CN105626270B - A kind of full authority control system fault-tolerance approach of fanjet - Google Patents
A kind of full authority control system fault-tolerance approach of fanjet Download PDFInfo
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- CN105626270B CN105626270B CN201511007923.0A CN201511007923A CN105626270B CN 105626270 B CN105626270 B CN 105626270B CN 201511007923 A CN201511007923 A CN 201511007923A CN 105626270 B CN105626270 B CN 105626270B
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- 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
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Abstract
The invention discloses a kind of full authority control system fault-tolerance approach of fanjet.The full authority control system fault-tolerance approach of fanjet comprises the following steps：Step 1：The signal that each sensor that full powers are rationed the power supply on control control system reception fanjet is transmitted；Step 2：Judge whether the signal that sensor is transmitted breaks down, if it is not, then terminating；If so, then carrying out next step；Step 3：Judge the species of failure occurred in the step 2；Step 4：The fault-tolerant solution when the failure of the species stored during the full powers ration the power supply control control system occurs is transferred, and performs the fault-tolerant solution.The full authority control system fault-tolerance approach of fanjet of the present invention realizes reconfiguring and optimize and not only substantially increasing the functional reliability of control system for Control system architecture and control system plan when the sensor signal failure such as rotating speed, temperature occurs in control system by the full authority control system fault-tolerance approach of fanjet of the present invention.
Description
Technical field
The present invention relates to fanjet control technology field, more particularly to a kind of full control of authority system of fanjet
Fault-tolerance approach of uniting and the full authority control system tolerant system of fanjet.
Background technology
Fault Tolerance Control Technology refers in the case where some component malfunctions cause original control plan not realize, controls
System processed passes through adjust automatically control plan and control structure, it is ensured that engine remain to by original performance or performance slightly have reduction and
It is safely completed the technology of set control task.Utilize the powerful computing capability of modern computer, logic judgment ability and decision-making
Ability, in terms of engine reliability and maintainability is improved, achieves good effect.Original machinery hydraulic pressure control system
Because the parameter of its synthesis is limited, whether it can not be realized as computing element using three-D cam or capsule stack more multiple
Miscellaneous control logic so that fault-tolerant design technique can not access effective hair in the control system based on mechanical-hydraulic
Exhibition.
Existing single fanjet aircraft has redundancy engine control system, and redundancy engine control system includes mutual
Rationed the power supply control control system and machinery hydraulic pressure control system for the full powers of redundancy, wherein, full powers control control system of rationing the power supply is master control
System, machinery hydraulic pressure control system is used as back-up system.In the above-mentioned aircraft with redundancy engine control system, do not have still
A kind of fault-tolerance approach.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
Overcome or at least it is an object of the invention to provide a kind of full authority control system fault-tolerance approach of fanjet
Mitigate at least one drawbacks described above in prior art.
To achieve the above object, the present invention provides a kind of full authority control system fault-tolerance approach of fanjet, for list
Fanjet aircraft, single fanjet aircraft has redundancy engine control system, the redundancy engine control
System includes the full powers that are mutually redundant and rationed the power supply control control system and machinery hydraulic pressure control system, wherein, the full powers are rationed the power supply control
Control system is master control system, and the machinery hydraulic pressure control system is as back-up system, the full control of authority of fanjet
System Fault Tolerance method comprises the following steps：
Step 1：The signal that each sensor that full powers are rationed the power supply on control control system reception fanjet is transmitted；
Step 2：Judge whether the signal that sensor is transmitted breaks down, if it is not, then terminating；If so, then carrying out next
Step；
Step 3：Judge the species of failure occurred in the step 2；
Step 4：Transfer the fault-tolerant solution when the failure of the species stored during the full powers ration the power supply control control system occurs
Certainly method, and perform the fault-tolerant solution.
Preferably, the species of the failure occurred in the step 3 includes：Sensor extreme value failure, engine parameter failure,
Engine parameter loop fault, sensor slope failure, digital electronic controller calculate failure, dutycycle electromagnetism failure, started
The small value failure in machine loop, the big value failure of engine circuit.
Preferably, the signal that the sensor is transmitted includes：nLChannel signal, nHChannel signal, T6Adjust passage letter
Number, α1Adjust channel signal, α2Adjust channel signal, πTChannel signal, spout regulation channel signal, Lm signals, L1 signals, Li
Signal, Lo signals, PLA Measurement channels signal, T1Measurement channel signal, T25Measurement channel signal, P31Measurement channel signal, P6Survey
Measure channel signal, PHMeasurement channel signal, Ln Measurement channels signal, LA1 Measurement channels signal, LA2 Measurement channels signal, numeral
Electronic controller signal, dutycycle electromagnetic signal.
Preferably, the fault-tolerant solution in the step 4 includes：
When nL channel signal failures, and failure mode is sensor extreme value failure, engine parameter failure, engine parameter
One in loop fault, sensor slope failure, then use and abandon nLPassage is controlled, and normal channel drop state is used；α1Favourable turn
The method of tool hydraulic control；
Work as nHChannel signal failure, and failure mode is sensor extreme value failure, engine parameter failure, engine parameter
One in loop fault, sensor slope failure, then use and abandon nHEvent is sentenced in passage control；α2Go to hydraulic pressure Standby control；
When T6 regulation channel signal failures, and failure mode is sensor extreme value failure, engine parameter failure, engine
One in parameter loop fault, sensor slope failure, then use and abandon T6Passage is controlled, the event of normal channel channel signal
Barrier, and failure mode is sensor extreme value failure, engine parameter failure, engine parameter loop fault, sensor slope event
One in barrier, then using α1Favourable turn tool hydraulic control；
Work as α2Channel signal failure is adjusted, and failure mode is that biography turns physical training condition control；
Work as α1One in regulation sensor extreme value failure or sensor slope failure, then using α2Favourable turn tool hydraulic control；If
Failure mode is sentenced therefore moment α to pass engine parameter loop fault2Whether control law is n2r25Control law, if so,
Then α2Switch to byControl law is controlled；If it is not, then going to α2Standby control；
Work as πTChannel signal failure, and failure mode is the small value failure of engine circuit, then judges fanjet state,
If fanjet is in Afterburning condition spout closed-loop control, by spout feedforward area amplification；If fanjet is in non-
During Afterburning condition, closed-loop control spout, and forbid reinforcing；If fanjet is in middle following state, π is removedTPassage
The small value failure of engine circuit, and cancel π after the failure is removedTTo spout in the small value trouble shooting of engine circuit of passage
When, feedforward area amplification, and allow engine to enter reinforcing；Work as πTChannel signal failure, and failure mode is engine circuit
Big value failure, then judge fanjet state, if fanjet is in Afterburning condition spout closed-loop control, spout still presses πT
Closed loop and the feedforward high selected control system of area；If fanjet is in non-Afterburning condition, spout closed-loop control, and forbid adding
Power；Work as πTMeasured value is less than πTDuring planned value+k, it is allowed to which fanjet is reinforced；
When spout regulation channel signal failure, and failure is sensor extreme value failure or sensor slope failure, then judges
Fanjet state, is pressed if fanjet is in middle and middle following stateOpen loop folding and unfolding control is carried out to spout
System, spout is received to minimum mechanical stop position or put to maximum machine stop position；It is prohibited from entering reinforcing；If fanjet
Turn mechanical-hydraulic Standby control during in Afterburning condition；If failure is engine parameter loop fault, tool hydraulic control of making a connection；
When Lm signal faults, and fault type is sensor extreme value failure, engine parameter failure, engine parameter loop
One kind in failure, sensor slope failure, then turn hydraulic machinery control；
When L1 signal faults, and fault type is sensor extreme value failure, engine parameter loop fault, sensor slope
One kind in failure, then judge fanjet state, and reinforcing locking logic is carried out in Afterburning condition；In non-Afterburning condition
When, it is prohibited from entering Afterburning condition；
When Li signal faults, and fault type is sensor extreme value failure, engine parameter loop fault, sensor slope
One kind in failure, then judge fanjet state, and reinforcing locking logic is carried out in Afterburning condition；In non-Afterburning condition
When, it is prohibited from entering Afterburning condition；
When Lo signal faults, and fault type is sensor extreme value failure, engine parameter loop fault, sensor slope
One kind in failure, then judge fanjet state, and reinforcing locking logic is carried out in Afterburning condition；In non-Afterburning condition
When, it is prohibited from entering Afterburning condition；
When PLA Measurement channel signal faults, and fault type is sensor extreme value failure or sensor slope failure, then turns
Back-up hydro-mechanical is controlled；
Work as T1Measurement channel signal fault, and fault type be sensor extreme value failure, engine parameter loop fault or
One kind in sensor slope failure, then turn back-up hydro-mechanical control；
Work as T25Measurement channel signal fault, and fault type be sensor extreme value failure, engine parameter loop fault or
One kind in sensor slope failure, then by α 2 be transformed into byControl；
Work as P31Measurement channel signal fault, and fault type be sensor extreme value failure, engine parameter loop fault or
One kind in sensor slope failure, then turn mechanical-hydraulic Standby control；
Work as P6Measurement channel signal fault, and fault type is sensor extreme value failure, engine parameter loop fault, biography
One kind in sensor slope failure, judges fanjet state, if in Afterburning condition, spout amplifies according to spout feedforward area
To control, exit after Afterburning condition and forbid being again introduced into Afterburning condition；If fanjet state is in middle and middle following shape
State, then be prohibited from entering Afterburning condition；
Work as PHMeasurement channel signal fault, and fault type is sensor extreme value failure or sensor slope failure, then sentences
Whether the altitude signal of disconnected aircraft is normal, if then rebuilding P by altitude signalH；
When Ln Measurement channel signal faults, and fault type is sensor extreme value failure or sensor slope failure, then turns
Mechanical-hydraulic Standby control；
When LA1 Measurement channel signal faults, and fault type is sensor extreme value failure, sensor slope failure, then α1
Still pressNormal control；
When LA2 Measurement channel signal faults, and fault type is sensor extreme value failure, sensor slope failure, then α2
Still rationed the power supply by full powers and control control system control；
When digital electronic controller signal fault, and result of calculation is not inconsistent with expected results, then it is assumed that digital and electronic is controlled
Cpu fault in device, turns mechanical-hydraulic Standby control；
When dutycycle electromagnetic signal failure, then turn mechanical-hydraulic Standby control.
Present invention also offers a kind of full authority control system tolerant system of fanjet, the fanjet full powers
Limit control system tolerant system includes：
Receiving unit, the receiving unit is used for the transmission signal for receiving each sensor；
Memory cell, the memory cell is used for the normal data for storing each sensor；
Comparison unit, the comparison unit is used for the transmission signal for obtaining the receiving unit and the memory cell institute
The normal data of storage is compared, so as to judge whether the signal that sensor is transmitted breaks down；
Failure sorts out judging unit, and the failure sorts out judging unit for the event for the signal for being transmitted the sensor
Barrier is sorted out, and judges the failure mode；
Solution memory cell, the solution memory cell is used for the solution for storing each failure mode；
Call unit, the call unit calls the solution memory cell to be stored when the failure occurs
Solution；
Execution unit, the execution unit is used to perform the solution that the call unit is transferred.
The present invention the full authority control system fault-tolerance approach of fanjet when control system occur rotating speed, temperature, pressure,
During the sensor signal failures such as geometric angle, metering valve aperture and throttle lever, it can be sent out by using the turbofan of the present invention
The full authority control system fault-tolerance approach of motivation realizes reconfiguring and optimizing not only for Control system architecture and control system plan
The functional reliability of control system is substantially increased, it is maintainable, and the performance of engine can be played to greatest extent.
Brief description of the drawings
Fig. 1 is the flow signal of the full authority control system fault-tolerance approach of fanjet according to a first embodiment of the present invention
Figure.
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme 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 represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention protection
The limitation of scope.
Single fanjet aircraft has redundancy engine control system, and redundancy engine control system includes being mutually redundant
Full powers ration the power supply control control system and machinery hydraulic pressure control system, wherein, full powers control control system of rationing the power supply is master control system, machine
Tool hydraulic control system is used as back-up system.
Fig. 1 is the flow signal of the full authority control system fault-tolerance approach of fanjet according to a first embodiment of the present invention
Figure.
The full authority control system fault-tolerance approach of fanjet as shown in Figure 1 comprises the following steps：
Step 1：The signal that each sensor that full powers are rationed the power supply on control control system reception fanjet is transmitted；
Step 2：Judge whether the signal that sensor is transmitted breaks down, if it is not, then terminating；If so, then carrying out next
Step；
Step 3：The species of the failure occurred in judgment step 2；
Step 4：Transfer the fault-tolerant solution party when the failure of the species stored during full powers ration the power supply control control system occurs
Method, and perform the fault-tolerant solution.
In the present embodiment, the species of the failure occurred in step 3 includes：
Sensor extreme value failure, engine parameter failure, engine parameter loop fault, sensor slope failure, numeral
Electronic controller calculates the small value failure of failure, dutycycle electromagnetism failure, engine circuit, the big value failure of engine circuit etc..
In the present embodiment, the signal that sensor is transmitted includes：
nLChannel signal, nHChannel signal, T6Adjust channel signal, α1Adjust channel signal, α2Adjust channel signal, πTIt is logical
Road signal, spout regulation channel signal, Lm signals, L1 signals, Li signals, Lo signals, PLA Measurement channels signal, T1Measurement is logical
Road signal, T25Measurement channel signal, P31Measurement channel signal, P6Measurement channel signal, PHMeasurement channel signal, Ln Measurement channels
Signal, LA1 Measurement channels signal, LA2 Measurement channels signal, digital electronic controller signal, dutycycle electromagnetic signal.
Collect in the present embodiment, the fault-tolerant solution in step 4 includes：
When nL channel signal failures, and failure mode is sensor extreme value failure, engine parameter failure, engine parameter
One in loop fault, sensor slope failure, then use and abandon nLPassage is controlled, and normal channel drop state is used；α1Favourable turn
The method of tool hydraulic control；
Work as nHChannel signal failure, and failure mode is sensor extreme value failure, engine parameter failure, engine parameter
One in loop fault, sensor slope failure, then use and abandon nHEvent is sentenced in passage control；α2Go to hydraulic pressure Standby control；
When T6 regulation channel signal failures, and failure mode is sensor extreme value failure, engine parameter failure, engine
One in parameter loop fault, sensor slope failure, then use and abandon T6Passage is controlled, the event of normal channel channel signal
Barrier, and failure mode is sensor extreme value failure, engine parameter failure, engine parameter loop fault, sensor slope event
One in barrier, then using α1Favourable turn tool hydraulic control；
Work as α2Channel signal failure is adjusted, and failure mode is that biography turns physical training condition control；
Work as α1One in regulation sensor extreme value failure or sensor slope failure, then using α2Favourable turn tool hydraulic control；If
Failure mode is sentenced therefore moment α to pass engine parameter loop fault2Whether control law is n2r25Control law, if so,
Then α2Switch to byControl law is controlled；If it is not, then going to α2Standby control；
Work as πTChannel signal failure, and failure mode is the small value failure of engine circuit, then judges fanjet state,
If fanjet is in Afterburning condition spout closed-loop control, by spout feedforward area amplification；If fanjet is in non-
During Afterburning condition, closed-loop control spout, and forbid reinforcing；If fanjet is in middle following state, π is removedTPassage
The small value failure of engine circuit, and cancel π after the failure is removedTTo spout in the small value trouble shooting of engine circuit of passage
When, feedforward area amplification, and allow engine to enter reinforcing；Work as πTChannel signal failure, and failure mode is engine circuit
Big value failure, then judge fanjet state, if fanjet is in Afterburning condition spout closed-loop control, spout still presses πT
Closed loop and the feedforward high selected control system of area；If fanjet is in non-Afterburning condition, spout closed-loop control, and forbid adding
Power；Work as πTMeasured value is less than πTDuring planned value+k, it is allowed to which fanjet is reinforced；
When spout regulation channel signal failure, and failure is sensor extreme value failure or sensor slope failure, then judges
Fanjet state, is pressed if fanjet is in middle and middle following stateOpen loop folding and unfolding control is carried out to spout
System, spout is received to minimum mechanical stop position or put to maximum machine stop position；It is prohibited from entering reinforcing；If fanjet
Turn mechanical-hydraulic Standby control during in Afterburning condition；If failure is engine parameter loop fault, tool hydraulic control of making a connection；
When Lm signal faults, and fault type is sensor extreme value failure, engine parameter failure, engine parameter loop
One kind in failure, sensor slope failure, then turn hydraulic machinery control；
When L1 signal faults, and fault type is sensor extreme value failure, engine parameter loop fault, sensor slope
One kind in failure, then judge fanjet state, and reinforcing locking logic is carried out in Afterburning condition；In non-Afterburning condition
When, it is prohibited from entering Afterburning condition；
When Li signal faults, and fault type is sensor extreme value failure, engine parameter loop fault, sensor slope
One kind in failure, then judge fanjet state, and reinforcing locking logic is carried out in Afterburning condition；In non-Afterburning condition
When, it is prohibited from entering Afterburning condition；
When Lo signal faults, and fault type is sensor extreme value failure, engine parameter loop fault, sensor slope
One kind in failure, then judge fanjet state, and reinforcing locking logic is carried out in Afterburning condition；In non-Afterburning condition
When, it is prohibited from entering Afterburning condition；
When PLA Measurement channel signal faults, and fault type is sensor extreme value failure or sensor slope failure, then turns
Back-up hydro-mechanical is controlled；
Work as T1Measurement channel signal fault, and fault type be sensor extreme value failure, engine parameter loop fault or
One kind in sensor slope failure, then turn back-up hydro-mechanical control；
Work as T25Measurement channel signal fault, and fault type be sensor extreme value failure, engine parameter loop fault or
One kind in sensor slope failure, then by α 2 be transformed into byControl；
Work as P31Measurement channel signal fault, and fault type be sensor extreme value failure, engine parameter loop fault or
One kind in sensor slope failure, then turn mechanical-hydraulic Standby control；
Work as P6Measurement channel signal fault, and fault type is sensor extreme value failure, engine parameter loop fault, biography
One kind in sensor slope failure, judges fanjet state, if in Afterburning condition, spout amplifies according to spout feedforward area
To control, exit after Afterburning condition and forbid being again introduced into Afterburning condition；If fanjet state is in middle and middle following shape
State, then be prohibited from entering Afterburning condition；
Work as PHMeasurement channel signal fault, and fault type is sensor extreme value failure or sensor slope failure, then sentences
Whether the altitude signal of disconnected aircraft is normal, if then rebuilding P by altitude signalH；
When Ln Measurement channel signal faults, and fault type is sensor extreme value failure or sensor slope failure, then turns
Mechanical-hydraulic Standby control；
When LA1 Measurement channel signal faults, and fault type is sensor extreme value failure, sensor slope failure, then α1
Still pressNormal control；
When LA2 Measurement channel signal faults, and fault type is sensor extreme value failure, sensor slope failure, then α2
Still rationed the power supply by full powers and control control system control；
When digital electronic controller signal fault, and result of calculation is not inconsistent with expected results, then it is assumed that digital and electronic is controlled
Cpu fault in device, turns mechanical-hydraulic Standby control；
When dutycycle electromagnetic signal failure, then turn mechanical-hydraulic Standby control.
Present invention also offers a kind of full authority control system tolerant system of fanjet, the limit control of fanjet full powers
System Fault Tolerance system processed includes：
Receiving unit, the receiving unit is used for the transmission signal for receiving each sensor；
Memory cell, the memory cell is used for the normal data for storing each sensor；
Comparison unit, the comparison unit is used for the transmission signal for obtaining the receiving unit and the memory cell institute
The normal data of storage is compared, so as to judge whether the signal that sensor is transmitted breaks down；
Failure sorts out judging unit, and the failure sorts out judging unit for the event for the signal for being transmitted the sensor
Barrier is sorted out, and judges the failure mode；
Solution memory cell, the solution memory cell is used for the solution for storing each failure mode；
Call unit, the call unit calls the solution memory cell to be stored when the failure occurs
Solution；
Execution unit, the execution unit is used to perform the solution that the call unit is transferred.
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
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (2)
1. a kind of full authority control system fault-tolerance approach of fanjet, for single fanjet aircraft, single turbofan hair
Motivation aircraft has a redundancy engine control system, and the full powers that the redundancy engine control system includes being mutually redundant are rationed the power supply control
Control system and machinery hydraulic pressure control system, wherein, the full powers ration the power supply control control system for master control system, the mechanical liquid
Pressure control system is used as back-up system, it is characterised in that the full authority control system fault-tolerance approach of fanjet is included such as
Lower step：
Step 1：The signal that each sensor that full powers are rationed the power supply on control control system reception fanjet is transmitted, the signal
Including nLChannel signal, nHChannel signal, T6Adjust channel signal, α1Adjust channel signal, α2Adjust channel signal, πTPassage is believed
Number, spout regulation channel signal, Lm signals, L1 signals, Li signals, Lo signals, PLA Measurement channels signal, T1Measurement channel is believed
Number, T25Measurement channel signal, P31Measurement channel signal, P6Measurement channel signal, PHMeasurement channel signal, Ln Measurement channels letter
Number, LA1 Measurement channels signal, LA2 Measurement channels signal, digital electronic controller signal, dutycycle electromagnetic signal；
Step 2：Judge whether the signal that sensor is transmitted breaks down, if it is not, then terminating；If so, then carrying out next step；
Step 3：Judge the species of failure occurred in the step 2, failure mode includes sensor extreme value failure, engine and joined
Number failure, engine parameter loop fault, sensor slope failure, digital electronic controller calculate failure, the event of dutycycle electromagnetism
The small value failure of barrier, engine circuit, the big value failure of engine circuit；
Step 4：Transfer the fault-tolerant solution party when the failure of the species stored during the full powers ration the power supply control control system occurs
Method, i.e.,
When nL channel signal failures, and failure mode is sensor extreme value failure, engine parameter failure, engine parameter loop
One in failure, sensor slope failure, then use and abandon nLPassage is controlled, and normal channel drop state is used；α1Favourable turn tool liquid
The method of voltage-controlled system；
Work as nHChannel signal failure, and failure mode is sensor extreme value failure, engine parameter failure, engine parameter loop
One in failure, sensor slope failure, then use and abandon nHEvent is sentenced in passage control；α2Go to hydraulic pressure Standby control；
When T6 regulation channel signal failures, and failure mode is sensor extreme value failure, engine parameter failure, engine parameter
One in loop fault, sensor slope failure, then use and abandon T6Passage is controlled, normal channel channel signal failure, and
Failure mode is in sensor extreme value failure, engine parameter failure, engine parameter loop fault, sensor slope failure
One, then using α1Favourable turn tool hydraulic control；
Work as α2Channel signal failure is adjusted, and failure mode is that biography turns physical training condition control；
Work as α1One in regulation sensor extreme value failure or sensor slope failure, then using α2Favourable turn tool hydraulic control；If failure
Species is sentenced therefore moment α to pass engine parameter loop fault2Whether control law is n2r25Control law, if so, then α2
Switch to byControl law is controlled；If it is not, then going to α2Standby control；
Work as πTChannel signal failure, and failure mode is the small value failure of engine circuit, then fanjet state is judged, if whirlpool
When fan engine is in Afterburning condition spout closed-loop control, by spout feedforward area amplification；If fanjet is in non-reinforcing
During state, closed-loop control spout, and forbid reinforcing；If fanjet is in middle following state, π is removedTPassage starts
The small value failure in machine loop, and cancel π after the failure is removedTWhen in the small value trouble shooting of engine circuit of passage to spout,
Feedover area amplification, and allows engine to enter reinforcing；Work as πTChannel signal failure, and failure mode is the big value of engine circuit
Failure, then judge fanjet state, if fanjet is in Afterburning condition spout closed-loop control, spout still presses πTClosed loop
With the feedforward high selected control system of area；If fanjet is in non-Afterburning condition, spout closed-loop control, and forbid reinforcing；When
πTMeasured value is less than πTDuring planned value+k, it is allowed to which fanjet is reinforced；
When spout regulation channel signal failure, and failure is sensor extreme value failure or sensor slope failure, then judges turbofan
Engine condition, is pressed if fanjet is in middle and middle following stateOpen loop folding and unfolding control is carried out to spout, will
Spout is received to minimum mechanical stop position or put to maximum machine stop position；It is prohibited from entering reinforcing；If fanjet is in
Turn mechanical-hydraulic Standby control during Afterburning condition；If failure is engine parameter loop fault, tool hydraulic control of making a connection；
When Lm signal faults, and fault type is sensor extreme value failure, engine parameter failure, the event of engine parameter loop
One kind in barrier, sensor slope failure, then turn hydraulic machinery control；
When L1 signal faults, and fault type is sensor extreme value failure, engine parameter loop fault, sensor slope failure
In one kind, then judge fanjet state, in Afterburning condition carry out reinforcing locking logic；In non-Afterburning condition, prohibit
Only enter Afterburning condition；
When Li signal faults, and fault type is sensor extreme value failure, engine parameter loop fault, sensor slope failure
In one kind, then judge fanjet state, in Afterburning condition carry out reinforcing locking logic；In non-Afterburning condition, prohibit
Only enter Afterburning condition；
When Lo signal faults, and fault type is sensor extreme value failure, engine parameter loop fault, sensor slope failure
In one kind, then judge fanjet state, in Afterburning condition carry out reinforcing locking logic；In non-Afterburning condition, prohibit
Only enter Afterburning condition；
When PLA Measurement channel signal faults, and fault type is sensor extreme value failure or sensor slope failure, then turns hydraulic pressure
Mechanical backup is controlled；
Work as T1Measurement channel signal fault, and fault type is sensor extreme value failure, engine parameter loop fault or sensor
One kind in slope failure, then turn back-up hydro-mechanical control；
Work as T25Measurement channel signal fault, and fault type is sensor extreme value failure, engine parameter loop fault or sensing
One kind in device slope failure, then by α 2 be transformed into byControl；
Work as P31Measurement channel signal fault, and fault type is sensor extreme value failure, engine parameter loop fault or sensing
One kind in device slope failure, then turn mechanical-hydraulic Standby control；
Work as P6Measurement channel signal fault, and fault type is sensor extreme value failure, engine parameter loop fault, sensor
One kind in slope failure, judges fanjet state, if in Afterburning condition, spout is controlled according to spout feedforward area amplification
System, exits after Afterburning condition and forbids being again introduced into Afterburning condition；If fanjet state is in middle and middle following state,
It is prohibited from entering Afterburning condition；
Work as PHMeasurement channel signal fault, and fault type is sensor extreme value failure or sensor slope failure, then judges aircraft
Altitude signal it is whether normal, if then rebuilding P by altitude signalH；
When Ln Measurement channel signal faults, and fault type is sensor extreme value failure or sensor slope failure, then tool of making a connection
Hydraulic pressure Standby control；
When LA1 Measurement channel signal faults, and fault type is sensor extreme value failure, sensor slope failure, then α1Still pressNormal control；
When LA2 Measurement channel signal faults, and fault type is sensor extreme value failure, sensor slope failure, then α2Still by complete
The automatically controlled control system control of authority；
When digital electronic controller signal fault, and result of calculation is not inconsistent with expected results, then it is assumed that in digital electronic controller
Cpu fault, turn mechanical-hydraulic Standby control；
When dutycycle electromagnetic signal failure, then turn mechanical-hydraulic Standby control.
2. a kind of full authority control system tolerant system of fanjet, it is characterised in that the fanjet full powers limit control
System Fault Tolerance system processed includes：
Receiving unit, the receiving unit is used for the transmission signal for receiving each sensor；
Memory cell, the memory cell is used for the normal data for storing each sensor；
Comparison unit, the transmission signal that the comparison unit is used to obtain the receiving unit is stored with the memory cell
Normal data be compared, so as to judge whether the signal that sensor is transmitted breaks down；
Failure sorts out judging unit, and the failure that the failure sorts out signal of the judging unit for the sensor to be transmitted is returned
Class, and judge the failure mode；
Solution memory cell, the solution memory cell is used for the solution for storing each failure mode；
Call unit, the call unit is when the failure occurs, the solution for calling the solution memory cell to be stored
Certainly method；
Execution unit, the execution unit is used to perform the solution that the call unit is transferred.
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| CN110320799B (en) * | 2019-06-13 | 2021-05-07 | 大连理工大学 | Undisturbed cut-in fault-tolerant control method for faults of aircraft engine actuator |
| WO2021072617A1 (en) * | 2019-10-15 | 2021-04-22 | 北京理工大学 | Fault tolerance control method of electromechanical composite transmission system of aircraft |
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