CN102865147B - Method for processing signal failure of control sensor by using dual-redundancy control rule - Google Patents
Method for processing signal failure of control sensor by using dual-redundancy control rule Download PDFInfo
- Publication number
- CN102865147B CN102865147B CN201110188216.1A CN201110188216A CN102865147B CN 102865147 B CN102865147 B CN 102865147B CN 201110188216 A CN201110188216 A CN 201110188216A CN 102865147 B CN102865147 B CN 102865147B
- Authority
- CN
- China
- Prior art keywords
- control rule
- design
- control
- standby
- aeroengine
- 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
Abstract
The invention discloses a method for processing a signal failure of a control sensor by using a dual-redundancy control rule, and is characterized by providing the method for processing the signal failure of the control sensor by using the dual-redundancy control rule, a dual-redundancy control rule design concept and a copy dual-redundancy control rule design principle, and a copy control rule design method and a design process of the dual-redundancy control rule. The main control rule is designed with the goal of enabling an aero-engine to obtain optimal thrust and economy in full flight envelope and ensuring the working stability and the structure strength of the engine; and the copy control rule design method provided by the invention is to perform the copy control rule design according to the copy control rule design principle on the basis that the main control rule design is finished. The method has the following advantages that the failure processing property of a digital control system is improved, the mission reliability of the aero-engine can be improved, the requirement of real-time control of the high-performance aero-engine is satisfied more easily, the method is more liable to implement, and the combination property of the aero-engine is improved.
Description
Technical field
The present invention relates to the aeroengine field of containing digital electronic control system, a kind of method that adopts two remaining control law processing control sensor signal faults is provided especially.
Background technique
In order to improve reliability, aeroengine digital electronic control system develops to fault-tolerant control from non-fault-tolerant control, in the situation that some parts breaks down, though system still can have reduction (can acceptance) by original performance index or performance index, but can complete safely control task.Fault-tolerant control comprises redundancy technology and reconfiguration technique.Redundancy technology, designs several control channel exactly, and in the time that a control channel breaks down, another control channel is devoted oneself to work.Redundancy technology is broadly divided into hardware remaining and analytic redundancy.Hardware remaining is to provide remaining with the backup hardware in control channel; Analytic redundancy and do not need to increase hardware but provide remaining for the engine sensor easily breaking down by the method for resolving.Conventionally the optimal estimation techniques in use modern control theory or the method for artificial-intelligent estimate the measured value of motor.In the time that certain sensor breaks down, just replace measured value by corresponding estimated value, control system is worked on.Reconfiguration technique refers in two redundant control systems, in the time that two passages have element to break down, still likely the fault-free part in two passages is reconfigured to new control channel of formation, and control system is worked on.The professor Sun Jianguo chief editor's of aviation industry publishing house publication in 2009 regular higher education Eleventh Five-Year Plan National planning teaching material " control of modern Aviation power plant " (revised edition) is come from this section of discussion.
The sensor that current aeroengine Digital Control System is participated in control directly adopts the two remainings of hardware, hardware three remainings conventionally, even adopt hardware redundancy design proposal, in the time controlling sensor fault, adopt the redundancy sensor signal of backup to complete control function; All fault in the situation that, adopt the method for analytic redundancy to replace fault sensor signal with the valuation of non-fault sensor signal in all hardware remaining.
The shortcoming that the method for employing increase sensor hardware remaining improves reliability is the weight that has increased aeroengine; The shortcoming that adopts analytic redundancy method to improve engine reliability is the accuracy that the accuracy of analytic redundancy sensor valuation depends on the airborne real-time model of motor, between valuation and measured value, there is error, easily cause the fluctuation of engine behavior and the deviation of control desired value, and increase the software operand of engine electronic control system device.Be in particular in several aspects:
1. increase sensor hardware remaining and improve engine reliability, bring the increase of engine weight, for advanced person's high thrust weight ratio aeroengine, thrust weight ratio is the index of most important measurement Technical advancement, and weight increase is fatal problem;
2. increase sensor hardware remaining and improve engine reliability, bring motor to become the increase of annex number and the increase of cost, reduce the economic index of motor;
3. increase sensor hardware remaining and improve engine reliability, bring processing, assembling, production, the work difficulty of maintenance and the increase of workload of motor, extend the development and production cycle of motor, also increase the making user cost of motor;
4. adopt analytic redundancy method to improve engine reliability, because motor exists manufacturing tolerances and performance degradation, between the analytic redundancy sensor valuation that engine mockup calculates and motor actual value, necessarily there is error, can cause the unstable and fault treatment of engine behavior in fault treating procedure to finish the error of rear control setting value;
Adopt analytic redundancy method to improve engine reliability, bring engine electronic control system device software operand significantly to increase, the requirement of controlling in real time for High Performance Aeroengine further improves, and increases Software for Design difficulty and the coding work amount controlled.
Summary of the invention
The object of the invention is the mission reliability of the aeroengine in order to improve equipped digital electronic control system, spy provides a kind of method that adopts two remaining control law processing control sensor signal faults.
The invention provides a kind of method that adopts two remaining control law processing control sensor signal faults, it is characterized in that: 1). propose to adopt two remaining control laws to control sensor signal fault handling method:
Existing aeroengine control rule realizes principle as shown in Figure 1, for controlled variable motor main combustion chamber amount of fuel, can only controlled parameter of closed loop control in full flight envelope, and in different envelope curves region or closed loop control high pressure rotor rotational speed N
h, or closed loop control rotational speed of lower pressure turbine rotor N
l; In figure, all adopt the two redundancy design schemes of hardware for the HP&LP Rotor speed probe of closed loop control.
What the two remaining control laws of employing provided by the invention were controlled sensor signal fault handling method realizes principle as shown in Figure 2.Carry out logic judgement according to engine intake temperature T 1 under normal circumstances, carry out main control plan; Under control system is being carried out situation that the speed probe of closed loop control or all hardware remaining of its input signal puocessing module all break down, carry out logic judgement according to trouble signal, carry out Standby control rule, form backup close loop control circuit, the former closed loop control signals of rotational speed sensor that isolation has been broken down, reach the object of system reconfiguration, improve the mission reliability of aeroengine;
2). two remaining control law design concepts and Standby control rule design principle are proposed
Existing aeroengine control rule is segmentation Combination Design within the scope of full envelope curve, seems a more than control law, is actually the control law of a combination.The control system of aeroengine has hardware remaining, software remaining, but never people proposed the control law of two remainings, the present invention proposes the design concept of two remaining control laws.Two remaining control laws are exactly that redundancy technology is applied among control law design, originally the control law of design is as main control rule, then designs the control law of a backup, in the time that main control rule cannot realize, realize the control law of backup, ensure to start function to finish the work safely.The invention provides Standby control rule design principle:
(1) require the Standby control rule of design can keep the performance index of motor constant;
(2) the fault treating procedure that is transformed into Standby control rule from main control rule, engine behavior is steady, and motor power does not allow sudden change;
(3) the Standby control rule of design is easy to realize, and controlled parameter sensors is equipped with on motor, does not increase the weight of aeroengine;
3). Standby control rule design method and the design cycle of two remaining control laws are proposed
The design of main control rule is so that stability and the structural strength of the thrust that within the scope of the full envelope curve of aeroengine, acquisition is best and Economy, guarantee engine operation are target; Standby control rule design method provided by the invention is on the basis of having designed in main control rule, carries out the design of Standby control rule according to Standby control rule design principle; Standby control rule design cycle as shown in Figure 3.
(1) according to Standby control rule design principle Article 3, select controlled parameter;
(2), according to the requirement of Standby control rule design principle Article 1, do not become target and carry out the proposal plan of Standby control rule to realize engine behavior;
(3), according to Standby control rule design principle Article 2, revise the Standby control rule of the variant part of aeroengine operation status;
(4) use aero engine total performance design program to carry out the performance index such as thrust, oil consumption rate of main control rule calculating aeroengine;
(5) carry out Standby control rule and calculate the performance index such as thrust, oil consumption rate of aeroengine by identical aero engine total performance design program;
(6) result of calculation of main control rule and Standby control rule is carried out in contrast, judges whether to meet the control accuracy requirement of aeroengine.If do not met the demands, according to Standby control rule design principle Article 2, further revise the Standby control rule of the variant part of performance index; If met the demands, Standby control rule has designed.
Advantage of the present invention:
The method of the two remaining control law processing control sensor signal faults of employing of the present invention, improves the troubleshooting capability of Digital Control System, can improve the mission reliability of aeroengine.Compared with increasing the method for sensor hardware remaining, the inventive method has reduced the number of sensors being assemblied in aeroengine, reduce the weight of aeroengine, lead time and the cost of production of aeroengine are saved, bring considerable economic benefit, be easier to meet the thrust weight ratio requirement of aeroengine; Compared with adopting the method for analytic redundancy, the less increase aeroengine control of the inventive method Software for Design difficulty and electronic controller software operand, can keep in fault treating procedure the stable and fault treatment of aeroengine operation status to finish rear control setting value error free, more easily meet the requirement that High Performance Aeroengine is controlled in real time, be easier to realize, improve the combination property of aeroengine.
Brief description of the drawings
Below in conjunction with drawings and the embodiments, the present invention is further detailed explanation:
The existing aeroengine control rule of Fig. 1 realizes theory diagram;
The two remaining control law fault treatments of Fig. 2 realize theory diagram;
The Standby control rule design flow diagram of the two remaining control laws of Fig. 3.
Embodiment
Embodiment 1
The invention provides a kind of method that adopts two remaining control law processing control sensor signal faults, it is characterized in that: 1). propose to adopt two remaining control laws to control sensor signal fault handling method:
Existing aeroengine control rule realizes principle as shown in Figure 1, for controlled variable motor main combustion chamber amount of fuel, can only controlled parameter of closed loop control in full flight envelope, in different envelope curves region according to engine intake temperature T 1 or closed loop control high pressure rotor rotational speed N
h, or closed loop control rotational speed of lower pressure turbine rotor N
l; In figure, all adopt the two redundancy design schemes of hardware for the HP&LP Rotor speed probe of closed loop control.
What the two remaining control laws of employing provided by the invention were controlled sensor signal fault handling method realizes principle as shown in Figure 2.Carry out logic judgement according to engine intake temperature T 1 under normal circumstances, carry out main control plan; Under control system is being carried out situation that the speed probe of closed loop control or all hardware remaining of its input signal puocessing module all break down, carry out logic judgement according to trouble signal, carry out Standby control rule, form backup close loop control circuit, the former closed loop control signals of rotational speed sensor that isolation has been broken down, reach the object of system reconfiguration, improve the mission reliability of aeroengine;
2). two remaining control law design concepts and Standby control rule design principle are proposed
Existing aeroengine control rule is segmentation Combination Design within the scope of full envelope curve, seems a more than control law, is actually the control law of a combination.The control system of aeroengine has hardware remaining, software remaining, but never people proposed the control law of two remainings, the present invention proposes the design concept of two remaining control laws.Two remaining control laws are exactly that redundancy technology is applied among control law design, originally the control law of design is as main control rule, then designs the control law of a backup, in the time that main control rule cannot realize, realize the control law of backup, ensure to start function to finish the work safely.
The invention provides Standby control rule design principle:
(1) require the Standby control rule of design can keep the performance index of motor constant;
(2) the fault treating procedure that is transformed into Standby control rule from main control rule, engine behavior is steady, and motor power does not allow sudden change;
(3) the Standby control rule of design is easy to realize, and controlled parameter sensors is equipped with on motor, does not increase the weight of aeroengine;
3). Standby control rule design method and the design cycle of two remaining control laws are proposed
The design of main control rule is so that stability and the structural strength of the thrust that within the scope of the full envelope curve of aeroengine, acquisition is best and Economy, guarantee engine operation are target; Standby control rule design method provided by the invention is on the basis of having designed in main control rule, carries out the design of Standby control rule according to Standby control rule design principle; Standby control rule design cycle as shown in Figure 3.
(1) according to Standby control rule design principle Article 3, select controlled parameter;
(2), according to the requirement of Standby control rule design principle Article 1, do not become target and carry out the proposal plan of Standby control rule to realize engine behavior;
(3), according to Standby control rule design principle Article 2, revise the Standby control rule of the variant part of aeroengine operation status;
(4) use aero engine total performance design program to carry out the performance index such as thrust, oil consumption rate of main control rule calculating aeroengine;
(5) carry out Standby control rule and calculate the performance index such as thrust, oil consumption rate of aeroengine by identical aero engine total performance design program;
(6) result of calculation of main control rule and Standby control rule is carried out in contrast, judges whether to meet the control accuracy requirement of aeroengine.If do not met the demands, according to Standby control rule design principle Article 2, further revise the Standby control rule of the variant part of performance index; If met the demands, Standby control rule has designed.
Claims (1)
1. a method that adopts two remaining control law processing control sensor signal faults, is characterized in that: 1). propose to adopt two remaining control laws to control sensor signal fault handling method:
Existing aeroengine control rule, for controlled variable motor main combustion chamber amount of fuel, can only controlled parameter of closed loop control in full flight envelope, carry out logic judgement in different envelope curves region according to engine intake temperature T 1, or closed loop control high pressure rotor rotational speed N
h, or closed loop control rotational speed of lower pressure turbine rotor N
l;
Carry out logic judgement according to engine intake temperature T 1 under normal circumstances, carry out main control plan; Under control system is being carried out situation that the speed probe of closed loop control or all hardware remaining of its input signal puocessing module all break down, carry out logic judgement according to trouble signal, carry out Standby control rule, form backup close loop control circuit, the former closed loop control signals of rotational speed sensor that isolation has been broken down, reach the object of system reconfiguration, improve the mission reliability of aeroengine;
2). two remaining control law design concepts and Standby control rule design principle are proposed
The design concept of two remaining control laws has been proposed; Two remaining control laws are exactly that redundancy technology is applied among control law design, originally the control law of design is as main control rule, then designs the control law of a backup, in the time that main control rule cannot realize, realize the control law of backup, ensure to start function to finish the work safely;
Standby control rule design principle:
(1) require the Standby control rule of design can keep the performance index of motor constant;
(2) the fault treating procedure that is transformed into Standby control rule from main control rule, engine behavior is steady, and motor power does not allow sudden change;
(3) the Standby control rule of design is easy to realize, and controlled parameter sensors is equipped with on motor, does not increase the weight of aeroengine;
3). Standby control rule design method and the design cycle of two remaining control laws are proposed
The design of main control rule is so that stability and the structural strength of the thrust that within the scope of the full envelope curve of aeroengine, acquisition is best and Economy, guarantee engine operation are target; Standby control rule design method is on the basis of having designed in main control rule, carries out the design of Standby control rule according to Standby control rule design principle;
(1) according to Standby control rule design principle Article 3, select controlled parameter;
(2), according to the requirement of Standby control rule design principle Article 1, do not become target and carry out the proposal plan of Standby control rule to realize engine behavior;
(3), according to Standby control rule design principle Article 2, revise the Standby control rule of the variant part of aeroengine operation status;
(4) use aero engine total performance design program to carry out the performance index such as thrust, oil consumption rate of main control rule calculating aeroengine;
(5) carry out Standby control rule and calculate the performance index such as thrust, oil consumption rate of aeroengine by identical aero engine total performance design program;
(6) result of calculation of main control rule and Standby control rule is carried out in contrast, judges whether to meet the control accuracy requirement of aeroengine; If do not met the demands, according to Standby control rule design principle Article 2, further revise the Standby control rule of the variant part of performance index; If met the demands, Standby control rule has designed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110188216.1A CN102865147B (en) | 2011-07-06 | 2011-07-06 | Method for processing signal failure of control sensor by using dual-redundancy control rule |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110188216.1A CN102865147B (en) | 2011-07-06 | 2011-07-06 | Method for processing signal failure of control sensor by using dual-redundancy control rule |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102865147A CN102865147A (en) | 2013-01-09 |
| CN102865147B true CN102865147B (en) | 2014-10-08 |
Family
ID=47444232
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110188216.1A Active CN102865147B (en) | 2011-07-06 | 2011-07-06 | Method for processing signal failure of control sensor by using dual-redundancy control rule |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102865147B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106323640B (en) * | 2015-06-30 | 2018-10-30 | 中航空天发动机研究院有限公司 | A kind of aero-engine acceleration and deceleration fuel feeding test method |
| CN110469440A (en) * | 2019-08-26 | 2019-11-19 | 象限空间（天津）科技有限公司 | Aviation piston engine double redundancy revolving speed acquires ITCS Ignition Timing Control System and method |
| CN110879549B (en) * | 2019-11-28 | 2023-05-05 | 四川泛华航空仪表电器有限公司 | Redundancy measurement architecture based on cross-comparison method and redundancy management method |
| CN111058958B (en) * | 2019-12-11 | 2022-01-07 | 厦门林巴贺航空发动机股份有限公司 | Control method of piston type aircraft engine |
| CN112363385A (en) * | 2020-09-30 | 2021-02-12 | 成都飞机工业（集团）有限责任公司 | Digital electronic control system of redundancy engine |
| CN112627992B (en) * | 2020-12-17 | 2023-03-14 | 中国航空工业集团公司成都飞机设计研究所 | Engine control system |
| CN113534656B (en) * | 2021-09-07 | 2022-01-21 | 中国商用飞机有限责任公司 | Telex flight backup control system and telex flight backup control method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4722061A (en) * | 1984-12-20 | 1988-01-26 | United Technologies Corporation | Establishing synthesis validity between two signal sources |
| US4821193A (en) * | 1985-08-26 | 1989-04-11 | General Electric Company | Digital control for gas turbine engine |
| EP1096122A1 (en) * | 1998-06-09 | 2001-05-02 | Otkritoe Aktsionernoe Obschestvo "Nauchno-Proizvodstvennoe Predpriyatie-Elektronno-Gidravlicheskaya Avtomatika" | Method for detecting sensor failures and for controlling the operation conditions of an object |
| CN101216701A (en) * | 2007-01-04 | 2008-07-09 | 北京航空航天大学 | 1553B bus based triplex hot-redundancy digital type actuator controller |
| CN101271332A (en) * | 2008-05-09 | 2008-09-24 | 北京方天长久科技有限公司 | Compact integrated redundancy controller and control method thereof |
| CN101631057A (en) * | 2009-08-17 | 2010-01-20 | 北京航空航天大学 | Network control method of dual-redundancy CAN bus |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA1026850A (en) * | 1973-09-24 | 1978-02-21 | Smiths Industries Limited | Dual, simultaneously operating control system with fault detection |
-
2011
- 2011-07-06 CN CN201110188216.1A patent/CN102865147B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4722061A (en) * | 1984-12-20 | 1988-01-26 | United Technologies Corporation | Establishing synthesis validity between two signal sources |
| US4821193A (en) * | 1985-08-26 | 1989-04-11 | General Electric Company | Digital control for gas turbine engine |
| EP1096122A1 (en) * | 1998-06-09 | 2001-05-02 | Otkritoe Aktsionernoe Obschestvo "Nauchno-Proizvodstvennoe Predpriyatie-Elektronno-Gidravlicheskaya Avtomatika" | Method for detecting sensor failures and for controlling the operation conditions of an object |
| CN101216701A (en) * | 2007-01-04 | 2008-07-09 | 北京航空航天大学 | 1553B bus based triplex hot-redundancy digital type actuator controller |
| CN101271332A (en) * | 2008-05-09 | 2008-09-24 | 北京方天长久科技有限公司 | Compact integrated redundancy controller and control method thereof |
| CN101631057A (en) * | 2009-08-17 | 2010-01-20 | 北京航空航天大学 | Network control method of dual-redundancy CAN bus |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102865147A (en) | 2013-01-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102865147B (en) | Method for processing signal failure of control sensor by using dual-redundancy control rule | |
| CN107703914A (en) | A kind of aero-engine FADEC security of system appraisal procedures | |
| CA2852299C (en) | Engine operations support systems and methods for reducing fuel flow | |
| CN102855349A (en) | Quick prototype design method and platform for gas path fault diagnosis for aeroengine | |
| CN110513198A (en) | A kind of fanjet control system Active Fault-tolerant Control Method | |
| CN106055770A (en) | Diagnostic method for gas path faults of aero-engine based on sliding mode theory | |
| CN110320799B (en) | Undisturbed cut-in fault-tolerant control method for faults of aircraft engine actuator | |
| Jaw et al. | Propulsion control technology development in the united states a historical perspective | |
| CN111666648B (en) | Method for simulating dynamic characteristics of aircraft engine | |
| CN111880403A (en) | Fault-tolerant two-degree-of-freedom [ mu ] controller for maximum thrust state of aircraft engine | |
| CN109445402A (en) | A kind of Fuel On Board system is from monitoring to computer control method | |
| Albert et al. | Aerodynamic design optimization of nacelle and intake | |
| US20090171631A1 (en) | Integrated Engineering Analysis Process | |
| CN109236390A (en) | Coil control structure, method, medium, terminal and steam turbine suitable for torque-motor | |
| Smith et al. | Next generation control system for helicopter engines | |
| US20090171626A1 (en) | Integrated Engineering Analysis System | |
| CN101794634A (en) | Digital computing method for pressure set value of deaerator of pressurized water reactor nuclear power station | |
| Liu et al. | The design and semi-physical simulation test of fault-tolerant controller for aero Engine | |
| Liu et al. | Intelligent fault-tolerant control system design and semi-physical simulation validation of aero-engine | |
| CN111734533B (en) | Turbofan engine-based model prediction method and system | |
| Chen et al. | Model-based Improved Advanced Adaptive Performance Recovery Control Method for A Commercial Turbofan Engine | |
| Saluru et al. | Active fault tolerant model predictive control of a turbofan engine using C-MAPSS40k | |
| Litt et al. | A retro-fit control architecture to maintain engine performance with usage | |
| Jia et al. | Multi-variable anti-disturbance controller with state-dependent switching law for adaptive cycle engine | |
| Hacker | L1 Adaptive Control of Uncertain Nonlinear Systems with Dynamic Constraints: As Applied to Commercial Aircraft Engines |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |