CN118953695A - An auxiliary system for determining the fault handling strategy of carrier-based aircraft engines - Google Patents
An auxiliary system for determining the fault handling strategy of carrier-based aircraft engines Download PDFInfo
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- CN118953695A CN118953695A CN202411032226.XA CN202411032226A CN118953695A CN 118953695 A CN118953695 A CN 118953695A CN 202411032226 A CN202411032226 A CN 202411032226A CN 118953695 A CN118953695 A CN 118953695A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
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- Aviation & Aerospace Engineering (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention discloses an auxiliary system for determining a fault treatment strategy of a carrier-based aircraft aeroengine, which comprises the following components: and the fault acquisition module is used for: for obtaining aviation of carrier-borne aircraft failure mode of the engine; the failure modes include: engine functional failure mode, risk level, and degree of association with control functions; the failure mode is obtained through interaction with the control system, and the association degree of the danger level and the control function is determined through preset analysis basic information; a fault state determination module: the system is used for extracting state points according to the fault mode, the working state and the activity flow and determining the alarm level; a fault handling policy determination module: for acquiring pilot response signals, determining treatment countermeasures, including pilot treatment countermeasures and control system treatment countermeasures. According to the technical scheme, fault treatment strategy analysis can be carried out from multiple aspects, complete and effective fault treatment countermeasures are formed, and the safe and reliable use of the engine is ensured.
Description
Technical Field
The invention relates to a safety design of a carrier-based aircraft aeroengine, in particular to an auxiliary system for determining a fault handling strategy of the carrier-based aircraft aeroengine.
Background
The aeroengine is a power source of the aircraft, and the normal and stable operation of the aeroengine is an important guarantee for the safe flight of the aircraft. However, the aero-engine has a complex structure and a plurality of flight processes, various faults are unavoidable in long-time working operation, when the engine encounters a fault, the operation thought and the disposal principle are incorrect in time, the flight accidents can be caused, and the catastrophic consequences of the death of the engine can be caused.
The establishment of a comprehensive and effective fault treatment strategy is an important guarantee for maintaining the normal operation of the aeroengine. The current common treatment countermeasures mostly take signal faults as traction, and the treatment countermeasures formulated on the basis of the signal faults are quite likely to not completely cover all critical functional fault states, and meanwhile, the design and implementation of an engine fault treatment strategy cannot be completely driven. To avoid the above problems, a technical solution is needed: the method can be used for effectively allocating the fault treatment strategy by taking the functional requirement as traction from forward design and determining the proper fault treatment strategy, so that the use safety of the engine is finally improved.
Disclosure of Invention
In order to achieve the above object, the present application provides an auxiliary system for determining a fault handling strategy of an aircraft engine of a carrier aircraft, comprising:
And the fault acquisition module is used for: for obtaining aviation of carrier-borne aircraft failure mode of the engine; the failure mode includes: engine functional failure mode, risk level, and degree of association with control functions; the failure mode is obtained through interaction with the control system, and the association degree of the dangerous grade and the control function is determined through preset analysis basic information;
a fault state determination module: the system is used for extracting state points according to the fault mode, the working state and the activity flow and determining the alarm level;
a fault handling policy determination module: for acquiring pilot response signals, determining treatment countermeasures, including pilot treatment countermeasures and control system treatment countermeasures;
and (3) a configuration module: for predefining the analysis basic information needed in the auxiliary system, and is loaded when other modules of the auxiliary system analyze.
The analysis basic information comprises a carrier-based aircraft engine working state, an activity flow, a degree of association of a failure mode and a control function and a carrier-based aircraft fault handling strategy analysis table; the association degree of the failure mode and the control function also comprises system level faults with the caused dangerous level of I and II type key function failure modes and dangerous level of I and II type key function failure modes related to the control function.
The contents of the ship-based aircraft fault handling policy analysis table include: activity, I, II failure modes, status points, pilot handling policies, system failure modes, control system handling policies, alert levels.
Further, the fault state determination module includes: the system comprises a scene definition unit, a state point determination unit and an alarm level determination unit;
The fault state determining module is used for extracting state points according to the fault mode, the working state and the activity flow and determining an alarm level;
The scene definition unit is used for interacting with the configuration module, acquiring an activity flow under a working scene, and determining the working state of the carrier-based aircraft aeroengine according to the activity flow;
The state point determining unit is used for obtaining state points on the basis of the activity flow; the carrier-based aircraft engine generates a failure mode in a flow link of an activity flow process, and a working state, treatment measures and alarm information in the flow link form a state point.
Further, when the disposal countermeasure determined by the failure disposal policy determination module is a pilot disposal countermeasure, defining the policy information includes: treatment timing, treatment procedure, and notes; attention is particularly paid in the context to attract a high degree of attention from the pilot.
When the treatment countermeasure determined by the fault treatment policy determining module is automatic treatment of the controller, fault treatment content is determined through fault reconstruction, parameter optimization and function degradation, and the generated policy information is a control plan or logic for automatic treatment of the control system.
Further, the fault handling policy determination module converts the handling countermeasures into control commands, which are transmitted to the control system and pilot side.
Further, after the failure acquisition module acquires the failure mode of the engine function, judging the dangerous grade of the failure mode, and if the dangerous grade is I and II and is related to the control function, continuing to determine and analyze the failure treatment strategy; otherwise, ending the fault handling policy determination analysis.
According to the invention, the forward design concept can be realized, the top-layer functional requirement is used as traction, the design and implementation of the engine fault treatment strategy are driven, all key functional fault states of the engine are ensured to be covered, the fault treatment strategy analysis is carried out from the aspects of scene analysis, defined state points, alarm levels, fault treatment countermeasures and the like, complete and effective fault treatment countermeasures are formed, and the safe and reliable use of the engine is ensured.
Drawings
Fig. 1 is a schematic structural diagram of an auxiliary system for determining a fault handling strategy of a carrier-based aircraft aeroengine according to an embodiment of the present invention;
Fig. 2 is a flowchart for determining a fault handling strategy for a carrier-based aircraft aeroengine provided according to an embodiment of the present invention;
FIG. 3 is a carrier-based aircraft takeoff activity flow provided according to an embodiment of the present invention;
Fig. 4 is a carrier-based aircraft landing activity flow provided according to an embodiment of the present invention.
Detailed Description
The auxiliary system for determining the fault treatment strategy of the aircraft engine of the carrier aircraft provided by the invention interacts with the engine control system and the pilot end, and realizes the analysis flow in the system: obtaining fault information from an engine control system, taking the risk analysis of the complete engine function as input and traction in an auxiliary system, defining an activity flow for carrying out scene analysis, failure criterion analysis and alarm level analysis aiming at a key function failure mode, providing effective fault treatment strategies from two dimensions of automatic treatment and pilot treatment, providing verification methods aiming at different fault treatment strategies, finally forming an engine fault treatment strategy covering all key function failure modes, and sending the fault treatment strategy to the control system or the pilot.
The following describes in detail the specific implementation of the present invention with reference to the drawings accompanying the specification.
The structure of the auxiliary system of the fault handling strategy of the aircraft-based aircraft engine is shown in fig. 1, and comprises: a P100 fault acquisition module, a P110 fault state determination module, a P120 fault handling policy determination module, and a P130 configuration module.
Wherein, the P130 configuration module may define in advance analysis basic information required in the auxiliary system, for example: the system comprises a carrier-based aircraft engine working state, an activity flow, a degree of association of failure modes and control functions and a carrier-based aircraft fault handling strategy analysis table; the association degree of the failure mode and the control function also comprises system level faults with the caused critical function failure modes of the I and the II types and critical function failure modes with the related critical function of the I and the II types.
The analysis basic information can be configured through a P130 configuration module and is called when other modules are applied; the information can be embedded into each module, so that the rule can be flexibly updated and applied during analysis of each module.
The association degree between the failure mode and the control function specifically comprises:
1) Critical functional failure modes of the dangerous class I and II related to the control function comprise that the engine thrust is reduced, the control function fails, the stress application is not on, the stress application is not off, the stress application is not expected to be off, the large and small throttle control fails, and the surge occurs.
2) The system level faults with the danger level of I and II key function failure modes are caused; taking the engine thrust drop as an example, the system level fault resulting in the engine thrust deficiency through control system Functional Hazard Analysis (FHA) includes: all redundancy faults of fan rotating speed, all redundancy faults of compressor outlet static pressure, corresponding redundancy faults of main fuel metering valve displacement, all redundancy faults of a nozzle electro-hydraulic servo valve, two-channel fault of the nozzle electro-hydraulic servo valve main control and failure of a switching valve, all redundancy faults of nozzle throat angle, and all redundancy faults of nozzle area control oil distributing valve displacement.
The carrier-based aircraft fault handling strategy analysis table specifically comprises: activity, I, II failure modes, status points, pilot handling strategies, system failure modes, control system handling strategies, alarm levels, etc.
P100: and the fault acquisition module is used for: for obtaining aviation of carrier-borne aircraft failure mode of the engine.
Specifically, the failure modes include: engine functional failure mode, risk level, and degree of association with control functions; wherein the failure mode is obtained through interaction with the control system; the risk level and the association degree with the control function are determined through preset analysis basic information.
The analysis basic information can be loaded from the P130 configuration module or can be stored in a reserved space in the fault acquisition module and then loaded.
Generally, the functions of the whole engine, the system and the parts are determined in the scheme stage, the function failure state of the whole engine, the system and the parts is identified through the function hazard analysis, the Function Hazard Analysis (FHA) of the whole engine is taken as input and traction, and the hazard class I and II function failure modes related to the control function are selected as analysis objects to carry out fault handling strategy analysis.
The process flow of the failure acquisition module is provided in step S100 of fig. 2: after the failure modes of the engine function are acquired, judging that the dangerous level is the I and II type failure modes and is related to the control function, and continuing to confirm and analyze the fault treatment strategies of other subsequent modules; otherwise, ending the fault handling policy determination analysis.
The invention provides an embodiment, in an auxiliary system for determining a fault handling strategy of a carrier-based aircraft engine, the fault handling strategy determination is carried out aiming at a BE carrier-based aircraft engine.
The BE carrier-based aircraft engine is a double-rotor turbofan engine with afterburners, and provides power for carrier-based aircraft catapulting/sliding take-off, carrier landing and combat, cabin air entraining and power required by an aircraft. In the working process of the carrier-based aircraft, the fault acquisition module acquires the working state and the failure mode of the BE carrier-based aircraft engine through the engine control system.
P110: a fault state determination module: the system is used for extracting state points according to the fault mode, the working state and the activity flow and determining the alarm level;
The fault state determination module includes: a P111 scene definition unit, a P112 state point determination unit and a P113 alarm level determination unit;
the P111 scene definition unit is used for interacting with the configuration module, acquiring an activity flow under the working scene, and determining the working state of the aircraft engine of the carrier aircraft according to the activity flow;
The working state of the engine of the carrier-based aircraft comprises the contents of carrier surface starting, taking off, transition state, non-stress stabilization, stress application, air starting, descending, carrier landing and the like; and defining the activity flow under different working scenes according to the requirements of the aircraft carrier on-board mission, wherein the activity flow is defined in a configuration mode in advance. Under different activity flows, the ship-based aircraft engine can be in different working states.
The working state and the activity flow of the engine of the carrier-based aircraft can be loaded from the P130 configuration module, and a reserved space can be reserved in the fault state determining module for storage.
Specifically, the carrier-based aircraft has different activity flows under different scenes, for example, fig. 3 is a carrier-based aircraft take-off activity flow, and fig. 4 is a carrier-based aircraft landing activity flow.
The P112 state point determining unit is used for acquiring state points on the basis of the activity flow.
Specifically, the carrier-based aircraft engine fails in a flow link of an activity flow process, and the control system outputs a failure mode, and the working state, the treatment measures and the alarm information in the link form a state point. In practical applications, the specific content of the formulated state point, such as treatment measures and alarm information, can be studied together by the aircraft side and the engine side. In the invention, in order to accurately formulate pilot treatment measures and control system treatment measures, state points are thinned and stored in a carrier-based aircraft fault treatment strategy analysis table.
In this embodiment, based on the carrier-based aircraft take-off activity flow shown in fig. 3, when the carrier-based aircraft activity flow reaches the link S301 "pilot pushes the throttle lever to the maximum stress state", and confirms the on-board state ", if a failure occurs at this time, the failure mode" engine thrust down "is acquired by the failure acquisition module, at this time, the state point is determined, the content includes the" landing gear bearing "state, the throttle lever position is at the maximum stress position, and the" rotation speed failure "alarm and the" nozzle adjustment failure "alarm are displayed. Specifically, for this status point, the detailed content can be extracted from the carrier-based aircraft fault handling policy analysis table as shown in table 1:
TABLE 1
The P113 alarm level determining unit is used for determining an alarm level according to the severity of the fault mode and the specific scene, and the content of the state point comprises the following components: alert, attention, and prompt. The alert level may provide input for subsequent alert designs.
The alarm level is determined as follows:
a) If the pilot is required to immediately recognize the fault situation and immediately take corrective or compensatory action, a warning level should be determined;
b) If the pilot is required to immediately know the fault condition and take action at a later time, the level of attention should be determined;
If the pilot is required to be aware of the fault situation and take action at a later time, a hint level should be determined.
The process flow of the fault state determination module is shown in step S110 of fig. 2.
P120: a fault handling policy determination module; for acquiring pilot response signals, determine treatment countermeasures, including pilot treatment countermeasures and control system treatment countermeasures.
When the handling countermeasure is a pilot handling countermeasure, defining the policy information includes: treatment timing, treatment procedure, and notes; and special emphasis is placed on the content to bring high attention to the pilot;
If the treatment countermeasure is automatic treatment of the controller, the fault treatment strategy determining module performs fault treatment through methods of fault reconstruction, parameter optimization, function degradation and the like, and the generated strategy information is a control plan or logic for automatic treatment of the control system. The policy information generating operation instruction may be subsequently sent to the control system.
In determining the disposition countermeasure, the logic of the failure disposition policy determination module includes:
Acquiring a pilot response signal, and if the pilot tries to intervene in the fault, determining that the fault handling strategy comprises pilot handling countermeasures;
analyzing pilot history handling information, judging the pilot handling countermeasure of the pilot and the proportion of automatic handling of the controller, and if the majority of the pilot is the pilot handling countermeasure, determining that the current fault handling policy is the pilot handling countermeasure;
And acquiring a scene of the fault mode, and if the processing instruction corresponding to the scene is clear, and the content of the processing instruction is a parameter adjustment and functional instruction, giving priority to the current fault treatment strategy as a controller treatment countermeasure.
The fault handling policy determination module may determine multiple handling countermeasures at a time, and the pilot handling countermeasures and the control system handling countermeasures may act on one fault mode at the same time. And for class i and ii failure situations, pilot handling countermeasures must be taken.
The specific flow is shown in step S230 of fig. 2.
After the treatment countermeasure is determined, the control system continues to interact, whether the treatment countermeasure is effective or not is judged, and if the treatment countermeasure is ineffective, the fault treatment countermeasure is re-proposed.
In the embodiment of the invention, based on the carrier-based aircraft take-off activity flow shown in fig. 3, when the carrier-based aircraft activity flow reaches S301 "pilot pushes the throttle lever to the maximum stress state, the on-board state is confirmed", and at this time, an engine thrust decline failure mode occurs, the risk class of the failure mode is class i, and a fault handling strategy is proposed from two dimensions of pilot handling and control system handling, and the specific content is shown in table 1.
Finally, the fault handling strategy determining module converts handling countermeasures into control instructions, and transmits the control instructions to a control system and a pilot side to determine the fault handling strategy of the aircraft engine of the carrier-based aircraft.
The invention relates to an auxiliary system for realizing an analysis method based on system engineering thinking, wherein a forward design concept can be realized in the auxiliary system, the top-layer functional requirement is used as traction, the design and realization of an engine fault treatment strategy are driven, all key functional fault states of an engine are ensured to be covered, the fault treatment strategy analysis is carried out from the aspects of scene analysis, defined state points, alarm levels, fault treatment countermeasures and the like, complete and effective fault treatment countermeasures are formed, and the safe and reliable use of the engine is ensured.
The above disclosure is only a few specific embodiments of the present invention, but the present invention is not limited thereto, and any changes that can be thought by those skilled in the art should fall within the protection scope of the present invention.
Claims (9)
1. An auxiliary system for determining a fault handling strategy for an aircraft-based aircraft engine, comprising:
And the fault acquisition module is used for: for obtaining aviation of carrier-borne aircraft failure mode of the engine; the failure mode includes: engine functional failure mode, risk level, and degree of association with control functions; the failure mode is obtained through interaction with the control system, and the association degree of the dangerous grade and the control function is determined through preset analysis basic information;
A fault state determination module: the alarm level is determined according to the fault mode, the working state and the state point extracted by the activity flow;
A fault handling policy determination module: for acquiring pilot response signals, determine treatment countermeasures, including pilot treatment countermeasures and control system treatment countermeasures.
2. The auxiliary system according to claim 1, wherein the analysis basic information comprises a carrier-based aircraft engine working state, an activity flow, a degree of association of a failure mode and a control function, and a carrier-based aircraft fault handling policy analysis table; the association degree of the failure mode and the control function also comprises system level faults with the caused critical function failure modes of the class I and the class II, and critical function failure modes with the critical function failure modes of the class I and the class II related to the control function.
3. The auxiliary system of claim 2, wherein the contents of the carrier-based aircraft fault handling policy analysis table comprise: activity, I, II failure modes, status points, pilot handling policies, system failure modes, control system handling policies, alert levels.
4. The assistance system of claim 1, further comprising a configuration module;
the configuration module is used for predefining analysis basic information needed in the auxiliary system and loading the analysis basic information when other modules of the auxiliary system analyze the analysis basic information.
5. The assistance system of claim 3, wherein the fault condition determination module comprises: the system comprises a scene definition unit, a state point determination unit and an alarm level determination unit;
the fault state determination module: the alarm level is determined according to the fault mode, the working state and the state point extracted by the activity flow;
The scene definition unit is used for interacting with the configuration module, acquiring an activity flow under a working scene, and determining the working state of the carrier-based aircraft aeroengine according to the activity flow;
the state point determining unit is used for acquiring state points on the basis of the activity flow; the carrier-based aircraft engine generates a failure mode in a flow link of an activity flow process, and a working state, treatment measures and alarm information in the flow link form a state point.
6. The assistance system of claim 1, wherein defining policy information when the treatment countermeasure determined by the fault treatment policy determination module is a pilot treatment countermeasure comprises: treatment timing, treatment procedure, and notes; attention is particularly paid in the context to attract a high degree of attention from the pilot.
7. The assist system of claim 1 wherein when the treatment countermeasure determined by the fault treatment policy determination module is controller automatic treatment, fault treatment content is determined by fault reconstruction, parameter preference, functional degradation, and the generated policy information is a control plan or logic for control system automatic treatment.
8. The assistance system of claim 1, wherein the fault handling policy determination module converts handling countermeasures into control instructions for transmission to the control system and pilot side.
9. The auxiliary system according to claim 1, wherein after the failure acquisition module acquires the failure mode of the engine function, judging a risk level of the failure mode, and if the risk level is of a class i or a class ii and is related to a control function, continuing the failure handling strategy determination analysis; otherwise, ending the fault handling policy determination analysis.
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| CN202411032226.XA CN118953695A (en) | 2024-07-30 | 2024-07-30 | An auxiliary system for determining the fault handling strategy of carrier-based aircraft engines |
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| CN202411032226.XA CN118953695A (en) | 2024-07-30 | 2024-07-30 | An auxiliary system for determining the fault handling strategy of carrier-based aircraft engines |
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