CN114049795A - Method and device for optimizing flight trajectory of aircraft - Google Patents
Method and device for optimizing flight trajectory of aircraft Download PDFInfo
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- CN114049795A CN114049795A CN202111181612.1A CN202111181612A CN114049795A CN 114049795 A CN114049795 A CN 114049795A CN 202111181612 A CN202111181612 A CN 202111181612A CN 114049795 A CN114049795 A CN 114049795A
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Abstract
The invention discloses a method and a system for optimizing the flight path of an airplane, wherein the method for optimizing the flight path of the airplane comprises the following steps: receiving an arrival time control constraint of an aircraft route; receiving real-time and predicted atmospheric conditions of an aircraft route; acquiring data related to aircraft operation constraints and real-time aircraft state and performance; generating a plurality of sets of values for one or more flight trajectory optimization parameters, the flight trajectory optimization parameters including at least flight cruise altitude; calculating the flight trajectory of the aircraft by using the received atmospheric conditions, aircraft operation constraints and real-time aircraft state and performance data for the generated value set of the flight trajectory optimization parameters; selecting at least one optimal flight cruise altitude based on optimization criteria, wherein the calculated flight trajectory meets the arrival time control constraint; at least one track change alert is generated with the selected optimal flight cruise altitude.
Description
[ technical field ] A method for producing a semiconductor device
The invention relates to a method and equipment for optimizing the flight path of an airplane when the airplane runs under RTA (real time assembly) constraint, in particular to a device for providing a flight path optimization suggestion under the track-based running, and belongs to the technical field of aircraft navigation.
[ background of the invention ]
With the increasing of air traffic flow, a new flight system based on an advanced flight management system needs to be established urgently, and flight path-based operation (TBO) is supported by improving the flight path prediction and optimization capability of the existing flight management system. Currently, air traffic control modernization projects such as the next generation air traffic system (NextGen) in the united states and the single sky program (SESAR) project in the european union are developed in all countries in the world, and China is also tightening to promote the air traffic control modernization.
Flight Management Systems (FMS) of modern aircraft allow pilots to operate the aircraft under a Required Time of Arrival (RTA) constraint by setting the required time of arrival at a particular waypoint on the airways. Based on the RTA, the FMS iterates according to a planned speed plan to ensure that waypoints are reached at the required times.
Aircraft typically determine the planned speed plan for flight operations based on a Cost Index (CI) selected by the airline to save fuel at the most economical speed. CI describes a trade-off between time cost and fuel cost. However, when the pilot is required to comply with RTA limits in flight, the time limit will dictate the new speed plan to follow. Thus, the current flight trajectory optimization strategy is to find a new RTA-compliant aircraft airspeed, such as by iterating the CI to obtain a new speed plan. In this case, the economic optimum has become a secondary requirement, and the total cost of flight increases.
Furthermore, limitations in RTA may not only bias the speed plan away from economic optimum, but may even push it toward the aircraft's operating limits (lowest and highest operating airspeeds). In such a case, the arrival time required to reach a given waypoint may be prevented due to unpredictable wind and temperature variations before the aircraft flies to the leg where the RTA is required, because it may not be possible to continue accelerating (if the highest operating speed is approached) or to decelerate further (if the lowest operating speed is approached). Due to the minimum or maximum operating airspeed, the RTA limit may not be reached at the current cruise altitude when initially set in the FMS. In both cases, the pilot receives a "RTA unsatisfied" message to indicate that the RTA cannot be satisfied.
[ summary of the invention ]
The invention aims to provide a method and a system for optimizing a flight path of an airplane, which are used for optimizing the flight path of the airplane under the condition of considering the requirement arrival time (RTA) constraint, providing a pilot to quickly preview the requirement arrival time (RTA) instruction of a controller, previewing a current flight plan and whether the performance of the airplane can meet the requirement arrival time (RTA) instruction, realizing a flight path optimization program under the condition of meeting the requirement arrival time (RTA) constraint, improving the economy of flight and realizing an alarm function when the requirement arrival time (RTA) instruction cannot be met.
In order to achieve the above object, the method for optimizing the flight trajectory of an aircraft according to the present invention comprises the following steps:
the method comprises the following steps: receiving one or more time-of-arrival control constraints for an aircraft route;
step two: receiving at least one real-time and predicted atmospheric condition relating to an aircraft route;
step three: acquiring data related to aircraft operation constraints and real-time aircraft state and performance;
step four: generating a plurality of sets of values for one or more flight trajectory optimization parameters, the one or more flight trajectory optimization parameters including at least a flight cruise altitude, such that all of the generated sets of values include a flight cruise altitude different from a current aircraft altitude;
step five: calculating a flight trajectory of the aircraft using the received atmospheric conditions and aircraft operational constraints and real-time aircraft state and performance data for the generated value set of one or more flight trajectory optimization parameters;
step six: selecting at least one optimal flight cruise altitude based on one or more optimization criteria, the calculated flight trajectory complying with an arrival time control constraint;
step seven: at least one track change alert is generated with the selected optimal flight cruise altitude.
According to the main feature above, the method may further comprise notifying the aircraft pilot of the trajectory change alert and receiving a new optimal flight cruise altitude from the aircraft pilot and communicating the new optimal flight cruise altitude to a flight management system of the aircraft. Alternatively, the method may include notifying the aircraft pilot of a trajectory change alert and manually inputting the new optimal flight cruise altitude to the aircraft's flight management system.
According to the main feature, the method further comprises, if the new trajectory fails to comply with the RTA constraint, performing another iteration up to a predefined maximum number of iterations, terminating the iteration if the maximum number of iterations has been reached, and informing the pilot that the required arrival time cannot be met, displaying a "required arrival time cannot be met" message.
To achieve the above object, a system for optimizing the flight trajectory of an aircraft embodying the present invention comprises:
the input module is used for receiving information input by a pilot;
a communication module in communication with the on-board flight management system for receiving atmospheric conditions relating to an aircraft route, and further for receiving data relating to aircraft operational constraints and real-time aircraft state and performance;
an optimization module that receives the data retrieved from the communication module, the required arrival time constraints and the one or more flight trajectory optimization parameters, the optimization module comprising a flight trajectory generator that generates a plurality of sets of values for the one or more flight trajectory optimization parameters such that all of the generated sets of values include a flight cruise altitude that is different from the current aircraft altitude, the flight trajectory generator calculating a flight trajectory of the aircraft for the generated sets of values of the flight trajectory optimization parameters while taking into account the received atmospheric conditions and data regarding aircraft operational constraints and real-time aircraft state and performance, and using a cost function to select, based on one or more optimization criteria, one or more optimal flight cruise altitudes having calculated flight trajectories that meet the arrival time control constraints;
and the display and alarm module is used for generating a track change alarm according to one or more selected optimal flight cruise altitudes.
According to the above main feature, wherein the input module is an input device such as a keyboard, a mouse or a touch screen, the pilot can establish a required arrival time constraint through the input module.
According to the main characteristics, the communication module is communicated with a flight management system of the airplane through an airborne AFDX network to receive real-time airplane data and atmospheric conditions.
In accordance with the above main features, the optimization module receives data retrieved from the communication module, RTA constraints and one or more flight trajectory optimization parameters, wherein the optimization parameters include at least flight cruise altitude and optionally aircraft airspeed, and wherein the required arrival time constraints include a required arrival time for at least one waypoint, and wherein the optimization parameters are either pre-established and stored in memory or are selectable by the pilot via the input module.
According to the above main feature, the communication module, the optimization module and the display and alarm module can be implemented in an electronic device, and the optimization module is an application installed in the electronic device.
Compared with the prior art, the method for optimizing the flight trajectory of the airplane can optimize a plurality of trajectory parameters by combining the flight altitude, and has the following beneficial effects:
(1) by flying at different altitudes at more economical airspeeds, fuel is saved during RTA operation.
(2) When the atmospheric conditions change, the situation that the RTA cannot be met occurs, and the pilot can be informed.
(3) Increasing the feasible time range of arrival at a given waypoint (increasing the time control margin) allows the aircraft to advance or retard arrival without changing routes.
[ description of the drawings ]
FIG. 1 is a schematic flow chart of a method for optimizing the flight trajectory of an aircraft embodying the present invention.
FIG. 2 is a block diagram illustrating components of a system for optimizing the flight trajectory of an aircraft embodying the present invention.
[ detailed description ] embodiments
The method of optimizing the flight trajectory of an aircraft embodying the invention first establishes an RTA constraint (e.g. input by the pilot or selected in the FMS), while performing calculations in the speed and altitude domains to find a new flight trajectory that meets the selected RTA time constraint, while determining the flight path constraint requirements of the aircraft, including: the method comprises the steps of speed constraint, altitude constraint, point passing mode and RTA, calculating an optimized flight path meeting constraint conditions based on flight path constraint requirements, calculating an estimated arrival time window of an aircraft to reach RTA flight path points, and checking whether the RTA requirements are met. And in consideration of the forecast wind of the current cruise altitude, searching a new speed plan which accords with the set RTA, if the new track cannot accord with the RTA constraint, executing another iteration, and reaching the maximum predefined maximum iteration number, terminating the iteration in advance, if the speed plan which accords with the RTA constraint is found, providing an updated forecast track, displaying and setting the new track to be started to a flight management system as a guidance reference, and if the RTA constraint cannot be realized, informing a pilot that the RTA cannot be met, and displaying a message that the RTA cannot be met.
Fig. 1 is a schematic flow chart of a method for optimizing a flight path of an aircraft according to the present invention. The method for optimizing the flight path of the airplane comprises the following steps:
the method comprises the following steps: receiving one or more time-of-arrival control constraints for an aircraft route;
step two: receiving at least one real-time and predicted atmospheric condition relating to an aircraft route;
step three: acquiring data related to aircraft operation constraints and real-time aircraft state and performance;
step four: generating a plurality of sets of values for one or more flight trajectory optimization parameters, the one or more flight trajectory optimization parameters including at least a flight cruise altitude, such that all of the generated sets of values include a flight cruise altitude different from a current aircraft altitude;
step five: calculating a flight trajectory of the aircraft using the received atmospheric conditions and aircraft operational constraints and real-time aircraft state and performance data for the generated value set of one or more flight trajectory optimization parameters;
step six: selecting at least one optimal flight cruise altitude based on one or more optimization criteria, the calculated flight trajectory complying with an arrival time control constraint;
step seven: at least one track change alert is generated with the selected optimal flight cruise altitude.
The method may also include notifying the aircraft pilot of the trajectory change alert and receiving a new optimal flight cruise altitude from the aircraft pilot and communicating the new optimal flight cruise altitude to a flight management system of the aircraft. Alternatively, the method may include notifying the aircraft pilot of a trajectory change alert and manually inputting the new optimal flight cruise altitude to the aircraft's flight management system.
The flight trajectory optimization parameters further include aircraft airspeed such that the generated value set includes different pairs of flight cruise altitude and aircraft airspeed, and the trajectory change alert includes at least one pair of an optimal flight cruise altitude and an optimal aircraft airspeed having a calculated flight trajectory that meets the arrival time control constraints. Optimization criteria may include fuel savings, speed control margins, and time control margins to meet time of arrival control constraints.
Data regarding real-time aircraft status and performance may include, for example, real-time aircraft mass and flight performance data, real-time fuel consumption rate, fuel consumption, and fuel remaining data. The data of the aircraft operating constraints and the real-time aircraft state and performance are preferably retrieved from a flight management system of the aircraft. The atmospheric conditions preferably comprise wind conditions and/or temperature conditions. The time of arrival control constraint may include a desired arrival time of the at least one waypoint.
The method for optimizing the flight path of the airplane further comprises executing another iteration if the new path cannot meet RTA constraints, stopping the iteration in advance when the maximum number of the iteration reaches the predefined maximum number of the iteration, informing a pilot that the RTA cannot be met, and displaying a message that the RTA cannot be met.
Fig. 2 is a block diagram of a system for optimizing the flight trajectory of an aircraft according to the present invention. The system for optimizing the flight path of the airplane comprises an input module, an optimization module, a display and alarm module and a communication module, and the functions of the modules are explained in detail below.
The input module can be an input device such as a keyboard, a mouse or a touch screen, and the pilot can establish an RTA constraint or input other related information through the input module.
A communication module, in accordance with a security/encryption protocol, communicates with the on-board flight management system via bluetooth, WIFI or any other wireless protocol, for receiving atmospheric conditions (real-time and/or predicted, and preferably including wind conditions) about the aircraft airline, and may also receive data about aircraft operating constraints and real-time aircraft status and performance. The communication module is communicated with a flight management system of the airplane through an airborne AFDX network, and receives real-time airplane data and atmospheric conditions.
The optimization module receives data retrieved from the communication module, RTA constraints, and one or more flight trajectory optimization parameters, wherein the optimization parameters include at least flight cruise altitude and may also include aircraft airspeed. The RTA constraints typically include the RTA of at least one waypoint. The optimization parameters may be pre-established and stored in an internal memory (not shown) of the electronic device, or may be selected by the pilot through an input module. The optimization module includes a flight trajectory generator that generates a plurality of value sets for one or more flight trajectory optimization parameters such that all of the generated value sets include a flight cruise altitude that is different from a current aircraft altitude. For example, if the optimization parameters include flight cruise altitude and aircraft airspeed, the generated values are paired (altitude, speed) values for which the altitude is different from the current aircraft altitude. The flight trajectory generator calculates the flight trajectory of the aircraft for the generated set of values of the flight trajectory optimization parameters while taking into account the received atmospheric conditions and data regarding aircraft operating constraints and real-time aircraft state and performance. The flight trajectory generator uses a cost function to select one or more optimal flight cruise altitudes having calculated flight trajectories that meet time-of-arrival control constraints based on one or more optimization criteria, which may include fuel economy, speed control margin, and/or time control margin.
The display and alert module is configured to generate a trajectory change alert based on one or more selected optimal flight cruise altitudes. For example, a trajectory change alert is displayed indicating an alternate optimal flight cruise altitude/second, for which fuel is saved or RTA robustness is improved, and a potential corresponding benefit (e.g., new altitudes are expected to save 250 kilograms of fuel). The pilot will then decide whether to accept an optimized flight trajectory with a different cruising altitude and a different aircraft airspeed, and the pilot may then choose to download the new optimized trajectory to the flight management system via the communication unit to generate a new flight trajectory.
In an implementation, the communication module, the optimization module, and the display and alarm module may be implemented in an electronic device, such as a laptop, a tablet, or a handheld electronic device, and the optimization module may be an application (e.g., APP) installed in the electronic device.
The method for optimizing the flight path of an aircraft according to the invention takes into account not only the change of speed plan, but also the change of cruising altitude and the use of corresponding wind conditions. The method may also take into account changes in aircraft airspeed as the cruising altitude changes. Changing the new optimal flight cruise altitude may improve fuel efficiency and enhance the robustness of the arrival time control. Fuel consumption refers to the amount of fuel burned along a route section under control of arrival time. To comply with the RTA limits, the aircraft needs to fly along a known distance at a given ground speed in order to reach the RTA waypoint at the correct time. Since the wind conditions at different altitudes are likely to be different, fuel consumption can potentially be reduced by climbing or descending to a new cruising altitude at which the required ground speed corresponds to a more efficient airspeed which directly affects the airspeed corresponding to the required ground speed, so that wind conditions also need to be taken into account when finding the most fuel efficient cruising altitude. At the same time, the new optimal flight cruise altitude may also provide robustness in time of arrival control, thereby improving speed control margins and time control margins. The speed control margin refers to a margin for the aircraft to increase or decrease speed in order to correct unexpected deviations and comply with established RTA limits. The speed control margin is closely related to the cruising altitude of the aircraft, which directly affects the minimum and maximum flying vacuum speeds (TAS). Unknown external disturbances, such as wind speed and wind direction, directly affect the ground speed of the aircraft and thus the feasibility of complying with the RTA constraints. Extending the speed margin by changing the cruising altitude may directly increase the chance of restricting the waypoint at the correct time of arrival. According to the lowest aviation system performance standard ("required navigation performance for area navigation", DO2360 change 1, section 2.2.1), the deviation from the RTA waypoint should not be more than 30 seconds in 95% of all operations.
Implementing the method of optimizing the flight trajectory of an aircraft of the present invention also allows improving the temporal control margin, which refers to the time interval defining the potential range of arrival times achievable around the currently estimated arrival time (ETA) at the time-constrained waypoint. The time control margin is increased in proportion to the speed control margin, the slower or faster the ground speed that may be achieved, the later or earlier the time of arrival that may be achieved.
Compared with the prior art, the method for optimizing the flight path of the airplane provides a novel flight path optimization method, the method can be combined with a vertical section (airplane height) to optimize a plurality of path parameters, such as a speed section, and the method has the following beneficial effects:
(1) by flying at different altitudes at more economical airspeeds, fuel is saved during RTA operation.
(2) When the atmospheric conditions change, the situation that the RTA cannot be met occurs, and the pilot can be informed.
(3) Increasing the feasible time range of arrival at a given waypoint (increasing the time control margin) allows the aircraft to advance or retard arrival without changing routes.
The method for optimizing the flight path of the airplane can be directly applied to various manned airplanes, generates an accurate and optimized four-dimensional flight path and sends the accurate and optimized four-dimensional flight path to the ground ATM, and after the negotiation is consistent, the flight performance can be monitored, so that the airplane capacity can be effectively improved, and the method can better adapt to air traffic control modernization.
It should be understood that equivalents and modifications of the technical solution and inventive concept thereof may occur to those skilled in the art, and all such modifications and alterations should fall within the scope of the appended claims.
Claims (9)
1. A method for optimizing the flight path of an airplane is characterized by comprising the following steps:
the method comprises the following steps: receiving one or more time-of-arrival control constraints for an aircraft route;
step two: receiving at least one real-time and predicted atmospheric condition relating to an aircraft route;
step three: acquiring data related to aircraft operation constraints and real-time aircraft state and performance;
step four: generating a plurality of sets of values for one or more flight trajectory optimization parameters, the one or more flight trajectory optimization parameters including at least flight cruise altitude;
step five: calculating a flight trajectory of the aircraft using the received atmospheric conditions and aircraft operational constraints and real-time aircraft state and performance data for the generated value set of one or more flight trajectory optimization parameters;
step six: selecting at least one optimal flight cruise altitude based on one or more optimization criteria, the calculated flight trajectory complying with an arrival time control constraint;
step seven: at least one track change alert is generated with the selected optimal flight cruise altitude.
2. A method of optimizing the flight trajectory of an aircraft as defined in claim 1, wherein: the method also includes notifying the aircraft pilot of the trajectory change alert and receiving a new optimal flight cruise altitude from the aircraft pilot and communicating the new optimal flight cruise altitude to a flight management system of the aircraft.
3. A method of optimizing the flight trajectory of an aircraft as defined in claim 1, wherein: the method also includes notifying the aircraft pilot of the change of trajectory alert and manually inputting the new optimal flight cruise altitude to a flight management system of the aircraft.
4. A method of optimizing the flight trajectory of an aircraft as defined in claim 1, wherein: the method further includes performing another iteration up to a predefined maximum number of iterations if the new trajectory fails to meet the required arrival time constraint, terminating the iteration if the maximum number of iterations has been reached, and notifying the pilot that the required arrival time cannot be met, displaying a "required arrival time cannot be met" message.
5. A system for optimizing the flight trajectory of an aircraft, the system comprising:
the input module is used for receiving information input by a pilot;
a communication module in communication with the on-board flight management system for receiving atmospheric conditions relating to an aircraft route, and further for receiving data relating to aircraft operational constraints and real-time aircraft state and performance;
an optimization module that receives the data retrieved from the communication module, the required arrival time constraints and the one or more flight trajectory optimization parameters, the optimization module comprising a flight trajectory generator that generates a plurality of sets of values for the one or more flight trajectory optimization parameters such that all of the generated sets of values include a flight cruise altitude that is different from the current aircraft altitude, the flight trajectory generator calculating a flight trajectory of the aircraft for the generated sets of values of the flight trajectory optimization parameters while taking into account the received atmospheric conditions and data regarding aircraft operational constraints and real-time aircraft state and performance, and using a cost function to select, based on one or more optimization criteria, one or more optimal flight cruise altitudes having calculated flight trajectories that meet the arrival time control constraints;
and the display and alarm module is used for generating a track change alarm according to one or more selected optimal flight cruise altitudes.
6. The system for optimizing flight trajectory for an aircraft of claim 5, wherein: the input module is an input device such as a keyboard, a mouse or a touch screen, and the pilot establishes a required arrival time constraint through the input module.
7. The system for optimizing flight trajectory for an aircraft of claim 5, wherein: the communication module is communicated with a flight management system of the airplane through an airborne AFDX network, and receives real-time airplane data and atmospheric conditions.
8. The system for optimizing flight trajectory for an aircraft of claim 5, wherein: the optimization module receives data retrieved from the communication module, RTA constraints and one or more flight trajectory optimization parameters, wherein the optimization parameters include at least flight cruise altitude and aircraft airspeed, the required arrival time constraints include a required arrival time for at least one waypoint, and the optimization parameters are pre-established and stored in memory or are selectable by the pilot via the input module.
9. The system for optimizing flight trajectory for an aircraft of claim 5, wherein: the communication module, the optimization module and the display and alarm module are realized in an electronic device, and the optimization module is an application program installed in the electronic device.
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