An aviation safety management monitoring system

Abstract

An aviation safety management monitoring system belongs to the technical field of aviation safety, and the temperature value and the intake air pressure value of the aviation engine in the continuous rotation period in each flight period change with time equation; according to the temperature value and the intake air pressure value of the aviation engine in the continuous rotation period in each flight period change with time equation, the abnormal amplitude of the intake air pressure in each flight period is obtained; according to the abnormal amplitude of the intake air pressure in all flight periods in the predefined time length, a plurality of abnormal amplitude queues are constructed; combined with other methods, the problem can be found out as soon as possible through real-time data detection, and the probability of the intake air leakage of the aviation engine can be evaluated in advance without performing the disassembly of the aviation engine.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation safety, and in particular relates to an aviation safety management and monitoring system. Background Art

[0002] Aviation safety is to ensure that there are no accidents related to aircraft operations, such as casualties and damage to aircraft. Aviation safety mainly includes flight safety, aviation ground safety and air defense safety.

[0003] In terms of aviation safety management, there is currently a control system and control method for tapping the acceleration potential of aircraft engines, as mentioned in patent publication number "CN103452674B", to perform engine safety management and monitoring in aviation safety. Specifically, the aircraft engine is equipped with a speed sensor, a temperature sensor, and an air pressure sensor connected to a full-authority digital electronic controller. The full-authority digital electronic controller controls the aircraft engine via a solenoid valve assembly based on the speed, temperature, and intake pressure values ​​of the aircraft engine respectively transmitted by the speed sensor, temperature sensor, and air pressure sensor, in combination with an optimal control strategy, thereby achieving safe management of the aircraft engine via the solenoid valve assembly.

[0004] However, such a function of safely managing aircraft engines through solenoid valve components is still too simple. At present, there is also real-time detection of aircraft engine malfunctions based on the aircraft engine's speed, temperature and intake pressure values. The malfunction mode is often determined by analyzing the aircraft engine's speed, temperature and intake pressure values. However, the accuracy and reliability of the analysis method of the aircraft engine's speed, temperature and intake pressure values ​​are affected by several factors, such as the levels of the aircraft engine's speed, temperature and intake pressure values, the complexity of the analysis method of the aircraft engine's speed, temperature and intake pressure values, the method selection, etc. In complex and multi-state aircraft engine operation scenarios, such factors often cause the analysis values ​​of the aircraft engine's speed, temperature and intake pressure values ​​to be incorrect or misidentified, thereby weakening the accuracy of real-time malfunction detection of aircraft engine operation information. Summary of the Invention

[0005] In order to solve the defects in the existing technology, the present invention provides an aviation safety management and monitoring system, which obtains the temperature value in the continuous rotation period of each flight period and the change equation of the intake air pressure value of the aircraft engine with time in a pre-defined time period; obtains the abnormal amplitude of the intake duct air pressure in each flight period based on the change equation of the temperature value in the continuous rotation period of each flight period and the intake air pressure value at the aircraft engine with time; constructs multiple abnormal amplitude queues based on the abnormal amplitude of the intake duct air pressure in all flight periods within the pre-defined time period; and constructs multiple abnormal amplitude queues based on the abnormal amplitude of each abnormal amplitude queue. The abnormal amplitude of the inlet pressure in each flight period in each adjacent decrement queue and each abnormal amplitude queue are used to obtain the probability that the abnormal amplitude of the inlet pressure meets the increase of the division level in the pre-defined time period; based on the probability that the abnormal amplitude of the inlet pressure meets the increase of the division level in the pre-defined time period and the abnormal amplitude of the inlet pressure in each flight period, the detection value of the real-time abnormality detection of the operation information of the aircraft engine is obtained, and the problem is found as soon as possible through real-time data detection. Without disassembling the aircraft engine, the probability of leakage in the aircraft engine's air intake can be evaluated in advance.

[0006] The present invention utilizes the following technical solutions.

[0007] An aviation safety management and monitoring method, comprising:

[0008] The full-authority digital electronic controller controls the aircraft engine via the solenoid valve assembly based on the aircraft engine speed, temperature, and intake air pressure values ​​received from the speed sensor, temperature sensor, and air pressure sensor, respectively, and incorporating an optimal control strategy. The aircraft engine speed, temperature, or intake air pressure value is the aircraft engine operating information.

[0009] The full authority digital electronic controller also executes the following method based on the aircraft engine speed value, temperature value and intake air pressure value received from the speed sensor, temperature sensor and air pressure sensor respectively:

[0010] Step 1: Obtaining a time-varying equation for the temperature and intake pressure of the aircraft engine during continuous rotation periods within each flight period of the aircraft engine within a predetermined time period.

