CN114756916A - Aircraft performance software computation kernel pre-post processing system, method, medium and device - Google Patents
Aircraft performance software computation kernel pre-post processing system, method, medium and device Download PDFInfo
- Publication number
- CN114756916A CN114756916A CN202210391819.XA CN202210391819A CN114756916A CN 114756916 A CN114756916 A CN 114756916A CN 202210391819 A CN202210391819 A CN 202210391819A CN 114756916 A CN114756916 A CN 114756916A
- Authority
- CN
- China
- Prior art keywords
- calculation
- data
- kernel
- module
- task
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/12—Geometric CAD characterised by design entry means specially adapted for CAD, e.g. graphical user interfaces [GUI] specially adapted for CAD
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention belongs to the technical field of data processing equipment, and discloses a pre-post processing system, a method, a medium and equipment for an aircraft performance software computing kernel, wherein the pre-post processing system for the aircraft performance software computing kernel comprises: a pre-processing module comprising: the system comprises a fixed data reading layer, a fixed data extraction layer, an input parameter reading layer, an input parameter extraction layer, an input parameter integrity checking layer, a regulation and manual conformance checking layer and an input parameter unit conversion layer; a performance service calculation module; a post-processing module comprising: the system comprises a calculation exception module, a calculation progress module, a calculation suspension module, a data dimension conversion module, a data block output module, a table output module, a user unit system restoration module and a task consistency check module. The invention meets the requirements of cloud computing and multi-model computing, conforms to the international standard of civil aviation, and can be continuously and stably applied to the architecture and the method of an airline company and operation support practice.
Description
Technical Field
The invention belongs to the technical field of data processing equipment, and particularly relates to a system, a method, a medium and equipment for processing the performance of an aircraft software computation kernel.
Background
At present, aircraft performance software is an industry tool which is provided for an airline company user by an aircraft manufacturer or an entrusting party thereof to use and is matched with a specific aircraft type to generate performance data content required by aircraft operation. The interactive interface mainly engages in graphical user input interaction, generation and assignment of calculation tasks, invocation of calculation kernels and processing and presentation of calculation results; the calculation kernel mainly encapsulates basic data such as pneumatics, thrust, machine types and the like closely related to the machine types, pre-processing such as analysis, translation, preparation and the like is carried out on calculation tasks through the pre-processing, the calculation results are formatted and output through the post-processing, and algorithm models with corresponding functions are called to complete corresponding simulation calculation. The two parts have independent functions and are required to cooperate with each other to achieve the final aim of the performance calculation implemented by a user through the interaction of the calculation task and the calculation result. Due to the numerous parameters of the computing task and the computing result, the parameters comprise: atmospheric environment parameters, airport parameters, airplane configuration parameters, engine setting parameters and the like, and the contents need to follow the logic constraint and range limitation in a machine model manual due to the limits of airworthiness certification and operation regulations and are not independent of each other, so that how to transmit and identify the information completely and effectively in the software operation process for a single machine model and how to prevent the information from being tampered and overlapped in the software operation process for different machine models, thereby causing the calculation kernel to be more robust and more efficient. The method is efficient, namely the method can be suitable for simulation calculation of different calculation functions and different models without deeply modifying a calculation kernel. No matter the addition of a computing function or the addition of a new machine type, relevant parameters, constraint logics and limiting conditions can be obviously changed, and how to establish a reasonable pretreatment and post-treatment architecture technology of a performance computing kernel can quickly adapt to relevant changes under the condition of minimum change work is urgently needed to be solved.
The transfer parameter of the performance software of the domestic airplane is mostly handled by directly transferring a self-defined array to a computing kernel through an interface, and writing and analyzing are carried out according to the agreed definition. Therefore, firstly, the problem is that parameters of different performance service calculation types are mixed together, which is not beneficial to expansion and maintenance; secondly, the problem that different machine types are difficult to reuse the same group of parameters is not beneficial to problem troubleshooting and maintenance improvement; the last problem is that once inappropriate, illogical, and out-of-limit inputs occur, problems such as simulation errors, calculation overrun, illegal results, and interface card crash can result. International mainstream aircraft manufacturers (boeing, air passenger) have unified the computing interface of their model matching performance software for data transmission, basically according to the relevant documents of international aviation protocol IATA departure. Although the standard defines each parameter related to the interface clearly according to the flight phase and performance service so as to facilitate the user to call the computing kernel of the model matching performance software of the user, the analysis and processing flow and link of the parameters in the computing kernel are not described. For commercial reasons, this part of the technology is not disclosed internationally.
With the development and the orderly development of the manufacturing activities of the domestic civil aircrafts, the delivery quantity of the domestic civil aircrafts is increasing day by day, the requirement that an airline company peels off a user interaction interface provided by a manufacturer and directly implements secondary development on an interface of a computing kernel packaged by the manufacturer is also increasing day by day, and the realization of a new and complete architecture method for the front and back processing of the aircraft performance software computing kernel is urgent.
Through the above analysis, the problems and defects of the prior art are as follows: in the prior art, the computing kernel architecture of the Chinese civil aircraft customized performance software has no public standard, cannot effectively meet the actual requirements of model change or third party calling, has poor maintainability and expandability and influences the popularization of the Chinese aircraft.
The difficulty in solving the above problems and defects is: the simulation calculation of the airplane performance software calculation kernel relates to multiple disciplines such as aerodynamics, atmospheric environment, airport conditions, flight mechanics, engines and the like; parameters and constraints which need to be processed in calculation are numerous, but parameters and constraints of different models have differences, parameters and constraints of different flight stages of the same model have differences, and parameters and constraints of different flight stages of the same model have differences; how to ensure the program robustness, result usability and function aggregation of the software under complex conditions has higher difficulty.
The significance for solving the problems and the defects is as follows: when the domestic civil aircraft is delivered, whether mature aircraft customization performance analysis software matched with the aircraft type can be provided becomes one of key factors for accepting and recognizing the capability of the domestic civil aircraft, and the situation that the first user does not receive the aircraft without the performance software appears at one time; a good airplane performance software architecture has positive significance for solving the problems.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a system, a method, a medium and equipment for processing the performance of an aircraft software calculation kernel.
The design aims to establish a front-back processing framework of an aircraft performance software computing kernel capable of meeting cloud computing requirements and multi-model computing requirements so as to meet diversified and intelligent use requirements of cloud computing calling, multi-model general computing, secondary packaging and the like when domestic civil transport aircraft carry out activities such as security assessment, performance verification and the like. The invention is a kernel bottom layer framework of airplane performance software, unifies the flows and methods of pre-processing and post-processing, is decoupled from airplane performance service algorithm, and is convenient to use and maintain. Analyzing, translating and preparing the calculation task through pretreatment; and formatting and outputting the calculation result through post-processing, and calling an algorithm model with a corresponding function to complete corresponding simulation calculation.
The invention is realized in such a way, and provides a method for pre-and post-processing an aircraft performance software calculation kernel, which comprises the following steps:
firstly, recording and transmitting the user performance simulation calculation conditions in any form through a task file in a task data form; the pneumatic, thrust and characteristic data of any machine type are organized by a specific structure;
the second step, the calculation kernel preferentially finishes the work of reading the model data from the model database after being started, so that the influence of frequent reading operation in the middle of simulation calculation on the calculation efficiency is prevented; the computing kernel checks the integrity of the task file to prevent program crash caused by the integrity; the computing kernel checks the integrity of the task data block to prevent the program from crashing caused by the integrity;
checking the correctness of the read model database according to the key data in the task file to prevent the result from being mismatched; the computing kernel checks the data type and the data integrity of the SCAP standard task to prevent operation exception caused by the data type and the data integrity; the computing kernel checks the data type and the data integrity of the non-standard task to prevent operation exception caused by the checking; the calculation inner core carries out unit standardization on data items with physical meanings of length, height, speed and weight in the task data so as to meet the requirement of simulating and calculating a unified physical unit and prevent abnormal operation and result errors;
Step four, calculating the data items of the internal core after the unit standardization to check so as to prevent physical overrun and logic overrun; the calculation kernel analyzes the algorithm function matched with the current task, and starts the corresponding algorithm function to perform simulation calculation; simultaneously starting monitoring by the computing kernel, recording computing progress information and abnormal information, writing the computing progress information and the abnormal information into a log file, and stopping computing when receiving a stopping signal; converting multidimensional data generated by the calculation kernel when the calculation is normally completed into two-dimensional data, and preparing for outputting;
step five, when the text is output, the calculation kernel organizes a plurality of data according to the output items preset by the program or appointed by the task; when the text is output, the calculation kernel converts the standardized data according to a unit system preset by a program or specified by a task; writing a result file into the calculation kernel according to a text format specified by a user;
step six, when the table is output, calculating an inner core to define, position and assemble each unit of the table; when the table is output, the calculation inner core assigns values to each unit of the table; the calculation kernel writes the result file according to a table format specified by a user; calculating a kernel overloading task file, and adding input to a result file to ensure that the result file has input and output contents at the same time to form a unique identification degree; and the calculation kernel writes the check code, the version number and the calculation time information into the result file, and then stands by or ends.
Further, in the first step, the task data includes: the texts, the numerical values and the enumeration items are organized according to the form of an aircraft performance calculation standard interface of the international aviation protocol.
Further, in the first step, the aerodynamic data organization mode takes a flap, an undercarriage, a spoiler and a center of gravity as main keywords, and takes an air pressure height, a temperature and a mach number as secondary keywords.
Another object of the present invention is to provide an aircraft performance software computation kernel pre-post processing system for implementing the aircraft performance software computation kernel pre-post processing method, the aircraft performance software computation kernel pre-post processing system including:
the system comprises a preprocessing module, a performance service calculation module and a post-processing module;
a pre-processing module comprising: the system comprises a fixed data reading layer, a fixed data extraction layer, an input parameter reading layer, an input parameter extraction layer, an input parameter integrity verification layer, a regulation and manual conformance inspection layer and an input parameter unit conversion layer;
a post-processing module comprising: the system comprises a calculation exception module, a calculation progress module, a calculation suspension module, a data dimension conversion module, a data block output module, a form output module, a user unit system restoration module and a task consistency checking module.
Further, the fixed data reading layer and the fixed data extraction layer complete reading of pneumatic data, thrust data, characteristic data and the like, and proper judgment is carried out by combining the model in the input parameters, so that a matched model database is read; and decrypting the encrypted model database and reading the decrypted model database into the memory.
Further, the input parameter reading layer and the input parameter extracting layer complete the identification and analysis of the calculation task file, the atmospheric environment conditions, airport conditions, airplane conditions, engine conditions and calculation conditions set by a user are read into the memory at one time according to a unified format and method, and after preprocessing such as format verification, complete verification, conformity inspection, conversion from a user unit system to a standard unit system and the like, corresponding business algorithm modules are called for calculation by combining performance calculation business in the input parameters.
Further, when the abnormal computation module still has the conditions of improper and non-logical conditions to cause simulation computation errors, computation overrun and result illegal of the service algorithm module after pre-processing, the possible error prompt or error information is stored in a stack and output to a log file;
The calculation progress module is used for stacking and storing the relative condition of the current calculation progress state and the estimated calculation total amount through progress information and outputting the relative condition to a progress file in the execution process of the business algorithm module;
the calculation stopping module stops the current calculation flow in real time and reasonably ends the program according to the user instruction in the simulation calculation process of the service algorithm module, so that no reasonable way is available for control when the simulation calculation is falsely dead or the calculation is abandoned;
the data dimension conversion module is used for completing the local or global storage requirement of data in calculation only by using the multidimensional array as a business algorithm module, and when the result data is output to a result file, the result data is converted into a two-dimensional array so as to meet the requirement of reading by a user.
Further, the data block output module is an output mode for directly organizing and displaying data in a text form according to the point, curve, grid and sequence conventional engineering formats;
the form output module is an output mode which directly organizes and displays the data in a text form according to the special format of the aircraft performance professional chart;
the user unit system restoring module restores the data which is calculated by using the standard unit system to the user set unit system in the task file according to the types of distance, height, speed and weight;
The task consistency check module identifies and prevents the inconsistency between the result generated by the computing kernel and the computing task, which causes the damage of the consistency of the result and the computing kernel, and generates check codes according to the task file and stores the check codes in the result file to achieve the input and output consistency check.
Another object of the present invention is to provide a program storage medium for receiving user input, wherein the stored computer program enables an electronic device to execute the aircraft performance software computing kernel pre-processing and post-processing method, comprising the following steps:
firstly, recording and transmitting the user performance simulation calculation conditions in any form through a task file in a task data form; the pneumatic, thrust and characteristic data of any machine type are organized by a specific structure;
the second step, the calculation kernel preferentially finishes the work of reading the model data from the model database after being started, so that the influence of frequent reading operation in the middle of simulation calculation on the calculation efficiency is prevented; the computing kernel checks the integrity of the task file to prevent the program from crashing; the computing kernel checks the integrity of the task data block to prevent the program from crashing caused by the integrity;
checking the correctness of the read model database according to the key data in the task file to prevent the result from being mismatched; the computing kernel checks the data type and the data integrity of the SCAP standard task to prevent operation exception caused by the data type and the data integrity; the computing kernel checks the data type and the data integrity of the non-standard task to prevent operation exception caused by the checking; the calculation inner core carries out unit standardization on data items with physical meanings of length, height, speed and weight in the task data so as to meet the requirement of simulating and calculating a unified physical unit and prevent abnormal operation and result errors;
Step four, calculating the data items of the internal core after the unit standardization to check so as to prevent physical overrun and logic overrun; the calculation kernel analyzes the algorithm function matched with the current task, and starts the corresponding algorithm function to perform simulation calculation; simultaneously starting monitoring by the computing kernel, recording computing progress information and abnormal information, writing the computing progress information and the abnormal information into a log file, and stopping computing when receiving a stopping signal; converting multidimensional data generated by the calculation kernel when the calculation is normally completed into two-dimensional data, and preparing for outputting;
step five, when the text is output, the calculation kernel organizes a plurality of data according to the output items preset by the program or appointed by the task; when the text is output, the calculation kernel converts the standardized data according to a unit system preset by a program or specified by a task; writing the result file into the calculation kernel according to the text format specified by the user;
step six, when the table is output, calculating an inner core to define, position and assemble each unit of the table; when the table is output, the calculation inner core assigns values to each unit of the table; the calculation kernel writes the result file according to a table format specified by a user; calculating a kernel overloading task file, and adding input to a result file to ensure that the result file has input and output contents at the same time to form a unique identification degree; and the calculation kernel writes the check code, the version number and the calculation time information into the result file, and then stands by or ends.
Another object of the present invention is to provide a computer program product stored on a computer readable medium, comprising a computer readable program for providing a user input interface to implement the aircraft performance software computing kernel pre-processing method when executed on an electronic device.
By combining all the technical schemes, the invention has the advantages and positive effects that: on the basis of a bottom layer mechanism of a computational kernel architecture of a centi-cleaning plane performance software, the architecture and the method which meet the requirements of Chinese civil aviation regulations and regulations, accord with the international civil aviation standards and can be continuously and stably applied to an airline company and operation support practice are designed and developed for domestic civil aircrafts. The method is successfully applied to the development work of ARJ21 airplane performance software, continuously supports the release performance analysis work of each ARJ21 airplane, is applied to the aspects of market promotion, airline adaptability analysis and the like related to airplane types, greatly improves the release performance analysis efficiency, and powerfully improves the user acceptance and market competitiveness of ARJ21 airplanes. By 31/7/2021, the performance of an airplane flight under safety guarantee ARJ21 is analyzed for 3.3 ten thousand times. The invention is a kernel bottom layer architecture supporting all foreseeable airplane performance calculation services, unifies the flows and the methods of pretreatment and post-treatment, decouples the flows and the algorithms of the pre-treatment and the post-treatment with the airplane performance calculation services, and is convenient for maintenance and expansion.
The invention separates the pre-processing and post-processing of the computation kernel from the aircraft performance algorithm service, and has clear logical level and task division; the method has a plurality of necessary inspection links typically related to aircraft performance calculation; the invention can uniformly complete the conversion between the user unit system and the standard unit system before and after calculation; the invention completely obtains the calculation abnormity and the calculation progress and caches and records the calculation abnormity and the calculation progress; the invention can quickly suspend calculation to prevent dead halt. The method adopted by the framework of the invention abstracts common characteristics of pretreatment and post-treatment involved in most airplane performance calculation, fully considers the possible situations of users in use, meets the requirements of most airplane performance calculation on pretreatment and post-treatment of a software kernel, has good adaptability, can be adopted no matter in single machine local calling or in server remote calling, and is easy for later-stage troubleshooting and positioning. In view of the strict requirements in the field of the industry on the conformance of the aircraft performance software computing kernel to the limits of regulations and manuals, the robustness in the using process, the correctness of the computing result and the like, the new architecture realizes the following contents:
1) The scientific and complete pre-calculation processing flow of the aircraft performance calculation kernel standardizes the analysis of the calculation task and the analysis process of a database, combs necessary logics of the calculation task inspection, and defines the links of the regulation and the manual conformance inspection of the calculation task, the conversion of a user unit system to a standard unit system and the like;
2) the scientific and complete aircraft performance calculation kernel post-calculation processing flow standardizes necessary contents such as calculation abnormity, calculation progress, calculation suspension and the like, and defines links such as data block output, table output, standard unit system conversion, user unit system conversion and the like;
3) clear logical hierarchy and task division needed by the pre-processing and post-processing architecture of the aircraft performance computing kernel comprise: file path analysis, database inspection, calculation task inspection, unit standardization processing and reduction, algorithm calling, calculation state inspection, output item and output format adjustment and the like; there are a number of necessary inspection processes typically associated with aircraft performance calculations, including: structural integrity checking, format correctness checking, content integrity checking, content rationality checking, regulation and manual conformance checking, anomaly checking, progress checking and the like;
Meanwhile, the invention also has the following advantages: unified airplane model data organization and reading rules; organizing, analyzing and reading rules of unified simulation calculation tasks; defining, analyzing and reading rules of unified input parameters; unified organization rules of output parameters; unified unit conversion rules of input and output parameters; a unified checksum check rule for input and output parameters; unified abnormal or alarm information processing rules; a pre-processing and post-processing system architecture independent of airplane performance simulation calculation function service; easy addition, easy modification, easy maintenance and easy expansion.
Drawings
FIG. 1 is a schematic structural diagram of a pre-processing system and a post-processing system of an aircraft performance software computing kernel according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a preprocessing module according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a post-processing module according to an embodiment of the present invention;
in the figure: 1. a pretreatment module; 1-1, fixing a data reading layer; 1-2, a fixed data extraction layer; 1-3, inputting a parameter reading layer; 1-4, inputting a parameter extraction layer; 1-5, inputting a parameter integrity check layer; 1-6, regulatory and manual compliance check layer; 1-7, inputting a parameter unit conversion layer; 2. a performance service calculation module; 3. a post-processing module; 3-1, calculating an abnormal module; 3-2, calculating a progress module; 3-3, a calculation stopping module; 3-4, a data dimension conversion module; 3-5, a data block output module; 3-6, a table output module; 3-7, a user unit system reduction module; 3-8, and a task consistency checking module.
Fig. 4 is a flowchart of a method for pre-processing and post-processing an aircraft performance software computation kernel according to an embodiment of the present invention.
Fig. 5 is a schematic diagram of a pre-processing process and a post-processing process of an aircraft performance software computing kernel according to an embodiment of the present invention.
Fig. 6 is a design drawing (preprocessing) of a compute kernel interface according to an embodiment of the present invention.
Fig. 7 is a design diagram (preprocessing) of a constraint control mechanism provided by an embodiment of the present invention.
Fig. 8 is a constraint control rule code (pre-processing) provided in an embodiment of the present invention.
Fig. 9 is a task interface parameter list (pre-processing) provided by the embodiment of the present invention.
FIG. 10 is a computational task input (pre-processing) provided by an embodiment of the invention.
FIG. 11 is a result of a computational task (post-processing) provided by an embodiment of the invention.
Fig. 12 is an application (post-processing) of the settlement task result provided by an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Aiming at the problems in the prior art, the invention provides a system, a method, a medium and equipment for processing the performance of an aircraft software computing kernel before and after, provides an innovative method for building the pre-processing and post-processing of the computing kernel facing to the cloud computing calling requirement and the multi-model computing requirement, and can meet the requirement that domestic civil transport aircraft carry out the work of safety evaluation, performance verification and the like in an electronic and intelligent mode.
Those skilled in the art of the aircraft performance software computational kernel pre-post processing system provided by the present invention may also implement other steps, and the aircraft performance software computational kernel pre-post processing system provided by the present invention in fig. 1 is merely a specific example.
As shown in fig. 1 to fig. 3, an aircraft performance software computing kernel pre-processing system according to an embodiment of the present invention includes: the system comprises a pretreatment module 1, a performance service calculation module 2 and a post-treatment module 3.
A pre-processing module comprising: the system comprises a fixed data reading layer 1-1, a fixed data extraction layer 1-2, an input parameter reading layer 1-3, an input parameter extraction layer 1-4, an input parameter integrity verification layer 1-5, a regulation and manual compliance inspection layer 1-6 and an input parameter unit conversion layer 1-7.
A post-processing module comprising: the system comprises an abnormal calculation module 3-1, a progress calculation module 3-2, a calculation suspension module 3-3, a data dimension conversion module 3-4, a data block output module 3-5, a table output module 3-6, a user unit system restoration module 3-7 and a task consistency check module 3-8.
The fixed data reading layer 1-1 and the fixed data extraction layer 1-2 mainly complete reading of pneumatic data, thrust data, characteristic data and the like (generally called model databases), and the process needs to be properly judged by combining models in input parameters so as to read a matched model database; the process requires decrypting the encrypted model database and then reading the decrypted model database into the memory.
The input parameter reading layer 1-3 and the input parameter extracting layer 1-4 mainly complete the identification and analysis of the calculation task file, and the atmospheric environment condition, airport condition, airplane condition, engine condition, calculation condition, etc. set by the user are read into the memory at one time according to the unified format and method, and are preprocessed through format check, complete check, conformity check, conversion from user unit system to standard unit system, etc., and then the corresponding service algorithm module is called to calculate by combining the performance calculation service in the input parameters.
The calculation exception module 3-1 is capable of stacking and outputting possible error prompt or error information to a log file when improper and non-logical conditions possibly exist after preprocessing, so that simulation calculation errors, calculation overrun, results are illegal and the like of the service algorithm module can be caused.
The calculation progress module 3-2 is used for stacking the relative condition of the current calculation progress state and the estimated calculation total amount through the progress information and outputting the stacked state to a progress file in the execution process of the business algorithm module.
The calculation stopping module 3-3 is used for stopping the current calculation process in real time and reasonably ending the program according to the user instruction in the simulation calculation process of the service algorithm module, so that the situation that no reasonable way is available for control when the simulation calculation is dead in time or the calculation is abandoned is prevented.
The data dimension conversion module 3-4 means that the service algorithm module must use a multidimensional array to be able to complete the local or global storage requirement of the data in calculation, but when the result data is output to the result file, the result data must be converted into a two-dimensional array to be able to meet the requirement of the user for reading.
The data block output module 3-5 is an output mode for directly organizing and displaying data in a text form according to conventional engineering formats such as points, curves, grids, sequences and the like.
And the table output module 3-6 is an output mode for directly organizing and displaying the data in a text form according to the special format of the aircraft performance professional chart.
The user unit system restoring module 3-7 is a user setting unit system for restoring the data after calculation by using the standard unit system to the task file according to the categories of distance, height, speed, weight and the like.
The task consistency checking module 3-8 is used for identifying and eliminating inconsistency between a result generated by a computing kernel and a computing task, which causes the consistency of the result and the computing task to be damaged, and generating a checking code according to a task file and storing the checking code in a result file so as to achieve input and output consistency checking.
As shown in fig. 4, the method for processing aircraft performance software computing kernel before and after according to the embodiment of the present invention includes:
s101: whatever form of user performance simulation calculation conditions, the user performance simulation calculation conditions can be finally recorded and transmitted in the form of task data through a task file; no matter what type of machine, pneumatic, thrust, characteristic and other data, the data need to be organized according to a specific structure;
s102: after the calculation kernel is started, the calculation kernel preferentially finishes the work of reading the model data from the model database, and the influence of frequent reading operation in the middle of simulation calculation on the calculation efficiency is prevented; the computing kernel checks the integrity of the task file, so that the program is prevented from being crashed; the computing kernel checks the integrity of the task data block, and prevents the program from crashing caused by the integrity;
s103: checking the correctness of the read machine type database according to the key data in the task file to prevent the result from being mismatched; the computing kernel checks the data type and the data integrity of the SCAP standard task, so that the operation exception caused by the data type and the data integrity is prevented; the computing kernel checks the data type and the data integrity of the non-standard task, so that the operation exception caused by the data type and the data integrity is prevented; the calculation inner core standardizes the data items with physical meanings such as length, height, speed, weight and the like in the task data in units so as to meet the requirement of unified physical units of simulation calculation and prevent abnormal operation and result errors;
S104: calculating a data item of which the inner core is standardized to check to prevent physical overrun and logic overrun; the calculation kernel analyzes the algorithm function matched with the current task, and starts the corresponding algorithm function to perform simulation calculation; the computing kernel simultaneously starts monitoring, records computing progress information and abnormal information, writes the computing progress information and the abnormal information into a log file, and stops computing when receiving a stop signal; converting multidimensional data generated by the calculation kernel when the calculation is normally finished into two-dimensional data, and preparing for outputting;
s105: when the text is output, the computing kernel organizes a plurality of data according to the output items preset by the program or appointed by the task; when the text is output, the calculation kernel converts the standardized data according to a unit system preset by a program or specified by a task; writing the result file into the calculation kernel according to the text format specified by the user;
s106: when the table is output, the calculation inner core defines, positions and assembles each unit of the table; when the table is output, the calculation inner core assigns values to each unit of the table; the calculation kernel writes the result file according to a table format specified by a user; calculating a kernel overloading task file, and adding input to a result file to ensure that the result file has input and output contents at the same time to form a unique identification degree; and the calculation kernel writes the check code, the version number and the calculation time information into the result file, and then stands by or ends.
In S101 provided by the embodiment of the present invention, the task data includes: the texts, the numerical values and the enumeration items are organized according to a form of a aircraft performance computing standard interface (SCAP) of the International aviation protocol; the compute kernel SCAP interface plan is shown in fig. 6.
In S101 provided by the embodiment of the present invention, the aerodynamic data organization method uses a flap, an undercarriage, a spoiler, and a center of gravity as main keywords, and uses an air pressure altitude, a temperature, and a mach number as sub keywords.
Example 1: constraint control mechanism in preprocessing
The constraint control mechanism can perform customized input on the name, type, default value, value range, unit system, control interaction relation and the like of the user interface control through the customized grammar, can more conveniently realize the relevant logical inspection and boundary inspection of regulations and manuals, and improves the conformity and consistency of output materials in the development stage. The design of the constraint control mechanism is shown in fig. 7, and the constraint rule for limiting the control is shown in fig. 8.
Example 2: interface mechanism in preprocessing
The interface mechanism is divided according to the performance simulation calculation service functions, and comprises the following steps: a takeoff calculation interface, a landing calculation interface, an entering and leaving field calculation interface, an air route calculation interface, an airport database interface and the like. The computing task interface list (local) is shown in fig. 9.
Example 3: a real takeoff analysis calculates mission inputs as shown in fig. 10.
Example 4: a real takeoff analysis calculates the mission results as shown in fig. 11.
Example 5: application scene of real computing task
By adopting the framework method, the obtained calculation output result can very conveniently support the development of batch test work, a result set is generated according to a pre-constructed calculation task set, and a result standard set and a modified result comparison set can be quickly compared. The application proves that the method supports batch computing of multiple computing tasks and can further meet the cloud computing requirement. As shown in fig. 12.
It should be noted that the embodiments of the present invention can be realized by hardware, software, or a combination of software and hardware. The hardware portion may be implemented using dedicated logic; the software portions may be stored in a memory and executed by a suitable instruction execution system, such as a microprocessor or specially designed hardware. Those skilled in the art will appreciate that the apparatus and methods described above may be implemented using computer executable instructions and/or embodied in processor control code, such code being provided on a carrier medium such as a disk, CD-or DVD-ROM, programmable memory such as read only memory (firmware), or a data carrier such as an optical or electronic signal carrier, for example. The apparatus and its modules of the present invention may be implemented by hardware circuits such as very large scale integrated circuits or gate arrays, semiconductors such as logic chips, transistors, or programmable hardware devices such as field programmable gate arrays, programmable logic devices, etc., or by software executed by various types of processors, or by a combination of hardware circuits and software, e.g., firmware.
The above description is only for the purpose of illustrating the present invention and the appended claims are not to be construed as limiting the scope of the invention, which is intended to cover all modifications, equivalents and improvements that are within the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. A method for pre-processing and post-processing an aircraft performance software calculation kernel is characterized by comprising the following steps:
firstly, recording and transmitting the user performance simulation calculation conditions in any form through a task file in a task data form; the pneumatic, thrust and characteristic data of any machine type are organized by a specific structure;
the calculation kernel preferentially finishes the work of reading the model data from the model database after being started so as to prevent frequent reading operation in the middle of simulation calculation from influencing calculation efficiency; the computing kernel checks the integrity of the task file to prevent the program from crashing; the computing kernel checks the integrity of the task data block to prevent the program from crashing caused by the integrity;
checking the correctness of the read model database according to the key data in the task file to prevent the result from being mismatched; the computing kernel checks the data type and the data integrity of the SCAP standard task to prevent operation exception caused by the data type and the data integrity; the computing kernel checks the data type and the data integrity of the non-standard task to prevent operation exception caused by the checking; the calculation inner core carries out unit standardization on data items with physical meanings of length, height, speed and weight in the task data so as to meet the requirement of simulating and calculating a unified physical unit and prevent abnormal operation and result errors;
Step four, calculating the data items of the internal core after the unit standardization to check so as to prevent physical overrun and logic overrun; the calculation kernel analyzes the algorithm function matched with the current task, and starts the corresponding algorithm function to perform simulation calculation; the computing kernel simultaneously starts monitoring, records computing progress information and abnormal information, writes the computing progress information and the abnormal information into a log file, and stops computing when receiving a stop signal; converting multidimensional data generated by the calculation kernel when the calculation is normally finished into two-dimensional data, and preparing for outputting;
step five, when the text is output, the calculation kernel organizes a plurality of data according to the output items preset by the program or appointed by the task; when the text is output, the calculation kernel converts the standardized data according to a unit system preset by a program or specified by a task; writing the result file into the calculation kernel according to the text format specified by the user;
step six, when the table is output, calculating an inner core to define, position and assemble each unit of the table; when the table is output, the calculation inner core assigns values to each unit of the table; the calculation kernel writes the result file according to a table format specified by a user; calculating a kernel overloading task file, and adding input to a result file to ensure that the result file has input and output contents at the same time to form a unique identification degree; and the calculation kernel writes the check code, the version number and the calculation time information into the result file, and then stands by or ends.
2. An aircraft performance software computing kernel preprocessing method as claimed in claim 1 wherein in said first step, the task data comprises: texts, numerical values and enumerated items are all organized according to the form of an aircraft performance calculation standard interface of the international aviation protocol.
3. The method for pre-processing and post-processing the aircraft performance software computing kernel as claimed in claim 1, wherein in the first step, the aerodynamic data is organized in a way that a flap, a landing gear, a spoiler and a center of gravity are used as main keywords, and an air pressure altitude, a temperature and a Mach number are used as secondary keywords.
4. An aircraft performance software computation kernel pre-post processing system for implementing the aircraft performance software computation kernel pre-post processing method according to any one of claims 1 to 3, wherein the aircraft performance software computation kernel pre-post processing system comprises:
the system comprises a preprocessing module, a performance service calculation module and a post-processing module;
a pre-processing module comprising: the system comprises a fixed data reading layer, a fixed data extraction layer, an input parameter reading layer, an input parameter extraction layer, an input parameter integrity verification layer, a regulation and manual conformance inspection layer and an input parameter unit conversion layer;
A post-processing module comprising: the system comprises a calculation exception module, a calculation progress module, a calculation suspension module, a data dimension conversion module, a data block output module, a table output module, a user unit system restoration module and a task consistency check module.
5. An aircraft performance software computing kernel pre-post processing system as defined in claim 4, wherein the fixed data reading layer and the fixed data extraction layer complete reading of pneumatic data, thrust data, feature data and the like, and perform appropriate judgment by combining models in input parameters, thereby reading a matched model database; and reading the encrypted model database into the memory after decrypting the encrypted model database.
6. The aircraft performance software computing kernel preprocessing system as claimed in claim 4, wherein said input parameter reading layer and input parameter extracting layer complete the recognition and analysis of the computing task file, read the atmospheric environment conditions, airport conditions, aircraft conditions, engine conditions, and computing conditions set by the user into the memory in one time according to the unified format and method, and call the corresponding service algorithm module for computation by combining the performance computing service in the input parameters after the preprocessing such as format verification, integrity verification, conformance check, user unit system to standard unit system conversion, etc.
7. An aircraft performance software computing kernel pre-post processing system as defined in claim 4, wherein the computing exception module, after pre-processing, may still have improper and non-logical conditions causing simulation computing errors, computing overrun, and illegal results of the service algorithm module, stacks and outputs possible error prompt or error information to the log file;
the calculation progress module is used for stacking and storing the relative condition of the current calculation progress state and the estimated calculation total amount through progress information and outputting the relative condition to a progress file in the execution process of the business algorithm module;
the calculation stopping module stops the current calculation flow in real time and reasonably ends the program according to the user instruction in the simulation calculation process of the service algorithm module, so that no reasonable way is available for control when the simulation calculation is falsely dead or the calculation is abandoned;
the data dimension conversion module is used for completing the local or global storage requirement of data in calculation only by using the multidimensional array as a business algorithm module, and when the result data is output to a result file, the result data is converted into a two-dimensional array so as to meet the requirement of reading by a user.
8. An aircraft performance software computational kernel pre-post processing system as defined in claim 4 wherein said data block output module is an output means for organizing and presenting data directly in text form in an ordered manner in conventional engineering formats of points, curves, grids, and sequences;
The table output module is an output mode which directly organizes and displays the data in a text form according to the special format of the aircraft performance professional chart;
the user unit system restoring module restores the data which is calculated by using the standard unit system to the user set unit system in the task file according to the types of distance, height, speed and weight;
the task consistency check module identifies and prevents the inconsistency of the result generated by the computing kernel and the computing task, which causes the damage of the conformity of the result and the computing kernel, and generates check codes according to the task file and stores the check codes in the result file, so as to achieve the consistency check of input and output.
9. A program storage medium for receiving user input, the stored computer program causing an electronic device to execute the method of pre-processing and post-processing an aircraft performance software computing kernel according to any one of claims 1 to 3, comprising the steps of:
firstly, recording and transmitting the user performance simulation calculation conditions in any form through a task file; the pneumatic, thrust and characteristic data of any machine type are organized by a specific structure;
the second step, the calculation kernel preferentially finishes the work of reading the model data from the model database after being started, so that the influence of frequent reading operation in the middle of simulation calculation on the calculation efficiency is prevented; the computing kernel checks the integrity of the task file to prevent program crash caused by the integrity; the computing kernel checks the integrity of the task data block to prevent the program from crashing caused by the integrity;
Checking the correctness of the read model database according to the key data in the task file to prevent the result from being mismatched; the computing kernel checks the data type and the data integrity of the SCAP standard task to prevent abnormal operation caused by the data type and the data integrity; the computing kernel checks the data type and the data integrity of the nonstandard task to prevent operation exception caused by the data type and the data integrity; the calculation inner core carries out unit standardization on data items with physical meanings of length, height, speed and weight in the task data so as to meet the requirement of simulating and calculating a unified physical unit and prevent abnormal operation and result errors;
step four, calculating the data items of the internal check unit after standardization to check so as to prevent physical overrun and logic overrun; the calculation kernel analyzes the algorithm function matched with the current task, and starts the corresponding algorithm function to perform simulation calculation; the computing kernel simultaneously starts monitoring, records computing progress information and abnormal information, writes the computing progress information and the abnormal information into a log file, and stops computing when receiving a stop signal; converting multidimensional data generated by the calculation kernel when the calculation is normally completed into two-dimensional data, and preparing for outputting;
step five, when the text is output, the calculation kernel organizes a plurality of data according to the output items preset by the program or appointed by the task; when the text is output, the calculation kernel converts the standardized data according to a unit system preset by a program or specified by a task; writing the result file into the calculation kernel according to the text format specified by the user;
Step six, when the table is output, calculating an inner core to define, position and assemble each unit of the table; when the table is output, the calculation inner core assigns values to each unit of the table; the calculation kernel writes the result file according to a table format specified by a user; calculating a kernel overloading task file, and adding input to a result file to ensure that the result file has input and output contents at the same time to form a unique identification degree; and the calculation kernel writes the check code, the version number and the calculation time information into the result file, and then stands by or ends.
10. A computer arrangement, characterized in that the computer arrangement comprises a memory and a processor, the memory storing a computer program which, when executed by the processor, causes the processor to carry out the steps of the aircraft performance software computation kernel pre-post processing method as claimed in claims 1-3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210391819.XA CN114756916B (en) | 2022-04-14 | 2022-04-14 | Aircraft performance software computation kernel pre-post processing system, method, medium and device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210391819.XA CN114756916B (en) | 2022-04-14 | 2022-04-14 | Aircraft performance software computation kernel pre-post processing system, method, medium and device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114756916A true CN114756916A (en) | 2022-07-15 |
| CN114756916B CN114756916B (en) | 2023-01-31 |
Family
ID=82332068
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210391819.XA Active CN114756916B (en) | 2022-04-14 | 2022-04-14 | Aircraft performance software computation kernel pre-post processing system, method, medium and device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114756916B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105162864A (en) * | 2015-09-14 | 2015-12-16 | 深圳市森普航科电子有限公司 | Aircraft performance calculating method and device |
| CN108108534A (en) * | 2017-12-06 | 2018-06-01 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of aircraft parameter computation model defines method |
| US20190164440A1 (en) * | 2017-11-24 | 2019-05-30 | Dassault Aviation | Aircraft mission computing system comprising a mission deck |
| CN110956334A (en) * | 2019-12-10 | 2020-04-03 | 中国民航科学技术研究院 | Aircraft takeoff performance optimization method and system based on ultra-long obstacle crossing path |
-
2022
- 2022-04-14 CN CN202210391819.XA patent/CN114756916B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105162864A (en) * | 2015-09-14 | 2015-12-16 | 深圳市森普航科电子有限公司 | Aircraft performance calculating method and device |
| US20190164440A1 (en) * | 2017-11-24 | 2019-05-30 | Dassault Aviation | Aircraft mission computing system comprising a mission deck |
| CN108108534A (en) * | 2017-12-06 | 2018-06-01 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of aircraft parameter computation model defines method |
| CN110956334A (en) * | 2019-12-10 | 2020-04-03 | 中国民航科学技术研究院 | Aircraft takeoff performance optimization method and system based on ultra-long obstacle crossing path |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114756916B (en) | 2023-01-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Prisaznuk | ARINC 653 role in integrated modular avionics (IMA) | |
| CN101750978B (en) | Open platform for supporting design, verification and validation of telex flight control system | |
| US20090254403A1 (en) | Line maintenance manager | |
| CA2768445C (en) | Process for development of monitoring tools | |
| US11829358B2 (en) | Systems and methods for natural language queries | |
| US11754995B2 (en) | Industrial internet of things for identifying and processing manufacturing problems, control methods, and storage medium | |
| CN112416369B (en) | Intelligent deployment method oriented to heterogeneous mixed environment | |
| CN108874678A (en) | A kind of automatic test approach and device of intelligent program | |
| CN111830861B (en) | Deduction method and system for spacecraft task planning | |
| US20220365518A1 (en) | Development of a product using a process control plan digital twin | |
| CN109657379A (en) | A kind of model aircraft simulation and verification platform | |
| CN116362837A (en) | Medical instrument cloud platform order management system | |
| CN114756916B (en) | Aircraft performance software computation kernel pre-post processing system, method, medium and device | |
| CN112446601B (en) | Method and system for diagnosing data of uncomputable area | |
| Pozin et al. | Models in performance testing | |
| Marques et al. | Verification Scenarios of Onboard Databases under the RTCA DO-178C and the RTCA DO-200B | |
| US20170372237A1 (en) | System and method for producing models for asset management from requirements | |
| CN111752806A (en) | Method for acquiring IO (input/output) indexes of virtual disk in cloud environment | |
| CN112016285A (en) | Logistics information processing method and system | |
| US10429843B1 (en) | Parametrizable automatic piloting system intended for an aircraft | |
| CN115019595A (en) | Avionics simulation I/O management-based training simulator implementation method and system | |
| CN114895883A (en) | Electric power industry informatization object model management platform system and control method thereof | |
| CN112559359B (en) | S-based 2 ML security critical system analysis and verification method | |
| Brovkina et al. | Graph-based data model for assembly-specific capability description for fully automated assembly line design | |
| CN114138442A (en) | Asynchronous task scheduling execution method, system and server |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |