CN114235420B - Aeroengine high-voltage rotating speed signal voting method based on 4 redundancy - Google Patents
Aeroengine high-voltage rotating speed signal voting method based on 4 redundancy Download PDFInfo
- Publication number
- CN114235420B CN114235420B CN202111432894.8A CN202111432894A CN114235420B CN 114235420 B CN114235420 B CN 114235420B CN 202111432894 A CN202111432894 A CN 202111432894A CN 114235420 B CN114235420 B CN 114235420B
- Authority
- CN
- China
- Prior art keywords
- signal
- rotating speed
- voting
- redundancy
- signals
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The high-voltage rotating speed signal voting method based on the 4 redundancy for the aero-engine provided by the application comprises the following steps: acquiring two high-voltage rotating speed acquisition signals of the high-voltage rotor through two rotating speed sensors; obtaining a first high-pressure rotating speed simulation signal by measuring the fuel input quantity, and obtaining a second high-pressure rotating speed simulation signal by measuring the low-pressure rotating speed, the engine inlet temperature and the flying speed; determining the absolute value of the difference value of any two signals, judging that the signal state is abnormal when the absolute value of the difference value of one signal and the absolute values of the other three signals are larger than a preset first error threshold value, otherwise, judging that the signal state is normal; carrying out first-round voting on the normal signals to obtain first-round voting values of the signals; determining the residual absolute value of the signal and the first round of voting value, judging whether the residual absolute value is larger than a second error threshold value, if so, the signal is abnormal, otherwise, the signal is normal; and carrying out second-round voting on the signals to obtain second-round voting values of the signals.
Description
Technical Field
The application belongs to the technical field of aeroengine temperature measurement, and particularly relates to a 4-redundancy-based aeroengine high-voltage rotating speed signal voting method.
Background
The rotational speed of the aircraft engine determines the mass air flow through the combustion chamber and thus the thrust level of the aircraft engine, which is one of the most important signals of the aircraft engine control and health management system.
Usually, important signals such as high-pressure rotating speed of an aero-engine can be acquired by adopting a dual-redundancy sensor. In order to increase engine reliability without adding additional weight and cost, a digital electronic controller or health management computer would be loaded with a real-time model of high pressure rotational speed. However, even if the normal rotation speed sensor with the same redundancy is provided with a small signal difference, the difference between the soft redundancy signal and the actual measurement signal of the hard redundancy of the sensor is larger, which makes the fusion voting of the normal and abnormal high-pressure rotation speed signals very difficult.
When the control system double-redundancy high-pressure rotating speed sensor votes, if the measured values of the double-channel sensor differ greatly, at least one sensor is required to be failed, but the failed channel cannot be distinguished, and the reliability of the engine is insufficient. If the control system has a physical sensor with triple redundancy or four redundancy, the reliability of the system can be obviously improved, but excessive hardware can introduce problems of cost, weight, space and the like of the aero-engine. And the control system is provided with a dual-redundancy high-voltage rotating speed sensor and an onboard real-time soft redundancy high-voltage rotating speed signal, so that the reliability of the engine can be improved.
Taking the 3-redundancy example shown in fig. 1 (4-redundancy signal principle and process are the same), the general voting steps are: firstly, sequencing signals of an N2 rotating speed (namely the rotating speed of a high-voltage rotor) sensor, taking an intermediate 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 do not exceed the range, inputting voting signals into a controller as (S1+S2+S3)/3; if the sensor acquisition value exceeds the threshold value, a plurality of control periods are needed for confirmation, and a plurality of control periods are still needed for confirmation when the fault exits, so that the confirmation period is long. Although the false alarm fault caused by noise can be remarkably reduced, the voting value is influenced by the fault value by adopting the logic before the fault sensor is not confirmed, and the voting value generates larger disturbance and discontinuity when isolating the fault, and the engine state is changed greatly after the false alarm fault is fed back to the control system.
Disclosure of Invention
The purpose of the application is to provide a high-pressure rotating speed signal voting method of an aeroengine based on 4 redundancy, so as to solve or alleviate at least one problem in the background art.
The technical scheme that this application provided is: an aeroengine high-pressure rotational speed signal voting method based on 4 redundancy, the method comprising:
acquiring a first high-pressure rotating speed acquisition signal and a second high-pressure rotating speed acquisition signal of the high-pressure rotor through a first rotating speed sensor and a second rotating speed sensor;
constructing a relation between fuel input quantity and high-pressure rotating speed of an engine, obtaining a first high-pressure rotating speed simulation signal by measuring the fuel input quantity, constructing 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 simulation signal by measuring the low-pressure rotating speed, the engine inlet temperature and the flying speed;
determining the absolute value of the difference value of any two signals, judging that the signal state is abnormal when the absolute value of the difference value of one signal and the absolute values of the other three signals are larger than a preset first error threshold value, otherwise, judging that the signal state is normal;
carrying out first-round voting on the normal signals to obtain first-round voting values of the signals;
determining the residual absolute value of a signal and a first round of voting value, judging whether the residual absolute value is larger than a second error threshold value, and if so, determining that the signal is abnormal, otherwise, determining that the signal is normal;
and carrying out second-round voting on the signals to obtain second-round voting values of the signals.
Further, when all 4 signal states of the 4 redundancy are abnormal, the fuel executing mechanism is placed in a system safety protection position.
Further, the maximum relative error between the acquired signals of the first rotating speed sensor and the second rotating speed sensor and the real rotating speed is E1, the maximum error between the first rotating speed analog signal and the real rotating speed is E2, and the maximum error between the second rotating speed analog signal and the real rotating speed is E3.
Further, the first error threshold is a sum of maximum relative errors for each pair of signals.
Further, the calculation method of the first round of voting values of the signals comprises the following steps:
wherein,for the ith signal S i Weight of C i For the redundancy confidence of the i-th signal, n is the redundancy number, i.e., n=4.
Further, the redundancy confidence C of the ith signal i The method comprises the following steps:
wherein D is ij And if the absolute value of the difference between the ith signal and the other jth signals is the absolute value, epsilon is a positive number.
Further, the calculation method of the second round of voting values of the signals comprises the following steps:
in the method, in the process of the invention,is the voting weight, k, of the ith signal i Is the state of the ith signal, D i For the ith redundancy signal S i And S is equal to b1 N is the number of residuals, n=4, and ε is a positive number.
Further, the state of the signal satisfies:
the high-voltage rotating speed signal voting method for the aero-engine based on 4 redundancy has the following advantages:
1) The method for introducing the confidence coefficient is applied to the voting of the high-pressure rotating speed signals of the engine, so that the uncertainty of information in a plurality of data generated by the engine in the hard redundancy and the soft redundancy is reduced, the accuracy and the precision of the high-pressure rotating speed signals are improved, and the reliability which is difficult to obtain by a dual-redundancy sensor is obtained.
2) The two-wheel voting method is introduced, the confidence method is combined, the influence of the introduction of fault signals in the fault confirmation period on the control quality of the aeroengine is reduced, and the problem of abrupt signal change after redundant voting caused by the fault isolation of the sensor can be restrained.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
FIG. 1 is a schematic diagram of a 3-redundancy voting process for high-pressure rotational speed of an aircraft engine in the prior art.
FIG. 2 is a schematic diagram of input and output signals of the high-pressure rotational speed voting system of the aircraft engine.
FIG. 3 is a schematic diagram of the voting process of the high-pressure rotating speed 4 redundancy signal of the aero-engine.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
The application provides a high-voltage rotating speed signal voting method of an aeroengine based on 4 redundancy, which comprises 2 similar hard redundancy signals and 2 dissimilar soft redundancy signals of sensors and is used for remarkably improving the reliability of the engine without adding extra hard redundancy. The method solves the problem of long fault confirmation period by utilizing a method of a single control period two-round voting end, introduces a signal confidence degree concept into signal voting, and if a sensor continuously breaks down from a certain moment, the confidence degree of the sensor gradually decreases 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 accurate all the time, and the problem of signal mutation after redundant voting caused by fault isolation of the sensor is effectively restrained and eliminated.
As shown in fig. 2, the input of the aero-engine high-pressure rotational speed signal voting system consists of four signals representing the high-pressure physical rotational speed (N2) of the engine, and specifically comprises: the system comprises a signal S1 collected by an N2 rotation speed sensor 1, a signal S2 collected by an N2 rotation speed sensor 2, an N2 rotation speed analog signal S3 obtained by an engine N2 model 1 constructed by a fuel metering valve linear displacement sensor and an N2 rotation speed analog signal S4 obtained by an engine N2 model 2 constructed by communication data of an N1 rotation 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 high-pressure rotating speed signal of the aeroengine based on the 4-redundancy signal is as follows:
1. first round voting
The 4 input signals output the states of the 4 input signals through the comparison module 1. The maximum relative error between the acquisition value of the rotation speed sensor and the real rotation speed value is E1, similarly, the maximum error between the rotation speed simulation value of the engine N2 model 1 and the real rotation speed value is E2, and the maximum error between the rotation speed simulation value of the engine N2 model 2 and the real rotation speed value is E3. The comparison module 1 presets an error threshold between signal comparison pairs, as shown in table 1, where the error threshold is the sum of the maximum relative errors of each pair of signals.
