[go: up one dir, main page]

CN112927562B - A calculation method of aircraft flight altitude profile based on specified altitude limit - Google Patents

A calculation method of aircraft flight altitude profile based on specified altitude limit Download PDF

Info

Publication number
CN112927562B
CN112927562B CN202110116380.5A CN202110116380A CN112927562B CN 112927562 B CN112927562 B CN 112927562B CN 202110116380 A CN202110116380 A CN 202110116380A CN 112927562 B CN112927562 B CN 112927562B
Authority
CN
China
Prior art keywords
altitude
height
aircraft
flight
sector
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN202110116380.5A
Other languages
Chinese (zh)
Other versions
CN112927562A (en
Inventor
张阳
储培
金叶
丁辉
田云钢
马龙彪
陈平
董斌
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
CETC 28 Research Institute
Original Assignee
CETC 28 Research Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by CETC 28 Research Institute filed Critical CETC 28 Research Institute
Priority to CN202110116380.5A priority Critical patent/CN112927562B/en
Publication of CN112927562A publication Critical patent/CN112927562A/en
Application granted granted Critical
Publication of CN112927562B publication Critical patent/CN112927562B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft
    • G08G5/30—Flight plan management
    • G08G5/34—Flight plan management for flight plan modification

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Traffic Control Systems (AREA)

Abstract

本发明提供了一种基于指定高度限制的航空器飞行高度剖面计算方法，获取航班飞行计划、空域扇区结构和高度限制；分析限制点的高度与其前一航段飞行高度的关系，确定是否存在高低扇区转变；若不存在，依次计算当前高度飞行到指定高度所需的最小水平距离、高度限制点到其所属扇区进入边界的距离，在计算高度剖面时通过两个距离的关系决定改变高度和平飞的先后顺序；若存在，基于上述处理逻辑，考虑高度限制点与目的机场的距离，当两者距离小于设定参数，在计算高度剖面过程中优先下降到指定高度，再保持平飞。本发明方法充分考虑了空管运行的规则和实际情况，能够提高预战术阶段飞行航迹预测经过扇区的准确性，为精准的扇区流量预测提供技术支持。

Figure 202110116380

The present invention provides a method for calculating the flight height profile of an aircraft based on a specified height limit, which obtains flight plan, airspace sector structure and height limit; analyzes the relationship between the height of the limit point and the flight height of the previous flight segment, and determines whether there is a high or low altitude Sector change; if it does not exist, calculate the minimum horizontal distance required to fly to the specified altitude from the current altitude, the distance from the altitude limit point to the entry boundary of the sector to which it belongs, and determine the altitude change based on the relationship between the two distances when calculating the altitude profile. The order of level flight; if it exists, based on the above processing logic, the distance between the altitude limit point and the destination airport is considered. When the distance between the two is less than the set parameter, it will give priority to descending to the specified altitude in the process of calculating the altitude profile, and then maintain level flight. The method of the invention fully considers the rules and actual conditions of the air traffic control operation, can improve the accuracy of the pre-tactical stage flight track prediction passing through the sector, and provide technical support for accurate sector flow prediction.

