CN115857851B

CN115857851B - Flight load center of gravity display method and device

Info

Publication number: CN115857851B
Application number: CN202211454515.XA
Authority: CN
Inventors: 李超; 陈铮; 李阳; 赵中星; 牛冰倩; 梁亚中; 李文孝; 张彧龙; 李昕冉; 韩跃
Original assignee: China Travelsky Technology Co Ltd
Current assignee: China Travelsky Technology Co Ltd
Priority date: 2022-11-21
Filing date: 2022-11-21
Publication date: 2024-05-14
Anticipated expiration: 2042-11-21
Also published as: CN115857851A

Abstract

The disclosure provides a flight stowage center of gravity display method and device, wherein the method comprises the following steps: acquiring a center of gravity envelope collection corresponding to a target machine type, wherein the center of gravity envelope collection comprises a plurality of center of gravity envelopes of the aircraft corresponding to the target machine type, and the center of gravity envelopes can represent the safe center of gravity range of the target machine type; determining a target barycenter envelope from a barycenter envelope set corresponding to the target model according to the condition parameters selected by the user; determining the loading center of gravity of an airplane corresponding to a target flight as a target center of gravity, wherein the airplane model corresponding to the target flight is a target airplane model; a flight stowage center of gravity display diagram including a target center of gravity envelope and a target center of gravity is generated and displayed so that a user knows whether the target center of gravity is within a safe center of gravity based on the stowage center of gravity display diagram. The flight stowage center of gravity display method and device provided by the invention enable staff to simply, conveniently and rapidly know whether the target center of gravity is within the safe center of gravity range.

Description

Flight load center of gravity display method and device

Technical Field

The disclosure relates to the technical field of data display, in particular to a flight stowage center of gravity display method and device.

Background

The aircraft loading is a necessary procedure before taking off the aircraft, the personnel comprehensively consider various factors influencing the balance of the aircraft, including determining the aircraft industry load distribution according to the industry load conditions of passengers, baggage, cargoes and the like, determining the actual fuel filling amount and the like according to the flight route of flights, obtaining the necessary weight, gravity center and other numerical values before taking off the aircraft, and determining whether the weight and the gravity center of the aircraft are in a specified range or not. Whether the gravity center of the aircraft is in the safety gravity center range is a key link of air transportation ground guarantee, and the flight safety of the aircraft is directly influenced.

In order to make it possible for the fitter to know whether the aircraft center of gravity is within the safety range, the current solution is to display the safety center of gravity range and the target center of gravity respectively in a digital manner, and to visually check whether the displayed target center of gravity is within the displayed safety center of gravity range. However, the above manner cannot make the fitter simply and quickly know whether the center of gravity of the target is in the safety range, and the user experience is poor.

Disclosure of Invention

In view of this, the disclosure provides a flight stowage center of gravity display method and apparatus, which are used to solve the problem that the existing display mode cannot make the stowers simply and quickly learn whether the target center of gravity is in the safety range, and the technical scheme is as follows:

a flight stowage center of gravity display method includes:

Acquiring a center of gravity envelope collection corresponding to a target machine type, wherein the center of gravity envelope collection comprises a plurality of center of gravity envelopes of airplanes of corresponding machine types, and the center of gravity envelopes can represent the safety center of gravity range of the target machine type;

determining a target gravity center envelope from a gravity center envelope set corresponding to the target model according to the condition parameters selected by the user;

Determining the loading gravity center of the aircraft corresponding to the target flight as a target gravity center, wherein the model of the aircraft corresponding to the target flight is the target model;

And generating and displaying a flight stowage center of gravity display diagram comprising the target center of gravity envelope and the target center of gravity, so that a user can know whether the target center of gravity is in a safe center of gravity range or not based on the stowage center of gravity display diagram.

A flight stowage center of gravity display device, comprising: the system comprises a center of gravity envelope collection acquisition module, a target center of gravity envelope determination module, a loading center of gravity determination module, a flight loading center of gravity display diagram generation module and a display module;

The center of gravity envelope collection acquisition module is used for acquiring a center of gravity envelope collection corresponding to a target model, wherein the center of gravity envelope collection comprises a plurality of center of gravity envelopes of airplanes of corresponding models, and the center of gravity envelopes can represent the safe center of gravity range of the target model;

The target barycenter envelope determining module is used for determining a target barycenter envelope from a barycenter envelope set corresponding to the target model according to the condition parameters selected by the user;

The loading center determining module is configured to determine a loading center of gravity of an aircraft corresponding to the target flight, as a target center of gravity, where a model of the aircraft corresponding to the target flight is the target model;

The flight load center of gravity display diagram generating module is used for generating a flight load center of gravity display diagram comprising the target center of gravity envelope and the target center of gravity;

The display module is used for displaying the flight load center of gravity display diagram so that a user can know whether the target center of gravity is in a safe center of gravity range or not based on the load center of gravity display diagram.

According to the flight load center of gravity display method and device, firstly, a center of gravity envelope set corresponding to a target machine type is obtained, then, a target center of gravity envelope is determined from the center of gravity envelope set corresponding to the target machine type according to condition parameters selected by a user, then, the load center of gravity of an aircraft corresponding to a target flight is determined as a target center of gravity, and finally, a flight load center of gravity display diagram comprising the target center of gravity envelope and the target center of gravity is generated and displayed. Because the target barycenter envelope represents the safe barycenter range, a user can intuitively know whether the target barycenter is in the safe barycenter range or not through the position relationship between the target barycenter and the target barycenter envelope in the flight barycenter display diagram, namely, the flight barycenter display method provided by the invention enables a fitter to simply, conveniently and rapidly know whether the target barycenter is in the safe barycenter range or not, and the user experience is better.

Drawings

The above and other features, advantages, and aspects of embodiments of the present disclosure will become more apparent by reference to the following detailed description when taken in conjunction with the accompanying drawings. The same or similar reference numbers will be used throughout the drawings to refer to the same or like elements. It should be understood that the figures are schematic and that elements and components are not necessarily drawn to scale.

Fig. 1 is a flow chart illustrating a flight stowage center of gravity display method according to an embodiment of the disclosure;

Fig. 2 is another flow chart of a flight stowage center of gravity display method according to an embodiment of the disclosure;

FIG. 3 is a schematic diagram of an example of a flight stowage center of gravity display provided by an embodiment of the present disclosure;

FIG. 4 is a schematic diagram of another example of a flight stowage center of gravity display provided by an embodiment of the present disclosure;

fig. 5 is a schematic structural diagram of a flight stowage center of gravity display device according to an embodiment of the disclosure;

fig. 6 is a schematic structural diagram of a flight stowage center of gravity display device according to an embodiment of the present disclosure.

Detailed Description

Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While certain embodiments of the present disclosure have been shown in the accompanying drawings, it is to be understood that the present disclosure may be embodied in various forms and should not be construed as limited to the embodiments set forth herein, but are provided to provide a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are for illustration purposes only and are not intended to limit the scope of the present disclosure.

The term "including" and variations thereof as used herein are intended to be open-ended, i.e., including, but not limited to. The term "based on" is based at least in part on. The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments. Related definitions of other terms will be given in the description below.

It should be noted that the terms "first," "second," and the like in this disclosure are merely used to distinguish between different devices, modules, or units and are not used to define an order or interdependence of functions performed by the devices, modules, or units.

It should be noted that references to "one", "a plurality" and "a plurality" in this disclosure are intended to be illustrative rather than limiting, and those of ordinary skill in the art will appreciate that "one or more" is intended to be understood as "one or more" unless the context clearly indicates otherwise.

Next, a flight stowage center of gravity display method and apparatus provided by the present disclosure will be described.

First embodiment

Referring to fig. 1, a flow chart illustrating a flight stowage center of gravity display method according to an embodiment of the disclosure is shown, where the method may include:

step S101: and acquiring a center of gravity envelope set corresponding to the target machine type.

The center of gravity envelope collection comprises a plurality of center of gravity envelopes of corresponding machine types. The center of gravity envelope represents a safe center of gravity range, i.e., a safe range of center of gravity.

It should be noted that, the barycenter envelope sets corresponding to different models may be different, so that in order to implement the present disclosure, a barycenter envelope set corresponding to each of a plurality of models may be pre-stored, and when the barycenter envelope set corresponding to the target model is obtained, the barycenter envelope set corresponding to the target model may be obtained from the pre-stored barycenter envelope sets corresponding to the plurality of models according to the target model.

Step S102: and according to the condition parameters selected by the user, determining the target barycenter envelope from the barycenter envelope set corresponding to the target model.

A plurality of condition parameters may be provided to the user so that the user selects a desired center of gravity envelope from the set of center of gravity envelopes based on the condition parameters. Different barycentric envelopes are selected by different conditional parameters.

Step S103: and determining the load center of gravity of the aircraft corresponding to the target flight as the target center of gravity.

The center of gravity of an aircraft refers to the center of gravity of the aircraft when loaded with cargo, mail, luggage, counterweights (also called ballast), passengers, and the like.

Specifically, the process of determining the load center of gravity of the aircraft corresponding to the target flight may include: and acquiring the basic gravity center corresponding to the target machine type, and determining the loading gravity center of the airplane corresponding to the targeted flight according to the basic gravity center corresponding to the target machine type and the industry load of the airplane corresponding to the targeted flight.

When the basic gravity center corresponding to the target model is obtained, the basic gravity center corresponding to the target model can be obtained from the basic gravity centers respectively corresponding to the pre-stored models according to the target model. The base gravity center is the gravity center of the corresponding aircraft under the condition of no industrial load, and optionally, the base gravity center can comprise a base take-off gravity center, a base zero oil gravity center and a base landing gravity center, wherein the base take-off gravity center is the gravity center of the aircraft of the corresponding aircraft, and the base zero oil gravity center is the gravity center of the aircraft of the corresponding aircraft under the condition of no oiling. The center of gravity of the foundation corresponding to each model is fixed.

Step S104: and generating and displaying a flight stowage center of gravity display diagram comprising the target center of gravity envelope and the target center of gravity.

The system has an objective fact in the work and life of people, namely the understanding capability of people to images is larger than the understanding capability of people to words, and the same things are more visual and easy to understand through image description, so that the efficiency can be improved. In view of this, the embodiment of the disclosure generates the flight stowage center of gravity display diagram including the target center of gravity envelope and the target center of gravity, and the flight stowage center of gravity display diagram can intuitively display the positional relationship between the target center of gravity and the target center of gravity envelope, and the user can intuitively learn whether the target center of gravity is within the safe center of gravity range through the positional relationship between the target center of gravity and the target center of gravity envelope in the flight stowage center of gravity display diagram, thereby improving the stowage efficiency and accuracy.

According to the flight stowage center of gravity display method provided by the embodiment of the disclosure, firstly, a center of gravity envelope set corresponding to a target machine type is obtained, then, a target center of gravity envelope is determined from the center of gravity envelope set corresponding to the target machine type according to condition parameters selected by a user, then, the stowage center of gravity of an aircraft corresponding to a target flight is determined and used as the target center of gravity, and finally, a flight stowage center of gravity display diagram comprising the target center of gravity envelope and the target center of gravity is generated and displayed. Because the target barycenter envelope represents the safe barycenter range, a user can intuitively know whether the target barycenter is in the safe barycenter range or not through the position relationship between the target barycenter and the target barycenter envelope in the flight stowage barycenter display diagram, namely, the flight stowage barycenter display method provided by the invention enables the user to simply, conveniently and rapidly know whether the target barycenter is in the safe barycenter range or not, and the user experience is better.

Second embodiment

Referring to fig. 2, another flow chart of a flight stowage center of gravity display method according to an embodiment of the disclosure is shown, where the method may include:

Step S201: and acquiring a center of gravity envelope set corresponding to the target machine type.

Optionally, the center of gravity envelope set corresponding to the target model may include a plurality of takeoff center of gravity envelopes, a plurality of zero oil center of gravity envelopes, and a plurality of landing center of gravity envelopes. The embodiment does not limit that the center of gravity envelope corresponding to the target model includes three center of gravity envelopes, namely, a take-off center of gravity envelope, a zero oil center of gravity envelope and a floor center of gravity envelope, and may include any one or any two of the three center of gravity envelopes, for example, may include a plurality of take-off center of gravity envelopes and a plurality of zero oil center of gravity envelopes.

Step S202: and according to the condition parameters selected by the user, determining the target barycenter envelope from the barycenter envelope set corresponding to the target model.

Specifically, according to the basic center of gravity corresponding to the target model and the condition parameters selected by the user, the process of determining the target center of gravity envelope from the center of gravity envelope set corresponding to the target model may include: according to the condition parameters selected by the user, determining a target take-off center of gravity envelope from a plurality of take-off center of gravity envelopes contained in a center of gravity envelope set corresponding to the target model; according to the condition parameters selected by the user, determining a target zero-oil gravity center envelope from a plurality of zero-oil gravity center envelopes contained in a gravity center envelope set corresponding to the target model; and determining the target floor center of gravity envelope from a plurality of floor center of gravity envelopes contained in the center of gravity envelope set corresponding to the target model according to the condition parameters selected by the user.

The following table shows an example of a plurality of barycentric envelopes included in a barycentric envelope set corresponding to a standard model and selection conditions thereof:

TABLE 1 wrap line for center of gravity of takeoff and selection conditions

TABLE 2 zero oil center of gravity envelope and selection conditions

TABLE 3 floor barycenter envelope and selection conditions

Note that not all models have a barycentric envelope as listed in the above table, and that "the barycentric envelope exists" in the selection condition in the above table means that the target model exists. The final target center of gravity envelope is determined according to the selection condition of each center of gravity envelope in the center of gravity envelope set corresponding to the target model, and the condition parameter selected by the user.

Step S203: and determining the load center of gravity of the aircraft corresponding to the target flight as the target center of gravity.

Alternatively, the target center of gravity may include a target takeoff center of gravity, a target zero oil center of gravity, and a target landing center of gravity.

Specifically, the process of determining the load center of gravity of the aircraft corresponding to the target flight as the target center of gravity may include: and acquiring the basic gravity center corresponding to the target machine type, and determining the loading gravity center of the aircraft corresponding to the target flight, namely the target gravity center, according to the basic gravity center corresponding to the target machine type and the industry load of the aircraft corresponding to the target flight.

When the basic gravity center corresponding to the target model is obtained, the basic gravity center corresponding to the target model can be obtained from the basic gravity centers respectively corresponding to a plurality of pre-stored models according to the target model. The base gravity center corresponding to the target machine type is the gravity center of the target machine type when the aircraft is not in industrial load, and the base gravity center can comprise a base take-off gravity center, a base zero-oil gravity center and a base landing gravity center, wherein the base take-off gravity center is the gravity center of the aircraft after oiling, the zero-oil gravity center is the gravity center of the target machine type when the aircraft is not in oiling, and the base landing gravity center is the gravity center of the aircraft during landing.

The process of determining the load center of gravity of the aircraft corresponding to the target flight according to the base center of gravity corresponding to the target machine type and the industry load of the aircraft corresponding to the target flight may include: according to the basic gravity center corresponding to the target machine type, determining the take-off oil quantity and the range oil consumption of the aircraft corresponding to the target flight, and determining the dry operation weight and the commercial load weight of the aircraft corresponding to the target flight; determining a zero oil weight from the dry operating weight and the payload (summing the operating weight and the payload to obtain a zero oil weight), and determining a zero oil weight index based on the zero oil weight to obtain a target zero oil center of gravity; determining a take-off weight according to the zero oil weight and the take-off oil amount (summing the zero oil weight and the take-off oil amount to obtain the take-off weight), and determining a take-off weight index based on the take-off weight to obtain a target take-off center of gravity; and determining the landing weight according to the take-off weight and the range oil consumption (subtracting the range oil consumption from the take-off weight to obtain the landing weight), and obtaining a landing weight index based on the landing weight to obtain the target landing gravity center. The dry operation weight is the sum of the basic weight of the airplane and basic operation items (the basic operation items are usually the total weight of a standard unit and a meal, wherein the standard unit comprises luggage of the unit), and the industrial load weight is the total number of industrial loads such as passengers, luggage, goods, mail and the like.

In one possible implementation, the conversion relation of the weight and the index may be preset, the zero oil weight is converted into the zero oil weight index based on the preset conversion relation when the zero oil weight index is determined based on the zero oil weight, the takeoff weight is converted into the takeoff weight index based on the preset conversion relation when the takeoff weight index is determined based on the takeoff weight, and the landing weight is converted into the landing weight index based on the preset conversion relation when the landing weight index is obtained based on the landing weight. In another possible implementation manner, a corresponding relation table of weight and index may be pre-constructed, when the zero oil weight index is determined based on the zero oil weight, the index corresponding to the zero oil weight is searched from the corresponding relation table of weight and index to be used as the zero oil weight index, when the take-off weight index is determined based on the take-off weight, the index corresponding to the take-off weight is searched from the corresponding relation table of weight and index to be used as the take-off weight index, and when the landing weight index is obtained based on the landing weight, the index corresponding to the landing weight is searched from the corresponding relation table of weight and index to be used as the landing weight index.

Through the above process, (zero oil weight index, zero oil weight), (take-off weight index, take-off weight), (floor weight index, floor weight) can be obtained, wherein, (zero oil weight index, zero oil weight) is taken as a target zero oil center of gravity, (take-off weight index, take-off weight) is taken as a target take-off center of gravity, (floor weight index, floor weight) is taken as a target floor center of gravity.

Optionally, the taxiing weight may be determined according to the takeoff weight and the taxiing oil amount, and the taxiing ability index may be determined based on the taxiing weight, and the dead weight may be determined according to the zero oil weight and the passenger weight, and the dead weight index may be determined based on the dead weight, and the obtained (taxiing weight index, taxiing weight) may be taken as the target taxiing center of gravity, and the (dead weight index, dead weight) may be taken as the target dead center of gravity.

Step S204: and determining the position of the center of gravity of the target in the center of gravity range corresponding to the target model, and predicting the center of gravity change trend based on the center of gravity of the target.

If the center of gravity range corresponding to the target model is FWDMAC (lower limit value in percentage form, such as 19.24%) to AFTMAC (upper limit value in percentage form, such as 39.13%), the process of determining the position of the center of gravity of the target within the center of gravity range corresponding to the target model includes: and converting the target gravity center into a value in a percentage form, representing the value as MAC, and calculating according to (MAC-FWDMAC)/(AFTMAC-FWDMAC) to obtain the position value of the target gravity center in the gravity center range corresponding to the target model.

For example, the center of gravity range corresponding to the target model is 19.24% -39.13%, and the position of the target center of gravity in the center of gravity range corresponding to the target model is: (27.21% -19.24%)/(39.13% -19.24%) =0.4.

When determining the position of the target gravity center within the safe gravity center range corresponding to the target model, it is necessary to determine the position of the target take-off gravity center within the safe take-off gravity center range, determine the position of the target zero oil gravity center within the safe zero oil gravity center range, and determine the position of the target landing gravity center within the safe landing gravity center range.

Step S205: and generating and displaying a flight stowage center of gravity display diagram comprising the target center of gravity envelope, the target center of gravity, the target curve and the target indication diagram.

The target curve is a curve capable of reflecting the gravity center change trend, and the target indication map is a curve capable of indicating the position of the gravity center of the target in the gravity center range corresponding to the target model.

Alternatively, the target indication map may be a bar graph, the left side of which may display the lower limit value FWDMAC in the gravity center ranges FWDMAC to AFTMAC, the right side of which may display the upper limit value AFTMAC in the gravity center ranges FWDMAC to AFTMAC, and the bar graph may display the position value of the target gravity center within the gravity center range. It should be noted that, each center of gravity corresponds to a bar graph, for example, the center of gravity of the target takeoff corresponds to a bar graph, the center of gravity of the target zero oil corresponds to a bar graph, and the center of gravity of the target landing corresponds to a bar graph. The bar graph allows the operator to more quickly see the approximate proportion of the center of gravity of the target that is within the safe center of gravity range.

Optionally, the color of the bar graphs corresponding to different barycenters is different, for example, the bar graph corresponding to the target take-off barycenter is blue, the bar graph corresponding to the target zero oil barycenter is purple, each barycenter corresponding bar graph may include a left bar graph and a right bar graph, a position value of the target barycenter in a safe barycenter range is displayed between the left bar graph and the right bar graph, if the position value of the target barycenter in the barycenter range is 0.5, the lengths of the left bar graph and the right bar graph are equal, if the position value of the target barycenter in the barycenter range is less than 0.5, the length of the left bar graph is less than the length of the right bar graph, and if the position value of the target barycenter in the barycenter range is greater than 0.5, the length of the left bar graph is greater than the length of the right bar graph. In addition, when the center of gravity of the target is not in the safe center of gravity range, the color of the bar graph can be changed to prompt the fitter, for example, when the center of gravity of the target is in the safe center of gravity range, the bar graph corresponding to the center of gravity of the target is blue, and when the center of gravity of the target is not in the center of gravity range, the bar graph corresponding to the center of gravity of the target is red.

Referring to fig. 3, an example of a flight stowage center display diagram is shown, where the flight stowage center display diagram includes a gravity center diagram and a bar diagram, the gravity center diagram uses a weight index as an abscissa, uses a weight as an ordinate, the gravity center diagram includes a target center of gravity envelope and a target center of gravity, and a curve reflecting a trend of change of the center of gravity, the target center of gravity envelope in fig. 3 includes a target take-off center of gravity envelope and a target zero oil center of gravity envelope, the target center of gravity in fig. 3 includes a target take-off center of gravity, a target zero oil center of gravity and a target landing center of gravity, the first bar diagram in fig. 3 is a bar diagram corresponding to the target zero oil center of gravity, the second bar diagram is a bar diagram corresponding to the target take-off center of gravity, and the third bar diagram is a bar diagram corresponding to the target landing center of gravity. Staff can intuitively see that the target take-off center is in the target take-off center envelope and the target zero oil center is in the target zero oil center envelope through fig. 3, which indicates that the target take-off center is in the safe take-off center range and the target zero oil center is in the safe zero oil center range, and the staff can intuitively know the position of the target zero oil center in the safe zero oil center range through the first bar chart, can intuitively know the position of the target take-off center in the safe take-off center range through the second bar chart, and can intuitively know the position of the target landing center in the safe landing center range through the third bar chart.

Referring to fig. 4, another example of a flight stowage center of gravity display is shown, and as can be seen from fig. 4, the target zero oil center of gravity is not within the target zero oil center of gravity envelope, the target take-off center of gravity is not within the target take-off center of gravity envelope, which means that the target zero oil center of gravity is not within the safe zero oil center of gravity range, and the target take-off center of gravity is not within the safe take-off center of gravity range.

According to the flight stowage center of gravity display method provided by the embodiment of the disclosure, firstly, a center of gravity envelope set corresponding to a target model is obtained, then, a target center of gravity envelope is determined from the center of gravity envelope set corresponding to the target model according to condition parameters selected by a user, then, the stowage center of gravity of an aircraft corresponding to the target flight is determined as a target center of gravity, then, the position of the target center of gravity in a center of gravity range corresponding to the target model is determined, and a center of gravity change trend is predicted based on the target center of gravity, and finally, a flight stowage center of gravity display diagram comprising the target center of gravity envelope, the target center of gravity, a target curve and a target indication diagram is generated and displayed. The flight stowage gravity center display method provided by the invention enables a user to simply, conveniently and rapidly acquire whether the target gravity center is in the safe gravity center range, the position of the target gravity center in the safe gravity center range and the gravity center change trend, and has better user experience.

The flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present disclosure. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.

Although operations are depicted in a particular order, this should not be understood as requiring that such operations be performed in the particular order shown or in sequential order. In certain circumstances, multitasking and parallel processing may be advantageous.

It should be understood that the various steps recited in the method embodiments of the present disclosure may be performed in a different order and/or performed in parallel. Furthermore, method embodiments may include additional steps and/or omit performing the illustrated steps. The scope of the present disclosure is not limited in this respect.

Computer program code for carrying out operations of the present disclosure may be written in one or more programming languages, including, but not limited to, an object oriented programming language such as Java, smalltalk, C ++ and conventional procedural programming languages, such as the "C" programming language or similar programming languages. The program code may execute entirely on the user's computer, partly on the user's computer, as a stand-alone software package, partly on the user's computer and partly on a remote computer or entirely on the remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer through any kind of network, including a Local Area Network (LAN) or a Wide Area Network (WAN), or the confirmation may be connected to an external computer (for example, through the Internet using an Internet service provider).

Third embodiment

The embodiment of the disclosure further provides a flight load center display device, and the flight load center display device and the flight load center display method described above can be referred to correspondingly.

Referring to fig. 5, a schematic structural diagram of a flight stowage center of gravity display device according to an embodiment of the disclosure may include: a barycenter envelope collection acquisition module 501, a target barycenter envelope determination module 502, a load barycenter determination module 503, a flight load barycenter display diagram generation module 504, and a display module 505.

The barycenter envelope set obtaining module 501 is configured to obtain a barycenter envelope set corresponding to a target model, where the barycenter envelope set includes a plurality of barycenter envelopes of aircraft corresponding to the target model, and the barycenter envelopes can represent a safe barycenter range of the target model.

The target barycentric envelope determining module 502 is configured to determine a target barycentric envelope from a barycentric envelope set corresponding to the target model according to a condition parameter selected by a user.

And the load center determining module 503 is configured to determine a load center of an aircraft corresponding to the target flight, as a target center of gravity, where a model of the aircraft corresponding to the target flight is the target model.

The flight deck gravity center display generating module 504 is configured to generate a flight deck gravity center display including the target gravity center envelope and the target gravity center.

The display module 505 is configured to display the flight stowage center of gravity display, so that a user can know whether the target center of gravity is within a safe center of gravity range based on the stowage center of gravity display.

Optionally, the flight stowage center of gravity display device provided in the embodiment of the present disclosure may further include: and the gravity center change trend prediction module.

And the gravity center change trend prediction module is used for predicting the gravity center change trend according to the target gravity center.

The flight load center of gravity display diagram generating module is specifically configured to, when generating a flight load center of gravity display diagram including the target center of gravity envelope and the target center of gravity:

Generating a flight stowage center of gravity display diagram comprising the target center of gravity envelope, the target center of gravity and a target curve, wherein the target curve is a curve capable of reflecting the center of gravity change trend.

Optionally, the flight stowage center of gravity display device provided in the embodiment of the present disclosure may further include: and a center of gravity position calculation module.

The gravity center position calculation module is used for calculating the position of the target gravity center in a safe gravity center range corresponding to the target machine type;

Generating a flight stowage center of gravity display diagram comprising the target center of gravity envelope, the target center of gravity and a target indication diagram, wherein the target indication diagram can indicate the position of the target center of gravity within a safe center of gravity range corresponding to the target model.

Optionally, the flight stowage center of gravity display device provided in the embodiment of the present disclosure may further include: and the center of gravity envelope storage module.

The barycenter envelope set acquisition module 501 is specifically configured to, when acquiring a barycenter envelope set corresponding to a target model:

and according to the target model, acquiring a center of gravity envelope set corresponding to the target model from center of gravity envelope sets respectively corresponding to a plurality of models prestored in a center of gravity envelope storage module.

Optionally, the load center determining module 503 is specifically configured to, when determining the load center of gravity of the aircraft corresponding to the target flight:

The method comprises the steps of obtaining a basic gravity center corresponding to a target machine type, wherein the basic gravity center is the gravity center of an aircraft of the corresponding machine type when no industry load exists, the basic gravity center comprises a basic take-off gravity center, a basic zero oil gravity center and a basic landing gravity center, the basic take-off gravity center is the gravity center of the aircraft of the corresponding machine type after refueling, and the basic zero oil gravity center is the gravity center of the aircraft of the corresponding machine type under the condition of no refueling;

and determining the loading gravity center of the aircraft corresponding to the target flight according to the basic gravity center corresponding to the target aircraft type and the industry load of the aircraft corresponding to the target flight.

Optionally, the flight stowage center of gravity display device provided in the embodiment of the present disclosure may further include: and a gravity center storage module.

The load center determining module 503 is specifically configured to, when acquiring the base center of gravity corresponding to the target model:

And according to the target model, acquiring the basic center of gravity corresponding to the target model from the basic centers respectively corresponding to a plurality of models prestored in the center of gravity storage module.

Optionally, the center of gravity envelope set comprises a plurality of take-off center of gravity envelopes, a plurality of zero oil center of gravity envelopes and a plurality of floor center of gravity envelopes;

The target barycentric envelope determining module 502 is specifically configured to, when determining a target barycentric envelope from a barycentric envelope set corresponding to the target model according to a condition parameter selected by a user:

Determining a target take-off center of gravity envelope from a plurality of take-off center of gravity envelopes contained in the center of gravity envelope set according to a condition parameter selected by a user;

According to the condition parameters selected by the user, determining a target zero-oil gravity center envelope from a plurality of zero-oil gravity center envelopes contained in the gravity center envelope set;

And determining a target ground center of gravity envelope from a plurality of ground center of gravity envelopes contained in the center of gravity envelope set according to the condition parameters selected by the user.

Optionally, the center of gravity is characterized by a weight and a weight index corresponding to the weight, the weight index being determined based on the corresponding weight;

The load center determining module 503 is specifically configured to, when determining the load center of the aircraft corresponding to the target flight according to the base center of gravity corresponding to the target model and the industry load of the aircraft corresponding to the target flight:

Determining the take-off oil quantity and the range oil consumption of the aircraft corresponding to the target flight according to the basic gravity center corresponding to the target aircraft type, and determining the dry operation weight and the commercial load weight of the aircraft corresponding to the target flight;

Determining a zero oil weight from the dry operating weight and the payload weight and a zero oil weight index based on the zero oil weight to obtain a target zero oil center of gravity;

Determining the take-off weight according to the zero oil weight and the take-off oil amount, and determining a take-off weight index based on the take-off weight to obtain a target take-off center of gravity;

And determining the landing weight according to the take-off weight and the range oil consumption, and determining a landing weight index based on the landing weight to obtain a target landing gravity center.

The flight stowage gravity center display device provided by the embodiment of the disclosure enables a user to simply, conveniently and quickly acquire whether the target gravity center is within the safe gravity center range, and in addition, the flight stowage gravity center display device provided by the embodiment of the disclosure can also be used for enabling the user to simply, conveniently and quickly acquire the position of the target gravity center within the safe gravity center range and the gravity center change trend.

The functions described above herein may be performed, at least in part, by one or more hardware logic components. For example, without limitation, exemplary types of hardware logic components that may be used include: a Field Programmable Gate Array (FPGA), an Application Specific Integrated Circuit (ASIC), an Application Specific Standard Product (ASSP), a system on a chip (SOC), a Complex Programmable Logic Device (CPLD), and the like.

Fourth embodiment

The embodiment of the invention also provides a flight load center of gravity display device, referring to fig. 6, which shows a schematic structural diagram of the flight load center of gravity display device, the flight load center of gravity display device may include: at least one processor 601, at least one communication interface 602, at least one memory 603 and at least one communication bus 604;

in the embodiment of the present invention, the number of the processor 601, the communication interface 602, the memory 603 and the communication bus 604 is at least one, and the processor 601, the communication interface 602 and the memory 603 complete communication with each other through the communication bus 604;

Processor 601 may be a central processing unit CPU, or an Application-specific integrated Circuit ASIC (Application SPECIFIC INTEGRATED Circuit), or one or more integrated circuits configured to implement embodiments of the present invention, etc.;

the memory 603 may include a high-speed RAM memory, and may further include a non-volatile memory (non-volatile memory), etc., such as at least one disk memory;

Wherein the memory stores a program, the processor is operable to invoke the program stored in the memory, the program operable to:

acquiring a center of gravity envelope collection corresponding to a target machine type, wherein the center of gravity envelope collection comprises a plurality of center of gravity envelopes of airplanes of corresponding machine types, and the center of gravity envelopes can represent the safety center of gravity range of the target machine type; determining a target gravity center envelope from a gravity center envelope set corresponding to the target model according to the condition parameters selected by the user; determining the loading gravity center of the aircraft corresponding to the target flight as a target gravity center, wherein the model of the aircraft corresponding to the target flight is the target model; and generating and displaying a flight stowage center of gravity display diagram comprising the target center of gravity envelope and the target center of gravity, so that a user can know whether the target center of gravity is in a safe center of gravity range or not based on the stowage center of gravity display diagram.

Alternatively, the refinement function and the extension function of the program may be described with reference to the above.

Fifth embodiment

The embodiment of the present disclosure also provides a readable storage medium storing a program adapted to be executed by a processor, the program being configured to:

It should be noted that the computer readable medium described in the present disclosure may be a computer readable signal medium or a computer readable storage medium, or any combination of the two. The computer readable storage medium can be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or a combination of any of the foregoing. More specific examples of the computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer diskette, 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 disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing. In the context of this disclosure, a computer-readable storage medium may be any tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device. In the present disclosure, however, the computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, with the computer-readable program code embodied therein. Such a propagated data signal may take any of a variety of forms, including, but not limited to, electro-magnetic, optical, or any suitable combination of the foregoing. A computer readable signal medium may also be any computer readable medium that is not a computer readable storage medium and that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code embodied on a computer readable medium may be transmitted using any appropriate medium, including but not limited to: electrical wires, fiber optic cables, RF (radio frequency), and the like, or any suitable combination of the foregoing.

The computer-readable storage medium may be contained in the electronic device; or may exist alone without being incorporated into the electronic device.

Sixth embodiment

The processes described above with reference to flowcharts may be implemented as computer software programs according to embodiments of the present disclosure. For example, embodiments of the present disclosure include a computer program product comprising a computer program embodied on a non-transitory computer readable medium, the computer program comprising program code for performing the method shown in the flow chart. In such an embodiment, the computer program may be downloaded and installed from a network via a communication device, or installed from a storage device, or installed from ROM. The above-described functions defined in the methods of the embodiments of the present disclosure are performed when the computer program is executed by a processing device.

According to one or more embodiments of the present disclosure, there is provided a flight stowage center of gravity display method including:

According to one or more embodiments of the present disclosure, the flight stowage center of gravity display method provided by the present disclosure further includes:

Predicting a gravity center change trend according to the target gravity center;

The generating a flight stowage center of gravity display diagram including the target center of gravity envelope and the target center of gravity includes:

calculating the position of the target gravity center in the safety gravity center range corresponding to the target model;

According to one or more embodiments of the present disclosure, in the flight stowage center of gravity display method provided by the present disclosure, the acquiring the center of gravity envelope set corresponding to the target model includes:

and acquiring a center of gravity envelope set corresponding to the target model from the center of gravity envelope sets respectively corresponding to a plurality of pre-stored models according to the target model.

According to one or more embodiments of the present disclosure, in the flight stowage center of gravity display method provided by the present disclosure, the determining the stowage center of gravity of the aircraft corresponding to the target flight includes:

According to one or more embodiments of the present disclosure, in the flight stowage center of gravity display method provided by the present disclosure, the center of gravity envelope set includes a plurality of takeoff center of gravity envelopes, a plurality of zero oil center of gravity envelopes, and a plurality of landing center of gravity envelopes;

the determining the target barycenter envelope from the barycenter envelope set corresponding to the target model according to the condition parameters selected by the user comprises the following steps:

According to one or more embodiments of the present disclosure, in the flight stowage center of gravity display method provided by the present disclosure, the center of gravity is characterized by a weight and a weight index corresponding to the weight, the weight index being determined based on the corresponding weight;

The determining the load center of gravity of the aircraft corresponding to the target flight according to the base center of gravity corresponding to the target aircraft and the industry load of the aircraft corresponding to the target flight comprises the following steps:

According to one or more embodiments of the present disclosure, there is provided a flight stowage center of gravity display device including: the system comprises a center of gravity envelope collection acquisition module, a target center of gravity envelope determination module, a loading center of gravity determination module, a flight loading center of gravity display diagram generation module and a display module;

According to one or more embodiments of the present disclosure, the flight stowage center of gravity display device provided by the present disclosure further includes: the gravity center change trend prediction module;

the gravity center change trend prediction module is used for predicting the gravity center change trend according to the target gravity center;

According to one or more embodiments of the present disclosure, the flight stowage center of gravity display device provided by the present disclosure further includes: a center of gravity position calculation module;

Although the subject matter has been described in language specific to structural features and/or methodological acts, it is to be understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or acts described above. Rather, the specific features and acts described above are example forms of implementing the claims.

While several specific implementation details are included in the above discussion, these should not be construed as limiting the scope of the disclosure. Certain features that are described in the context of separate embodiments can also be implemented in combination in a single embodiment. Conversely, various features that are described in the context of a single embodiment can also be implemented in multiple embodiments separately or in any suitable subcombination.

The foregoing description is only of the preferred embodiments of the present disclosure and description of the principles of the technology being employed. It will be appreciated by persons skilled in the art that the scope of the disclosure referred to in this disclosure is not limited to the specific combinations of features described above, but also covers other embodiments which may be formed by any combination of features described above or equivalents thereof without departing from the spirit of the disclosure. Such as those described above, are mutually substituted with the technical features having similar functions disclosed in the present disclosure (but not limited thereto).

Claims

1. A flight stowage center of gravity display method, comprising:

determining a target gravity center envelope from a gravity center envelope set corresponding to the target model according to the condition parameters selected by the user; wherein, different condition parameters correspond to different barycentric envelopes;

Determining the loading center of gravity of an airplane corresponding to a target flight as a target center of gravity, wherein the airplane model corresponding to the target flight is the target model;

Generating a flight stowage center of gravity display diagram comprising the target center of gravity envelope, the target center of gravity and a target indication diagram, wherein the target indication diagram can indicate the position of the target center of gravity in a safety center of gravity range corresponding to the target model, so that a user can know whether the target center of gravity is in the safety center of gravity range or not based on the stowage center of gravity display diagram;

The determining the target barycenter envelope from the barycenter envelope set corresponding to the target model according to the condition parameters selected by the user comprises:

According to the condition parameters selected by the user, determining a target take-off center of gravity envelope from a plurality of take-off center of gravity envelopes contained in a center of gravity envelope set corresponding to the target model; according to the condition parameters selected by the user, determining a target zero-oil gravity center envelope from a plurality of zero-oil gravity center envelopes contained in a gravity center envelope set corresponding to the target model; determining a target ground center of gravity envelope from a plurality of ground center of gravity envelopes contained in a center of gravity envelope set corresponding to the target model according to the condition parameters selected by the user; wherein, the center of gravity envelope of taking off of a plurality of pieces includes: the corresponding selection condition is that the takeoff oil mass limit takeoff center of gravity envelope exists, when the takeoff oil mass exceeds the weight defined by the takeoff oil mass limit takeoff center of gravity envelope, or the Tail oil tank oil mass is input and CG CHG in Tail oil tank Fuel gauge Aircraft Information-Tail Fuel data is set as Y; the cumulative Load limiting TAKE-OFF center of gravity envelope exists under the corresponding selection Condition that when Combined Load Limits, condition is TAKE OFF CG, type is TO% MAC data exists, and the actual combinedLoad exceeds the normal_CG value corresponding TO a certain rule; an extreme climate limiting barycenter envelope, the corresponding selection condition being that the extreme climate limiting barycenter envelope exists; the lowest zero oil takeoff center of gravity envelope corresponds to the selection condition that the lowest zero oil takeoff center of gravity envelope exists, and when the actual zero oil weight of the flight is greater than an input value; the standard take-off center of gravity envelope corresponds to the selection condition that the standard take-off center of gravity envelope is adopted when the take-off oil mass limit take-off center of gravity envelope, the accumulated load limit take-off center of gravity, the extreme climate limit center of gravity envelope and the lowest zero oil take-off center of gravity envelope do not determine the center of gravity envelope;

The target indication diagrams are bar diagrams, the colors of the bar diagrams corresponding to different barycenters are different, each bar diagram corresponding to each barycenter comprises a left bar diagram and a right bar diagram, a position value of the target barycenter in a safe barycenter range is displayed between the left bar diagram and the right bar diagram, and when the target barycenter is not in the safe barycenter range, the color of the bar diagram is changed to prompt a load carrier.

2. The flight stowage center of gravity display method of claim 1, further comprising:

3. The flight stowage center of gravity displaying method according to any one of claims 1 to 2, wherein the acquiring the center of gravity envelope set corresponding to the target model includes:

4. The flight stowage center of gravity display method according to any one of claims 1-2, wherein the determining the stowage center of gravity of the aircraft corresponding to the target flight includes:

5. The flight stowage center of gravity display method according to any one of claims 1 to 2, wherein the center of gravity envelope set includes a plurality of takeoff center of gravity envelopes, a plurality of zero oil center of gravity envelopes, and a plurality of floor center of gravity envelopes;

6. The method of claim 4, wherein the center of gravity is characterized by a weight and a weight index corresponding to the weight, the weight index being determined based on the corresponding weight;

7. A flight stowage center of gravity display device, comprising: the system comprises a center of gravity envelope collection acquisition module, a target center of gravity envelope determination module, a loading center of gravity determination module, a flight loading center of gravity display diagram generation module and a display module;

The loading center determining module is used for determining the loading center of gravity of the aircraft corresponding to the target flight as a target center of gravity, wherein the model of the aircraft corresponding to the target flight is the target model;

the flight stowage center of gravity display diagram generation module is used for generating a flight stowage center of gravity display diagram comprising the target center of gravity envelope, the target center of gravity and a target indication diagram, wherein the target indication diagram can indicate the position of the target center of gravity in a safe center of gravity range corresponding to the target model;

The display module is used for displaying the flight load center of gravity display diagram so that a user can know whether the target center of gravity is in a safe center of gravity range or not based on the load center of gravity display diagram;

The target barycenter envelope determining module determines a target barycenter envelope from a barycenter envelope set corresponding to the target model according to a condition parameter selected by a user, and the determining comprises:

according to the condition parameters selected by the user, determining a target take-off center of gravity envelope from a plurality of take-off center of gravity envelopes contained in a center of gravity envelope set corresponding to the target model; according to the condition parameters selected by the user, determining a target zero-oil gravity center envelope from a plurality of zero-oil gravity center envelopes contained in a gravity center envelope set corresponding to the target model; determining a target ground center of gravity envelope from a plurality of ground center of gravity envelopes contained in a center of gravity envelope set corresponding to the target model according to the condition parameters selected by the user; wherein, the center of gravity envelope of taking off of a plurality of pieces includes: the corresponding selection condition is that the takeoff oil mass limit takeoff center of gravity envelope exists, when the takeoff oil mass exceeds the weight defined by the takeoff oil mass limit takeoff center of gravity envelope, or the Tail oil tank oil mass is input and CG CHG in Tail oil tank Fuel gauge Aircraft Information-Tail Fuel data is set as Y; the cumulative Load limiting TAKE-OFF center of gravity corresponds TO the selection Condition that the cumulative Load limiting TAKE-OFF center of gravity envelope exists, when Combined Load Limits, condition is TAKE OFF CG, type is TO% MAC data exist, and the actual coded Load exceeds the normal_CG value corresponding TO a certain rule; an extreme climate limiting barycenter envelope, the corresponding selection condition being that the extreme climate limiting barycenter envelope exists; the lowest zero oil takeoff center of gravity envelope corresponds to the selection condition that the lowest zero oil takeoff center of gravity envelope exists, and when the actual zero oil weight of the flight is greater than an input value; the standard take-off center of gravity envelope corresponds to the selection condition that the standard take-off center of gravity envelope is adopted when the take-off oil mass limit take-off center of gravity envelope, the accumulated load limit take-off center of gravity, the extreme climate limit center of gravity envelope and the lowest zero oil take-off center of gravity envelope do not determine the center of gravity envelope;

The target indication diagrams are bar charts, the colors of the bar charts corresponding to different barycenters are different, each bar chart corresponding to the barycenters can comprise a left bar chart and a right bar chart, the position value of the target barycenter in the safety barycenter range is displayed between the left bar chart and the right bar chart, and when the target barycenter is not in the safety barycenter range, the color of the bar charts is changed to prompt a load carrier.

8. The flight stowage center of gravity display device of claim 7, further comprising: the gravity center change trend prediction module;