application form for the aircraft integrated flight test task for multi-business collaboration, realizing the rapid processing of aircraft flight release applications and enhancing the collaborative efficiency among aircraft flight release application approvers.

[0025] Refer to Figure 1 , Figure 1 which is a schematic diagram of the computer device structure for the hardware operating environment involved in the embodiments of this application.

[0026] As Figure 1As shown in the figure, the computer device may include: a processor 1001, such as a Central Processing Unit (CPU), a communication bus 1002, a user interface 1003, a network interface 1004, and a memory 1005. Among them, the communication bus 1002 is used to realize the connection and communication between these components. The user interface 1003 may include a display screen and an input unit such as a keyboard. Optionally, the user interface 1003 may further include a standard wired interface and a wireless interface. The network interface 1004 may optionally include a standard wired interface and a wireless interface (such as a Wireless-Fidelity (WI-FI) interface). The memory 1005 may be a high-speed Random Access Memory (RAMD) or a stable non-volatile memory (Non-Volatile Memory, NVM), such as a disk memory. Optionally, the memory 1005 may also be a storage device independent of the aforementioned processor 1001.

[0027] Those skilled in the art can understand that Figure 1 the structure shown in the figure does not constitute a limitation on the computer device, and it may include more or fewer components than shown in the figure, or combine some components, or have a different component layout.

[0028] As Figure 1 shown, the memory 1005, as a storage medium, may include an operating system, a data storage module, a network communication module, a user interface module, and an electronic program.

[0029] In Figure 1 the computer device shown, the network interface 1004 is mainly used for data communication with a network server; the user interface 1003 is mainly used for data interaction with a user; the processor 1001 and the memory 1005 in the computer device of the present invention may be disposed in the computer device, and the computer device calls the aircraft release emergency processing device stored in the memory 1005 through the processor 1001 and executes the aircraft release emergency processing method provided in the embodiment of the present application. Figure 2 This is a flowchart of the aircraft release emergency processing method provided in the embodiment of the present application. This method can be executed by the processor 1001. Referring to Figure 2 , the aircraft release emergency processing method includes:

[0030] S10. Determine the installation concern information based on the configuration items of the pre-built whole-machine integration material decomposition clue model for installation, where the installation concern information includes the first installation decision information and the installation tolerance coefficient;

[0031] Specifically, the whole-aircraft disassembly model can be an integrated material disassembly clue model for aircraft receiving, and configuration items of the whole aircraft to be received are obtained according to the integrated material disassembly clue model for aircraft receiving. Here, the configuration items are a collective term for the first-level disassembly system, the second-level disassembly system, and the third-level disassembly system of the whole aircraft to be received. The pre-set receiving concern information is obtained based on the configuration items of the integrated material disassembly clue model for aircraft receiving. The receiving concern information can specifically include: delivery unit, delivery responsible person, delivery time, manufacturing unit, installation time, receiving inspection concern items, prominent problems, causes and solutions, receiving tolerance coefficient, receiving unit, receiving responsible person, receiving time, etc. The first receiving decision information is generated according to the receiving concern information. Specifically, the processor 1001 generates the first receiving decision information of the aircraft to be received according to the receiving concern information, prominent problems, causes and solutions. The purpose of generating the first receiving decision information is to track the clearance result of the remaining work by using the first receiving decision information. The first receiving decision information is a necessary information basis for the aircraft research and development unit, the assembly unit, the receiving unit, and the flight test unit to make correct decisions.

[0032] In the embodiment of the present application, the configuration items of the integrated material disassembly clue model for aircraft receiving include the first-level disassembly system to the third-level disassembly system. Among them, the first-level disassembly system is the logical subsystem of the whole aircraft to be received, the second-level disassembly system is the physical system included in each logical subsystem, and the third-level disassembly system is the physical components included in each physical system. Step S10 can specifically include the following execution steps:

[0033] S11. Comprehensively evaluate the first receiving decision information of the third-level disassembly system to obtain a first quantization value. Here, the first receiving decision information categories include: receiving inspection concern items, prominent problems existing in the receiving inspection, causes of the problems, and solutions to the problems;

[0034] S12. Determine a second quantization value of the second-level disassembly system based on the average value of the first quantization value;

[0035] S13. Determine a third quantization value of the first-level disassembly system based on the average value of the second quantization value;

[0036] S14. Determine the receiving tolerance coefficient of the whole aircraft to be received based on the average value of the third quantization value;

[0037] S15. Determine the flight test aircraft based on the receiving tolerance coefficient.

[0038] Specifically, the top-level complete aircraft to be installed is the root node of the complete aircraft integrated material decomposition clue model for installation, including one or more first-level decomposition systems. The first-level decomposition system is a logical system defined based on the top-level complete aircraft and oriented to the inspection requirements for aircraft installation, and includes one or more second-level decomposition systems; the second-level decomposition system is an actual aircraft physical system divided according to the physical composition based on the first-level decomposition system, and includes one or more third-level decomposition components; the third-level decomposition component is the actual physical component that makes up the second-level decomposition system and is the leaf node of the complete aircraft integrated material decomposition clue model for installation. The top-level complete aircraft can be represented by the aircraft model / batch number code.

[0039] The installation tolerance coefficient of the third-level decomposition component is a quantified value obtained by comprehensively evaluating the prominent problems, causes of the problems, and solutions in the installation inspection of the third-level decomposition component. The installation tolerance coefficient of the second-level decomposition system is equal to the average value of the installation tolerance coefficients of the third-level decomposition components. The installation tolerance coefficient of the first-level decomposition system is equal to the average value of the installation tolerance coefficients of the second-level decomposition systems. The installation tolerance coefficient of the top-level complete aircraft is equal to the average value of the installation tolerance coefficients of the first-level decomposition systems.

[0040] It should be noted that the installation inspection concern items of the top-level complete aircraft include whether the aircraft appearance, cover sealing, etc. meet the requirements. The aircraft appearance includes situations such as paint loss and bumps on the complete aircraft. The cover sealing includes the sealing date, first overhaul period, validity period, and implementing personnel, etc. Whether the installation inspection concern items meet the requirements is the basis for evaluating whether the functions, performance, safety, fault tolerance, etc. of the aircraft to be installed can meet the requirements.

[0041] S20. Determine the aircraft to be test-flown based on the first installation decision information and the installation tolerance coefficient

[0042] Exemplarily, {-M, 0.6, 1} indicates that the configuration item of the complete aircraft integrated material decomposition clue model for installation does not meet the aircraft installation conditions, where M is a real number much larger than the total number of leaf nodes of the configuration item of the complete aircraft integrated material decomposition clue model for installation; 0.6 indicates that the configuration item of the complete aircraft integrated material decomposition clue model for installation partially meets the installation conditions; 1 indicates that the configuration item of the complete aircraft integrated material decomposition clue model for installation safely meets the installation conditions.

[0043] S30. Obtain the actual aircraft material list during the manufacturing process of the aircraft to be test-flown, and determine the second installation decision information of the aircraft to be test-flown based on the actual aircraft material list, and bind the second installation decision information with the first installation decision information to obtain the third installation decision information;

[0044] In the embodiment of the present application, step S30 may include the following specific implementation steps:

[0045] S31. Obtain the actual aircraft material list during the manufacturing process of the aircraft to be test-flown;

[0046] Among them, the actual aircraft material list is the carrier for collecting physical data during the aircraft manufacturing process and is used for data organization and management of the product breakdown structure for aircraft manufacturing. The actual aircraft material list includes the outstanding AO (Assembly Outline) of the aircraft, out-of-tolerance sheets, deviation sheets, non-conformance sheets, etc. Among them, AO is the aircraft assembly outline, which is used to guide the execution of aircraft assembly operations.

[0047] S32. Determine the second aircraft installation decision information of the aircraft to be test-flown based on the actual aircraft material list;

[0048] Specifically, the processor generates the second aircraft installation decision information based on the actual aircraft material list by comprehensively considering the outstanding AO, out-of-tolerance sheets, deviation sheets, and non-conformance sheets of the aircraft. That is to say, the second aircraft installation decision information includes outstanding AO information and quality document information. Among them, quality documents are the general term for documents such as out-of-tolerance sheets, deviation sheets, and non-conformance sheets.

[0049] S33. Bind the second aircraft installation decision information with the first aircraft installation decision information to obtain the third aircraft installation decision information.

[0050] Specifically, before the test flight after the installation of the test flight aircraft, the processor 1001 binds the second aircraft installation decision information with the first aircraft installation decision information, and forms a list of the third aircraft installation decision information as a basis for subsequent emergency decision-making.

[0051] S40. Generate the test flight approval process information of the aircraft to be test-flown based on the third aircraft installation decision information and the test flight requirements;

[0052] In the embodiment of the present application, step S40 may include the following execution process:

[0053] S41. Obtain the test flight requirements, and create a test flight task for the test flight aircraft based on the test flight requirements. Among them, the test flight requirements include: test flight type requirements, test flight subject requirements,

[0054] It should be noted that the test flight requirements may specifically include aircraft model / batch requirements, pilot requirements, support team requirements, landing number requirements, and requirements for test flight meteorology, airspace, and airport.

[0055] S42. Generate the test flight approval process information based on the test flight type requirements, the test flight subject requirements, and the third aircraft installation decision information. The test flight approval process information includes approvers and approval processes. Among them, the approvers may include: the person in charge of the production management department, the person in charge of the process management department, the person in charge of the design department, the person in charge of the inspection management department, the project general manager, and the user representative.

[0056] Specifically, according to different combinations of flight test requirements and third acceptance decision information, the processor 1001 can generate different flight test application handling processes, and different flight test application handling processes correspond to different approvers and their approval sequences. The flight test application handling process automatically generated by the processor, along with its approvers and approval sequences, improves work efficiency, greatly facilitates the approval process, and avoids errors and omissions.

[0057] S50. Obtain the approval result of the aircraft to be flight-tested based on the flight test approval process information, and send the approval result of the aircraft to be flight-tested to the flight test applicant.

[0058] In the embodiment of the present application, the specific execution process of step S50 may include:

[0059] S51. Generate a takeoff application form for the aircraft to be flight-tested based on the flight test task and flight test application flight test approval process information. The content of the takeoff application form includes the third acceptance decision information.

[0060] It should be noted that the content of the takeoff application form may also include: aircraft model / batch number, flight test type, flight test subject, application form number, applicant, and application date.

[0061] Specifically, the processor 1001 can specifically generate a takeoff application form for the aircraft to be flight-tested based on the combination of the aircraft model / batch number of the flight test aircraft, the flight test task, and the flight test application flight test approval process information. This takeoff application form can be specifically generated according to needs and objective circumstances, greatly facilitating the user. The processor 1001 improves work efficiency, saves time, and meets the requirements of emergency use.

[0062] S52. Receive the approved takeoff application form and send the approved takeoff application form to the applicant.

[0063] Specifically, the processor 1001 can sequentially and automatically send the takeoff application form to each approver according to the approvers and approval sequence in the flight test approval process information. After the reviewer completes the approval process, the approved takeoff application form is received. This process can achieve the high efficiency and convenience of the approval process and avoid omissions in the approval process. The approver can be the flight test pilot, the flight test support team, and other units and individuals related to takeoff. The processor 1001 can automatically distribute the takeoff application form according to the flight test approval process information.

[0064] It should be noted that this takeoff application form can be used for emergency takeoff or for ordinary takeoff requirements, and its application scenario is not restricted here.

[0065] Continuing from the previous embodiment, the implementation process of step S50 may further include the following steps:

[0066] S53. Generate the first test flight state based on the test flight mission.

[0067] S54. Generate the second test flight state based on the submitted flight release application form.

[0068] S55. Generate the third test flight state based on the approved flight release application form.

[0069] S56. Generate the fourth test flight state based on the flight release application form approved by all approvers.

[0070] Specifically, the first test flight state can be the new test flight mission state, the second test flight state can be the flight release application state of the test flight mission, the third test flight state can be the flight release approval state of the test flight mission, and the fourth test flight state can be the distribution state of the test flight mission.

[0071] By executing step S61 - step S64, the processor 1001 can track the status of the aircraft test flight mission. The purpose of the processor 1001 to track these statuses is to enable the user to clearly understand the task node status of the current test flight mission, so as to better make service emergency decisions according to the node status.

[0072] Exemplarily, the process of the test flight mission status change is as follows:

[0073] T101: The test flight mission status is "initial state".

[0074] T102: After the processor 1001 completes the construction of the test flight mission, the test flight mission status becomes "new test flight mission".

[0075] T103: After the processor 1001 completes the generation and submission of the flight release application form for the test flight mission, the test flight mission status becomes "flight release application of the test flight mission".

[0076] T104: After the processor 1001 approves the flight release application form for the test flight mission, the test flight mission status becomes "flight release approval of the test flight mission".

[0077] T105: After the processor 1001 completes the approval of the flight release application form for the test flight mission and all approvers agree, the test flight mission status becomes "distribution of the test flight mission".

[0078] In the embodiment of the present application, after step S10, the aircraft flight release emergency handling method may further include the following execution process:

[0079] S61. Generate the fifth test flight state based on the acceptance tolerance coefficient.

[0080] It should be noted that the processor 1001 of the processor 100 can also track the state transition process of the aircraft during the test flight. The aircraft states include aircraft installation, aircraft takeoff application, aircraft takeoff approval, aircraft takeoff preparation, etc.

[0081] Exemplarily, T201: The aircraft state is "initial state";

[0082] T202: After the processor 1001 completes the calculation of the installation tolerance coefficient of the top-level whole machine, the aircraft state becomes "aircraft installation";

[0083] T203: After the processor 1001 completes the generation and submission of the test flight mission takeoff application form, the aircraft state becomes "aircraft takeoff application";

[0084] T204: After the processor 1001 approves the test flight mission takeoff application form, the aircraft state becomes "aircraft takeoff approval";

[0085] T205: After the processor 1001 approves the test flight mission takeoff application form and all approvers agree, the aircraft state becomes "aircraft takeoff preparation".

[0086] In summary, in the embodiment of the present application, an aircraft takeoff emergency handling method is proposed. By determining the installation concern information through the configuration items of the pre-constructed whole machine integrated material decomposition clue model for installation, where the installation concern information includes the first installation decision information and the installation tolerance coefficient; determining the aircraft to be test flown based on the first installation decision information and the installation tolerance coefficient; obtaining the actual aircraft material list during the manufacturing process of the aircraft to be test flown, and determining the second installation decision information of the aircraft to be test flown based on the actual aircraft material list, binding the second installation decision information with the first installation decision information to obtain the third installation decision information; generating the test flight approval process information of the aircraft to be test flown based on the third installation decision information and the test flight requirements; obtaining the approval result of the aircraft to be test flown based on the test flight approval process information, and sending the approval result of the aircraft to be test flown to the test flight applicant. The present application uses the installation tolerance coefficient to judge whether to receive the aircraft, thereby improving the installation efficiency; determining the aircraft emergency takeoff application and the approval result of the aircraft emergency takeoff application based on the received aircraft, realizing the rapid processing and efficient collaboration of the aircraft takeoff application, and solving the technical problems of low efficiency of aircraft installation inspection and complex and long-cycle review process of takeoff application.

[0087] Based on the above embodiment, the present application also provides an aircraft takeoff emergency handling device for solving the technical problems of low efficiency of aircraft installation inspection and complex and long-cycle review process of takeoff application. Figure 3 This is the structural block diagram of the aircraft takeoff emergency handling device provided by the embodiment of the present application. Refer to Figure 3, the aircraft release emergency handling device 200 may include an information acquisition module 201, a flight test determination module 202, a binding module 203, a process generation module 204, and an output module 205. Among them, the information acquisition module 201 may be configured to determine the installation concern information based on the configuration items of the pre-built whole-aircraft integrated material decomposition clue model for installation. The installation concern information includes the first installation decision information and the installation tolerance coefficient. The flight test determination module 202 may be configured to determine the aircraft to be flight-tested based on the first installation decision information and the installation tolerance coefficient. The binding module 203 may be configured to obtain the actual aircraft material list during the manufacturing process of the aircraft to be flight-tested, and determine the second installation decision information of the aircraft to be flight-tested based on the actual aircraft material list, bind the second installation decision information with the first installation decision information to obtain the third installation decision information. The process generation module 204 may be configured to generate the flight test approval process information of the aircraft to be flight-tested based on the third installation decision information and the flight test requirements. The output module 205 may be configured to obtain the approval result of the aircraft to be flight-tested based on the flight test approval process information and send the approval result of the aircraft to be flight-tested to the flight test applicant.

[0088] Figure 4 This is the structural block diagram of the installation module provided by the embodiment of the present application. Refer to Figure 4 , in the embodiment of the present application, the configuration items include the first-level decomposition system to the third-level decomposition system. Among them, the first-level decomposition system is the logical subsystem of the whole aircraft to be installed, the second-level decomposition system is the physical system included in each logical subsystem, and the third-level decomposition system is the physical components included in each physical system. The information acquisition module 201 may include a first quantization subunit 2011, a second quantization subunit 2012, a third quantization subunit 2013, a coefficient generation unit 2014, and a determination unit 2015. Among them, the first quantization subunit 2011 may be configured to comprehensively evaluate the first installation decision information of the third-level decomposition system to obtain a first quantization value. The first installation decision information categories include: installation inspection concern items, outstanding problems existing in the installation inspection, reasons for the problems, and solutions to the problems. The second quantization subunit 2012 may be configured to determine the second quantization value of the second-level decomposition system based on the average value of the first quantization value. The third quantization subunit 2013 may be configured to determine the third quantization value of the first-level decomposition system based on the average value of the second quantization value. The coefficient generation unit 2014 may be configured to determine the installation tolerance coefficient of the whole aircraft to be installed based on the average value of the third quantization value. The determination unit 2015 may be configured to determine the flight test aircraft based on the installation tolerance coefficient.

[0089] Determine the flight test aircraft based on the installation tolerance coefficient.

[0090] In an embodiment of the present application, the process generation module 204 may be used to obtain flight test requirements, create a flight test task for the flight test aircraft based on the flight test requirements, where the flight test requirements include: flight test type requirements and flight test subject requirements; generate the flight test approval process information based on the flight test type requirements, the flight test subject requirements, and the third acceptance decision information, and the flight test approval process information includes the approvers and the approval process, where the approvers include: the person in charge of the production management department, the person in charge of the process management department, the person in charge of the design department, the person in charge of the inspection management department, the project general manager, and the user representative.

[0091] In an embodiment of the present application, the output module 205 may be used to generate a take-off application form for the aircraft to be flight tested based on the flight test task and the flight test application flight test approval process information, and the content of the take-off application form includes the third acceptance decision information; send the take-off application form to each of the approvers; receive the approved take-off application form and send the approved take-off application form to the applicant.

[0092] In an embodiment of the present application, the output module 205 may be used to generate a first flight test status based on the flight test task; generate a second flight test status based on the submitted take-off application form; generate a third flight test status based on the approved take-off application form; generate a fourth flight test status based on the take-off application form agreed by all approvers.

[0093] In an embodiment of the present application, the aircraft take-off emergency handling device 200 may further include a factory-institute collaboration module 206, and the factory-institute collaboration module 206 may be used to receive and parse the take-off application form. The factory-institute collaboration module uses a message format and content described in Extensible Markup Language, and the factory-institute collaboration module includes a data packet layer, a file layer, and a data item layer.

[0094] In an embodiment of the present application, the factory-institute collaboration module 206 may include a data packet layer, a file layer, and a data item layer, and each layer uses Extensible Markup Language to describe the message format and content.

[0095] Based on the above embodiments, an embodiment of the present application further provides a computer-readable storage medium, refer to Figure 5, which shows that the computer-readable storage medium is an optical disc 50, on which a computer algorithm, i.e., an algorithm product, is stored. When the computer algorithm runs on a microprocessor, it will implement the steps described in the above method embodiments. For example, based on the configuration items of the pre-constructed whole-machine integrated material decomposition clue model for the butt joint, the butt joint concern information is determined, where the butt joint concern information includes the first butt joint decision information and the butt joint tolerance coefficient; based on the first butt joint decision information and the butt joint tolerance coefficient, the aircraft to be flight-tested is determined; the actual aircraft material list during the manufacturing process of the aircraft to be flight-tested is obtained, and based on the actual aircraft material list, the second butt joint decision information of the aircraft to be flight-tested is determined, and the second butt joint decision information is bound to the first butt joint decision information to obtain the third butt joint decision information; based on the third butt joint decision information and the flight test requirements, the flight test approval process information of the aircraft to be flight-tested is generated; based on the flight test approval process information, the approval result of the aircraft to be flight-tested is obtained, and the approval result of the aircraft to be flight-tested is sent to the flight test applicant. The specific implementation manners of each step will not be repeated here.

[0096] It should be noted that examples of computer-readable storage media may also 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 optical and magnetic storage media, which will not be elaborated one by one here.

[0097] In addition, on the basis of the above embodiments, the embodiments of the present application further provide a software generation device. Figure 6 The block diagram of an exemplary software generation device 60 suitable for implementing the embodiments of the present application is shown. The software generation device 60 may be a computer system or a server. Figure 6 The software generation device 60 shown is merely an example and should not impose any limitations on the functions and usage scope of the embodiments of the present application.

[0098] Refer to Figure 6 , the components of the software generation device 60 may include, but are not limited to: one or more processors or processing units 601, a system memory 602, and a bus 603 connecting different system components (including the system memory 602 and the processing unit 601).

[0099] The software generation device 60 typically includes a variety of computer system-readable media. These media can be any available media accessible by the software generation device 60, including volatile and non-volatile media, removable and non-removable media.

[0100] System memory 602 may include computer system readable media in the form of volatile memory, such as random access memory (RAM) 6021 and / or cache memory 6022. The software generation device 60 may further include other removable / non-removable, volatile / non-volatile computer system storage media. By way of example only, ROM 6023 may be used to read and write to non-removable, non-volatile magnetic media ( Figure 6 not shown in the figure, commonly referred to as a "hard disk drive"). Although not shown in Figure 6 the figure, a disk drive for reading and writing to a removable non-volatile disk (such as a "floppy disk") and an optical disk drive for reading and writing to a removable non-volatile optical disk (such as a CD-ROM, DVD-ROM or other optical media) may be provided. In these cases, each drive may be connected to the bus 603 that connects different system components through one or more data media interfaces. The system memory 602 may include at least one algorithm product, which has a set (such as at least one) of algorithm modules configured to perform the functions of the embodiments of the present application.

[0101] An algorithm / utility 6025 having a set (at least one) of algorithm modules 6024 may be stored in, for example, the system memory 602, and such algorithm modules 6024 include but are not limited to: an operating system, one or more application algorithms, other algorithm modules, and algorithm data, and the implementation of a network environment may be included in each or some combination of these examples. The algorithm modules 6024 generally perform the functions and / or methods in the embodiments described in the present application.

[0102] The software generation device 60 may also communicate with one or more external devices 604 (such as a keyboard, a pointing device, a display, etc.). Such communication may be carried out through an input / output (I / O) interface 605. Moreover, the software generation device 60 may also communicate with one or more networks (such as a local area network (LAN), a wide area network (WAN) and / or a public network, such as the Internet) through a network adapter 606. As Figure 6 shown, the network adapter 606 communicates with other modules (such as the processing unit 601, etc.) of the software generation device 60 through the bus 603 that connects different system components. It should be understood that although Figure 6 not shown in the figure, other hardware and / or software program modules may be used in combination with the software generation device 60.

[0103] The processing unit 601 executes various functional applications and data processing by running algorithms stored in the system memory 602. For example, based on the configuration items of the pre-built whole-machine integrated material decomposition clue model for butt joint installation, the butt joint concern information is determined, where the butt joint concern information includes the first butt joint decision information and the butt joint affordability coefficient; based on the first butt joint decision information and the butt joint affordability coefficient, the aircraft to be flight-tested is determined; the actual aircraft material list during the manufacturing process of the aircraft to be flight-tested is obtained, and based on the actual aircraft material list, the second butt joint decision information of the aircraft to be flight-tested is determined, and the second butt joint decision information is bound to the first butt joint decision information to obtain the third butt joint decision information; based on the third butt joint decision information and the flight test requirements, the flight test approval process information of the aircraft to be flight-tested is generated; based on the flight test approval process information, the approval result of the aircraft to be flight-tested is obtained, and the approval result of the aircraft to be flight-tested is sent to the flight test applicant. The specific implementation methods of each step will not be repeated here. It should be noted that although several units / modules or sub-units / sub-modules of the device are mentioned in the above detailed description, this division is only exemplary and not mandatory. In fact, according to the embodiments of the present application, the features and functions of the two or more units / modules described above can be embodied in one unit / module. Conversely, the features and functions of one unit / module described above can be further divided and embodied by multiple units / modules.

[0104] In the description of the present application, it should be noted that the terms "first", "second", and "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0105] Those skilled in the art can clearly understand that for the convenience and brevity of description, the specific working processes of the systems, devices, and units described above can refer to the corresponding processes in the foregoing method embodiments and will not be elaborated here.

[0106] In several embodiments provided in the present application, it should be understood that the disclosed systems, devices, and methods can be implemented in other ways. The device embodiments described above are only illustrative. For example, the division of units is only a logical function division, and there can be other division methods in actual implementation. For another example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the displayed or discussed mutual coupling or direct coupling or communication connection can be through some communication interfaces, and the indirect coupling or communication connection of the devices or units can be in an electrical, mechanical, or other form.

[0107] The unit described as a separation component may or may not be physically separated. The component shown as a unit may or may not be a physical unit, that is, it may be located in one place or distributed across multiple network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0108] In addition, each functional unit in various embodiments of the present application can be integrated into one processing unit, or each unit can exist physically alone, or two or more units can be integrated into one unit.

[0109] If the function is implemented in the form of a software program functional unit and sold or used as an independent product, it can be stored in a non-volatile computer-readable storage medium executable by a processor. Based on this understanding, the technical solution of the present application, in essence, or the part that contributes to the prior art, or a part of this technical solution, can be embodied in the form of a software program product. This computer software program product is stored in a storage medium and includes several instructions for causing a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods in various embodiments of the present application. The aforementioned storage medium includes: USB flash drives, mobile hard disks, read-only memories (ROM, Read-Only Memory), random access memories (RAM, Random Access Memory), magnetic disks, or optical discs, and other media that can store algorithm codes.

[0110] Finally, it should be noted that: the above-described embodiments are only specific implementation manners of the present application, used to illustrate the technical solutions of the present application, rather than limiting it. The protection scope of the present application is not limited thereto. Although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: any person skilled in the art within the technical scope disclosed by the present application can still modify the technical solutions described in the foregoing embodiments, or can easily think of changes, or perform equivalent replacements on some of the technical features; and these modifications, changes, or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should all be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

[0111] In addition, although the operations of the method of the present application are described in a specific order in the drawings, this does not require or imply that these operations must be performed in this specific order, or that all the shown operations must be performed to achieve the desired result. Additionally or alternatively, some steps can be omitted, multiple steps can be combined into one step for execution, and / or one step can be decomposed into multiple steps for execution.

[0112] The above are only the preferred embodiments of the present application, and do not limit the patent scope of the present application accordingly. Any equivalent structure or equivalent process transformation made by using the content of the specification and drawings of the present application, or directly or indirectly applied in other related technical fields, shall be similarly included in the patent protection scope of the present application.

Claims

1. An emergency handling method for aircraft takeoff, characterized in that Including: Determining the make-up concern information of the configuration items based on the pre-built whole-aircraft integrated material decomposition clue model for make-up, where the make-up concern information includes the first make-up decision information and the make-up affordability coefficient; Determining the aircraft to be test-flown based on the first make-up decision information and the make-up affordability coefficient; Obtaining the actual aircraft material list during the manufacturing process of the aircraft to be test-flown, and determining the second make-up decision information of the aircraft to be test-flown based on the actual aircraft material list, binding the second make-up decision information with the first make-up decision information to obtain the third make-up decision information; Generating the test-flight approval process information of the aircraft to be test-flown based on the third make-up decision information and the preset test-flight requirements; Obtaining the approval result of the aircraft to be test-flown based on the test-flight approval process information, and sending the approval result of the aircraft to be test-flown to the test-flight applicant.

2. The aircraft release emergency handling method according to claim 1, characterized in that, The configuration items of the whole-aircraft integrated material decomposition clue model for make-up include the first-level decomposition system to the third-level decomposition system. Among them, the first-level decomposition system is the logical subsystem of the aircraft to be made up as a whole, the second-level decomposition system is the physical system included in each logical subsystem, and the third-level decomposition system is the physical components included in each physical system. Determining the aircraft to be test-flown based on the first make-up decision information and the make-up affordability coefficient includes: Comprehensively evaluating the first make-up decision information of the third-level decomposition system to obtain a first quantitative value, where the categories of the first make-up decision information include: make-up inspection concern items, prominent problems existing in the make-up inspection, reasons for the problems, and solutions to the problems; Determining the second quantitative value of the second-level decomposition system based on the average value of the first quantitative value; Determining the third quantitative value of the first-level decomposition system based on the average value of the second quantitative value; Determining the make-up affordability coefficient of the whole aircraft to be made up based on the average value of the third quantitative value; Determining the test-flight aircraft based on the make-up affordability coefficient.

3. The aircraft release emergency handling method according to claim 2, characterized in that, Generating the test-flight approval process information of the aircraft to be test-flown based on the third make-up decision information and the preset test-flight requirements. The test-flight approval process information includes: Obtaining the preset test-flight requirements, and creating a test-flight task for the test-flight aircraft based on the test-flight requirements, where the test-flight requirements include: test-flight type requirements, test-flight subject requirements; Generating the test-flight approval process information based on the test-flight type requirements, the test-flight subject requirements, and the third make-up decision information. The test-flight approval process information includes the approvers and the approval process, where the approvers include: the person in charge of the production management department, the person in charge of the process management department, the person in charge of the design department, the person in charge of the inspection management department, the project general manager, and the user representative.

4. The aircraft release emergency handling method according to claim 3, wherein Obtaining the approval result of the aircraft to be test-flown based on the test-flight approval process information. The test-flight approval process information includes: Generating a take-off application form for the aircraft to be test-flown based on the test-flight task and the test-flight application test-flight approval process information. The content of the take-off application form includes the third make-up decision information; Sending the take-off application form to each of the approvers; Receive the approved flight release application form and send the approved flight release application form to the applicant.

5. The aircraft release emergency handling method according to claim 4, wherein The flight test approval process information for obtaining the approval result of the aircraft to be flight tested based on the flight test approval process information further includes: Generate a first flight test status based on the flight test mission; Generate a second flight test status based on the submitted flight release application form; Generate a third flight test status based on the approved flight release application form; Generate a fourth flight test status based on the flight release application form approved by all approvers.

6. An aircraft release emergency handling device, characterized in that, It includes: An information acquisition module for determining the installation concern information based on the configuration items of a pre-constructed integrated material decomposition clue model for aircraft installation, where the installation concern information includes first installation decision information and installation affordability coefficient; A flight test determination module for determining the aircraft to be flight tested based on the first installation decision information and the installation affordability coefficient; A binding module for obtaining the actual aircraft material list during the manufacturing process of the aircraft to be flight tested, and determining the second installation decision information of the aircraft to be flight tested based on the actual aircraft material list, binding the second installation decision information with the first installation decision information to obtain third installation decision information; A process generation module for generating the flight test approval process information of the aircraft to be flight tested based on the third installation decision information and the preset flight test requirements; An output module for obtaining the approval result of the aircraft to be flight tested based on the flight test approval process information and sending the approval result of the aircraft to be flight tested to the flight test applicant.

7. The aircraft release emergency handling device according to claim 6, characterized in that The aircraft flight release emergency handling device further includes: A factory and institute collaboration module for receiving and parsing the flight release application form, and the factory and institute collaboration module uses a message format and content described in extensible markup language.

8. The aircraft release emergency handling device according to claim 7, characterized in that, The factory and institute collaboration module includes a data packet layer, a file layer, and a data item layer, and each layer uses extensible markup language to describe the message format and content.

9. A computer-readable storage medium, characterized in that, It includes instructions that, when running on a computer, cause the computer to execute the aircraft flight release emergency handling method according to any one of claims 1 to 5.

10. An aircraft take-off emergency handling device, characterized in that, The aircraft flight release emergency handling device includes: At least one processor, a memory, and an input-output unit; Wherein, the memory is used to store a computer program, and the processor is used to call the computer program stored in the memory to execute the aircraft flight release emergency handling method according to any one of claims 1 to 5.

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