Figure 202110116380

Description

Aircraft flight altitude profile calculation method based on specified altitude limit
Technical Field
The invention belongs to the field of air traffic management, and particularly relates to an aircraft flight altitude profile calculation method based on specified altitude limit.
Background
With the continuous increase of air traffic, the demand of air traffic fine operation and management is more urgent. The need for empty pipe operations is increasingly unsatisfied by still employing flight-based planning in combination with experience-based interval allocation in traffic-flow-dense airspaces. The method provides a new concept of taking four-dimensional track operation as future air traffic operation for the international civil aviation, and takes the four-dimensional track of the full life cycle of the flight of an aircraft as the center, and the air traffic control department, the airline company, the aircraft and the airport share, negotiate and manage the dynamic track, thereby realizing the cooperative decision between flight and control. This also puts higher demands on the 4D track prediction capability of the air traffic system.
The accurate 4D flight path is the basis for efficient use of a plurality of decision support tools of the air traffic management system, can be used for various stages of air traffic flow prediction and management, flight conflict detection, airplane entering sequence, auxiliary control command and the like, and improves the utilization rate of airspace resources. The 4D flight path includes: horizontal flight path, altitude profile and velocity profile, which are typically processed independently and eventually integrated for computational convenience. The 4D track prediction method commonly used in the current system is calculated by adopting a mode of combining a flight plan and an aircraft performance model. In this approach, the altitude profile is typically relatively simple, i.e., the aircraft climbs to cruise altitude, then flies flat to the descent peak, and then descends to the destination airport. The cruise altitude uses the altitude in the flight plan or the historical experience altitude, and considers the altitude limits such as the operation limit issued by the air traffic control, the control transfer protocol and the like, so that the predicted altitude profile has larger deviation from the actual altitude profile, and the calculation of the speed profile and the flight time can be influenced. Particularly, in the flow prediction process, since the high-altitude sector and the low-altitude sector may belong to different control units, the deviation of the height profile will cause inaccuracy of sector flow prediction, influence the formulation of a flow management strategy, and cause reduction of the overall operation efficiency. Currently, an accurate height profile calculation method which fully considers the practical operation of the air traffic control and the height limit is not available to support the prediction of an accurate 4D track.
Disclosure of Invention
The purpose of the invention is as follows: the invention aims to solve the technical problem of researching and inventing an aircraft flight height profile calculation method based on specified height limit from the perspective of accurately predicting the 4D flight path of an aircraft aiming at the development requirement of an air traffic control system for the refined operation with the 4D flight path as the core.
In order to solve the technical problem, the invention discloses an aircraft flight height profile calculation method based on specified height limit, which comprises the following steps:
step 1: acquiring basic information such as a flight plan, an airspace sector structure, a entering and leaving procedure, height limitation of waypoints and the like;
step 2: calculating a height profile from a takeoff airport to a first waypoint according to an off-site program, and updating a track starting point to be the first waypoint;
and step 3: finding the next height limiting point backwards from the track starting point, calculating the height profile from the track starting point to the entering boundary of a sector before the height limiting point, and updating the track starting point;
and 4, step 4: judging whether the flight is converted from a high-altitude sector to a low-altitude sector or not according to the relationship among the flight height of the flight path starting point, the designated height of the limit point and the airspace sector structure;
and 5: according to the judgment result in the step 4, determining the sequence of the flat flight and climbing or descending processes:
step 5-1: when the situation of switching from a high-altitude sector to a low-altitude sector does not exist, determining the sequence of the horizontal flight and the climbing or descending process according to the relation between the required climbing or descending distance and the boundary of the sector;
step 5-2: when the situation that the high-altitude sector is converted into the low-altitude sector exists, judging whether a descending process needs to be preferentially executed or not by evaluating the distance between the altitude limit point and a target airport; when the distance between the two is less than or equal to the set parameter LT, the aircraft descends to the designated height first and then keeps flying horizontally; otherwise, determining the sequence of the horizontal flight and the descending process according to the relation between the required descending distance and the sector boundary; whether the descending process needs to be preferentially executed or not is judged according to the distance between the height limiting point and the target airport, so that the calculation of the height profile is more fit with the operation reality.
Step 6: calculating the height profile from the track starting point to the height limiting point according to the height profile change process determined in the step 5, and updating the track starting point;
and 7: judging whether the track starting point is the last route point or not, and if so, executing the step 8; if not, executing step 3;
and 8: and calculating the height profile from the starting point of the flight path to the destination airport according to the approach program.
In one implementation manner, in step 1, the flight plan includes information of a takeoff airport, a waypoint, a landing airport and a cruising altitude required for calculating the altitude profile, and also includes an aircraft model; the airspace sector structure is used for determining a high-altitude sector, a low-altitude sector and sector types corresponding to different heights of the waypoints; the entrance and exit field program is used for calculating the height profile of the exit field and the entrance field; the altitude restrictions of waypoints are derived from restrictions imposed by hand-over protocols, traffic management or regulation; the first waypoint and the last waypoint in the flight plan correspond to the departure point and the approach point, respectively, and the height limit of the waypoints is below 6000 meters according to the air traffic control operation rule.
In one implementation mode, in the step 2, the flight distance of the aircraft from the runway to the first waypoint is determined according to the departure procedure calculation of the takeoff airport, the calculation of the climbing process is divided into 3 sub-processes of acceleration climbing, low-grade table climbing and high-grade table climbing, and the height profile calculation formula is
Figure BDA0002920810490000031
In the formula: h is height, t is time, m is aircraft mass, VTasThe aircraft vacuum speed is g, the gravity acceleration is g, the aircraft thrust is T, and the aircraft drag is D;
Figure BDA0002920810490000032
an energy distribution coefficient representing the ratio of the thrust for climbing to the thrust for acceleration when climbing at a selected speed; the aircraft thrust T, aircraft drag D and aircraft vacuum speed V corresponding to the aircraft in different stages and heights can be obtained from a BADA database issued by European control through the aircraft modelTas(ii) a The climbing process adopts step-by-step iterative calculation, and the weight of the airplane is calculated at each time interval
Figure BDA0002920810490000033
Keeping constant, determining each time interval
Figure BDA0002920810490000034
Inner aircraft vacuum velocity VTasCalculating each time interval according to the above formula
Figure BDA0002920810490000035
The height profile calculation of the climbing process from the takeoff airport to the first waypoint is sequentially finished according to the climbing rate in the aircraft; if the specified altitude limit is reached before the first waypoint, the level flight condition is maintained to the first waypoint.
In one implementation, in step 3, a next altitude limiting point is found from the track starting point backward, the calculation formula of the altitude profile of the entering boundary of the sector before the track starting point to the altitude limiting point is the same as that in step 2, and the processing logic is as follows: when the calculated altitude profile does not reach the cruising altitude, namely the flight does not enter the cruising state, if the horizontal distance between the altitude limit point and the takeoff airport is less than 200 kilometers, climbing to the limit altitude, and then keeping level flight; otherwise, climbing to the cruising height first and then keeping level flight; if the flight has entered the cruise phase, the level flight is maintained to the entry boundary of the sector preceding the altitude limit point. The consideration of whether the aircraft enters the cruise phase ensures that the aircraft can fly at the cruise altitude as far as possible in the altitude profile calculation, and the operation is more consistent with the actual situation.
In one implementation manner, in step 4, when the flight path starting point is in the high-altitude sector and the specified altitude of the limit point is lower than the flight altitude of the flight path starting point, whether the specified altitude is in the airspace of the low-altitude sector is determined according to the airspace sector structure, so as to determine whether the aircraft flies from the high-altitude sector to the low-altitude sector.
In one implementation, the step 5-1 includes:
5-1 a: calculating the minimum horizontal distance L required for the current height to climb or descend to the specified heightminConsidering that the aircraft needs to meet the altitude restrictions in advance,
Lmin＝Lf+20km
wherein L isfFor the horizontal distance of the current height climbing or descending to the designated height, the climbing rate or descending rate of the current height climbing or descending to the designated height is calculated according to the height profile calculation formula in the step 2, and the time required for the current height climbing or descending to the designated height is calculated according to the height difference of the current height climbing or descending to the designated height
Figure BDA0002920810490000043
By time
Figure BDA0002920810490000042
And at this stage the aircraft vacuum velocity VTasAnd wind speed VwindCalculating to obtain Lf；
Figure BDA0002920810490000041
5-1 b: calculating the distance L from the height limit point to the entering boundary of the sector to which the height limit point belongs, namely the distance from the height limit point to the boundary line;
5-1 c: when L is more than or equal to LminThen, the altitude profile change process of the aircraft is described as follows: firstly keeping flat flying to the distance before the height limit point LminThen executing descending or climbing process to a specified height, and then flying horizontally to a height limit point;
5-1 d: when L < LminWhen it is, let Lmin＝min{Lf+L，LcAnd the change process of the height profile of the aircraft comprises the following steps: firstly keeping flat flying to the distance before the height limit point LminThen executing descending or climbing process to a specified height, and then flying horizontally to a height limit point; wherein L iscIs the horizontal distance between the track starting point and the height limit point.
In one implementation, the parameter LT in step 5-2 is set to 200 km; when the horizontal distance between the altitude limit point and the destination airport is more than 200 kilometers, the altitude profile change process comprises the following steps:
5-2 a: calculating the minimum horizontal distance L required by the current height to fall to the specified heightminConsidering that the aircraft needs to meet the altitude restrictions in advance,
Lmin＝Lf+20km
wherein L isfFor the horizontal distance that the current height descends to the designated height, the descending rate that the current height descends to the designated height is calculated and obtained according to the height profile calculation formula in the step 2, and then the time required by the current height to descend to the designated height is calculated according to the height difference that the current height descends to the designated height
Figure BDA0002920810490000051
By time
Figure BDA0002920810490000052
And at this stage the aircraft vacuum velocity VTasAnd wind speed VwindCalculating to obtain Lf；
Figure BDA0002920810490000053
5-2 b: calculating the distance L from the height limit point to the entering boundary of the sector to which the height limit point belongs, namely the distance from the height limit point to the boundary line;
5-2 c: when L is more than or equal to LminThen, the altitude profile change process of the aircraft is described as follows: firstly, useKeeping flat flying to the distance before the height limit point LminThen, a descending process is carried out to a specified height, and then the aircraft flies to a height limit point;
5-2 d: when L < LminWhen it is, let Lmin＝min{Lf+L，LcAnd the change process of the height profile of the aircraft comprises the following steps: firstly keeping flat flying to the distance before the height limit point LminThen, a descending process is carried out to a specified height, and then the aircraft flies to a height limit point; wherein L iscIs the horizontal distance between the track starting point and the height limit point.
In the steps 3, 4 and 5, the important operation factor of the airspace sector boundary is considered in the process of determining the flight state and calculating the altitude profile. When the sequence of the level flight, descending or climbing process is determined, the level flight state when the control handover is carried out across the sector boundary is kept, and the reasonability and the refinement degree of the height profile are increased.
In one implementation, the calculation formula for calculating the height profile from the track starting point to the height limiting point in step 6 according to the height profile change process determined in step 5 is the same as that in step 2.
In one implementation, the formula for calculating the altitude profile of the approach stage in step 8 is the same as that in step 2, and the horizontal distance L required for descending from the current altitude to the altitude of the destination airport is calculated and determineddThe aircraft is kept level flying from the current altitude to the distance destination airport LdThen begins to descend to the destination airport; calculating and obtaining the descending rate from the current height to the target airport height according to the height profile calculation formula in the step 2, and calculating the time required by the current height to descend to the airport height according to the height difference between the current height and the airport height
Figure BDA0002920810490000054
By time
Figure BDA0002920810490000055
And at this stage the aircraft vacuum velocity VTasAnd wind speed VwindCalculating to obtain Ld。
Figure BDA0002920810490000056
The invention has the following technical effects:
1. the invention provides a quick implementation method for aircraft height profile calculation in the pre-tactical stage; in the process of determining the flight state and calculating the altitude profile, the important operation factor of the boundary of the airspace sector is considered. When the sequence of the level flight, descending or climbing process is determined, the level flight state when the control handover is carried out across the sector boundary is kept, and the reasonability and the refinement degree of the height profile are increased.
2. The invention provides technical support for accurate prediction of the four-dimensional track, when a next height limiting point is found backwards from a track starting point, whether the aircraft enters a cruise stage or not is considered when the height profile from the track starting point to a sector entering boundary before the height limiting point is calculated, and the aircraft can fly by using the cruise height as much as possible during calculation of the height profile, which is more consistent with the actual operation; when the situation that the flight is converted from a high-altitude sector to a low-altitude sector exists, whether the descending process needs to be preferentially executed or not is judged according to the distance between the height limiting point and the destination airport, so that the calculation of the height profile is more fit with the operation reality.
Drawings
The foregoing and/or other advantages of the invention will become further apparent from the following detailed description of the invention when taken in conjunction with the accompanying drawings.
FIG. 1 is a flow chart of a method of the present invention;
FIG. 2 is a height profile without a transition from a high altitude sector to a low altitude sector;
fig. 3 is a height profile of a transition from a high altitude sector to a low altitude sector.
Detailed Description
Embodiments of the present invention will be described below with reference to the accompanying drawings.
As shown in FIG. 1, the invention discloses a method for calculating a flight altitude profile of an aircraft based on specified altitude limits, which comprises the following steps:
step 1: acquiring basic information such as a flight plan, an airspace sector structure, a entering and leaving procedure, height limitation of waypoints and the like; the flight plan comprises information of a takeoff airport, a waypoint, a landing airport and a cruising altitude required by calculating the altitude profile, and also comprises an aircraft model; the airspace sector structure is used for determining a high-altitude sector, a low-altitude sector and sector types corresponding to different heights of the waypoints; the entrance and exit field program is used for calculating the height profile of the exit field and the entrance field; the height limit of the waypoints comes from the limit proposed by a handover protocol, traffic management or control and the like, the first waypoint and the last waypoint in the flight plan respectively correspond to an departure point and an approach point, and the specified height limit is available according to the air traffic control operation rule and is usually below 6000 meters;
step 2: calculating a height profile from a takeoff airport to a first waypoint according to an off-site program, and updating a track starting point to be the first waypoint; the method comprises the steps of calculating and determining the flight distance of an aircraft from a runway to a first route point according to an departure program of a takeoff airport, wherein the calculation of a climbing process is divided into 3 sub-processes of accelerating climbing, low-grade table climbing and high-grade table climbing, and the calculation formula is that
Figure BDA0002920810490000071
In the formula: h is the height, t is the time, and m is the mass of the aircraft; vTasIs the aircraft vacuum speed; g is the gravitational acceleration, T is the aircraft thrust, and D is the aircraft resistance;
Figure BDA0002920810490000072
the energy distribution coefficient represents the ratio of the thrust for climbing to the thrust for acceleration when climbing at a selected speed. The Base OfAircraft Data (BADA) database issued by European controller contains performance parameters of the common aircraft model, including thrust, drag and speed corresponding to different stages and altitudes, and the performance parameters are obtained through the aircraft modelThe aircraft thrust T, aircraft drag D and aircraft vacuum speed V corresponding to different stages and altitudes of the aircraft can be obtained from the BADA databaseTas. The climbing process adopts the idea of gradually iterating calculation, and the climbing process is carried out at each time interval
Figure BDA0002920810490000073
Determining each time interval on the assumption that the weight of the aircraft remains unchanged
Figure BDA0002920810490000076
Inner VTasThen calculate each time interval according to the formula (1)
Figure BDA0002920810490000074
The internal climbing rate, the height profile calculation of the climbing process from the takeoff airport to the first route point and the time interval
Figure BDA0002920810490000075
Typically 8 seconds. If the specified altitude limit is reached before the first waypoint, the level flight condition is maintained to the first waypoint.
And step 3: and finding the next height limit point backwards from the track starting point, calculating the height profile from the track starting point to the entering boundary of a sector before the height limit point, and updating the track starting point. The calculation process of the height profile of the step still utilizes the calculation formula of the step 2, but the processing logic is as follows: 1) when the calculated altitude profile does not reach the cruising altitude, namely the flight does not enter the cruising state, if the horizontal distance between the altitude limit point and the takeoff airport is less than 200 kilometers, climbing to the limit altitude, and then keeping level flight; otherwise, climbing to the cruising height first and then keeping level flight; 2) if the flight has entered the cruise phase, the level flight is maintained to the entry boundary of the sector preceding the altitude limit point.
And 4, step 4: and judging whether the flight is converted from the high-altitude sector to the low-altitude sector or not according to the relationship among the flight altitude of the flight path starting point, the designated altitude of the limit point and the airspace sector structure. When the flight path starting point is in the high-altitude sector and the designated height of the limit point is lower than the flight height of the flight path starting point, judging whether the designated height is in the low-altitude sector according to the airspace sector structure so as to judge whether the aircraft flies from the high-altitude sector to the low-altitude sector; the boundary between the high and low altitude sectors is different within each geofence, but is typically 7800 meters or 6600 meters.
And 5: according to the judgment result in the step 4, determining the sequence of the flat flight and climbing or descending processes:
step 5-1: when there is no situation of switching from the high altitude sector to the low altitude sector, as shown in fig. 2, the sequence of the level flight and the climbing or descending process is determined according to the relationship between the required climbing or descending distance and the sector boundary. The specific calculation process is as follows:
5-1 a: calculating the minimum horizontal distance L required for the current height to climb or descend to the specified heightminConsidering that aircraft generally need to meet altitude restrictions in advance,
Lmin＝Lf+20km
wherein L isfFor the distance from the current height to the specified height, the climbing rate or the descending rate of the current height to the specified height can be calculated according to the formula (1), and the time required for the current height to climb or descend to the specified height is calculated according to the height difference of the current height to the specified height
Figure BDA0002920810490000081
By time
Figure BDA0002920810490000082
And at this stage the aircraft vacuum velocity VTasAnd wind speed VwindCalculating to obtain Lf；
Figure BDA0002920810490000083
5-1 b: calculating the distance L from the height limit point to the entering boundary of the sector to which the height limit point belongs;
5-1 c: when L is more than or equal to LminThen, the description may be that the altitude change process is completed in the last sector, and the altitude profile change process of the aircraft is as follows: firstly keeping flat flying to the distance before the height limit point LminThen executing descending or climbing process to a specified height, and then flying horizontally to a height limit point;
5-1 d: when L < LminWhen it is, let Lmin＝min{Lf+L，LcAnd the change process of the height profile of the aircraft comprises the following steps: firstly keeping flat flying to the distance before the height limit point LminThen executing descending or climbing process to a specified height, and then flying horizontally to a height limit point; wherein L iscIs the horizontal distance between the track starting point and the height limit point.
Step 5-2: when the situation of switching from the high-altitude sector to the low-altitude sector exists, as shown in fig. 3, whether a descending process needs to be preferentially executed is judged by evaluating the distance between the altitude limit point and the destination airport; when the horizontal distance between the altitude limit point and the destination airport is less than or equal to 200 kilometers (the set parameter LT), the change process of the altitude profile of the aircraft is as follows: descending to a specified height, and keeping level flight to a height limit point; when the horizontal distance between the altitude limit point and the destination airport is more than 200 km, the determination of the altitude profile change process is consistent with step 5-1, and comprises the following steps:
5-2 a: calculating the minimum horizontal distance L required by the current height to fall to the specified heightminConsidering that the aircraft needs to meet the altitude restrictions in advance,
Lmin＝Lf+20km
wherein L isfFor the horizontal distance that the current height descends to the designated height, the descending rate that the current height descends to the designated height is calculated and obtained according to the height profile calculation formula in the step 2, and then the time required by the current height to descend to the designated height is calculated according to the height difference that the current height descends to the designated height
Figure BDA0002920810490000091
By time
Figure BDA0002920810490000092
And at this stage the aircraft vacuum velocity VTasAnd wind speed VwindCalculating to obtain Lf；
Figure BDA0002920810490000093
5-2 b: calculating the distance L from the height limit point to the entering boundary of the sector to which the height limit point belongs;
5-2 c: when L is more than or equal to LminThen, the altitude profile change process of the aircraft is described as follows: firstly keeping flat flying to the distance before the height limit point LminThen, a descending process is carried out to a specified height, and then the aircraft flies to a height limit point;
5-2 d: when L < LminWhen it is, let Lmin＝min{Lf+L，LcAnd the change process of the height profile of the aircraft comprises the following steps: firstly keeping flat flying to the distance before the height limit point LminThen, a descending process is carried out to a specified height, and then the aircraft flies to a height limit point; wherein L iscIs the horizontal distance between the track starting point and the height limit point.
Step 6: and (5) calculating the height profile from the track starting point to the height limiting point according to the height profile change process determined in the step (5), and updating the track starting point. The calculation formula for the height profile from the starting point of the flight path to the height limit point is the same as that in step 2.
And 7: judging whether the track starting point is the last route point or not, and if so, executing the step 8; if not, step 3 is performed.
And 8: and calculating the height profile from the starting point of the flight path to the destination airport according to the approach program. The height profile of the approach phase is substantially symmetrical to the height profile of the departure phase, and is still calculated using equation (1). First, the horizontal distance L required to descend from the current altitude to the destination airport is calculated and determineddThe aircraft is kept level flying from the current altitude to the distance destination airport LdThen begins to descend to the destination airport.Calculating and obtaining the descending rate from the current height to the target airport height according to the height profile calculation formula in the step 2, and calculating the time required by the current height to descend to the airport height according to the height difference between the current height and the airport height
Figure BDA0002920810490000101
By time
Figure BDA0002920810490000102
And at this stage the aircraft vacuum velocity VTasAnd wind speed VwindCalculating to obtain Ld。
Figure BDA0002920810490000103
The present invention provides a method for calculating a flight height profile of an aircraft based on specified height limits, and a plurality of methods and ways for implementing the method, and the above description is only a specific embodiment of the present invention, and it should be noted that, for a person skilled in the art, a plurality of modifications and embellishments can be made without departing from the principle of the present invention, and these modifications and embellishments should also be regarded as the protection scope of the present invention. All the components not specified in the present embodiment can be realized by the prior art.

Claims (7)

1.一种基于指定高度限制的航空器飞行高度剖面计算方法，其特征在于，包括如下步骤：1. an aircraft flight height profile calculation method based on the specified altitude restriction, is characterized in that, comprises the steps: 步骤1：获取飞行计划、空域扇区结构、进离场程序和航路点的高度限制基础信息；Step 1: Obtain basic information on flight plan, airspace sector structure, approach and departure procedures and altitude restrictions of waypoints; 步骤2：根据离场程序计算起飞机场到第一个航路点的高度剖面，并更新航迹起始点为第一个航路点；Step 2: Calculate the height profile from the departure airport to the first waypoint according to the departure procedure, and update the start point of the track to the first waypoint; 步骤3：从航迹起始点开始向后找到下一个高度限制点，计算航迹起始点到该高度限制点前一个扇区进入边界的高度剖面，并更新航迹起始点；Step 3: Find the next altitude limit point backward from the track start point, calculate the altitude profile from the track start point to the entry boundary of the sector before the altitude limit point, and update the track start point; 步骤4：通过航迹起始点的飞行高度、限制点指定高度和空域扇区结构之间的关系，判断航班是否由高空扇区向低空扇区转换；Step 4: According to the relationship between the flight altitude of the track start point, the designated altitude of the limit point and the airspace sector structure, determine whether the flight is converted from a high-altitude sector to a low-altitude sector; 步骤5：根据步骤4的判断结果，确定平飞和爬升过程的先后顺序，或者平飞和下降过程的先后顺序：Step 5: According to the judgment result of Step 4, determine the sequence of level flight and climb, or the sequence of level flight and descent: 步骤5-1：当不存在由高空扇区向低空扇区转换情况时，根据所需爬升或下降距离和扇区边界的关系，若需爬升，确定平飞和爬升过程的先后顺序，若需下降，确定平飞和下降过程的先后顺序；Step 5-1: When there is no transition from high-altitude sector to low-altitude sector, according to the relationship between the required climb or descent distance and the sector boundary, if climbing is required, determine the sequence of level flight and climb. Descending, determine the sequence of level flight and descent; 步骤5-2：当存在由高空扇区向低空扇区转换情况时，通过评估高度限制点与目的机场的距离来判断是否需要优先执行下降过程；当两者之间的距离小于等于设定的参数LT时，则先下降到指定高度，再保持平飞；否则，根据所需下降距离和扇区边界的关系，确定平飞和下降过程的先后顺序；Step 5-2: When there is a transition from the high-altitude sector to the low-altitude sector, judge whether the descent process needs to be performed preferentially by evaluating the distance between the altitude limit point and the destination airport; when the distance between the two is less than or equal to the set When the parameter is LT, first descend to the specified altitude, and then maintain level flight; otherwise, determine the sequence of level flight and descent process according to the relationship between the required descent distance and sector boundary; 步骤6：根据步骤5确定的高度剖面变化过程，计算航迹起始点到高度限制点的高度剖面，并更新航迹起始点；Step 6: According to the change process of the altitude profile determined in Step 5, calculate the altitude profile from the starting point of the track to the altitude limit point, and update the starting point of the track; 步骤7：判断航迹起始点是否为最后一个航路点，如果是则执行步骤8；如果不是执行步骤3；Step 7: Determine whether the start point of the track is the last waypoint, if so, go to Step 8; if not, go to Step 3; 步骤8：根据进场程序计算航迹起始点到目的机场的高度剖面；Step 8: Calculate the altitude profile from the start point of the track to the destination airport according to the approach procedure; 所述步骤5-1包括：The step 5-1 includes: 5-1a：计算当前高度爬升或下降到指定高度所需的最小水平距离Lmin，考虑到航空器需要提前满足高度限制，5-1a: Calculate the minimum horizontal distance L min required to climb or descend to the specified altitude at the current altitude, considering that the aircraft needs to meet the altitude restrictions in advance, Lmin＝Lf+20kmL min =L f +20km 其中Lf为当前高度爬升或下降到指定高度的水平距离，根据步骤2中高度剖面计算公式计算获得当前高度爬升或下降到指定高度的爬升率或下降率，再根据当前高度爬升或下降到指定高度的高度差计算出当前高度爬升或下降到指定高度所需要的时间
Figure FDA0003390729510000021
由时间
Figure FDA0003390729510000022
和此阶段航空器真空速VTas和风速Vwind计算得到Lf；Among them, L f is the horizontal distance from the current altitude to climb or descend to the specified altitude. According to the altitude profile calculation formula in step 2, the climb rate or descent rate of the current altitude to climb or descend to the specified altitude is calculated and obtained, and then climb or descend to the specified altitude according to the current altitude. The altitude difference calculates the time required to climb or descend to the specified altitude from the current altitude
Figure FDA0003390729510000021
by time
Figure FDA0003390729510000022
L f is obtained by calculating the true air speed V Tas and wind speed V wind of the aircraft at this stage;
Figure FDA0003390729510000023
Figure FDA0003390729510000023
 5-1b：计算高度限制点到其所属扇区进入边界的距离L；5-1b: Calculate the distance L from the height limit point to the entry boundary of the sector to which it belongs; 5-1c：当L≥Lmin时，说明能够在最后一个扇区完成高度改变过程，则航空器的高度剖面变化过程为：先保持平飞至距离高度限制点之前Lmin的位置，然后执行下降或爬升过程到指定高度，然后平飞至高度限制点；5-1c: When L≥L min , it means that the altitude change process can be completed in the last sector, then the altitude profile change process of the aircraft is: first maintain level flight to the position L min before the altitude limit point, and then perform descent Or climb to the specified altitude, and then level off to the altitude limit point; 5-1d：当L＜Lmin时，令Lmin＝min{Lf+L,Lc}，航空器的高度剖面变化过程为：先保持平飞至距离高度限制点之前Lmin的位置，然后执行下降或爬升过程到指定高度，然后平飞至高度限制点；其中Lc为航迹起始点与高度限制点之间的水平距离；5-1d: When L < L min , let L min =min{L f +L,L c }, the altitude profile change process of the aircraft is: first keep level flight to the position of L min before the altitude limit point, then Execute the descent or climb process to the specified altitude, and then fly level to the altitude limit point; where L c is the horizontal distance between the start point of the track and the altitude limit point; 所述步骤5-2中参数LT设置为200公里；当高度限制点与目的机场的水平距离大于200公里时，高度剖面变化过程包括：In the step 5-2, the parameter LT is set to 200 kilometers; when the horizontal distance between the altitude limit point and the destination airport is greater than 200 kilometers, the altitude profile change process includes: 5-2a：计算当前高度下降到指定高度所需的最小水平距离Lmin，考虑到航空器需要提前满足高度限制，5-2a: Calculate the minimum horizontal distance L min required to descend from the current altitude to the specified altitude, considering that the aircraft needs to meet the altitude limit in advance, Lmin＝Lf+20kmL min =L f +20km 其中Lf为当前高度下降到指定高度的水平距离，根据步骤2中高度剖面计算公式计算获得当前高度下降到指定高度的下降率，再根据当前高度下降到指定高度的高度差计算出当前高度下降到指定高度所需要的时间
Figure FDA0003390729510000024
由时间
Figure FDA0003390729510000025
和此阶段航空器真空速VTas和风速Vwind计算得到Lf；Among them, L f is the horizontal distance from the current height to the specified height. According to the height profile calculation formula in step 2, the rate of descent from the current height to the specified height is calculated, and then the current height is decreased according to the height difference between the current height and the specified height. Time required to reach the specified altitude
Figure FDA0003390729510000024
by time
Figure FDA0003390729510000025
L f is obtained by calculating the true air speed V Tas and wind speed V wind of the aircraft at this stage;
Figure FDA0003390729510000026
Figure FDA0003390729510000026
 5-2b：计算高度限制点到其所属扇区进入边界的距离L；5-2b: Calculate the distance L from the height limit point to the entry boundary of the sector to which it belongs; 5-2c：当L≥Lmin时，说明能够在最后一个扇区完成高度改变过程，则航空器的高度剖面变化过程为：先保持平飞至距离高度限制点之前Lmin的位置，然后执行下降过程到指定高度，然后平飞至高度限制点；5-2c: When L≥L min , it means that the altitude change process can be completed in the last sector, then the altitude profile change process of the aircraft is: first maintain level flight to the position L min before the altitude limit point, and then perform descent Process to the specified altitude, and then fly level to the altitude limit point; 5-2d：当L＜Lmin时，令Lmin＝min{Lf+L,Lc}，航空器的高度剖面变化过程为：先保持平飞至距离高度限制点之前Lmin的位置，然后执行下降过程到指定高度，然后平飞至高度限制点；其中Lc为航迹起始点与高度限制点之间的水平距离。5-2d: When L<L min , let L min =min{L f +L,L c }, the altitude profile change process of the aircraft is: first keep level flight to the position of L min before the altitude limit point, then Execute the descent process to the specified altitude, and then fly level to the altitude limit point; where L c is the horizontal distance between the track start point and the altitude limit point. 2.根据权利要求1所述的一种基于指定高度限制的航空器飞行高度剖面计算方法，其特征在于，所述步骤1中，飞行计划中包含了计算高度剖面所需的起飞机场、航路点、降落机场和巡航高度信息，还包含了航空器机型；空域扇区结构用于确定高空扇区和低空扇区，以及航路点不同高度所对应的扇区类型；进离场程序用于计算离场和进场阶段的高度剖面；航路点的高度限制来源于移交协议、流量管理或管制提出的限制；飞行计划中的第一个航路点和最后一个航路点分别对应于离场点和进场点，航路点的高度限制根据空管运行规则，在6000米以下。2. a kind of aircraft flight height profile calculation method based on the specified height restriction according to claim 1, is characterized in that, in described step 1, in the flight plan, the required take-off airport, waypoint for calculating the height profile are included in the flight plan. , landing airport and cruising altitude information, and also includes aircraft type; the airspace sector structure is used to determine the high-altitude sector and low-altitude sector, as well as the sector types corresponding to different altitudes of the waypoint; the approach and departure procedures are used to calculate the distance Altitude profiles for the field and approach phases; altitude constraints for waypoints are derived from handover agreements, flow management, or constraints imposed by controls; the first and last waypoints in the flight plan correspond to departures and arrivals, respectively The altitude limit of the waypoint is below 6000 meters according to the air traffic control operation rules. 3.根据权利要求2所述的一种基于指定高度限制的航空器飞行高度剖面计算方法，其特征在于，所述步骤2中，根据起飞机场的离场程序计算确定航空器从跑道到第一个航路点的飞行距离，爬升过程的计算分为加速爬升、低等表爬升和高等表爬升3个子过程，高度剖面计算公式为3. a kind of aircraft flight height profile calculation method based on the specified height restriction according to claim 2, is characterized in that, in described step 2, according to the departure procedure calculation of the departure airport, it is determined that the aircraft is from the runway to the first The flight distance of the waypoint, the calculation of the climb process is divided into three sub-processes: accelerated climb, low-level climb and high-level climb. The altitude profile calculation formula is:
Figure FDA0003390729510000031
Figure FDA0003390729510000031
 式中：h为高度，t为时间，m为航空器质量，VTas为航空器真空速，g为重力加速度，T为航空器推力，D为航空器阻力；
Figure FDA0003390729510000032
为能量分配系数，表示按照选定的速度进行爬升时，用于爬升的推力与用于加速的推力的比值；通过航空器机型能够从欧控发布的BADA数据库获得航空器在不同阶段和高度对应的航空器推力T、航空器阻力D和航空器真空速VTas；爬升过程采用逐步迭代计算，飞机的重量在每个时间间隔
Figure FDA0003390729510000033
内保持不变，确定每个时间间隔
Figure FDA0003390729510000034
内的航空器真空速VTas，根据上述公式计算出各个时间间隔
Figure FDA0003390729510000035
内的爬升率，依次完成起飞机场到第一个航路点爬升过程的高度剖面计算；如果在第一个航路点之前达到指定的高度限制，则保持平飞状态至第一个航路点。where h is the height, t is the time, m is the mass of the aircraft, V Tas is the true speed of the aircraft, g is the acceleration of gravity, T is the thrust of the aircraft, and D is the resistance of the aircraft;
Figure FDA0003390729510000032
is the energy distribution coefficient, indicating the ratio of the thrust used for climbing to the thrust used for acceleration when climbing at the selected speed; through the aircraft type, it is possible to obtain the corresponding values of the aircraft at different stages and altitudes from the BADA database issued by Eurocontrol. Aircraft thrust T, aircraft resistance D and aircraft true airspeed V Tas ; the climb process adopts step-by-step iterative calculation, the weight of the aircraft is in each time interval
Figure FDA0003390729510000033
remain constant within each time interval
Figure FDA0003390729510000034
The airspeed V Tas of the aircraft in the
Figure FDA0003390729510000035
The altitude profile calculation of the climb process from the takeoff airport to the first waypoint is completed in turn; if the specified altitude limit is reached before the first waypoint, the state of level flight will be maintained to the first waypoint. 4.根据权利要求3所述的一种基于指定高度限制的航空器飞行高度剖面计算方法，其特征在于，所述步骤3中，从航迹起始点开始向后找到下一个高度限制点，航迹起始点到该高度限制点前一个扇区进入边界的高度剖面计算公式和步骤2中相同，处理逻辑如下：当已完成计算的高度剖面未曾达到巡航高度，即航班尚未进入巡航状态时，如果该高度限制点与起飞机场水平距离小于200公里，则先爬升至该限制高度，然后保持平飞；否则先爬升到巡航高度，再保持平飞；如果航班已经进入巡航阶段，则保持平飞状态至该高度限制点前一个扇区的进入边界。4. a kind of aircraft flight height profile calculation method based on specified altitude restriction according to claim 3, is characterized in that, in described step 3, from track starting point, find the next altitude restriction point backward, track The calculation formula of the altitude profile from the starting point to the entry boundary of the sector before the altitude limit point is the same as that in step 2, and the processing logic is as follows: when the altitude profile that has been calculated has not reached the cruising altitude, that is, the flight has not yet entered the cruise state, if the If the horizontal distance between the altitude limit point and the take-off airport is less than 200 kilometers, first climb to the limit altitude, and then maintain level flight; otherwise, climb to the cruising altitude first, and then maintain level flight; if the flight has entered the cruise phase, maintain level flight status The entry boundary to the sector preceding this altitude limit point. 5.根据权利要求4所述的一种基于指定高度限制的航空器飞行高度剖面计算方法，其特征在于，所述步骤4中，当航迹起始点处于高空扇区，并且限制点的指定高度低于航迹起始点的飞行高度时，则根据空域扇区结构判断该指定高度是否处于低空扇区空域内，以此来判定航空器是否将由高空扇区飞向低空扇区。5. a kind of aircraft flight height profile calculation method based on the specified altitude restriction according to claim 4, is characterized in that, in described step 4, when the track start point is in the high-altitude sector, and the specified height of the restriction point is low When the flight altitude is at the starting point of the track, according to the airspace sector structure, it is judged whether the specified altitude is within the airspace of the low-altitude sector, so as to determine whether the aircraft will fly from the high-altitude sector to the low-altitude sector. 6.根据权利要求5所述的一种基于指定高度限制的航空器飞行高度剖面计算方法，其特征在于，所述步骤6中根据步骤5确定的高度剖面变化过程，计算航迹起始点到高度限制点的高度剖面计算公式和步骤2中相同。6. a kind of aircraft flight height profile calculation method based on the specified height restriction according to claim 5, is characterized in that, in described step 6, according to the height profile change process determined in step 5, calculate track starting point to height restriction The formula for calculating the height profile of the point is the same as in step 2. 7.根据权利要求6所述的一种基于指定高度限制的航空器飞行高度剖面计算方法，其特征在于，所述步骤8中进场阶段的高度剖面计算公式和步骤2中相同，计算并确定从当前高度下降到目的机场高度所需的水平距离Ld，航空器从当前高度保持平飞至距离目的机场Ld的位置，然后开始下降到目的机场；根据步骤2中高度剖面计算公式计算获得从当前高度下降到目的机场高度的下降率，再根据当前高度下降到机场高度的高度差计算出当前高度下降到机场高度所需要的时间
Figure FDA0003390729510000041
由时间
Figure FDA0003390729510000042
和此阶段航空器真空速VTas和风速Vwind计算获得Ld：7. a kind of aircraft flight height profile calculation method based on the specified height restriction according to claim 6, is characterized in that, the height profile calculation formula of approach stage in described step 8 is identical with in step 2, calculate and determine from. The horizontal distance L d required to descend from the current altitude to the altitude of the destination airport, the aircraft maintains level flight from the current altitude to the position L d from the destination airport, and then starts to descend to the destination airport; The rate of descent from the altitude to the altitude of the destination airport, and then calculate the time required to descend from the current altitude to the airport altitude according to the altitude difference from the current altitude to the airport altitude
Figure FDA0003390729510000041
by time
Figure FDA0003390729510000042
And at this stage, the aircraft's true airspeed V Tas and wind speed V wind are calculated to obtain L d :
Figure FDA0003390729510000043
Figure FDA0003390729510000043
CN202110116380.5A 2021-01-28 2021-01-28 A calculation method of aircraft flight altitude profile based on specified altitude limit Active CN112927562B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202110116380.5A CN112927562B (en) 2021-01-28 2021-01-28 A calculation method of aircraft flight altitude profile based on specified altitude limit