Table 1 compares input signal pairing comparison threshold 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 comprising the certain signal is greater than the error threshold), the signal state is abnormal (abnormal-0), otherwise the signal state is normal (normal-1). The normal signal can be input into the voter 1 through the threshold gate 1 module, and the abnormal signal cannot pass.
When all 4 signal states are abnormal, the fuel executing mechanism is arranged at a system safety protection position.
The confidence concept is introduced into the signal voting method as follows:
the signal vote value of voter 1 is:
wherein,refers to the ith redundancy signal S i Weights of S b1 N is the number of residuals for the first round of vote values of the signal, in this method n=4.
Assuming that the absolute values of the differences between the ith and the other jth redundancy signals are D ij Then the ith redundancy confidence C i The method comprises the following steps:
where ε is typically a very small positive number.
2. Second round voting
Input signal S i By and-voter 1 signal S b1 Generating residual absolute value R i (i=1, 2,3, 4) is input into the comparison module 2 and is respectively matched with a preset error threshold e i Comparison is shown in table 2.
Table 1 compares input signal pair comparison threshold in module 2
| Absolute value of signal residual | Error threshold: |
| R 1 | e 1 |
| R 2 | e 2 |
| R 3 | e 3 |
| R 4 | e 4 |
the signal state is defined by V i (i=1, 2,3, 4) means that the signal is abnormal (abnormal-0) when the absolute value of the residual is greater than the error threshold, otherwise the signal is normal (normal-1). V (V) i The (i=1, 2,3, 4) value will input signal S i And the voter 2, and then a second round of vote values are obtained.
The method for calculating the signals in the voter 2 comprises the following steps:
wherein,is the signal voting weight,/>D i Refers to the ith redundancy signal S i And S is equal to b1 N is the number of residuals, in this method n=4, epsilon is typically a very small positive number.
The high-voltage rotating speed signal voting method for the aero-engine based on 4 redundancy has the following advantages:
1) The method for introducing the confidence coefficient is applied to the voting of the high-pressure rotating speed signals of the engine, so that the uncertainty of information in a plurality of data generated by the engine in the hard redundancy and the soft redundancy is reduced, the accuracy and the precision of the high-pressure rotating speed signals are improved, and the reliability which is difficult to obtain by a dual-redundancy sensor is obtained.
2) The two-wheel voting method is introduced, the confidence method is combined, the influence of the introduction of fault signals in the fault confirmation period on the control quality of the aeroengine is reduced, and the problem of abrupt signal change after redundant voting caused by the fault isolation of the sensor can be restrained.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in 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. An aeroengine high-pressure rotating speed signal voting method based on 4 redundancy, which is characterized by comprising the following steps:
acquiring a first high-pressure rotating speed acquisition signal and a second high-pressure rotating speed acquisition signal of the high-pressure rotor through a first rotating speed sensor and a second rotating speed sensor;
constructing a relation between fuel input quantity and high-pressure rotating speed of an engine, obtaining a first high-pressure rotating speed simulation signal by measuring the fuel input quantity, constructing 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 simulation signal by measuring the low-pressure rotating speed, the engine inlet temperature and the flying speed;
determining the absolute value of the difference value of any two signals, judging that the signal state is abnormal when the absolute value of the difference value of one signal and the absolute values of the other three signals are larger than a preset first error threshold value, otherwise, judging that the signal state is normal;
carrying out first-round voting on the normal signals to obtain first-round voting values of the signals;
determining the residual absolute value of a signal and a first round of voting value, judging whether the residual absolute value is larger than a second error threshold value, and if so, determining that the signal is abnormal, otherwise, determining that the signal is normal;
and carrying out second-round voting on the signals to obtain second-round voting values of the signals.
2. The 4-redundancy-based high-pressure rotational speed signal voting method for an aircraft engine according to claim 1, wherein when all of 4 signal states of the 4 redundancy are abnormal, the fuel actuator is placed in a system safety protection position.
3. The 4-redundancy-based aeroengine high-voltage rotating speed signal voting method according to claim 1, wherein the maximum relative error between the acquired 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.
4. A method of voting on the basis of 4-redundancy aero-engine high-voltage rotation speed signals according to claim 3, characterized in that said first error threshold is the sum of the maximum relative errors of each pair of signals.
5. The 4-redundancy-based high-pressure rotating speed signal voting method for the aeroengine, as claimed in claim 4, is characterized in that the first round of voting value of the signal is calculated by the following method:
wherein,for the ith signal S i Weight of C i For the redundancy confidence of the i-th signal, n is the redundancy number, i.e., n=4.
6. A 4-redundancy-based aircraft engine high-voltage rotational speed signal voting method according to claim 5, characterized in that the redundancy confidence C of the i-th signal i The method comprises the following steps:
wherein D is ij And if the absolute value of the difference between the ith signal and the other jth signals is the absolute value, epsilon is a positive number.
7. The 4-redundancy-based high-pressure rotating speed signal voting method for the aeroengine of claim 6, wherein the calculation method for the second round of voting values of the signals is as follows:
in the method, in the process of the invention,is the voting weight, k, of the ith signal i Is the state of the ith signal, D i For the ith redundancy signal S i And S is equal to b1 N is the number of residuals, n=4, and ε is a positive number.
8. The 4-redundancy-based high-pressure rotational speed signal voting method for an aircraft engine according to claim 7, wherein the state of the signal satisfies:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111432894.8A CN114235420B (en) | 2021-11-29 | 2021-11-29 | Aeroengine high-voltage rotating speed signal voting method based on 4 redundancy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111432894.8A CN114235420B (en) | 2021-11-29 | 2021-11-29 | Aeroengine high-voltage rotating speed signal voting method based on 4 redundancy |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114235420A CN114235420A (en) | 2022-03-25 |
| CN114235420B true CN114235420B (en) | 2024-04-16 |
Family
ID=80751778
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111432894.8A Active CN114235420B (en) | 2021-11-29 | 2021-11-29 | Aeroengine high-voltage rotating speed signal voting method based on 4 redundancy |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114235420B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114893302B (en) * | 2022-04-14 | 2023-10-17 | 北京动力机械研究所 | Small turbofan engine rotating speed judging method and redundancy control method |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6016465A (en) * | 1995-07-10 | 2000-01-18 | The Secretary Of State For Defence | Sensor fault detection system |
| DE102011114223A1 (en) * | 2010-09-30 | 2012-04-05 | Gm Global Technology Operations Llc (N.D.Ges.D. Staates Delaware) | Vehicle i.e. two-mode/strong hybrid vehicle, has control system executing transition from two modes of operation, in order to synchronize rotation speed of machine during operation mode transition slippage |
| WO2012050470A1 (en) * | 2010-10-11 | 2012-04-19 | General Electric Company | Systems, methods, and apparatus for remediating confidence values from redundant sensors |
| CN104678764A (en) * | 2015-01-28 | 2015-06-03 | 北京航空航天大学 | Flight control system sensor hybrid redundancy method based on analytic reconstructed signal |
| CN105204431A (en) * | 2015-08-11 | 2015-12-30 | 中国航空工业集团公司西安飞机设计研究所 | Monitoring-determining method and device for four redundancy signals |
| CN105424966A (en) * | 2015-12-11 | 2016-03-23 | 中国航空工业集团公司西安航空计算技术研究所 | Engine rotating speed measurement circuit and method |
| CN108897309A (en) * | 2018-07-13 | 2018-11-27 | 南京航空航天大学 | Aero-Engine Sensor Failure diagnosis and partition method based on fuzzy membership |
| CN109635318A (en) * | 2018-11-01 | 2019-04-16 | 南京航空航天大学 | A kind of aero-engine sensor intelligent analytic redundancy design method based on KEOS-ELM algorithm |
| CN112596372A (en) * | 2020-12-30 | 2021-04-02 | 中国航发控制系统研究所 | High-adaptability redundancy signal voting method |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7132982B2 (en) * | 1999-03-05 | 2006-11-07 | Rannock Corporation | Method and apparatus for accurate aircraft and vehicle tracking |
| GB0029760D0 (en) * | 2000-12-06 | 2001-01-17 | Secr Defence Brit | Tracking systems for detecting sensor errors |
-
2021
- 2021-11-29 CN CN202111432894.8A patent/CN114235420B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6016465A (en) * | 1995-07-10 | 2000-01-18 | The Secretary Of State For Defence | Sensor fault detection system |
