A method for diagnosing faults of an embedded flight parameter sensing system for a blunt body

Abstract

The application relates to a fault diagnosis method of an embedded flight parameter sensing system for a blunt body, which is accurate in fault diagnosis, can diagnose the complete failure of a pressure measuring hole, can diagnose the abnormal fluctuation of pressure in the pressure measuring hole, that is, the case that the fluctuation amplitude of pressure exceeds the error limit of an algorithm, has high reliability in fault diagnosis, has strong engineering applicability, has a wide application speed range and can be applied to the fields of low speed, subsonic speed, transonic speed, supersonic speed and hypersonic speed.

Description

Technical Field

[0001] This invention provides a fault diagnosis method for an embedded flight parameter sensing system for blunt-nosed aircraft, belonging to the field of flight parameter measurement and control technology. Background Technology

[0002] Accurate measurement and calculation of flight parameters such as Mach number, angle of attack, sideslip angle, and free-flow static pressure are crucial for the real-time control of aircraft. Embedded flight parameter sensing systems acquire surface pressure data through pressure-sensing holes configured in specific areas of the aircraft surface. Reliable pressure data is key to ensuring the normal operation of the system. In actual engineering implementation, due to the harsh flight environment and hardware configuration requirements of the aircraft, inaccurate surface pressure data due to pressure-sensing hole failure is inevitable. (1) Pressure sensor failure leads to complete failure of the pressure signal from the pressure-sensing hole; (2) Blockage of the pressure-sensing hole leads to inaccurate pressure signals, severely challenging its performance and even causing it to fail. Therefore, reliable fault diagnosis technology is crucial to ensuring the normal engineering implementation of the system.

[0003] In actual flight missions, the system provides real-time calculated incoming flow parameters for flight control, such as free-flow static pressure, Mach number, altitude, angle of attack, and sideslip angle. To ensure flight control safety, robust fault diagnosis technology is crucial. For faulty pressure gauges in the system, the fault diagnosis mode requires the system to accurately eliminate faulty gauges and employ corresponding redundant calculation schemes to ensure the system continuously and stably outputs flight parameters. Therefore, accurately identifying faults and adopting appropriate redundant calculation schemes are important guarantees for reliable performance. As an integrated system for calculating flight parameters, the establishment of its redundancy scheme and fault diagnosis mode is crucial for product finalization and reliable and stable calculation, primarily aiming to improve data reliability and the accuracy of calculated flight parameters. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of traditional fault diagnosis methods and provide a diagnostic method based on a key threshold fault diagnosis mode. The fault diagnosis is accurate, capable of diagnosing not only complete failure of the pressure measuring orifice but also abnormal pressure fluctuations, i.e., pressure fluctuation amplitudes exceeding the algorithm error limit. The fault diagnosis is highly reliable, has strong engineering applicability, and a wide application range, suitable for low-speed, subsonic, transonic, supersonic, and hypersonic applications.

[0005] The technical solution of this invention is: a fault diagnosis method for an embedded flight parameter sensing system for blunt-nosed aircraft, wherein the embedded flight parameter sensing system for blunt-nosed aircraft has at least 6 pressure measurement holes configured in a specific area on the leading edge surface of the blunt nose of the aircraft, and the method steps are as follows:

[0006] (1) The maximum and minimum values ​​of each pressure measurement hole within the flight envelope were determined using numerical modeling methods;

[0007] (2) Determine whether the pressure data collected by all pressure measuring holes are within their corresponding maximum and minimum value ranges. If they are, proceed to step (3); otherwise, remove the pressure measuring holes that are not within the range as faulty pressure measuring holes.

[0008] (3) Select any three different pressure measuring holes arranged along the longitudinal centerline of the angle of attack, and calculate the local angle of attack under different combinations using the three-point algorithm based on all different combinations;

[0009] (4) Based on all the calculated local angle of attack values, use weighted average estimation to calculate the mean of the angle of attack estimate, and determine whether the maximum value among the differences between all local angles of attack and the mean is not greater than the angle of attack deviation threshold. If the relationship is not established, proceed to step (5); if it is established, proceed to step (6).

[0010] (5) Eliminate faulty pressure test holes one by one, calculate the local angle of attack of all combinations of pressure test holes, repeat step (4) until it is established, remove the faulty pressure test holes, and execute step (6).

[0011] (6) According to the pressure measuring hole number, the pressure measuring holes configured on the transverse centerline are added one by one in a single positive sequence. Based on all the combinations of 3 different pressure measuring holes, the local sideslip angle is calculated using a three-point algorithm.

[0012] (7) Based on all local sideslip angle values, calculate the estimated mean of sideslip angle using weighted average estimation. Determine whether the maximum value among the differences between all local sideslip angles and the estimated mean of sideslip angle is not greater than the sideslip angle deviation threshold. If the relationship is not established, remove the newly added pressure test hole. If the relationship is established, the added pressure test hole is not faulty and proceed to step (8).

[0013] (8) Based on steps (4)-(7), calculate the local angle of attack and local sideslip angle based on the preliminary judgment that there is no fault in the pressure test hole, and determine the incoming injection angle of the fault-free pressure test hole;

[0014] (9) Based on the injection angle of the pressure measuring hole determined in step (8) and the pressure value collected by the corresponding pressure measuring hole, calculate the solution value of all odd and even equations based on the three different combinations of pressure measuring holes and compare it with the defined deviation threshold. If the solution value is greater than the defined deviation threshold, proceed to step (10); otherwise, proceed directly to step (11).

[0015] (10) Based on the odd-even equation established by the rough set theory reduction, identify and remove all pressure measuring holes that appear in all combinations of pressure measuring holes that do not satisfy the relationship in step (10).

[0016] (11) Calculate the Mach number, angle of attack, sideslip angle, static pressure and dynamic pressure flight parameters based on the pressure data obtained from the pressure measurement holes that are free of faults.

[0017] Preferably, the positions of the at least six pressure measuring holes are as follows:

[0018] The pressure measuring hole located at the stagnation point has a circumferential angle of 0° and a conical angle of 0°.

[0019] The pressure measuring hole is located on the lower surface of the longitudinal centerline, with a circumferential angle of 0° and a cone angle between 30° and 60°.

[0020] The pressure measuring hole located on the upper surface of the longitudinal centerline has a circumferential angle of 180° and a cone angle between 30° and 60°.

[0021] The pressure measuring hole is located on the left surface of the transverse centerline, with a circumferential angle of 90° and a cone angle between 30° and 60°.

[0022] The pressure measuring hole is located on the right surface of the transverse centerline, with a circumferential angle of 270° and a cone angle between 30° and 60°.

[0023] Preferably, the deviation threshold δ in step (9) is determined as follows:

[0024] δ = max{δ1,δ2,δ3}

[0025] in,

[0026]

[0027]

[0028]

[0029] Where α, β, and Ma are the state parameters in the numerical modeling process, representing the angle of attack, sideslip angle, and Mach number, respectively. i The pressure values ​​collected from the pressure measuring hole.

[0030] Preferably, the weighting coefficients in the weighted averages in steps (4) and (7) are set as follows:

[0031] When the pressure testing port combination contains stagnation points,

[0032]

[0033] When the pressure testing port combination does not include stagnation points,

[0034]

[0035] in, is the average weighting coefficient, w(i,j,k) is the weighting coefficient of the combination of pressure test holes pi,pj,pk, and i,j,k are the pressure test hole numbers.

[0036] Preferably, in step (3), any three different pressure measuring holes configured along the longitudinal centerline are selected, and the local angle of attack is calculated based on all different combinations using a three-point algorithm. The three-point algorithm refers to obtaining the analytical solution of the local angle of attack by using only three different combinations of pressure measuring holes located on the longitudinal centerline, according to the positional relationship of the pressure measuring holes and the pressure difference relationship between any two pressure measuring holes.

[0037] Preferably, in step (5), the faulty pressure test hole is determined by the reverse elimination method according to the pressure test hole number. The reverse elimination method means that the pressure value of the corresponding pressure test hole is added one by one in descending order according to the selected pressure test hole number to calculate the local angle of attack, and it is judged whether the relationship in step (4) is satisfied. If the relationship is not established, the corresponding pressure test hole is the faulty pressure test hole.

[0038] Preferably, the solution value χP of the parity equation in step (9) is determined as follows:

[0039] χp=[cos 2 θ k -cos 2 θ j cos 2 θ i -cos 2 θ k cos 2 θ j -cos 2 θ i ][p i ,p j ,p k ] T

[0040] Where χp is the solution value of the odd-even equation, θ i ,θ j ,θ k Let p be the inflow and outflow angle of the pressure measuring holes pi, pj, pk. i ,p j ,p k Here are the pressure values ​​for the pressure measuring holes pi, pj, and pk, where i, j, and k are the hole numbers.

[0041] Preferably, the formula for calculating the incoming flow angle in step (8) is as follows:

[0042] cosθ i =cosα e cosβ e cosλ i +sinβ e sinφ i sinλ i +sinα e cosβe cosφ i sinλ i

[0043] Where, α e ,β e These are the local angle of attack and local sideslip angle calculated in step (8), respectively; φ i , λ i Let be the circumferential angle and the conical angle at the pi-th pressure measurement point.

[0044] Preferably, in step (10), the parity equation established by reduction based on rough set theory determines all pressure gauges that appear in combinations of pressure gauges that do not satisfy the relationship in step (10), including:

[0045] Define the parameter κ(t).

[0046] If κ(t=(i,j,k),i≠j≠k)==0 is satisfied, the pressure measuring hole is normal;

[0047] If κ(t=i)==1&&κ(t≠i)==0, the pressure measuring hole pi is faulty;

[0048] If κ(t=i,t=j)==1&&κ(t≠i,t≠j)==0(i≠j), then the pressure measuring holes pi and pj are faulty;

[0049] Where t represents the number determined based on all different pressure measuring hole combinations, t=(i,j,k), i≠j≠k represents the number based on all different pressure measuring hole combinations pi, pj, pk, t=i represents the number of the combination containing pressure measuring hole pi in all different pressure measuring hole combinations, t≠i represents the number of the combination not containing pressure measuring hole pi in all different pressure measuring hole combinations, t=j represents the number of the combination containing pressure measuring hole pj in all different pressure measuring hole combinations, t≠j represents the number of the combination not containing pressure measuring hole pj in all different pressure measuring hole combinations, i,j,k are different pressure measuring hole numbers; if the solution value of the odd-even equation of the pressure measuring hole combination pi,pj,pk does not satisfy the relationship in step (9), κ(t)=1 is defined; if the relationship in step (9) is satisfied, κ(t)=0 is defined.

[0050] Preferably, the deviation threshold δ determined in step (9) is generally taken as 1.1 to 1.3 times the theoretical design value in actual engineering applications.

[0051] The advantages of this invention compared to the prior art are:

[0052] (1) Comprehensive and reliable fault diagnosis. The fault diagnosis method of the present invention first performs preliminary fault diagnosis based on physical error limits; secondly, it performs secondary fault elimination based on a three-point algorithm; and finally, it determines the faulty pressure test hole based on a key threshold. The method of the present invention can not only diagnose completely failed pressure test holes, but also diagnose faulty pressure test holes that exceed the algorithm error limits, thus providing comprehensive and reliable fault diagnosis.

[0053] (2) Accurate fault diagnosis. The fault diagnosis method of the present invention determines the key threshold based on the rate of change of each pressure measuring hole in the entire flight envelope with the angle of attack, sideslip angle and Mach number, which can accurately reflect the fault situation of a certain pressure measuring hole; at the same time, faulty pressure measuring holes that exceed the algorithm error limit can be accurately identified, and the fault diagnosis is accurate.

[0054] (3) Strong feasibility in practical engineering. The fault diagnosis method of the present invention can fully guarantee the reliability of system calculation when a certain pressure measuring hole fails, and can guarantee the reliable calculation of the system when a system failure occurs, thus having strong feasibility in practical engineering.

[0055] (4) Wide range of applications. The fault diagnosis method of the present invention can be used for fault diagnosis of embedded flight parameter sensing systems of low-speed, subsonic, transonic, supersonic and hypersonic aircraft, and has a wide range of applications. Attached Figure Description

[0056] Figure 1 This is a flowchart of the fault diagnosis method of the present invention;

[0057] Figure 2 This is a schematic diagram of the pressure measuring hole configuration used in this invention;

[0058] Figure 3 Example of determining a fault in a pressure testing port using the fault diagnosis method of the present invention;

[0059] Figure 4 This is a comparison chart of the angle of attack and the true flight trajectory obtained when a fault is determined using the fault diagnosis method of the present invention to identify a fault in a pressure measuring hole. Detailed Implementation

[0060] This invention provides a fault diagnosis method for an embedded flight parameter sensing system for blunt-nosed airframes. This invention offers accurate fault diagnosis, capable of diagnosing not only complete failure of pressure gauges but also abnormal pressure fluctuations (i.e., pressure fluctuation amplitudes exceeding the algorithm's error limit). The invention boasts high reliability, strong engineering applicability, and a wide application range, suitable for low-speed, subsonic, transonic, supersonic, and hypersonic applications. This invention has broad prospects for engineering applications.

[0061] like Figure 1As shown, this invention provides a fault diagnosis method for an embedded flight parameter sensing system for blunt-nosed aircraft, the steps of which are as follows:

[0062] (1) As Figure 2 As shown, 11 pressure measuring holes, numbered p1, p2, p3, p4, p5, p6, p7, p8, p9, p10, and p11, are configured in a specific area on the leading edge surface of the blunt nose of the aircraft. In practical engineering applications, the pressure values ​​collected by the pressure measuring holes p1 (i = 1, ... 11) are defined as p1, p2, p3, p4, p5, p6, p7, p8, p9, p10, and p11. i (i = 1, ... 11);

[0063] (1.1) The positional relationship of pressure measuring holes p1, p2, p3, p4, p5, p6, p7, p8, p9, p10, and p11 is determined by the circumferential angle and conical angle of the pressure measuring hole, in degrees, and must satisfy the following:

[0064] (a)p1: Located at the stationary point, with an inscribed angle of 0° and a cone angle of 0°;

[0065] (b)p3,p5,p9: Located on the lower surface of the longitudinal centerline, with a circumferential angle of 0° and a cone angle between 30° and 60°;

[0066] (c)p2,p4,p8: Located on the upper surface of the longitudinal centerline, with a circumferential angle of 180° and a cone angle between 30° and 60°;

[0067] (d)p6, p10: Located on the left surface of the transverse midline, with a circumferential angle of 90° and a cone angle between 30° and 60°;

[0068] (e)p7,p11: Located on the right surface of the transverse midline, with a circumferential angle of 270° and a cone angle between 30° and 60°;

[0069] The definitions of the circumferential angle and cone angle of the pressure measuring hole in (a) to (e) are as follows:

[0070] The circumferential angle of a pressure measuring hole is defined as the angle between the line connecting the longitudinal axis and the location of the pressure measuring hole to the longitudinal cross-sectional outline in the front view, and the longitudinal cross-sectional centerline. The unit is °, and the range is 0° to 360°. The starting position, i.e., the position where the circumferential angle is 0°, is defined as the intersection of the line connecting the longitudinal centerline and the bottom of the longitudinal cross-sectional outline. Clockwise is positive.

[0071] The cone angle is defined as the angle between the surface normal direction at the location of the pressure measuring hole and the longitudinal axis of the blunt head precursor, in degrees, and ranging from 0° to 90°.

[0072] (2) Using numerical modeling, determine the maximum value p of the pressure measuring orifice pi (i = 1, ... 11) in step (1) within the flight envelope.i-max (i = 1, 2... 11) and the minimum value p i-min (i = 1, 2... 11);

[0073] (2.1) Flight envelope refers to the time-varying Mach number, angle of attack, sideslip angle, and altitude envelope of an aircraft during actual flight.

[0074] (3) Change p in step (1) i (i = 1, 2... and the maximum value p determined in step (2) i-max (i = 1, 2... 11) and the minimum value p i-min (Comparing i = 1, 2... 11, the following conditions are met)

[0075] p i-min ≤p i ≤p i-max (i = 1, 2... 11)

[0076] Execute step (4) and remove pressure test holes that do not meet the above conditions as faulty pressure test holes;

[0077] (4) Select any three different pressure measuring holes arranged along the longitudinal centerline of the angle of attack. Based on all different combinations, use the three-point algorithm to calculate the local angle of attack α. e (i,j,k)(i<j<k,i,j,k=1,2,3,4,5,8,9);

[0078] (4.1) Three-point algorithm: Using only three different combinations of pressure measuring holes located on the longitudinal centerline, the analytical solution of the local angle of attack is obtained based on the positional relationship of the pressure measuring holes and the pressure difference relationship between any two pressure measuring holes;

[0079] (5) Based on all the local angle of attack values ​​obtained in step (4), calculate the mean of the angle of attack estimates using a weighted average estimation. Determine whether the local angle of attack values ​​obtained in step (4) meet the requirements.

[0080]

[0081] Where δα is the angle of attack deviation threshold, α e (i,j,k) represents the local angle of attack value obtained based on different combinations of 3 pressure measuring holes, and i<j<k,i,j,k=1,2,3,4,5,8,9;

[0082] (5.1) The weighting coefficients are determined according to the following formula:

[0083] When the pressure testing port combination contains p1,

[0084]

[0085] When the pressure test port combination does not include p1,

[0086]

[0087] in, is the average weighting coefficient, w(i,j,k) is the weighting coefficient of the combination of pressure test holes pi,pj,pk, where i,j,k are the pressure test hole numbers;

[0088] (6) If step (5) is not true, proceed to step (7); if step (5) is true, proceed to step (8).

[0089] (7) Based on the pressure test hole number, the faulty pressure test hole is determined by the reverse elimination method. The local angle of attack of all combinations containing the pressure test hole is calculated. Steps (5) and (6) are executed repeatedly until the relationship in step (5) is established. The faulty pressure test hole is eliminated and step (8) is executed.

[0090] (7.1) The reverse elimination method refers to the following steps: according to the pressure test hole numbers from largest to smallest, first add the pressure value of pressure test hole p9 to calculate whether the local angle of attack meets step (5), then add the pressure value of pressure test hole p8 to calculate whether the local angle of attack meets step (5), and so on in reverse order. Finally, add the pressure value of pressure test hole p1 to calculate whether the local angle of attack meets step (5).

[0091] (8) Based on the pressure measuring hole number, the pressure measuring holes located on the transverse centerline are added one by one in a single positive sequence. Based on all combinations of three different pressure measuring holes, the local sideslip angle β is calculated using a three-point algorithm. em (m = 6, 7, 10, 11);

[0092] (8.1) Three-point algorithm: Using only three different combinations of pressure measuring holes located on the transverse centerline, the analytical solution of the local sideslip angle is obtained based on the positional relationship of the pressure measuring holes and the pressure difference relationship between any two pressure measuring holes;

[0093] (8.2) Single sequential addition of configuration means that, according to the pressure test hole numbers in ascending order, first add the pressure value p1 of pressure test hole p1 to calculate whether the local angle of attack meets step (9), then add the pressure value p6 of pressure test hole p6 to calculate whether the local sideslip angle meets step (9), and so on, and finally add the pressure value p11 of pressure test hole p1. 11 Calculate whether the local sideslip angle satisfies step (9);

[0094] (9) Based on all the local sideslip angle values ​​obtained in step (8), calculate the mean of the sideslip angle estimates using a weighted average estimation. Determine if it satisfies

[0095]

[0096] Where δβ is the sideslip angle deviation threshold, β em The values ​​of the local sideslip angle are obtained based on different combinations of three pressure gauge holes;

[0097] (9.1) The weighting coefficients are determined according to the following formula:

[0098] When the pressure testing port combination contains p1,

[0099]

[0100] When the pressure test port combination does not include p1,

[0101]

[0102] in, is the average weighting coefficient, w(i,j,k) is the weighting coefficient of the combination of pressure test holes pi,pj,pk, where i,j,k are the pressure test hole numbers;

[0103] (10) If step (9) is true, the added pressure test hole is not faulty, and step (11) is executed; if step (9) is not true, the newly added pressure test hole is removed.

[0104] (11) Based on steps (4)-(10), calculate the local angle of attack and local sideslip angle based on the initial judgment that there is no fault in the pressure test hole;

[0105] (12) Determine the inlet injection angle of the pressure measuring hole based on the local angle of attack and local sideslip angle determined in step (11);

[0106] (12.1) The incoming radiation angle is determined according to the following formula,

[0107] cosθ i =cosα e cosβ e cosλ i +sinβ e sinφ i sinλ i +sinα e cosβ e cosφ i sinλ i

[0108] Among them, α e ,β e These are the local angle of attack and the local sideslip angle, respectively; φ i , λ i The circumferential angle and cone angle at the i-th pressure measurement point;

[0109] (13) Based on the inflow angle of the pressure measuring orifice determined in step (12) and the pressure value of the corresponding pressure measuring orifice in step (1), calculate the solution value χP of all odd and even equations based on the three different combinations of pressure measuring orifices, and compare it with the defined deviation threshold δ to determine whether it meets the requirements.

[0110] χP≤δ

[0111] Where χ is the position coefficient matrix of three different pressure measuring holes, P is the pressure value matrix of three different pressure measuring holes, and δ is the defined deviation threshold;

[0112] (13.1) The solution value χP of the odd-even equation is determined as follows:

[0113] χp=[cos 2 θ k -cos 2 θ j cos 2 θ i -cos 2 θ k cos 2 θ j -cos 2 θ i ][p i ,p j ,p k ] T

[0114] Where, α e ,β e These are the effective angle of attack and effective sideslip angle, respectively; φ i , λ i The circumferential angle and cone angle at the i-th pressure measurement point;

[0115] (13.2) The deviation threshold δ is determined as follows:

[0116] δ = max{δ1,δ2,δ3}

[0117] in,

[0118]

[0119]

[0120]

[0121] Where α, β, and Ma are the state parameters in the numerical modeling process, representing the angle of attack, sideslip angle, and Mach number, respectively. i (i = 1 to 11) represents the pressure value;

[0122] (14) If step (13) is true, proceed to step (17); if step (13) is false, proceed to step (15).

[0123] (15) Based on the odd-even equation established by the rough set theory reduction, determine all pressure measuring holes that appear in the pressure measuring hole combinations that do not satisfy step (13).

[0124] (15.1) The method for establishing the parity equation based on rough set theory through reduction is as follows:

[0125] Define the parameter κ(t).

[0126] If κ(t=(i,j,k),i≠j≠k)==0 is satisfied, the pressure measuring hole is normal;

[0127] If κ(t=i)==1&&κ(t≠i)==0, the pressure measuring hole pi is faulty;

[0128] If κ(t=i,t=j)==1&&κ(t≠i,t≠j)==0(i≠j), then the pressure measuring holes pi and pj are faulty;

[0129] Where t represents the number determined based on all different pressure measuring hole combinations, t=(i,j,k), i≠j≠k represents the number determined based on all different pressure measuring hole combinations pi, pj, pk, t=i represents the number of the combination containing pressure measuring hole pi in all different pressure measuring hole combinations, t≠i represents the number of the combination not containing pressure measuring hole pi in all different pressure measuring hole combinations, t=j represents the number of the combination containing pressure measuring hole pj in all different pressure measuring hole combinations, t≠j represents the number of the combination not containing pressure measuring hole pj in all different pressure measuring hole combinations, i,j,k are different pressure measuring hole numbers; if the solution value of the odd-even equation of the pressure measuring hole combination pi,pj,pk does not satisfy the relationship in step (9), κ(t)=1 is defined; if it satisfies the relationship in step (9), κ(t)=0 is defined. (16) Remove the pressure measuring holes determined in step (15);

[0130] (17) Calculate the Mach number, angle of attack, sideslip angle, static pressure and dynamic pressure flight parameters based on the pressure data obtained from the pressure measuring hole where there is no fault.

[0131] Figure 3 Example of determining a fault in a pressure testing port using the fault diagnosis method of the present invention; Figure 4 The figure shows a comparison between the angle of attack obtained when a fault is determined in a pressure measuring hole using the fault diagnosis method of the present invention and the actual value of the flight trajectory. As can be seen from the figure, the angle of attack obtained when a fault is determined in a pressure measuring hole using the fault diagnosis method of the present invention matches the actual trajectory well, and the actual error distribution is small.

[0132] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A fault diagnosis method for an embedded flight parameter sensing system for a blunt-nosed aircraft, wherein the embedded flight parameter sensing system for a blunt-nosed aircraft has at least six pressure measurement holes configured in a specific area on the leading edge surface of the blunt nose of the aircraft, characterized in that... The steps are as follows: (1) The maximum and minimum values ​​of each pressure measurement hole within the flight envelope were determined using numerical modeling. (2) Determine whether the pressure data collected by all pressure measuring holes are within their corresponding maximum and minimum value ranges. If they are, proceed to step (3); otherwise, remove the pressure measuring holes that are not within the range as faulty pressure measuring holes. (3) Select any three different pressure measuring holes arranged along the longitudinal centerline of the angle of attack, and calculate the local angle of attack under different combinations using the three-point algorithm based on all different combinations; (4) Based on all the calculated local angle of attack values, use weighted average estimation to calculate the mean of the angle of attack estimate, and determine whether the maximum value among the differences between all local angles of attack and the mean is not greater than the angle of attack deviation threshold. If the relationship is not established, proceed to step (5); if it is established, proceed to step (6). (5) Eliminate faulty pressure test holes one by one, calculate the local angle of attack of all combinations of pressure test holes, repeat step (4) until it is established, remove the faulty pressure test holes, and execute step (6). (6) According to the pressure measuring hole number, the pressure measuring holes configured on the transverse centerline are added one by one in a single positive sequence. Based on all the three different combinations of pressure measuring holes, the local sideslip angle is calculated using a three-point algorithm. (7) Based on all local sideslip angle values, calculate the estimated mean of sideslip angle using weighted average estimation. Determine whether the maximum value among the differences between all local sideslip angles and the estimated mean of sideslip angle is not greater than the sideslip angle deviation threshold. If the relationship is not established, remove the newly added pressure test hole. If the relationship is established, the added pressure test hole is not faulty and proceed to step (8). (8) Based on steps (4)-(7), calculate the local angle of attack and local sideslip angle based on the preliminary judgment that there is no fault in the pressure test hole, and determine the incoming injection angle of the fault-free pressure test hole; (9) Based on the injection angle of the pressure measuring hole determined in step (8) and the pressure value collected by the corresponding pressure measuring hole, calculate the solution value of all odd and even equations based on the three different combinations of pressure measuring holes and compare it with the defined deviation threshold. If the solution value is greater than the defined deviation threshold, proceed to step (10); otherwise, proceed directly to step (11). (10) Based on the odd-even equation established by the rough set theory reduction, identify and remove all pressure measuring holes that appear in all combinations of pressure measuring holes that do not satisfy the relationship in step (10). In step (10), based on the parity equation established by rough set theory reduction, all pressure gauges that appear in all combinations of pressure gauges that do not satisfy the relationship in step (10) are identified as follows: Define parameters If satisfied The pressure test port is normal; If satisfied The pressure test port PI is faulty; If satisfied The pressure testing ports pi and pj are faulty. Where t represents the number determined based on all different combinations of pressure measuring holes, This indicates the numbering based on all different pressure gauge combinations pi, pj, pk. This indicates that all different pressure gauge combinations contain the combination number of pressure gauge pi. This indicates the number of the combination that does not contain pressure gauge pi among all different pressure gauge combinations. This indicates that the combination number containing pressure gauge pj is present in all different pressure gauge combinations. This indicates the number of the combination that does not contain pressure gauge pj among all different pressure gauge combinations, where i, j, k are different pressure gauge numbers; the solution value of the odd-even equation of the pressure gauge combinations pi, pj, pk does not satisfy the relationship in step (9), and is defined as follows. ; satisfying the relationship in step (9), define ; (11) Calculate the Mach number, angle of attack, sideslip angle, static pressure and dynamic pressure flight parameters based on the pressure data obtained from the pressure measurement holes that are free of faults.

2. The method according to claim 1, characterized in that: The positions of the at least 6 pressure measuring holes are as follows: The pressure measuring hole located at the stagnation point has a circumferential angle of 0° and a conical angle of 0°. The pressure measuring hole is located on the lower surface of the longitudinal centerline, with a circumferential angle of 0° and a cone angle between 30° and 60°. The pressure measuring hole is located on the upper surface of the longitudinal centerline, with a circumferential angle of 180° and a cone angle between 30° and 60°. The pressure measuring hole is located on the left surface of the transverse centerline, with a circumferential angle of 90° and a cone angle between 30° and 60°. The pressure measuring hole is located on the right surface of the transverse centerline, with a circumferential angle of 270° and a cone angle between 30° and 60°.

3. The method according to claim 2, characterized in that: Deviation threshold in step (9) The determination method is as follows: in, Where α, β, and Ma are the state parameters in the numerical modeling process, namely the angle of attack, sideslip angle, and Mach number, respectively. The pressure values ​​collected from the pressure measuring hole.

4. The method according to claim 1, characterized in that: The weighting coefficients in the weighted averages of steps (4) and (7) are set as follows: When the pressure testing port combination contains stagnation points, When the pressure testing port combination does not include stagnation points, in, The average weighting coefficient. represents the weighting coefficients for the combination of pressure test holes pi, pj, pk, where i, j, k are the pressure test hole numbers.

5. The method according to claim 1, characterized in that: In step (3), any three different pressure measuring holes are selected along the longitudinal centerline, and the local angle of attack is calculated based on all different combinations using a three-point algorithm. The three-point algorithm means that by using only three different combinations of pressure measuring holes located on the longitudinal centerline, the analytical solution of the local angle of attack is obtained according to the positional relationship of the pressure measuring holes and the pressure difference relationship between any two pressure measuring holes.

6. The method according to claim 1, characterized in that: In step (5), the faulty pressure test hole is determined by the reverse elimination method according to the pressure test hole number. The reverse elimination method means that the pressure value of the corresponding pressure test hole is added one by one in descending order according to the selected pressure test hole number to calculate the local angle of attack, and it is judged whether the relationship in step (4) is satisfied. If the relationship is not established, the corresponding pressure test hole is the faulty pressure test hole.

7. The method according to claim 1, characterized in that: The solution value of the odd-even equation in step (9) The determination method is as follows: in, The solution value for the odd / even equation. , , Let pi, pj, pk be the inflow angles of the pressure measuring holes. Here are the pressure values ​​for the pressure measuring holes pi, pj, and pk, where i, j, and k are the hole numbers.

8. The method according to claim 1 or 7, characterized in that: The formula for calculating the incoming flow angle in step (8) is as follows: in, , These are the local angle of attack and local sideslip angle calculated in step (8), respectively; , Let be the circumferential angle and the conical angle at the pi-th pressure measurement point.

9. The method according to claim 1, characterized in that: The deviation threshold determined in step (9) In practical engineering applications, Take 1.1 to 1.3 times the theoretical design value.

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