A system for determining carbon emissions of target aircraft

Abstract

The present invention provides a target aircraft carbon emission determination system, which relates to the technical field of aircraft carbon emission determination. The system comprises: obtaining the flight time T of the target aircraft on a target flight path, the take-off weight of the target aircraft, the flight altitude and the flight speed of the target aircraft in the level flight phase on the target flight path, and determining the carbon emission calculation weight corresponding to the target aircraft from a preset carbon emission calculation weight mapping table according to the model of the target aircraft, so as to determine the carbon emissions in the climbing phase, the level flight phase and the landing phase, and then obtain the carbon emissions corresponding to the target aircraft flying on the target flight path; the present invention can make the determined carbon emissions corresponding to the target aircraft flying on the target flight path more accurate.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft carbon emission determination, and in particular to a target aircraft carbon emission determination system. Background Art

[0002] Against the backdrop of the global climate crisis, achieving low-carbon aviation has become a vital issue; however, the premise for achieving low-carbon aviation is how to accurately calculate the carbon emissions caused by aircraft flights; in the prior art, the calculation of carbon emissions caused by aircraft flights is usually based on the distance the aircraft flies; however, there are many different types of aircraft, and different types of aircraft have different weights and engine parameters, and the flight states corresponding to the same flight path are also different. The above factors will lead to large differences in the carbon emissions of aircraft when flying the same distance. If the corresponding carbon emissions are determined only by the flight distance, the accuracy of the determined carbon emissions will be low. Summary of the invention

[0003] The present invention provides a target aircraft carbon emission determination system to solve the technical problem of low accuracy of the aircraft carbon emission determination in the prior art.

[0004] According to a target aircraft carbon emissions determination system provided by the present application, the system includes: a processor and a storage medium, wherein the storage medium stores at least one instruction or at least one program, and the at least one instruction or the at least one program is loaded by the processor to implement the following steps:

[0005] S100, obtaining a target flight path corresponding to the target aircraft; wherein the target flight path is any historical flight path corresponding to the target aircraft;

[0006] S200, obtaining the flight time T of the target aircraft on the target flight path, the take-off weight M of the target aircraft, the flight altitude H and the flight speed V of the target aircraft in the level flight phase on the target flight path;

[0007] S300, according to the model of the target aircraft, determining the carbon emission calculation weight corresponding to the target aircraft from a preset carbon emission calculation weight mapping table; wherein the carbon emission calculation weight mapping table includes a number of different aircraft models and the carbon emission calculation weight corresponding to each aircraft model;

[0008] S400: If the computing power of the target device is greater than the preset computing power threshold, the carbon emissions Q of the target aircraft during the climb phase on the target flight path are determined based on T, M, H, V and the corresponding calculation weight of the target aircraft. 1 , Carbon emissions during level flight Q 2 and the carbon emissions during the landing phase Q3 ; The target device is used to calculate the carbon emissions generated by the target aircraft along the target flight path;

[0009] S500, according to Q 1 , Q 2 and Q 3 , determine the carbon emissions corresponding to the target aircraft flying on the target flight path Q = Q 1 +Q 2 +Q 3 ; Among them, Q is positively correlated with M, V and T, and negatively correlated with H.

[0010] The present invention has at least the following beneficial effects:

[0011] The target aircraft carbon emissions determination system of the present invention obtains the flight time T of the target aircraft on the target flight path, the take-off weight of the target aircraft, the flight altitude and the flight speed of the target aircraft in the level flight phase on the target flight path, and determines the carbon emissions calculation weight corresponding to the target aircraft from a preset carbon emissions calculation weight mapping table according to the model of the target aircraft, so as to determine the carbon emissions in the climb phase, the level flight phase and the landing phase, and then obtain the carbon emissions corresponding to the target aircraft flying on the target flight path; in the present invention, when determining the carbon emissions corresponding to the target aircraft flying on the target flight path, the flight time of the target aircraft on the target flight path, the take-off weight of the target aircraft, the flight altitude and the flight speed of the target aircraft in the level flight phase on the target flight path are comprehensively considered; in addition, when aircraft of different models fly on the same route, the corresponding carbon emissions calculation weights are different, so that the determined carbon emissions corresponding to the target aircraft flying on the target flight path are more accurate.

[0012] Furthermore, the prior art calculates carbon emissions through fixed routes, but incorporates fewer factors and results of inaccurate carbon emissions calculations; while the method of calculating carbon emissions through flight trajectory points requires greater computing power; the method in the present invention divides the flight trajectory into three stages for calculation. Compared with the prior art method of calculating carbon emissions based on fixed routes, the calculation results of carbon emissions are more accurate. Compared with the method of calculating carbon emissions based on flight trajectory points, less computing power is required to calculate carbon emissions. While ensuring the accuracy of carbon emissions calculations, computing power is saved and the scope of use is wider. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0014] Figure 1 A flowchart of steps executed by a processor of a target aircraft carbon emissions determination system provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0015] The technical solutions in the embodiments of the present application are described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by technicians in the relevant technical field without creative work are within the scope of protection of the present application.

[0016] It is noteworthy that in the following description, specific details such as specific system structures, technologies, etc. are proposed for the purpose of illustration rather than limitation, so as to provide a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application can also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to prevent unnecessary details from hindering the description of the present application.

[0017] It should be understood that when used in the present specification and the appended claims, the term "comprising" indicates the presence of the described features, integrals, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or their collections. It should also be understood that when the term "and / or" is used in the present specification and the appended claims, it refers to any combination of one or more of the associated listed items and all possible combinations, and includes these combinations.

[0018] In the description of the present specification and the appended claims, if the term "if" is used, it can be interpreted as "in the case of" or "when" or "uponce" or "in response to determining" or "in response to detecting" according to the context. Similarly, the phrase "if it is determined" or "if [the described condition or event] is detected" can be interpreted as meaning "uponce it is determined" or "in response to determining" or "uponce [the described condition or event] is detected" or "in response to detecting [the described condition or event]" according to the context.

[0019] In the description of this application specification and the appended claims, the terms "first", "second", "third", etc., are only used to distinguish the description and are not to be understood as indicating or implying relative importance, nor are they used to describe a specific order or sequence.

[0020] The following will refer to Figure 1A flow chart of steps executed by a processor of a target aircraft carbon emissions determination system is shown, and a target aircraft carbon emissions determination system is introduced.

[0021] The target aircraft carbon emissions determination system includes: a processor and a storage medium, wherein the storage medium stores at least one instruction or at least one program, and the at least one instruction or at least one program is loaded by the processor to implement the following steps:

[0022] S100, obtaining a target flight path corresponding to the target aircraft; wherein the target flight path is any historical flight path corresponding to the target aircraft.

[0023] In this embodiment, the target aircraft can be any civil aircraft. The target aircraft has several corresponding flight paths within a preset historical time period, and the target flight path is any of the several flight paths; for example: the target flight path is the flight path corresponding to a certain type of aircraft flying from location 1 to location 2 at a specific time; it can be understood that, when flying from location 1 to location 2, the flight paths corresponding to different aircraft may be different.

[0024] S200, obtaining the flight time T of the target aircraft on the target flight path, the take-off weight M of the target aircraft, the flight altitude H and the flight speed V of the target aircraft in the level flight phase on the target flight path.

[0025] In this embodiment, information such as flight duration T, flight altitude H, and flight speed can be obtained through the ADS-B data generated when the target aircraft flies on the target flight path; the take-off weight M of the target aircraft can be directly determined through the flight parameters of the target aircraft; the flight altitude is the altitude, which can be the average flight altitude of the target aircraft in the level flight phase; the flight speed can be the average flight speed in the level flight phase.

[0026] S300, according to the model of the target aircraft, determine the carbon emission calculation weight corresponding to the target aircraft from a preset carbon emission calculation weight mapping table; wherein the carbon emission calculation weight mapping table includes several different aircraft models and the carbon emission calculation weight corresponding to each aircraft model.

[0027] In this embodiment, a carbon emission calculation weight mapping table is preset, which includes several different aircraft models, and each aircraft model corresponds to a carbon emission calculation weight; the carbon emission calculation weight corresponding to the target aircraft may include a first carbon emission calculation weight B and a second carbon emission calculation weight β.

[0028] In this embodiment, the first carbon emission calculation weight B and the second carbon emission calculation weight β can be obtained by the following steps:

[0029] S310, determine the relationship between the carbon emissions of the target aircraft and the flight time T of the target aircraft on the target flight path, the take-off weight M of the target aircraft, the flight altitude H of the target aircraft in the level flight phase on the target flight path, and the flight speed V, that is, Q=x×M×(V×T / H) y ; Where Q is the carbon emissions corresponding to a certain flight path of the target aircraft, and x and y are the calculation weights.

[0030] S320, obtaining flight parameters corresponding to each flight path in several historical flight paths of the target aircraft; the flight parameters include the flight time of the target aircraft on the corresponding flight path, the take-off weight of the target aircraft, the flight altitude and flight speed of the target aircraft in the level flight phase on the target flight path.

[0031] S330, based on Q = x × M × (V × T / H) y The flight parameters obtained in S320 are used to solve the equation to obtain the values ​​of x and y, that is, the first carbon emission calculation weight B=x and the second carbon emission calculation weight β=y corresponding to the target aircraft are obtained.

[0032] When solving the equation, we can use Q=x×M×(V×T / H) y Find the logarithm, then solve the linear equation, and determine x and y using the least squares method.

[0033] In this embodiment, Q = x × M × (V × T / H) y The derivation principle is as follows:

[0034] It is understandable that if the aircraft is in the level flight stage, then the carbon emissions of the aircraft are mainly related to the aircraft's weight M, a series of aircraft parameters μ, flight altitude H, flight speed V and flight time T; thus, a functional relationship Q=f(M, μ, H, V, T) is established between carbon emissions and the above parameters; for fixed models, μ can be ignored, and Q=f(M, H, V, T) is obtained.

[0035] Based on the above relationship, further analysis: If Q = x × M b1 ×H b2 ×V b3 ×T b4 ; It can be further converted by dimensional analysis: the unit of Q is kg, x is a coefficient and has no dimension, the dimension of M is kg, the dimension of H is m, the dimension of V is m / s, and the dimension of T is s; and then the dimensional relationship kg= (kg) is obtained b1 × (m) b2 × (m) b3 ×(s) -b3+b4; Then we get b1=1, b2=-b3=-b4; let y=b2=-b3=-b4, we can get: relationship Q=x×M×(V×T / H) y .

[0036] S400: If the computing power of the target device is greater than the preset computing power threshold, the carbon emissions Q of the target aircraft during the climb phase on the target flight path are determined based on T, M, H, V and the corresponding calculation weight of the target aircraft. 1 , Carbon emissions during level flight Q 2 and the carbon emissions during the landing phase Q 3 ; The target device is used to calculate the carbon emissions generated by the target aircraft along the target flight path.

[0037] In this embodiment, Q = B × M × (V × T / H) β ; β>0; It can be understood that the greater the take-off weight of the target aircraft, the faster the speed and the longer the flight time, the more fuel will be consumed, and accordingly, the corresponding carbon emissions of the target aircraft should also be greater; the higher the flight altitude of the target aircraft, the smaller the wind resistance during flight, the higher the engine efficiency, and accordingly, the smaller the corresponding carbon emissions of the target aircraft; the relationship conforms to the above formula.

[0038] In this embodiment, the computing power of the target device for calculating carbon emissions can be first obtained. If the computing power of the target device is greater than the preset computing power threshold, a more accurate carbon emission calculation method can be executed, that is, the entire flight process is divided into the take-off phase, the level flight phase and the landing phase, and the carbon emissions of each phase are calculated separately.

[0039] Further, the carbon emission calculation weight corresponding to the target aircraft includes a first carbon emission calculation weight B and a second carbon emission calculation weight β; after step S400 and before step S500, the following steps are also included:

[0040] S401: If the computing power of the target device is less than or equal to the preset computing power threshold, determine Q=B×M×(V×T / H) based on T, M, H, V, B and β. β ;β>0.

[0041] In this embodiment, if the computing power of the target device is less than or equal to the preset computing power threshold, the flight process of the target aircraft can be regarded as a whole flight process to calculate the carbon emissions, and the calculation process is relatively simple and the calculation efficiency is high; however, when the flight distance is short, the target aircraft will have two stages in the flight process, namely the climbing stage and the landing stage; when the flight distance is long, there will be a climbing stage, a level flight stage and a landing stage; in different stages, the fuel consumption rate of the target aircraft is different, and the fuel consumption rate in the climbing stage is greater than the fuel consumption rate in the level flight stage and the landing stage; the fuel consumption rates are different, and the corresponding carbon emissions calculation weights should also be different.

[0042] Further, based on the above situation, in order to improve the accuracy of aircraft carbon emission calculation, after step S200 and before step S300, the following steps are further included:

[0043] S210, dividing the target flight path into a climbing phase, a level flight phase, and a landing phase according to historical flight information of the target aircraft on the target flight path.

[0044] In this embodiment, the corresponding flight trajectory generated according to each flight trajectory point corresponding to the target aircraft on the target flight path can determine the flight trajectory point corresponding to the dividing point between the climbing phase and the level flight phase, and the flight trajectory point corresponding to the dividing point between the level flight phase and the landing phase, and then divide the target flight path into the climbing phase, the level flight phase and the landing phase.

[0045] S220, obtain the flight time T of the target aircraft in the climbing phase 1 , the flight time in the level flight phase is T 2 And the flight time T during the landing phase 3 ; Among them, T 1 +T 2 +T 3 =T.

[0046] In this embodiment, according to the take-off time point t corresponding to the target aircraft 0 , landing time t 1 , the time point t corresponding to the flight trajectory point corresponding to the dividing point between the climb phase and the level flight phase 2 , and the time point t corresponding to the flight trajectory point corresponding to the dividing point between the level flight phase and the landing phase 3 , we can determine T 1 =t 2 -t 0 ; T 2 =t 3 -t 2 ; T 3 =t1 -t 3 .

[0047] Further, step S300 includes the following steps:

[0048] S310, according to the model of the target aircraft, determine the third carbon emission calculation weight A corresponding to the target aircraft in the climb phase from a preset carbon emission calculation weight mapping table. 1 and the fourth carbon emission calculation weight α1, the fifth carbon emission calculation weight A during the level flight phase 2 and the sixth carbon emission calculation weight α2, and the seventh carbon emission calculation weight A during the landing phase 3 And the eighth carbon emission calculation weight α3.

[0049] In this embodiment, after the flight process of the target aircraft is divided into a climbing phase, a level flight phase and a landing phase, the climbing phase, the level flight phase and the landing phase respectively correspond to a set of carbon emission calculation weights; the carbon emission calculation weights of the climbing phase, the level flight phase and the landing phase corresponding to different types of aircraft can be determined respectively by the method in steps S310-S330, thereby obtaining the carbon emission calculation weight mapping table in this embodiment.

[0050] Further, step S400 may include the following steps:

[0051] S410, obtaining the altitude H of the target aircraft at takeoff 1 And the altitude H at which the vehicle lands 2 ;

[0052] S420, according to T 1 , M, H 1 ,H,V,A 1 and α1, determine the carbon emissions Q of the target aircraft during the climb phase of the target flight path 1 =A 1 ×M×(V×T 1 / (HH 1 ) α1 ; A 1 >0,α1>0.

[0053] S430, according to T 2 , M, H, V, A 2 and α2, determine the carbon emissions Q of the target aircraft during the level flight phase of the target flight path 2 =A 2 ×M×(V×T 2 / H) α2 ; A 2 >0,α2>0.

[0054] S440, according to T 3 , M, H, V, A 1 and α3, determine the carbon emissions Q of the target aircraft during the landing phase of the target flight path 3 =A 3 ×M×(V×T 3 / (HH 2 ) α3 ; A 3 >0,α3>0.

[0055] Further, step S430 may include the following steps:

[0056] S431, obtaining the flight altitude corresponding to each flight trajectory point of the target aircraft in the level flight phase on the target flight path.

[0057] S432, obtaining the standard deviation of the flight altitude corresponding to all flight trajectory points in the level flight phase.

[0058] S433, if the standard deviation is less than the preset flight altitude standard deviation threshold, 2 , M, H, V, A 2 and α2, determine the carbon emissions Q of the target aircraft during the level flight phase of the target flight path 2 =A 2 ×M×(V×T 2 / H) α2 .

[0059] In this embodiment, the target aircraft may encounter obstacles during the level flight phase, for example, avoiding clouds. In this case, it is usually necessary to first climb to a height higher than the highest point of the obstacle, then fly over the obstacle, and finally descend to the flight altitude before climbing. When the target aircraft is climbing, the flight altitude will change significantly. If there is no obstacle to avoid, the altitude will not change significantly. Therefore, if the standard deviation of the flight altitudes corresponding to all flight trajectory points during the level flight phase is less than the preset flight altitude standard deviation threshold, it is determined that the target aircraft does not have the obstacle to avoid, and the target aircraft can be determined based on T 2 , M, H, V, A 2 and α2 determines Q 2 .

[0060] Furthermore, after step S433, the following contents are also included:

[0061] S434: If the standard deviation is greater than a preset flight altitude standard deviation threshold, each flight trajectory point in the level flight phase is sorted according to the chronological order of the flight trajectory points.

[0062] In this embodiment, if the standard deviation is greater than the preset flight altitude standard deviation threshold, it indicates that the target aircraft is avoiding obstacles during the level flight phase; at this time, the flight trajectory points can be sorted according to the time of each flight trajectory point corresponding to the level flight phase.

[0063] S435, obtaining a flight altitude difference between a latter flight trajectory point and a former flight trajectory point of two adjacent flight trajectory points in the sorted flight trajectory points.

[0064] S436, traverse all flight altitude differences, determine the flight trajectory points corresponding to the flight altitude differences greater than the first preset flight altitude difference threshold as the flight trajectory points of the sub-climbing phase, and determine the flight trajectory points corresponding to the flight altitude differences less than the second preset flight altitude difference threshold as the flight trajectory points of the sub-landing phase; wherein the first preset flight altitude difference threshold is greater than 0, and the second preset flight altitude difference threshold is less than 0.

[0065] S437, traversing all the flight trajectory points in the level flight phase except the flight trajectory points in the sub-climb phase and the flight trajectory points in the sub-landing phase, and determining the flight trajectory points whose corresponding flight altitudes are greater than a preset flight altitude threshold as the flight trajectory points in the sub-level flight phase; wherein the preset flight altitude threshold is the average flight altitude corresponding to the flight trajectory points in the sub-climb phase.

[0066] In this embodiment, when the target aircraft is flying in level flight phase, the flight altitude difference between the latter flight trajectory point and the adjacent previous flight trajectory point in the sorted flight trajectory points is close to 0; in the climbing phase, the flight altitude continues to increase, so the corresponding flight altitude difference is large; in the landing phase, the flight altitude continues to decrease, so the corresponding flight altitude difference is a negative value; the flight altitude of the trajectory point corresponding to the sub-level flight phase is large; based on the above characteristics, the trajectory points corresponding to the sub-climbing phase, sub-landing phase and sub-level flight phase corresponding to the level flight phase can be determined.

[0067] S438, obtaining the duration ZT corresponding to the sub-climbing phase 1 , the duration ZT corresponding to the level flight stage 2 and flight altitude ZH, duration ZT corresponding to the sub-landing phase 3 ; ZH is determined by the information of the flight trajectory points during the level flight phase.

[0068] In this embodiment, after the flight trajectory point corresponding to each sub-stage is determined, ZT can be determined according to the time point and flight altitude corresponding to each flight trajectory point. 1 , ZT 2 , ZH and ZT 3 ; ZH can be the average flight altitude corresponding to each flight trajectory point in the sub-level flight phase.

[0069] S439, confirm Q 2 =A 2 ×M×(V×(T 2 -ZT 1 -ZT 2 -ZT 3 ) / H) α2 +A 1 ×M×(V×ZT 1 / (ZH-H) α1 +A 2 ×M×(V×ZT 2 / ZH) α2 +A 3 ×M×(V×ZT 3 / (ZH-H 2 ) α3 .

[0070] In this embodiment, since the target aircraft has to avoid obstacles during the level flight phase, the duration of the level flight phase is T 2 -ZT 1 -ZT 2 -ZT 3 , and then the carbon emissions of the target aircraft in the level flight phase in addition to avoiding obstacles can be determined; A 1 ×M×(V×ZT 1 / (ZH-H) α1 +A 2 ×M×(V×ZT 2 / ZH) α2 +A 3 ×M×(V×ZT 3 / (ZH-H 2 ) α3 It is the carbon emissions corresponding to the target aircraft avoiding obstacles; since the carbon emissions corresponding to the process of the target aircraft avoiding obstacles are calculated separately, the determined carbon emissions are more accurate.

[0071] S500, according to Q 1 , Q 2 and Q 3 , determine the carbon emissions corresponding to the target aircraft flying on the target flight path Q = Q 1 +Q 2 +Q 3 ; Among them, Q is positively correlated with M, V and T, and negatively correlated with H.

[0072] In this embodiment, after determining the calculation weights of the carbon emissions corresponding to the climb phase, level flight phase and landing phase respectively, combined with the flight parameters of the target aircraft in each phase, the carbon emissions corresponding to the climb phase, level flight phase and landing phase can be determined respectively, and then Q is obtained; it can be understood that when the target aircraft is flying in the same phase, the engine is operating under the same working conditions, and the engine's working conditions are different in different phases; therefore, this method can improve the accuracy of determining the carbon emissions of the target aircraft.

[0073] Furthermore, before step S100, the following steps are also included:

[0074] S010, obtaining initial flight trajectory point data corresponding to the target flight path.

[0075] S020, false identification is performed on the initial flight trajectory point data to obtain target flight trajectory point data.

[0076] In this embodiment, the aircraft can be understood as a civil aircraft, and the initial flight trajectory point data corresponding to the flight path of each aircraft when flying on each route can be obtained through the ADS-B system used by civil aviation; it can be understood that there will be false flight trajectory points in the initial flight trajectory points, and the false flight trajectory points can be generated by electromagnetic interference or artificial means, and the false flight data needs to be filtered out; it should be noted that those skilled in the art can use existing false flight data filtering methods to identify and filter false initial flight trajectory points, which will not be elaborated here.

[0077] Furthermore, after step S500, the following steps are also included:

[0078] S600: predicting the carbon emissions of each target aircraft in a future time period based on the corresponding carbon emissions of each target aircraft in a preset time period.

[0079] S700, optimizing the flight of target aircraft according to the carbon emissions of each target aircraft in a future time period.

[0080] In this embodiment, after obtaining the corresponding carbon emissions of each target aircraft within a preset time period, a preset prediction model can be used to predict the carbon emissions of each target aircraft in a future time period. Based on the prediction data, the flight of the target aircraft can be optimized so that the carbon emissions of the target aircraft meet the relevant requirements.

[0081] The target aircraft carbon emissions determination system of this embodiment obtains the flight time T of the target aircraft on the target flight path, the takeoff weight of the target aircraft, the flight altitude and flight speed of the target aircraft in the level flight phase on the target flight path, and determines the carbon emissions calculation weight corresponding to the target aircraft from a preset carbon emissions calculation weight mapping table according to the model of the target aircraft, and then determines the carbon emissions corresponding to the target aircraft flying on the target flight path; in the present invention, when determining the carbon emissions corresponding to the target aircraft flying on the target flight path, the flight time of the target aircraft on the target flight path, the takeoff weight of the target aircraft, the flight altitude and flight speed of the target aircraft in the level flight phase on the target flight path are comprehensively considered; in addition, when aircraft of different models fly on the same flight path, the corresponding carbon emissions calculation weights are different, so that the determined carbon emissions corresponding to the target aircraft flying on the target flight path are more accurate.

[0082] Furthermore, the prior art calculates carbon emissions through fixed routes, but incorporates fewer factors and results of inaccurate carbon emissions calculations; while the method of calculating carbon emissions through flight trajectory points requires greater computing power; the method in the present invention divides the flight trajectory into three stages for calculation. Compared with the prior art method of calculating carbon emissions based on fixed routes, the calculation results of carbon emissions are more accurate. Compared with the method of calculating carbon emissions based on flight trajectory points, less computing power is required to calculate carbon emissions. While ensuring the accuracy of carbon emissions calculations, computing power is saved and the scope of use is wider.

[0083] In addition, the carbon emissions corresponding to the process of the target aircraft avoiding obstacles are calculated separately, so that the accuracy of determining the carbon emissions corresponding to the target aircraft flying on the target flight path is further improved.

[0084] In addition, although the steps of the method in the present disclosure are described in a specific order in the drawings, this does not require or imply that the steps must be performed in this specific order, or that all the steps shown must be performed to achieve the desired results. Additionally or alternatively, some steps may be omitted, multiple steps may be combined into one step, and / or one step may be decomposed into multiple steps, etc.

[0085] An embodiment of the present invention also provides a non-transitory computer-readable storage medium, which can be set in an electronic device to store at least one instruction or at least one program related to implementing a method in a method embodiment. The at least one instruction or the at least one program is loaded and executed by the processor to implement the method provided in the above embodiment.

[0086] The program product may adopt any combination of one or more readable media. The readable medium may be a readable signal medium or a readable storage medium. The readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination of the above. More specific examples (non-exhaustive list) of readable storage media include: an electrical connection with one or more wires, a portable disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above.

[0087] Computer readable signal media may include data signals propagated in baseband or as part of a carrier wave, in which readable program code is carried. Such propagated data signals may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. Readable signal media may also be any readable medium other than a readable storage medium, which may send, propagate, or transmit a program for use by or in conjunction with an instruction execution system, apparatus, or device.

[0088] The program code embodied on the readable medium may be transmitted using any appropriate medium, including but not limited to wireless, wired, optical cable, RF, etc., or any suitable combination of the foregoing.

[0089] Program code for performing the operations of the present application may be written in any combination of one or more programming languages, including object-oriented programming languages ​​such as Java, C++, etc., and conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user computing device, partially on the user device, as a separate software package, partially on the user computing device and partially on a remote computing device, or entirely on a remote computing device or server. In the case of a remote computing device, the remote computing device may be connected to the user computing device through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computing device (e.g., using an Internet service provider to connect through the Internet).

[0090] An embodiment of the present invention further provides an electronic device, comprising a processor and the aforementioned non-transitory computer-readable storage medium.

[0091] The electronic device is merely an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0092] The electronic device is presented in the form of a general-purpose computing device. The components of the electronic device may include, but are not limited to: the at least one processor mentioned above, the at least one memory mentioned above, and a bus connecting different system components (including the memory and the processor).

[0093] The memory stores program codes, which can be executed by the processor, so that the processor executes the steps in various embodiments described in this specification.

[0094] The memory may include readable media in the form of volatile memory, such as random access memory (RAM) and / or cache memory, and may further include read only memory (ROM).

[0095] The memory may also include a program / utility having a set (at least one) of program modules, such program modules including but not limited to: an operating system, one or more application programs, other program modules and program data, each of which or some combination may include an implementation of a network environment.

[0096] The bus may represent one or more of several types of bus structures, including a memory bus or memory controller, a peripheral bus, an accelerated graphics port, a processor, or a local bus using any of a variety of bus architectures.

[0097] The electronic device may also communicate with one or more external devices (e.g., keyboards, pointing devices, Bluetooth devices, etc.), may communicate with one or more devices that enable a user to interact with the electronic device, and / or may communicate with any device (e.g., routers, modems, etc.) that enables the electronic device to communicate with one or more other computing devices. Such communication may be performed through an input / output (I / O) interface. Furthermore, the electronic device may also communicate with one or more networks (e.g., local area networks (LANs), wide area networks (WANs), and / or public networks, such as the Internet) through a network adapter. The network adapter communicates with other modules of the electronic device through a bus. It should be understood that, although not shown in the figure, other hardware and / or software modules may be used in conjunction with the electronic device, including but not limited to: microcode, device drivers, redundant processors, external disk drive arrays, RAID systems, tape drives, and data backup storage systems, etc.

[0098] Through the description of the above implementation, it is easy for those skilled in the art to understand that the example implementation described here can be implemented by software, or by software combined with necessary hardware. Therefore, the technical solution according to the implementation of the present disclosure can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (which can be a CD-ROM, a USB flash drive, a mobile hard disk, etc.) or on a network, including several instructions to enable a computing device (which can be a personal computer, a server, a terminal device, or a network device, etc.) to execute the method according to the implementation of the present disclosure.

[0099] An embodiment of the present invention further provides a computer program product, which includes program code. When the program product is run on an electronic device, the program code is used to enable the electronic device to execute the steps of the method according to various exemplary embodiments of the present invention described above in this specification.

[0100] Although some specific embodiments of the present invention have been described in detail by way of example, it should be understood by those skilled in the art that the above examples are only for illustration, not for limiting the scope of the present invention. It should also be understood by those skilled in the art that various modifications may be made to the embodiments without departing from the scope and spirit of the present invention.

Claims

1. A target aircraft carbon emissions determination system, characterized in that: The system includes: a processor and a storage medium, wherein the storage medium stores at least one instruction or at least one program, and the at least one instruction or at least one program is loaded and executed by the processor, thereby implementing the following steps: S100, obtaining a target flight path corresponding to the target aircraft; wherein the target flight path is any historical flight path corresponding to the target aircraft; S200, obtaining the flight time T of the target aircraft on the target flight path, the take-off weight M of the target aircraft, the flight altitude H and the flight speed V of the target aircraft in the level flight phase on the target flight path; S300, according to the model of the target aircraft, determining the carbon emission calculation weight corresponding to the target aircraft from a preset carbon emission calculation weight mapping table; wherein the carbon emission calculation weight mapping table includes a number of different aircraft models and the carbon emission calculation weight corresponding to each aircraft model; S400, if the computing power of the target device is greater than the preset computing power threshold, the carbon emissions Q1 of the target aircraft in the climbing phase, the carbon emissions Q2 of the level flight phase, and the carbon emissions Q3 of the landing phase on the target flight path are determined according to T, M, H, V and the calculation weight corresponding to the target aircraft; the target device is used to calculate the carbon emissions generated by the target aircraft along the target flight path; S500, based on Q1, Q2 and Q3, determine the carbon emissions corresponding to the target aircraft flying on the target flight path Q = Q1 + Q2 + Q3; wherein Q is positively correlated with M, V and T, and negatively correlated with H; The carbon emission calculation weights corresponding to the target aircraft include a first carbon emission calculation weight B and a second carbon emission calculation weight β; after step S400 and before step S500, the following steps are also included: S401: If the computing power of the target device is less than or equal to the preset computing power threshold, determine Q=B×M×(V×T / H) based on T, M, H, V, B and β. β ;β>0; After step S200 and before step S300, the following steps are further included: S210, dividing the target flight path into a climbing phase, a level flight phase, and a landing phase according to historical flight information of the target aircraft on the target flight path; S220, obtaining the flight time T1 of the target aircraft in the climbing phase, the flight time T2 of the level flight phase, and the flight time T3 of the landing phase; wherein T1+T2+T3=T.

2. The target aircraft carbon emissions determination system according to claim 1, characterized in that: Step S300 includes the following steps: S310, according to the model of the target aircraft, determine from the preset carbon emission calculation weight mapping table the third carbon emission calculation weight A1 and the fourth carbon emission calculation weight α1 of the climbing phase, the fifth carbon emission calculation weight A2 and the sixth carbon emission calculation weight α2 of the level flight phase, and the seventh carbon emission calculation weight A3 and the eighth carbon emission calculation weight α3 of the landing phase corresponding to the target aircraft.

3. The target aircraft carbon emissions determination system according to claim 2, characterized in that: Q1, Q2 and Q3 are determined by the following steps: S410, obtaining the altitude H1 of the target aircraft when it takes off and the altitude H2 when it lands on the ground; S420, based on T1, M, H1, H, V, A1 and α1, determine the carbon emissions of the target aircraft during the climb phase of the target flight path Q1 = A1 × M × (V × T1 / (H-H1)) α1 ; A1＞0，α1＞0； S430, based on T2, M, H, V, A2 and α2, determine the carbon emissions of the target aircraft during the level flight phase of the target flight path Q2 = A2 × M × (V × T2 / H) α2 ; A2>0, α2>0; S440, based on T3, M, H, V, A1 and α3, determine the carbon emissions of the target aircraft during the landing phase of the target flight path Q3 = A3 × M × (V × T3 / (H-H2)) α3 ;A3>0,α3>0.

4. The target aircraft carbon emissions determination system according to claim 3, characterized in that: Step S430 includes the following steps: S431, obtaining the flight altitude corresponding to each flight trajectory point of the target aircraft in the level flight phase on the target flight path; S432, obtaining the standard deviation of the flight altitude corresponding to all flight trajectory points in the level flight phase; S433: If the standard deviation is less than the preset flight altitude standard deviation threshold, the carbon emissions of the target aircraft in the level flight phase of the target flight path are determined according to T2, M, H, V, A2 and α2. Q2 = A2 × M × (V × T2 / H) α2 .

5. The target aircraft carbon emissions determination system according to claim 4, characterized in that: After step S433, the following contents are also included: S434, if the standard deviation is greater than a preset flight altitude standard deviation threshold, sorting each flight trajectory point in the level flight phase according to the order of time corresponding to the flight trajectory point; S435, obtaining a flight altitude difference between a latter flight trajectory point and a former flight trajectory point of two adjacent flight trajectory points in the sorted flight trajectory points; S436, traversing all flight altitude differences, determining the flight trajectory points corresponding to the flight altitude differences greater than the first preset flight altitude difference threshold as the flight trajectory points of the sub-climbing phase, and determining the flight trajectory points corresponding to the flight altitude differences less than the second preset flight altitude difference threshold as the flight trajectory points of the sub-landing phase; wherein the first preset flight altitude difference threshold is greater than 0, and the second preset flight altitude difference threshold is less than 0; S437, traversing all the flight trajectory points in the level flight phase except the flight trajectory points in the sub-climb phase and the flight trajectory points in the sub-landing phase, and determining the flight trajectory points whose corresponding flight altitudes are greater than a preset flight altitude threshold as the flight trajectory points in the sub-level flight phase; wherein the preset flight altitude threshold is the average flight altitude corresponding to the flight trajectory points in the sub-climb phase; S438, obtaining the duration ZT1 corresponding to the sub-climbing phase, the duration ZT2 and the flight altitude ZH corresponding to the sub-level flight phase, and the duration ZT3 corresponding to the sub-landing phase; ZH is determined by the information of the flight trajectory point of the sub-level flight phase; S439, determine Q2 = A2 × M × (V × (T2 - ZT1 - ZT2 - ZT3) / H) α2 + A1 × M × (V × ZT1 / (ZH - H)) α1 + A2 × M × (V × ZT2 / ZH) α2 + A3 × M × (V × ZT3 / (ZH - H2)) α3 。 6. The target aircraft carbon emissions determination system according to claim 1, characterized in that: Before step S100, the method further includes the following steps: S010, obtaining initial flight trajectory point data corresponding to the target flight path; S020, false identification is performed on the initial flight trajectory point data to obtain target flight trajectory point data.

7. The target aircraft carbon emissions determination system according to claim 1, characterized in that: After step S500, the following steps are also included: S600, predicting the carbon emissions of each target aircraft in a future time period according to the corresponding carbon emissions of each target aircraft in a preset time period; S700, optimizing the flight of target aircraft according to the carbon emissions of each target aircraft in a future time period.

8. The target aircraft carbon emissions determination system according to claim 1, characterized in that: The flight altitude H is the altitude above sea level; H is determined by the flight altitude of the flight trajectory point corresponding to the target flight path.

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