CN114235420A - 4-redundancy-based aeroengine high-pressure rotating speed signal voting method - Google Patents
4-redundancy-based aeroengine high-pressure rotating speed signal voting method Download PDFInfo
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Abstract
The application provides an aeroengine high-pressure rotating speed signal voting method based on 4 redundancies, which comprises the following steps: acquiring two high-pressure rotating speed acquisition signals of the high-pressure rotor through two rotating speed sensors; obtaining a first high-pressure rotating speed analog signal by measuring fuel input quantity, and obtaining a second high-pressure rotating speed analog signal by measuring low-pressure rotating speed, engine inlet temperature and flying speed; determining the absolute value of the difference between any two signals, judging that the signal state is abnormal when the absolute value of the difference between one signal and the rest three signals is greater than a preset first error threshold, and otherwise, judging that the signal state is normal; carrying out first round voting on the normal signals to obtain a first round voting value of the signals; determining the absolute value of the residual between the signal and the first voting value, judging whether the absolute value of the residual is greater than a second error threshold, and if the absolute value of the residual is greater than the second error threshold, the signal is abnormal, otherwise the signal is normal; and carrying out second round voting on the signals to obtain a second round voting value of the signals.
Description
Technical Field
The application belongs to the technical field of aero-engine temperature measurement, and particularly relates to a 4-redundancy-based aero-engine high-pressure rotating speed signal voting method.
Background
The rotation speed of the aircraft engine determines the mass flow rate of air passing through the combustion chamber, so that the thrust of the aircraft engine is determined, and the rotation speed is one of the most important signals of an aircraft engine control and health management system.
Generally, important signals such as high-pressure rotating speed of an aircraft engine and the like can be acquired by using a dual-redundancy sensor. To improve engine reliability without additional weight and cost, a digital electronic controller or health management computer may be loaded with a real-time model for high pressure rotational speed. However, even if the normal rotating speed sensors with the same redundancy of the aircraft engine have slight signal difference, the difference between the soft redundancy signal and the measured signal of the hard redundancy of the sensor is larger, so that the fusion voting of the normal and abnormal high-voltage rotating speed signals is very difficult.
When the control system votes by the dual-redundancy high-voltage rotating speed sensors, if the difference of the measured values of the dual-channel sensors is large, at least one sensor is in fault, but the fault channel cannot be distinguished, and the reliability of the engine is insufficient. If the control system has triple redundancy or quad redundancy physical sensors, the reliability of the system can be obviously improved, but the problems of cost, weight, space and the like of the aircraft engine can be caused by excessive hardware. And the control system is provided with a dual-redundancy high-pressure rotating speed sensor and an airborne real-time soft-redundancy high-pressure rotating speed signal at the same time, so that the reliability of the engine can be improved.
Taking the 3-redundancy shown in fig. 1 as an example (the principle and process of the 4-redundancy signal are the same), the voting step is usually: firstly, sorting signals of a sensor with the rotating speed of N2 (namely the rotating speed of a high-pressure rotor), taking a middle value Median as a reference value, comparing a maximum value Max and a minimum value Min with the reference value, and if the maximum value Max and the minimum value Min are not out of range, inputting a voting signal to a controller to be (S1+ S2+ S3)/3; if the acquisition value of the sensor exceeds the threshold value, a plurality of control cycles are required for confirmation, and when the fault exits, more than one control cycles are still required for confirmation, so that the confirmation cycle is longer. Although this may significantly reduce false alarm failures due to noise effects, the use of this logic will subject the voted value to the fault value before the faulty sensor is identified, and the voted value will be subject to large disturbances and discontinuities when the fault is isolated, which will result in large changes in engine conditions after feedback to the control system.
Disclosure of Invention
The application aims to provide a voting method for a high-pressure rotating speed signal of an aircraft engine based on 4 redundancy, so as to solve or alleviate at least one problem in the background art.
The technical scheme provided by the application is as follows: a4-redundancy-based aircraft engine high-pressure rotating speed signal voting method comprises the following steps:
acquiring a first high-voltage rotating speed acquisition signal and a second high-voltage rotating speed acquisition signal of the high-voltage rotor through a first rotating speed sensor and a second rotating speed sensor;
establishing a relation between fuel input quantity and high-pressure rotating speed of an engine, obtaining a first high-pressure rotating speed analog signal by measuring the fuel input quantity, establishing a relation between low-pressure rotating speed, engine inlet temperature and flying speed and the high-pressure rotating speed of the engine, and obtaining a second high-pressure rotating speed analog signal by measuring the low-pressure rotating speed, the engine inlet temperature and the flying speed;
determining the absolute value of the difference between any two signals, judging that the signal state is abnormal when the absolute value of the difference between one signal and the rest three signals is greater than a preset first error threshold, and otherwise, judging that the signal state is normal;
carrying out first round voting on the normal signals to obtain a first round voting value of the signals;
determining a residual absolute value of the signal and the first voting value, judging whether the residual absolute value is greater than a second error threshold, if so, determining that the signal is abnormal, otherwise, determining that the signal is normal;
and carrying out second voting on the signals to obtain a second voting value of the signals.
Further, when all the signal states of the 4 redundancies are abnormal, the fuel actuating mechanism is arranged at a system safety protection position.
Further, the maximum relative error between the collected signals of the first rotating speed sensor and the second rotating speed sensor and the actual rotating speed is E1, the maximum error between the first rotating speed analog signal and the actual rotating speed is E2, and the maximum error between the second rotating speed analog signal and the actual rotating speed is E3.
Further, the first error threshold is a sum of maximum relative errors of each pair of signals.
Further, the method for calculating the first voting value of the signal comprises the following steps:
wherein the content of the first and second substances,
for the ith signal SiWeight of (C)iAnd n is the confidence of the ith signal, and is the number of the residuals, namely n is 4.
Further, the confidence of the i-th signal is CiComprises the following steps:
in the formula, DijIs as followsiThe absolute value of the difference between one signal and the other jth signal is positive.
Further, the method for calculating the second voting value of the signal comprises the following steps:
in the formula (I), the compound is shown in the specification,
is the voting weight, k, of the ith signaliIs the state of the ith signal, DiFor the ith redundancy signal SiAnd Sb1N is the number of residuals, n is 4, and epsilon is a positive number.
Further, the state of the signal satisfies:
the aero-engine high-pressure rotating speed signal voting method based on the redundancy of 4 has the following advantages:
1) the method of introducing confidence coefficient is applied to voting of the high-pressure rotating speed signal of the engine, so that the uncertainty of information of the engine in a plurality of data generated by hard redundancy and soft redundancy is reduced, the accuracy and precision of the high-pressure rotating speed signal are improved, and the reliability which is difficult to obtain by a dual-redundancy sensor is obtained.
2) A two-wheel voting method is introduced, a confidence coefficient method is combined, the influence of the introduction of fault signals in a fault confirmation period on the control quality of the aero-engine is reduced, and the problem of signal mutation after redundancy voting caused by fault isolation of the sensors can be solved.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a schematic diagram of a voting process of a high-pressure rotating speed 3 redundancy of an aircraft engine in the prior art.
FIG. 2 is a schematic diagram of input and output signals of the high-pressure rotating speed voting system of the aircraft engine.
FIG. 3 is a schematic diagram of an aircraft engine high-pressure rotating speed 4 redundancy signal voting process.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
The application provides a 4-redundancy-based aeroengine high-pressure rotating speed signal voting method which comprises 2 sensor similar hard redundancy signals and 2 non-similar soft redundancy signals and is used for remarkably improving the reliability of an engine without increasing extra hard redundancy. According to the method, the problem of long fault confirmation period is solved by using a single control period two-wheel voting end method, a signal confidence coefficient concept is introduced into signal voting, if the sensor continuously breaks down from a certain moment, the confidence coefficient of the sensor is gradually reduced to 0, so that the proportion of the fault signal in the voting value is gradually reduced to 0, the voting value can be considered to be always accurate, and the problem of signal mutation after redundancy voting caused by fault isolation of the sensor is effectively restrained and eliminated.
As shown in fig. 2, the input of the aircraft engine high-pressure rotation speed signal voting system is composed of four signals representing the high-pressure physical rotation speed (N2) of the engine, and specifically includes: the engine speed simulation system comprises a signal S1 acquired by an N2 speed sensor 1, a signal S2 acquired by an N2 speed sensor 2, an N2 speed simulation signal S3 acquired by an engine N2 model 1 constructed by a fuel metering valve linear displacement sensor, and an N2 speed simulation signal S4 acquired by an engine N2 model 2 constructed by communication data of an N1 speed voting value, an engine inlet temperature voting value and a Mach number voting value.
As shown in fig. 3, the voting process of the aero-engine high-pressure rotating speed signal based on the 4-redundancy signal of the present application is as follows:
first, first round watch block
The 4 input signals output the states of the 4 input signals through the comparison module 1. The maximum relative error between the collected value of the rotating speed sensor and the real rotating speed value is E1, similarly, the maximum error between the rotating speed simulation value of the engine N2 model 1 and the real rotating speed value is E2, and the maximum error between the rotating speed simulation value of the engine N2 model 2 and the real rotating speed value is E3. The comparison module 1 sets a threshold value of error between the signal comparison pairs in advance, as shown in table 1, where the threshold value of error is the sum of the maximum relative errors of each pair of signals.
Table 1 comparison of input signal pair comparison thresholds in module 1
| Input signal comparison pair | Error threshold [% ]] |
| S1 and S2 | E1+E1 |
| S1 and S3 | E1+E2 |
| S1 and S4 | E1+E3 |
| S2 and S3 | E1+E2 |
| S2 and S4 | E1+E3 |
| S3 and S4 | E2+E3 |
When the absolute value of the difference between the acquired value or analog value of a certain signal and the acquired values or analog values of the other three signals is greater than the error threshold (i.e., when the absolute value of the difference between the three comparison pairs containing a certain signal is greater than the error threshold), the signal state is abnormal (abnormal-0), otherwise, the signal state is normal (normal-1). Normal signals can be input into the voter 1 through the threshold gate 1 module, and abnormal signals cannot pass through.
When the 4 signal states are all abnormal, the fuel actuating mechanism is arranged at the system safety protection position.
The following introduces a confidence concept into the signal voting method:
the signal vote value of voter 1 is:
wherein the content of the first and second substances,
refers to the ith redundancy signal SiWeight of (1), Sb1And n is the number of the residuals, wherein n is 4.
Suppose that the absolute values of the differences between the ith redundancy signal and the other jth redundancy signals are DijThen the ith redundancy confidence coefficient CiComprises the following steps:
in the formula, ε is generally a very small positive number.
Second and second round watch block
Input signal SiBy means of the signal S in the voter 1b1Generating a residual absolute value Ri(i is 1,2,3,4), input into the comparison module 2, and respectively compared with the preset error threshold eiFor comparison, as shown in table 2.
Table 1 comparison of input signal pair comparison thresholds in module 2
| Absolute value of signal residual | Error threshold value: |
| R1 | e1 |
| R2 | e2 |
| R3 | e3 |
| R4 | e4 |
signal state is represented by Vi(i ═ 1,2,3,4) indicates that when the absolute value of the residual is greater than the error threshold, the signal is abnormal (abnormal-0), otherwise the signal is normal (normal-1). Vi(i ═ 1,2,3,4) value is input into signal SiCommunicating with the voter 2 and then obtaining a second tier vote value.
The calculation method of the voting signals in the voter 2 comprises the following steps:
wherein the content of the first and second substances,
is the weight of the voting of the signal,
Diis the ith redundancy signal SiAnd Sb1N is the number of residuals, in this method, n is 4, and epsilon is generally a very small positive number.
