Multi-aircraft real-time interval and flight parameter analysis method based on actual flight procedure

Abstract

This invention discloses a method for analyzing real-time multi-aircraft spacing and flight parameters based on actual flight procedures. The method includes the following steps: establishing a characterization method for the characteristic parameters of the actual flight procedures to obtain flight procedure characteristic parameters describing the multi-aircraft operation mode; determining the aircraft operation profile and establishing a multi-aircraft omnidirectional spacing calculation and constraint model; establishing a flight parameter solution model; performing real-time calculations and outputting the real-time multi-aircraft spacing and flight parameters. This invention achieves the solution of real-time multi-aircraft spacing and flight parameters through analytical methods, solving the problems of refined modeling and real-time flight parameter solution based on actual flight procedures. It provides a parameter analysis method reference and real-time decision support for accurate perception and conflict early warning of multi-aircraft operation status in future air traffic.

Description

Technical Field

[0001] This invention belongs to the field of civil aviation technology, specifically relating to a method for real-time interval analysis of multiple aircraft and flight parameters based on actual flight procedures. Background Technology

[0002] The continuous growth in air traffic volume has led to an increasing traffic density in terminal areas and around airports, posing significant challenges to safety and efficiency. Terminal airspace is characterized by high density and complex operations, requiring aircraft to follow pre-set standard flight procedures for arrival, departure, takeoff, and landing. Maintaining safe separation between aircraft is a core task of air traffic control, and accurate, real-time analysis of multi-aircraft spacing is the technological foundation for improving airspace capacity and ensuring operational safety. Furthermore, considering the needs of sustainable civil aviation operations, the analysis of multi-aircraft flight parameters such as fuel consumption and emissions contributes to refined flight management.

[0003] The main shortcomings of existing technologies are as follows: In terms of spacing calculation, the real-time position of the aircraft is not deeply integrated with the precise flight procedure, resulting in an inability to reflect the true operational status of the aircraft on the programmed trajectory; modeling is mainly based on a single operational profile (horizontal or vertical profile), lacking the comprehensive representation capability of omnidirectional spacing characteristics. In terms of constructing the basic flight parameter calculation model, parameter analysis has a single dimension, mainly relying on position and altitude information, failing to fully explore and utilize the spacing information contained in multiple flight parameters such as velocity profile, track angle, and estimated time, resulting in incomplete situational awareness; kinematic models are typically used to model and simplify the flight process to achieve rapid position decision-making and control, but the impact of aircraft performance on spacing and sustainable operational objectives cannot be considered. Therefore, there is an urgent need in this field for a multi-aircraft real-time spacing and flight parameter analysis method based on actual flight procedures, which, through close coupling with real flight procedures, achieves accurate and collaborative analysis of real-time flight parameters for multiple aircraft, thereby providing more accurate decision support for air traffic control. Summary of the Invention

[0004] The purpose of this invention is to provide a method for analyzing real-time intervals and flight parameters of multiple aircraft based on actual flight procedures, in order to solve the problem that existing methods are not applicable to the operation process with intersection points of flight procedures under omnidirectional interval constraints.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A method for analyzing real-time intervals and flight parameters of multiple aircraft based on actual flight procedures includes the following steps:

[0007] Step 1: Based on the actual flight procedure, establish a characterization method for its characteristic parameters to obtain flight procedure characteristic parameters that describe the multi-aircraft operation mode;

[0008] Step 2: Based on the flight procedure characteristic parameters obtained in Step 1, determine the aircraft operation profile and establish a multi-aircraft omnidirectional spacing calculation and constraint model;

[0009] Step 3: Based on the operational profile determined in Step 2, establish a flight parameter solution model, wherein the flight parameters include remaining range, track position, flight altitude, fuel consumption, and emission temperature rise;

[0010] Step 4: Based on the flight procedure characteristic parameters obtained in Step 1, the interval calculation and constraint model established in Step 2, and the flight parameter solution model established in Step 3, perform real-time calculations and output the real-time intervals and flight parameters of multiple aircraft.

[0011] Furthermore, step 1 includes the following sub-steps:

[0012] Step 1.1, analyze flight procedures and multi-aircraft operation characteristics:

[0013] Based on the process of multiple aircraft flying towards the same destination along the flight procedure, the approach mode is divided into following mode and convergence mode according to their relative positions; and the multi-aircraft approach mode is determined according to the flight procedure.

[0014] Step 1.2, Establish the method for horizontal profile projection of flight procedures:

[0015] Project the flight procedure in the WGS84 coordinate system onto the horizontal plane. The reference plane of the horizontal profile is the sea level. The positive direction of the horizontal axis X is the opposite direction of the final approach flight procedure. The vertical axis Y conforms to the right-hand rule with the X axis. The same end point that multiple aircraft fly to along the flight procedure is the origin of the XOY plane.

[0016] Step 1.3, establish a mathematical model of the flight procedure horizontal profile:

[0017] Based on the multi-machine access mode determined in step 1.1, a mathematical model of the horizontal profile is established.

[0018] Furthermore, in step 1.1,

[0019] Follow mode is defined as follows: when multiple aircraft fly using the same flight procedure and are at the same or similar flight altitude, the aircraft that follows the aircraft that precedes it will fly. In this case, only the longitudinal spacing requirement between the two aircraft needs to be considered.

[0020] The convergence mode is defined as follows: multiple aircraft fly using different procedures during the initial flight, and there is a common positioning point between the different flight procedures. After the positioning point, multiple aircraft fly using a common flight procedure.

[0021] Furthermore, in step 1.3, the horizontal profile mathematical model is divided into two cases according to the entry mode, specifically:

[0022] Scenario 1: The approach mode is a hybrid of follow and convergence modes. The specific flight procedure horizontal profile model is as follows:

[0023] The convergence flight procedure is simplified based on the convergence node to consist of one node. and A geometric model composed of straight lines; used for flight procedure traffic flow. It means that, among them The sequence number indicates the flight procedure; the characteristic parameters of the flight procedure are represented by... It means that, among them For traffic flow direction, The length of the flight path in the flight procedure;

[0024] One node represents a flight procedure intersection; Among the straight lines, the one connecting the origin and nodes of the XOY plane represents the outflow traffic flow flight procedure. The characteristic parameters are Remaining The straight lines represent the inflow traffic flow flight procedure. The characteristic parameters are The positive X-axis direction corresponds to the 0° direction of traffic flow.

[0025] Scenario 2: For flight procedures that only have a follow mode, the specific horizontal profile model is as follows:

[0026] The flight process contains only one flight procedure. The characteristic parameters are The positive direction of the X-axis is the 0° direction of traffic flow.

[0027] Furthermore, step 2 includes the following sub-steps:

[0028] Step 2.1, establish a horizontal profile of multi-machine operation:

[0029] The aircraft flies along a predetermined flight procedure, and its horizontal profile coincides with the horizontal profile of the flight procedure. The aircraft's horizontal profile can be obtained based on the horizontal profile of the flight procedure. The projection plane of the multi-aircraft operation horizontal profile coincides with the projection plane of the flight procedure, i.e., the XOY plane. The aircraft's heading is... The aircraft is in flight procedure When taking off, ;

[0030] Step 2.2, establish a vertical profile for multi-machine operation:

[0031] The reference plane for the aircraft's vertical profile is a vertical plane passing through the direction of the outflow traffic flow. The horizontal axis Range represents the aircraft's remaining range, the vertical axis H is the flight altitude, and the origin is the position when the altitude is 0 and the remaining range is 0.

[0032] Step 2.3, Establish a method for describing multi-aircraft flight paths:

[0033] Based on the horizontal and vertical coordinate systems obtained in steps 1.2 and 2.2, a method for describing multi-aircraft flight paths is established:

[0034] Multiple aircraft forming a flight sequence Let represent the maximum value of the aircraft sequence number. Then, the total number of aircraft contained in the aircraft sequence is . ;airplane The trajectory characteristic parameters are used It means that, among them Represents the x-axis of the flight path. Represents the vertical coordinate of the flight path. Indicates flight altitude. Indicates flight time;

[0035] in, This is the aircraft's serial number. Indicates the head machine. Indicates the preceding machine. This indicates the aircraft; the order of the aircraft sequence is determined by the remaining range. The decision was made that the remaining range of different aircraft would meet the requirements. ; This represents the x-coordinate value of the horizontal profile. This represents the ordinate value of the horizontal profile. Indicates the vertical profile flight altitude. Indicates flight time;

[0036] Step 2.4, establish a multi-aircraft flight interval calculation model:

[0037] Considering multi-aircraft omnidirectional spacing, calculation methods for longitudinal, lateral, and vertical spacing are established:

[0038]

[0039] in, The sequence number indicating the flight time; Indicates airplane exist The remaining flight distance at that moment, Indicates airplane exist The remaining flight distance at that moment; Indicates airplane exist The x-axis of time, Indicates airplane exist The x-axis represents the time interval; Indicates airplane exist The vertical axis of time, Indicates airplane exist The vertical axis of time; Indicates the total flight duration of the flight sequence; This represents the serial number of any aircraft. Indicates the longitudinal spacing between the front and rear engines; Indicates for Time machine and Lateral spacing of aircraft; Indicates the vertical spacing between the front and rear units; Indicates airplane exist Flight altitude at any given moment Indicates airplane exist Flight altitude at any given moment;

[0040] Step 2.5: Consider the minimum safety spacing of multiple aircraft in all directions, and establish constraint models for longitudinal, lateral, and vertical spacing.

[0041] Furthermore, step 3 includes the following sub-steps:

[0042] Step 3.1, establish a solution model for the remaining flight range of the aircraft:

[0043] airplane exist The remaining flight distance at that time is determined by The remaining flight distance at any given time is calculated using the following method:

[0044]

[0045] in, and These represent the flight vacuum speed and indicated airspeed, respectively. Based on the flight speed conversion method Calculated; Effective wind speed; This represents the time interval between two decision points;

[0046] Step 3.2, establish the solution model for the aircraft trajectory parameters:

[0047] airplane exist Tracks of Time From the remaining voyage and Tracks of Time It was calculated that on the horizontal plane The specific calculation method is as follows:

[0048]

[0049] The methods for calculating aircraft flight time and altitude are as follows:

[0050]

[0051] in, This is the initial flight altitude; The inclination angle of the flight path;

[0052] Step 3.3, establish the aircraft fuel consumption solution model:

[0053] First, based on the BADA model, the method for calculating fuel flow rate of the aircraft in different flight phases is determined; then, the method for calculating fuel flow rate is determined. Fuel consumption over a period of time; finally, determine the cumulative fuel consumption at each moment;

[0054] Step 3.4: Establish a solution model for global warming caused by aircraft emissions:

[0055] First, the corrected fuel flow calculation method for the aircraft was determined based on the Boeing Method-II method; then, the emissions calculation model was used to determine... The emission amounts of different pollutants within a given time period are determined; then, the total global temperature rise caused by different emissions is determined based on a temperature rise calculation model; finally, the cumulative temperature rise caused by all emissions at each time point is determined.

[0056] Furthermore, step 4 includes the following sub-steps:

[0057] Step 4.1: Determine the initial scenario parameters, input parameters, output parameters, and control parameters based on the actual flight procedure;

[0058] Step 4.2: Initialize the control parameter solver and drive the multi-aircraft scenario along the flight program based on the control parameters;

[0059] Step 4.3: Initialize the scenario and drive multiple aircraft to run according to the flight procedure based on the control parameter solver; record all running process parameters, and save all parameters after the aircraft sequence reaches the end point, including the multi-aircraft interval parameters and flight parameters.

[0060] Furthermore, in step 4.1,

[0061] The initial scenario parameters include: the flight procedure for multi-aircraft operation, the number of aircraft, and the initial flight path parameters of the aircraft;

[0062] Input parameters include: number of aircraft, basic performance parameters required for aircraft fuel consumption and temperature rise calculation, and safety interval constraint parameters;

[0063] Output parameters include: real-time aircraft trajectory, fuel consumption and temperature rise, and multi-aircraft spacing;

[0064] Control parameters include: aircraft sequence airspeed and aircraft sequence track inclination.

[0065] This invention also provides a multi-aircraft real-time interval and flight parameter analysis system based on actual flight procedures, comprising:

[0066] At least one processor; and

[0067] A memory that is communicatively connected to the at least one processor;

[0068] The memory stores instructions that can be executed by the at least one processor to enable the system to perform the method.

[0069] The present invention also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the method described thereon.

[0070] Beneficial effects:

[0071] This invention achieves the solution of real-time intervals and flight parameters for multiple aircraft using analytical methods, and also considers the calculation of fuel consumption and emission parameters. It provides a parameter analysis method reference and real-time decision support for accurate perception and conflict early warning of multi-aircraft operational situations in future air traffic. This invention also constructs a method for characterizing flight procedure characteristic parameters, reasonably representing the characteristics based on actual flight procedures. Through modeling and analytical methods, this invention achieves the analysis of real-time intervals and flight parameters for multiple aircraft, improving the scalability of the method and enabling it to adapt to more complex operational scenarios, providing a methodological reference for future applications. Attached Figure Description

[0072] Figure 1 This is a diagram illustrating the architecture of the multi-aircraft real-time interval and flight parameter analysis method based on actual flight procedures of this invention.

[0073] Figure 2 This is a schematic diagram of the approach process based on the actual flight procedure in an embodiment of the present invention;

[0074] Figure 3 This is a schematic diagram of the horizontal cross-section of the flight path and flight track after coordinate transformation according to the present invention;

[0075] Figure 4 This is a schematic diagram of the vertical cross-section of the route and flight path after coordinate transformation according to the present invention;

[0076] Figure 5 This is a schematic diagram of the decision results in an embodiment of the present invention. Detailed Implementation

[0077] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0078] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings.

[0079] Please see Figures 1 to 5 This embodiment provides a specific implementation process for a multi-aircraft real-time interval and flight parameter analysis method based on actual flight procedures. For ease of explanation, this embodiment uses the standard multi-aircraft terminal arrival process (i.e., the aircraft approach process) as an example, and the specific steps are as follows:

[0080] Step 1: Based on the actual flight procedure, establish a characterization method for its characteristic parameters to obtain flight procedure characteristic parameters that describe the multi-aircraft operation mode;

[0081] Specifically, it includes the following sub-steps:

[0082] Step 1.1, analyze flight procedures and multi-aircraft operation characteristics:

[0083] Based on the process of multiple aircraft flying towards the same destination along the flight procedure, it is divided into following mode and convergence mode according to their mutual positional relationship;

[0084] The follow mode is defined as: multiple aircraft flying using the same procedure, with a small difference in altitude between the two aircraft, which can be regarded as flying at the same altitude for a very short period of time. This scenario can be approximated as the rear aircraft following the front aircraft. At this time, only the longitudinal spacing requirement between the two aircraft needs to be considered.

[0085] The convergence mode is defined as follows: multiple aircraft fly using different procedures during the initial flight, and there is a common positioning point between the different flight procedures. After the positioning point, multiple aircraft fly using a common flight procedure.

[0086] like Figure 2 The diagram shows four flight procedures for a multi-aircraft approach at an airport in this embodiment: FITBO, HON, NUGAR, and TOBID. The FITBO, HON, and NUGAR procedures terminate at the BNN navigation point, while the TOBID procedure terminates at another unmarked navigation point. For HON and NUGAR with TOBID, the flight procedures converge at the TOBID location point; for FITBO with HON and NUGAR, the flight procedures converge at the SOPIT location point.

[0087] Step 1.2, Establish the method for horizontal profile projection of flight procedures:

[0088] Project the flight procedure in the WGS84 coordinate system onto the horizontal plane. The reference plane of the horizontal profile is the sea level. The positive direction of the horizontal axis X is the opposite direction of the final approach flight procedure. The vertical axis Y conforms to the right-hand rule with the X axis. The same end point that multiple aircraft fly towards along the flight procedure is the origin of the XOY plane. That is, the origin O is the projection point of the approach trajectory end point on the reference plane.

[0089] Step 1.3, establish a mathematical model of the flight procedure horizontal profile:

[0090] Based on the multi-machine approach mode determined in step 1.1, a horizontal profile mathematical model is established. The horizontal profile mathematical model is divided into two cases according to the approach mode, as follows:

[0091] Scenario 1: The approach mode is a hybrid of follow and convergence modes. The specific flight procedure horizontal profile model is as follows:

[0092] The convergence flight procedure is simplified based on the convergence node to consist of one node. and A geometric model composed of straight lines; used for flight procedure traffic flow. It means that, among them The sequence number indicates the flight procedure; the characteristic parameters of the flight procedure are represented by... It means that, among them For traffic flow direction, For the flight path length of the flight procedure, such as Figure 3 As shown.

[0093] One node represents a flight procedure intersection; Among the straight lines, the one connecting the origin and nodes of the XOY plane represents the outflow traffic flow flight procedure. The characteristic parameters are Remaining The straight lines represent the inflow traffic flow flight procedure. The characteristic parameters are The positive direction of the X-axis is the 0° direction of traffic flow.

[0094] The specific values ​​of the important parameters in this embodiment are as follows: , Randomly generated within the [20, 100] km interval; the inflow traffic flow flight procedure during the arrival process consists of 2 routes. The inflow traffic flow flight direction angle is randomly generated, ensuring that the angle between any two flight paths is not less than 15°.

[0095] It should be noted that in this step... Based on specific experiments, adjustments can be made in other embodiments of the present invention according to actual needs.

[0096] Scenario 2: For flight procedures that only have a follow mode, the specific horizontal profile model is as follows:

[0097] The flight process contains only one flight procedure. The characteristic parameters are The positive direction of the X-axis is the 0° direction of traffic flow.

[0098] This situation is not involved in this embodiment.

[0099] Step 2: Based on the flight procedure characteristic parameters obtained in Step 1, determine the aircraft operation profile and establish a multi-aircraft omnidirectional spacing calculation and constraint model;

[0100] Specifically, it includes the following sub-steps:

[0101] Step 2.1, establish a horizontal profile of multi-machine operation:

[0102] The aircraft flies along a predetermined flight procedure, and its horizontal profile coincides with the horizontal profile of the flight procedure. The aircraft's horizontal profile can be obtained based on the horizontal profile of the flight procedure. The projection plane of the multi-aircraft operation horizontal profile coincides with the projection plane of the flight procedure, i.e., the XOY plane. The aircraft's heading is... The aircraft is in flight procedure When taking off, .

[0103] Step 2.2, establish a vertical profile for multi-machine operation:

[0104] The reference plane for the aircraft's vertical profile is a vertical plane passing through the direction of the outflow traffic flow. The horizontal axis Range represents the aircraft's remaining range, the vertical axis H is the flight altitude, and the origin is the position when the altitude is 0 and the remaining range is 0.

[0105] Step 2.3, Establish a method for describing multi-aircraft flight paths:

[0106] Based on the horizontal and vertical coordinate systems obtained in steps 1.2 and 2.2, a method for describing multi-aircraft flight paths is established:

[0107] Multiple aircraft forming a flight sequence Let represent the maximum value of the aircraft sequence number. Then, the total number of aircraft contained in the aircraft sequence is . ;airplane The trajectory characteristic parameters are used It means that, among them Represents the x-axis of the flight path. Represents the vertical coordinate of the flight path. Indicates flight altitude. Indicates flight time;

[0108] in, This is the aircraft's serial number. Indicates the head machine. Indicates the preceding machine. This indicates the aircraft; the order of the aircraft sequence is determined by the remaining range. The decision was made that the remaining range of different aircraft would meet the requirements. ; This represents the x-coordinate value of the horizontal profile. This represents the ordinate value of the horizontal profile. Indicates the vertical profile flight altitude. Indicates flight time.

[0109] It should be noted that in this step... Based on specific experiments, adjustments can be made in other embodiments of the present invention according to actual needs.

[0110] Step 2.4, establish a multi-aircraft flight interval calculation model:

[0111] like Figure 3 and Figure 4 As shown, considering multi-aircraft omnidirectional spacing, the calculation methods for longitudinal, lateral, and vertical spacing are established:

[0112]

[0113] in, The sequence number indicating the flight time; Indicates airplane exist The remaining flight distance at that moment, Indicates airplane exist The remaining flight distance at that moment; Indicates airplane exist The x-axis of time, Indicates airplane exist The x-axis represents the time interval; Indicates airplane exist The vertical axis of time, Indicates airplane exist The vertical axis of time; Indicates the total flight duration of the flight sequence; This represents the serial number of any aircraft. Indicates the longitudinal spacing between the front and rear engines; Indicates for Time machine and Lateral spacing of aircraft; Indicates the vertical spacing between the front and rear units; Indicates airplane exist Flight altitude at any given moment Indicates airplane exist The flight altitude at any given moment.

[0114] Step 2.5, establish a multi-aircraft flight interval constraint model:

[0115] Considering the minimum safety separation for multi-aircraft omnidirectional operations, constraint models for longitudinal, lateral, and vertical separations are established, specifically as follows:

[0116]

[0117] in, , and These are the constraint values ​​for longitudinal, lateral, and vertical intervals, respectively.

[0118] In this embodiment, , , There are differences depending on the aircraft type classification. The specific aircraft types and their classifications are shown in Table 1.

[0119] Table 1: Aircraft Types and CCAR Classifications

[0120]

[0121] The minimum longitudinal wake safety intervals for different aircraft type combinations are shown in Table 2.

[0122] Table 2: Minimum longitudinal wake safety separation

[0123]

[0124] Step 3: Based on the operational profile determined in Step 2, establish a flight parameter solution model. The flight parameters include remaining range, track position, flight altitude, fuel consumption, and emission temperature rise.

[0125] Specifically, it includes the following sub-steps:

[0126] Step 3.1, establish a solution model for the remaining flight range of the aircraft:

[0127] airplane exist The remaining flight distance at any given time can be determined by The remaining flight distance at any given time is calculated using the following method:

[0128]

[0129] in, and These represent the flight vacuum speed and indicated airspeed, respectively. It can be based on the flight speed conversion method. Calculated; Effective wind speed; It represents the time interval between two decision moments.

[0130] In this embodiment, the initial total range of the lead aircraft is 160km, and the initial total range of the remaining aircraft in the sequence is initialized based on the interval distance with respect to the lead aircraft. The initial interval is... Randomly generated within the interval; Randomly generated within the interval [240, 330] kt; =10 s.

[0131] Step 3.2, establish the solution model for the aircraft trajectory parameters:

[0132] airplane exist Tracks of Time From the remaining voyage and Tracks of Time It was calculated that on the horizontal plane The specific calculation method is as follows:

[0133]

[0134] The methods for calculating aircraft flight time and altitude are as follows:

[0135]

[0136] in, This is the initial flight altitude; The inclination angle of the flight path.

[0137] In this embodiment, the initial flight altitude Randomly generated within the interval [6, 8] km, with the initial altitude of the following aircraft not lower than that of the preceding aircraft; since all aircraft are initially in level flight, the initial... =0°.

[0138] Step 3.3, establish the aircraft fuel consumption solution model:

[0139] First, based on the BADA model, the method for calculating fuel flow rate of the aircraft in different flight phases is determined; then, the method for calculating fuel flow rate is determined. Fuel consumption over a period of time; finally, determine the cumulative fuel consumption at each moment.

[0140] Step 3.4: Establish a solution model for global warming caused by aircraft emissions:

[0141] First, the corrected fuel flow calculation method for the aircraft was determined based on the Boeing Method-II method; then, the emissions calculation model was used to determine... The emission amounts of different pollutants within a given time period are determined; then, the total global temperature rise caused by different emissions is determined based on a temperature rise calculation model; finally, the cumulative temperature rise caused by all emissions at each time point is determined.

[0142] Step 4: Based on the flight procedure characteristic parameters obtained in Step 1, the interval calculation and constraint model established in Step 2, and the flight parameter solution model established in Step 3, perform real-time calculations and output the real-time intervals and flight parameters of multiple aircraft.

[0143] Specifically, it includes the following sub-steps:

[0144] Step 4.1: Determine the initial scenario parameters, input parameters, output parameters, and control parameters based on the actual flight procedure;

[0145] The initial scenario parameters include: the flight procedure for multi-aircraft operation, the number of aircraft, and the initial flight path parameters of the aircraft;

[0146] Input parameters include: number of aircraft, basic performance parameters required for aircraft fuel consumption and temperature rise calculation, and safety interval constraint parameters;

[0147] Output parameters include: real-time aircraft trajectory, fuel consumption and temperature rise, and multi-aircraft spacing;

[0148] Control parameters include: aircraft sequence airspeed and aircraft sequence track inclination.

[0149] In this embodiment, the number of aircraft The relevant parameters of the aircraft sequence are shown in Table 3:

[0150] Table 3: Aircraft Sequence and Initial Position Parameters

[0151]

[0152] Step 4.2: Initialize the control parameter solver and drive the multi-aircraft scenario along the flight program based on the control parameters;

[0153] Step 4.3: Initialize the scenario and drive multiple aircraft to run according to the flight procedure based on the control parameter solver. Record all parameters during the operation process. After the aircraft sequence reaches the end point, save all parameters, including the multi-aircraft interval parameters and flight parameters.

[0154] After completing a round of decision-making, output and save the results. The decision results for all control variables of the aircraft and their corresponding flight parameters, as well as the fuel consumption, temperature rise, and multi-aircraft spacing corresponding to each decision step. The flight path results over time are as follows: Figure 5As shown, the spacing between the aircraft meets safety constraints, the total fuel consumption is approximately 5.40 tons, and the total temperature rise is 1.36 × 10⁻⁶ tons. -11 ℃.

[0155] Based on the complete process and implementation details disclosed in the above method embodiments, those skilled in the art will understand that the present invention also provides a flight data parsing system and a corresponding storage medium for implementing the method.

[0156] The flight data analysis system, as a preferred implementation, is based on the synergy of software and hardware to achieve the aforementioned method. This system typically includes at least one processor and a memory communicatively connected to the processor. The memory stores computer program instructions. When these instructions are executed by the processor, the control system sequentially performs the following operations: establishing a characteristic parameter representation based on the input actual flight program data; determining the aircraft operational profile and constructing a multi-aircraft omnidirectional spacing calculation and constraint model; establishing a flight parameter solution model including remaining range, flight path position, flight altitude, fuel consumption, and emission temperature rise; and finally performing real-time calculations and outputting the real-time multi-aircraft spacing and flight parameter results. This system, as the physical carrier of the method, can provide accurate real-time decision support for air traffic control.

[0157] Accordingly, the computer program instructions for implementing the above method steps can be stored in a computer-readable storage medium (e.g., USB flash drive, portable hard drive, read-only memory, random access memory, magnetic disk, or optical disk). When the program in the storage medium is read into a computer or dedicated processor system and executed, the parsing method described in this invention can be implemented.

[0158] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for analyzing real-time intervals and flight parameters of multiple aircraft based on actual flight procedures, characterized in that: Includes the following steps: Step 1: Based on the actual flight procedure, establish a characterization method for its characteristic parameters to obtain flight procedure characteristic parameters that describe the multi-aircraft operation mode; Step 1 includes the following sub-steps: Step 1.1, analyze flight procedures and multi-aircraft operation characteristics: Based on the process of multiple aircraft flying towards the same destination along the flight procedure, the approach mode is divided into following mode and convergence mode according to their relative positions; and the multi-aircraft approach mode is determined according to the flight procedure. Follow mode is defined as follows: when multiple aircraft fly using the same flight procedure and are at the same or similar flight altitude, the aircraft that follows the aircraft that precedes it will fly. In this case, only the longitudinal spacing requirement between the two aircraft needs to be considered. The convergence mode is defined as follows: multiple aircraft fly using different procedures during the initial flight, and there is a common positioning point between the different flight procedures. After the positioning point, multiple aircraft fly using a common flight procedure. Step 1.2, Establish the method for horizontal profile projection of flight procedures: Project the flight procedure in the WGS84 coordinate system onto the horizontal plane. The reference plane of the horizontal profile is the sea level. The positive direction of the horizontal axis X is the opposite direction of the final approach flight procedure. The vertical axis Y conforms to the right-hand rule with the X axis. The same end point that multiple aircraft fly to along the flight procedure is the origin of the XOY plane. Step 1.3, establish a mathematical model of the flight procedure horizontal profile: Based on the multi-machine access mode determined in step 1.1, establish a mathematical model of the horizontal profile; The mathematical model of the horizontal profile is divided into two cases according to the entry mode, as follows: Scenario 1: The approach mode is a hybrid of follow and convergence modes. The specific flight procedure horizontal profile model is as follows: The convergence flight procedure is simplified based on the convergence node to consist of one node. and A geometric model composed of straight lines; used for flight procedure traffic flow. It means that among them The sequence number indicates the flight procedure; the characteristic parameters of the flight procedure are represented by... It means that among them For traffic flow direction, The length of the flight path in the flight procedure; One node represents a flight procedure intersection; Among the straight lines, the one connecting the origin and nodes of the XOY plane represents the outflow traffic flow flight procedure. The characteristic parameters are Remaining The straight lines represent the inflow traffic flow flight procedure. The characteristic parameters are The positive X-axis direction corresponds to the 0° direction of traffic flow. Scenario 2: For flight procedures that only have a follow mode, the specific horizontal profile model is as follows: The flight process contains only one flight procedure. The characteristic parameters are The positive X-axis direction corresponds to the 0° direction of traffic flow. Step 2: Based on the flight procedure characteristic parameters obtained in Step 1, determine the aircraft operation profile and establish a multi-aircraft omnidirectional spacing calculation and constraint model; Step 3: Based on the operational profile determined in Step 2, establish a flight parameter solution model, wherein the flight parameters include remaining range, track position, flight altitude, fuel consumption, and emission temperature rise; Step 4: Based on the flight procedure characteristic parameters obtained in Step 1, the interval calculation and constraint model established in Step 2, and the flight parameter solution model established in Step 3, perform real-time calculations and output the real-time intervals and flight parameters of multiple aircraft.

2. The method according to claim 1, characterized in that: Step 2 includes the following sub-steps: Step 2.1, establish a horizontal profile of multi-machine operation: The aircraft flies along a predetermined flight procedure, and its horizontal profile coincides with the horizontal profile of the flight procedure. The aircraft's horizontal profile can be obtained based on the horizontal profile of the flight procedure. The projection plane of the multi-aircraft operation horizontal profile coincides with the projection plane of the flight procedure, i.e., the XOY plane. The aircraft's heading is... The aircraft is in flight procedure When taking off, ; Step 2.2, establish a vertical profile for multi-machine operation: The reference plane for the aircraft's vertical profile is a vertical plane passing through the direction of the outflow traffic flow. The horizontal axis Range represents the aircraft's remaining range, the vertical axis H is the flight altitude, and the origin is the position when the altitude is 0 and the remaining range is 0. Step 2.3, Establish a method for describing multi-aircraft flight paths: Based on the horizontal and vertical coordinate systems obtained in steps 1.2 and 2.2, a method for describing multi-aircraft flight paths is established: Multiple aircraft forming a flight sequence Let represent the maximum value of the aircraft sequence number. Then, the total number of aircraft contained in the aircraft sequence is . ;airplane The trajectory characteristic parameters are used It means that among them Represents the x-axis of the flight path. Represents the vertical coordinate of the flight path. Indicates flight altitude. Indicates flight time; in, For the aircraft's serial number, Indicates the head machine. Indicates the preceding machine. This indicates the aircraft; the order of the aircraft sequence is determined by the remaining range. The decision was made that the remaining range of different aircraft would meet the requirements. ; This represents the x-coordinate value of the horizontal profile. This represents the ordinate value of the horizontal profile. Indicates the vertical profile flight altitude. Indicates flight time; Step 2.4, establish a multi-aircraft flight interval calculation model: Considering multi-aircraft omnidirectional spacing, calculation methods for longitudinal, lateral, and vertical spacing are established: in, The sequence number indicating the flight time; Indicates airplane exist The remaining flight distance at that moment, Indicates airplane exist The remaining flight distance at that moment; Indicates airplane exist The x-axis of time, Indicates airplane exist The x-axis represents the time interval; Indicates airplane exist The vertical axis of time, Indicates airplane exist The vertical axis of time; Indicates the total flight duration of the flight sequence; This represents the serial number of any aircraft. Indicates the longitudinal spacing between the front and rear engines; Indicates for Time machine and Lateral spacing of aircraft; Indicates the vertical spacing between the front and rear units; Indicates airplane exist Flight altitude at any given moment Indicates airplane exist Flight altitude at any given moment; Step 2.5: Consider the minimum safety spacing of multiple aircraft in all directions, and establish constraint models for longitudinal, lateral, and vertical spacing.

3. The method according to claim 2, characterized in that: Step 3 includes the following sub-steps: Step 3.1, establish a solution model for the remaining flight range of the aircraft: airplane exist The remaining flight distance at that time is determined by The remaining flight distance at any given time is calculated using the following method: in, and These represent the flight vacuum speed and indicated airspeed, respectively. Based on the flight speed conversion method Calculated; Effective wind speed; This represents the time interval between two decision points; Step 3.2, establish the solution model for the aircraft trajectory parameters: airplane exist Tracks of Time From the remaining voyage and Tracks of Time It was calculated that on the horizontal plane The specific calculation method is as follows: The methods for calculating aircraft flight time and altitude are as follows: in, This is the initial flight altitude; The inclination angle of the flight path; Step 3.3, establish the aircraft fuel consumption solution model: First, based on the BADA model, the method for calculating fuel flow rate of the aircraft in different flight phases is determined; then, the method for calculating fuel flow rate is determined. Fuel consumption over a period of time; finally, determine the cumulative fuel consumption at each moment; Step 3.4: Establish a solution model for global warming caused by aircraft emissions: First, the corrected fuel flow calculation method for the aircraft was determined based on the Boeing Method-II method; then, the emissions calculation model was used to determine... The emission amounts of different pollutants within a given time period are determined; then, the total global temperature rise caused by different emissions is determined based on a temperature rise calculation model; finally, the cumulative temperature rise caused by all emissions at each time point is determined.

4. The method according to claim 1, characterized in that: Step 4 includes the following sub-steps: Step 4.1: Determine the initial scenario parameters, input parameters, output parameters, and control parameters based on the actual flight procedure; Step 4.2: Initialize the control parameter solver and drive the multi-aircraft scenario along the flight program based on the control parameters; Step 4.3: Initialize the scenario and drive multiple aircraft to run according to the flight procedure based on the control parameter solver; record all running process parameters, and save all parameters after the aircraft sequence reaches the end point, including the multi-aircraft interval parameters and flight parameters.

5. The method according to claim 4, characterized in that: In step 4.1, The initial scenario parameters include: the flight procedure for multi-aircraft operation, the number of aircraft, and the initial flight path parameters of the aircraft; Input parameters include: number of aircraft, basic performance parameters required for aircraft fuel consumption and temperature rise calculation, and safety interval constraint parameters; Output parameters include: real-time aircraft trajectory, fuel consumption and temperature rise, and multi-aircraft spacing; Control parameters include: aircraft sequence airspeed and aircraft sequence track inclination.

6. A multi-aircraft real-time interval and flight parameter analysis system based on actual flight procedures, characterized in that: include: At least one processor; as well as A memory that is communicatively connected to the at least one processor; The memory stores instructions that can be executed by the at least one processor to enable the system to perform the method as described in any one of claims 1-5.

7. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, it implements the method as described in any one of claims 1-5.

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