CN106960084A - A kind of aero-engine limitation protector method for designing with risk assessment of transfiniting - Google Patents
A kind of aero-engine limitation protector method for designing with risk assessment of transfiniting Download PDFInfo
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Abstract
Protector method for designing is limited the invention discloses a kind of aero-engine with the risk evaluation mechanism that transfinites.When being in a state of emergency for aircraft; there is the problem of excessive control conservative is totally unfavorable to flight safety in existing controller; risk evaluation module is introduced engine limitation protector by the present invention; by carrying out active judgement to engine health parameter-beyond-limit risk; decide whether activation limitation protector, weaken unnecessary conservative limitation with this so that engine makes flexible to emergency; to ensure flight safety, engine performance is given full play to while improving robustness.Wherein, the assessment parameter threshold in risk evaluation module is realized using genetic algorithm, and optimal solution is searched out in the reasonable scope, so as to set rationally reliable threshold value.The present invention establishes certain h type engine h Control System Imitation platform, and simulating, verifying is carried out to this method, the result shows that this method largely reduces control conservative, improves engine response speed, and this method is simple in construction, small is changed to original controller architecture, effect of optimization is notable, with very strong practical meaning in engineering.
Description
Technical field
The present invention relates to aero-engine control and risk assessment field of transfiniting, and in particular to can be to engine work to one kind
Make parameter to carry out evaluation of risk, improve limitation protector conservative, the method for lifting engine performance.
Background technology
Conventional engine controller is mainly comprising two parts at present：Power management linear controller and limitation are protected
Device.Power management linear controller is only responsible for regulation fuel flow to produce satisfactory power output, regardless of whether super
Go out safety limit range (surge margin, chamber pressure etc.).For example, using rotation speed of the fan as controlled volume, although linear controller
Fuel delivery can be adjusted so that rotating speed meets instruction and required well, but remaining parameter such as turbine temperature, surge margin all can
Significantly exceed safe edge dividing value.So need to be introduced into limitation protector to ensure that security parameter does not transfinite in whole flight course,
The work of engine reliable, safety.
For modern aeroengine, limitation parameter of protector can be divided into two parts：Component physical attribute limiting value, calm the anger
Machine surge margin limiting value.Limited component physical attribute comprising HP＆LP Rotor rotating speed maximum as shown in figure 1, limit, burning
Room inlet pressure maximum limitation, rotor rate of acceleration maximum limitation during acceleration, Wf/Ps3 minimum limitations.
The control logic that current engine limitation protector is used selects height to select logic to be low, and the logical construction can effectively exist
Switch between power controller and relay protective scheme controller there is provided smooth oil mass signal, while key parameter can be ensured not
The trouble free service transfinited with engine.But there is very big conservative, reduce engine response speed in this control logic,
Main cause has at following 2 points：
(1) when it is determined that each limits Protection parameters, what is taken into full account is that engine works under worst environment
Situation, now limits protector and still ensures that security parameter does not transfinite, protects corresponding component, therefore the control law of limitation protector
Inherently there is very big conservative.
(2) low to select height to select control logic essence be opened loop control, so even without there are the urgent feelings reached the limit values
Condition, limits protector and is also possible to active, and then limit low choosing height and select the output fuel oil of structure to increase, reduce and start
Machine response quickly of system.
When engine is in nominal situation, conservative controller design can't have a negative impact to engine, but
It is that when for example aircraft rudder surface is impaired, aircraft can only complete maneuver by motor power when aircraft is in emergency, this
When controller conservative can hinder engine carry out quick response so that aircraft is difficult successfully to land.So needing research to change
The method of kind engine controller conservative.
The research method that many conservatives and engine response on controller improve, document are had pointed out at present【1】
(Richter,Hanz,and Litt,Jonathan S.A Novel Controller for Gas Turbine Engine
With Aggressive Limit Management, AIAA-2011-5857,2011) propose a kind of application synovial membrane limitation guarantor
The aero-engine control unit scheme of device is protected, to avoid the controller overprotection unnecessary to engine and intervention, ensures and flies
Row safety, but sliding mode control theory is relative complex, realizes that the program needs to redesign controller, consumption according to sliding mode control theory
Take a large amount of manpower and materials.Document【2】(J Litt, D Frederick, TH Guo, The Case for Intelligent
Propulsion Control for Fast Engine Response, AIAA, 2006) propose by increasing power management control
Device gain processed improves response speed, but its research finds that hair can be slowed down on the contrary by increasing power management control gain simply
Motivation response speed, and this method changes larger to controller so that research process is complex, and fails to each running parameter
The risk situation that transfinites rationally assess.
The content of the invention
A kind of aero-engine limitation protector method for designing with risk assessment of transfiniting of the present invention, in traditional limitation
The risk evaluation module that transfinites is introduced on the basis of protector, the module can be quantified to the security parameter risk situation under current working
Analysis, rationally assessment, judge whether corresponding limitation protector needs to be activated, so as to reduce according to the risk assessment value that transfinites
The conservative of whole controller, engine response speed is accelerated, further excavated engine Potential performance, also to start
Machine can more flexibly tackle various extreme emergency situations, ensure flight safety.
To achieve the above object, the technical solution adopted by the present invention step is as follows：
Step 1：Based on MATLAB/Simulink platform building Simulation of Aeroengine Control System platforms, build first
Engine modified linearized model, resettles power management linear controller and traditional, unmodified limitation protector module, complete
Connect whether debugging control systemic-function is perfect after into each module, whether its structure meets emulation needs.
Step 2：It is determined that the methods of risk assessment that transfinites, i.e., according to the work at present value and boundary threshold of certain parameter, calculate
One group of value-at-risk that transfinites of the parameter, if the value-at-risk that transfinites is beyond threshold value, corresponding limitation protector activation participates in height
Control logic is selected, if without departing from risk threshold value, then it is assumed that be currently in safe operating mode, corresponding limitation protector need not work
Make, thus specifically, quantitatively analysis transfinite risk, it is ensured that engine tackles rapidly extreme situation, while maintaining flight safety,
Also enhance the bold and resolute property of engine.
Step 3：On this basis, with reference to engine actual working state to the risk that transfinites in the risk evaluation module that transfinites
Threshold value is optimized using genetic algorithm, is calculated the risk dynamic threshold that transfinites and is conducive to more precisely rationally control.
Step 4：Method in above-mentioned steps sets up the risk evaluation module that transfinites, and is added to the limit in emulation platform
In protector module processed, to realize the Control System Imitation platform after improving.
Step 5：Simulating, verifying is carried out for certain h type engine h, and by simulation result with not using the risk assessment algorithm that transfinites
Control simulation result be compared, made and sentenced with the correctness to transfinite methods of risk assessment and the risk function of use
It is disconnected.
Beneficial effect
(1) risk evaluation module that transfinites is introduced controller by the present invention to carry out active judgement to the operating mode of security parameter,
The unnecessary participation height selected control system if security parameter is had no chance and reaches restricted boundary.It so can largely avoid limit
The Redundant Control effect of protector processed, and then the fuel value that Guarantee control system is finally selected can meet wanting for flight safety
Ask, a higher value can be maintained at again so that engine response is very fast, lifts its transition state performance.
(2) present invention is significant in practice in engineering, when aircraft is in certain dangerous working condition, with the wind that transfinites
The limitation protector that danger is assessed can overcome existing control system control, and conservative is too strong, response speed slow shortcoming excessively, to subtract
Low control conservative, it is ensured that engine response can quickly follow pilot command, to ensure flight safety, and then reduce part to damage
Consumption, extension engine life.
Brief description of the drawings
Fig. 1 is the basic controller emulation platform schematic diagram before improving.
Fig. 2 is the risk assessment calculation procedure that transfinites.
Fig. 3 is using traditional control system and the simulation result comparison diagram with the risk assessment control system that transfinites.
Embodiment
By taking the control system of civilian point of row's fanjet of certain type as an example, the specific implementation process of the present invention is described in detail.
Step 1：Control System Imitation platform is built according to engine control system structure, is set up and sent out using exponent weight
Motivation modified linearized model, and controller module is set up, control parameter can be obtained according to practical tuning method or using something lost
The optimized algorithms such as propagation algorithm optimize calculating and obtained.After emulation platform is completed, carry out transition state for certain h type engine h and imitate
True analysis checking.Emulation platform connection diagram is as shown in Figure 1.
Step 2：The methods of risk assessment that transfinites that the type control system is used is as follows：
Assuming that the currency of certain security parameter is T1, its restricted boundary value is Tm, and the value of last moment is T0.Define herein
Amplitude assesses parameter Aeval,
Convergence degree assesses parameter Seval,
Aeval characterizes current parameter value ratio shared in excursion is entirely allowed, and Seval characterizes the parameter
The time length required for restricted boundary is reached with current rate of change.If the Aeval of certain security parameter exceedes the amplitude of setting
Threshold value A max, and Seval is less than the convergence degree threshold value Smin of setting, then it is assumed that the parameter is in dangerous working condition, is closer to border
Value, and its change is more acutely, will exceed boundary value in future, it limits protector and can be activated, and participates in height selected control system
Logic is selected, and otherwise the limitation protector is stopped, and is not involved in control system calculating.
In the method, the amplitude thresholds Amax of limitation protector is static constant, and convergence degree threshold value Smin is one
Dimensional vector, it is dynamic change in simulation process, can obtain the moment according to current emulation moment linear interpolation corresponding
Convergence degree threshold value, compared with static threshold, dynamic Smin can further reduce system conservative.
It can be seen from the above method, the key of this method is to select suitable Amax, Smin vector so that system can
Reduce conservative, again will not be because undue weakening limits the effect of protector and causes some security parameters of engine to enter dangerous
Operating mode.The methods of risk assessment calculation procedure that transfinites is as shown in Figure 2.
Step 3：According to the method for step 2, the risk evaluation module that transfinites is set up for each limitation protector, and first will be each
Amplitude thresholds are set as that 0, convergence degree threshold value is set as 10000.The risk evaluation module that now transfinites almost cuts little ice, will
System output now is contrasted with original system output, and specification module is set up correct if two times result is basically identical.
Step 4：It is using genetic algorithm optimization amplitude thresholds Amax and convergence degree threshold value Smin, sets target function f：
Wherein t represents current time, CVardem[t] represents that the moment controls variable command value, CVarfebWhen [t] represents this
Carve control variable feedback value, αt(Tm- T) it is penalty term, T represents every security parameter, αtFor penalty factor, can dynamic regulation punish
Penalize a numerical value.
Step 5：Genetic algorithm optimization result is substituted into some engine controllers and carries out simulating, verifying, simulation result is as schemed
Shown in 3, the h type engine h control system control parameter is rotation speed of the fan, and its middle short line is scribed ss rotation speed of the fan Nf-dmd, dot-dash
Line is that rotating speed the output line Nf, solid line Nf-Eval produced using traditional control system is using the control with risk assessment of transfiniting
The rotation speed change that system processed is produced, it can be seen that can effectively reduce control using the control system with risk assessment of transfiniting and make
With conservative, using the margin of safety of part, significantly shorten the engine response time.
Claims (3)
1. limit protector method for designing the invention discloses a kind of aero-engine with the risk evaluation mechanism that transfinites.For flying
When machine is in a state of emergency, there is the problem of excessive control conservative is totally unfavorable to flight safety, this hair in existing controller
The bright risk evaluation module that will transfinite introduces engine limitation protector, by being carried out actively to engine health parameter-beyond-limit risk
Judge, decide whether activation limitation protector, weaken unnecessary conservative limitation with this so that engine is made to emergency
It is flexible, to ensure flight safety, engine performance is given full play to while improving robustness.Claim is as follows：
A kind of aero-engine limitation protector method for designing with risk assessment of transfiniting, it is characterised in that：
In step 2, one group of risk assessment parameter that transfinites of design is quantitatively divided the risk that transfinites of the currently practical operating mode of engine
Analysis, actively judges whether to connect limiter protector, the risk assessment parameter that transfinites includes amplitude and convergence degree, represents current respectively
The distance and velocity of approach of running parameter and restricted boundary, two parameter image characterize all kinds of risks that transfinite so that risk is sentenced
Off line system is succinctly efficient.
2. a kind of aero-engine limitation protector method for designing with risk assessment of transfiniting, it is characterised in that：
In step 3, according to engine actual operating mode, using genetic algorithm dynamic calculation convergence degree threshold value, according to engine
The different working stages such as start, cruise, climbing, control instruction is limited in rationally by continuous Automatic adjusument convergence degree threshold value
In the range of, further reduction control system conservative, lifts the flexible property of engine.
3. a kind of aero-engine limitation protector method for designing with risk assessment of transfiniting, it is characterised in that：
In step 4, compared with traditional control system, increased risk assessment of transfiniting is realized actively judges choosing to limitation protector
The effect selected, it is to avoid the excessive limitation of protector, reduces control action conservative, improves engine response speed, enter
One step better ensures that the flight safety of aircraft in case of emergency while playing engine Potential performance.Module overall structure
Simplify, effect of optimization is notable.
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Cited By (3)
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| CN111456856A (en) * | 2020-04-04 | 2020-07-28 | 西北工业大学 | Robust controller for reducing conservative maximum thrust state of aero-engine |
| CN112523874A (en) * | 2020-12-07 | 2021-03-19 | 南京航空航天大学 | Multivariable limit protection control method for aircraft engine |
| CN115030823A (en) * | 2022-07-06 | 2022-09-09 | 南京航空航天大学 | Turbofan engine acceleration control method and acceleration controller |
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Cited By (4)
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| CN111456856A (en) * | 2020-04-04 | 2020-07-28 | 西北工业大学 | Robust controller for reducing conservative maximum thrust state of aero-engine |
| CN112523874A (en) * | 2020-12-07 | 2021-03-19 | 南京航空航天大学 | Multivariable limit protection control method for aircraft engine |
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