The aero-engine high-pressure rotating speed signal voting method based on the redundancy of 4 has the following advantages:
1) the method of introducing confidence coefficient is applied to voting of the high-pressure rotating speed signal of the engine, so that the uncertainty of information of the engine in a plurality of data generated by hard redundancy and soft redundancy is reduced, the accuracy and precision of the high-pressure rotating speed signal are improved, and the reliability which is difficult to obtain by a dual-redundancy sensor is obtained.
2) A two-wheel voting method is introduced, a confidence coefficient method is combined, the influence of the introduction of fault signals in a fault confirmation period on the control quality of the aero-engine is reduced, and the problem of signal mutation after redundancy voting caused by fault isolation of the sensors can be solved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A4-redundancy-based aircraft engine high-pressure rotating speed signal voting method is characterized by comprising the following steps:
acquiring a first high-voltage rotating speed acquisition signal and a second high-voltage rotating speed acquisition signal of the high-voltage rotor through a first rotating speed sensor and a second rotating speed sensor;
establishing a relation between fuel input quantity and high-pressure rotating speed of an engine, obtaining a first high-pressure rotating speed analog signal by measuring the fuel input quantity, establishing a relation between low-pressure rotating speed, engine inlet temperature and flying speed and the high-pressure rotating speed of the engine, and obtaining a second high-pressure rotating speed analog signal by measuring the low-pressure rotating speed, the engine inlet temperature and the flying speed;
determining the absolute value of the difference between any two signals, judging that the signal state is abnormal when the absolute value of the difference between one signal and the rest three signals is greater than a preset first error threshold, and otherwise, judging that the signal state is normal;
carrying out first round voting on the normal signals to obtain a first round voting value of the signals;
determining a residual absolute value of the signal and the first voting value, judging whether the residual absolute value is greater than a second error threshold, if so, determining that the signal is abnormal, otherwise, determining that the signal is normal;
and carrying out second voting on the signals to obtain a second voting value of the signals.
2. A 4-redundancy-based aircraft engine high-pressure rotating speed signal voting method according to claim 1, characterized in that when all the signal states of the 4-redundancy are abnormal, the fuel actuator is placed in a system safety protection position.
3. The 4-redundancy-based aircraft engine high-pressure rotating speed signal voting method according to claim 1, wherein the maximum relative error between the collected signals of the first rotating speed sensor and the second rotating speed sensor and the actual rotating speed is E1, the maximum error between the first rotating speed simulation signal and the actual rotating speed is E2, and the maximum error between the second rotating speed simulation signal and the actual rotating speed is E3.
4. A 4-redundancy-based aircraft engine high-pressure rotational speed signal voting method according to claim 3, wherein the first error threshold is the sum of the maximum relative errors of each pair of signals.
5. A voting method for a high-pressure rotating speed signal of an aircraft engine based on 4 redundancy, according to claim 4, characterized in that the first voting value of the signal is calculated by:
wherein the content of the first and second substances,
for the ith signal SiWeight of (C)iAnd n is the confidence of the ith signal, and is the number of the residuals, namely n is 4.
6. 4-redundancy-based aircraft engine height according to claim 5The method for voting the signal of the pressure and the rotating speed is characterized in that the redundancy confidence coefficient C of the ith signaliComprises the following steps:
in the formula, DijIs as followsiThe absolute value of the difference between one signal and the other jth signal is positive.
7. A voting method for a high-pressure rotating speed signal of an aircraft engine based on 4 redundancy, according to claim 6, wherein the second voting value of the signal is calculated by:
in the formula (I), the compound is shown in the specification,
is the voting weight, k, of the ith signaliIs the state of the ith signal, DiFor the ith redundancy signal SiAnd Sb1N is the number of residuals, n is 4, and epsilon is a positive number.
8. A 4-redundancy-based aircraft engine high-pressure rotating speed signal voting method according to claim 7, wherein the states of the signals satisfy:
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114893302A (en) * | 2022-04-14 | 2022-08-12 | 北京动力机械研究所 | Small turbofan engine rotating speed fault judging method and redundancy control method |
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