An aerodynamic trajectory simulation method satisfying regulatory constraints
By using a segmented performance parameter system and an intelligent backtracking correction strategy, the difficulties in simulating the nonlinear characteristics of aerodynamic parameters and satisfying control constraints in traditional trajectory simulation methods have been solved, achieving efficient and accurate aircraft trajectory simulation and optimizing airspace resource utilization.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- 中电莱斯信息系统有限公司
- Filing Date
- 2026-04-17
- Publication Date
- 2026-07-21
AI Technical Summary
Traditional flight path simulation methods struggle to accurately simulate the nonlinear characteristics of aerodynamic parameters, resulting in low reliability of simulated flight states and difficulty in meeting regulatory constraints, thus impacting the safety and efficiency of air transport systems.
A segmented performance parameter system is used to describe aircraft motion. Combined with control constraints, a dynamic flight process-flight rule mapping table is created. The trajectory is iteratively adjusted through an intelligent backtracking correction strategy to meet control conditions.
It improves the accuracy and efficiency of flight path simulation, enabling low-cost and high-efficiency simulation of aircraft four-dimensional trajectories, optimizing airspace resource utilization, and enhancing the safety margin and operational efficiency of air transport systems.
Smart Images
Figure CN122433591A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of flight path simulation, and more particularly to an aerodynamic flight path simulation method that satisfies regulatory constraints. Background Technology
[0002] With the continuous growth of global air traffic, the contradiction between airspace resource scarcity and air transport safety has become increasingly prominent. Therefore, it is urgent to build a next-generation air traffic control automation system based on high-precision trajectory prediction.
[0003] Traditional flight path simulation methods abstract an aircraft as a point mass to describe its motion. Based on Newton's second law, aerodynamics is simplified to the resultant force acting on the aircraft's center of mass, assuming a constant acceleration, and mathematically expressing this as a set of linear differential equations for the trajectory. The point mass model directly generates the trajectory by solving these integral differential equations, eliminating the need for complex data training and resulting in lower computational resource consumption. However, the simplification of the model also introduces limitations, making it difficult to accurately simulate the nonlinear characteristics of aerodynamic parameters, thus significantly reducing the reliability of the simulated flight state.
[0004] This method comprehensively considers the influence of aircraft and regulatory factors, using an aircraft performance model and a segmented performance parameter system to describe the aircraft's motion process. The aircraft performance model integrates aerodynamic, mass, and engine performance parameters, supporting simulation of the entire process from takeoff to landing. Simultaneously, by integrating regulatory constraints into the flight plan, it enables corrections to the flight trajectory. This method simulates the four-dimensional trajectory data of aircraft according to regulatory constraints, helping air traffic control units compare the feasibility of different route planning schemes during the strategic phase, analyze the rationality of flight schedules during the pre-tactical phase, and efficiently and cost-effectively utilize limited airspace resources, thereby improving the safety margin and operational efficiency of the air transport system. Summary of the Invention
[0005] Purpose of the invention: The technical problem to be solved by the present invention is to provide an aerodynamic trajectory simulation method that meets regulatory constraints, addressing the shortcomings of the existing technology.
[0006] To address the aforementioned technical problems, this invention discloses an aerodynamic trajectory simulation method that satisfies regulatory constraints, comprising the following steps:
[0007] Step 1: Construct a sequence of key points for the flight path based on the coordinates of the take-off and landing airports, arrival and departure procedure parameters, and latitude and longitude data of the planned waypoints in the aircraft flight plan, and add key point control constraints;
[0008] Step 2: Establish a mapping table from flight process to flight rules;
[0009] Step 3: According to the currently effective flight rules, calculate the subsequent waypoint based on the current waypoint and subsequent key points;
[0010] Step 4: Determine whether the flight has completed the current segment based on the calculated subsequent waypoints, and update the heading angle for the next segment;
[0011] Step 5: If the next critical point is reached, determine whether the flight path meets the speed and altitude control constraints of the critical point.
[0012] Step 6: When a critical point control constraint is violated, a backtracking correction strategy is created, and the trajectory is recalculated iteratively until the control constraint conditions of the critical point are met.
[0013] Step 7: Execute the flight rule sequence sequentially until all flight rules have been executed, and output the final simulated flight track data.
[0014] The process of constructing the sequence of key points in the flight path described in step 1 is as follows:
[0015] Step 1-1: Combine the coordinates of the take-off and landing airports, arrival and departure procedure parameters, and latitude and longitude data of the planned waypoints in the flight plan, and obtain the set of key points for the entire flight route through spatial topology analysis;
[0016] Steps 1-2: Add height and speed limits to the corresponding key points.
[0017] Step 2 specifically involves establishing a mapping table from flight process to flight rules based on the aircraft's flight speed and altitude profiles. The specific process is as follows:
[0018] Step 2-1: According to the flight altitude profile, the flight phase includes the climb phase, cruise phase and descent phase. The flight rules include speed, altitude and distance. The values of the rules are determined by the flight phase.
[0019] Step 2-2: Based on the flight speed profile of the climb phase, decompose the climb phase flight process into an acceleration climb phase, etc. Climbing section, etc. During the climb and acceleration phases, kinematic and dynamic flight rules are established to correspond to the flight process.
[0020] Steps 2-3: Based on the flight speed and altitude profiles of the cruise segment, decompose the cruise segment flight process into equal parts. Climbing section, etc. The descent phase, acceleration level flight phase, deceleration level flight phase, and constant speed level flight phase are used to create kinematic and dynamic flight rules corresponding to the flight process.
[0021] Steps 2-4: Based on the flight speed profile during the descent phase, decompose the descent process into a deceleration descent phase, etc. Descent segment, etc. During the descent and deceleration level flight phases, kinematic and dynamic flight rules are created corresponding to the sub-flight processes;
[0022] Steps 2-5: Add the rules for each flight process in the climb, cruise, and descent phases to the flight rule library in sequence, and create a mapping table from flight processes to flight rules;
[0023] The calculation steps for subsequent waypoints described in step 3 include:
[0024] Step 3-1: Set the currently effective dynamic flight rules according to the current flight phase;
[0025] Step 3-2: Calculate the initial waypoints based on the aircraft performance model and the set of key points for the entire flight.
[0026] Step 3-3: Based on the aircraft performance model, calculate the thrust, drag, energy sharing factor, climb and descent rate, fuel consumption, and altitude for the next track point.
[0027] Steps 3-4: Calculate the speed, distance, pitch angle, and mass of the next waypoint based on the currently effective flight rules and the performance model.
[0028] Step 4, which describes updating the heading angle for the next leg, includes:
[0029] Step 4-1: Compare the flight distance of the next waypoint with the distance to the key point. If the flight distance is less than or equal to the distance to the key point, it means that the flight has not completed the current segment. In this case, the track angle of the next waypoint remains unchanged.
[0030] Step 4-2: If the flight distance is greater than the distance to the key point, it means that the flight has completed the current segment of flight, and the track angle of the next point is updated.
[0031] In step 5, the process of determining whether the flight path meets the speed and altitude control constraints at key points is as follows:
[0032] Step 5-1: Compare the speed of the next waypoint with the speed range of the key point, and compare the altitude of the next waypoint with the altitude range of the key point;
[0033] Step 5-2: If the speed of the waypoint is within the speed range of the key point and the altitude of the waypoint is within the range of the key point, it means that the waypoint meets the speed and altitude limits of the key point.
[0034] Step 5-3: If the speed of the waypoint is not within the speed range of the critical point, or the altitude of the waypoint is not within the altitude range of the critical point, it means that the waypoint cannot meet the speed and altitude restrictions of the critical point.
[0035] The specific steps for creating a backtracking correction strategy in step 6, which involves violating critical point control constraints, include:
[0036] Step 6-1: If the next waypoint cannot simultaneously meet the speed and altitude limits of the critical point, it indicates that the waypoint violates the control constraints of the critical point. The modified flight rules with adaptive constraints are added according to the flight phase.
[0037] Step 6-2: Calculate the new track start point index. Delete the set of waypoints with an index greater than 1. Waypoints;
[0038] Step 6-3: Repeat steps 3, 4, and 5 to iteratively calculate the waypoints until the constraints of the key points are met, or the number of backtracking corrections exceeds the upper limit of the number of backtracking corrections.
[0039] The modified flight rule update described in step 6-1 includes: assuming the current state is the [number]th ... The following are the update formulas for the velocity and altitude items of all newly added rules in the subsequent backtracking correction strategy:
[0040]
[0041]
[0042] in, For the next waypoint speed, For the next waypoint The height.
[0043] Step 7, which involves sequentially executing the flight rule sequence, includes:
[0044] Step 7-1: Compare the attributes of the next waypoint with the rule items of the current flight rule according to the flight rules, and update the rule status;
[0045] Step 7-2: Execute the next flight rule sequentially until all flight rules have been executed, then end the trajectory generation calculation and output the final simulated trajectory data.
[0046] The next trackpoint attribute described in step 7-1 is its data item, which includes speed data, altitude data, and distance data.
[0047] Beneficial effects:
[0048] This invention fully considers the impact of control constraints on trajectory generation. By intervening in the trajectory at key points, it creates an intelligent backtracking and correction strategy, simulates the control behavior of controllers, and iteratively adjusts the speed and altitude of the aircraft. At the same time, by creating a dynamic flight process-flight rule mapping table, it establishes an explicit correlation between the aircraft's aerodynamic parameters and flight constraints, reduces the complexity of the simulation algorithm, achieves millisecond-level constraint verification, and greatly shortens the simulation time of the trajectory. Attached Figure Description
[0049] Figure 1 This is a schematic diagram of the overall process of the present invention.
[0050] Figure 2 This is a horizontal cross-sectional view of the key points of the single-track flight path and the simulated flight path in an embodiment of the present invention.
[0051] Figure 3 This is a vertical cross-sectional view of the simulated flight path under each flight process of a single flight path in an embodiment of the present invention. Detailed Implementation
[0052] This invention proposes an aerodynamic trajectory simulation method that satisfies regulatory constraints. It creates a dynamic flight process-flight rule mapping table, generates a four-dimensional trajectory in segments, and fully considers the impact of regulatory constraints on trajectory generation, creating an intelligent backtracking correction strategy to obtain aircraft trajectories with better simulation results.
[0053] The embodiments of the present invention will now be described with reference to the accompanying drawings.
[0054] Combination Figure 1 An aerodynamic trajectory simulation method that satisfies regulatory constraints includes the following steps:
[0055] Step 1: Construct a sequence of critical points for the flight path based on the airport coordinates, arrival and departure procedure parameters, and planned waypoint latitude and longitude data from the aircraft's flight plan. Add critical point control constraints as follows:
[0056] Step 1-1, denote the set of takeoff and landing airport points in the flight plan as... The set of entry procedure points is as follows The set of departure procedure points is as follows Waypoint set ,in, , , These are the number of arrival procedure points, departure procedure points, and waypoints, respectively.
[0057] Steps 1-2 involve performing spatial topology analysis on the arrival procedures, departure procedures, and waypoints to calculate the departure procedure point set. Meeting at waypoints The intersection of these points yields the set of connection points between waypoints and departure procedure points. Calculate the set of entry procedure points Meeting at waypoints The intersection of these points yields the set of connection points between waypoints and approach procedure points. ;
[0058] Steps 1-3, specify the take-off and landing airport locations, Entry procedure points Pre-departure procedure point, and The waypoints between them are linked together to form an ordered set of key points. , means as follows:
[0059]
[0060] in, For the total number of key points, the first Note the key points as follows Key points The vector form is represented as follows:
[0061]
[0062] in, , , , , and They represent the first Name, code, longitude, latitude, distance, and regulatory constraints of each key point;
[0063] Steps 1-4: Based on the navigation data, add control constraints to the corresponding key points, including altitude and speed limits, as shown below:
[0064]
[0065] in, , , and They represent key points respectively. Lower limit of altitude, upper limit of altitude, lower limit of speed, and upper limit of speed;
[0066] Step 2: Based on the flight speed and altitude profiles, establish a mapping table from flight process to flight rules, as follows:
[0067] Step 2-1: According to the flight altitude profile, the flight phase includes the climb phase, cruise phase and descent phase. Each flight phase contains several flight processes. Different flight processes correspond to different flight rules. The flight rules consist of dynamic constraints, kinematic constraints and termination conditions. The kinematic constraints include three rule items: speed, altitude and flight distance (i.e., the horizontal distance already flown from the takeoff airport). The rule items can be omitted.
[0068] Step 2-2: Based on the flight speed profile of the climb phase, decompose the climb phase into four discrete flight processes, denoted as... ,in, Indicates the accelerated climb phase. Indicates etc. Climbing section, Indicates etc. Climbing section, Indicates the acceleration phase of level flight;
[0069] Create a mapping function from the climb phase flight process to flight rules. For any flight process during the climb phase ,have ,in, This is a set of flight rules for the climb phase. ;
[0070] The mapping relationship between the climb phase flight process and flight rules is shown in the table below:
[0071] Table 1. Mapping Relationship between Climb Phase Flight Process and Flight Rules
[0072] Flight process Flight rules Accelerated Climb Section Termination condition: speed , Calculate the speed for cruising wait Climbing section Speed constraint: speed , Cruise speed calculation termination condition: altitude , For climbing and changing altitude wait Climbing section Speed constraint: speed , To correct the Mach velocity termination condition: height , cruising altitude Acceleration Level Flight Height constraint: height , Cruise altitude termination condition: speed , For cruise vacuum speed
[0073] Steps 2-3: Based on the flight speed and altitude profiles of the cruise segment, decompose the cruise segment into a discrete flight process, denoted as... ,in, Indicates the constant speed level flight phase;
[0074] Create a projection function from the cruise segment flight process to flight rules. For any flight process during the cruise segment ,have ,in, This is a set of flight rules for the cruise segment, and the cruise segment flight rules are... ;
[0075] The mapping relationship between the cruise phase flight process and flight rules is shown in the table below:
[0076] Table 2. Mapping Relationship between Cruise Segment Flight Process and Flight Rules
[0077] Flight process Flight rules Constant speed level flight section Speed constraint: speed , Cruise vacuum speed altitude constraint: altitude , Cruise altitude termination condition: flight distance , For cruising horizontal distance
[0078] Steps 2-4: Based on the flight velocity profile of the descent phase, decompose the descent phase into four discrete flight processes, denoted as... ,in, Indicates the deceleration descent phase. Indicates etc. Descent phase, Indicates etc. Descent phase, Indicates the deceleration and level flight phase;
[0079] Create a mapping function from the descent phase of flight to flight rules. For any flight process during the descent phase ,have ,in, This is the set of flight rules for the descent phase. ;
[0080] The mapping relationship between the descent phase of flight and flight rules is shown in the table below:
[0081] Table 3. Mapping Relationship between Descent Phase Flight Process and Flight Rules
[0082] Flight process Flight rules Deceleration Level Flight Height constraint: height , Cruise altitude termination condition: speed , For cruise vacuum speed wait Descent Speed constraint: speed , To correct the Mach velocity termination condition: height , For climbing and changing altitude wait Descent Speed constraint: speed , Cruise speed calculation termination condition: speed , Calculate the speed for cruising Deceleration descent phase Termination condition: altitude , Airport elevation
[0083] Steps 2-5: Add the flight procedures and rule sequences for the climb, cruise, and descent phases to the flight procedure library. and rule base In this process, a mapping table is established from the flight process to the flight rules. The set of flight processes is represented as , The total number of flight processes is represented by the set of dynamic flight rules as follows: , The total number of rules;
[0084] Step 3: According to the currently effective flight rules, calculate the subsequent waypoint based on the current waypoint and subsequent key points. The calculation steps include:
[0085] Step 3-1: Based on the current flight phase, set the currently effective dynamic flight rules. ;
[0086] Step 3-2, based on the BADA performance model (Base of Aircraft Data) and the set of key points for the entire flight. Calculate the initial waypoint ,have ,in , , , and These are the takeoff stall speed, takeoff airport elevation, takeoff airport longitude, takeoff airport latitude, and takeoff mass, respectively, and the initial track point. Add to trackpoint set middle;
[0087] Step 3-3, design the time interval as follows The current waypoint is the trackpoints The subsequent track points are recorded as Based on the BADA performance model, we obtain thrust ,resistance Energy sharing factor Climbing and descent rates and fuel consumption Combined with time interval Further calculations yielded height ;
[0088] Steps 3-4, according to the currently effective flight rules. And the BADA performance model calculation trackpoints speed According to the time interval Further calculations yielded the distance. Pitch angle ,quality ;
[0089] Step 4: Determine whether the flight has completed the current segment and update the heading angle for the next segment. The steps include:
[0090] Step 4-1, let the current key point be... The next key point is The next waypoint is recorded as Compare waypoints Flight distance Distance from key points (i.e., the distance from the key point to the departure airport);
[0091] Step 4-2, if This indicates that the flight has not completed the current segment of flight. track angle ;
[0092] Step 4-3, if This indicates that the flight has completed the current segment. Since the Earth is an oblate spheroid, based on the key points... and The latitude and longitude can be obtained by converting latitude and longitude (lon, lat) from degrees to radians:
[0093]
[0094] track angle The calculation process is as follows:
[0095]
[0096] Step 5: If the next critical point is reached, determine whether the flight path meets the speed and altitude control constraints of the critical point. The process is as follows:
[0097] Step 5-1, set the next key point as The next waypoint is recorded as ,So Regulatory constraints Compare waypoints speed and key point speed range Compare waypoints height and key point height range ;
[0098] Step 5-2, if and , indicating waypoints Meet the key points Speed and altitude restrictions;
[0099] Step 5-3, if or , indicating waypoints Key points cannot be satisfied simultaneously Speed and altitude restrictions;
[0100] Step 6: When the critical point control constraints are violated, a backtracking correction strategy is created to recalculate the trajectory iteratively until the control constraints of the critical point are met.
[0101] The specific steps include:
[0102] Step 6-1, if the waypoint Key points cannot be satisfied simultaneously The speed and altitude limits indicate Violation of key points The control constraints, and the modified flight rules with adaptive constraints added according to the flight phase, are as follows:
[0103] If the waypoint Currently in the climbing phase, add an accelerated climbing phase, etc. The flight rules for the climb and constant-speed level flight phases, and the mapping relationship between the flight process and the flight rules, are shown in the table below:
[0104] Table 4. Mapping Relationship between Climb Phase Flight Process and Flight Rules
[0105] Flight process Flight rules Accelerated Climb Section Termination condition: speed , Speed limit at key points wait Climbing section Speed constraint: speed , Termination condition for speed limit at critical point: height , Limit the height of key points Constant speed level flight section Height constraints: , Termination condition for critical point altitude limit: flight distance , Horizontal distance of key points
[0106] If the waypoint During the cruise phase, if Add, etc. Flight rules for the climb phase, acceleration to level flight phase, and constant speed level flight phase, if Add, etc. The flight rules for the descent phase, the deceleration level flight phase, and the constant speed level flight phase, and the mapping relationship between the flight process and the flight rules are shown in the table below:
[0107] Table 5. Mapping Relationship between Climb Cruise Segment Flight Process and Flight Rules
[0108] Flight process Flight rules wait Climbing section Speed constraint: speed , To correct the Mach velocity termination condition: height , Limit the height of key points wait Descent Speed constraint: speed , To correct the Mach velocity termination condition: height , Limit the height of key points Acceleration Level Flight Height constraint: height , Termination condition for critical point height limit: speed , Speed limit at key points Deceleration Level Flight Height constraint: height , Termination condition for critical point height limit: speed , Speed limit at key points Constant speed level flight section Speed constraint: speed , Height constraint for critical point speed limit: Height , Termination condition for critical point altitude limit: flight distance , Horizontal distance of key points
[0109] If the waypoint During the descent phase, add a constant-speed level flight phase, etc. The flight rules for the descent and deceleration phases, and the mapping relationship between the flight process and the flight rules, are shown in the table below:
[0110] Table 5. Mapping Relationship between Descent Phase Flight Process and Flight Rules
[0111] Flight process Flight rules wait Descent Termination condition: speed , Speed limit at key points Deceleration descent phase Termination condition: altitude , Limit the height of key points Constant speed level flight section Height constraint: height , Termination condition for critical point altitude limit: flight distance , Horizontal distance of key points
[0112] Let the current one be the first... The second creation of a backtracking correction strategy, the speed item of all newly added rules. and height item The updated formula is as follows:
[0113]
[0114]
[0115] Step 6-2, set the time backtracking length as... Minutes, current waypoint Calculate the number of backtracking points The new track calculation starting point index is:
[0116]
[0117] Step 6-3, delete the set of waypoints The index is greater than Waypoints;
[0118] Step 6-4: Repeat steps 3, 4, and 5 to iteratively calculate waypoints until the key points are satisfied. The constraints, or the number of backtracking corrections. , This is the maximum number of backtracking corrections.
[0119] Step 7: Execute the flight rule sequence sequentially until all flight rules have been executed, and output the final simulated flight path data. The process includes:
[0120] Step 7-1, set the current flight rules The next waypoint is recorded as According to flight rules Data items and flight rules The specific rules are as follows:
[0121] If the flight rules are accelerated climb rules, accelerated level flight rules, decelerated level flight rules, and decelerated descent rules, compare the waypoints. Speed data and flight rules speed term ,if If so, the current rule has been executed.
[0122] If the flight rules are equal Climbing rules, etc. Climbing rules, etc. Decrease rules, etc. Descent rules, rules, comparison Height data and flight rules height item ,if If so, the current rule has been executed.
[0123] If the flight rules are constant speed level flight rules, compare waypoints. Distance data and flight rules Distance term ,if If the current rule has been executed, the rule status will be updated to "complete".
[0124] If the current flight rules constraints are not met, calculate the next waypoint until the constraints are met.
[0125] Step 7-2: Execute the next flight rule sequentially until all flight rules have been executed, then end the trajectory generation calculation and output the final simulated trajectory data.
[0126] In this embodiment, as Figure 2 and Figure 3 The figures in the image show the vertical profile of the simulated trajectory during each flight process of a single flight path, as well as the horizontal profile of the key points of the flight path relative to the simulated trajectory. The experimental objective is to create a dynamic flight process-flight rule mapping table, generate a segmented four-dimensional trajectory, and correct the trajectory by creating an intelligent backtracking correction strategy based on control constraints. Figure 2 The horizontal profile of the single-track range key points and the simulated track is shown. The large black dots represent range key points generated based on information such as arrival and departure procedures and flight plans, while the small gray dots represent the simulated horizontal track. It can be seen that the horizontal simulated track perfectly matches the range key points, and the transition at the key point junctions is smooth. Figure 3 The vertical profile diagrams of the simulated flight path under each flight process of a single flight path are shown. Solid lines represent the velocity profile, dashed lines represent the altitude profile, and dotted lines represent the climb / descent rate profile. The locations where the three characteristic values of velocity, altitude, and climb / descent rate abruptly change in the vertical profile indicate the end of a flight process. The locations circled in gray in the diagram indicate that a backtracking adjustment of control constraints was performed within that interval. These results demonstrate that the method of this invention can incorporate control constraints into flight path simulation calculations. By creating an intelligent backtracking correction strategy, iteratively adjusting the aircraft's speed and altitude, a corrected flight path that satisfies the constraints is obtained, achieving coupled optimization of control constraints and aerodynamic flight paths.
[0127] This invention provides an aerodynamic trajectory simulation method that satisfies regulatory constraints. Many methods and approaches exist for implementing this technical solution; the above description is merely a preferred embodiment of the invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of this invention, and these improvements and modifications should also be considered within the scope of protection of this invention. All components not explicitly stated in this embodiment can be implemented using existing technologies.
Claims
1. An aerodynamic trajectory simulation method that satisfies regulatory constraints, characterized in that, Includes the following steps: Step 1: Construct a sequence of key points for the flight path based on the coordinates of the take-off and landing airports, arrival and departure procedure parameters, and latitude and longitude data of the planned waypoints in the aircraft flight plan, and add key point control constraints; Step 2: Establish a mapping table from flight process to flight rules; Step 3: According to the currently effective flight rules, calculate the subsequent waypoint based on the current waypoint and subsequent key points; Step 4: Determine whether the flight has completed the current segment based on the calculated subsequent waypoints, and update the heading angle for the next segment; Step 5: If the next critical point is reached, determine whether the flight path meets the speed and altitude control constraints of the critical point. Step 6: When a critical point control constraint is violated, a backtracking correction strategy is created, and the trajectory is recalculated iteratively until the control constraint conditions of the critical point are met. Step 7: Execute the flight rule sequence sequentially until all flight rules have been executed, and output the final simulated flight track data.
2. The aerodynamic trajectory simulation method satisfying regulatory constraints according to claim 1, characterized in that, The process of constructing the sequence of key points in the flight path described in step 1 is as follows: Step 1-1: Combine the coordinates of the take-off and landing airports, the arrival and departure procedure parameters, and the latitude and longitude data of the planned waypoints in the flight plan to obtain the set of key points for the entire flight route; Steps 1-2: Add height and speed limits to the corresponding key points.
3. The aerodynamic trajectory simulation method satisfying regulatory constraints according to claim 2, characterized in that, Step 2 specifically involves establishing a mapping table from flight process to flight rules based on the aircraft's flight speed and altitude profiles. The specific process is as follows: Step 2-1: According to the flight altitude profile, the flight phase includes the climb phase, cruise phase and descent phase. The flight rules include speed, altitude and distance. The values of the rules are determined by the flight phase. Step 2-2: Based on the flight speed profile of the climb phase, decompose the climb phase flight process into an acceleration climb phase, etc. Climbing section, etc. During the climb and acceleration phases, kinematic and dynamic flight rules are established to correspond to the flight process. Steps 2-3: Based on the flight speed and altitude profiles of the cruise segment, decompose the cruise segment flight process into equal parts. Climbing section, etc. The descent phase, acceleration level flight phase, deceleration level flight phase, and constant speed level flight phase are used to create kinematic and dynamic flight rules corresponding to the flight process. Steps 2-4: Based on the flight speed profile during the descent phase, decompose the descent process into a deceleration descent phase, etc. Descent segment, etc. During the descent and deceleration level flight phases, kinematic and dynamic flight rules are created corresponding to the sub-flight processes; Steps 2-5: Add the rules for each flight process in the climb, cruise, and descent phases to the flight rule library in sequence, creating a mapping table from flight processes to flight rules.
4. The aerodynamic trajectory simulation method satisfying regulatory constraints according to claim 3, characterized in that, The calculation steps for subsequent waypoints described in step 3 include: Step 3-1: Set the currently effective dynamic flight rules according to the current flight phase; Step 3-2: Calculate the initial waypoints based on the aircraft performance model and the set of key points for the entire flight. Step 3-3: Based on the aircraft performance model, calculate the thrust, drag, energy sharing factor, climb and descent rate, fuel consumption, and altitude for the next track point. Steps 3-4: Calculate the speed, distance, pitch angle, and mass of the next waypoint based on the currently effective flight rules and the performance model.
5. The aerodynamic trajectory simulation method satisfying regulatory constraints according to claim 4, characterized in that, Step 4, which describes updating the heading angle for the next leg, includes: Step 4-1: Compare the flight distance of the next waypoint with the distance to the key point. If the flight distance is less than or equal to the distance to the key point, it means that the flight has not completed the current segment. In this case, the track angle of the next waypoint remains unchanged. Step 4-2: If the flight distance is greater than the distance to the key point, it means that the flight has completed the current segment of flight, and the track angle of the next point is updated.
6. The aerodynamic trajectory simulation method satisfying regulatory constraints according to claim 5, characterized in that, In step 5, the process of determining whether the flight path meets the speed and altitude control constraints at key points is as follows: Step 5-1: Compare the speed of the next waypoint with the speed range of the key point, and compare the altitude of the next waypoint with the altitude range of the key point; Step 5-2: If the speed of the track point is within the critical point speed range and the altitude of the track point is within the critical point range, it means that the track point meets the speed and altitude restrictions of the critical point; if the speed of the track point is not within the critical point speed range or the altitude of the track point is not within the critical point altitude range, it means that the track point does not meet the speed and altitude restrictions of the critical point.
7. The aerodynamic trajectory simulation method satisfying regulatory constraints according to claim 6, characterized in that, The specific steps for creating a backtracking correction strategy to address violations of critical point control constraints, as described in step 6, include: Step 6-1: If the next waypoint cannot simultaneously meet the speed and altitude limits of the critical point, it indicates that the waypoint violates the control constraints of the critical point. The modified flight rules with adaptive constraints are added according to the flight phase. Step 6-2: Calculate the new track start point index. Delete the set of waypoints with an index greater than 1. Waypoints; Step 6-3: Repeat steps 3, 4, and 5 to iteratively calculate the waypoints until the constraints of the key points are met, or the number of backtracking corrections exceeds the upper limit of the number of backtracking corrections.
8. The aerodynamic trajectory simulation method satisfying regulatory constraints according to claim 7, characterized in that, The modified flight rule update described in step 6-1 includes: assuming the current state is the [number]th ... The second creation of a backtracking correction strategy, the speed item of all newly added rules. and height item The updated formula is as follows: in, For the next waypoint speed, For the next waypoint The height.
9. The aerodynamic trajectory simulation method satisfying regulatory constraints according to claim 7, characterized in that, Step 7, which involves sequentially executing the flight rule sequence, includes: Step 7-1: Compare the attributes of the next waypoint with the rule items of the current flight rule according to the flight rules, and update the rule status; Step 7-2: Execute the next flight rule sequentially until all flight rules have been executed, then end the trajectory generation calculation and output the final simulated trajectory data.
10. The aerodynamic trajectory simulation method satisfying regulatory constraints according to claim 9, characterized in that, The next trackpoint attribute mentioned in step 7-1 is its data item, which includes speed data, altitude data, and distance data.