CN102865147A - 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
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- CN102865147A CN102865147A CN2011101882161A CN201110188216A CN102865147A CN 102865147 A CN102865147 A CN 102865147A CN 2011101882161 A CN2011101882161 A CN 2011101882161A CN 201110188216 A CN201110188216 A CN 201110188216A CN 102865147 A CN102865147 A CN 102865147A
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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 contain the aeroengine field of 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, the aeroengine digital electronic control system develops to fault-tolerant control from non-fault-tolerant control, namely in the situation that some parts breaks down, though still can there be reduction (can acceptance) in system by original performance index or performance index, but can finish safely control task.Fault-tolerant control comprises redundancy technology and reconfiguration technique.Redundancy technology designs several control channels exactly, and when a control channel broke down, another control channel was devoted oneself to work.Redundancy technology is broadly divided into hardware remaining and analytic redundancy.The hardware remaining is to provide remaining with the backup hardware in the control channel; Analytic redundancy and do not need to increase hardware but provide remaining with the method for resolving for the engine sensor that easily breaks down.Usually the optimal estimation techniques in the use modern control theory or the method for artificial-intelligent estimate the measured value of motor.When certain sensor breaks down, just replace measured value with corresponding estimated value, control system is worked on.Reconfiguration technique refers to when two passages have element to break down, still the fault-free part in two passages to be reconfigured new control channel of formation in two redundant control systems, 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 discussion.
The sensor that present aeroengine Digital Control System is participated in control directly adopts the two remainings of hardware, hardware three remainings usually, even employing hardware redundancy design proposal, when the control sensor fault, adopt the redundancy sensor signal of backup to finish the control function; In the situation that all hardware remaining fault all, the method that adopts analytic redundancy replaces the fault sensor signal with the valuation of non-fault sensor signal.
The shortcoming that adopts the method that increases sensor hardware remaining to improve reliability is the weight that has increased aeroengine; The shortcoming that adopts the 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, there is error between valuation and the measured value, 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 the 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, prolong the development and production cycle of motor, also increase the making user cost of motor;
4. adopt the analytic redundancy method to improve engine reliability, because motor exists manufacturing tolerances and performance degradation, necessarily there is error between the analytic redundancy sensor valuation that engine mockup calculates and the motor actual value, can causes the unstable and fault treatment of engine behavior in the fault treating procedure to finish the rear error of controlling setting value;
Adopt the analytic redundancy method to improve engine reliability, bring engine electronic control system device software operand significantly to increase, the in real time requirement of control further improves for High Performance Aeroengine, increases control Software for Design difficulty and coding work amount.
Summary of the invention
The objective of the invention is the mission reliability for the aeroengine that improves equipped digital electronic control system, the 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 the 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 zone or closed loop control high pressure rotor rotational speed N
H, perhaps closed loop control rotational speed of lower pressure turbine rotor N
LThe HP﹠LP Rotor speed probe that is used for closed loop control among the figure all adopts the two redundancy design schemes of hardware.
The realization principle that the two remaining control laws of employing provided by the invention are controlled the sensor signal fault handling method as shown in Figure 2.Carry out logic according to engine intake temperature T 1 under normal circumstances and judge, carry out the main control plan; Under control system is being carried out situation that all hardware remaining of the speed probe of closed loop control or its input signal puocessing module all breaks down, carrying out logic according to trouble signal judges, carry out the Standby control rule, consist of the backup close loop control circuit, the former closed loop control signals of rotational speed sensor that isolation has been broken down, reach the purpose 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 in the full envelope curve scope, 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 the 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 redundancy technology is applied among the control law design, originally the control law of design designs the control law of a backup, when the main control rule can't realize again as the main control rule, realize the control law of backup, guarantee 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) engine behavior is steady the fault treating procedure that is transformed into the Standby control rule from the main control rule, and motor power does not allow sudden change;
(3) the Standby control rule of design is easy to realize, 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 acquisition is best in the full envelope curve scope of aeroengine and Economy, assurance engine operation are target; Standby control rule design method provided by the invention is on the basis that the design of main control rule is finished, and 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 the 3rd of Standby control rule design principle, selects controlled parameter;
(2) according to the requirement of Standby control rule design principle article one, do not become the proposal plan that target is carried out the Standby control rule with the realization engine behavior;
(3) according to Standby control rule design principle second, revise the Standby control rule of the variant part of aeroengine operation status;
(4) carry out the main control rule with aero engine total performance design program and calculate the performance index such as the thrust of aeroengine, oil consumption rate;
(5) carry out the Standby control rule with identical aero engine total performance design program and calculate the performance index such as the thrust of aeroengine, oil consumption rate;
(6) result of calculation of main control rule and Standby control rule is carried out in contrast, judges whether to satisfy the control accuracy requirement of aeroengine.If do not meet the demands, according to Standby control rule design principle second, further revise the Standby control rule of the variant part of performance index; If meet the demands, the design of Standby control rule is finished.
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.Compare with the method that increases sensor hardware remaining, the inventive method has reduced the number of sensors that is assemblied on the aeroengine, reduced the weight of aeroengine, lead time and the cost of production of aeroengine have been saved, bring considerable economic benefit, be easier to satisfy the thrust weight ratio requirement of aeroengine; Compare with the method that adopts analytic redundancy, the less increase aeroengine control of the inventive method Software for Design difficulty and electronic controller software operand, the control setting value is error free after keeping in the fault treating procedure the stable and fault treatment of aeroengine operation status to finish, more easily satisfy the in real time requirement of control of High Performance Aeroengine, be easier to realize, improve the combination property of aeroengine.
Description of drawings
The present invention is further detailed explanation below in conjunction with drawings and the embodiments:
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 the 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 zone according to engine intake temperature T 1 or closed loop control high pressure rotor rotational speed N
H, perhaps closed loop control rotational speed of lower pressure turbine rotor N
LThe HP﹠LP Rotor speed probe that is used for closed loop control among the figure all adopts the two redundancy design schemes of hardware.
The realization principle that the two remaining control laws of employing provided by the invention are controlled the sensor signal fault handling method as shown in Figure 2.Carry out logic according to engine intake temperature T 1 under normal circumstances and judge, carry out the main control plan; Under control system is being carried out situation that all hardware remaining of the speed probe of closed loop control or its input signal puocessing module all breaks down, carrying out logic according to trouble signal judges, carry out the Standby control rule, consist of the backup close loop control circuit, the former closed loop control signals of rotational speed sensor that isolation has been broken down, reach the purpose 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 in the full envelope curve scope, 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 the 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 redundancy technology is applied among the control law design, originally the control law of design designs the control law of a backup, when the main control rule can't realize again as the main control rule, realize the control law of backup, guarantee 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) engine behavior is steady the fault treating procedure that is transformed into the Standby control rule from the main control rule, and motor power does not allow sudden change;
(3) the Standby control rule of design is easy to realize, 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 acquisition is best in the full envelope curve scope of aeroengine and Economy, assurance engine operation are target; Standby control rule design method provided by the invention is on the basis that the design of main control rule is finished, and 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 the 3rd of Standby control rule design principle, selects controlled parameter;
(2) according to the requirement of Standby control rule design principle article one, do not become the proposal plan that target is carried out the Standby control rule with the realization engine behavior;
(3) according to Standby control rule design principle second, revise the Standby control rule of the variant part of aeroengine operation status;
(4) carry out the main control rule with aero engine total performance design program and calculate the performance index such as the thrust of aeroengine, oil consumption rate;
(5) carry out the Standby control rule with identical aero engine total performance design program and calculate the performance index such as the thrust of aeroengine, oil consumption rate;
(6) result of calculation of main control rule and Standby control rule is carried out in contrast, judges whether to satisfy the control accuracy requirement of aeroengine.If do not meet the demands, according to Standby control rule design principle second, further revise the Standby control rule of the variant part of performance index; If meet the demands, the design of Standby control rule is finished.
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 the 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 in different envelope curves zone according to engine intake temperature T 1 and judge, perhaps closed loop control high pressure rotor rotational speed N
H, perhaps closed loop control rotational speed of lower pressure turbine rotor N
L
The present invention proposes, and carries out logic according to engine intake temperature T 1 under normal circumstances and judges, carries out the main control plan; Under control system is being carried out situation that all hardware remaining of the speed probe of closed loop control or its input signal puocessing module all breaks down, carrying out logic according to trouble signal judges, carry out the Standby control rule, consist of the backup close loop control circuit, the former closed loop control signals of rotational speed sensor that isolation has been broken down, reach the purpose 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 redundancy technology is applied among the control law design, originally the control law of design designs the control law of a backup, when the main control rule can't realize again as the main control rule, realize the control law of backup, guarantee 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) engine behavior is steady the fault treating procedure that is transformed into the Standby control rule from the main control rule, and motor power does not allow sudden change;
(3) the Standby control rule of design is easy to realize, 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 acquisition is best in the full envelope curve scope of aeroengine and Economy, assurance engine operation are target; Standby control rule design method provided by the invention is on the basis that the design of main control rule is finished, and carries out the design of Standby control rule according to Standby control rule design principle;
(1) according to the 3rd of Standby control rule design principle, selects controlled parameter;
(2) according to the requirement of Standby control rule design principle article one, do not become the proposal plan that target is carried out the Standby control rule with the realization engine behavior;
(3) according to Standby control rule design principle second, revise the Standby control rule of the variant part of aeroengine operation status;
(4) carry out the main control rule with aero engine total performance design program and calculate the performance index such as the thrust of aeroengine, oil consumption rate;
(5) carry out the Standby control rule with identical aero engine total performance design program and calculate the performance index such as the thrust of aeroengine, oil consumption rate;
(6) result of calculation of main control rule and Standby control rule is carried out in contrast, judges whether to satisfy the control accuracy requirement of aeroengine;
If do not meet the demands, according to Standby control rule design principle second, further revise the Standby control rule of the variant part of performance index; If meet the demands, the design of Standby control rule is finished.
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106323640A (en) * | 2015-06-30 | 2017-01-11 | 中航空天发动机研究院有限公司 | Acceleration and deceleration oil supply test method for aeroengines |
| 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 |
| CN110879549A (en) * | 2019-11-28 | 2020-03-13 | 四川泛华航空仪表电器有限公司 | Redundancy measurement framework based on cross-comparison method and redundancy management method |
| CN111058958A (en) * | 2019-12-11 | 2020-04-24 | 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 |
| CN112627992A (en) * | 2020-12-17 | 2021-04-09 | 中国航空工业集团公司成都飞机设计研究所 | Engine control system |
| CN113534656A (en) * | 2021-09-07 | 2021-10-22 | 中国商用飞机有限责任公司 | Telex flight backup control system and telex flight backup control method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5059612A (en) * | 1973-09-24 | 1975-05-23 | ||
| 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 |
-
2011
- 2011-07-06 CN CN201110188216.1A patent/CN102865147B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5059612A (en) * | 1973-09-24 | 1975-05-23 | ||
| 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 |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106323640A (en) * | 2015-06-30 | 2017-01-11 | 中航空天发动机研究院有限公司 | Acceleration and deceleration oil supply test method for aeroengines |
| 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 |
| CN110879549A (en) * | 2019-11-28 | 2020-03-13 | 四川泛华航空仪表电器有限公司 | Redundancy measurement framework based on cross-comparison method and redundancy management 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 |
| CN111058958A (en) * | 2019-12-11 | 2020-04-24 | 厦门林巴贺航空发动机股份有限公司 | Control method of piston type aircraft engine |
| 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 |
| CN112627992A (en) * | 2020-12-17 | 2021-04-09 | 中国航空工业集团公司成都飞机设计研究所 | Engine control system |
| 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 |
| CN113534656A (en) * | 2021-09-07 | 2021-10-22 | 中国商用飞机有限责任公司 | Telex flight backup control system and telex flight backup control method |
| 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 |
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