CN114183251A - Surge protection control method for aircraft engine - Google Patents
Surge protection control method for aircraft engine Download PDFInfo
- Publication number
- CN114183251A CN114183251A CN202111316224.XA CN202111316224A CN114183251A CN 114183251 A CN114183251 A CN 114183251A CN 202111316224 A CN202111316224 A CN 202111316224A CN 114183251 A CN114183251 A CN 114183251A
- Authority
- CN
- China
- Prior art keywords
- engine
- surge protection
- aircraft
- signal
- state
- 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.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 27
- 230000003213 activating effect Effects 0.000 claims abstract description 4
- 230000005283 ground state Effects 0.000 claims description 6
- 238000007689 inspection Methods 0.000 abstract description 3
- 230000002035 prolonged effect Effects 0.000 abstract description 2
- 206010063385 Intellectualisation Diseases 0.000 abstract 1
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 239000000725 suspension Substances 0.000 description 2
- 230000004913 activation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Images
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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention provides an aircraft engine surge protection control method, which comprises the following steps: s1: in an initial state, the electromechanical management computer collects the criterion parameters of engine control in real time; s2: judging the state of the airplane according to the criterion parameters; s3: acquiring relevant data of the engine according to the airplane state acquired by the S3, and creating an engine state file; s4: and after carrying out logic operation on the relevant data of the engine collected in the S4, activating an engine surge protection system, and synchronously transmitting the relevant data of the engine to data recording equipment for storage. The method realizes the surge protection control of the engine, enhances the fault-tolerant capability of the fault mode of the engine system, improves the ground inspection safety and the intellectualization of the engine system, and reduces control parts under the traditional control mode; meanwhile, the service life of the engine system is prolonged, so that the development and use cost of the system is reduced, and the method has important application value.
Description
Technical Field
The invention belongs to the technical field of avionics, and particularly relates to a surge protection control method for an aircraft engine.
Background
Surge is an unstable operating condition of an aircraft engine. If surging occurs, the engine working condition is rapidly worsened (stopped) if the surging occurs, and the engine mechanical damage is caused if the surging occurs, so that the flight safety is seriously endangered, therefore, the surging is accurately identified in time at the beginning of the surging or the initial stage of the surging of the engine, and corresponding surging eliminating measures (such as surging protection) are adopted, which is an important precondition for avoiding serious accidents of the engine, such as air stopping, blade fracture and the like.
Therefore, it is desirable to provide a surge protection control method for an aircraft engine to improve the working performance of the aircraft engine, and ensure that the aircraft engine can be normally started and normally operated under transient and steady conditions during ground inspection, no surge occurs, and stopping is avoided.
Disclosure of Invention
In order to solve the technical problems, the electromechanical management computer acquires input criterion parameters related to engine surge protection control from an onboard machine in real time, and after logical operation and judgment are carried out, control instructions are periodically output to an onboard engine system through a 1553B bus, and are collected at the same time, so that the engine surge protection control is realized.
The invention aims to provide an aircraft engine surge protection control method, which comprises the following steps:
s1: in an initial state, the electromechanical management computer collects the criterion parameters of engine control in real time;
s2: judging the state of the airplane according to the criterion parameters;
s3: acquiring relevant data of the engine according to the airplane state acquired by the S3, and creating an engine state file;
s4: and after carrying out logic operation on the relevant data of the engine collected in the S4, activating an engine surge protection system, and synchronously transmitting the relevant data of the engine to data recording equipment for storage.
The aircraft engine surge protection control method provided by the invention is also characterized in that the criterion parameters comprise an engine self-checking switch signal, an engine system switch signal, an engine working/cold running signal, a rear flap landing position 30 degree signal, a flap takeoff position 20 degree signal and an aircraft landing gear wheel load signal.
The aircraft engine surge protection control method provided by the invention is also characterized in that the aircraft state comprises an aircraft ground state, and the aircraft ground state refers to that the voltage of a nose landing gear wheel-borne signal is effective, the voltage of a left landing gear wheel-borne signal is effective, the voltage of a right landing gear wheel-borne signal is effective, meanwhile, a rear flap landing position 30-degree signal is ineffective in suspension, and a flap takeoff position 20-degree signal is ineffective in suspension.
The aircraft engine surge protection control method provided by the invention is also characterized in that the acquisition period of the related data in the S3 is 50 milliseconds.
The aircraft engine surge protection control method provided by the invention is also characterized in that the engine state file in the S3 comprises engine state information, wherein the engine state information refers to that an engine self-detection switch signal is valid as the ground, an engine normal/emergency system switch signal is valid as the ground and an engine working/cold running signal is valid as the ground.
The aircraft engine surge protection control method provided by the invention is also characterized in that the output period of the engine control command in the S4 is 50 milliseconds.
The aircraft engine surge protection control method provided by the invention is also characterized in that the S4 further comprises the step of controlling the output of the electromechanical management computer in the form of 1553B bus parameter values to be in an engine surge protection system state so as to activate the engine to enter the surge protection system.
Compared with the prior art, the invention has the beneficial effects that:
according to the aircraft engine surge protection control method provided by the invention, the electromechanical management computer is used for acquiring input criterion parameters related to engine surge protection control from an aircraft in real time, after logical operation and judgment are carried out, a control instruction is periodically output to an onboard engine system through a 1553B bus, and the control instruction is acquired back at the same time, so that the engine surge protection control is realized, the fault-tolerant capability of a fault mode of the engine system is enhanced, the ground inspection safety and the intelligence of the engine system are improved, and control parts under the traditional control mode are reduced; meanwhile, the service life of the engine system is prolonged, so that the development and use cost of the system is reduced, and the method has important application value.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1: the invention provides a flow chart of a surge protection control method of an aircraft engine.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the following embodiments are specifically described in the aircraft engine surge protection control method provided by the invention with reference to the attached drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
As shown in fig. 1, an embodiment of the present invention provides an aircraft engine surge protection control method, which is based on the characteristics that an electromechanical management computer has independent onboard data real-time acquisition, recording, data comprehensive management, control output, state monitoring, and the like, and adopts an electromechanical management computer engine surge protection control algorithm to control activation and shutdown of an aircraft engine surge protection system, so as to realize switching between an "oil tank group 1" and an "oil tank group 2", thereby realizing control of aircraft engine system surge protection.
The method comprises the following steps:
s1: in an initial state, the electromechanical management computer collects the criterion parameters of engine control in real time;
s2: judging the state of the airplane according to the criterion parameters;
s3: acquiring relevant data of the engine according to the airplane state acquired by the S3, and creating an engine state file;
s4: and after carrying out logic operation on the relevant data of the engine collected in the S4, activating an engine surge protection system, and synchronously transmitting the relevant data of the engine to data recording equipment for storage.
In some embodiments, the criterion parameters include an engine self-check switch signal, an engine system switch signal, an engine working/cold running signal, a rear flap landing position 30 ° signal, a flap takeoff position 20 ° signal, and an aircraft landing gear wheel load signal.
In some embodiments, the aircraft state comprises an aircraft ground state, and the aircraft ground state refers to that the voltage of a nose landing gear wheel load signal is valid, "27V" voltage of a left landing gear wheel load signal is valid, the voltage of a right landing gear wheel load signal is valid, "27V" voltage of a right landing gear wheel load signal is valid, and meanwhile, a rear flap landing position 30 ° signal is invalid, "floating" and a flap takeoff position 20 ° signal is invalid.
In some embodiments, the acquisition period of the relevant data in S3 is 50 milliseconds.
In some embodiments, the engine state file in S3 includes engine state information indicating that the engine self-check switch signal is active, the engine normal/emergency system switch signal is active, and the engine on/cold signal is active.
In some embodiments, the output period of the engine control command in S4 is 50 milliseconds.
In some embodiments, the S4 further comprises the electromechanical supervisory computer controlling the output in the form of 1553B bus parameter values to an "engine surge protection system" state to activate the engine to enter the surge protection system.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (7)
1. An aircraft engine surge protection control method, characterized in that it comprises the steps of:
s1: in an initial state, the electromechanical management computer collects the criterion parameters of engine control in real time;
s2: judging the state of the airplane according to the criterion parameters;
s3: acquiring relevant data of the engine according to the airplane state acquired by the S3, and creating an engine state file;
s4: and after carrying out logic operation on the relevant data of the engine collected in the S4, activating an engine surge protection system, and synchronously transmitting the relevant data of the engine to data recording equipment for storage.
2. The aircraft engine surge protection control method of claim 1, wherein the criterion parameters include an engine self-check switch signal, an engine system switch signal, an engine on/cold run signal, a rear flap landing position 30 ° signal, a flap takeoff position 20 ° signal, and an aircraft landing gear on-wheel signal.
3. The aircraft engine surge protection control method of claim 1, wherein the aircraft state comprises an aircraft ground state, and the aircraft ground state refers to that a voltage of a nose landing gear wheel load signal "27V" is valid, a voltage of a left landing gear wheel load signal "27V" is valid, a voltage of a right landing gear wheel load signal "27V" is valid, and simultaneously a 30 ° signal of a rear flap landing position is "suspended" is invalid, and a 20 ° signal of a flap takeoff position is "suspended" is invalid.
4. The aircraft engine surge protection control method of claim 1, wherein the collection period of the relevant data in S3 is 50 milliseconds.
5. The aircraft engine surge protection control method of claim 1, wherein the engine status file in S3 includes engine status information indicating that the engine self-check switch signal is active "ground", the engine normal/emergency system switch signal is active "ground", and the engine on/off cold signal is active "ground".
6. The aircraft engine surge protection control method of claim 1, wherein the output period of the engine control command in S4 is 50 milliseconds.
7. The aircraft engine surge protection control method of claim 1, wherein said S4 further comprises the electromechanical supervisory computer controlling the output in the form of 1553B bus parameter values to an "engine surge protection system" state to activate the engine into the surge protection system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111316224.XA CN114183251A (en) | 2021-11-08 | 2021-11-08 | Surge protection control method for aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111316224.XA CN114183251A (en) | 2021-11-08 | 2021-11-08 | Surge protection control method for aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114183251A true CN114183251A (en) | 2022-03-15 |
Family
ID=80540815
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111316224.XA Pending CN114183251A (en) | 2021-11-08 | 2021-11-08 | Surge protection control method for aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114183251A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103640692A (en) * | 2013-11-28 | 2014-03-19 | 陕西千山航空电子有限责任公司 | Handle-based autonomous control method of training plane undercarriage system |
| CN110427045A (en) * | 2019-07-17 | 2019-11-08 | 陕西千山航空电子有限责任公司 | A kind of adaptive implementation method of aero-engine multimode |
| CN110657031A (en) * | 2019-09-30 | 2020-01-07 | 山东超越数控电子股份有限公司 | Method for identifying surge of aircraft engine |
| RU2751467C1 (en) * | 2020-10-29 | 2021-07-14 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-воздушных сил "Военно-воздушная академия имени профессора Н.Е. Жуковского и Ю.А. Гагарина" (г. Воронеж) Министерства обороны Российской Федерации | Method for rapid diagnostics of pre-surge condition of gas turbine engines of aircraft |
| CN113482960A (en) * | 2021-06-23 | 2021-10-08 | 中国航发沈阳发动机研究所 | Method for judging surge of aviation gas turbine engine |
-
2021
- 2021-11-08 CN CN202111316224.XA patent/CN114183251A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103640692A (en) * | 2013-11-28 | 2014-03-19 | 陕西千山航空电子有限责任公司 | Handle-based autonomous control method of training plane undercarriage system |
| CN110427045A (en) * | 2019-07-17 | 2019-11-08 | 陕西千山航空电子有限责任公司 | A kind of adaptive implementation method of aero-engine multimode |
| CN110657031A (en) * | 2019-09-30 | 2020-01-07 | 山东超越数控电子股份有限公司 | Method for identifying surge of aircraft engine |
| RU2751467C1 (en) * | 2020-10-29 | 2021-07-14 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-воздушных сил "Военно-воздушная академия имени профессора Н.Е. Жуковского и Ю.А. Гагарина" (г. Воронеж) Министерства обороны Российской Федерации | Method for rapid diagnostics of pre-surge condition of gas turbine engines of aircraft |
| CN113482960A (en) * | 2021-06-23 | 2021-10-08 | 中国航发沈阳发动机研究所 | Method for judging surge of aviation gas turbine engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9327600B1 (en) | Aircraft utilities and power distribution system | |
| CN207908981U (en) | A kind of system for flight control computer | |
| CN112379694A (en) | Emergency processing method and system for flight fault | |
| CN101797978A (en) | Brake integrated controller of unmanned plane | |
| CN110239743A (en) | The method of controlling security of dynamical system in helicopter W.T test | |
| CN109378884A (en) | Fault grading and interaction control system and method based on battery management system | |
| CN113093618B (en) | Brake controller hardware architecture and control method | |
| CN109445402A (en) | A kind of Fuel On Board system is from monitoring to computer control method | |
| CN204928331U (en) | Battery cell , unmanned aerial vehicle and external member that is used for assembling into unmanned aerial vehicle | |
| CN103640692A (en) | Handle-based autonomous control method of training plane undercarriage system | |
| CN201321949Y (en) | Safety device for wind generating set | |
| CN109693625A (en) | Automobile standby power supply module and automobile power supply system comprising it | |
| EP1350942A2 (en) | Thrust control malfunction accomodation system and method | |
| CN111261458B (en) | Contactor control method adopting non-similar dual processors in aviation power distribution system | |
| WO2021012474A1 (en) | Vehicle control system and control method for electric airline catering truck | |
| US8905720B2 (en) | Arrangement and method for monitoring a hydraulic system | |
| CN114183251A (en) | Surge protection control method for aircraft engine | |
| CN113608429A (en) | Distributed redundancy unmanned aerial vehicle | |
| CN113525700A (en) | Health monitoring system for single-machine structure of airplane | |
| CN106628248A (en) | Alarming method and system and monitoring terminal applied to airplane | |
| CN115817548A (en) | Rail vehicle air conditioner control method, device and medium thereof | |
| CN106741861B (en) | A kind of bipolar direct drive valve actuator current protection strategy | |
| CN115290137A (en) | Vxworks-based real-time fault diagnosis method for fuel oil supply system | |
| CN112078807B (en) | Control system and method for reversing solenoid valve of aircraft fuel system | |
| CN113815636A (en) | Vehicle safety monitoring method and device, electronic equipment and storage medium |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20220315 |