CN108985471B - Aircraft management system based on 3D lightweight model - Google Patents
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Abstract
The invention provides an aircraft management system based on a 3D lightweight model, which takes airworthiness files as standards, manages, records and analyzes the service information of an aircraft through an aviation information management subsystem, and integrates the information to evaluate the structural reliability of the aircraft; the 3D lightweight model of the aircraft is created through the three-dimensional management subsystem, the maintenance information is associated in the 3D lightweight model according to the position information, the aircraft management information is greatly simplified, and managers can read and interactively operate through a PC or a mobile terminal, so that the flexibility of airworthiness management of the aircraft and even a fleet is effectively improved. Through the processing, relevant managers and maintenance personnel can visually and conveniently acquire and share the change condition of the aircraft attribute information, and the aircraft structure reliability assessment is quantified and visualized, so that the visualization, the flow and the intelligent management of the aircraft structure business information are realized.
Description
Technical Field
The invention belongs to the technical field of airworthiness management of aircrafts, and particularly relates to an aircraft management system based on a 3D lightweight model.
Background
As the number of transport aircraft increases and the service life of the aircraft increases, the problems with aircraft during the design, manufacture, use and maintenance phases begin to become increasingly exposed. The problems of corrosion, fatigue, damage and aging of aircraft structures either manifest themselves or combine together, leading to a decline in the physical properties of the aircraft, a reduction in the load-bearing capacity and safety margins, and the safety issues become more and more pronounced.
The main countries and regions of the world civil aviation transportation industry have clear requirements for the continuous airworthiness and safety improvement of aircrafts (such as AC 120-84/23-13A/120-17A issued by FAA, etc.), and CCAR 121R5 issued by the China civil aviation administration has been effective in 2017 and 10 months. Taking the continuous airworthiness and safety improvement regulation of the J aircraft attached to the CCAR 121R5 in China as an example, 8 corresponding consultation notices (basically the same as FAA) are matched, the regulation and AC not only provide clear and strict requirements for the structure and the maintenance engineering management of the system of the aircraft, but also clear local parties need to forcibly check the operated aircraft by taking fourteen years as a threshold value and seven years as a cycle period besides daily supervision so as to ensure the practical implementation of the continuous airworthiness and safety management requirements of the aircraft.
Because aircraft structures have certain particularity in the aspects of management and technology, the problems that data records are inaccurate or incomplete, configuration management and structural reliability management cannot be really developed and the like generally exist in current aircraft structure management, the implementation of multiple management requirements such as corrosion evaluation, damage tolerance inspection of repair and modification and the like is not satisfactory, and a plurality of defects exist. Thus, FAA, EASA and CAAC all take into effect regulations for the continued airworthiness and safety improvement of aircraft, which means that maintenance engineering management on the civil aviation industry chain will face enormous challenges and pressures worldwide, especially as aviation operators will directly take over the pressures of regulatory implementation. For this reason, MROs must be faced with higher management requirements for the airline operators, and the technical standards and management requirements of the leasing companies upstream of the industrial chain need to be changed accordingly, otherwise the value of the fleet may be drastically reduced due to the inability to meet the requirements of the new regulations, and the companies will suffer huge economic losses.
As for the analysis and discovery of the advantages and disadvantages of the industrial problems and other similar tool software, application software for solving the problem of continuous airworthiness management of aircrafts in a system is urgently needed in the market
Disclosure of Invention
In order to solve the technical problem, the invention provides an aircraft management system based on a 3D lightweight model.
The specific technical scheme of the invention is as follows:
the invention provides an aircraft management system based on a 3D lightweight model, which comprises the following parts:
the system comprises an aircraft information management subsystem, a data processing subsystem and a data processing subsystem, wherein the aircraft information management subsystem is used for collecting structural information, configuration information and related continuous airworthiness management information of an aircraft, monitoring, managing and evaluating service management information of the aircraft, the service information comprises airworthiness file information, maintenance scheme information, damage handling information, modification information and reliability information, and each piece of service information comprises position information and event information;
the three-dimensional management subsystem is used for constructing a 3D model according to the structural information and the configuration information of the aircraft, and compressing the 3D model to obtain a 3D lightweight model; and the aircraft information management subsystem searches a corresponding position in the 3D lightweight model according to the position information for matching, associates the position information with the service information corresponding to the position information, and performs interactive operation through a terminal.
Further, the aircraft information management subsystem comprises the following parts:
the airworthiness management module is used for managing airworthiness files and evaluating and recording the continuous airworthiness condition of the aircraft;
the damage handling and evaluation management module is used for recording, evaluating and managing the damage information of the aircraft;
the maintenance scheme management module is used for providing maintenance reference schemes of various aircrafts, establishing a maintenance scheme of a novel aircraft in due time and receiving revision requests of other management modules in the aircraft information management subsystem;
the reliability management module is used for evaluating the comprehensive reliability of the aircraft according to the information provided by the airworthiness management module, the damage handling and evaluation management module and the maintenance scheme management module;
and the general service and platform setting module is used for automatically associating the recorded information and the evaluation information with corresponding positions in the D lightweight model according to the corresponding positions, comprehensively managing the aircraft information management subsystem and providing general management service.
Further, the airworthiness management module comprises the following parts:
the airworthiness file management unit is used for collecting, evaluating and managing airworthiness files and industry reference data, wherein the airworthiness files comprise mandatory airworthiness files and non-mandatory airworthiness files;
the engineering evaluation management unit is used for receiving, evaluating and executing the mandatory airworthiness file and the service announcement received by the system;
and the project review management unit is used for receiving, evaluating and executing the non-mandatory airworthiness file and the industry reference data received by the system.
Further, the injury treatment and assessment management module comprises the following parts:
the damage and treatment management unit is used for recording the physical damage condition of the aircraft, giving a treatment scheme of treatment operation and recording the actual treatment operation;
the corrosion prevention and control management unit is used for carrying out risk assessment on corrosion damage of the aircraft structure, proposing prevention and improvement measures and simultaneously executing control management;
the structure modification management unit is used for evaluating and managing a structure modification scheme of the aircraft, implementation of the modification scheme and continuous airworthiness after modification implementation, and evaluating and managing according to different modification schemes and generated mutual influence;
and the structural damage tolerance management unit is used for evaluating and managing the damage of the fatigue critical part and the pressurization boundary part occurring in the aircraft and the damage tolerance of the fatigue critical part and the pressurization boundary part in the refitting scheme.
Further, the reliability management module comprises the following parts:
the structural reliability evaluation unit is used for evaluating the structural reliability of the aircraft according to the information provided by the airworthiness management module, the damage handling and evaluation management module and the maintenance scheme management module to acquire structural reliability data;
the time management unit is used for monitoring the execution file meeting the airworthiness file requirement according to the specification of the airworthiness file, and performing continuous airworthiness management on the evaluation result of the reliability management module;
and the data visualization unit is used for processing and quantifying the structural reliability data and displaying the structural reliability data in an intuitive chart form.
Further, the general service and platform setting module comprises the following parts:
the airworthiness report management unit is used for automatically summarizing the service state information and the reliability data information of the aircraft into a report format according to the regulation requirement format;
the system comprises an execution file management unit, a data processing unit and a data processing unit, wherein the execution file management unit is used for evaluating and auditing the service requirements and airworthiness file requirements of all modules in the aircraft information management subsystem and generating an engineering execution file which can be executed by a service production department according to the requirements, and the execution file comprises file generation time, specific operation steps, required articles and process methods and execution deadline;
the system comprises a structural file management unit, a configuration file management unit and a configuration file management unit, wherein the structural file management unit is used for establishing a complete structural string file, a mounting position and a space position for a fleet, and when the structural string file is transferred, the corresponding structural configuration file is packed and transferred;
and the information association unit is used for automatically associating the recorded information and the evaluation information with corresponding positions or components in the D lightweight model.
Further, the general service and platform setting module further comprises the following parts:
and the label generating unit is used for respectively generating a unique label for each part in the aircraft according to the service information and the configuration information, wherein the label is a bar code or an RFID passive label and is used for quickly retrieving and inquiring the service information and the configuration information.
Further, the three-dimensional management subsystem comprises the following parts:
the application program management module is used for carrying out centralized management on tools and plug-ins in the three-dimensional management subsystem;
the 3D model management module is used for constructing a 3D model according to the structural information and the attribute information of the aircraft and performing 3D display;
the structure unit service attribute editing module is used for dividing the 3D model into a plurality of structure units according to structure and function, and adding service attribute to each structure unit and editing;
and the structural unit management module is used for editing and interactively operating each structural unit in the 3D model in an object mode.
Further, the 3D model management module includes the following parts:
the model data conversion unit is used for importing the original model data of the aircraft, performing discrete processing on the original model data and converting the original model data into standard geometric figure data;
the model data compression unit is used for compressing the geometric figure data through a geometric compression algorithm;
the model loading unit is used for analyzing and restoring the compressed geometric data and loading the geometric data into a 3D model;
a 3D display unit for angle, multi-azimuth and multi-scale view presentation from inside and outside of the 3D model, respectively;
a configuration analysis unit for comparing configuration differences of different models
Further, the structural unit management module comprises the following parts:
a positioning unit for formulating multiple positioning modes for the 3D model according to standard orientation and conventional orientation, and managing the mutual switching of different positioning modes
The structure unit interaction unit is used for selecting a structure unit from the 3D model and carrying out interaction operation;
and the analysis calculation unit is used for calculating and analyzing the change of the attribute information of the structural unit and generating a visual chart.
The invention has the following beneficial effects: the invention provides an aircraft management system based on a 3D lightweight model, which takes airworthiness files as standards, manages, records and analyzes the service information of an aircraft through an aviation information management subsystem, and integrates the information to manage the structural reliability of the aircraft; the 3D lightweight model of the aircraft is created through the three-dimensional management subsystem, the service information is associated in the 3D lightweight model according to the position information, the aircraft management information can be greatly simplified, and managers can read and interactively operate through a PC or a mobile terminal, so that the flexibility of airworthiness management of the aircraft and even a fleet is effectively improved. Through the processing, relevant managers and maintenance personnel can visually and conveniently acquire and share the change condition of the aircraft attribute information, and the aircraft structure reliability assessment is quantified and visualized, so that the visualization, the flow and the intelligent management of the aircraft structure business information are realized.
Drawings
Fig. 1 is a schematic structural diagram of an aircraft management system based on a 3D lightweight model according to embodiment 1;
fig. 2 is a schematic structural diagram of an aircraft information management subsystem in an aircraft management system based on a 3D lightweight model according to embodiment 2;
fig. 3 is a schematic structural diagram of a three-dimensional management subsystem in the aircraft management system based on the 3D lightweight model according to embodiment 2.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings.
Example 1
As shown in fig. 1, embodiment 1 of the present invention provides an aircraft management system based on a 3D lightweight model, including the following parts:
the aircraft information management subsystem 1 is used for collecting structural information, configuration information and relevant continuous airworthiness management of an aircraft, monitoring, managing and evaluating business information of the aircraft, wherein the business information comprises airworthiness file information, maintenance scheme information, damage handling information, modification information and reliability information, and each piece of business information comprises position information and event information;
the three-dimensional management subsystem 2 is used for constructing a 3D model according to the structural information and the configuration information of the aircraft, and compressing the 3D model to obtain a 3D lightweight model; the aircraft information management subsystem 1 searches corresponding positions in the 3D lightweight model according to the position information (including coordinates, regions, part numbers and the like) for matching, associates the corresponding positions with the service information corresponding to the position information, and performs interactive operation through a terminal.
The aircraft information management subsystem 1 is based on IAAS services such as public cloud services (Ali cloud ECS servers and Tencent cloud), and a PaaS cloud platform based on a micro-service architecture and a Docker container technology provides a set of flow system for rapid service development, deployment, operation and maintenance management and continuous development and continuous integration for developers. The platform provides resources such as infrastructure, middleware, data service, cloud server and the like, developers only need to develop business codes and submit the business codes to the platform code base to perform necessary configuration, the system can be automatically constructed and deployed, and agile development and rapid iteration of application are realized. In the system architecture, the PaaS cloud platform is mainly divided into a micro-service architecture, a Docker container technology and a DevOps. OpenShift is adopted as a service platform of a cloud container, and the service platform brings docker and Kubernetes technologies into enterprise service application. OpenShift can easily and quickly realize the construction, development and deployment of applications in any architecture (in public or private cloud). In the technical implementation of cloud service, the platform simplifies and encapsulates the general data authority, reduces the granularity to personnel, and supports personnel and data, and role and data authority customization. The data authority not only supports organization, department and role, but also can support filtering of data information of business fields of the user through configuration. Spring transaction @ transaction annotation is used for transaction processing, method-level transaction control is carried out, and independent transaction processing and rollback are not needed. Such as configuring propagation behavior, performing transaction inheritance, sub-transactions, transaction rollback behavior, etc., configuring isolation levels to read uncommitted data, etc.
The three-dimensional management subsystem 2 is a subsystem developed on the basis of WebGL (novel native Web graphic library), hardware 3D accelerated rendering is provided for HTML5Canvas on the basis of OpengleS, aircraft models and related visualization data are displayed in a browser in a smooth mode through a display card, cross-platform and native support is supported to operate in webview, pc, ios and Android, high-performance or intensive calculation is performed through a WebGL shader or webassempty, a large aircraft model is loaded, checked and operated at a browser end, various auxiliary visualization displays of complex aircraft structure management are completed, and complex calculations such as marking and patching are completed.
In order to implement the above functions, the aircraft information management subsystem 1 includes the following parts:
the airworthiness management module 11 is used for managing airworthiness files and evaluating and recording the continuous airworthiness condition of the aircraft;
the damage handling and evaluation management module 12 is used for recording, evaluating and managing the service information of the aircraft;
the maintenance scheme management module 13 is used for providing maintenance reference schemes of various aircrafts, establishing a maintenance scheme of a novel aircraft, and receiving revision requests of other management modules in the aircraft information management subsystem 1;
the reliability management module 14 is used for evaluating the comprehensive reliability of the aircraft according to the information provided by the airworthiness management module 11, the damage handling and evaluation management module 12 and the maintenance scheme management module 13;
and the general service and platform setting module 15 is used for automatically associating the recorded information and the evaluation information with corresponding positions in the 3D lightweight model according to the corresponding positions, comprehensively managing the aircraft information management subsystem, and providing general management services (including file management, information automatic association and the like).
Faults and damages of aircraft mainly include the following conditions:
(1) the performances of the aircraft and the systems and parts thereof are obviously degraded;
(2) the problems of aging of parts, insulation aging of an electric circuit, easy short circuit, ignition and the like occur, and the sealing performance of the rubber seal is poor;
(3) the mechanical accessories are seriously worn;
(4) the properties of the part material such as strength, pressure resistance, tensile strength and the like are reduced due to corrosion, fatigue, stress, cracks and the like;
(5) the reliability of the system and the components is reduced, so that the failure of the system and the components is obviously increased.
Once the positions, components and regions of the aircraft structure maintenance scheme, the airworthiness file and the like are determined, the platform can automatically display all service information (the structure maintenance scheme, the airworthiness file and evaluation information, historical damage and disposal information, reliability alarm, structure modification information and the like) related to the aircraft structure maintenance scheme, the airworthiness file and the evaluation information, the historical damage and disposal information, the reliability alarm, the structure modification information and the like) and provide all-around information for engineers, so that correct decision making is facilitated, and therefore, any technical files related to fatigue key structures, such as airworthiness instructions, service notifications and the like can be accurately identified and timely evaluated, adopted and executed; and evaluating and finding the damage on the fatigue key reference structure, and after the repair is finished, prompting an engineer that DTI information needs to be acquired and added into a maintenance scheme by the system, and tracking subsequent management and control until the work is closed.
The three-dimensional management subsystem 2 comprises the following parts:
the application program management module 21 is used for performing centralized management on tools and plug-ins in the three-dimensional management subsystem;
the application management module 21 is a medium-large application framework integrating various applications, wherein the execution of related commands and transactions is controlled through Command and Transaction, the loading, caching and the like (such as textures, geometric models and the like) of resource class files are managed through IO and Cache, plug-ins with related functions are added through plugin and are easy to expand, selection is used for controlling pick-up related behaviors and interacting with a UI module, and MVC is mainly used for designing aircraft objects, aircraft structural part objects, marks and patch objects, and 2d and 3d views and related logic controls of the objects;
the 3D model management module 22 is used for constructing a 3D model according to the structural information and the attribute information of the aircraft and performing 3D display;
the structure unit service attribute editing module 23 is configured to divide the 3D model into a plurality of structure units according to structure and function, and add a service attribute to each structure unit and edit the service attribute;
and the structural unit management module 24 is used for editing and interactively operating each structural unit in the 3D model in an object mode.
The aircraft management system based on the 3D lightweight model provided in this embodiment has a general service implementation method that an aircraft is parameterized and modeled, configuration data and position information of a component are defined in the model, a business entity modeling software tool is used to derive the model into an intermediate format, the model is lightened through feature extraction and a data compression algorithm and then loaded to a PC or a mobile terminal for use, the service information related to a structure is associated with a region, a position, a component and the like of the aircraft parameterized model through the aircraft structure management system, the structure service information is displayed in a lump by using a three-dimensional model view-based stereo excellent interaction means, and software is used to automatically remind and judge a task, so that the work efficiency of an engineer is improved.
The system mainly obtains the service data of the structure from three modules of airworthiness files, structure damage management and structure modification management, an engineer evaluates and implements the service data, the airworthiness files, the damage, the modification structural part or the modification influence area are calibrated on a three-dimensional view in the evaluating process, relevant information is comprehensively displayed through the three-dimensional view in the evaluating process, and the platform manages the association and the mutual influence among the service information, so that a complete service integral service is formed, and the reliability management of the structure of the aircraft is finally realized.
Example 2
As shown in fig. 2, this embodiment 2 provides an aircraft management system based on a 3D lightweight model based on embodiment 1, and this embodiment 2 further defines that the airworthiness management module 11 includes the following parts:
a airworthiness document management unit 111, configured to collect, evaluate and manage airworthiness documents and industry reference data, where the airworthiness documents include mandatory airworthiness documents (airworthiness commands issued by airworthiness authorities) and non-mandatory airworthiness documents (service announcements, service letters, and the like issued by aircraft manufacturers);
the engineering evaluation management unit 112 is configured to receive, evaluate and execute the mandatory airworthiness file and the service announcement received by the system;
the project review management unit 113 is configured to receive, evaluate, and execute a non-mandatory airworthiness file and an industry reference file received by the system.
The injury treatment and assessment management module 12 includes the following:
the damage and treatment management unit 121 is used for recording physical damage conditions of the aircraft structure, giving a reference treatment scheme of treatment operation after evaluation by professional engineers, recording actual treatment operation, and automatically judging and reminding according to configuration attribute information; for example, for the damage on the fatigue critical part or the pressurized structural part, a prompt is sent for whether the structural damage tolerance evaluation needs to be carried out;
a corrosion prevention and control management unit 122, configured to perform risk assessment on corrosion damage of the aircraft structure, propose prevention and improvement measures, perform control management, and perform automatic judgment and prompting according to configuration attribute information; for example, for corrosion damage of the PSE, the corrosion evaluation is prompted, and a subsequent corrosion evaluation task is automatically initiated after confirmation is obtained;
a structural refitting management unit 123, configured to evaluate and manage a structural refitting scheme of the aircraft, implementation of the refitting scheme, and continued airworthiness after the refitting implementation, and evaluate and manage according to different refitting schemes and generated mutual influences; for example, if there is just a airworthiness command in the repair area or the modification affected area of the structural member, the platform will automatically remind the engineer to apply for the AMOC;
a structural damage tolerance management unit 124 for assessing and managing damage to fatigue critical components, pressurization boundary components occurring within the aircraft, and damage tolerance of fatigue critical components and pressurization boundary components in a retrofit solution.
The reliability management module 14 includes the following parts:
the structural reliability evaluation unit 141 is configured to evaluate the structural reliability of the aircraft according to the information provided by the airworthiness management module 11, the damage handling and evaluation management module 12, and the maintenance plan management module 13, and acquire structural reliability data;
a time management unit 142, configured to manage execution deadline in the execution file and an evaluation result of the reliability management module 13 according to a specification of the airworthiness file; the evaluation result and the time for executing the file are scientifically managed, so that the structural engineering evaluation decision and the execution file are not overdue or omitted, and the closed-loop management of a complete chain is realized;
the data visualization unit 143 is configured to process and quantify the structural reliability data, and display the structural reliability data in an intuitive chart form; through comprehensive arrangement of module damage and abnormal information data such as aircraft damage, modification and maintenance schemes and the like, quantification of the module damage and abnormal information data is performed, and through big data cleaning, mining and processing, structural reliability management is achieved, and a user is assisted to master the structural performance change trend of a single aircraft and a fleet in time; for structural reliability data presentation, various visual graphical displays may be provided, such as histograms, pie charts, thermodynamic diagrams, and the like.
The general service and platform setting module 15 includes the following parts:
the airworthiness report management unit 151 is used for automatically summarizing the service state information (including an aircraft damage map, a repair map, a pit map, a difficult-to-use report, an important refitting list, an important repair list, an airworthiness instruction list and the like) and the reliability data information of the aircraft into a report format according to the regulation requirement format;
an execution file management unit 152, configured to evaluate and review the service requirements and airworthiness file requirements of all modules in the aircraft information management subsystem 1 (this step is completed by an engineer), generate an execution file that a service production department can follow the executed project, where the execution file includes file generation time, specific operation steps, required supplies (materials, tools, etc.), required process methods (special processes, connection methods, etc.), and execution deadline;
the structured file management unit 153 is used for establishing a complete structured configuration file with a structure capable of being stringed, installed and in a space position for the fleet, and when the structure capable of being stringed is transferred, the corresponding structured file is packed and transferred;
an information associating unit 154 for automatically associating the recorded information and the evaluation information with respective positions or constructions in the 3D lightweight model.
In order to facilitate the manager to quickly obtain the relevant information and reduce the time cost, the general service and platform setting module 15 further includes the following parts:
the tag generation unit 155 is configured to generate a unique tag for each part in the aircraft according to the service information and the configuration information, where the tag is a barcode or an RFID passive tag; the module automatically generates labels in the forms of bar codes, RFID passive labels and the like (common two-dimensional code forms can also be adopted) for concerned items such as parts, repair, modification and the like, and information can be quickly inquired and acquired on site through mobile platforms such as a tablet, a mobile phone, an RFID reader and the like
Example 3
As shown in fig. 3, this embodiment 3 provides an aircraft management system based on a 3D lightweight model based on embodiment 1, and this embodiment 3 further defines that the 3D model management module 22 includes the following parts:
the model data conversion unit 221 is used for importing the original model data of the aircraft into a 3d max conversion plug-in unit, performing discrete processing, and converting the original model data into a standard novel geometric figure data gltf2.0 format;
a model data compression unit 222, configured to compress, by using a google draw geometric compression algorithm, mesh data (including compressed vertex positions, connection information, texture coordinates, and normal data) in the geometric figure data in the gltf2.0 format;
on the premise of ensuring the visual fidelity and precision requirements, the 3D model file can be greatly reduced, the aircraft model can be downloaded more quickly, and the 3D graph can be displayed more quickly. By the compression technique, the converted size of the whole aircraft model is about 17.5 MB;
the model loading unit 223 is used for analyzing and restoring the compressed geometric data by utilizing webelementary and webworker, and loading the compressed geometric data into a 3D model;
the model loading utilizes webassempty and webworker to analyze compressed geometric data in a web program with performance close to the native performance, so that the geometric data are restored at a higher speed, and quick loading is realized, and the technology enables the whole aircraft model to be loaded within 10s (model files are cached) (on pc, mobile equipment can additionally increase some time due to hardware performance);
a 3D display unit 224 for angle, multi-azimuth and multi-scale view presentation from inside and outside of the 3D model, respectively;
the 3D display unit 224 is a graphic display component based on threj s (webgl) and raplaelj s (svg) kernels, has a cross-platform property based on the native HTML5 standard, can perform graphic acceleration with a graphics card, and provides smooth 3D display and related visualization effects. This module provides the following functions: translation, rotation, zooming and self-adaptive centered display; providing a front view, a rear view, an upper view, a lower view, a left view, a right view, an isometric view, and other aeronautical predefined views; providing a cross-sectional view function of the three coordinate axis directions of the aircraft; soft shadow effect and sky box background; providing highlighting, flashing, semi-transparent, coloring and the like to display the designated 3D object; providing a rapid centered display designated object, supporting classified filtering display, and supporting filtering display according to the section of the aircraft; the method supports displaying the related information of the structural object in a Tool Tips mode and displaying various related information items;
the configuration analysis unit 225 is used for comparing configuration differences of different machine types, so that engineers can visually and conveniently see the change of the configuration on different machine types, and time cost for analyzing different refitting schemes can be greatly saved.
The structural unit management module 24 includes the following parts:
the positioning unit 241 is used for making a plurality of positioning modes for the 3D model according to the standard orientation and the conventional orientation respectively and managing the mutual switching of different positioning modes;
the positioning unit 241 not only provides standard position input modes (BS, WL, BL), but also considers the current use and maintenance habits of the aircraft, and can identify position information such as a fuselage station position and a stringer position; meanwhile, interaction modes such as model position pickup, curved surface pickup, parameter generation standard bounding boxes, non-equal straight section variant bounding boxes ((stretching bodies, sweeping bodies) pickup and the like can be adopted, so that the problems that the aircraft structural member is complex to position and accurate positions cannot be provided on site are solved;
a structural unit interaction unit 242, configured to select a structural unit from the 3D model and perform an interaction operation;
conventional interaction operations include the following: acquiring a selected structural unit (one \ a plurality \ a group); acquiring one selected structural unit (hovering the mouse for more than 2 seconds); acquiring adjacent structural units, marks and patches; acquiring the picked-up position (coordinates of a single point or coordinates of a selected range); acquiring a selected mark; obtaining a selected patch; displaying one or a plurality of structural units; displaying the range selected by the user in the 3D model; displaying and filtering the components by aircraft section or category;
and an analysis calculating unit 243, configured to calculate and analyze the change of the attribute information of the structural unit, and generate a visualized chart.
A manager calls services deployed by an aircraft management system through a user terminal, a model file required by a user is loaded into a PC (personal computer), a VR (virtual reality) terminal, a mobile phone, a tablet and customized terminal equipment, and structural business information related to the aircraft is input and submitted into an aircraft information management cloud platform through methods such as manual input, mobile phone photographing input, augmented reality and the like; once the model is loaded on the PC, the mobile terminal or the tablet terminal, the platform manages the components in an object manner, and implements the functions of editing the service attributes of the aircraft units, selecting and picking up the aircraft units (single selection, frame selection, stereo variant bounding box selection, etc.), precisely positioning coordinates (station STA, stringer STR, longitudinal line (BL) and waterline position (WL)), marking, patch, component adjacent search, aircraft unit calculation and analysis, damage map, thermodynamic diagram, and the like, respectively.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the present invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (8)
1. An aircraft management system based on a 3D lightweight model is characterized by comprising the following parts:
the system comprises an aircraft information management subsystem (1) and a service management subsystem, wherein the aircraft information management subsystem is used for collecting structural information, configuration information and related continuous airworthiness management information of an aircraft, monitoring, managing and evaluating service management information of the aircraft, the service management information comprises airworthiness file information, maintenance scheme information, damage handling information, modification information and reliability information, and each piece of service management information comprises position information and event information;
the three-dimensional management subsystem (2) is used for constructing a 3D model according to the structural information and the configuration information of the aircraft, and compressing the 3D model to obtain a 3D lightweight model; the aircraft information management subsystem (1) searches for a corresponding position in the 3D lightweight model according to the position information for matching, associates the position information with the service management information corresponding to the position information, and performs interactive operation through a terminal;
the aircraft information management subsystem (1) comprises the following parts:
the airworthiness management module (11) is used for managing airworthiness files and evaluating and recording the continuous airworthiness condition of the aircraft;
a damage handling and assessment management module (12) for recording, assessing and managing damage information of the aircraft;
the maintenance scheme management module (13) is used for providing maintenance reference schemes of various aircrafts, establishing a maintenance scheme of a novel aircraft in due time and receiving revision requests of other management modules in the aircraft information management subsystem (1);
a reliability management module (14) for evaluating the overall reliability of the aircraft according to the information provided by the airworthiness management module (11), the damage handling and assessment management module (12) and the maintenance protocol management module (13);
the general service and platform setting module (15) is used for automatically associating the recorded information and the evaluation information with corresponding positions in the 3D lightweight model according to the corresponding positions, comprehensively managing the aircraft information management subsystem (1) and providing general management service;
the general service and platform setting module (15) comprises the following parts:
the airworthiness report management unit (151) is used for automatically summarizing the business state information and the reliability data information of the aircraft into a report format according to the regulation requirement format;
the execution file management unit (152) is used for evaluating and auditing the service requirements and airworthiness file requirements of all modules in the aircraft information management subsystem (1) and generating a project execution file which can be executed by a service production department, wherein the execution file comprises file generation time, specific operation steps, required supplies and process methods and execution deadline;
the system comprises a structured file management unit (153) and a data processing unit, wherein the structured file management unit is used for establishing a complete structured configuration file with a structure capable of being stringed, installed and in a space position for a fleet, and when the structured stringed is transferred, the corresponding structured configuration file is packed and transferred;
an information associating unit (154) for automatically associating the recorded information and the evaluation information with respective positions or members in the 3D lightweight model.
2. 3D lightweight model based aircraft management system according to claim 1, characterized in that the airworthiness management module (11) comprises the following parts:
the airworthiness file management unit (111) is used for collecting, evaluating and managing airworthiness files and industry reference data, wherein the airworthiness files comprise mandatory airworthiness files and non-mandatory airworthiness files;
the engineering evaluation management unit (112) is used for receiving, evaluating and executing the mandatory airworthiness file and the service announcement received by the system;
and the project review management unit (113) is used for receiving, evaluating and executing the non-mandatory airworthiness file and the industry reference data received by the system.
3. 3D lightweight model based aircraft management system according to claim 1, characterized in that the damage handling and assessment management module (12) comprises the following parts:
a damage and treatment management unit (121) for recording the physical damage condition of the aircraft, giving a treatment scheme of treatment operation and recording the actual treatment operation;
a corrosion prevention and control management unit (122) for risk assessment of corrosion damage to the aircraft structure and for proposing preventive and improvement measures while performing control management;
a structural refitting management unit (123) for evaluating and managing structural refitting schemes, implementation of the refitting schemes and continuous airworthiness after the refitting implementation of the aircraft, and evaluating and managing according to different refitting schemes and generated mutual influence;
a structural damage tolerance management unit (124) for assessing and managing damage to fatigue critical and pressurization boundary pieces occurring within the aircraft and damage tolerance of fatigue critical and pressurization boundary pieces in a retrofit scenario.
4. 3D lightweight model based aircraft management system according to claim 1, characterized in that the reliability management module (14) comprises the following parts:
a structural reliability evaluation unit (141) for evaluating the structural reliability of the aircraft according to the information provided by the airworthiness management module (11), the damage handling and evaluation management module (12) and the maintenance scheme management module (13) to obtain structural reliability data; the time management unit (142) is used for monitoring the execution files meeting the airworthiness file requirements according to the provisions of the airworthiness files, and performing continuous airworthiness management on the evaluation result of the reliability management module (14);
and the data visualization unit (143) is used for processing and quantifying the structural reliability data and displaying the structural reliability data in a visual chart form.
5. 3D lightweight model based aircraft management system according to claim 1, characterized in that the general service and platform setup module (15) further comprises the following parts:
and the label generating unit (155) is used for respectively generating a unique label for each part in the aircraft according to the business management information and the configuration information, wherein the label is a bar code or an RFID passive label and is used for quickly retrieving and inquiring the business management information and the configuration information.
6. 3D lightweight model based aircraft management system according to claim 1, characterized in that the three-dimensional management subsystem (2) comprises the following parts:
the application program management module (21) is used for carrying out centralized management on tools and plug-ins in the three-dimensional management subsystem (2);
the 3D model management module (22) is used for constructing a 3D model according to the structural information and the attribute information of the aircraft and performing 3D display;
the structure unit service attribute editing module (23) is used for dividing the 3D model into a plurality of structure units according to structure and function, and adding service attribute to each structure unit and editing;
and the structural unit management module (24) is used for editing and interactively operating each structural unit in the 3D model in an object mode.
7. The 3D lightweight model based aircraft management system according to claim 6, characterized in that the 3D model management module (22) comprises the following parts:
the model data conversion unit (221) is used for importing the original model data of the aircraft, performing discrete processing on the imported original model data and converting the imported original model data into standard geometric figure data;
a model data compression unit (222) for compressing the geometry data by a geometry compression algorithm;
a model loading unit (223) for analyzing and restoring the compressed geometric data and loading into a 3D model;
a 3D display unit (224) for angle, multi-azimuth and multi-scale view presentation from inside and outside the 3D model, respectively;
and the configuration analysis unit (225) is used for comparing configuration differences of different models.
8. The 3D lightweight model based aircraft management system according to claim 6, characterized in that the structural unit management module (24) comprises the following parts:
a positioning unit (241) for making a plurality of positioning modes for the 3D model according to a standard orientation and a conventional orientation, and managing a structural unit interaction unit (242) for mutual switching of different positioning modes, and selecting a structural unit from the 3D model and performing interaction operation;
and the analysis calculation unit (243) is used for calculating and analyzing the attribute information change of the structural unit and generating a visual chart.
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| CN114707680B (en) * | 2022-05-17 | 2022-08-26 | 北京汉端科技有限公司 | Aircraft 3D model generation method and device, electronic equipment and readable medium |
| CN115034630A (en) * | 2022-06-16 | 2022-09-09 | 北京汉端科技有限公司 | Method, device, equipment and readable medium for displaying configuration information in grading mode |
| CN114996534A (en) * | 2022-06-16 | 2022-09-02 | 北京汉端科技有限公司 | Cloud platform continuous airworthiness management system and method based on digital twin technology |
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