Aviation safety management monitoring system

Abstract

The invention discloses an aviation safety management monitoring system, belongs to the technical field of aviation safety, and relates to a change equation of temperature values in continuous rotation time periods in flight time periods of all flights and air inlet pressure values of an aero-engine along with moments. According to a change equation of the temperature value in the continuous rotation time period in the flight time period of each flight and the air inlet pressure value at the position of the aero-engine along with the time, the abnormal amplitude value of the air inlet channel pressure in the flight time period of each flight is obtained; constructing a plurality of abnormal amplitude queues according to the abnormal amplitude of the air inlet air pressure in the flight period of the whole flight in the predefined duration; in combination with other methods, problems can be found out as soon as possible through real-time data detection, and the probability of leakage of the air inlet of the aero-engine can be evaluated in advance under the condition that the aero-engine is not disassembled.

Description

Technical Field

[0001] The 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 aircraft damage. 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 the patent publication number "CN103452674B" to perform engine safety management and monitoring in terms of aviation safety. Specifically, 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 controls the aircraft engine through a solenoid valve assembly based on the speed value, temperature value and intake air pressure value of the aircraft engine respectively transmitted by the speed sensor, temperature sensor and air pressure sensor and in combination with the optimal control strategy, thereby achieving safe management of the aircraft engine through the solenoid valve assembly.

[0004] However, the 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 aircraft engine's speed, temperature and intake pressure analysis method, the method selection, etc. In complex and polymorphic 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 abnormal detection of aircraft engine operation information. Summary of the invention

[0005] In order to solve the defects in the prior art, 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 pressure in each flight period according to 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 a plurality of abnormal amplitude queues according to the abnormal amplitude of the intake duct pressure in all flight periods in the pre-defined time period; and constructs a plurality of abnormal amplitude queues according to the abnormal amplitude of each abnormal amplitude queue. The abnormal amplitude of the inlet pressure in each flight period in each adjacent reduction 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 abnormal detection of the operation information of the aircraft engine is obtained, and the problem is found out as soon as possible through real-time data detection, and the probability of leakage in the air intake of the aircraft engine can be evaluated in advance without disassembling the aircraft engine.

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

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

[0008] The full authority digital electronic controller controls the aircraft engine through the solenoid valve assembly according to the aircraft engine speed value, temperature value and intake air pressure value respectively transmitted by the speed sensor, temperature sensor and air pressure sensor and in combination with the optimal control strategy. The aircraft engine speed value, temperature value or intake air pressure value is the operation information of the aircraft engine;

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

[0010] Step 1, obtaining a variation equation of the temperature value and the intake air pressure value of the aircraft engine during the continuous rotation period of the aircraft engine in each flight period of the aircraft engine during a predefined time period;

[0011] Step 2, according to the equation of the change of the temperature value in the continuous rotation period of the aircraft engine in each flight period and the intake air pressure value at the aircraft engine with time, obtain the abnormal amplitude of the intake air pressure of the aircraft engine in each flight period;

[0012] Step 3, construct multiple abnormal amplitude queues according to the abnormal amplitude of the inlet pressure in all flight periods in the pre-defined time; obtain the probability that the abnormal amplitude of the inlet pressure in the pre-defined time meets the increase of the division level according to each value in the adjacent decrement queue of each abnormal amplitude queue and the abnormal amplitude of the inlet pressure in each flight period in each abnormal amplitude queue;

[0013] Step 4, based on the probability of the abnormal amplitude of the inlet pressure meeting the increased level of the division in the pre-defined time and the abnormal amplitude of the inlet pressure during each flight period, the detection value of the real-time abnormality detection of the operation information of the aircraft engine is obtained.

[0014] Further, the pre-defined flight period of the aircraft engine is U;

[0015] During the predefined time period, the least square method is used to obtain the fitting line and 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 pre-defined duration is the total duration of the twenty flight periods.

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

[0018]

[0019] Here, L y Represents the correlation factor of the total pressure and temperature values ​​during the flight period of the yth flight, 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 in the flight period of the yth flight, M y Represents the temperature value in the continuous rotation period during the flight period of the yth flight.

[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 reference correlation factor in the pre-defined time period.

[0021] Furthermore, a normalized value obtained by subtracting a reference correlation factor within a predefined duration as a minuend and a correlation factor of the total air pressure and temperature values ​​in the flight period of the yth flight as a subtrahend is defined as the abnormal amplitude of the inlet air pressure in the flight period of the yth flight.

[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] Further, Step 3 includes: defining the abnormal amplitude of the inlet duct pressure from the first flight period to the last flight period in the predefined time as the first abnormal amplitude queue; defining the abnormal amplitude of the inlet duct pressure from the second flight period to the last flight period in the predefined time as the second abnormal amplitude queue; similarly obtaining the T"th abnormal amplitude queue composed of the abnormal amplitude of the inlet duct pressure from the T"th flight period to the last flight period in the predefined time;

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

[0025] The probability of abnormal amplitude queues meeting the level increase is calculated 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, Represents the use of Z-score method to Perform dimensionless transformation, T j represents the standard deviation of the elements in the adjacent reduction queue of the jth abnormal amplitude queue, L j represents the number of abnormal amplitudes of the inlet pressure in the entire flight period of the jth abnormal amplitude queue, F j，L represents the abnormal amplitude of the inlet pressure during the Lth flight period in the jth abnormal amplitude queue, F 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, the probability of the overall abnormal amplitude queue meeting the level increase is obtained;

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

[0031]

[0032] Here, Q' represents the probability that the amplitude of the inlet pressure disturbance 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 that the entire abnormal amplitude queue meets 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 inlet of the aircraft engine will leak, Q' represents the probability that the inlet pressure abnormal amplitude meets the increase of the division level in the pre-defined time, T' is the number of flight hours in the pre-defined time, and F y represents the abnormal amplitude of the inlet pressure during the flight period of the yth flight, Represents the use of 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 air intake 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 through a solenoid valve assembly according to the speed value, temperature value and intake air pressure value of the aircraft engine respectively transmitted by the speed sensor, the temperature sensor and the air pressure sensor and in combination with an optimal control strategy;

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

[0041] A variation module, which is used to obtain a variation equation of the temperature value and the intake air pressure value of the aircraft engine during the continuous rotation period of the aircraft engine in each flight period of the aircraft engine during a predefined time period, which changes with time;

[0042] An abnormal module, which is used to obtain the abnormal amplitude of the intake duct pressure of the aircraft engine in each flight period according to the temperature value in the continuous rotation period of the aircraft engine in each flight period and the change equation of the intake air pressure value at the aircraft engine with time;

[0043] A probability module is used to construct multiple abnormal amplitude queues according to the abnormal amplitude of the air inlet pressure in all flight periods in a predefined time; and to obtain the probability that the abnormal amplitude of the air inlet pressure in the predefined time meets the increased level of the division level according to each value in the adjacent decrement queue of each abnormal amplitude queue and the abnormal amplitude of the air inlet pressure in each flight period in each abnormal amplitude queue;

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

[0045] The beneficial effect of the present invention lies in that, compared with the prior art, the present invention obtains the temperature value in the continuous rotation period in each flight period of a flight in a predefined time and the change equation of the intake air pressure value of the aircraft engine along with time; according to the change equation of the temperature value in the continuous rotation period in each flight period and 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; according to the leading numerical sampling method and the most efficient method, the numerical value can be changed 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 numerical analysis, and provides great support for the timely detection and overcoming of hidden air pressure abnormality problems, and constructs multiple abnormal amplitude queues according to the abnormal amplitude of the intake air pressure in all flight periods of the predefined time. ; 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 that the abnormal amplitude of the inlet duct air pressure meets 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, can be grasped, and the accuracy of the detection value of the real-time abnormal detection of the operation information of the aircraft engine is further improved. According to the probability that the abnormal amplitude of the inlet duct air pressure meets the increase of the division level in the 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, and the defects can be found out as soon as possible through real-time data detection, and the probability of leakage in the air intake duct of the aircraft engine can be estimated in advance without performing the division of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 It 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] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely expressed in combination with the drawings in the embodiments of the present invention. The embodiments expressed in this application are only embodiments of a part of the present invention, not all embodiments. According to the spirit of the present invention, other embodiments obtained by ordinary technicians in this field without creative work are all within the scope of protection of the present invention.

[0049] like Figure 1 As shown, an aviation safety management and monitoring method according to the present invention comprises:

[0050] The full authority digital electronic controller controls the aircraft engine through the solenoid valve assembly according to the aircraft engine speed value, temperature value and intake air pressure value respectively transmitted by the speed sensor, temperature sensor and air pressure sensor and in combination with the optimal control strategy. The aircraft engine speed value, temperature value or intake air pressure value is the operation information of the aircraft engine, thereby achieving safe management of the aircraft engine through the solenoid valve assembly;

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

[0052] Step 1, obtaining a variation equation of the temperature value and the intake air pressure value of the aircraft engine during the continuous rotation period of the aircraft engine in each flight period of the aircraft engine during a predefined 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 time period, the least square method is used to obtain the fitting line and 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 pre-defined duration is the total duration of twenty flight periods.

[0056] Step 2, according to the equation of the change of the temperature value in the continuous rotation period of the aircraft engine in each flight period and the intake air pressure value at the aircraft engine with time, obtain the abnormal amplitude of the intake air pressure of the aircraft engine in each flight period;

[0057] Under normal conditions, the higher the temperature, the higher the intake volume. At this time, the temperature and 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 knot. 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, which represents 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 interval, the abnormal amplitude of the intake duct pressure 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 of the correlation factor of the total air pressure and temperature value 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 the yth flight, 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 in the flight period of the yth flight, M yRepresents the temperature value in the continuous rotation period during the flight period of the yth flight.

[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 flight period of the yth flight, it means that the inlet air pressure is abnormal.

[0063] According to the above method, the correlation factor 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 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 benchmark correlation factor in the pre-defined time period.

[0065] In a preferred but non-limiting embodiment of the present invention, the normalized value obtained by subtracting the reference correlation factor within a predefined time period as the minuend and the correlation factor of the total air pressure and temperature value in the flight period of the yth flight as the subtrahend is defined as the abnormal amplitude of the air inlet pressure in the flight period of the yth flight. Here, the Z-score method is used to obtain the normalized value of the subtracted value.

[0066] Step 3, construct multiple abnormal amplitude queues according to the abnormal amplitude of the inlet pressure in all flight periods in the pre-defined time; obtain the probability that the abnormal amplitude of the inlet pressure in the pre-defined time meets the increase of the division level according to each value in the adjacent decrement queue of each abnormal amplitude queue and the abnormal amplitude of the inlet pressure in each flight period in each abnormal amplitude queue;

[0067] In a preferred but non-limiting embodiment of the present invention, the adjacent reduction 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] It is not possible to determine whether the intake duct pressure is abnormal just by relying on the abnormal amplitude of the intake duct pressure during the current intake period. Just like when the turbocharger of an aircraft engine is not boosted smoothly, the intake duct pressure will also be low. At this time, it is necessary to calculate the probability of leakage in the intake duct of the aircraft engine based on the abnormal pressure distribution.

[0069] When tiny holes appear in the air intake duct of an aircraft engine, the air tightness of the air intake duct is poor, and the air pressure in the air intake duct is weakened, which often leads to abnormal air pressure in the air intake duct, and the air tightness of the air intake duct often deteriorates in the future period, that is, during multiple intake periods, the air pressure abnormality in the air intake duct often increases in levels in some areas. At this time, the air intake duct of the current aircraft engine is often leaking.