| DE102011114223A1 (en) * | 2010-09-30 | 2012-04-05 | Gm Global Technology Operations Llc (N.D.Ges.D. Staates Delaware) | Vehicle i.e. two-mode/strong hybrid vehicle, has control system executing transition from two modes of operation, in order to synchronize rotation speed of machine during operation mode transition slippage |
| WO2012050470A1 (en) * | 2010-10-11 | 2012-04-19 | General Electric Company | Systems, methods, and apparatus for remediating confidence values from redundant sensors |
| CN104678764A (en) * | 2015-01-28 | 2015-06-03 | 北京航空航天大学 | Flight control system sensor hybrid redundancy method based on analytic reconstructed signal |
| CN105204431A (en) * | 2015-08-11 | 2015-12-30 | 中国航空工业集团公司西安飞机设计研究所 | Monitoring-determining method and device for four redundancy signals |
| CN105424966A (en) * | 2015-12-11 | 2016-03-23 | 中国航空工业集团公司西安航空计算技术研究所 | Engine rotating speed measurement circuit and method |
| CN108897309A (en) * | 2018-07-13 | 2018-11-27 | 南京航空航天大学 | Aero-Engine Sensor Failure diagnosis and partition method based on fuzzy membership |
| CN109635318A (en) * | 2018-11-01 | 2019-04-16 | 南京航空航天大学 | A kind of aero-engine sensor intelligent analytic redundancy design method based on KEOS-ELM algorithm |
| CN112596372A (en) * | 2020-12-30 | 2021-04-02 | 中国航发控制系统研究所 | High-adaptability redundancy signal voting method |
Non-Patent Citations (2)
| Title |
|---|
| "Requirements Analysis of a Quad-Redundant Flight Control System";Jhon Backs 等;《NASA Formal Mathods》;82-96 * |
| "基于MBSE思想的航空发动机控制系统设计方法";李琛 等;《航空发动机》;第47卷(第4期);123-130 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114235420A (en) | 2022-03-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109154236B (en) | Consider sensor failures to control gas turbines | |
| CN102066951B (en) | Systems and methods for detecting and isolating faults in pressure sensing of a flush air data system (FADS) | |
| US3851157A (en) | Self-correcting feedback control system | |
| US6598195B1 (en) | Sensor fault detection, isolation and accommodation | |
| US6578794B1 (en) | Methods and systems for jet engine overthrust protection | |
| US7130772B2 (en) | Method and apparatus for estimating a parameter based on a plurality of redundant signals | |
| KR20080097911A (en) | Sensor failure detection and isolation method and sensor failure adaptation method | |
| US6480780B1 (en) | Regulator or engine regulator, engine and a method for regulating an actuating or propulsion system and an engine | |
| EP0866998A1 (en) | A method of predictive maintenance of a process control system haivng fluid movement | |
| CN114235420B (en) | Aeroengine high-voltage rotating speed signal voting method based on 4 redundancy | |
| US20250116971A1 (en) | System for controlling a device provided with at least one redundant sensor for detecting and isolating failures in one of the sensors | |
| US5680310A (en) | Method and apparatus for sensing a steady state engine condition using a trending algorithm | |
| CN105334845B (en) | Mechanical dual-redundancy electrical four-redundancy angle-of-attack redundancy management method | |
| CN114282570A (en) | Fault tolerance method and fault tolerance system for sensor of aircraft engine | |
| US20050174073A1 (en) | System for controlling the operation of at least one aircraft engine | |
| CN117272602A (en) | Successive approximation type four-redundancy atmospheric parameter voting system and method | |
| CN114397677B (en) | Faulty satellite detection method at receiver end based on non-parametric estimation | |
| US20190064198A1 (en) | Air data system architectures using integrated pressure probes | |
| Vladov | Algorithms for diagnostic and parameter of failures of channels of measurement of TV3-117 aircraft engine automatic control system in flight modes based on neural network technologies | |
| Whitmore | Failure detection and fault management techniques for a pneumatic high-angle-of-attack flush airdata sensing (HI-FADS) system | |
| Li et al. | Multiple fault diagnosis of aeroengine control system based on autoassociative neural network | |
| Zakharov et al. | Network redundant dcs configuration management | |
| Whitmore et al. | Failure detection and fault management techniques for flush airdata sensing systems | |
| Patton et al. | A review of parity space approaches to fault diagnosis applicable toaerospace systems | |
| Feng et al. | Hybrid Fault Diagnosis and Isolation for Component and Sensor of APU in a Distributed Control System. |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |