CN105626271B - A kind of aeroengine control system combined fault logical process method - Google Patents
A kind of aeroengine control system combined fault logical process method Download PDFInfo
- Publication number
- CN105626271B CN105626271B CN201511008792.8A CN201511008792A CN105626271B CN 105626271 B CN105626271 B CN 105626271B CN 201511008792 A CN201511008792 A CN 201511008792A CN 105626271 B CN105626271 B CN 105626271B
- Authority
- CN
- China
- Prior art keywords
- engine
- failure
- control system
- group
- fault
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/48—Control of fuel supply conjointly with another control of the plant
Abstract
The invention discloses a kind of aeroengine control system combined fault logical process methods.The aeroengine control system combined fault logical process method includes the following steps：Step 1：According to engine type, multiple engine controlled variables are chosen；Step 2：Judge whether the failure that engine occurs is combined fault, if it is not, then stopping aeroengine control system combined fault logical process method；If so, carrying out in next step；Step 3：Enumerate each failure of the engine in the combined fault；Step 4：There is provided a processing tactful group for each failure；Step 5：Recombinant is carried out, to form practical strategies group, each engine controlled variable in the practical strategies group has unique action command, and the practical strategies group can solve the influence caused by each failure.The aeroengine control system combined fault logical process method of the present invention being capable of reasonable orderly, effective processing aero-engine combined fault.
Description
Technical field
The present invention relates to aeroengine control system technical fields, more particularly to a kind of aeroengine control system
Combined fault logical process method and aeroengine control system combined fault logical process system.
Background technology
Aero-engine failure be due to part component failure in system and cause whole system function deteriorate event.
When system jam, fault tolerant mechanism can reorganize and build the control system being made of fault-free component, make its work
Make, in normal or suboptimum state, to achieve the purpose that recovery system performance or at least ensure system safety operation.
When single failure occurs in aeroengine control system, it is clear and unique to handle strategy.But work as multiple failures simultaneously
When occurring and handling tactful different, the processing logic of this combined fault becomes tedious complexity.In the prior art, not yet
For the processing method of combined fault.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Invention content
The purpose of the present invention is to provide a kind of aeroengine control system combined fault logical process methods to overcome
Or at least mitigate the prior art at least one of drawbacks described above.
To achieve the above object, the present invention provides a kind of aeroengine control system combined fault logical process method,
The aeroengine control system combined fault logical process method includes the following steps：
Step 1：According to engine type, multiple engine controlled variables are chosen；
Step 2：Judge whether the failure that engine occurs is combined fault, if it is not, then stopping aero-engine control system
System combined fault logical process method；If so, carrying out in next step；
Step 3：Enumerate each failure of the engine in the combined fault；
Step 4：There is provided a processing tactful group for each failure, wherein each processing strategy group includes the multiple
The change of engine controlled variable makes engine pass through to each engine controlled variable in the multiple engine controlled variable
Change so as to solving the influence caused by the failure；
Step 5：Each processing strategy group in the step 4 is subjected to recombinant, to form practical strategies group, the reality
Each engine controlled variable in the multiple engine controlled variable in the strategy group of border has unique action command, and
The practical strategies group can solve the influence caused by each failure in the step 3.
Preferably, the control variable in the step 1 includes：Main fuel flow, reinforcing fuel flow, fan blade angle
Degree, compressor blade angle, area of injection orifice.
The present invention also provides a kind of aeroengine control system combined fault logical process system, the aeroplane engines
Machine control system combined fault logical process system includes：
Policy storage unit is handled, the processing Policy storage unit is for storing processing strategy；
Fault memory cell, the fault memory cell is for storing engine failure；
Integral unit, the integral unit are used to that processing strategy and the fault memory cell in Policy storage unit will to be handled
In engine failure be associated；
Assembled unit, the processing strategy after the assembled unit is used to the integral unit being associated with carry out recombinant, from
And form practical strategies group；
Motor unit, the motor unit are formed by practical strategies group according to the assembled unit and are acted, to
Solve the influence caused by failure.
The aeroengine control system combined fault logical process method of the present invention can be reasonable orderly, effective
Handle aero-engine combined fault.
Description of the drawings
Fig. 1 is the stream of aeroengine control system combined fault logical process method according to a first embodiment of the present invention
Journey schematic diagram.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
The every other embodiment that member is obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term "center", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, and does not indicate or imply the indicated dress
It sets or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as protecting the present invention
The limitation of range.
Fig. 1 is the stream of aeroengine control system combined fault logical process method according to a first embodiment of the present invention
Journey schematic diagram.
Aeroengine control system combined fault logical process method as shown in Figure 1 includes the following steps：Step 1：
According to engine type, multiple engine controlled variables are chosen；
Step 2：Judge whether the failure that engine occurs is combined fault, if it is not, then stopping aero-engine control system
System combined fault logical process method；If so, carrying out in next step；
Step 3：Enumerate each failure of the engine in the combined fault；
Step 4：There is provided a processing tactful group for each failure, wherein each processing strategy group includes multiple starts
Machine controls the change of variable, so that engine is passed through the change to each engine controlled variable and is made so as to solve the failure
At influence；
Step 5：Each processing strategy group in step 4 is subjected to recombinant, to form practical strategies group, the practical plan
Each engine controlled variable slightly in group has unique action command, and the practical strategies group can be in settlement steps to deal 3
Influence caused by each failure.
In the present embodiment, the control variable in step 1 includes：Main fuel flow, reinforcing fuel flow, fan blade angle
Degree, compressor blade angle, area of injection orifice.Wherein, compressor blade angle include α 1,
α2。
It is understood that as needed, other control variables can also be chosen.For example, valve area etc..In the application
In, each control variable can only adjust one, each can also adjust, as long as can reach the purpose of the application.
The application is further elaborated by way of example below, it is possible to understand that, which is not constituted to this
Any restrictions of application.
In the citing, the engine control scalar of selection is：Compressor blade angle includes α 1, α 2 and valve area
A8。
In the citing, combined fault type is：1 channel failures of α, N2 channel failures, controller hardware failure.
It establishes and handles tactful group shown in table 1：
Table 1：
Each strategy group is subjected to recombinant, to form practical strategies group, which can solve above-mentioned each
Influence caused by a failure.The practical strategies group such as table 2：
Table 2：
According to the practical strategies group of table 2, action command is carried out, to eliminate the influence caused by each failure.
The present invention also provides a kind of aeroengine control system combined fault logical process system, the aeroplane engines
Machine control system combined fault logical process system includes：
Policy storage unit is handled, the processing Policy storage unit is for storing processing strategy；
Fault memory cell, the fault memory cell is for storing engine failure；
Integral unit, the integral unit are used to that processing strategy and the fault memory cell in Policy storage unit will to be handled
In engine failure be associated；
Assembled unit, the processing strategy after the assembled unit is used to the integral unit being associated with carry out recombinant, from
And form practical strategies group；
Motor unit, the motor unit are formed by practical strategies group according to the assembled unit and are acted, to
Solve the influence caused by failure.
The aeroengine control system combined fault logical process method of the present invention can be reasonable orderly, effective
Handle aero-engine combined fault.
Advantageously, the aeroengine control system combined fault logical process method of the present invention is for full powers limit control
The fanjet of system control.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, it will be understood by those of ordinary skill in the art that：It is still
Can be with technical scheme described in the above embodiments is modified, or which part technical characteristic is equally replaced
It changes；And these modifications or replacements, the essence for various embodiments of the present invention technical solution that it does not separate the essence of the corresponding technical solution
God and range.
Claims (3)
1. a kind of aeroengine control system combined fault logical process method, which is characterized in that the aero-engine control
System in combination fault logic processing method processed includes the following steps：
Step 1：According to engine type, multiple engine controlled variables are chosen；
Step 2：Judge whether the failure that engine occurs is combined fault, if it is not, then stopping aeroengine control system group
Close fault logic processing method；If so, carrying out in next step；
Step 3：Enumerate each failure of the engine in the combined fault；
Step 4：There is provided a processing tactful group for each failure, wherein each processing strategy group includes the multiple starts
Machine controls the change of variable, and engine is made to pass through to each engine controlled variable in the multiple engine controlled variable
Change so as to solve the influence caused by the failure；
Step 5：Each processing strategy group in the step 4 is subjected to recombinant, to form practical strategies group, the practical plan
Each engine controlled variable in the multiple engine controlled variable slightly in group has unique action command, and the reality
Border strategy group can solve the influence caused by each failure in the step 3.
2. aeroengine control system combined fault logical process method as described in claim 1, which is characterized in that described
Control variable in step 1 includes：Main fuel flow, reinforcing fuel flow, fan blade angle, compressor blade angle, spray
Open area.
3. a kind of aeroengine control system combined fault logical process system, which is characterized in that the aero-engine control
System in combination fault logic processing system processed includes：
Policy storage unit is handled, the processing Policy storage unit is for storing processing strategy；
Fault memory cell, the fault memory cell is for storing engine failure；
Integral unit, the integral unit are used to handle in processing strategy and the fault memory cell in Policy storage unit
Engine failure is associated；
Assembled unit, the processing strategy after the assembled unit is used to the integral unit being associated with carries out recombinant, to shape
At practical strategies group；
Motor unit, the motor unit is formed by practical strategies group according to the assembled unit and is acted, to solve
Influence caused by failure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511008792.8A CN105626271B (en) | 2015-12-29 | 2015-12-29 | A kind of aeroengine control system combined fault logical process method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511008792.8A CN105626271B (en) | 2015-12-29 | 2015-12-29 | A kind of aeroengine control system combined fault logical process method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105626271A CN105626271A (en) | 2016-06-01 |
| CN105626271B true CN105626271B (en) | 2018-07-13 |
Family
ID=56041542
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201511008792.8A Active CN105626271B (en) | 2015-12-29 | 2015-12-29 | A kind of aeroengine control system combined fault logical process method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105626271B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107168297B (en) * | 2017-07-03 | 2019-08-13 | 电子科技大学 | A kind of reliability verification method and platform of flight-control computer |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3630745B2 (en) * | 1994-12-27 | 2005-03-23 | 富士重工業株式会社 | Failure diagnosis method for air-fuel ratio control system |
| US6550319B1 (en) * | 1998-11-30 | 2003-04-22 | Ford Global Technologies, Inc. | Fault diagnostic for an internal combustion engine having air assisted injectors |
| CN101666711B (en) * | 2009-09-16 | 2011-06-15 | 中国人民解放军海军航空工程学院 | Method for diagnosing engine integrated faults based on fuzzy semanteme network |
| CN104699068A (en) * | 2013-12-04 | 2015-06-10 | 贵州航空发动机研究所 | Universal simulator for aircraft engines |
| CN104050371B (en) * | 2014-06-17 | 2017-05-03 | 南京航空航天大学 | Multi-fault diagnosis method based on improved SDG |
| CN204028691U (en) * | 2014-06-27 | 2014-12-17 | 中航商用航空发动机有限责任公司 | Aeromotor hardware is in loop test system |
-
2015
- 2015-12-29 CN CN201511008792.8A patent/CN105626271B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105626271A (en) | 2016-06-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20200200090A1 (en) | Blockchain based vehicle control | |
| CN106575101B (en) | Feed back control system and electric power steering device | |
| US9346549B2 (en) | Method for regulating the de-icing of a leading edge of an aircraft and device for its implementation | |
| CN104870832B (en) | Hydraulic circuit and handling vehicle | |
| CN105626271B (en) | A kind of aeroengine control system combined fault logical process method | |
| US9457908B2 (en) | Self-cooled motor driven compressor | |
| EP2341232A3 (en) | Method for controlling fuel flow within a machine | |
| US20170152794A1 (en) | Waste gate assembly | |
| US8239088B2 (en) | Method for identifying a defective control device | |
| WO2009152511A3 (en) | Control flow deviation detection for software security | |
| EP2940317B1 (en) | Hydraulic circuit system for forced regeneration of diesel particulate filter | |
| JP6139791B2 (en) | Unmanned aerial vehicle and data processing method thereof | |
| CN105157296B (en) | The blower control method and control system of dual system cooling by wind | |
| US20140061517A1 (en) | Device for Regulating the Pressure and/or Mass Flow for a Space Propulsion System | |
| CN104594959A (en) | Automatic cylinder switch controlling system of turbine started through intermediate-pressure cylinder | |
| CN103967591A (en) | Diesel engine subsequent pressurizing structure with stable switching function and subsequent pressurizing method | |
| US20170306790A1 (en) | Fuel systems for turbomachines | |
| US10352261B2 (en) | Method for smoothly connecting a load during an activated cylinder deactivation process of an internal combustion engine | |
| US10174690B2 (en) | Auxiliary-machine control device, control system, turbocharger, control method, and program | |
| JP2013096408A5 (en) | ||
| EP3147221B1 (en) | Aircraft nitrogen generation and oxygen distribution | |
| US20180362176A1 (en) | Method for dynamic command limiting in a distributed control system | |
| JP6766587B2 (en) | Electronic control device | |
| CN207795350U (en) | The rapid regeneration device of DPF | |
| CN110077873B (en) | Anti-collision control method and device for sliding barrel of ship loader |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |