Emergency processing method and system under power failure of aircraft and medium

Abstract

The embodiment of the invention provides an emergency processing method and system under the power failure of an aircraft and a medium, and the method comprises the steps: obtaining the operation state data of the aircraft, inputting a preset model, and obtaining an operation state feature value; comparing the running state characteristic value with a preset running state characteristic value to obtain a state deviation rate; judging whether the state deviation rate is greater than or equal to a preset state deviation rate threshold value or not; if yes, aircraft fault information is output; carrying out difference value calculation on the aircraft fault information and preset fault information to obtain a fault difference value; if the fault difference value is larger than or equal to a set fault difference threshold value, it is judged that the aircraft is in power failure, and an emergency strategy is generated; aircraft control information is generated according to the emergency strategy; controlling the aircraft to carry out emergency landing according to the aircraft control information; the power failure state is judged according to the aircraft fault information, the maximum flight area of the aircraft is judged according to the energy information, emergency landing points are flexibly selected for emergency landing, and the safety of the aircraft is improved.

Description

Technical Field

[0001] The present application relates to the field of aircraft emergency handling, and more specifically, to an emergency handling method, system and medium for aircraft power failure. Background Art

[0002] With the continuous development of science and technology, the application of unmanned aerial vehicles has achieved unprecedented development. Aircraft are often more suitable for some repetitive mechanical tasks or highly dangerous tasks. In the civil field, the application of unmanned aerial vehicles in the industry is the real rigid demand for unmanned aerial vehicles; their applications in aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, creating romance and other fields have greatly expanded the use of unmanned aerial vehicles themselves.

[0003] Existing emergency handling methods cannot determine the maximum flight area of ​​an aircraft based on the aircraft's power failure and energy information, making it difficult to dynamically select the aircraft's emergency landing location. The safety of the aircraft during flight is poor.

[0004] In view of the above problems, effective technical solutions are urgently needed. Summary of the invention

[0005] The purpose of the embodiments of the present application is to provide an emergency handling method, system and medium for aircraft power failure, which can determine the power failure state through aircraft fault information and the maximum flight area of ​​the aircraft based on energy information, and flexibly select an emergency landing point for emergency landing, thereby improving the safety of the aircraft.

[0006] The embodiment of the present application also provides an emergency handling method for aircraft power failure, including:

[0007] Obtain aircraft operation status data and input it into a preset model to obtain operation status characteristic values;

[0008] Compare the running state characteristic value with the preset running state characteristic value to obtain the state deviation rate;

[0009] Determining whether the state deviation rate is greater than or equal to a preset state deviation rate threshold;

[0010] If it is greater than or equal to, then output aircraft fault information;

[0011] Performing a difference calculation between the aircraft fault information and the preset fault information to obtain a fault difference;

[0012] If the fault difference is greater than or equal to the set fault difference threshold, the aircraft power failure is determined and an emergency strategy is generated;

[0013] Generate aircraft control information according to the emergency strategy; control the aircraft for emergency landing according to the aircraft control information.

[0014] Optionally, in the emergency handling method for aircraft power failure described in the embodiment of the present application, the acquiring of aircraft operation status data and inputting a preset model to obtain an operation status characteristic value includes:

[0015] Obtain the aircraft's navigation speed, navigation direction, and yaw angle data, and generate a data set;

[0016] Input the data set into the preset neural network model for training to obtain training result data;

[0017] Determining whether the training result data converges;

[0018] If convergence occurs, obtain the validation set data, verify the training result data based on the validation set data, and obtain the accuracy;

[0019] Determining whether the accuracy meets a preset condition;

[0020] If satisfied, the operating status characteristic value is output through the neural network model;

[0021] If it is not satisfied, correction information is generated and the neural network model parameters are corrected through the correction information.

[0022] Optionally, in the emergency handling method for aircraft power failure described in the embodiment of the present application, generating aircraft control information according to the emergency strategy; and controlling the aircraft for emergency landing according to the aircraft control information include:

[0023] When the aircraft power fails, obtain the aircraft operation status information and the nearest landing point location information;

[0024] Determine whether the aircraft can reach the landing point based on the nearest landing point location information;

[0025] If yes, the aircraft returns the nearest landing point location information;

[0026] If not, obtain the image information around the current position of the aircraft;

[0027] Extracting image feature values ​​based on the current surrounding image information of the aircraft;

[0028] Determine whether the flatness of the surrounding area is greater than a preset flatness threshold;

[0029] If it is greater, temporary landing point information is generated, and the aircraft is driven to make an emergency landing according to the temporary landing point information.

[0030] Optionally, in the emergency handling method for aircraft power failure described in the embodiment of the present application, generating aircraft control information according to the emergency strategy; and controlling the aircraft for emergency landing according to the aircraft control information include:

[0031] When the aircraft power fails, obtain the aircraft operation status information and energy information;

[0032] Determine whether the aircraft can reach the take-off position based on the aircraft's energy information;

[0033] If yes, the aircraft is controlled to return to the aircraft take-off position;

[0034] If not, the energy information of the aircraft is input into the flight model to obtain the maximum flight distance of the aircraft;

[0035] Establish landing area information based on the aircraft's maximum flight distance;

[0036] Search for the best landing point based on the landing area information and collect the best landing point parameter information;

[0037] Generate aircraft landing parameters based on the optimal landing point parameter information to control the aircraft to fly and land.

[0038] Optionally, in the emergency handling method for aircraft power failure described in the embodiment of the present application, searching for the best landing point according to the landing area information and collecting the best landing point parameter information includes:

[0039] Calculate the glide distance based on the optimal landing point parameter information;

[0040] determining whether the glide distance satisfies a preset glide distance, and if so, generating a first landing parameter, and causing the aircraft to glide and land according to the first landing parameter;

[0041] If it is less than, a second landing parameter is generated, and the aircraft is controlled to make a vertical landing according to the second landing parameter;

[0042] During the vertical landing of the aircraft, the aircraft descent speed is collected;

[0043] Compare the aircraft's descent speed with the preset speed to obtain a speed deviation rate;

[0044] Determining whether the speed deviation rate is greater than a preset speed deviation rate threshold;

[0045] If it is greater, the second landing parameter is adjusted and updated.

[0046] Optionally, in the emergency handling method for aircraft power failure described in the embodiment of the present application, if is greater than , generating a first landing parameter, and making the aircraft glide and land according to the first landing parameter; comprising:

[0047] Obtain aircraft attitude information;

[0048] Comparing the aircraft attitude information with preset attitude information to obtain an attitude deviation rate;

[0049] Determining whether the posture deviation rate is greater than a preset deviation rate threshold;

[0050] If it is greater, adjustment information is generated and the first landing parameter is adjusted according to the adjustment information.

[0051] In a second aspect, an embodiment of the present application provides an emergency handling system for aircraft power failure, the system comprising: a memory and a processor, the memory comprising a program of an emergency handling method for aircraft power failure, and the program of the emergency handling method for aircraft power failure, when executed by the processor, implements the following steps:

[0052] Obtain aircraft operation status data and input it into a preset model to obtain operation status characteristic values;

[0053] Compare the running state characteristic value with the preset running state characteristic value to obtain the state deviation rate;

[0054] Determining whether the state deviation rate is greater than or equal to a preset state deviation rate threshold;

[0055] If it is greater than or equal to, then output aircraft fault information;

[0056] Performing a difference calculation between the aircraft fault information and the preset fault information to obtain a fault difference;

[0057] If the fault difference is greater than or equal to the set fault difference threshold, the aircraft power failure is determined and an emergency strategy is generated;

[0058] Generate aircraft control information according to the emergency strategy; control the aircraft for emergency landing according to the aircraft control information.

[0059] Optionally, in the emergency handling system for aircraft power failure described in the embodiment of the present application, the acquiring of aircraft operation status data and inputting a preset model to obtain an operation status characteristic value includes:

[0060] Obtain the aircraft's navigation speed, navigation direction, and yaw angle data, and generate a data set;

[0061] Input the data set into the preset neural network model for training to obtain training result data;

[0062] Determining whether the training result data converges;

[0063] If convergence occurs, obtain the validation set data, verify the training result data based on the validation set data, and obtain the accuracy;

[0064] Determining whether the accuracy meets a preset condition;

[0065] If satisfied, the operating status characteristic value is output through the neural network model;

[0066] If it is not satisfied, correction information is generated and the neural network model parameters are corrected through the correction information.

[0067] Optionally, in the emergency handling system for aircraft power failure described in the embodiment of the present application, generating aircraft control information according to the emergency strategy; and controlling the aircraft for emergency landing according to the aircraft control information include:

[0068] When the aircraft power fails, obtain the aircraft operation status information and the nearest landing point location information;

[0069] Determine whether the aircraft can reach the landing point based on the nearest landing point location information;

[0070] If yes, the aircraft returns the nearest landing point location information;

[0071] If not, obtain the image information around the current position of the aircraft;

[0072] Extracting image feature values ​​based on the current surrounding image information of the aircraft;

[0073] Determine whether the flatness of the surrounding area is greater than a preset flatness threshold;

[0074] If it is greater, temporary landing point information is generated, and the aircraft is driven to make an emergency landing according to the temporary landing point information.

[0075] In a third aspect, an embodiment of the present application further provides a computer-readable storage medium, wherein the computer-readable storage medium includes an emergency handling method program for aircraft power failure. When the emergency handling method program for aircraft power failure is executed by a processor, the steps of the emergency handling method for aircraft power failure as described in any one of the above items are implemented.

[0076] As can be seen from the above, an emergency handling method, system and medium for aircraft power failure provided in an embodiment of the present application obtains aircraft operating status data and inputs a preset model to obtain an operating status characteristic value; compares the operating status characteristic value with a preset operating status characteristic value to obtain a state deviation rate; determines whether the state deviation rate is greater than or equal to a preset state deviation rate threshold; if greater than or equal to, outputs aircraft fault information; performs a difference calculation between the aircraft fault information and the preset fault information to obtain a fault difference; if the fault difference is greater than or equal to the set fault difference threshold, determines that the aircraft power has failed, and generates an emergency strategy; generates aircraft control information according to the emergency strategy; controls the aircraft for emergency landing according to the aircraft control information; determines the power failure state through the aircraft fault information and determines the maximum flight area of ​​the aircraft according to the energy information, and flexibly selects the emergency landing point for emergency landing, thereby improving the safety of the aircraft.

[0077] Other features and advantages of the present application will be described in the subsequent description, and the advantages of the present application will become apparent from the description or understood by practicing the embodiments of the present application. The purpose and other advantages of the present application can be realized and obtained by the structures specifically pointed out in the written description, claims, and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0078] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments of the present application will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0079] Figure 1 A flow chart of an emergency handling method for aircraft power failure provided in an embodiment of the present application;

[0080] Figure 2 A neural network model training flow chart of an emergency treatment method for aircraft power failure provided in an embodiment of the present application;

[0081] Figure 3 A flow chart of obtaining a temporary landing point for an emergency treatment method for aircraft power failure provided in an embodiment of the present application;

[0082] Figure 4 An aircraft emergency landing flow chart of an emergency handling method for aircraft power failure provided in an embodiment of the present application;

[0083] Figure 5A second landing parameter update flow chart of the emergency handling method under aircraft power failure provided in an embodiment of the present application;

[0084] Figure 6 A schematic diagram of the structure of an emergency response system for aircraft power failure provided in an embodiment of the present application. DETAILED DESCRIPTION

[0085] The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the application claimed for protection, but merely represents the selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without making creative work belong to the scope of protection of the present application.

[0086] It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings. At the same time, in the description of this application, the terms "first", "second", etc. are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0087] Please refer to Figure 1 , Figure 1 This is a flow chart of an emergency processing method for aircraft power failure in some embodiments of the present application. The emergency processing method for aircraft power failure is used in a terminal device, and the emergency processing method for aircraft power failure includes the following steps:

[0088] S101, obtaining aircraft operation status data and inputting a preset model to obtain an operation status characteristic value;

[0089] S102, comparing the running state characteristic value with a preset running state characteristic value to obtain a state deviation rate;

[0090] S103, determining whether the state deviation rate is greater than or equal to a preset state deviation rate threshold; if greater than or equal to, outputting aircraft fault information;

[0091] S104, performing a difference calculation between the aircraft fault information and the preset fault information to obtain a fault difference; if the fault difference is greater than or equal to a preset fault difference threshold, it is determined that the aircraft power fails, and an emergency strategy is generated;

[0092] S105, generating aircraft control information according to the emergency strategy; and controlling the aircraft to perform emergency landing according to the aircraft control information.

[0093] It should be noted that the operating status characteristic values ​​are classified to obtain multiple sub-state characteristic values ​​of different categories, and the difference between the sub-state characteristic values ​​belonging to the same category and the preset operating status characteristic values ​​is calculated, and the difference deviation is compared. The deviation rate of the same category is calculated based on the difference deviation. Sub-state characteristic values ​​of different categories are not comparable.

[0094] Please refer to Figure 2 , Figure 2 This is a neural network model training flow chart of an emergency handling method for aircraft power failure in some embodiments of the present application. According to an embodiment of the present invention, aircraft operation status data is obtained and input into a preset model to obtain operation status characteristic values, including:

[0095] S201, obtaining the aircraft's navigation speed, navigation direction, and yaw angle data, and generating a data set;

[0096] S202, inputting the data set into a preset neural network model for training to obtain training result data;

[0097] S203, determining whether the training result data has converged; if converged, obtaining validation set data, and validating the training result data according to the validation set data to obtain accuracy;

[0098] S204, determining whether the accuracy meets a preset condition;

[0099] If satisfied, the operating status characteristic value is output through the neural network model;

[0100] If it is not satisfied, correction information is generated and the neural network model parameters are corrected through the correction information.

[0101] Please refer to Figure 3 , Figure 3 The present invention is a flowchart of a temporary landing point acquisition method for emergency handling of aircraft power failure in some embodiments of the present invention. According to an embodiment of the present invention, aircraft control information is generated according to an emergency strategy; and an aircraft is controlled to perform emergency landing according to the aircraft control information, including:

[0102] S301, when the aircraft power fails, obtain the aircraft operation status information and the nearest landing point location information;

[0103] S302, judging whether the aircraft can reach the nearest landing point according to the nearest landing point location information; if so, the aircraft returns the nearest landing point location information; if not, obtaining the image information around the current position of the aircraft;

[0104] S303, extracting image feature values ​​according to the current surrounding image information of the aircraft;

[0105] S304, determining whether the flatness of the surrounding area is greater than a preset flatness threshold; if so, generating temporary landing point information, and driving the aircraft to perform an emergency landing according to the temporary landing point information.

[0106] It should be noted that the temporary landing point information includes the location coordinates of the temporary landing point, topographic information, slope information and geological information.

[0107] Please refer to Figure 4 , Figure 4 The present invention is a flowchart of an emergency landing of an aircraft of an emergency handling method under aircraft power failure in some embodiments of the present invention. According to an embodiment of the present invention, aircraft control information is generated according to an emergency strategy; and an aircraft is controlled to perform emergency landing according to the aircraft control information, including:

[0108] S401, when the aircraft power fails, obtaining aircraft operation status information and energy information;

[0109] S402, judging whether the aircraft can reach the take-off position according to the energy information of the aircraft;

[0110] S403, if yes, control the aircraft to return to the take-off position; if no, input the energy information of the aircraft into the flight model to obtain the maximum flight distance of the aircraft;

[0111] S404, establishing landing area information according to the maximum flight distance of the aircraft;

[0112] S405, searching for the best landing point according to the landing area information, and collecting parameter information of the best landing point;

[0113] S406, generating aircraft landing parameters according to the optimal landing point parameter information to control the aircraft to perform flight landing.

[0114] Please refer to Figure 5 , Figure 5 The second landing parameter update flow chart of an emergency handling method for aircraft power failure in some embodiments of the present application. According to an embodiment of the present invention, searching for the best landing point according to the landing area information and collecting the best landing point parameter information includes:

[0115] S501, calculating the glide distance according to the optimal landing point parameter information;

[0116] S502, determining whether the glide distance meets a preset glide distance, if it does, generating a first landing parameter, and making the aircraft glide and land according to the first landing parameter; if it does, generating a second landing parameter, and controlling the aircraft to make a vertical forced landing according to the second landing parameter;

[0117] S503, during the vertical forced landing of the aircraft, collecting the aircraft descent speed;

[0118] S504, comparing the aircraft descent speed with a preset speed to obtain a speed deviation rate;

[0119] S505, determining whether the speed deviation rate is greater than a preset speed deviation rate threshold; if greater, adjusting the second landing parameter and updating the second landing parameter.

[0120] According to an embodiment of the present invention, if is greater than , a first landing parameter is generated, and the aircraft is caused to glide and land according to the first landing parameter; comprising:

[0121] Obtain aircraft attitude information;

[0122] Compare the aircraft attitude information with the preset attitude information to obtain the attitude deviation rate;

[0123] Determine whether the posture deviation rate is greater than a preset deviation rate threshold;

[0124] If it is greater, adjustment information is generated and the first landing parameter is adjusted according to the adjustment information.

[0125] According to an embodiment of the present invention, it also includes:

[0126] Obtain aircraft landing parameters, and generate landing time according to the aircraft landing parameters;

[0127] Compare the landing time with the preset landing time to obtain the time deviation rate;

[0128] Determine whether the time deviation rate is greater than a preset time deviation rate threshold;

[0129] If it is greater, the remaining capacity information is generated; the aircraft attitude adjustment information is generated according to the remaining capacity information; the aircraft landing parameters are urgently adjusted according to the attitude adjustment information, so that the aircraft landing attitude reaches the predetermined attitude, ensuring a smooth landing of the aircraft.

[0130] Please refer to Figure 6 , Figure 6It is a structural diagram of an emergency processing system for aircraft power failure in some embodiments of the present application. In a second aspect, the embodiment of the present application provides an emergency processing system 6 for aircraft power failure, the system comprising: a memory 61 and a processor 62, the memory comprising a program of an emergency processing method for aircraft power failure, and when the program of the emergency processing method for aircraft power failure is executed by the processor, the following steps are implemented:

[0131] Obtain aircraft operation status data and input it into a preset model to obtain operation status characteristic values;

[0132] Compare the running state characteristic value with the preset running state characteristic value to obtain the state deviation rate;

[0133] Determine whether the state deviation rate is greater than or equal to a preset state deviation rate threshold;

[0134] If it is greater than or equal to, then output aircraft fault information;

[0135] Performing a difference calculation between the aircraft fault information and the preset fault information to obtain a fault difference;

[0136] If the fault difference is greater than or equal to the set fault difference threshold, the aircraft power failure is determined and an emergency strategy is generated;

[0137] Generate aircraft control information according to the emergency strategy; control the aircraft for emergency landing according to the aircraft control information.

[0138] It should be noted that the operating status characteristic values ​​are classified to obtain multiple sub-state characteristic values ​​of different categories, and the difference between the sub-state characteristic values ​​belonging to the same category and the preset operating status characteristic values ​​is calculated, and the difference deviation is compared. The deviation rate of the same category is calculated based on the difference deviation. Sub-state characteristic values ​​of different categories are not comparable.

[0139] According to an embodiment of the present invention, aircraft operation status data is obtained and input into a preset model to obtain an operation status characteristic value, including:

[0140] Obtain the aircraft's navigation speed, navigation direction, and yaw angle data, and generate a data set;

[0141] Input the data set into the preset neural network model for training to obtain training result data;

[0142] Determine whether the training result data converges;

[0143] If convergence occurs, obtain the validation set data, verify the training result data based on the validation set data, and obtain the accuracy;

[0144] Determine whether the accuracy meets the preset conditions;

[0145] If satisfied, the operating status characteristic value is output through the neural network model;

[0146] If it is not satisfied, correction information is generated and the neural network model parameters are corrected through the correction information.

[0147] According to an embodiment of the present invention, generating aircraft control information according to an emergency strategy; and controlling an aircraft for emergency landing according to the aircraft control information include:

[0148] When the aircraft power fails, obtain the aircraft operation status information and the nearest landing point location information;

[0149] Determine whether the aircraft can reach the landing point based on the nearest landing point location information;

[0150] If yes, the aircraft returns the nearest landing point location information;

[0151] If not, obtain the image information around the current position of the aircraft;

[0152] Extracting image feature values ​​based on the current surrounding image information of the aircraft;

[0153] Determine whether the flatness of the surrounding area is greater than a preset flatness threshold;

[0154] If it is greater, temporary landing point information is generated, and the aircraft is driven to make an emergency landing according to the temporary landing point information.

[0155] It should be noted that the temporary landing point information includes the location coordinates of the temporary landing point, topographic information, slope information and geological information.

[0156] According to an embodiment of the present invention, generating aircraft control information according to an emergency strategy; and controlling an aircraft for emergency landing according to the aircraft control information include:

[0157] When the aircraft power fails, obtain the aircraft operation status information and energy information;

[0158] Determine whether the aircraft can reach the take-off position based on the aircraft's energy information;

[0159] If yes, the aircraft is controlled to return to the aircraft take-off position;

[0160] If not, the energy information of the aircraft is input into the flight model to obtain the maximum flight distance of the aircraft;

[0161] Establish landing area information based on the aircraft's maximum flight distance;

[0162] Search for the best landing point based on the landing area information and collect the best landing point parameter information;

[0163] Generate aircraft landing parameters based on the optimal landing point parameter information to control the aircraft to fly and land.

[0164] According to an embodiment of the present invention, searching for an optimal landing point according to landing area information and collecting optimal landing point parameter information includes:

[0165] Calculate the glide distance based on the optimal landing point parameter information;

[0166] Determining whether the glide distance satisfies a preset glide distance, and if so, generating a first landing parameter, and making the aircraft glide and land according to the first landing parameter;

[0167] If it is less than, a second landing parameter is generated, and the aircraft is controlled to make a vertical landing according to the second landing parameter;

[0168] During the vertical landing of the aircraft, the aircraft descent speed is collected;

[0169] Compare the aircraft's descent speed with the preset speed to obtain a speed deviation rate;

[0170] Determine whether the speed deviation rate is greater than a preset speed deviation rate threshold;

[0171] If it is greater, the second landing parameter is adjusted and updated.

[0172] According to an embodiment of the present invention, if is greater than , a first landing parameter is generated, and the aircraft is caused to glide and land according to the first landing parameter; comprising:

[0173] Obtain aircraft attitude information;

[0174] Compare the aircraft attitude information with the preset attitude information to obtain the attitude deviation rate;

[0175] Determine whether the posture deviation rate is greater than a preset deviation rate threshold;

[0176] If it is greater, adjustment information is generated and the first landing parameter is adjusted according to the adjustment information.

[0177] According to an embodiment of the present invention, it also includes:

[0178] Obtain aircraft landing parameters, and generate landing time according to the aircraft landing parameters;

[0179] Compare the landing time with the preset landing time to obtain the time deviation rate;

[0180] Determine whether the time deviation rate is greater than a preset time deviation rate threshold;

[0181] If it is greater, the remaining capacity information is generated; the aircraft attitude adjustment information is generated according to the remaining capacity information; the aircraft landing parameters are urgently adjusted according to the attitude adjustment information, so that the aircraft landing attitude reaches the predetermined attitude, ensuring a smooth landing of the aircraft.

[0182] A third aspect of the present invention provides a computer-readable storage medium, which includes an emergency handling method program for aircraft power failure. When the emergency handling method program for aircraft power failure is executed by a processor, the steps of the emergency handling method for aircraft power failure as described above are implemented.

[0183] The present invention discloses an emergency handling method, system and medium for aircraft power failure, which obtains aircraft operation status data and inputs a preset model to obtain an operation status characteristic value; compares the operation status characteristic value with a preset operation status characteristic value to obtain a state deviation rate; determines whether the state deviation rate is greater than or equal to a preset state deviation rate threshold; if greater than or equal to, outputs aircraft fault information; performs difference calculation between the aircraft fault information and the preset fault information to obtain a fault difference; if the fault difference is greater than or equal to the set fault difference threshold, determines that the aircraft power fails and generates an emergency strategy; generates aircraft control information according to the emergency strategy; controls the aircraft to perform emergency landing according to the aircraft control information; determines the power failure state through the aircraft fault information and determines the aircraft's maximum flight area according to the energy information, and flexibly selects an emergency landing point for emergency landing, thereby improving the safety of the aircraft.

[0184] In the several embodiments provided in the present application, it should be understood that the disclosed devices and methods can be implemented in other ways. The device embodiments described above are only schematic. For example, the division of units is only a logical function division. There may be other division methods in actual implementation, such as: multiple units or components can be combined, or can be integrated into another system, or some features can be ignored or not executed. In addition, the coupling, direct coupling, or communication connection between the components shown or discussed can be through some interfaces, and the indirect coupling or communication connection of devices or units can be electrical, mechanical or other forms.

[0185] The units described above as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units; they may be located in one place or distributed on multiple network units; some or all of the units may be selected according to actual needs to achieve the purpose of the present embodiment.

[0186] In addition, all functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may be separately used as a unit, or two or more units may be integrated into one unit; the above-mentioned integrated units may be implemented in the form of hardware or in the form of hardware plus software functional units.

[0187] Those skilled in the art can understand that: all or part of the steps of implementing the above method embodiments can be completed by hardware related to program instructions, and the aforementioned program can be stored in a readable storage medium. When the program is executed, it executes the steps of the above method embodiments; and the aforementioned storage medium includes: mobile storage devices, read-only memories (ROM, Read-Only Memory), random access memories (RAM, Random Access Memory), disks or optical disks, and other media that can store program codes.

[0188] Alternatively, if the above-mentioned integrated unit of the present invention is implemented in the form of a software function module and sold or used as an independent product, it can also be stored in a readable storage medium. Based on this understanding, the technical solution of the embodiment of the present invention can be essentially or partly reflected in the form of a software product that contributes to the prior art. The software product is stored in a storage medium and includes several instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the methods described in each embodiment of the present invention. The aforementioned storage medium includes: various media that can store program codes, such as mobile storage devices, ROM, RAM, magnetic disks or optical disks.

Claims

1. An emergency handling method for aircraft power failure, characterized in that: include: Obtain aircraft operation status data and input it into a preset model to obtain operation status characteristic values; Compare the running state characteristic value with the preset running state characteristic value to obtain the state deviation rate; Determining whether the state deviation rate is greater than or equal to a preset state deviation rate threshold; If it is greater than or equal to, then output aircraft fault information; Performing a difference calculation between the aircraft fault information and the preset fault information to obtain a fault difference; If the fault difference is greater than or equal to the set fault difference threshold, the aircraft power failure is determined and an emergency strategy is generated; Generate aircraft control information according to the emergency strategy; control the aircraft for emergency landing according to the aircraft control information.

2. The emergency handling method for aircraft power failure according to claim 1, characterized in that: The step of obtaining the aircraft operation status data and inputting the preset model to obtain the operation status characteristic value includes: Obtain the aircraft's navigation speed, navigation direction, and yaw angle data, and generate a data set; Input the data set into the preset neural network model for training to obtain training result data; Determining whether the training result data converges; If convergence occurs, obtain the validation set data, verify the training result data based on the validation set data, and obtain the accuracy; Determining whether the accuracy meets a preset condition; If satisfied, the operating status characteristic value is output through the neural network model; If it is not satisfied, correction information is generated and the neural network model parameters are corrected through the correction information.

3. The emergency treatment method for aircraft power failure according to claim 2, characterized in that: Generating aircraft control information according to the emergency strategy; and controlling the aircraft for emergency landing according to the aircraft control information include: When the aircraft power fails, obtain the aircraft operation status information and the nearest landing point location information; Determine whether the aircraft can reach the landing point based on the nearest landing point location information; If yes, the aircraft returns the nearest landing point location information; If not, obtain the image information around the current position of the aircraft; Extracting image feature values ​​based on the current surrounding image information of the aircraft; Determine whether the flatness of the surrounding area is greater than a preset flatness threshold; If it is greater, temporary landing point information is generated, and the aircraft is driven to make an emergency landing according to the temporary landing point information.

4. The emergency treatment method for aircraft power failure according to claim 3, characterized in that: Generate aircraft control information according to the emergency strategy; control the aircraft for emergency landing according to the aircraft control information, including: When the aircraft power fails, obtain the aircraft operation status information and energy information; Determine whether the aircraft can reach the take-off position based on the aircraft's energy information; If yes, the aircraft is controlled to return to the aircraft take-off position; If not, the energy information of the aircraft is input into the flight model to obtain the maximum flight distance of the aircraft; Establish landing area information based on the aircraft's maximum flight distance; Search for the best landing point based on the landing area information and collect the best landing point parameter information; Generate aircraft landing parameters based on the optimal landing point parameter information to control the aircraft to fly and land.

5. The emergency handling method for aircraft power failure according to claim 4, characterized in that: The step of searching for the best landing point according to the landing area information and collecting parameter information of the best landing point includes: Calculate the glide distance based on the optimal landing point parameter information; determining whether the glide distance satisfies a preset glide distance, and if so, generating a first landing parameter, and causing the aircraft to glide and land according to the first landing parameter; If it is less than, a second landing parameter is generated, and the aircraft is controlled to make a vertical landing according to the second landing parameter; During the vertical landing of the aircraft, the aircraft descent speed is collected; Compare the aircraft's descent speed with the preset speed to obtain a speed deviation rate; Determining whether the speed deviation rate is greater than a preset speed deviation rate threshold; If it is greater, the second landing parameter is adjusted and updated.

6. The emergency handling method for aircraft power failure according to claim 5, characterized in that: If the above value is greater than , generating a first landing parameter, and making the aircraft glide and land according to the first landing parameter; comprising: Obtain aircraft attitude information; Comparing the aircraft attitude information with preset attitude information to obtain an attitude deviation rate; Determining whether the posture deviation rate is greater than a preset deviation rate threshold; If it is greater, adjustment information is generated and the first landing parameter is adjusted according to the adjustment information.

7. An emergency handling system for aircraft power failure, characterized in that: The system includes: a memory and a processor, wherein the memory includes a program of an emergency processing method under aircraft power failure, and when the program of the emergency processing method under aircraft power failure is executed by the processor, the following steps are implemented: Obtain aircraft operation status data and input it into a preset model to obtain operation status characteristic values; Compare the running state characteristic value with the preset running state characteristic value to obtain the state deviation rate; Determining whether the state deviation rate is greater than or equal to a preset state deviation rate threshold; If it is greater than or equal to, then output aircraft fault information; Performing a difference calculation between the aircraft fault information and the preset fault information to obtain a fault difference; If the fault difference is greater than or equal to the set fault difference threshold, the aircraft power failure is determined and an emergency strategy is generated; Generate aircraft control information according to the emergency strategy; control the aircraft for emergency landing according to the aircraft control information.

8. The emergency handling system for aircraft power failure according to claim 7, characterized in that: The step of obtaining the aircraft operation status data and inputting the preset model to obtain the operation status characteristic value includes: Obtain the aircraft's navigation speed, navigation direction, and yaw angle data, and generate a data set; Input the data set into the preset neural network model for training to obtain training result data; Determining whether the training result data converges; If convergence occurs, obtain the validation set data, verify the training result data based on the validation set data, and obtain the accuracy; Determining whether the accuracy meets a preset condition; If satisfied, the operating status characteristic value is output through the neural network model; If it is not satisfied, correction information is generated and the neural network model parameters are corrected through the correction information.

9. The emergency handling system for aircraft power failure according to claim 8, characterized in that: Generating aircraft control information according to the emergency strategy; and controlling the aircraft for emergency landing according to the aircraft control information include: When the aircraft power fails, obtain the aircraft operation status information and the nearest landing point location information; Determine whether the aircraft can reach the landing point based on the nearest landing point location information; If yes, the aircraft returns the nearest landing point location information; If not, obtain the image information around the current position of the aircraft; Extracting image feature values ​​based on the current surrounding image information of the aircraft; Determine whether the flatness of the surrounding area is greater than a preset flatness threshold; If it is greater, temporary landing point information is generated, and the aircraft is driven to make an emergency landing according to the temporary landing point information.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium includes an emergency processing method program for aircraft power failure. When the emergency processing method program for aircraft power failure is executed by a processor, the steps of the emergency processing method for aircraft power failure as described in any one of claims 1 to 6 are implemented.

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