CN114841676A - Method for batch computing of multi-model performance chart data based on SCAP (Supervisory control and protocol) - Google Patents

Abstract

The invention discloses a method for batch computing multi-model performance chart data based on an SCAP protocol, which comprises the following steps: configuring model parameter data based on the SCAP protocol; generating a calculation input file according to the configured model parameter data based on the SCAP protocol; calling a kernel file of manufacturer performance calculation software by combining the calculation input file to obtain output result data; verifying the consistency of the output result data and the result data of the manufacturer performance calculation software; configuring a performance chart calculation template according to the model; generating a calculation input file according to a configured performance chart calculation template based on an SCAP protocol; calling a kernel file of manufacturer performance computing software to obtain output result data; analyzing the output result data and generating performance chart data; the method is applied to the manufacturing work of the takeoff and landing performance chart data of the airline company, can reduce the work load, reduce the human error rate and improve the aviation operation safety.

Description

Method for batch computing of multi-model performance chart data based on SCAP (Supervisory control and protocol)

Technical Field

The invention relates to the technical field of airplane performance calculation, in particular to a method for batch calculation of multi-model performance chart data based on a SCAP protocol.

Background

With the gradual expansion of the civil aviation flight volume, the flight safety becomes extremely important, the civil aviation flight safety not only concerns the life and property safety of passengers, but also concerns the future development of the whole civil aviation industry, and simultaneously reflects the national image of China.

The performance calculation software refers to the calculation software which is used by an aircraft manufacturer to calculate and determine the key parameters of the aircraft in each stage, such as weight, speed, height, oil consumption, distance and the like, according to specific and approved mathematical models for the performance data of the aircraft in different stages of takeoff, climbing, cruising, descending, waiting and landing, and is beneficial to obtaining more accurate aircraft performance data during the operation of a unit, and meanwhile, the calculation result is also one of the main dimensions for evaluating the performance of the aircraft in each stage.

At present, the mainstream airplane models in China are airbus, boeing and Chinese business airplane models, and the performance calculation software corresponding to the airplane models of each airplane manufacturer is respectively an airbus PEP, a boeing BPS, a PET and a Chinese business flight PES. Therefore, the reality of coexistence of multiple models, multiple manufacturers and multiple performance calculation software is common in all large airlines.

In the daily data maintenance process, performance engineers need to install performance calculation software provided by manufacturers at a computer terminal and maintain airport basic information of airports, runways and obstacles in the performance engineers, the repetitive workload is large, the risk of human errors exists, and the performance engineers need to provide performance chart data to support flight operation. The performance chart data refers to a performance analysis table which is required by an airline to prepare a running model for taking off at the airport before each flight is released. The performance analysis table gives the information of the temperature condition, the takeoff form, the takeoff weight under the QNH correction condition and the V1, VR and V2 speed of the running machine model on each airport runway in detail, provides data for the machine set for controlling the total takeoff weight and inputs the data into an airplane Flight Management Computer (FMC) for preparation before flight. The performance chart data is generally obtained by manual calculation according to the set wind, temperature, corrected air pressure and relevant parameter conditions of airplane performance by using performance calculation software provided by various manufacturers. The airport runway data in the performance chart is periodic data updated every 28 days, and a performance engineer needs to update the data periodically, which means that the performance chart data information of part of airports needs to be updated every 28 days. However, the performance calculation software provided by each manufacturer does not provide a function of calculating performance chart data in batches, and the data formats of the generated performance charts are different for different performance calculation software used by each aircraft manufacturer, so that when the performance chart data is manufactured, performance calculation conditions of different models need to be configured in the performance calculation software provided by the manufacturer in sequence and calculated airport basic information needs to be input to generate the performance chart data.

Disclosure of Invention

The invention provides a method for batch computing multi-model performance chart data based on an SCAP (supervisory control and protocol) protocol, aiming at solving the problem that the performance chart data cannot be computed in batch due to the fact that software is computed in multiple models, multiple manufacturers and multiple performances at present. Particularly for airlines with multiple models that require large volumes of performance chart data to be computed every 28 days of airport data cycles updated. The method is applied to the work of making performance chart data of different stages such as take-off or landing by performance departments of each navigation department, can reduce the work load of performance engineers, improve the production efficiency, reduce the hidden danger of human errors and promote the aviation safety. The technical scheme of the invention comprises the following steps:

step 1: configuring model parameter data based on an SCAP protocol;

step 2: generating a calculation input file according to the configured model parameter data based on the SCAP protocol;

and step 3: calling a kernel file of manufacturer performance calculation software by combining the calculation input file to obtain output result data;

and 4, step 4: verifying the consistency of the output result data and the result data of the manufacturer performance calculation software;

and 5: configuring a performance chart calculation template according to the model;

step 6: generating a calculation input file according to a configured performance chart calculation template based on an SCAP protocol;

and 7: calling a kernel file of manufacturer performance computing software to obtain output result data;

and 8: and analyzing the output result data and generating performance chart data.

Further, step 1: configuring model parameter data based on SCAP protocol, comprising the following steps:

step 1-1: and respectively configuring performance parameter data of the air passenger, the Boeing and the Chinese commercial aircraft type in the takeoff and landing stages based on the SCAP protocol. The performance parameter data comprises parameter names and parameter default value configurations of a POPT class, a CONF class, a UNIT class, an XMET class, a RWDD class, an OBSD class and an FPTD class;

step 1-2: and respectively configuring performance parameter selectable data of the take-off and landing stages of the air passenger, the Boeing and Chinese business aircraft models based on the SCAP protocol. The performance parameter selectable data comprises parameter selectable values and code information of a POPT class, a CONF class, a UNIT class, an XMET class, a RWDD class, an OBSD class and an FPTD class;

step 1-3: and respectively configuring the performance parameter association data of the air passenger, the boeing and the Chinese commercial aircraft type in the takeoff and landing stages based on the SCAP protocol. Wherein the performance parameter association data comprises the association of performance parameter options and the maintenance of association values.

Further, step 2: generating a calculation input file according to the configured model parameter data based on the SCAP protocol, comprising the following steps:

step 2-1: and extracting a database and unit identification information of the model based on the model parameter data configured by the SCAP protocol. The model database is mainly formed by adding numbers to the beginning of letters, for example, the model database of 737-800W (24K) is D02604, and unit identification information is information of brake type, rotating speed standard and engine type;

step 2-2: extracting option value information of a road surface condition, a flap, an air conditioner, anti-icing and reverse thrust based on model parameter data configured by an SCAP protocol;

step 2-3: configuring information of units of four codes, name, elevation and height distance of the airport based on the SCAP protocol;

step 2-4: configuring the distance of the runway and the information of the obstacles based on the SCAP protocol;

step 2-5: configuring the calculated wind and temperature information based on the model parameter data configured by the SCAP protocol;

step 2-6: configuring an output format and calculating key word information based on the model parameter data configured by the SCAP protocol;

step 2-7: and generating a calculation input file according to the configuration information combination.

Further, step 3: the method for obtaining the output result data by calling the kernel file of the manufacturer performance calculation software in combination with the calculation input file comprises the following steps:

step 3-1: preparing kernel files of performance computing software of a manufacturer, wherein the kernel files comprise a model database file, an application program, a dynamic link library file, an input file and a configuration file;

step 3-2: using an application program or executing a method defined by a dynamic link library file and calling a kernel file of manufacturer performance calculation software to generate an output result file and a log file;

step 3-3: and checking whether the log file has error information or not, and if not, indicating that the calculation is successful. If error information exists, checking whether the model parameter data configured in the step 1 is correct according to the error information, checking the model parameter data according to technical document parameters provided by manufacturers based on an SCAP protocol, and executing again according to the step 1;

step 3-4: and analyzing the output result file into output result data by using a regular expression, wherein the output result information comprises output result information of the takeoff and landing stages. Calculating the takeoff stage, wherein the takeoff stage comprises the steps of outputting result information including maximum takeoff weight limit value, V1 speed, V2 speed and VR speed data; and the landing stage calculation comprises outputting result information as maximum landing weight limit and landing distance data.

Further, step 4: the consistency of the result of the manufacturer performance calculation software and the output result data is verified, and the method comprises the following steps:

step 4-1: selecting the same airport runway information, and verifying and comparing whether the output result data is consistent with the output result data of manufacturer performance calculation software or not by using the calculation conditions formed by fixed wind speed, temperature, flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data;

step 4-2: selecting different airport runway information, and verifying and comparing whether output result data is consistent with output result data of manufacturer performance calculation software or not by using calculation conditions formed by fixed wind speed, temperature, flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data;

step 4-3: selecting the same airport runway information, and verifying and comparing whether output result data is consistent with output result data of manufacturer performance calculation software or not according to calculation conditions which are respectively obtained by different flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data under the fixed wind speed and temperature conditions;

step 4-4: and selecting the same airport runway information, and verifying and comparing whether the output result data is consistent with the output result data of manufacturer performance calculation software or not by using fixed flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data and calculation conditions which are respectively obtained according to different wind speeds and temperature compositions.

Further, step 5: the method for calculating the template according to the model configuration performance chart comprises the following steps:

step 5-1: respectively creating performance chart calculation templates of take-off and landing stages of different models;

step 5-2: configuring a temperature data range of a performance chart calculation template in a take-off and landing stage;

step 5-3: configuring a wind data range of a performance chart calculation template in the take-off and landing stages;

step 5-4: configuring the road surface condition option data of a performance chart calculation template in the take-off and landing stages;

step 5-5: configuring flap option data of a performance chart calculation template in the take-off and landing stages;

and 5-6: configuring air conditioner option data of a performance chart calculation template in the take-off and landing stages;

and 5-7: configuring anti-icing option data of a performance chart calculation template in the take-off and landing stages;

and 5-8: and configuring a performance chart in the takeoff and landing phases to calculate reverse thrust option data of the template.

Further, step 6: generating a calculation input file according to a configured performance chart calculation template based on an SCAP protocol, comprising the following steps of:

step 6-1: extracting a database and unit identification data of the model based on model parameter data configured by an SCAP protocol;

step 6-2: configuring data of units of four codes, name, elevation and height distance of the airport based on the SCAP protocol;

step 6-3: configuring data of the distance and the obstacles of the runway based on the SCAP protocol;

step 6-4: extracting the performance chart configured in the step 5 to calculate the parameter value data of the pavement condition value, the flap, the air conditioner, the anti-icing option and the reverse thrust option of the template;

step 6-5: extracting wind and temperature data of the performance chart calculation template configured in the step 5;

step 6-6: configuring and calculating an output format and calculating keyword data in an input file based on the SCAP;

step 6-7: and generating a calculation input file according to the configuration information combination.

Further, step 7: the method for obtaining the output result data by calling the kernel file of the manufacturer performance computing software comprises the following steps:

step 7-1: preparing kernel files of performance computing software of manufacturers, wherein the kernel files comprise model database files, application programs, dynamic link library files, input files and configuration files;

step 7-2: using an application program or executing a method defined by a dynamic link library file and calling a kernel file of manufacturer performance calculation software to generate an output result file and a log file;

and 7-3: and checking whether the log file has error information or not, and if not, indicating that the calculation is successful. If the error information exists, checking whether the model parameter data configured in the step 1 is correct according to the error information, checking the model parameter data according to technical document parameters provided by manufacturers based on the SCAP protocol, and executing again according to the step 1.

Further, step 8: analyzing the output result data and generating performance chart data, comprising the following steps:

step 8-1: matching output result data according to key word key values in technical documents of manufacturer performance calculation software, and intercepting information in output results by a splitting method of a regular expression;

step 8-2: and converting the data part of the performance chart in the intercepted information into a PDF file format for storage.

The invention has the following advantages:

the method can realize batch calculation of multi-model performance chart data, effectively improve the production efficiency of the performance chart data, reduce the workload of performance engineers, reduce the hidden danger of human errors and promote aviation safety.

Drawings

Fig. 1 is a flowchart of a method for batch computing multi-model performance chart data based on a SCAP protocol according to an embodiment of the present invention.

FIG. 2 is a diagram illustrating an embodiment of the present invention invoking a kernel file of vendor performance calculation software to obtain output result data.

Fig. 3 is performance chart data for converting output result data into a PDF file format according to 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 following detailed description is provided with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

At present, each navigation department generally has the actual situation of coexistence of multiple models, multiple manufacturers and multiple performance calculation software, and performance parameter standards of different aircraft performance calculation software provided by each aircraft manufacturer have great difference, so that the data of the multiple models of performance charts cannot be calculated in batch, the manual calculation workload is large, the risk of artificial calculation errors exists, and the operation safety of aviation is damaged.

Based on the method, the multi-model performance chart data can be calculated in batches based on the SCAP, the artificial workload is reduced, the accuracy, the reliability and the safety of the data are improved, and the potential safety hazard of aviation operation is reduced.

Taking a calculation process of performance chart data of a boeing machine type take-off stage as an example, as shown in fig. 1, a method for batch calculation of performance chart data of the boeing machine type take-off stage based on an SCAP protocol in the embodiment of the present invention mainly includes the following steps:

step 1: configuring model parameter data based on the SCAP protocol;

step 2: generating a calculation input file according to the configured model parameter data based on the SCAP protocol;

and step 3: calling a kernel file of manufacturer performance calculation software by combining the calculation input file to obtain output result data;

and 4, step 4: verifying the consistency of the output result data and the result data of the manufacturer performance calculation software;

and 5: configuring a performance chart calculation template according to the model;

step 6: generating a calculation input file according to a configured performance chart calculation template based on an SCAP protocol;

and 7: calling a kernel file of manufacturer performance computing software to obtain output result data;

and 8: and analyzing the output result data and generating performance chart data.

Step 1, configuring model parameter data based on the SCAP protocol, comprising:

step 1-1: parameter data of a boeing machine type takeoff stage are configured based on a SCAP protocol, and the parameter data are mainly based on STAS technical documents provided by boeing, wherein the documents specify information such as POPT, CONF, UNIT, RWDD, XMET and OBSD.

Step 1-2: the method comprises the steps of configuring selection parameter items of the parameters of the boeing machine type takeoff stage based on the SCAP protocol, and maintaining selection parameter item data of corresponding POPT types, CONF types, UNIT types, RWDD types, XMET types and OBSD types.

Step 1-3: and configuring the associated item value of the selected parameter item of the performance parameter of the boeing machine type based on the SCAP protocol, wherein the associated item value maintenance comprises the associated item value maintenance of the selected parameter item corresponding to POPT type, CONF type, UNIT type, RYD type, XMET type, OBSD type and keyword type.

Step 2, generating a calculation input file according to the configured model parameter data based on the SCAP protocol, wherein the calculation input file comprises the following steps:

step 2-1: and configuring information such as a database, unit identifiers, output formats, engine numbers, temperature identifiers, weight units and the like in the input file based on the SCAP protocol. The method comprises the following specific steps:

ACMDBI=D02604

ACTYPE=737-800

ALTUNT=M

BRAKES=CAT_N

CERTIF=FAA-SCAP

DEPTHU=MM

DESCRIBE='DRY RUNWAY'

DISTU=M

ENGTYP=CFM56-7B24

LINES PER PAGE=80

MMID=BTM

REVNBR=S012

TMPUNT=C

WTUNIT=KG

OUTPUT OPTION WIND1。

step 2-2: and extracting option value information of the road surface condition, the flap, the air conditioner, the anti-icing and the reverse thrust based on the model parameter data configured by the SCAP protocol. The POPT, CONF, XMET and UNIT are included, and the configuration is as follows:

POPT(1)=0

POPT(2)=0

POPT(4)=1

POPT(5)=0

POPT(6)=9.E20

POPT(7)=0

POPT(8)=0

POPT(9)=9.E20

POPT(11)=1

POPT(12)=20

POPT(13)=36

POPT(14)=0

POPT(15)=9.E20

POPT(16)=9.E20

POPT(17)=9.E20

POPT(18)=0

POPT(19)=122

POPT(20)=0

POPT(21)=7

POPT(22)=9.E20

POPT(23)=9.E20

POPT(24)=77791

POPT(25)=0

POPT(26)=5

POPT(27)=0

POPT(28)=9.E20

POPT(29)=9.E20

POPT(30)=9.E20

CONF(1)=1

CONF(2)=9.E20

CONF(3)=5

CONF(4)=2

CONF(5)=0

CONF(6)=9.E20

CONF(7)=0

CONF(8)=1

CONF(9)=0

CONF(10)=9.E20

CONF(11)=9.E20

CONF(13)=9.E20

CONF(14)=9.E20

CONF(15)=9.E20

CONF(16)=225

CONF(17)=9.E20

CONF(18)=9.E20

CONF(19)=9.E20

CONF(20)=0

XMET(5)=1013.25

UNIT(6)=0

UNIT(8)=0。

step 2-3: and configuring information of units of four codes, name, elevation and height distance of the airport based on the SCAP protocol. The method comprises the following specific steps:

AIRPORT1

'ZBAA' 'CAPITAL' 'BEIJING,CHINA' 'MMLOLO' 36。

step 2-4: and configuring the distance of the runway and the information of the obstacles based on the SCAP protocol. The method comprises the following specific steps:

RWYS

'01' 1 3800.0 500.0 0.0 3800.0 0.18 0.18 0.18 4

9 900000 0

57 4030 0

50 2483 0

46 2759 0。

step 2-5: and configuring information of the calculated temperature and wind in the input file based on the SCAP protocol. The method comprises the following specific steps:

WINDS=0

TEMPS=12。

step 2-6: airport runway information is calculated based on selections in the SCAP protocol configuration input file. The method comprises the following specific steps:

SELECT RUNWAY ZBAA/01

CALC。

step 2-7: and generating a calculation input file according to the configuration information combination. The named compute input file is scapnp.

And step 3: the method for obtaining the output result data by calling the kernel file of the manufacturer performance calculation software in combination with the calculation input file comprises the following steps:

step 3-1: preparing the kernel files of the performance computing software of the manufacturer, including model database files, application programs, dynamic link library files, input files and configuration files. Specific files include STAS.exe, STAS.for, D02604.db2, D02604.db1, D02604.sif and the like.

Step 3-2: and generating an output result file and a log file by using an application program or a method defined by executing the dynamic link library file and calling a kernel file of the manufacturer performance computing software. And (3) preparing a kernel file for calculating the input file STASINP.in and the wave-phone type performance calculating software generated in the step (2), calling the kernel of the wave-phone type performance calculating software, and calculating to obtain an output file STASOUT and a log file STASERROR.txt.

Step 3-3: and checking whether the log file has error information or not, and if not, indicating that the calculation is successful. If the error information exists, checking whether the model parameter data configured in the step 1 is correct according to the error information, checking the model parameter data according to technical document parameters provided by manufacturers based on the SCAP protocol, and executing again according to the step 1. Firstly, checking whether the output log file contains STASERROR. txt, wherein ERROR information is generally represented by an ERROR keyword, and NOTE or partial WARNING is represented if the calculation is successful. And no error file exists in the output file, and display information is NOTE, wherein the display information is NOTE, the OBSTACLE number 1 is on the min V1 flight path, the information shows that the calculation success only prompts that the minimum V1 is limited by an Obstacle, and module warning information is displayed at the same time, but the information is only prompt information and does not represent calculation errors.

Step 3-4: and analyzing the output result file into output result data by using a regular expression, wherein the output result information comprises output result information of the takeoff and landing stages.

Calculating the data including the maximum takeoff weight limit value, the V1 speed, the V2 speed and the VR speed in the takeoff calculation step; and the landing stage calculation comprises outputting result information as maximum landing weight limit and landing distance data. And analyzing the corresponding output result information from the output file to be V1= 151.8V 2=157.3 VR =152.9, and the maximum takeoff weight limit value is 77791 KG.

And 4, step 4: verifying the consistency of the output result data and the result data of the manufacturer performance calculation software, comprising the following steps:

step 4-1: and selecting the same airport runway information, and verifying and comparing whether the output result data and the output result data of the manufacturer performance calculation software are in accordance with the data error range by using the calculation conditions formed by fixed wind speed, temperature, flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data.

Selecting a ZBAA airport 01 runway to use the calculation conditions of calm wind, 12 ℃, dry road surface, flap 05, air conditioner AUTO, ice release OFF and all reverse thrust work, and starting to calculate to obtain output result data.

The output result information of the zba airport 01 runway is V1= 151.8V 2=157.3 VR =152.9, the maximum takeoff weight limit value is 77791KG, the result information of the manufacturer performance calculation software PET calculation is V1= 151.8V 2=157.3 VR =152.9, and the maximum takeoff weight limit value is 77791 KG.

The compared output result data is consistent with the output result data of the manufacturer performance calculation software.

Step 4-2: and selecting different airport runway information, and verifying and comparing whether the output result data is consistent with the output result data of manufacturer performance calculation software or not by using calculation conditions formed by fixed wind speed, temperature, flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data.

Different airports and runway data are selected to participate in calculation, and a 01 runway of a ZBAA airport, an 11 runway of a ZLXN airport and a 02L runway of a ZUUU airport are selected to use a dry road surface, a flap 05, an air conditioner AUTO, an ice release OFF, all reverse thrust working conditions and a temperature of 12 ℃ calm wind to carry out calculation to obtain output result data.

The output result information of the zba airport 01 runway is V1= 151.8V 2=157.3 VR =152.9, the maximum takeoff weight limit value is 77791KG, the result information of the manufacturer performance calculation software PET calculation is V1= 151.8V 2=157.3 VR =152.9, and the maximum takeoff weight limit value is 77791 KG.

The output result information of the ZLXN airport 01 runway is V1= 141V 2=146.5 VR =142.6, the maximum takeoff weight limit value is 66438KG, the result information of the vendor performance calculation software PET calculation is V1= 141V 2=146.5 VR =142.6, and the maximum takeoff weight limit value is 66438 KG.

The output result information of the ZUUU airport 02L runway is V1= 150.4V 2=155.6 VR =151.4, the maximum takeoff weight limit value is 75987KG, the result information of the manufacturer performance calculation software PET calculation is V1= 150.4V 2=155.6 VR =151.4, and the maximum takeoff weight limit value is 75987 KG.

The compared output result data is consistent with the output result data of the manufacturer performance calculation software.

Step 4-3: and selecting the same airport runway information, and verifying and comparing whether the output result data is consistent with the output result data of manufacturer performance calculation software or not according to calculation conditions which are respectively obtained by different flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data under the fixed wind speed and temperature conditions.

Selecting a ZBAA airport 01 runway, using dead wind, 12 ℃, and respectively carrying out calculation verification by combining 32 calculation conditions with the calculation conditions of dry and wet pavement options, flap options of 01 and 05, AUTO and OFF air conditioners, OFF and ON ice-releasing options and working and non-working reverse thrust options, and verifying whether the comparison output result data is consistent with the output result data of manufacturer performance calculation software.

Because the number of the combinations is too large, the embodiment only shows three combinations to calculate, verify and compare whether the output result data is consistent with the output result data of the manufacturer performance calculation software.

Condition 1: the method comprises the following steps of quiet wind, 12 ℃, dry road surface, flap 01, air conditioner AUTO, ice prevention OFF and reverse thrust;

results 1: the output result information of the zba airport 01 runway is V1= 158V 2=163.2 VR =159.3, the maximum takeoff weight limit value is 77791KG, the result information of the manufacturer performance calculation software PET calculation is V1= 151.8V 2=157.3 VR =152.9, and the maximum takeoff weight limit value is 77791 KG.

Condition 2: calm wind, 12 ℃, wet road surface, flap 05, air conditioner AUTO, anti-icing OFF and reverse thrust work;

results 2: the output result information of the zbcaa airport 01 runway is V1= 145.4V 2=157.3 VR =152.9, the maximum takeoff weight limit value is 77791KG, the result information of the manufacturer performance calculation software PET calculation is V1= 145.4V 2=157.3 VR =152.9, and the maximum takeoff weight limit value is 77791 KG.

Condition 3: the method comprises the following steps of working in a manner of calm wind, 12 ℃, dry road surface, flap 05, air conditioner AUTO, anti-icing OFF and reverse thrust;

results 3: the output result information of the zba airport 01 runway is V1= 151.8V 2=157.3 VR =152.9, the maximum takeoff weight limit value is 77791KG, the result information of the manufacturer performance calculation software PET calculation is V1= 151.8V 2=157.3 VR =152.9, and the maximum takeoff weight limit value is 77791 KG.

The compared output result data is consistent with the output result data of the manufacturer performance calculation software.

Step 4-4: and selecting the same airport runway information, and verifying and comparing whether the output result data is consistent with the output result data of manufacturer performance calculation software or not by using fixed flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data and calculation conditions which are respectively obtained according to different wind speeds and temperature compositions.

Selecting a ZBAA airport 01 runway by using a dry road surface, a flap 05, an air conditioner AUTO, an ice releasing OFF and all reverse-thrust works, selecting the dry road surface, the flap 05, the air conditioner AUTO, the ice releasing OFF and all reverse-thrust works, respectively using calculation conditions of-10 KT, 0KT and 10KT of wind speed, and-5 ℃,0 ℃, 5 ℃,10 ℃, 12 ℃, 14 ℃, 16 ℃, 18 ℃, 20 ℃, 22 ℃, 24 ℃, 26 ℃, 28 ℃ and 30 ℃ of temperature, respectively carrying out calculation verification by combining 42 calculation conditions, and verifying whether the comparison output result data is consistent with the output result data of manufacturer performance calculation software.

Because the number of the combinations is too large, the embodiment only shows three combinations to calculate, verify and compare whether the output result data is consistent with the output result data of the manufacturer performance calculation software.

Condition 1: top wind-10 KT, 12 ℃, dry road surface, flap 05, air conditioner AUTO, ice releasing OFF and all reverse thrust work;

results 1: the output result information of the zba airport 01 runway is V1= 149.8V 2=156.4 VR =151.8, the maximum takeoff weight limit value is 76689KG, the result information of the manufacturer performance calculation software PET calculation is V1= 149.8V 2=156.4 VR =151.8, and the maximum takeoff weight limit value is 76689 KG.

Condition 2: calm wind, 26 ℃, dry road surface, flap 05, air conditioner AUTO, ice releasing OFF and all reverse thrust work;

results 2: the output result information of the zba airport 01 runway is V1= 151.8V 2=157.3 VR =153, the maximum takeoff weight limit value is 77791KG, the result information of the manufacturer performance calculation software PET calculation is V1= 151.8V 2=157.3 VR =153, and the maximum takeoff weight limit value is 77791 KG.

Condition 3: the downwind is 10KT, the temperature is 30 ℃, the dry road surface, the flap 05, the air conditioner AUTO, the ice releasing OFF and all the reverse thrust work are carried out;

results 3: the output result information of the zba airport 01 runway is V1= 152V 2=157.2 VR =152.9, the maximum takeoff weight limit value is 77699KG, the result information of the vendor performance calculation software PET calculation is V1= 152V 2=157.2 VR =152.9, and the maximum takeoff weight limit value is 77699 KG.

The compared output result data is consistent with the output result data of the manufacturer performance calculation software.

And 5: the performance chart calculation template is configured according to the model, and comprises the following steps:

step 5-1: respectively creating performance chart calculation templates of takeoff stages of different models;

and respectively maintaining a configuration performance chart calculation template according to the type of the wave phone, wherein the template configuration items comprise calculated wind speed, temperature, flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data.

Step 5-2: configuring a temperature data range of a performance chart calculation template in a takeoff stage; the data ranges for the temperature configuration are as follows:

-5,0,5,10,12,14,16,18,20,22,24,26,28,30。

step 5-3: configuring a wind data range of a performance chart calculation template in a takeoff stage;

the range of wind data configuration is as follows:

wind: -10,0,10.

Step 5-4: configuring the performance chart of the takeoff stage to calculate the road surface condition option data of the template;

the pavement condition data is configured as follows:

road surface value: DRY.

Step 5-5: configuring a performance chart in a takeoff stage to calculate flap option data of a template;

the flap data configuration is as follows:

flap value: 05.

and 5-6: configuring air conditioner option data of a performance chart calculation template in a take-off stage;

the air conditioning data is configured as follows:

air conditioner value: AUTO.

And 5-7: configuring anti-icing option data of a performance chart calculation template in a take-off stage;

the anti-icing data is configured as follows:

anti-icing value: and OFF.

And 5-8: configuring reverse thrust option data of a performance chart calculation template in a takeoff stage;

the back-stepping data is configured as follows:

and (3) reverse deducing value: all the reverse thrusts work.

Step 6: generating a calculation input file according to a configured performance chart calculation template based on an SCAP protocol, wherein the method comprises the following steps:

step 6-1: configuring information such as a database, unit identifiers, an output format, an engine number, temperature identifiers, weight units and the like in an input file based on an SCAP protocol, and specifically configuring as follows:

ACMDBI=D02604

ACTYPE=737-800

ALTUNT=M

BRAKES=CAT_N

CERTIF=FAA-SCAP

DEPTHU=MM

DESCRIBE='DRY RUNWAY'

DISTU=M

ENGTYP=CFM56-7B24

LINES PER PAGE=80

MMID=BTM

REVNBR=S012

TMPUNT=C

WTUNIT=KG

OUTPUT OPTION WIND1。

step 6-2: and configuring information of units of four codes, name, elevation and height distance of the airport based on the SCAP protocol. The configuration is as follows:

AIRPORT1

'ZBAA' 'CAPITAL' 'BEIJING,CHINA' 'MMLOLO' 36。

step 6-3: and configuring the distance of the runway and the information of the obstacles based on the SCAP protocol. The method comprises the following specific steps:

RWYS

'01' 1 3800.0 500.0 0.0 3800.0 0.18 0.18 0.18 4

9 900000 0

57 4030 0

50 2483 0

46 2759 0。

step 6-4: and extracting parameter value data of the road surface condition value, the flap, the air conditioner, the anti-icing option and the reverse thrust option of the performance chart calculation template configured in the step 5. The POPT, CONF, XMET and UNIT classes comprise the following classes:

POPT(1)=0

POPT(2)=0

POPT(4)=1

POPT(5)=0

POPT(6)=9.E20

POPT(7)=0

POPT(8)=0

POPT(9)=9.E20

POPT(11)=1

POPT(12)=20

POPT(13)=36

POPT(14)=0

POPT(15)=9.E20

POPT(16)=9.E20

POPT(17)=9.E20

POPT(18)=0

POPT(19)=122

POPT(20)=0

POPT(21)=7

POPT(22)=9.E20

POPT(23)=9.E20

POPT(24)=77791

POPT(25)=0

POPT(26)=5

POPT(27)=0

POPT(28)=9.E20

POPT(29)=9.E20

POPT(30)=9.E20

CONF(1)=1

CONF(2)=9.E20

CONF(3)=5

CONF(4)=2

CONF(5)=0

CONF(6)=9.E20

CONF(7)=0

CONF(8)=1

CONF(9)=0

CONF(10)=9.E20

CONF(11)=9.E20

CONF(13)=9.E20

CONF(14)=9.E20

CONF(15)=9.E20

CONF(16)=225

CONF(17)=9.E20

CONF(18)=9.E20

CONF(19)=9.E20

CONF(20)=0

XMET(5)=1013.25

UNIT(6)=0

UNIT(8)=0。

step 6-5: extracting wind and temperature data of the performance chart calculation template configured in the step 5;

WINDS=-10,0,10

TEMPS=-5,0,5,10,12,14,16,18,20,22,24,26,28,30。

step 6-6: configuring and calculating an output format and calculating keyword data in an input file based on the SCAP;

SELECT RUNWAY ZBAA/01

CALC。

step 6-7: and generating a calculation input file according to the configuration information combination. Named input file is scapip.

And 7: calling a kernel file of manufacturer performance computing software to obtain output result data, wherein the output result data comprises the following steps:

step 7-1: preparing the kernel files of the performance computing software of the manufacturer, including model database files, application programs, dynamic link library files, input files and configuration files.

Step 7-2: an output result file and a log file are generated by using an application program or a method defined by executing the dynamic link library file and calling a kernel file of the manufacturer performance computing software, wherein the output result file is shown in fig. 2.

And 7-3: and checking whether the log file has error information or not, and if not, indicating that the calculation is successful. If the error information exists, checking whether the model parameter data configured in the step 1 is correct according to the error information, checking the model parameter data according to technical document parameters provided by manufacturers based on the SCAP protocol, and executing again according to the step 1.

And 8: parsing the output result data and generating performance graph data, including:

step 8-1: matching output result data according to key word key values in technical documents of manufacturer performance calculation software, and intercepting information in output results by a splitting method of a regular expression; fig. 2 shows a calculation output result file, which consists of three parts, version information of the calculation performance chart, performance chart data declaration and performance chart data. The content of the analysis only needs to analyze the performance chart data, so that a regular expression is used: the ELEVATION [ \ S ]' splits the performance chart data to obtain the initial text information of the performance chart data.

Step 8-2: and converting the data part of the performance chart in the intercepted information into a PDF file format for storage. The extracted performance chart data is converted into a PDF file by using a PDF plug-in, and the position information stored in the PDF file is stored, and the converted file is shown in fig. 3.

Therefore, the process of batch calculation of the performance chart data of the boeing machine type takeoff stage based on the SCAP protocol is completed. The method of the example only demonstrates operation during the takeoff phase, and is equally applicable to landing phases. According to the method of the embodiment, the performance chart data can be generated in batches for both the air passenger type and the Chinese commercial aircraft type according to the method of the embodiment.

The above description is only one embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention still belong to the protection scope of the technical solution of the present invention.

Claims (7)

1. A method for batch computation of multi-model performance chart data based on SCAP protocol is characterized by comprising the following steps:

step 1: configuring model parameter data based on the SCAP protocol;

step 2: generating a calculation input file according to the configured model parameter data based on the SCAP protocol;

and step 3: calling a kernel file of manufacturer performance calculation software by combining the calculation input file to obtain output result data;

and 4, step 4: verifying the consistency of the output result data and the result data of the manufacturer performance calculation software;

and 5: configuring a performance chart calculation template according to the model;

step 6: generating a calculation input file according to a configured performance chart calculation template based on an SCAP protocol;

and 7: calling a kernel file of manufacturer performance computing software to obtain output result data;

and 8: and analyzing the output result data and generating performance chart data.

2. The method for batch computation of multi-model performance chart data based on the SCAP protocol as claimed in claim 1, wherein the step 1 comprises the steps of:

step 1-1: respectively configuring performance parameter data of the take-off and landing stages of the airbus, the boeing and the Chinese commercial aircraft type based on an SCAP protocol;

step 1-2: configuring selectable data of performance parameters of the take-off and landing stages of the air passenger, the boeing and the Chinese commercial aircraft type respectively based on an SCAP protocol;

step 1-3: and respectively configuring the performance parameter association data of the air passenger, the boeing and the Chinese commercial aircraft type in the takeoff and landing stages based on the SCAP protocol.

3. The method for batch computation of multi-model performance chart data based on the SCAP protocol as claimed in claim 1, wherein the step 2 comprises the steps of:

step 2-1: extracting a database and unit identification information of the model based on model parameter data configured by an SCAP protocol;

step 2-2: extracting option value information of a road surface condition, a flap, an air conditioner, anti-icing and reverse thrust based on model parameter data configured by an SCAP protocol;

step 2-3: configuring information of units of four codes, name, elevation and height distance of the airport based on the SCAP protocol;

step 2-4: configuring the distance of the runway and the information of the obstacles based on the SCAP protocol;

step 2-5: configuring the calculated wind and temperature information based on the model parameter data configured by the SCAP protocol;

step 2-6: configuring an output format and calculating key word information based on the model parameter data configured by the SCAP protocol;

step 2-7: and generating a calculation input file according to the configuration information combination.

4. The method for batch computation of multi-model performance chart data based on the SCAP protocol as claimed in claim 1, wherein the step 3 comprises the steps of:

step 3-1: preparing kernel files of performance computing software of manufacturers, wherein the kernel files comprise model database files, application programs, dynamic link library files, input files and configuration files;

step 3-2: using an application program or executing a method defined by a dynamic link library file and calling a kernel file of manufacturer performance calculation software to generate an output result file and a log file;

step 3-3: checking whether the log file has error information or not, and if not, indicating that the calculation is successful; if error information exists, checking whether the model parameter data configured in the step 1 is correct according to the error information, checking the model parameter data according to technical document parameters provided by manufacturers based on an SCAP protocol, and executing again according to the step 1;

step 3-4: and analyzing the output result file into output result data by using a regular expression.

5. The method for batch computation of multi-model performance chart data based on the SCAP protocol as claimed in claim 1, wherein the step 4 comprises the steps of:

step 4-1: selecting the same airport runway information, verifying the same airport runway information by using a calculation condition formed by fixed wind speed, temperature, flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data, and comparing whether the output result data is consistent with the output result data of manufacturer performance calculation software or not;

step 4-2: selecting different airport runway information, verifying the information by using a calculation condition formed by fixed wind speed, temperature, flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data, and comparing whether the output result data is consistent with the output result data of manufacturer performance calculation software or not;

step 4-3: selecting the same airport runway information, verifying the same airport runway information by using calculation conditions which are respectively obtained according to different flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data under the condition of fixed wind speed and temperature, and comparing whether the output result data is consistent with the output result data of manufacturer performance calculation software or not;

step 4-4: and selecting the same airport runway information, verifying by using fixed flap option data, reverse thrust option data, air conditioner option data, anti-icing option data and pavement option data and calculating conditions which are respectively obtained according to different wind speeds and temperature compositions, and comparing whether the output result data is consistent with the output result data of manufacturer performance calculating software or not.

6. The method for batch computation of multi-model performance chart data based on the SCAP protocol as claimed in claim 1, wherein the step 5 comprises the steps of:

step 5-1: respectively creating performance chart calculation templates of take-off and landing stages of different models;

step 5-2: configuring a temperature data range of a performance chart calculation template in a take-off and landing stage;

step 5-3: configuring a wind data range of a performance chart calculation template in a take-off and landing stage;

step 5-4: configuring the road surface condition option data of a performance chart calculation template in the take-off and landing stages;

step 5-5: configuring flap option data of a performance chart calculation template in the take-off and landing stages;

and 5-6: configuring air conditioner option data of a performance chart calculation template in the take-off and landing stages;

and 5-7: configuring anti-icing option data of a performance chart calculation template in the take-off and landing stages;

and 5-8: and configuring a performance chart in the takeoff and landing phases to calculate reverse thrust option data of the template.

7. The method for batch computation of multi-model performance chart data based on the SCAP protocol as claimed in claim 1, wherein the step 8 comprises the steps of:

step 8-1: matching output result data according to key word key values in technical documents of manufacturer performance calculation software, and intercepting information in output results by a splitting method of a regular expression;

step 8-2: and converting the data part of the performance chart in the intercepted information into a PDF file format for storage.

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