CN113380075A - Method and system for measuring landing air distance - Google Patents
Method and system for measuring landing air distance Download PDFInfo
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Abstract
The invention discloses a method and a system for measuring a landing air distance, which improve the calculation precision of the landing air distance and improve the effects of pilot control quality monitoring and civil aviation safety risk assessment. The technical scheme is as follows: analyzing and decoding parameters related to the landing air distance measurement in each flight of each airplane of different types, writing big data, matching and associating the parameters with flight information in a flight operation system, and establishing a relationship matching table of flight data and flight information; making static data tables of airport runway and lower sliding table data, storing the static data tables in a big data environment, taking a landing airport and a landing runway as data main keys, matching and associating the static data tables of the airport runway and the lower sliding table data with a relation matching table, and constructing a flight information dynamic table containing the lower sliding table data; carrying out normalization processing on the parameters; and measuring the horizontal distance from the runway entrance to the grounding point based on the distance from the gliding platform to the runway entrance and the gliding angle in different airports and different runways.
Description
Technical Field
The invention relates to a civil aviation safety risk assessment technology, in particular to a method and a system for measuring landing air distance in the precise approach landing process of a civil aircraft.
Background
The event of an aircraft rushing out of or moving out of an airport runway during takeoff or landing is referred to as a rush out runway event, also referred to as runway departure. In 2015-2019, the number of accidents deviating from the runway accounts for 25% of the total number of accidents, which results in 55 deaths, the number of fatal accidents deviating from the runway accounts for 11% of the total number of fatal accidents, and the deviation from the runway is the second leading cause of fatal accidents.
In 2019, the number of accidents of rush out of the runway is 17, accounting for 32% of the total number of accidents, wherein 2 accidents are fatal accidents and the number of dead people is 3. The drift out of the runway is a high-risk unsafe event, which often causes serious losses such as casualties, body injuries and the like, and poses serious threats to the world civil aviation safety. Between five years of 2012-2016, 83% of the excursions out of the runway occurred during the landing phase. The drift-out runway can be divided into a drift-out runway and a drift-out runway, and the drift-out runway means one side of the airplane drift-out runway; rushing out of the runway refers to the airplane rushing out of the end of the runway. The drift-out runway events are combined together for statistics in the civil aviation industry, and the industry needs to provide an index for evaluating the risk of the aircraft drifting out of the runway.
According to the navigation equipment used in the last navigation section of the instrument approach program, the instrument approach program is divided into a non-precision approach program and a precision approach program. The used navigation equipment only provides azimuth information and does not provide glide slope information in the last navigation segment, and the procedure is a non-precision approach procedure; the used navigation equipment can provide both azimuth information and glide slope information in the final flight segment as a precise approach program. In 2020, the 320 series of airplanes in a company land in a close approach mode, the number of flights accounts for 97% of the total number of flights of the series of airplanes, and the proportion of heavy airplanes such as 330 is higher.
The aircraft landing phase refers to the operational phase from when the aircraft is at a vertical altitude of 50 feet from the airport surface to when the aircraft is completely stopped on the runway. The landing stage consists of a landing aerial section and a ground deceleration sliding section. The landing aerial section can be divided into a gliding section, a leveling section, a flat floating section and a grounding section. The horizontal distance required for the aircraft to land and come to a complete stop from a point 15 meters (50 feet) above the landing surface is called the landing distance. And the distance from 50 feet to ground, i.e., the landing air distance, refers to the horizontal distance required for the aircraft to land from a point 15 meters (50 feet) above the landing surface to the aircraft, i.e., any main wheels that are grounded and no longer lift off the ground. The united states federal aviation administration states that in revised advisory announcements regarding the reduction of runway overrun risks: the ground point increases the risk of rushing out of the runway.
The airline company evaluates the risk of rushing out of the runway, and the key point is how long the runway is used in the landing process of the airplane or how long the runway is consumed by the grounding of the airplane. Currently, a point 50 feet above the landing surface is generally used as a starting position, and the landing distance and the landing air distance are calculated. In actual flight, the instantaneous height of the aircraft during the landing phase when it flies over the runway threshold is not necessarily 50 feet from the standard height, i.e. the vertical projection of the aircraft 50 feet above the landing surface is not necessarily coincident with the runway threshold. The difference between the instantaneous altitude of the aircraft flying over the runway threshold and the standard altitude of 50 feet or the difference between the moment when the aircraft is at the altitude of 50 feet and the moment when the aircraft flies over the runway threshold directly influences the calculation accuracy of the landing distance and the landing air distance.
In view of this, the airline companies need a new calculation method based on air-ground information interaction to improve the calculation accuracy of the landing distance and the landing air distance, provide more accurate and reliable indexes for runway rushing risk assessment, better participate in building an index system of a flight big data platform, improve the pilot operation quality of the airline companies, and guarantee the flight safety.
Disclosure of Invention
The following presents a simplified summary of one or more aspects in order to provide a basic understanding of such aspects. This summary is not an extensive overview of all contemplated aspects, and is intended to neither identify key or critical elements of all aspects nor delineate the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed description that is presented later.
The invention aims to solve the problems and provides a method and a system for measuring the landing air distance, so that the calculation precision of the landing air distance is improved, and the effects of pilot control quality monitoring and civil aviation safety risk assessment are improved.
The technical scheme of the invention is as follows: the invention discloses a method for measuring landing air distance, which comprises the following steps:
step 1: analyzing and decoding parameters related to the landing air distance measurement in each flight of each airplane of different types, writing big data, matching and associating the parameters with flight information in a flight operation system, and establishing a relationship matching table of flight data and flight information;
step 2: making static data tables of the data of the airport runway and the lower sliding table, and storing the static data tables in a big data environment, wherein the static data tables of the data of the airport runway and the lower sliding table are matched and associated with the relation matching table in the step 1 by taking a landing airport and a landing runway as main keys of the data, and constructing a flight information dynamic table containing the data of the lower sliding table;
and step 3: carrying out normalization processing on parameters of different types of airplanes related to the measurement of the landing air distance;
and 4, step 4: and measuring the horizontal distance from the runway entrance to the grounding point based on the distances and the glide angles of the glide-slope from the runway entrances in different airports and different runways after normalization processing.
According to an embodiment of the method for measuring the landing air distance of the present invention, the parameters related to the landing air distance measurement in steps 1 and 3 include: radio height, glide angle offset, ground speed and main landing gear retraction indication of each flight of each airplane of different types.
According to an embodiment of the method for measuring landing air distance of the present invention, step 4 further comprises:
step 4-1: determining the moment when the airplane flies over the runway entrance according to the principle of dynamic geometrical relationship based on the distance between the gliding platform and the runway entrance and the gliding angle in different airports and different runways, and defining the moment as a time point t 1;
step 4-2: defining the moment when any main wheel is grounded and no longer lifted off the ground as a time point t 2;
step 4-3: and starting from a time point t1 to a time point t2, integrating the ground speed with the time, and calculating a measured value of the distance from the runway entrance to the grounding point.
According to an embodiment of the method for measuring the landing air distance, in step 4-1, the dynamic geometrical relationship is as follows:
in the above formula, d is the horizontal distance from the airplane to the GP station, h is the radio altitude of the airplane, and theta0Is the glide angle, and d θ is the glide angle offset;
in the above formula, D is the distance between GP station and runway threshold, H is the radio altitude when the airplane is at the upper part of runway threshold, and theta0Is a glide angle, d θ0The glide angle offset for an aircraft when it is over the runway threshold. The radio altitude and glide-angle deviation of the airplane are time variables respectively expressed as h (t), d theta (t), when h (t)/tan (theta)0+ D θ (t)) is equal to or smaller than D for the first time, the corresponding time t is marked as time t 1.
According to an embodiment of the method for measuring the landing air distance, in step 4-3, the formula of integrating the ground speed with the time is as follows:
wherein, D _ td is the horizontal distance between the runway entrance and the grounding point, and GSC is the ground speed of the airplane.
The invention also discloses a system for measuring the landing air distance, which comprises:
the system comprises a relationship matching table construction module, a system management module and a system management module, wherein the relationship matching table construction module is used for analyzing and decoding parameters related to landing air distance measurement in each flight of each airplane of different types, writing big data and matching and associating the parameters with flight information in a flight operation system, and establishing a relationship matching table of flight data and flight information;
the flight information dynamic table building module is used for manufacturing static data tables of airport runway and lower sliding table data and storing the static data tables in a big data environment, wherein the static data tables of the airport runway and the lower sliding table data are matched and associated with the relation matching table by taking a landing airport and a landing runway as main data keys, and a flight information dynamic table containing the lower sliding table data is built;
the parameter normalization module is used for performing normalization processing on parameters of different types of airplanes related to the measurement of the landing air distance;
and the distance measuring and calculating module is used for measuring the horizontal distance from the runway entrance to the grounding point based on the distances and the glide angles of the glide-slope from the runway entrances in different airports and different runways after normalization processing.
According to an embodiment of the system for measuring landing air distance, the parameters related to the landing air distance measurement in the relationship matching table construction module and the parameter normalization module include: radio height, glide angle offset, ground speed and main landing gear retraction indication of each flight of each airplane of different types.
According to an embodiment of the system for measuring landing air distance of the present invention, the distance measuring module is further configured to process the following steps:
determining the moment when the airplane flies over the runway entrance according to the principle of dynamic geometrical relationship based on the distance between the gliding platform and the runway entrance and the gliding angle in different airports and different runways, and defining the moment as a time point t 1;
defining the moment when any main wheel is grounded and no longer lifted off the ground as a time point t 2;
and starting from a time point t1 to a time point t2, integrating the ground speed with the time, and calculating a measured value of the distance from the runway entrance to the grounding point.
According to an embodiment of the system for measuring landing air distance of the present invention, the dynamic geometrical relationship of the distance measuring module is as follows:
in the above formula, d is the horizontal distance from the airplane to the GP station, h is the radio altitude of the airplane, and theta0In order to obtain a lower slip angle,d θ is glide angle offset;
in the above formula, D is the distance between GP station and runway threshold, H is the radio altitude when the airplane is at the upper part of runway threshold, and theta0Is a glide angle, d θ0The glide angle offset for an aircraft when it is over the runway threshold. The radio altitude and glide-angle deviation of the airplane are time variables respectively expressed as h (t), d theta (t), when h (t)/tan (theta)0+ D θ (t)) is equal to or smaller than D for the first time, the corresponding time t is marked as time t 1.
According to an embodiment of the system for measuring landing air distance of the present invention, the distance measuring module is further configured such that the formula of integrating the ground speed with respect to time is:
wherein, D _ td is the horizontal distance between the runway entrance and the grounding point, and GSC is the ground speed of the airplane.
Compared with the prior art, the invention has the following beneficial effects: the invention aims at the problem that the existing traditional method can not detect (calculate) the accurate time of the airplane entering the runway, and can only adopt a point 50 feet higher than the landing surface as the starting position to calculate the landing air distance. Specifically, the innovation of the invention mainly comprises:
(1) the method comprises the steps of determining the moment when the airplane flies over the runway entrance, and accurately determining the lower time limit when the ground speed is integrated with the time. When the horizontal distance from the aircraft to the GP station (lower slipway) is equal to or less than the distance from the GP station to the runway threshold for the first time, this instant is the lower time limit.
(2) The method has the advantages that the operation data such as radio height, glide angle offset, ground speed, main undercarriage retraction indication and the like of different airplane types operating airplanes are effectively stored and normalized, so that the subsequent calculation formula of the distance from the runway entrance to the grounding point is suitable for all airplane types operated by a navigation driver.
(3) The method adopts modern big data processing technology and combines traditional flight safety analysis to create a measured value 'runway entrance to grounding point distance', and forms an effective dynamic index for evaluating the risk of the airplane rushing out of the runway.
Drawings
The above features and advantages of the present disclosure will be better understood upon reading the detailed description of embodiments of the disclosure in conjunction with the following drawings. In the drawings, components are not necessarily drawn to scale, and components having similar relative characteristics or features may have the same or similar reference numerals.
Fig. 1A and 1B show schematic diagrams of a runway.
FIG. 2 is a flowchart illustrating an embodiment of a method for measuring landing air distance according to the present invention.
FIG. 3 shows a schematic diagram of an embodiment of the landing air distance measurement system of the present invention.
FIG. 4 shows a schematic diagram of an MSAP platform.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments. It is noted that the aspects described below in connection with the figures and the specific embodiments are only exemplary and should not be construed as imposing any limitation on the scope of the present invention.
Fig. 2 shows a flow of an embodiment of the method for measuring landing air distance of the present invention. Referring to fig. 2, the steps of the method of the present embodiment are detailed as follows.
Step 1: analyzing and decoding parameters related to the landing air distance measurement in each flight of each airplane of different types, writing big data, matching and associating the big data with flight information in a flight operation system, and establishing a relation matching table of flight data and flight information.
Wherein the parameters related to the landing air distance measurement comprise: radio altitude, glide angle offset, ground speed, main landing gear retraction indication, etc. of each flight of each aircraft of different models.
The analysis decoding, big data writing and the matching correlation with the flight information in the flight operation system are processed by using a parameter automatic decoding and data processing module of an MSAP platform (a system for storing, processing and using big flight data).
The MSAP platform refers to the description of the applicant in another patent (application No. 202010740438.9), and please refer to fig. 4, and the MSAP platform includes a parameter automatic decoding and data processing module, an engineering parameter module, an analysis parameter module, and an analysis module, wherein the parameter automatic decoding and data processing module is used for performing decoding and analysis on all parameters of different models, writing large data, and matching and associating with flight information in a flight operation system.
The parameter automatic decoding and data processing module is configured to decode QAR data in the QAR data original file of each flight and export a full parameter file containing full parameters in a CSV format; associating the QAR data original file, the full parameter file and flight information in a flight operation system, determining a data primary key, storing decoded flight data in an HBase cluster through columnar storage conversion, and compressing the flight data; and then, performing primary cleaning and filtering on the flight data according to the configured cleaning rule.
The parameter automatic decoding and data processing module automatically generates a log file after decoding in the process of decoding the QAR data, the log file records the name of the QAR data original file and the name of the full parameter file, judges whether the full parameter file is a result after correct decoding, and if not, performs re-decoding on the corresponding QAR data original file under manual intervention according to the information in the log file.
Step 2: and (3) making static data tables of the data of the airport runway and the GP stations (lower sliding table), storing the static data tables in a big data environment, wherein the static data tables of the data of the airport runway and the GP stations and the relation matching table in the step (1) are matched and associated by taking the landing airport and the landing runway as main data keys, and constructing a flight information dynamic table containing the GP station data.
And step 3: and carrying out normalization processing on parameters of different types of airplanes related to the measurement of the landing air distance.
The parameters related to the landing air distance measurement in this step include: radio altitude, glide angle offset, ground speed, main landing gear retraction indication, etc.
In this embodiment, the engineering parameter module in the MSAP platform is used to perform normalization processing on the above parameters.
The engineering parameter module is connected with the output end of the parameter automatic decoding and data processing module and is used for carrying out normalization processing on the engineering parameters of different airplane types based on the flight data output by the parameter automatic decoding and data processing module.
The engineering parameter module is configured to perform secondary cleaning and filtering on the flight data according to the configured cleaning rules to obtain model parameter base metadata; and mapping and matching the metadata of the parameter base of different machine types and the standard engineering parameters according to the set matching rules.
The processing of the project parameter module for mapping and matching the metadata of the different model parameter bases and the standard project parameters further comprises:
performing first-layer automatic matching through name regular matching, finding out machine type parameters with the same or similar names, and verifying the data output range;
after the first-layer automatic matching is finished, performing second-layer automatic matching on unmatched model parameters through semantic similar matching;
calculating the credibility of the matching results subjected to automatic matching of the first layer and the second layer;
manually verifying the residual unmatched model parameters, and manually adjusting and matching the parameters according to the calculated credibility;
and setting a standard frequency, and automatically performing frequency increase in an average filling mode on the parameters lower than the standard frequency, and simultaneously supporting manual frequency setting.
The project parameter module is also configured to provide an interface of a custom function and a project parameter custom script, the custom function is used for editing and customizing new project parameters through the interface, and the machine type parameter base metadata is processed to obtain a project parameter base.
And 4, step 4: and measuring the horizontal distance from the runway entrance to the grounding point according to the dynamic geometrical relationship based on the distances and the downward sliding angles of the GP stations of different airports and different runways after normalization processing.
Step 4 further comprises:
step 4-1: and determining the moment when the airplane flies over the entrance of the runway according to the principle of dynamic geometrical relationship based on the distances and the downward sliding angles of GP stations of different airports and different runways, and defining the moment as a time point t 1.
The following is a detailed description, and the calculation principle thereof will be described with reference to fig. 1A and 1B. Fig. 1A shows a state where the aircraft is not flying to the runway threshold, and fig. 1B shows a state where the aircraft is flying over the runway threshold. In the formulas of FIGS. 1A and 1B and throughout, L is the runway length, D is the horizontal distance from the aircraft to the GP station, D is the distance from the runway threshold, H is the radio altitude of the aircraft, H is the radio altitude when the aircraft is above the runway threshold, θ0Is the glide angle, d θ is the glide angle offset, d θ0The glide angle offset for an aircraft when it is over the runway threshold.
From the geometric relationship in FIG. 1A, we obtain:
in the above formula (1), d is the horizontal distance from the airplane to the GP station, h is the radio altitude of the airplane, and theta0D θ is the glide angle offset.
The tangent of the sum of the glide angle and the glide angle offset in equation (1) above represents the vertical distance of the aircraft from the landing surface, i.e., the radio altitude, versus the horizontal distance of the aircraft from the GP station. And during landing, when the horizontal distance from the airplane to the GP station is equal to or less than the distance from the GP station to the runway threshold for the first time, the airplane flies over the runway threshold at the moment. As shown in fig. 1B, the geometric relational expression is shown in formula (2):
in the above formula (2), D is the distance between the GP station and the runway threshold, H is the radio altitude when the airplane is at the upper part of the runway threshold, and theta0Is a glide angle, d θ0The glide angle offset for an aircraft when it is over the runway threshold.
The radio altitude and glide-angle deviation of the airplane are time variables which can be respectively expressed as h (t) and d theta (t). The distance D between GP table and runway entrance and the glide angle theta are given for airport and runway0The detailed values may be consulted for airport detailed rules, which are constants. When h (t)/tan (theta)0+ D θ (t)) is first equal to or less than D, the corresponding time t is marked as time t 1.
Step 4-2: the time at which either main wheel is grounded and no longer lifted off the ground is defined as time t 2.
Step 4-3: and starting from a time point t1 to a time point t2, integrating the ground speed with the time, and calculating a measured value of the distance from the runway entrance to the grounding point.
The formula for the integration is as follows:
wherein, D _ td is the horizontal distance between the runway entrance and the grounding point, and GSC is the ground speed of the airplane.
Step 4 is completed by an analysis parameter module in the MSAP platform.
The analysis parameter module comprises a standard analysis parameter library unit and an analysis parameter editing unit, the standard analysis parameter library unit is used for establishing a preset concerned statistical parameter system covering the whole process of flying from takeoff to landing, and the analysis parameter editing unit is used for providing algorithm grammar used for calculating the analysis parameters of the flight big data specific indexes. The analysis parameter module is configured to calculate analysis parameters by a user-defined script mode by using a system function based on uniform standard engineering parameters, external parameters GP table distance and a glide angle in the engineering parameter module according to civil aviation business logic. The analysis parameter module adopts a Spark distributed computing engine, a computing request of analysis parameters is sent to Spark on YARN, Spark cuts the flight-analysis parameters as the minimum unit for parallel computing, each core is responsible for computing the minimum unit, and any core can be distributed with a new computing task after computing one analysis parameter of one flight. The analysis parameter module stores script calculation results of Spark operation in a column-type database Kudu, a standard analysis parameter library is established in Kudu, and a plurality of analysis parameters in the standard analysis parameter library cover flight indexes of the whole flight process.
FIG. 3 illustrates the principle of an embodiment of the landing air distance measurement system of the present invention. Referring to fig. 3, the system of the present embodiment includes: the system comprises a relation matching table construction module, a flight information dynamic table construction module, a parameter normalization module and a distance measurement and calculation module.
The output end of the relation matching construction module is connected with the flight information dynamic table construction module, the output end of the flight information dynamic table construction module is connected with the parameter normalization module, and the output end of the parameter normalization module is connected with the distance measurement module.
The relationship matching table building module is used for analyzing and decoding parameters related to the landing air distance measurement in each flight of each airplane of different types, writing big data, matching and associating the parameters with flight information in a flight operation system, and building a relationship matching table of flight data and flight information.
Wherein the parameters related to the landing air distance measurement comprise: radio altitude, glide angle offset, ground speed, main landing gear retraction indication, etc. of each flight of each aircraft of different models.
The analysis decoding, big data writing and the matching correlation with the flight information in the flight operation system are processed by using a parameter automatic decoding and data processing module of an MSAP platform (a system for storing, processing and using big flight data).
The MSAP platform refers to the description of the applicant in another patent (application No. 202010740438.9), and please refer to fig. 4, and the MSAP platform includes a parameter automatic decoding and data processing module, an engineering parameter module, an analysis parameter module, and an analysis module, wherein the parameter automatic decoding and data processing module is used for performing decoding and analysis on all parameters of different models, writing large data, and matching and associating with flight information in a flight operation system.
The parameter automatic decoding and data processing module is configured to decode QAR data in the QAR data original file of each flight and export a full parameter file containing full parameters in a CSV format; associating the QAR data original file, the full parameter file and flight information in a flight operation system, determining a data primary key, storing decoded flight data in an HBase cluster through columnar storage conversion, and compressing the flight data; and then, performing primary cleaning and filtering on the flight data according to the configured cleaning rule.
The parameter automatic decoding and data processing module automatically generates a log file after decoding in the process of decoding the QAR data, the log file records the name of the QAR data original file and the name of the full parameter file, judges whether the full parameter file is a result after correct decoding, and if not, performs re-decoding on the corresponding QAR data original file under manual intervention according to the information in the log file.
The flight information dynamic table construction module is used for manufacturing static data tables of airport runway and lower sliding table data and storing the static data tables in a big data environment, wherein the static data tables of the airport runway and the lower sliding table data are matched and associated with the relation matching table by taking a landing airport and a landing runway as main data keys, and the flight information dynamic table containing the lower sliding table data is constructed.
The parameter normalization module is used for performing normalization processing on parameters of different types of airplanes related to the landing air distance measurement.
Parameters related to landing air distance measurement include: radio altitude, glide angle offset, ground speed, main landing gear retraction indication, etc.
In this embodiment, the engineering parameter module in the MSAP platform is used to perform normalization processing on the above parameters.
The engineering parameter module is connected with the output end of the parameter automatic decoding and data processing module and is used for carrying out normalization processing on the engineering parameters of different airplane types based on the flight data output by the parameter automatic decoding and data processing module.
The engineering parameter module is configured to perform secondary cleaning and filtering on the flight data according to the configured cleaning rules to obtain model parameter base metadata; and mapping and matching the metadata of the parameter base of different machine types and the standard engineering parameters according to the set matching rules.
The processing of the project parameter module for mapping and matching the metadata of the different model parameter bases and the standard project parameters further comprises:
performing first-layer automatic matching through name regular matching, finding out machine type parameters with the same or similar names, and verifying the data output range;
after the first-layer automatic matching is finished, performing second-layer automatic matching on unmatched model parameters through semantic similar matching;
calculating the credibility of the matching results subjected to automatic matching of the first layer and the second layer;
manually verifying the residual unmatched model parameters, and manually adjusting and matching the parameters according to the calculated credibility;
and setting a standard frequency, and automatically performing frequency increase in an average filling mode on the parameters lower than the standard frequency, and simultaneously supporting manual frequency setting.
The project parameter module is also configured to provide an interface of a custom function and a project parameter custom script, the custom function is used for editing and customizing new project parameters through the interface, and the machine type parameter base metadata is processed to obtain a project parameter base.
The distance measuring and calculating module is used for measuring the horizontal distance from the runway entrance to the grounding point based on the distances and the glide-angle between the glide-slope and the runway entrance in different airports and different runways after normalization processing.
The distance measurement module is further configured to perform the following processing.
And determining the moment when the airplane flies over the entrance of the runway according to the principle of dynamic geometrical relationship based on the distances and the downward sliding angles of GP stations of different airports and different runways, and defining the moment as a time point t 1.
The following is a detailed description, and the calculation principle thereof will be described with reference to fig. 1A and 1B. Fig. 1A shows a state where the aircraft is not flying to the runway threshold, and fig. 1B shows a state where the aircraft is flying over the runway threshold. In the formulas of FIGS. 1A and 1B and throughout, L is the runway length, D is the horizontal distance from the aircraft to the GP station, D is the distance from the runway threshold, H is the radio altitude of the aircraft, H is the radio altitude when the aircraft is above the runway threshold, θ0Is the glide angle, d θ is the glide angle offset, d θ0The glide angle offset for an aircraft when it is over the runway threshold.
From the geometric relationship in FIG. 1A, we obtain:
in the above formula (1), d is the horizontal distance from the airplane to the GP station, h is the radio altitude of the airplane, and theta0D θ is the glide angle offset.
The tangent of the sum of the glide angle and the glide angle offset in equation (1) above represents the vertical distance of the aircraft from the landing surface, i.e., the radio altitude, versus the horizontal distance of the aircraft from the GP station. And during landing, when the horizontal distance from the airplane to the GP station is equal to or less than the distance from the GP station to the runway threshold for the first time, the airplane flies over the runway threshold at the moment. As shown in fig. 1B, the geometric relational expression is shown in formula (2):
in the above formula (2), D is the distance between the GP station and the runway threshold, H is the radio altitude when the airplane is at the upper part of the runway threshold, and theta0Is a glide angle, d θ0The glide angle offset for an aircraft when it is over the runway threshold.
The radio altitude and glide-angle deviation of the airplane are time variables which can be respectively expressed as h (t) and d theta (t). The distance D between GP table and runway entrance and the glide angle theta are given for airport and runway0The detailed values may be consulted for airport detailed rules, which are constants. When h (t)/tan (theta)0+ D θ (t)) is first equal to or less than D, the corresponding time t is marked as time t 1.
The time at which either main wheel is grounded and no longer lifted off the ground is defined as time t 2.
And starting from a time point t1 to a time point t2, integrating the ground speed with the time, and calculating a measured value of the distance from the runway entrance to the grounding point.
The formula for the integration is as follows:
wherein, D _ td is the horizontal distance between the runway entrance and the grounding point, and GSC is the ground speed of the airplane.
The above processing is accomplished by an analysis parameter module in the MSAP platform.
The analysis parameter module comprises a standard analysis parameter library unit and an analysis parameter editing unit, the standard analysis parameter library unit is used for establishing a preset concerned statistical parameter system covering the whole process of flying from takeoff to landing, and the analysis parameter editing unit is used for providing algorithm grammar used for calculating the analysis parameters of the flight big data specific indexes. The analysis parameter module is configured to calculate analysis parameters based on unified engineering parameters in the engineering parameter module according to civil aviation business logic, and in addition, external parameters of GP table distance and glide angle, by using system functions and in a user-defined script mode. The analysis parameter module adopts a Spark distributed computing engine, a computing request of analysis parameters is sent to Spark on YARN, Spark cuts the flight-analysis parameters as the minimum unit for parallel computing, each core is responsible for computing the minimum unit, and any core can be distributed with a new computing task after computing one analysis parameter of one flight. The analysis parameter module stores script calculation results of Spark operation in a column-type database Kudu, a standard analysis parameter library is established in Kudu, and a plurality of analysis parameters in the standard analysis parameter library cover flight indexes of the whole flight process.
While, for purposes of simplicity of explanation, the methodologies are shown and described as a series of acts, it is to be understood and appreciated that the methodologies are not limited by the order of acts, as some acts may, in accordance with one or more embodiments, occur in different orders and/or concurrently with other acts from that shown and described herein or not shown and described herein, as would be understood by one skilled in the art.
Those of skill would further appreciate that the various illustrative logical blocks, modules, circuits, and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware, computer software, or combinations of both. To clearly illustrate this interchangeability of hardware and software, various illustrative components, blocks, modules, circuits, and steps have been described above generally in terms of their functionality. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the overall system. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.
The various illustrative logical blocks, modules, and circuits described in connection with the embodiments disclosed herein may be implemented or performed with a general purpose processor, a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field Programmable Gate Array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components, or any combination thereof designed to perform the functions described herein. A general purpose processor may be a microprocessor, but in the alternative, the processor may be any conventional processor, controller, microcontroller, or state machine. A processor may also be implemented as a combination of computing devices, e.g., a combination of a DSP and a microprocessor, a plurality of microprocessors, one or more microprocessors in conjunction with a DSP core, or any other such configuration.
The steps of a method or algorithm described in connection with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. A software module may reside in RAM memory, flash memory, ROM memory, EPROM memory, EEPROM memory, registers, hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to the processor such the processor can read information from, and write information to, the storage medium. In the alternative, the storage medium may be integral to the processor. The processor and the storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In the alternative, the processor and the storage medium may reside as discrete components in a user terminal.
In one or more exemplary embodiments, the functions described may be implemented in hardware, software, firmware, or any combination thereof. If implemented in software as a computer program product, the functions may be stored on a computer-readable medium or transmitted over as one or more instructions or code. Computer-readable media includes both computer storage media and communication media including any medium that facilitates transfer of a computer program from one place to another. A storage media may be any available media that can be accessed by a computer. By way of example, and not limitation, such computer-readable media can comprise RAM, ROM, EEPROM, CD-ROM or other optical disk storage, magnetic disk storage or other magnetic storage devices, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and that can be accessed by a computer. Any connection is properly termed a computer-readable medium. For example, if the software is transmitted from a web site, server, or other remote source using a coaxial cable, fiber optic cable, twisted pair, Digital Subscriber Line (DSL), or wireless technologies such as infrared, radio, and microwave, then the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwave are included in the definition of medium. Disk (disk) and disc (disc), as used herein, includes Compact Disc (CD), laser disc, optical disc, Digital Versatile Disc (DVD), floppy disk and blu-ray disc where disks (disks) usually reproduce data magnetically, while discs (discs) reproduce data optically with lasers. Combinations of the above should also be included within the scope of computer-readable media.
The previous description of the disclosure is provided to enable any person skilled in the art to make or use the disclosure. Various modifications to the disclosure will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other variations without departing from the spirit or scope of the disclosure. Thus, the disclosure is not intended to be limited to the examples and designs described herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A method for measuring landing air distance is characterized by comprising the following steps:
step 1: analyzing and decoding parameters related to the landing air distance measurement in each flight of each airplane of different types, writing big data, matching and associating the parameters with flight information in a flight operation system, and establishing a relationship matching table of flight data and flight information;
step 2: making static data tables of the data of the airport runway and the lower sliding table, and storing the static data tables in a big data environment, wherein the static data tables of the data of the airport runway and the lower sliding table are matched and associated with the relation matching table in the step 1 by taking a landing airport and a landing runway as main keys of the data, and constructing a flight information dynamic table containing the data of the lower sliding table;
and step 3: carrying out normalization processing on parameters of different types of airplanes related to the measurement of the landing air distance;
and 4, step 4: and measuring the horizontal distance from the runway entrance to the grounding point based on the distances and the glide angles of the glide-slope platforms of different airports and different runways after normalization processing from the runway entrance.
2. The method for measuring landing air distance according to claim 1, wherein the parameters related to landing air distance measurement in steps 1 and 3 include: radio height, glide angle offset, ground speed and main landing gear retraction indication of each flight of each airplane of different types.
3. The method for measuring landing air distance according to claim 1, wherein step 4 further comprises:
step 4-1: determining the moment when the airplane flies over the runway entrance according to the principle of dynamic geometrical relationship based on the distance between the gliding platform and the runway entrance and the gliding angle in different airports and different runways, and defining the moment as a time point t 1;
step 4-2: defining the moment when any main wheel is grounded and no longer lifted off the ground as a time point t 2;
step 4-3: and starting from a time point t1 to a time point t2, integrating the ground speed with the time, and calculating a measured value of the distance from the runway entrance to the grounding point.
4. The method for measuring landing air distance according to claim 3, wherein in step 4-1, the dynamic geometrical relationship is as follows:
in the above formula, d is the horizontal distance from the airplane to the GP station, h is the radio altitude of the airplane, and theta0Is the glide angle, and d θ is the glide angle offset;
in the above formula, D is the distance between GP station and runway threshold, H is the radio altitude when the airplane is at the upper part of runway threshold, and theta0Is a glide angle, d θ0The glide-angle deviation of the airplane when the airplane is at the entrance of the runway, the radio altitude of the airplane and the glide-angle deviation are time variables respectively expressed as h (t), d theta (t), when h (t)/tan (theta)0+ D θ (t)) is smaller than or equal to D for the first time, the corresponding time t marksTime point t 1.
5. The method for measuring landing air distance according to claim 3, wherein in step 4-3, the formula of integrating ground speed with time is:
wherein, D _ td is the horizontal distance between the runway entrance and the grounding point, and GSC is the ground speed of the airplane.
6. A system for measuring landing air distance, the system comprising:
the system comprises a relationship matching table construction module, a system management module and a system management module, wherein the relationship matching table construction module is used for analyzing and decoding parameters related to landing air distance measurement in each flight of each airplane of different types, writing big data and matching and associating the parameters with flight information in a flight operation system, and establishing a relationship matching table of flight data and flight information;
the flight information dynamic table building module is used for manufacturing static data tables of airport runway and lower sliding table data and storing the static data tables in a big data environment, wherein the static data tables of the airport runway and the lower sliding table data are matched and associated with the relation matching table by taking a landing airport and a landing runway as main data keys, and a flight information dynamic table containing the lower sliding table data is built;
the parameter normalization module is used for performing normalization processing on parameters of different types of airplanes related to the measurement of the landing air distance;
and the distance measuring and calculating module is used for measuring the horizontal distance from the runway entrance to the grounding point based on the distances and the glide angles of the glide-slope from the runway entrances in different airports and different runways after normalization processing.
7. The system of claim 6, wherein the parameters related to the landing air distance measurement in the relational matching table construction module and the parameter normalization module comprise: radio height, glide angle offset, ground speed and main landing gear retraction indication of each flight of each airplane of different types.
8. The landing airspace distance measurement system of claim 6, wherein the distance measurement module is further configured to process the steps of:
determining the moment when the airplane flies over the runway entrance according to the principle of dynamic geometrical relationship based on the distance between the gliding platform and the runway entrance and the gliding angle in different airports and different runways, and defining the moment as a time point t 1;
defining the moment when any main wheel is grounded and no longer lifted off the ground as a time point t 2;
and starting from a time point t1 to a time point t2, integrating the ground speed with the time, and calculating a measured value of the distance from the runway entrance to the grounding point.
9. The system of claim 8, wherein the distance estimation module is further configured to determine the dynamic geometry as follows:
in the above formula, d is the horizontal distance from the airplane to the GP station, h is the radio altitude of the airplane, and theta0Is the glide angle, and d θ is the glide angle offset;
in the above formula, D is the distance between GP station and runway threshold, H is the radio altitude when the airplane is at the upper part of runway threshold, and theta0Is a glide angle, d θ0The glide-angle deviation of the airplane when the airplane is at the entrance of the runway, the radio altitude of the airplane and the glide-angle deviation are time variables respectively expressed as h (t), d theta (t), when h (t)/tan (theta)0+ D θ (t)) is smaller than or equal to D for the first time, the corresponding time t is marked as time point t1。
10. The system of claim 8, wherein the distance estimation module is further configured to integrate the ground speed with time according to the formula:
wherein, D _ td is the horizontal distance between the runway entrance and the grounding point, and GSC is the ground speed of the airplane.
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| CN117421541A (en) * | 2023-12-19 | 2024-01-19 | 珠海翔翼航空技术有限公司 | Method, system and equipment for measuring and calculating ground speed of airplane when hand wheel is operated |
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