[0011] Step 2: Obtain the abnormal amplitude of the aircraft engine's intake pressure during each flight period based on the equation representing the temperature value during the continuous rotation period of the aircraft engine and the intake pressure value at the aircraft engine as a function of time.

[0012] Step 3: Based on the abnormal amplitudes of the inlet pressure during all flight periods within a predefined duration, multiple abnormal amplitude queues are constructed; based on the values ​​in the adjacent decrement queues of each abnormal amplitude queue and the abnormal amplitudes of the inlet pressure during each flight period within each abnormal amplitude queue, the probability that the abnormal amplitude of the inlet pressure during the predefined duration meets the increased level of the division level is obtained;

[0013] In step 4, based on the probability of the intake pressure abnormal amplitude meeting the increased level of the division within a predefined time period and the abnormal amplitude of the intake pressure during each flight period, the detection value of the aircraft engine operation information real-time abnormality detection is obtained.

[0014] Furthermore, the predefined flight period of the aircraft engine is U;

[0015] During the predefined registration time, the least square method is used to obtain the fitting line and the variation equation g of the intake air pressure value of the aircraft engine during the continuous rotation period of each flight period. y (u), where u is the value of the X-axis of the rectangular coordinate system where the fitting line is located, and the value of the Y-axis of the rectangular coordinate system where the fitting line is located is the intake pressure value.

[0016] Furthermore, the predefined duration is the total duration of the twenty flight periods.

[0017] Furthermore, taking the yth flight period as an example, the calculation equation for the correlation factor of the total air pressure and temperature values ​​in the yth flight period is:

[0018]

[0019] Here, L y Represents the correlation factor of the total pressure and temperature values ​​during the flight period of flight y, b y represents the continuous rotation period in the flight period of the yth flight, g y (u) represents the equation of variation of the intake air pressure value at the aircraft engine during the continuous rotation period of the yth flight period, M y Represents the temperature value during the continuous rotation period during the flight period of flight y.

[0020] Furthermore, the average of the correlation factors of the total air pressure and temperature values ​​in the flight periods of all flights in the previous pre-defined time period in the current pre-defined time period is defined as the benchmark correlation factor in the pre-defined time period.

[0021] Furthermore, a normalized value obtained by subtracting a baseline correlation factor within a predefined time period from a correlation factor of the total air pressure and temperature values ​​during the yth flight period is defined as the abnormal amplitude of the inlet air pressure during the yth flight period.

[0022] Furthermore, the adjacent decrement queue of the abnormal amplitude queue is a queue formed by subtracting the previous element from each subsequent element in the abnormal amplitude queue.

[0023] Furthermore, Step 3 includes: defining the abnormal amplitude of the inlet duct air pressure from the first flight period to the last flight period in the pre-defined time as the first abnormal amplitude queue; defining the abnormal amplitude of the inlet duct air pressure from the second flight period to the end of the last flight period in the pre-defined time as the second abnormal amplitude queue; similarly obtaining the T"th abnormal amplitude queue composed of the abnormal amplitude of the inlet duct air pressure from the T"th flight period to the end of the last flight period in the pre-defined time;

[0024] Obtain the adjacent decrement queue of each abnormal amplitude queue;

[0025] Calculate the probability of abnormal amplitude queues meeting the level increase separately;

[0026] Then the probability that the jth abnormal amplitude queue meets the level increase is:

[0027]

[0028] Here, Q j represents the probability that the jth abnormal amplitude queue meets the level increase, Representatives use the Z-score method to Perform dimensionless transformation, T j represents the standard deviation of the elements in the adjacent decrement queue of the jth abnormal amplitude queue, L j F represents the number of abnormal amplitudes of the inlet pressure during the entire flight period of the jth abnormal amplitude queue, j，L F represents the abnormal amplitude of the inlet pressure during the Lth flight period in the jth abnormal amplitude queue, j，L -1 represents the abnormal amplitude of the inlet pressure during the L-1th flight period in the jth abnormal amplitude queue;

[0029] Based on this, we can obtain the probability that the entire abnormal amplitude queue meets the level increase;

[0030] Therefore, the specific calculation equation for the probability that the amplitude of the intake duct pressure abnormality meets the increase in the division level within the predefined time period is:

[0031]

[0032] Here, Q' represents the probability that the amplitude of the intake pressure abnormality meets the increased level of the division within a predefined time period, Q j represents the probability that the jth abnormal amplitude queue meets the level increase, T” is the predefined number of critical quantities, Q zg Represents the highest amount of probability among all abnormal amplitude queues that meet the increased level.

[0033] Furthermore, the predefined number threshold is fifteen.

[0034] Furthermore, the calculation equation for the probability of leakage in the intake duct of an aircraft engine is:

[0035]

[0036] Here, R represents the probability that the engine's inlet will leak, Q' represents the probability that the inlet pressure abnormality amplitude meets the division level increase within a predefined time, T' is the number of flight periods within a predefined time, and F y represents the abnormal amplitude of the inlet pressure during the flight period of flight y, Representatives use the Z-score method to Perform dimensionless transformation.

[0037] Furthermore, Step 4 also includes: pre-defining a critical value, and when the probability of leakage in the intake duct of the aircraft engine is higher than the pre-defined critical value, indicating that the operation information of the aircraft engine is abnormal.

[0038] An aviation safety management and monitoring system, comprising:

[0039] The aircraft engine is provided with a speed sensor, a temperature sensor, and an air pressure sensor connected to a full authority digital electronic controller. The full authority digital electronic controller is used to control the aircraft engine via a solenoid valve assembly based on the speed, temperature, and intake air pressure values ​​received from the speed sensor, temperature sensor, and air pressure sensor, respectively, and in combination with an optimal control strategy.

[0040] Modules running on a full authority digital electronic controller include:

[0041] a variation module for obtaining a variation equation for the temperature and intake pressure of the aircraft engine during a continuous rotation period of the aircraft engine within each flight period of the aircraft engine within a predefined time period, as the temperature and intake pressure of the aircraft engine change over time;

[0042] an abnormality module for obtaining an abnormal amplitude of the intake pressure of the aircraft engine during each flight period based on an equation representing a temperature value during a continuous rotation period of the aircraft engine and an intake pressure value at the aircraft engine as a function of time;

[0043] A probability module is used to construct multiple abnormal amplitude value queues based on the abnormal amplitude values ​​of the inlet pressure during all flight periods within a predefined duration; and to obtain the probability that the abnormal amplitude value of the inlet pressure during the predefined duration meets the increased level of the division level based on the values ​​in the adjacent decrement queues of each abnormal amplitude value queue and the abnormal amplitude value of the inlet pressure during each flight period within each abnormal amplitude value queue;

[0044] The detection module is used to obtain the detection value of the aircraft engine operation information for real-time abnormality detection based on the probability that the abnormal amplitude of the intake duct pressure meets the increased level of the division level within a pre-defined time period and the abnormal amplitude of the intake duct pressure during each flight period.

[0045] The beneficial effect of the present invention is that, compared with the prior art, the present invention obtains the temperature value in the continuous rotation period in each flight period of a predefined duration and the change equation of the intake air pressure value of the aircraft engine along with time; based on the temperature value in the continuous rotation period in each flight period and the change equation of the intake air pressure value at the aircraft engine along with time, the abnormal amplitude of the intake air pressure in each flight period is obtained; it is based on the leading numerical sampling method and the most efficient method to change the numerical value into an intake air pressure value fitting line with good experience, which not only ensures the accuracy and completeness of the numerical value, but also greatly improves the speed and accuracy of the numerical analysis, and provides great support for the immediate detection and overcoming of hidden air pressure abnormality problems, and constructs multiple abnormal amplitude queues based on the abnormal amplitude of the intake air pressure in all flight periods of a predefined duration. ; According to each value in the adjacent decrement queue of each abnormal amplitude queue and the abnormal amplitude of the inlet duct air pressure in each flight period in each abnormal amplitude queue, the probability of the abnormal amplitude of the inlet duct air pressure meeting the increase of the division level in a pre-defined time period is obtained; by adding the adjacent decrement queue, the changing trend of the abnormal amplitude of the inlet duct air pressure, especially the situation of the increase of the division level, is grasped, which further improves the accuracy of the detection value of the real-time abnormal detection of the operation information of the aircraft engine. According to the probability of the abnormal amplitude of the inlet duct air pressure meeting the increase of the division level in a pre-defined time period and the abnormal amplitude of the inlet duct air pressure in each flight period, the detection value of the real-time abnormal detection of the operation information of the aircraft engine is obtained, thereby detecting defects as soon as possible through real-time data detection, and estimating the probability of leakage in the intake duct of the aircraft engine in advance without performing the division into aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 This is a partial flow chart of the aviation safety management and monitoring method described in the present invention;

[0047] Figure 2 It is a schematic diagram of the module structure of the aviation safety management and monitoring system described in the present invention. DETAILED DESCRIPTION

[0048] To make the objectives, technical solutions, and advantages of the present invention more clear, the following will be combined with the accompanying drawings in the embodiments of the present invention to clearly and completely express the technical solutions of the present invention. The embodiments expressed in this application are only part of the embodiments of the present invention, not all of the embodiments. Based on the spirit of the present invention, other embodiments obtained by ordinary technicians in this field without making creative work are all within the scope of protection of the present invention.

[0049] like Figure 1 As shown, the aviation safety management and monitoring method of the present invention includes:

[0050] The full-authority digital electronic controller controls the aircraft engine via the solenoid valve assembly based on the aircraft engine speed, temperature, and intake air pressure values ​​received from the speed sensor, temperature sensor, and air pressure sensor, respectively, and combines this with an optimal control strategy. The aircraft engine speed, temperature, or intake air pressure values ​​represent the aircraft engine's operating information, thereby enabling safe management of the aircraft engine via the solenoid valve assembly.

[0051] The full authority digital electronic controller also executes the following method based on the aircraft engine speed value, temperature value and intake air pressure value received from the speed sensor, temperature sensor and air pressure sensor respectively:

[0052] Step 1: Obtaining a time-varying equation for the temperature and intake pressure of the aircraft engine during continuous rotation periods within each flight period of the aircraft engine within a predetermined time period.

[0053] In a preferred but non-limiting embodiment of the present invention, the predefined flight period of the aircraft engine is U;

[0054] During the predefined registration time, the least square method is used to obtain the fitting line and the variation equation g of the intake air pressure value of the aircraft engine during the continuous rotation period of each flight period. y(u) (the change equation is the fitting equation corresponding to the fitting line), where u is the value of the X-axis of the rectangular coordinate system where the fitting line is located, and the value of the Y-axis of the rectangular coordinate system where the fitting line is located is the intake pressure value, that is, the change of u is from the intake start time zero to the intake end time of the aircraft engine in each flight period, and the value of the Y-axis of the rectangular coordinate system where the fitting line is located is the intake pressure value of the aircraft engine at each time.

[0055] In a preferred but non-limiting embodiment of the present invention, the predefined duration is the total duration of twenty flight periods.

[0056] Step 2: Obtain the abnormal amplitude of the aircraft engine's intake pressure during each flight period based on the equation representing the temperature value during the continuous rotation period of the aircraft engine and the intake pressure value at the aircraft engine as a function of time.

[0057] Under normal conditions, the higher the temperature, the higher the intake volume. At this time, the temperature and the intake volume are positively correlated with each other, and the intake volume is determined by the continuous rotation period and the air pressure delivered from the intake duct of the aircraft engine. The longer the continuous rotation period, the higher the intake volume; the higher the air pressure delivered from the intake duct, the higher the intake pressure value at the aircraft engine. The higher the speed of the aircraft engine, the higher the intake volume in one section. Therefore, the intake pressure value at the aircraft engine is positively correlated with the continuous rotation period and the temperature value. Under normal conditions, the quotient obtained by dividing the intake pressure value by the temperature value is a constant.

[0058] In the fitting equation of the intake pressure value of the aircraft engine along with time, the intake pressure value at the aircraft engine and the continuous rotation period can be represented by the pressure change equation and the size of the area enclosed by the X-axis, representing the total pressure during the continuous intake period. First, the correlation factor of the total pressure and the temperature value is calculated. When the correlation factor exceeds the set reference value range, the amplitude of the intake duct pressure abnormality is higher.

[0059] In a preferred but non-limiting embodiment of the present invention, taking the yth flight period as an example, the calculation equation for the correlation factor of the total air pressure and temperature values ​​in the yth flight period is:

[0060]

[0061] Here, L y Represents the correlation factor of the total pressure and temperature values ​​during the flight period of flight y, b y represents the continuous rotation period in the flight period of the yth flight, g y (u) represents the equation of variation of the intake air pressure value at the aircraft engine during the continuous rotation period of the yth flight period, M yRepresents the temperature value during the continuous rotation period during the flight period of flight y.

[0062] and Represents the total intake air pressure value at the aircraft engine. The total intake air pressure value is related to the intake air volume. The higher the total intake air pressure value, the higher the intake air volume. Represents the correlation factor between the total air pressure and temperature values. This quantity is a constant under normal conditions. When this quantity shows an error during the yth flight period, it means that the inlet pressure is abnormal.

[0063] According to the above method, the correlation factor of the total air pressure and temperature values ​​in all flight periods in the previous pre-defined time period in the current pre-defined time period can be obtained.

[0064] In a preferred but non-limiting embodiment of the present invention, the average of the correlation factors of the total air pressure and temperature values ​​in the flight periods of all flights in the previous pre-defined time period in the current pre-defined time period is defined as the baseline correlation factor in the pre-defined time period.

[0065] In a preferred but non-limiting embodiment of the present invention, a normalized value obtained by subtracting a baseline correlation factor within a predetermined time period from the correlation factor of the total pressure and temperature values ​​during the yth flight period is defined as the magnitude of the inlet pressure aberration during the yth flight period. Here, the Z-score method is used to obtain the normalized value of this subtraction.

[0066] Step 3: Based on the abnormal amplitudes of the inlet pressure during all flight periods within a predefined duration, multiple abnormal amplitude queues are constructed; based on the values ​​in the adjacent decrement queues of each abnormal amplitude queue and the abnormal amplitudes of the inlet pressure during each flight period within each abnormal amplitude queue, the probability that the abnormal amplitude of the inlet pressure during the predefined duration meets the increased level of the division level is obtained;

[0067] In a preferred but non-limiting embodiment of the present invention, the adjacent decrement queue of the abnormal amplitude queue is a queue formed by subtracting the previous element from each subsequent element in the abnormal amplitude queue.

[0068] Relying solely on the amplitude of the intake pressure disturbance during the current intake period cannot determine whether the intake pressure is abnormal. Just like when the turbocharger of an aircraft engine's boost is unstable, the intake pressure will also be low. In this case, the probability of leakage in the aircraft engine's intake duct must be calculated based on the pressure disturbance distribution.

[0069] When the inlet passage of an aero-engine presents a small hole, the inlet passage air tightness is poor, the inlet passage air pressure is weakened, and often causes the inlet passage air pressure to be abnormal. In the future, the inlet passage air tightness is often poor, that is, during multiple inlets, the inlet passage air pressure abnormality often presents a level increase in some areas. At this time, the inlet passage of the present aero-engine often presents leakage.

[0070] In the preferred but non-limiting embodiment of the present application, Step 3 comprises: defining the abnormality amplitudes of the inlet passage air pressure in the first flight period to the last flight period in the predefined time length as the first abnormality amplitude queue; defining the abnormality amplitudes of the inlet passage air pressure in the second flight period to the last flight period in the predefined time length as the second abnormality amplitude queue; and similarly obtaining the Tth abnormality amplitude queue composed of the abnormality amplitudes of the inlet passage air pressure in the Tth flight period to the last flight period in the predefined time length.

[0071] In the preferred but non-limiting embodiment of the present application, the number of critical quantities is fifteen.

[0072] Obtaining the adjacent decrement queue of each abnormality amplitude queue.

[0073] Respectively calculating the probability of the abnormality amplitude queue meeting the level increase. Here, the queue meeting the level increase represents that the abnormality amplitude of the inlet passage air pressure meets the partial level increase, which meets the characteristics of the poor inlet passage air tightness, and the probability of the aero-engine inlet passage presenting leakage is higher.

[0074] Taking the jth abnormality amplitude queue, the probability of the jth abnormality amplitude queue meeting the level increase is:

[0075]

[0076] Here, Q j represents the probability of the jth abnormality amplitude queue meeting the level increase, represents the use of the Z-score method on performs non-dimensionalization, T j represents the standard deviation of the elements in the adjacent decrement queue of the jth abnormality amplitude queue, L j represents the number of abnormality amplitudes of the inlet passage air pressure in all flight periods of the jth abnormality amplitude queue, F j，L represents the abnormality amplitude of the inlet passage air pressure in the Lth flight period in the jth abnormality amplitude queue, F j，L -1 represents the abnormality amplitude of the inlet passage air pressure in the L-1th flight period in the jth abnormality amplitude queue;

[0077] And Represents the average of the elements in the adjacent decrement queues of the j-th abnormal amplitude queue. The higher the average, the higher the probability that the j-th abnormal amplitude queue meets the level increase. j Represents the standard deviation of the adjacent reduction queues of the j-th abnormal amplitude queue. The lower the standard deviation, the higher the probability that the j-th abnormal amplitude queue meets the level increase.

[0078] According to the above method, the probability of the entire abnormal amplitude queue meeting the level increase is obtained;

[0079] Therefore, the specific calculation equation for the probability that the amplitude of the intake duct pressure abnormality meets the increase in the division level within the predefined time period is:

[0080]

[0081] Here, Q' represents the probability that the amplitude of the intake pressure abnormality meets the increased level of the division within a predefined time period, Q j represents the probability that the jth abnormal amplitude queue meets the level increase, T” is the predefined number of critical quantities, Q zg Represents the highest amount of probability among all abnormal amplitude queues that meet the increased level.

[0082] and It represents the average probability that the entire abnormal amplitude queue meets the increased level. The higher the average probability, the higher the probability that the abnormal amplitude of the intake duct pressure meets the increased level of the distribution within the pre-defined time period.

[0083] In step 4, based on the probability of the intake pressure abnormal amplitude meeting the increased level of the division within a predefined time period and the abnormal amplitude of the intake pressure during each flight period, the detection value of the aircraft engine operation information real-time abnormality detection is obtained.

[0084] The above method calculates the probability that the amplitude of the intake duct air pressure disturbance within a predefined time period conforms to the increase in the distribution level. The higher the probability, the more it conforms to the characteristic of the deterioration of the intake duct air tightness. Then, the higher the probability that the intake duct of the aircraft engine will leak in the future period. Moreover, the higher the amplitude of the intake duct air pressure disturbance within the predefined time period, the higher the probability that the intake duct of the aircraft engine will leak in the future period.

[0085] In a preferred but non-limiting embodiment of the present invention, the equation for the probability of leakage in the intake duct of an aircraft engine is:

[0086]

[0087] Here, R represents the probability that the engine's inlet will leak, Q' represents the probability that the inlet pressure abnormality amplitude meets the division level increase within a predefined time, T' is the number of flight periods within a predefined time, and F y represents the abnormal amplitude of the inlet pressure during the flight period of flight y, Representatives use the Z-score method to Perform dimensionless transformation.

[0088] and It represents the average of the amplitude of the abnormal pressure in the air intake during the entire flight period. The higher the average is and the more it conforms to the characteristics of increasing division levels, the higher the probability that the air intake of the aircraft engine will leak.

[0089] In a preferred but non-limiting embodiment of the present invention, Step 4 further includes: pre-defining a critical value, and when the probability of leakage in the intake duct of the aircraft engine is higher than the pre-defined critical value, indicating that the operation information of the aircraft engine is abnormal.

[0090] When the probability of leakage in the intake duct of an aircraft engine is higher than the pre-defined critical value, it is confirmed that the air tightness of the intake duct of the aircraft engine is deteriorating, and gas leakage will often occur in the future, which will often lead to insufficient intake pressure of the aircraft engine and increase the probability of aircraft engine failure. Therefore, the aircraft engine is overhauled at this time to prevent a catastrophic accident. The pre-defined critical value in this application is seventy percent. On the other hand, when T' is zero in the equation, let T' be one to ensure that the equation is feasible.

[0091] In summary, obtain the equation of variation of the temperature value and the intake air pressure value of the aircraft engine in the continuous rotation period of each flight period in a predefined time; obtain the abnormal amplitude of the intake duct pressure in each flight period based on the equation of variation of the temperature value and the intake air pressure value of the aircraft engine in the continuous rotation period of each flight period; construct multiple abnormal amplitude queues based on the abnormal amplitude of the intake duct pressure in all flight periods in a predefined time; construct multiple abnormal amplitude queues based on the values ​​and the values ​​in the adjacent decrement queues of each abnormal amplitude queue. The abnormal amplitude of the inlet pressure in each flight period within the abnormal amplitude queue is used to obtain the probability that the abnormal amplitude of the inlet pressure meets the increase of the division level within the pre-defined time period; based on the probability that the abnormal amplitude of the inlet pressure meets the increase of the division level within the pre-defined time period and the abnormal amplitude of the inlet pressure in each flight period, the detection value of the real-time abnormal detection of the operation information of the aircraft engine is obtained, and the problem is found as soon as possible through real-time data detection. Without disassembling the aircraft engine, the probability of leakage in the aircraft engine's air intake can be evaluated in advance.

[0092] like Figure 2 As shown, the aviation safety management and monitoring system of the present invention includes:

[0093] The aircraft engine is equipped with a speed sensor, a temperature sensor, and an air pressure sensor connected to a full-authority digital electronic controller. The full-authority digital electronic controller is used to control the aircraft engine via a solenoid valve assembly based on the aircraft engine speed, temperature, and intake air pressure values ​​received from the speed sensor, temperature sensor, and air pressure sensor, respectively, in combination with an optimal control strategy, thereby achieving safe management of the aircraft engine via the solenoid valve assembly.

[0094] Modules running on a full authority digital electronic controller include:

[0095] a variation module for obtaining a variation equation for the temperature and intake pressure of the aircraft engine during a continuous rotation period of the aircraft engine within each flight period of the aircraft engine within a predefined time period, as the temperature and intake pressure of the aircraft engine change over time;

[0096] an abnormality module for obtaining an abnormal amplitude of the intake pressure of the aircraft engine during each flight period based on an equation representing a temperature value during a continuous rotation period of the aircraft engine and an intake pressure value at the aircraft engine as a function of time;

[0097] A probability module is used to construct multiple abnormal amplitude value queues based on the abnormal amplitude values ​​of the inlet pressure during all flight periods within a predefined duration; and to obtain the probability that the abnormal amplitude value of the inlet pressure during the predefined duration meets the increased level of the division level based on the values ​​in the adjacent decrement queues of each abnormal amplitude value queue and the abnormal amplitude value of the inlet pressure during each flight period within each abnormal amplitude value queue;

[0098] The detection module is used to obtain the detection value of the aircraft engine operation information for real-time abnormality detection based on the probability that the abnormal amplitude of the intake duct pressure meets the increased level of the division level within a pre-defined time period and the abnormal amplitude of the intake duct pressure during each flight period.

[0099] The beneficial effect of the present invention is that, compared with the prior art, the present invention obtains the temperature value in the continuous rotation period in each flight period of a predefined duration and the change equation of the intake air pressure value of the aircraft engine along with time; based on the temperature value in the continuous rotation period in each flight period and the change equation of the intake air pressure value at the aircraft engine along with time, the abnormal amplitude of the intake air pressure in each flight period is obtained; it is based on the leading numerical sampling method and the most efficient method to change the numerical value into an intake air pressure value fitting line with good experience, which not only ensures the accuracy and completeness of the numerical value, but also greatly improves the speed and accuracy of the numerical analysis, and provides great support for the immediate detection and overcoming of hidden air pressure abnormality problems, and constructs multiple abnormal amplitude queues based on the abnormal amplitude of the intake air pressure in all flight periods of a predefined duration. ; According to each value in the adjacent decrement queue of each abnormal amplitude queue and the abnormal amplitude of the inlet duct air pressure in each flight period in each abnormal amplitude queue, the probability of the abnormal amplitude of the inlet duct air pressure meeting the increase of the division level in a pre-defined time period is obtained; by adding the adjacent decrement queue, the changing trend of the abnormal amplitude of the inlet duct air pressure, especially the situation of the increase of the division level, is grasped, which further improves the accuracy of the detection value of the real-time abnormal detection of the operation information of the aircraft engine. According to the probability of the abnormal amplitude of the inlet duct air pressure meeting the increase of the division level in a pre-defined time period and the abnormal amplitude of the inlet duct air pressure in each flight period, the detection value of the real-time abnormal detection of the operation information of the aircraft engine is obtained, thereby detecting defects as soon as possible through real-time data detection, and estimating the probability of leakage in the intake duct of the aircraft engine in advance without performing the division into aircraft engines.

[0100] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in the field should understand that the specific implementation methods of the present invention can still be modified or replaced by equivalents. Any modification or equivalent replacement that does not deviate from the spirit and scope of the present invention should be covered within the protection space of the claims of the present invention.

Claims

1. An aviation safety management and monitoring method, characterized in that: include: The full-authority digital electronic controller controls the aircraft engine via the solenoid valve assembly based on the aircraft engine speed, temperature, and intake air pressure values ​​received from the speed sensor, temperature sensor, and air pressure sensor, respectively, and incorporating an optimal control strategy. The aircraft engine speed, temperature, or intake air pressure value is the aircraft engine operating information. The full authority digital electronic controller also executes the following method based on the aircraft engine speed value, temperature value and intake air pressure value received from the speed sensor, temperature sensor and air pressure sensor respectively: Step 1: Obtaining a time-varying equation for the temperature and intake pressure of the aircraft engine during continuous rotation periods within each flight period of the aircraft engine within a predetermined time period. Step 2: Obtain the abnormal amplitude of the aircraft engine's intake pressure during each flight period based on the equation representing the temperature value during the continuous rotation period of the aircraft engine and the intake pressure value at the aircraft engine as a function of time. Step 3: Based on the abnormal amplitudes of the inlet pressure during all flight periods within a predefined duration, multiple abnormal amplitude queues are constructed; based on the values ​​in the adjacent decrement queues of each abnormal amplitude queue and the abnormal amplitudes of the inlet pressure during each flight period within each abnormal amplitude queue, the probability that the abnormal amplitude of the inlet pressure during the predefined duration meets the increased level of the division level is obtained; In step 4, based on the probability of the intake pressure abnormal amplitude meeting the increased level of the division within a predefined time period and the abnormal amplitude of the intake pressure during each flight period, the detection value of the aircraft engine operation information real-time abnormality detection is obtained.

2. The aviation safety management and monitoring method according to claim 1, characterized in that: The predefined flight period of an aircraft engine is U; During the predefined registration time, the least square method is used to obtain the fitting line and the variation equation g of the intake air pressure value of the aircraft engine during the continuous rotation period of each flight period. y (u), where u is the value of the X-axis of the rectangular coordinate system where the fitting line is located, and the value of the Y-axis of the rectangular coordinate system where the fitting line is located is the intake pressure value.

3. The aviation safety management and monitoring method according to claim 1, characterized in that: The predefined duration is the total duration of the twenty flight periods.

4. The aviation safety management and monitoring method according to claim 3, characterized in that: Taking the yth flight period as an example, the calculation equation of the correlation factor of the total air pressure and temperature values ​​in the yth flight period is: Here, L y Represents the correlation factor of the total pressure and temperature values ​​during the flight period of flight y, b y represents the continuous rotation period in the flight period of the yth flight, g y (u) represents the equation of variation of the intake air pressure value at the aircraft engine during the continuous rotation period of the yth flight period, M y Represents the temperature value during the continuous rotation period during the flight period of flight y.

5. The aviation safety management and monitoring method according to claim 4, characterized in that: The average of the correlation factors of the total pressure and temperature values ​​of all flight periods in the previous pre-defined time period in the current pre-defined time period is defined as the base correlation factor in the pre-defined time period; The normalized value obtained by subtracting the correlation factor of the total pressure and temperature values ​​in the yth flight period from the baseline correlation factor within the predefined time period as the minuend is defined as the abnormal amplitude of the inlet pressure in the yth flight period; The adjacent decrement queue of the abnormal amplitude queue is a queue formed by subtracting the previous element from each subsequent element in the abnormal amplitude queue.

6. The aviation safety management and monitoring method according to claim 5, characterized in that: Step 3 includes: defining the abnormal amplitude of the inlet duct air pressure from the first flight period to the last flight period in the predefined time as the first abnormal amplitude value queue; defining the abnormal amplitude of the inlet duct air pressure from the second flight period to the end of the last flight period in the predefined time as the second abnormal amplitude value queue; similarly obtaining the abnormal amplitude of the inlet duct air pressure from the T"th flight period to the end of the last flight period in the predefined time as the T"th abnormal amplitude value queue; Obtain the adjacent decrement queue of each abnormal amplitude queue; Calculate the probability of abnormal amplitude queues meeting the level increase separately; Then the probability that the jth abnormal amplitude queue meets the level increase is: Here, Q j represents the probability that the jth abnormal amplitude queue meets the level increase, Representatives use the Z-score method to Perform dimensionless transformation, T j represents the standard deviation of the elements in the adjacent decrement queue of the jth abnormal amplitude queue, L j F represents the number of abnormal amplitudes of the inlet pressure during the entire flight period of the jth abnormal amplitude queue, j，L F represents the abnormal amplitude of the inlet pressure during the Lth flight period in the jth abnormal amplitude queue, j，L -1 represents the abnormal amplitude of the inlet pressure during the L-1th flight period in the jth abnormal amplitude queue; Based on this, we can obtain the probability that the entire abnormal amplitude queue meets the level increase; Therefore, the specific calculation equation for the probability that the amplitude of the intake duct pressure abnormality meets the increase in the division level within the predefined time period is: Here, Q' represents the probability that the amplitude of the intake pressure abnormality meets the increased level of the division within a predefined time period, Q j represents the probability that the jth abnormal amplitude queue meets the level increase, T” is the predefined number of critical quantities, Q zg Represents the highest amount of probability among all abnormal amplitude queues that meet the increased level.

7. The aviation safety management and monitoring method according to claim 6, characterized in that: The predefined number threshold is fifteen.

8. The aviation safety management and monitoring method according to claim 7, characterized in that: The calculation equation for the probability of leakage in the intake duct of an aircraft engine is: Here, R represents the probability that the engine's inlet will leak, Q' represents the probability that the inlet pressure abnormality amplitude meets the division level increase within a predefined time, T' is the number of flight periods within a predefined time, and F y represents the abnormal amplitude of the inlet pressure during the flight period of flight y, Representatives use the Z-score method to Perform dimensionless transformation.

9. The aviation safety management and monitoring method according to claim 8, characterized in that: Step 4 also includes: pre-defining a critical value, and when the probability of leakage in the air intake of the aircraft engine is higher than the pre-defined critical value, the operation information of the aircraft engine is abnormal.

10. An aviation safety management and monitoring system, characterized in that: include: The aircraft engine is provided with a speed sensor, a temperature sensor, and an air pressure sensor connected to a full authority digital electronic controller. The full authority digital electronic controller is used to control the aircraft engine via a solenoid valve assembly based on the speed, temperature, and intake air pressure values ​​received from the speed sensor, temperature sensor, and air pressure sensor, respectively, and in combination with an optimal control strategy. Modules running on a full authority digital electronic controller include: a variation module for obtaining a variation equation for the temperature and intake pressure of the aircraft engine during a continuous rotation period of the aircraft engine within each flight period of the aircraft engine within a predefined time period, as the temperature and intake pressure of the aircraft engine change over time; an abnormality module for obtaining an abnormal amplitude of the intake pressure of the aircraft engine during each flight period based on an equation representing a temperature value during a continuous rotation period of the aircraft engine and an intake pressure value at the aircraft engine as a function of time; A probability module is used to construct multiple abnormal amplitude value queues based on the abnormal amplitude values ​​of the inlet pressure during all flight periods within a predefined duration; and to obtain the probability that the abnormal amplitude value of the inlet pressure during the predefined duration meets the increased level of the division level based on the values ​​in the adjacent decrement queues of each abnormal amplitude value queue and the abnormal amplitude value of the inlet pressure during each flight period within each abnormal amplitude value queue; The detection module is used to obtain the detection value of the aircraft engine operation information for real-time abnormality detection based on the probability that the abnormal amplitude of the intake duct pressure meets the increased level of the division level within a pre-defined time period and the abnormal amplitude of the intake duct pressure during each flight period.

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