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202110116380.5A CN112927562B (en) 2021-01-28 2021-01-28 A calculation method of aircraft flight altitude profile based on specified altitude limit

Publications (2)

Publication Number Publication Date
CN112927562A CN112927562A (en) 2021-06-08
CN112927562B true CN112927562B (en) 2022-03-04

Family

ID=76167946

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202110116380.5A Active CN112927562B (en) 2021-01-28 2021-01-28 A calculation method of aircraft flight altitude profile based on specified altitude limit

Country Status (1)

Country Link
CN (1) CN112927562B (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114047774B (en) * 2021-11-11 2023-11-14 中国电子科技集团公司第二十八研究所 Verification method for four-rotor unmanned aerial vehicle operation simulation in low-altitude layered airspace
CN114333426A (en) * 2021-11-26 2022-04-12 中国航空无线电电子研究所 An approach flight parameter optimization method based on multi-waypoint height window constraints
CN114912688B (en) * 2022-05-18 2024-04-30 中国电子科技集团公司第二十八研究所 Aircraft track prediction method based on climbing section energy sharing factor estimation
CN115206135B (en) * 2022-06-16 2024-02-13 中国电子科技集团公司第二十八研究所 An aircraft command altitude planning method with uncertain climb rate

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6134500A (en) * 1999-06-03 2000-10-17 United Air Lines, Inc. System and method for generating optimal flight plans for airline operations control
FR2935495A1 (en) * 2008-08-29 2010-03-05 Thales Sa SYSTEM AND METHOD FOR CALCULATING FLIGHT PREDICTIONS BY VERTICAL SECTIONS
CN101692315A (en) * 2009-09-25 2010-04-07 民航总局空管局技术中心 Method for analyzing high precision 4D flight trajectory of airplane based on real-time radar data
CN101739845A (en) * 2009-12-18 2010-06-16 中国航空无线电电子研究所 Aeronautical data chain information-based civil aircraft aviation electronic verification system and method thereof
CN103093649A (en) * 2011-10-31 2013-05-08 通用电气公司 Methods and systems for inferring aircraft parameters
CN104240541A (en) * 2014-09-09 2014-12-24 中国电子科技集团公司第二十八研究所 4D track generating method
CN105701552A (en) * 2014-10-11 2016-06-22 中国国际航空股份有限公司 Method of calculating vertical section of flight route
CN108693890A (en) * 2017-04-04 2018-10-23 泰勒斯公司 The aircraft decline stage manages
CN108766035A (en) * 2018-06-12 2018-11-06 云南农业大学 A kind of unmanned plane terrain match flight control system under dot density guiding
CN110930770A (en) * 2019-11-06 2020-03-27 南京莱斯信息技术股份有限公司 Four-dimensional track prediction method based on control intention and airplane performance model

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2983594B1 (en) * 2011-12-02 2014-09-26 Thales Sa METHOD FOR MANAGING A VERTICAL FLIGHT PLAN
CN109191925B (en) * 2018-10-17 2020-07-14 中国电子科技集团公司第二十八研究所 A multi-airspace trajectory planning and negotiation method for four-dimensional trajectory operation
CN111444174B (en) * 2020-02-25 2024-06-14 民航数据通信有限责任公司 Method and device for checking and controlling flight program track data

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6134500A (en) * 1999-06-03 2000-10-17 United Air Lines, Inc. System and method for generating optimal flight plans for airline operations control
FR2935495A1 (en) * 2008-08-29 2010-03-05 Thales Sa SYSTEM AND METHOD FOR CALCULATING FLIGHT PREDICTIONS BY VERTICAL SECTIONS
CN101692315A (en) * 2009-09-25 2010-04-07 民航总局空管局技术中心 Method for analyzing high precision 4D flight trajectory of airplane based on real-time radar data
CN101739845A (en) * 2009-12-18 2010-06-16 中国航空无线电电子研究所 Aeronautical data chain information-based civil aircraft aviation electronic verification system and method thereof
CN103093649A (en) * 2011-10-31 2013-05-08 通用电气公司 Methods and systems for inferring aircraft parameters
CN104240541A (en) * 2014-09-09 2014-12-24 中国电子科技集团公司第二十八研究所 4D track generating method
CN105701552A (en) * 2014-10-11 2016-06-22 中国国际航空股份有限公司 Method of calculating vertical section of flight route
CN108693890A (en) * 2017-04-04 2018-10-23 泰勒斯公司 The aircraft decline stage manages
CN108766035A (en) * 2018-06-12 2018-11-06 云南农业大学 A kind of unmanned plane terrain match flight control system under dot density guiding
CN110930770A (en) * 2019-11-06 2020-03-27 南京莱斯信息技术股份有限公司 Four-dimensional track prediction method based on control intention and airplane performance model

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
THALES自动化系统飞行轨迹计算与投递原理浅析;陈玉平;《数字技术与应用》;20170115;全文 *
航空器四维航迹实时预测与动态生成研究;刘杰;《中国优秀硕士学位论文全文数据库》;20200215;全文 *
面向航空器战略航迹规划的风场信息插值方法;汤新民等;《指挥信息系统与技术》;20200116;全文 *

Also Published As

Publication number Publication date
CN112927562A (en) 2021-06-08

Similar Documents

Publication Publication Date Title
CN112927562B (en) A calculation method of aircraft flight altitude profile based on specified altitude limit
CN110930770B (en) Four-dimensional track prediction method based on control intention and airplane performance model
EP3598262B1 (en) Method and system for determining a climb profile
CN107085978B (en) A method for generating control-aided decision-making instructions based on required arrival time
US8645009B2 (en) Method for flying an aircraft along a flight path
CN110991684B (en) Vertical channel optimization
CN111047913B (en) Method and electronic device for optimizing a vertical profile of an aircraft flight
EP2631890A2 (en) Methods for in-flight adjusting of a flight plan
CN111583724A (en) A Pre-tactical Stage Interval Management Method for 4D Track Operation
US9963247B2 (en) Method and system for automatic determination of an optimized descent and approach profile for an aircraft
CN107402576A (en) Method for the reference Vertical Profile of automatic reclosing aircraft
JP2014019431A (en) Systems and methods for flight management
CN110059863B (en) Aircraft four-dimensional track optimization method based on required arrival time
CN105701552B (en) Method for determining vertical section of flight route
CN114283624B (en) Aircraft position prediction method based on air-ground track information sharing
CN110727286B (en) Method and system for determining a descent profile
CN117406767A (en) A method for quickly generating aircraft flight trajectories based on flight plans
CN103578299A (en) Method for simulating flight process of aircraft
CN111142561A (en) A vertical altitude guidance method for a flight management system
CN110889543A (en) RTA sequence allocation method based on four-dimensional track operation
US20250201132A1 (en) Device and method for managing energy for descent and approach phases of an aircraft
CN112882488B (en) Aircraft 4D trajectory prediction method and device
De Jong et al. Time and energy management during descent: Human vs automated response
CN111123977A (en) A time guidance method for flight management system
CN119495214A (en) A method for calculating aircraft routes based on route decomposition

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
CB02 Change of applicant information

Address after: 210000 No.1, Lingshan South Road, Qixia District, Nanjing City, Jiangsu Province

Applicant after: THE 28TH RESEARCH INSTITUTE OF CHINA ELECTRONICS TECHNOLOGY Group Corp.

Address before: 210007 1 East Street, alfalfa garden, Qinhuai District, Nanjing, Jiangsu.

Applicant before: THE 28TH RESEARCH INSTITUTE OF CHINA ELECTRONICS TECHNOLOGY Group Corp.

CB02 Change of applicant information
GR01 Patent grant
GR01 Patent grant