Unmanned aircraft oxygen leakage detection method and system and medium

Abstract

The embodiment of the invention provides an oxygen leakage detection method and system for an unmanned aircraft and a medium. The method comprises the following steps: acquiring internal pressure information of the aircraft; comparing the internal pressure information of the aircraft with preset pressure information to obtain pressure difference information; inputting the pressure difference information into a preset gas leakage model, and outputting gas leakage information; decomposing components of leaked gas according to the gas leakage information, and acquiring oxygen leakage information; transmitting the oxygen leakage information to a terminal according to a predetermined mode; according to the method, the gas leakage is identified and judged by judging the internal pressure change of the aircraft and analyzing the pressure relief state of the internal space of the aircraft, so that the oxygen leakage is analyzed according to the components of the leaked gas, and the oxygen leakage in the aircraft is more accurately detected.

Description

Technical Field

[0001] The present application relates to the field of aircraft oxygen leak detection, and more specifically, to a method, system, and medium for detecting oxygen leaks in unmanned aircraft. Background Art

[0002] Aircraft are human-made and human-controlled aircraft that can fly within the atmosphere. They are lifted and flown by the static buoyancy of air or the aerodynamic forces generated by the relative motion of air. Common aircraft include balloons, gliders, airships, airplanes, helicopters, and quadcopters. A glider is a heavier-than-air fixed-wing aircraft that does not rely on a power unit to fly. After takeoff, it relies solely on the reaction force of the air acting on its lifting surface to fly freely. Generally, gliders do not have a power unit, but there are also powered gliders equipped with power units. Powered gliders are equipped with a small auxiliary power unit for self-takeoff. During flight, the aircraft needs to exchange internal and external gases to ensure that the oxygen content inside the aircraft is within a safe range. Existing methods for detecting oxygen leaks in aircraft all rely on real-time detection by installing multiple gas detection sensors inside the aircraft. However, the detection accuracy is poor and it is impossible to accurately analyze oxygen leakage information through gas leakage models, which will result in large detection errors. To address the above problems, effective technical solutions are urgently needed. Summary of the Invention

[0003] The purpose of the embodiments of the present application is to provide an unmanned aircraft oxygen leak detection method, system and medium, which can identify and determine gas leaks by judging the pressure changes inside the aircraft and analyzing the pressure relief state of the aircraft's internal space, thereby analyzing oxygen leaks based on the components of the leaked gas and more accurately detecting oxygen leaks in the aircraft.

[0004] The present application also provides a method for detecting oxygen leakage in an unmanned aerial vehicle, comprising:

[0005] Obtain aircraft internal pressure information;

[0006] Compare the internal pressure information of the aircraft with the preset pressure information to obtain pressure difference information;

[0007] Input the pressure difference information into the preset gas leakage model and output the gas leakage information;

[0008] Decompose the components of the leaked gas according to the gas leakage information and obtain oxygen leakage information;

[0009] The oxygen leakage information is transmitted to the terminal in a predetermined manner.

[0010] Optionally, in the unmanned aerial vehicle oxygen leak detection method described in the embodiment of the present application, after obtaining the aircraft internal pressure information, the method further includes:

[0011] Obtaining the internal pressure information of the aircraft, and spatially dividing the internal pressure information of the aircraft to obtain pressure information of a plurality of subspaces;

[0012] Compare the pressure information of adjacent subspaces to obtain the pressure deviation rate;

[0013] Determining whether the pressure deviation rate is greater than or equal to a preset deviation rate threshold;

[0014] If it is greater than or equal to, it is determined that the corresponding subspace pressure is abnormal;

[0015] If it is less than, it is determined that the corresponding subspace pressure is normal.

[0016] Optionally, in the unmanned aerial vehicle oxygen leak detection method described in an embodiment of the present application, obtaining the aircraft internal pressure information and spatially dividing the aircraft internal pressure information to obtain a plurality of subspace pressure information specifically includes:

[0017] Obtain aircraft parameter information and divide the interior space of the aircraft into equal volumes to form several subspaces;

[0018] Obtaining gas flow information of several subspaces and generating a pressure correction coefficient based on the gas flow information;

[0019] The pressure correction coefficient is multiplied by the internal pressure information of the aircraft to obtain the pressure information of several subspaces.

[0020] Optionally, in the unmanned aerial vehicle oxygen leak detection method described in the embodiment of the present application, the aircraft internal pressure information is compared with preset pressure information to obtain pressure difference information, the pressure difference information is input into a preset gas leakage model, and the gas leakage information is output, specifically:

[0021] Acquiring aircraft internal pressure information at adjacent time nodes to obtain first pressure information and second pressure information;

[0022] By comparing the first pressure information and the second pressure information with the preset pressure information respectively, first pressure difference information and second pressure difference information are obtained;

[0023] Inputting the first pressure difference information and the second pressure difference information into the gas leakage model respectively to obtain first gas leakage information and second gas leakage information;

[0024] Subtracting the first gas leakage information from the second gas leakage information, and performing absolute value calculation to obtain difference information;

[0025] The aircraft decompression rate is calculated based on the difference information, and the aircraft decompression status information is generated based on the aircraft decompression rate.

[0026] Optionally, in the unmanned aerial vehicle oxygen leak detection method described in the embodiment of the present application, after calculating the aircraft depressurization rate based on the difference information and generating aircraft depressurization status information based on the aircraft depressurization rate, the method further includes:

[0027] Obtain aircraft decompression status information;

[0028] Comparing the aircraft decompression state information with preset state information to obtain a decompression state deviation rate;

[0029] Determining whether the pressure relief state deviation rate is greater than or equal to a preset deviation rate threshold;

[0030] If it is greater than or equal to, an alarm message is generated and an alarm is issued for the aircraft decompression state according to the alarm message;

[0031] If it is less than, the aircraft decompression status will be detected in real time.

[0032] Optionally, in the unmanned aerial vehicle oxygen leak detection method described in the embodiment of the present application, the components of the leaked gas are decomposed according to the gas leakage information, and the oxygen leakage information is obtained, specifically:

[0033] Obtain gas leakage information and decompose the leaked gas into components to obtain the proportion information of each component;

[0034] Calculate the concentration information of each component according to the proportion information of each component, and filter according to the concentration information of each component to obtain the oxygen leakage concentration information;

[0035] Compare the oxygen leakage concentration information with the preset concentration information to obtain the concentration change rate;

[0036] Determining whether the concentration deviation rate is greater than or equal to a preset deviation rate threshold;

[0037] If it is greater than or equal to, oxygen leakage information is obtained;

[0038] If it is less than, it is determined that the leaked gas is within the normal error range.

[0039] In a second aspect, an embodiment of the present application provides an unmanned aircraft oxygen leak detection system, the system comprising: a memory and a processor, the memory comprising a program for an unmanned aircraft oxygen leak detection method, and the processor executing the program of the unmanned aircraft oxygen leak detection method to implement the following steps:

[0040] Obtain aircraft internal pressure information;

[0041] Compare the internal pressure information of the aircraft with the preset pressure information to obtain pressure difference information;

[0042] Input the pressure difference information into the preset gas leakage model and output the gas leakage information;

[0043] Decompose the components of the leaked gas according to the gas leakage information and obtain oxygen leakage information;

[0044] The oxygen leakage information is transmitted to the terminal in a predetermined manner.

[0045] Optionally, in the unmanned aerial vehicle oxygen leak detection system according to the embodiment of the present application, after obtaining the internal pressure information of the aircraft, the system further includes:

[0046] Obtaining the internal pressure information of the aircraft, and spatially dividing the internal pressure information of the aircraft to obtain pressure information of a plurality of subspaces;

[0047] Compare the pressure information of adjacent subspaces to obtain the pressure deviation rate;

[0048] Determining whether the pressure deviation rate is greater than or equal to a preset deviation rate threshold;

[0049] If it is greater than or equal to, it is determined that the corresponding subspace pressure is abnormal;

[0050] If it is less than, it is determined that the corresponding subspace pressure is normal.

[0051] Optionally, in the unmanned aerial vehicle oxygen leak detection system described in the embodiment of the present application, the obtaining of the aircraft internal pressure information and spatially dividing the aircraft internal pressure information to obtain a plurality of sub-space pressure information specifically includes:

[0052] Obtain aircraft parameter information and divide the interior space of the aircraft into equal volumes to form several subspaces;

[0053] Obtaining gas flow information of several subspaces and generating a pressure correction coefficient based on the gas flow information;

[0054] The pressure correction coefficient is multiplied by the internal pressure information of the aircraft to obtain the pressure information of several subspaces.

[0055] In a third aspect, an embodiment of the present application further provides a computer-readable storage medium, which includes an unmanned aircraft oxygen leak detection method program. When the unmanned aircraft oxygen leak detection method program is executed by a processor, the steps of the unmanned aircraft oxygen leak detection method as described in any one of the above items are implemented.

[0056] As can be seen from the above, the embodiments of the present application provide an unmanned aircraft oxygen leak detection method, system and medium, which obtain the internal pressure information of the aircraft; compare the internal pressure information of the aircraft with preset pressure information to obtain pressure difference information; input the pressure difference information into a preset gas leakage model to output gas leakage information; decompose the components of the leaked gas according to the gas leakage information, and obtain oxygen leakage information; transmit the oxygen leakage information to a terminal in a predetermined manner; analyze the pressure relief state of the internal space of the aircraft according to the change of the internal pressure of the aircraft, identify and judge the gas leakage by judging the pressure relief state, and thus analyze the oxygen leakage according to the components of the leaked gas, so as to more accurately detect the oxygen leakage in the aircraft.

[0057] Other features and advantages of the present application will be described in the subsequent description. The objects and advantages of the present application can be realized and obtained through the structures particularly pointed out in the written description, claims, and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0058] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments of the present application. 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 relevant drawings can be obtained based on these drawings without creative work.

[0059] Figure 1 A flow chart of a method for detecting oxygen leaks in an unmanned aerial vehicle provided in an embodiment of the present application;

[0060] Figure 2 A subspace pressure analysis flow chart of the unmanned aerial vehicle oxygen leak detection method provided in an embodiment of the present application;

[0061] Figure 3 A flowchart of obtaining subspace pressure information of the unmanned aerial vehicle oxygen leak detection method provided in an embodiment of the present application;

[0062] Figure 4 This is a schematic diagram of the structure of the unmanned aerial vehicle oxygen leak detection system provided in an embodiment of the present application. DETAILED DESCRIPTION

[0063] 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 generally 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 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 fall within the scope of protection of the present application.

[0064] It should be noted that similar reference numerals and letters represent similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined or 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 should not be understood as indicating or implying relative importance.

[0065] Please refer to Figure 1 , Figure 1 The flowchart of a method for detecting oxygen leaks in an unmanned aerial vehicle (UAV) in some embodiments of the present application is shown. The method is used in a terminal device and includes the following steps:

[0066] S101, obtaining aircraft internal pressure information;

[0067] S102, comparing the internal pressure information of the aircraft with the preset pressure information to obtain pressure difference information;

[0068] S103, inputting the pressure difference information into a preset gas leakage model and outputting gas leakage information;

[0069] S104, decomposing the leaked gas into components according to the gas leakage information, and obtaining oxygen leakage information;

[0070] S105: Transmit the oxygen leakage information to the terminal in a predetermined manner.

[0071] It should be noted that, as an implementation, 16 piezoresistive pressure sensors are evenly distributed along the inner wall of the aircraft cabin to collect cabin pressure data in real time and transmit it to the flight control computer. The system uses a dynamic pressure threshold calibration module to process raw data, including the current flight altitude obtained from the onboard air data system and the cabin temperature measured by a temperature sensor. This data then uses a pre-stored pressure-altitude compensation curve to generate a real-time safety threshold. Furthermore, the pressure differential calculation stage uses a differential algorithm to compare the instantaneous pressure with the safety threshold and output pressure differential information. In this embodiment, the core step is gas leakage model analysis. Pressure differential information, cabin volume, and ambient temperature are input into a physical model based on the Navier-Stokes equations. The model is calibrated through wind tunnel testing and outputs the leakage volume and coordinates of the suspected leak area. In the oxygen leak determination phase, when the leakage volume exceeds a preset threshold, the mass spectrometer located closest to the leak point is activated to perform a 0.1-second rapid component analysis of the collected gas and calculate the oxygen volume concentration. If the oxygen volume concentration drops by ≥3% compared to the baseline value, an oxygen leak event is flagged. Ultimately, through a hierarchical transmission mechanism, the leak level and location data are pushed to the ground station via a communication link, simultaneously triggering the cabin's audible and visual alarms. By assessing internal aircraft pressure changes and inputting a preset gas leak model, the system acquires real-time gas leak information. The leaked gas is then decomposed into its components, allowing oxygen to be screened and differentiated, enabling accurate identification and analysis of oxygen leaks.

[0072] Please refer to Figure 2 , Figure 2 This is a subspace pressure analysis flow chart of a method for detecting oxygen leaks in an unmanned aircraft in some embodiments of the present application. According to an embodiment of the present invention, after obtaining the internal pressure information of the aircraft, the method further includes:

[0073] S201, obtaining aircraft internal pressure information, and spatially dividing the aircraft internal pressure information to obtain a plurality of sub-space pressure information;

[0074] S202, comparing pressure information of adjacent subspaces to obtain a pressure deviation rate;

[0075] S203, determining whether the pressure deviation rate is greater than or equal to a preset deviation rate threshold;

[0076] S204, if it is greater than or equal to, it is determined that the corresponding subspace pressure is abnormal;

[0077] S205: If it is less than, it is determined that the corresponding subspace pressure is normal.

[0078] It should be noted that, as an implementation method, subspace pressure monitoring relies on three-dimensional spatial grid control. The aircraft CAD model is imported into pre-set software, and the cabin is divided into unit cubes. A pressure sensor is deployed at the center of each unit. An anomaly detection algorithm is used to collect pressure values ​​in adjacent subspaces every 0.5 seconds, and the normalized deviation rate of these adjacent subspaces is calculated. A threshold determination mechanism is then used to compare the deviation rate with a preset static threshold. If the deviation rate is greater than or equal to the static threshold, the subspace is marked as abnormal and dynamic compensation is initiated. If the deviation rate is less than the static threshold, the subspace pressure is deemed normal. By dividing the aircraft interior into subspaces, performing pressure identification on each subspace, and determining the pressure information of adjacent subspaces, the pressure information of adjacent subspaces is normally minimal. Only when a leak occurs in one subspace will a significant pressure deviation between the two adjacent subspaces occur, allowing for precise identification of abnormal and normal subspaces.

[0079] Please refer to Figure 3 , Figure 3 This is a flow chart of obtaining subspace pressure information for a method for detecting oxygen leaks in an unmanned aircraft in some embodiments of the present application. According to an embodiment of the present invention, obtaining aircraft internal pressure information and spatially dividing the aircraft internal pressure information to obtain a plurality of subspace pressure information specifically includes:

[0080] S301, obtaining aircraft parameter information, dividing the interior space of the aircraft into equal volumes to form a plurality of subspaces;

[0081] S302, obtaining gas flow information of a plurality of subspaces, and generating a pressure correction coefficient based on the gas flow information;

[0082] S303: Multiply the pressure correction coefficient by the aircraft internal pressure information to obtain a plurality of subspace pressure information.

[0083] It should be noted that, as an implementation method, the engineering implementation of equal-volume segmentation is based on parametric modeling. The aircraft cabin dimensions are first imported from the aircraft's bill of materials (BOM), a surface model is generated using a Python script, and then adaptive tetrahedral meshing is used to create several subspaces. The key to the airflow compensation mechanism lies in constructing a velocity-pressure mapping database. By setting boundary conditions, the steady-state flow velocity at all monitoring points in the cabin is calculated, and a lookup table of corresponding flow velocity values ​​is output based on the location coordinates of the monitoring points. The real-time sensor pressure and the steady-state flow velocity corresponding to the monitoring point are substituted into a preset correction formula to calculate the corresponding pressure correction coefficient. Finally, the corrected pressure value for each subspace is obtained based on the pressure correction coefficient and the pressure value of each subspace. By performing equal-volume segmentation on the aircraft's interior, the volume of each subspace is constant under normal circumstances. When a gas leak occurs in one of the subspaces, the gas flow within that subspace fluctuates. By analyzing the gas flow information in the subspace, the pressure is corrected, resulting in accurate calculation of the subspace's pressure information and pressure change information.

[0084] According to an embodiment of the present invention, the internal pressure information of the aircraft is compared with the preset pressure information to obtain pressure difference information, and the pressure difference information is input into a preset gas leakage model to output gas leakage information, specifically:

[0085] Acquiring aircraft internal pressure information at adjacent time nodes to obtain first pressure information and second pressure information;

[0086] By comparing the first pressure information and the second pressure information with the preset pressure information respectively, first pressure difference information and second pressure difference information are obtained;

[0087] Inputting the first pressure difference information and the second pressure difference information into the gas leakage model respectively to obtain first gas leakage information and second gas leakage information;

[0088] Subtracting the first gas leakage information from the second gas leakage information, and performing absolute value calculation to obtain difference information;

[0089] The aircraft decompression rate is calculated based on the difference information, and the aircraft decompression status information is generated based on the aircraft decompression rate.

[0090] It should be noted that, as an implementation method, the pressure relief state analysis adopts a time series comparison architecture, stores pressure snapshots according to a preset monitoring period, and selects the pressure information of two consecutive time windows as data packets. The difference between the two pressure information and the set standard pressure information is calculated respectively to obtain the corresponding two pressure difference data. The two pressure difference data are input into the preset gas leakage model, and two leakage flow values ​​are output. The absolute value of the difference between the two leakage flow values ​​is calculated as the flow difference information to calculate the aircraft pressure relief rate. The pressure relief state of the aircraft is judged according to the pressure relief rate, wherein the pressure relief state includes normal fluctuations, slow leakage and extreme pressure loss. In this embodiment, by judging the changes in the internal pressure of the aircraft at adjacent time nodes, the gas leakage information is accurately analyzed, and the pressure relief rate of the aircraft is calculated. The pressure relief state of the aircraft is calculated by the pressure relief rate, and the calculation result is more accurate.

[0091] According to an embodiment of the present invention, after calculating the aircraft decompression rate based on the difference information and generating aircraft decompression state information based on the aircraft decompression rate, the method further includes:

[0092] Obtain aircraft decompression status information;

[0093] Comparing the aircraft decompression state information with preset state information to obtain a decompression state deviation rate;

[0094] Determine whether the pressure relief state deviation rate is greater than or equal to a preset deviation rate threshold;

[0095] If it is greater than or equal to, an alarm message is generated and an alarm is issued for the aircraft decompression state according to the alarm message;

[0096] If it is less than, the aircraft decompression status will be detected in real time.

[0097] It should be noted that the real-time decompression status is compared with the preset status to calculate the decompression status deviation rate, and a threshold is used to determine whether to activate an alarm. If the deviation rate is greater than or equal to the preset safety threshold, an emergency response is triggered, including but not limited to disconnecting non-critical circuits, releasing emergency oxygen, and recording black box codes. If the deviation rate is less than the preset safety threshold, the decompression status is continuously recorded. In this embodiment, the decompression status of the aircraft is determined. When the decompression status shows a significant deviation, it indicates an emergency situation. At this time, an alarm for the aircraft decompression status needs to be issued, thereby enabling a faster response, rapid maintenance, and improved aircraft safety.

[0098] According to an embodiment of the present invention, the components of the leaked gas are decomposed according to the gas leakage information, and oxygen leakage information is obtained, specifically:

[0099] Obtain gas leakage information and decompose the leaked gas into components to obtain the proportion information of each component;

[0100] Calculate the concentration information of each component according to the proportion information of each component, and filter according to the concentration information of each component to obtain the oxygen leakage concentration information;

[0101] Compare the oxygen leakage concentration information with the preset concentration information to obtain the concentration change rate;

[0102] Determining whether the concentration deviation rate is greater than or equal to a preset deviation rate threshold;

[0103] If it is greater than or equal to, oxygen leakage information is obtained;

[0104] If it is less than, it is determined that the leaked gas is within the normal error range.

[0105] It should be noted that, as an implementation method, dual-channel analysis is used to verify oxygen leakage. The main channel uses mass spectrometry: the leaked gas is introduced into the ionization chamber through a capillary tube, and the oxygen ion intensity ratio is measured by magnetic field deflection to calculate the oxygen mole fraction. The auxiliary channel uses TDLAS technology: a near-infrared laser penetrates the gas chamber, and the O2 absorption spectrum is inverted through the HITRAN database to output the oxygen concentration value. The real-time concentration change rate is obtained by comparing the oxygen concentration with the preset marked concentration; if the concentration change rate is greater than or equal to the preset deviation rate threshold, it is determined to be an oxygen leak; otherwise, it is determined to be within the normal measurement error range. By decomposing the leaked gas into components, the component ratio in the leaked gas is analyzed, and the concentration information of each component is calculated, so that the oxygen leakage concentration can be analyzed more accurately and whether the oxygen leakage concentration is within the normal error range can be determined. If the error is large, the oxygen leakage information is identified and judged.

[0106] According to an embodiment of the present invention, the further embodiment includes:

[0107] Obtain the oxygen leakage concentration at adjacent time nodes, perform difference calculation on the oxygen leakage concentration at adjacent time nodes, and obtain the oxygen leakage rate;

[0108] Determining whether the oxygen leakage rate is greater than or equal to a preset leakage rate threshold;

[0109] If it is greater than or equal to, it is determined that the oxygen leakage is fast, and a first alarm message is generated to issue a real-time alarm for the oxygen leakage information;

[0110] If it is less than, it is determined that the oxygen leakage is slow, and a second alarm message is generated to issue a real-time alarm for the oxygen leakage information.

[0111] It should be noted that, as an implementation method, the core of the leakage rate graded alarm lies in the time domain differential processing. The oxygen concentration value is recorded according to the preset processing cycle, and the instantaneous leakage rate is calculated based on the concentration difference through the five-point differential formula. When the leakage rate is greater than or equal to the set threshold, a red full-screen alarm is triggered and emergency oxygen is released. When the leakage rate is less than the set threshold, a yellow pop-up prompt is triggered and a broadcast prompt is issued. By judging the oxygen leakage rate and performing different types of alarms, the oxygen leakage rate is distinguished by the first alarm information and the second alarm information to improve the alarm differentiation. The first alarm information and the second alarm information can be distinguished by the frequency of the alarm or the volume of the alarm.

[0112] According to an embodiment of the present invention, the further embodiment includes:

[0113] Real-time collection of aircraft extravehicular environmental parameters, including temperature, humidity, flight altitude, and body vibration spectrum;

[0114] Obtaining disturbance factor information based on the external environment parameters and a preset disturbance factor relationship;

[0115] If the disturbance factor information is greater than a preset disturbance factor threshold, the model accuracy is verified by periodically injecting tracer gas.

[0116] It should be noted that the disturbance factor relationship is:

[0117] λ=k1△T+k2△H+k3A v , where λ is the disturbance factor, k1, k2, k3 are calibration coefficients, △T is the temperature difference between inside and outside the cabin, △H is the height difference, A v =vibration energy. When the disturbance factor exceeds a preset threshold, the calibration process is activated. By injecting a trace amount of tracer gas into the chamber every 5 minutes, the model's predicted leak location is compared with the actual sensor response location, enabling model validation and calibration.

[0118] According to an embodiment of the present invention, the further embodiment includes:

[0119] Oxygen leak level and remaining flight time;

[0120] When it is determined that the oxygen leakage is slow, the mission can be continued or an emergency return can be triggered based on the relationship between the remaining flight time and the preset safety flight threshold.

[0121] It should be noted that, as an implementation method, when the oxygen leakage is slow and the remaining flight time exceeds 30 minutes, the aircraft is allowed to continue to perform the current mission to ensure the mission completion rate; if the remaining flight time does not exceed 30 minutes, the emergency return operation is triggered after the heading is corrected and the aircraft climbs to a safe altitude to reduce the accident rate of the aircraft.

[0122] Please refer to Figure 4 , Figure 4 is a schematic diagram of the structure of an unmanned aircraft oxygen leak detection system in some embodiments of the present application. In a second aspect, embodiments of the present application provide an unmanned aircraft oxygen leak detection system 4, comprising: a memory 41 and a processor 42. The memory 41 includes a program for an unmanned aircraft oxygen leak detection method. When the program is executed by the processor, the unmanned aircraft oxygen leak detection method performs the following steps:

[0123] Obtain aircraft internal pressure information;

[0124] Compare the internal pressure information of the aircraft with the preset pressure information to obtain pressure difference information;

[0125] Input the pressure difference information into the preset gas leakage model and output the gas leakage information;

[0126] Decompose the components of the leaked gas according to the gas leakage information and obtain oxygen leakage information;

[0127] The oxygen leakage information is transmitted to the terminal in a predetermined manner.

[0128] It should be noted that, as an implementation, 16 piezoresistive pressure sensors are evenly distributed along the inner wall of the aircraft cabin to collect cabin pressure data in real time and transmit it to the flight control computer. The system uses a dynamic pressure threshold calibration module to process raw data, including the current flight altitude obtained from the onboard air data system and the cabin temperature measured by a temperature sensor. This data then uses a pre-stored pressure-altitude compensation curve to generate a real-time safety threshold. Furthermore, the pressure differential calculation stage uses a differential algorithm to compare the instantaneous pressure with the safety threshold and output pressure differential information. In this embodiment, the core step is gas leakage model analysis. Pressure differential information, cabin volume, and ambient temperature are input into a physical model based on the Navier-Stokes equations. The model is calibrated through wind tunnel testing and outputs the leakage volume and coordinates of the suspected leak area. In the oxygen leak determination phase, when the leakage volume exceeds a preset threshold, the mass spectrometer located closest to the leak point is activated to perform a 0.1-second rapid component analysis of the collected gas and calculate the oxygen volume concentration. If the oxygen volume concentration drops by ≥3% compared to the baseline value, an oxygen leak event is flagged. Ultimately, through a hierarchical transmission mechanism, the leak level and location data are pushed to the ground station via a communication link, simultaneously triggering the cabin's audible and visual alarms. By assessing internal aircraft pressure changes and inputting a preset gas leak model, the system acquires real-time gas leak information. The leaked gas is then decomposed into its components, allowing oxygen to be screened and differentiated, enabling accurate identification and analysis of oxygen leaks.

[0129] According to an embodiment of the present invention, after obtaining the internal pressure information of the aircraft, the method further includes:

[0130] Obtaining the internal pressure information of the aircraft, and spatially dividing the internal pressure information of the aircraft to obtain pressure information of a plurality of subspaces;

[0131] Compare the pressure information of adjacent subspaces to obtain the pressure deviation rate;

[0132] Determining whether the pressure deviation rate is greater than or equal to a preset deviation rate threshold;

[0133] If it is greater than or equal to, it is determined that the corresponding subspace pressure is abnormal;

[0134] If it is less than, it is determined that the corresponding subspace pressure is normal.

[0135] It should be noted that, as an implementation method, subspace pressure monitoring relies on three-dimensional spatial grid control. The aircraft CAD model is imported into pre-set software, and the cabin is divided into unit cubes. A pressure sensor is deployed at the center of each unit. An anomaly detection algorithm is used to collect pressure values ​​in adjacent subspaces every 0.5 seconds, and the normalized deviation rate of these adjacent subspaces is calculated. A threshold determination mechanism is then used to compare the deviation rate with a preset static threshold. If the deviation rate is greater than or equal to the static threshold, the subspace is marked as abnormal and dynamic compensation is initiated. If the deviation rate is less than the static threshold, the subspace pressure is deemed normal. By dividing the aircraft interior into subspaces, performing pressure identification on each subspace, and determining the pressure information of adjacent subspaces, the pressure information of adjacent subspaces is normally minimal. Only when a leak occurs in one subspace will a significant pressure deviation between the two adjacent subspaces occur, allowing for precise identification of abnormal and normal subspaces.

[0136] According to an embodiment of the present invention, the internal pressure information of the aircraft is obtained, and the internal pressure information of the aircraft is spatially divided to obtain a plurality of sub-space pressure information, specifically including:

[0137] Obtain aircraft parameter information and divide the interior space of the aircraft into equal volumes to form several subspaces;

[0138] Obtaining gas flow information of several subspaces and generating a pressure correction coefficient based on the gas flow information;

[0139] The pressure correction coefficient is multiplied by the internal pressure information of the aircraft to obtain the pressure information of several subspaces.

[0140] It should be noted that, as an implementation method, the engineering implementation of equal-volume segmentation is based on parametric modeling. The aircraft cabin dimensions are first imported from the aircraft's bill of materials (BOM), a surface model is generated using a Python script, and then adaptive tetrahedral meshing is used to create several subspaces. The key to the airflow compensation mechanism lies in constructing a velocity-pressure mapping database. By setting boundary conditions, the steady-state flow velocity at all monitoring points in the cabin is calculated, and a lookup table of corresponding flow velocity values ​​is output based on the location coordinates of the monitoring points. The real-time sensor pressure and the steady-state flow velocity corresponding to the monitoring point are substituted into a preset correction formula to calculate the corresponding pressure correction coefficient. Finally, the corrected pressure value for each subspace is obtained based on the pressure correction coefficient and the pressure value of each subspace. By performing equal-volume segmentation on the aircraft's interior, the volume of each subspace is constant under normal circumstances. When a gas leak occurs in one of the subspaces, the gas flow within that subspace fluctuates. By analyzing the gas flow information in the subspace, the pressure is corrected, resulting in accurate calculation of the subspace's pressure information and pressure change information.

[0141] According to an embodiment of the present invention, the internal pressure information of the aircraft is compared with the preset pressure information to obtain pressure difference information, and the pressure difference information is input into a preset gas leakage model to output gas leakage information, specifically:

[0142] Acquiring aircraft internal pressure information at adjacent time nodes to obtain first pressure information and second pressure information;

[0143] By comparing the first pressure information and the second pressure information with the preset pressure information respectively, first pressure difference information and second pressure difference information are obtained;

[0144] Inputting the first pressure difference information and the second pressure difference information into the gas leakage model respectively to obtain first gas leakage information and second gas leakage information;

[0145] Subtracting the first gas leakage information from the second gas leakage information, and performing absolute value calculation to obtain difference information;

[0146] The aircraft decompression rate is calculated based on the difference information, and the aircraft decompression status information is generated based on the aircraft decompression rate.

[0147] It should be noted that, as an implementation method, the pressure relief state analysis adopts a time series comparison architecture, stores pressure snapshots according to a preset monitoring period, and selects the pressure information of two consecutive time windows as data packets. The difference between the two pressure information and the set standard pressure information is calculated respectively to obtain the corresponding two pressure difference data. The two pressure difference data are input into the preset gas leakage model, and two leakage flow values ​​are output. The absolute value of the difference between the two leakage flow values ​​is calculated as the flow difference information to calculate the aircraft pressure relief rate. The pressure relief state of the aircraft is judged according to the pressure relief rate, wherein the pressure relief state includes normal fluctuations, slow leakage and extreme pressure loss. In this embodiment, by judging the changes in the internal pressure of the aircraft at adjacent time nodes, the gas leakage information is accurately analyzed, and the pressure relief rate of the aircraft is calculated. The pressure relief state of the aircraft is calculated by the pressure relief rate, and the calculation result is more accurate.

[0148] According to an embodiment of the present invention, after calculating the aircraft decompression rate based on the difference information and generating aircraft decompression state information based on the aircraft decompression rate, the method further includes:

[0149] Obtain aircraft decompression status information;

[0150] Comparing the aircraft decompression state information with preset state information to obtain a decompression state deviation rate;

[0151] Determine whether the pressure relief state deviation rate is greater than or equal to a preset deviation rate threshold;

[0152] If it is greater than or equal to, an alarm message is generated and an alarm is issued for the aircraft decompression state according to the alarm message;

[0153] If it is less than, the aircraft decompression status will be detected in real time.

[0154] It should be noted that the real-time decompression status is compared with the preset status to calculate the decompression status deviation rate, and a threshold is used to determine whether to activate an alarm. If the deviation rate is greater than or equal to the preset safety threshold, an emergency response is triggered, including but not limited to disconnecting non-critical circuits, releasing emergency oxygen, and recording black box codes. If the deviation rate is less than the preset safety threshold, the decompression status is continuously recorded. In this embodiment, the decompression status of the aircraft is determined. When the decompression status shows a significant deviation, it indicates an emergency situation. At this time, an alarm for the aircraft decompression status needs to be issued, thereby enabling a faster response, rapid maintenance, and improved aircraft safety.

[0155] According to an embodiment of the present invention, the components of the leaked gas are decomposed according to the gas leakage information, and oxygen leakage information is obtained, specifically:

[0156] Obtain gas leakage information and decompose the leaked gas into components to obtain the proportion information of each component;

[0157] Calculate the concentration information of each component according to the proportion information of each component, and filter according to the concentration information of each component to obtain the oxygen leakage concentration information;

[0158] Compare the oxygen leakage concentration information with the preset concentration information to obtain the concentration change rate;

[0159] Determining whether the concentration deviation rate is greater than or equal to a preset deviation rate threshold;

[0160] If it is greater than or equal to, oxygen leakage information is obtained;

[0161] If it is less than, it is determined that the leaked gas is within the normal error range.

[0162] It should be noted that, as an implementation method, dual-channel analysis is used to verify oxygen leakage. The main channel uses mass spectrometry: the leaked gas is introduced into the ionization chamber through a capillary tube, and the oxygen ion intensity ratio is measured by magnetic field deflection to calculate the oxygen mole fraction. The auxiliary channel uses TDLAS technology: a near-infrared laser penetrates the gas chamber, and the O2 absorption spectrum is inverted through the HITRAN database to output the oxygen concentration value. The real-time concentration change rate is obtained by comparing the oxygen concentration with the preset marked concentration; if the concentration change rate is greater than or equal to the preset deviation rate threshold, it is determined to be an oxygen leak; otherwise, it is determined to be within the normal measurement error range. By decomposing the leaked gas into components, the component ratio in the leaked gas is analyzed, and the concentration information of each component is calculated, so that the oxygen leakage concentration can be analyzed more accurately and whether the oxygen leakage concentration is within the normal error range can be determined. If the error is large, the oxygen leakage information is identified and judged.

[0163] According to an embodiment of the present invention, the further embodiment includes:

[0164] Obtain the oxygen leakage concentration at adjacent time nodes, perform difference calculation on the oxygen leakage concentration at adjacent time nodes, and obtain the oxygen leakage rate;

[0165] Determining whether the oxygen leakage rate is greater than or equal to a preset leakage rate threshold;

[0166] If it is greater than or equal to, it is determined that the oxygen leakage is fast, and a first alarm message is generated to issue a real-time alarm for the oxygen leakage information;

[0167] If it is less than, it is determined that the oxygen leakage is slow, and a second alarm message is generated to issue a real-time alarm for the oxygen leakage information.

[0168] It should be noted that, as an implementation method, the core of the leakage rate graded alarm lies in the time domain differential processing. The oxygen concentration value is recorded according to the preset processing cycle, and the instantaneous leakage rate is calculated based on the concentration difference through the five-point differential formula. When the leakage rate is greater than or equal to the set threshold, a red full-screen alarm is triggered and emergency oxygen is released. When the leakage rate is less than the set threshold, a yellow pop-up prompt is triggered and a broadcast prompt is issued. By judging the oxygen leakage rate and performing different types of alarms, the oxygen leakage rate is distinguished by the first alarm information and the second alarm information to improve the alarm differentiation. The first alarm information and the second alarm information can be distinguished by the frequency of the alarm or the volume of the alarm.

[0169] According to an embodiment of the present invention, the further embodiment includes:

[0170] Real-time collection of aircraft extravehicular environmental parameters, including temperature, humidity, flight altitude, and body vibration spectrum;

[0171] Obtaining disturbance factor information based on the external environment parameters and a preset disturbance factor relationship;

[0172] If the disturbance factor information is greater than a preset disturbance factor threshold, the model accuracy is verified by periodically injecting tracer gas.

[0173] It should be noted that the disturbance factor relationship is:

[0174] λ=k1△T+k2△H+k3A v , where λ is the disturbance factor, k1, k2, k3 are calibration coefficients, △T is the temperature difference between inside and outside the cabin, △H is the height difference, A v =vibration energy. When the disturbance factor exceeds a preset threshold, the calibration process is activated. By injecting a trace amount of tracer gas into the chamber every 5 minutes, the model's predicted leak location is compared with the actual sensor response location, enabling model validation and calibration.

[0175] According to an embodiment of the present invention, the further embodiment includes:

[0176] Oxygen leak level and remaining flight time;

[0177] When it is determined that the oxygen leakage is slow, the mission can be continued or an emergency return can be triggered based on the relationship between the remaining flight time and the preset safety flight threshold.

[0178] It should be noted that, as an implementation method, when the oxygen leakage is slow and the remaining flight time exceeds 30 minutes, the aircraft is allowed to continue to perform the current mission to ensure the mission completion rate; if the remaining flight time does not exceed 30 minutes, the emergency return operation is triggered after the heading is corrected and the aircraft climbs to a safe altitude to reduce the accident rate of the aircraft.

[0179] A third aspect of the present invention provides a computer-readable storage medium, which includes an unmanned aircraft oxygen leak detection method program. When the unmanned aircraft oxygen leak detection method program is executed by a processor, the steps of any of the above-mentioned unmanned aircraft oxygen leak detection methods are implemented.

[0180] The present invention discloses an unmanned aircraft oxygen leak detection method, system and medium, which obtain aircraft internal pressure information; compare the aircraft internal pressure information with preset pressure information to obtain pressure difference information; input the pressure difference information into a preset gas leakage model to output gas leakage information; decompose the leaked gas into components based on the gas leakage information and obtain oxygen leakage information; transmit the oxygen leakage information to a terminal in a predetermined manner; analyze the pressure relief state of the aircraft internal space based on the change in the aircraft internal pressure, identify and judge the gas leakage by judging the pressure relief state, and thus analyze the oxygen leakage according to the components of the leaked gas, thereby more accurately detecting oxygen leakage in the aircraft.

[0181] In the several embodiments provided in this application, it should be understood that the disclosed devices and methods can be implemented in other ways. The device embodiments described above are merely schematic. For example, the division of units is merely a logical function division. In actual implementation, there may be other division methods, 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.

[0182] 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 across multiple network units; some or all of the units may be selected according to actual needs to achieve the purpose of the scheme of this embodiment.

[0183] 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.

[0184] Those skilled in the art will understand that all or part of the steps of the above-mentioned method embodiment 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-mentioned method embodiment; and the aforementioned storage medium includes: mobile storage devices, read-only memory (ROM), random access memory (RAM), magnetic disk or optical disk, etc. Various media that can store program codes.

[0185] Alternatively, if the above-mentioned integrated unit of the present invention is implemented in the form of a software functional 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, or the part that contributes to the prior art, can be embodied in the form of a software product, which is stored in a storage medium and includes a number of instructions for enabling a computer device (which can be a personal computer, server, or 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. A method for detecting oxygen leakage in an unmanned aerial vehicle, characterized in that: include: Obtain aircraft internal pressure information; Compare the internal pressure information of the aircraft with the preset pressure information to obtain pressure difference information; Input the pressure difference information into the preset gas leakage model and output the gas leakage information; Decompose the components of the leaked gas according to the gas leakage information and obtain oxygen leakage information; The oxygen leakage information is transmitted to the terminal in a predetermined manner.

2. The unmanned aerial vehicle oxygen leak detection method according to claim 1, characterized in that: After obtaining the internal pressure information of the aircraft, the method further includes: Obtaining the internal pressure information of the aircraft, and spatially dividing the internal pressure information of the aircraft to obtain pressure information of a plurality of subspaces; Compare the pressure information of adjacent subspaces to obtain the pressure deviation rate; Determining whether the pressure deviation rate is greater than or equal to a preset deviation rate threshold; If it is greater than or equal to, it is determined that the corresponding subspace pressure is abnormal; If it is less than, it is determined that the corresponding subspace pressure is normal.

3. The unmanned aerial vehicle oxygen leak detection method according to claim 1, characterized in that: The obtaining of the aircraft internal pressure information and spatially dividing the aircraft internal pressure information to obtain a plurality of sub-space pressure information specifically includes: Obtain aircraft parameter information and divide the interior space of the aircraft into equal volumes to form several subspaces; Obtaining gas flow information of several subspaces and generating a pressure correction coefficient based on the gas flow information; The pressure correction coefficient is multiplied by the internal pressure information of the aircraft to obtain the pressure information of several subspaces.

4. The unmanned aerial vehicle oxygen leak detection method according to claim 3, characterized in that: The aircraft internal pressure information is compared with the preset pressure information to obtain pressure difference information, the pressure difference information is input into the preset gas leakage model, and the gas leakage information is output, specifically: Acquiring aircraft internal pressure information at adjacent time nodes to obtain first pressure information and second pressure information; By comparing the first pressure information and the second pressure information with the preset pressure information respectively, first pressure difference information and second pressure difference information are obtained; Inputting the first pressure difference information and the second pressure difference information into the gas leakage model respectively to obtain first gas leakage information and second gas leakage information; Subtracting the first gas leakage information from the second gas leakage information, and performing absolute value calculation to obtain difference information; The aircraft decompression rate is calculated based on the difference information, and the aircraft decompression status information is generated based on the aircraft decompression rate.

5. The unmanned aerial vehicle oxygen leak detection method according to claim 4, characterized in that: After calculating the aircraft decompression rate based on the difference information and generating aircraft decompression status information based on the aircraft decompression rate, the method further includes: Obtain aircraft decompression status information; Comparing the aircraft decompression state information with preset state information to obtain a decompression state deviation rate; Determining whether the pressure relief state deviation rate is greater than or equal to a preset deviation rate threshold; If it is greater than or equal to, an alarm message is generated and an alarm is issued for the aircraft decompression state according to the alarm message; If it is less than, the aircraft decompression status will be detected in real time.

6. The unmanned aerial vehicle oxygen leak detection method according to claim 5, characterized in that: The components of the leaked gas are decomposed according to the gas leakage information, and the oxygen leakage information is obtained, specifically: Obtain gas leakage information and decompose the leaked gas into components to obtain the proportion information of each component; Calculate the concentration information of each component according to the proportion information of each component, and filter according to the concentration information of each component to obtain the oxygen leakage concentration information; Compare the oxygen leakage concentration information with the preset concentration information to obtain the concentration change rate; Determining whether the concentration deviation rate is greater than or equal to a preset deviation rate threshold; If it is greater than or equal to, oxygen leakage information is obtained; If it is less than, it is determined that the leaked gas is within the normal error range.

7. An unmanned aerial vehicle oxygen leak detection system, characterized in that: The system includes: a memory and a processor, wherein the memory includes a program of an unmanned aircraft oxygen leak detection method, and when the program of the unmanned aircraft oxygen leak detection method is executed by the processor, the following steps are implemented: Obtain aircraft internal pressure information; Compare the internal pressure information of the aircraft with the preset pressure information to obtain pressure difference information; Input the pressure difference information into the preset gas leakage model and output the gas leakage information; Decompose the components of the leaked gas according to the gas leakage information and obtain oxygen leakage information; The oxygen leakage information is transmitted to the terminal in a predetermined manner.

8. The unmanned aerial vehicle oxygen leak detection system according to claim 7, characterized in that: After obtaining the internal pressure information of the aircraft, the method further includes: Obtaining the internal pressure information of the aircraft, and spatially dividing the internal pressure information of the aircraft to obtain pressure information of a plurality of subspaces; Compare the pressure information of adjacent subspaces to obtain the pressure deviation rate; Determining whether the pressure deviation rate is greater than or equal to a preset deviation rate threshold; If it is greater than or equal to, it is determined that the corresponding subspace pressure is abnormal; If it is less than, it is determined that the corresponding subspace pressure is normal.

9. The unmanned aerial vehicle oxygen leak detection system according to claim 8, characterized in that: The obtaining of the aircraft internal pressure information and spatially dividing the aircraft internal pressure information to obtain a plurality of sub-space pressure information specifically includes: Obtain aircraft parameter information and divide the interior space of the aircraft into equal volumes to form several subspaces; Obtaining gas flow information of several subspaces and generating a pressure correction coefficient based on the gas flow information; The pressure correction coefficient is multiplied by the internal pressure information of the aircraft to obtain the pressure information of several subspaces.

10. A computer-readable storage medium, characterized in that The computer-readable storage medium includes an unmanned aerial vehicle oxygen leak detection method program, and when the unmanned aerial vehicle oxygen leak detection method program is executed by a processor, the steps of the unmanned aerial vehicle oxygen leak detection method according to any one of claims 1 to 6 are implemented.

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