[0070] In a preferred but non-limiting embodiment of the present invention, 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 duration as the first abnormal amplitude queue; defining the abnormal amplitude of the inlet duct air pressure from the second flight period to the final inlet duct air pressure of the last flight period in the pre-defined duration 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 final inlet duct air pressure of the last flight period in the pre-defined duration;

[0071] In a preferred but non-limiting embodiment of the present invention, the predefined number threshold is fifteen.

[0072] Obtain the adjacent reduction queues of each abnormal amplitude queue;

[0073] The probability of abnormal amplitude queues meeting the increase in level is calculated separately. If there is an increase in the level of random queues, it means that the abnormal amplitude of the inlet pressure meets the increase in the level of the distribution, which meets the characteristics of the deterioration of the air tightness of the inlet, then the probability of leakage in the inlet of the aircraft engine is higher;

[0074] Taking the jth abnormal amplitude queue as an example, the probability that the jth abnormal amplitude queue meets the level increase is:

[0075]

[0076] Here, Q j represents the probability that the jth abnormal amplitude queue meets the level increase, Represents the use of Z-score method to Perform dimensionless transformation, T j represents the standard deviation of the elements in the adjacent reduction queue of the jth abnormal amplitude queue, L j represents the number of abnormal amplitudes of the inlet pressure in the entire flight period of the jth abnormal amplitude queue, F j，L represents the abnormal amplitude of the inlet pressure during the Lth flight period in the jth abnormal amplitude queue, F j，L -1 represents the abnormal amplitude of the inlet pressure during the L-1th flight period in the jth abnormal amplitude queue;

[0077] and represents the average of the elements in the adjacent reduction 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 overall abnormal amplitude queue meeting the level increase is obtained;

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

[0080]

[0081] Here, Q' represents the probability that the amplitude of the inlet pressure disturbance 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 that the entire abnormal amplitude queue meets 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 air pressure meets the increased level of the distribution within the pre-defined time period.

[0083] Step 4, based on the probability of the abnormal amplitude of the inlet pressure meeting the increased level of the division in the pre-defined time and the abnormal amplitude of the inlet pressure during each flight period, the detection value of the real-time abnormality detection of the operation information of the aircraft engine is obtained.

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

[0085] In a preferred but non-limiting embodiment of the present invention, the calculation equation for the probability that the air intake of the aircraft engine will show leakage is:

[0086]

[0087] Here, R represents the probability that the inlet of the aircraft engine will leak, Q' represents the probability that the inlet pressure abnormal amplitude meets the increase of the division level in the pre-defined time, T' is the number of flight hours in the pre-defined time, and F y represents the abnormal amplitude of the inlet pressure during the flight period of the yth flight, Represents the use of Z-score method to Perform dimensionless transformation.

[0088] and It represents the average of the amplitude of abnormal inlet pressure during the entire flight period. The higher the average is and the more it conforms to the characteristics of increasing distribution level, the higher the probability of leakage in the inlet of the aircraft engine.

[0089] In a preferred but non-limiting embodiment of the present invention, 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, the operation information of the aircraft engine is abnormal.

[0090] When the probability of leakage in the air intake duct of the aircraft engine is higher than the pre-defined recognition critical amount, it is confirmed that the air tightness of the air intake duct of the aircraft engine is deteriorating, and gas leakage will often occur in the future, which will often cause insufficient air 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 catastrophic accidents. The pre-defined recognition critical amount 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 variation equation of the temperature value in the continuous rotation period and the intake air pressure value of the aircraft engine with time in each flight period in a predefined time; obtain the abnormal amplitude of the intake duct pressure in each flight period according to the variation equation of the temperature value in the continuous rotation period and the intake air pressure value at the aircraft engine with time in each flight period; construct multiple abnormal amplitude queues according to the abnormal amplitude of the intake duct pressure in all flight periods in a predefined time; and construct multiple abnormal amplitude queues according to each value in the adjacent decrement queue of each abnormal amplitude queue and each value in the adjacent decrement queue 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 out as soon as possible through real-time data detection, and the probability of leakage in the air intake of the aircraft engine can be evaluated in advance without disassembling the aircraft engine.

[0092] like Figure 2 As shown, an aviation safety management and monitoring system according to the present invention comprises:

[0093] 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 through the solenoid valve assembly according to the speed value, temperature value and intake air pressure value of the aircraft engine respectively transmitted by the speed sensor, the temperature sensor and the air pressure sensor and in combination with the optimal control strategy, thereby achieving safe management of the aircraft engine through the solenoid valve assembly;

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

[0095] A variation module, which is used to obtain a variation equation of the temperature value and the intake air pressure value of the aircraft engine during the continuous rotation period of the aircraft engine in each flight period of the aircraft engine during a predefined time period, which changes with time;

[0096] An abnormal module, which is used to obtain the abnormal amplitude of the intake duct pressure of the aircraft engine in each flight period according to the temperature value in the continuous rotation period of the aircraft engine in each flight period and the change equation of the intake air pressure value at the aircraft engine with time;

[0097] A probability module is used to construct multiple abnormal amplitude queues according to the abnormal amplitude of the air inlet pressure in all flight periods in a predefined time; and to obtain the probability that the abnormal amplitude of the air inlet pressure in the predefined time meets the increased level of the division level according to each value in the adjacent decrement queue of each abnormal amplitude queue and the abnormal amplitude of the air inlet pressure in each flight period in each abnormal amplitude queue;

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

[0099] The beneficial effect of the present invention lies in that, compared with the prior art, the present invention obtains the temperature value in the continuous rotation period in each flight period of a flight in a predefined time and the change equation of the intake air pressure value of the aircraft engine along with time; according to the change equation of the temperature value in the continuous rotation period in each flight period and 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; according to the leading numerical sampling method and the most efficient method, the numerical value can be changed 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 numerical analysis, and provides great support for the timely detection and overcoming of hidden air pressure abnormality problems, and constructs multiple abnormal amplitude queues according to the abnormal amplitude of the intake air pressure in all flight periods of the predefined time. ; 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 that the abnormal amplitude of the inlet duct air pressure meets 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, can be grasped, and the accuracy of the detection value of the real-time abnormal detection of the operation information of the aircraft engine is further improved. According to the probability that the abnormal amplitude of the inlet duct air pressure meets the increase of the division level in the 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, and the defects can be found out as soon as possible through real-time data detection, and the probability of leakage in the air intake duct of the aircraft engine can be estimated in advance without performing the division of the aircraft engine.

[0100] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution 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 relevant field should understand that the specific implementation methods of the present invention can still be modified or replaced by equivalents, and any modifications or equivalent replacements that do 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 through the solenoid valve assembly according to the aircraft engine speed value, temperature value and intake air pressure value respectively transmitted by the speed sensor, temperature sensor and air pressure sensor and in combination with the optimal control strategy. The aircraft engine speed value, temperature value or intake air pressure value is the operation information of the aircraft engine; The full authority digital electronic controller also executes the following method based on the speed value, temperature value and intake air pressure value of the aircraft engine respectively transmitted by the speed sensor, temperature sensor and air pressure sensor: Step 1, obtaining a variation equation of the temperature value and the intake air pressure value of the aircraft engine during the continuous rotation period of the aircraft engine in each flight period of the aircraft engine during a predefined time period; Step 2, according to the equation of the change of the temperature value in the continuous rotation period of the aircraft engine in each flight period and the intake air pressure value at the aircraft engine with time, obtain the abnormal amplitude of the intake air pressure of the aircraft engine in each flight period; Step 3, construct multiple abnormal amplitude queues according to the abnormal amplitude of the inlet pressure in all flight periods in the pre-defined time; obtain the probability that the abnormal amplitude of the inlet pressure in the pre-defined time meets the increase of the division level according to each value in the adjacent decrement queue of each abnormal amplitude queue and the abnormal amplitude of the inlet pressure in each flight period in each abnormal amplitude queue; Step 4, based on the probability of the abnormal amplitude of the inlet pressure meeting the increased level of the division in the pre-defined time and the abnormal amplitude of the inlet pressure during each flight period, the detection value of the real-time abnormality detection of the operation information of the aircraft engine 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 time period, the least square method is used to obtain the fitting line and 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 flight period of the yth flight as an example, the calculation equation of the correlation factor of the total air pressure and temperature value in the flight period of the yth flight is: Here, L y Represents the correlation factor of the total pressure and temperature values ​​during the flight period of the yth flight, 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 in the flight period of the yth flight, M y Represents the temperature value in the continuous rotation period during the flight period of the yth flight.

5. The aviation safety management and monitoring method according to claim 4, characterized in that: 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 reference correlation factor in the pre-defined time period; The normalized value obtained by subtracting the reference correlation factor within the predefined time period as the minuend and the correlation factor of the total pressure and temperature values ​​in the flight period of the yth flight as the subtrahend is defined as the abnormal amplitude of the inlet pressure in the flight period of the yth flight; 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 pressure from the first flight period to the last flight period in the predefined time as the first abnormal amplitude queue; defining the abnormal amplitude of the inlet duct pressure from the second flight period to the last flight period in the predefined time as the second abnormal amplitude queue; similarly obtaining the T”th abnormal amplitude queue composed of the abnormal amplitude of the inlet duct pressure from the T”th flight period to the last flight period in the predefined time; Obtain the adjacent reduction queues of each abnormal amplitude queue; The probability of abnormal amplitude queues meeting the level increase is calculated 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, Represents the use of Z-score method to Perform dimensionless transformation, T j represents the standard deviation of the elements in the adjacent reduction queue of the jth abnormal amplitude queue, L j represents the number of abnormal amplitudes of the inlet pressure in the entire flight period of the jth abnormal amplitude queue, F j，L represents the abnormal amplitude of the inlet pressure during the Lth flight period in the jth abnormal amplitude queue, F 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, the probability of the overall abnormal amplitude queue meeting the level increase is obtained; Therefore, the specific calculation equation for the probability that the amplitude of the inlet pressure abnormality meets the increase of the division level within the predefined time period is: Here, Q' represents the probability that the amplitude of the inlet pressure disturbance 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 that the entire abnormal amplitude queue meets 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 inlet of the aircraft engine will leak, Q' represents the probability that the inlet pressure abnormal amplitude meets the increase of the division level in the pre-defined time, T' is the number of flight hours in the pre-defined time, and F y represents the abnormal amplitude of the inlet pressure during the flight period of the yth flight, Represents the use of 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 duct of the aircraft engine is higher than the pre-defined critical value, indicating that 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 through a solenoid valve assembly according to the speed value, temperature value and intake air pressure value of the aircraft engine respectively transmitted by the speed sensor, the temperature sensor and the air pressure sensor and in combination with an optimal control strategy; Modules running on a full authority digital electronic controller include: A variation module, which is used to obtain a variation equation of the temperature value and the intake air pressure value of the aircraft engine during the continuous rotation period of the aircraft engine in each flight period of the aircraft engine during a predefined time period, which changes with time; An abnormal module, which is used to obtain the abnormal amplitude of the intake duct pressure of the aircraft engine in each flight period according to the temperature value in the continuous rotation period of the aircraft engine in each flight period and the change equation of the intake air pressure value at the aircraft engine with time; A probability module is used to construct multiple abnormal amplitude queues according to the abnormal amplitude of the air inlet pressure in all flight periods in a predefined time; and to obtain the probability that the abnormal amplitude of the air inlet pressure in the predefined time meets the increased level of the division level according to each value in the adjacent decrement queue of each abnormal amplitude queue and the abnormal amplitude of the air inlet pressure in each flight period in each abnormal amplitude queue; The detection module is used to obtain the detection value of the real-time abnormality detection of the operation information of the aircraft engine based on the probability that the abnormal amplitude of the inlet pressure meets the increased level of the division level in a pre-defined time and the abnormal amplitude of the inlet pressure during each flight period.

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