CN115726889B - Intelligent flow control device of aviation fuel pump control system - Google Patents
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Abstract
The invention provides an intelligent flow control device of an aviation fuel pump control system, which comprises: the system comprises a flow control area dividing module, an executing mechanism frequency response testing module, an executing mechanism frequency response estimating module, a PI controller parameter automatic calculating module, a PI control parameter soft switching module and a flow PI controller module; through the parameter switching of the flow area division and the PI controller, the precise control of the fuel flow of the aero-engine in the full flow area is realized; by automatic flow area division, scientificity of flow control area division is improved, and debugging efficiency of the device is improved; the PI controller parameters are calculated based on the frequency response estimation of the actuating mechanism, so that the full-flow-domain constant-gain constant-phase margin control of the aero-engine can be realized, and the control margin of the aero-engine can be guaranteed more conveniently.
Description
Technical Field
The invention belongs to the field of fuel control of aeroengines, and particularly relates to an intelligent flow control device of an aviation fuel pump control system.
Background
In recent years, the technology of multi-electric/hybrid aero-engine is internationally under the hot trend of research, and people have conducted researches on key components of the multi-electric/hybrid aero-engine to different degrees. An aircraft engine fuel pump control system using an electric fuel pump as a core architecture is one of key components of multi-electric/hybrid engine development, and is also regarded as a great innovation of the aircraft engine fuel control system in the industry.
High-precision control of engine fuel flow under a pump control architecture is one of key core technologies for pump control system research. Under the pump control architecture, the fuel pump is directly driven by the motor, and the fuel flow of the engine is regulated through the rotating speed of the motor. In a pump control system, the efficiency of a fuel pump is always in a nonlinear relation with the rotating speed, and the rotating speed control of a motor also presents certain nonlinearity as an actuating mechanism of a flow controller; when the motor driver, the motor and the fuel pump are taken as an actuating mechanism of the flow controller as a whole, a control model is difficult to build by an analytic method, and model parameters also change along with working conditions.
In the whole envelope range of the aeroengine, the fuel flow is regulated from 1% rated flow to 100% rated flow, the required flow regulation is wide in range and high in regulation precision, and the design of a flow control strategy and a flow control method is extremely difficult. In the existing flow controllers, a PI controller with lower dependence on a controlled object model is mostly adopted, and parameters of the PI controller are adjusted to be a tedious time-consuming and low-efficiency task, but in a wider flow adjustment range, a single PI control parameter meets flow control requirements in a certain flow range, and still is difficult to meet high-precision control requirements in a full flow range.
Disclosure of Invention
The invention provides an intelligent flow control device of an aviation fuel pump control system, which meets the high-precision control requirement of flow in the full flow range of the operation of an aviation engine.
The invention provides an intelligent flow control device of an aviation fuel pump control system, which comprises: the system comprises a flow control area dividing module, an executing mechanism frequency response testing module, an executing mechanism frequency response estimating module, a PI controller parameter automatic calculating module, a PI control parameter soft switching module and a flow PI controller module;
the flow control area dividing module is used for dividing the flow control area of the full fuel flow area of the aviation fuel pump control system and sending the flow control area to the executing mechanism frequency response testing module;
The actuating mechanism frequency response testing module is used for applying excitation corresponding to each flow control area to the actuating mechanism in each flow control area, acquiring actual flow response corresponding to each flow control area, and outputting the actual flow response corresponding to each flow control area to the actuating mechanism frequency response estimating module;
The executing mechanism frequency response estimation module is used for acquiring the executing mechanism frequency response corresponding to each flow control area according to the actual flow response corresponding to each flow control area, and outputting the amplitude frequency characteristic and the phase frequency characteristic in the executing mechanism frequency response corresponding to each flow control area to the PI controller parameter automatic calculation module;
the PI controller parameter automatic calculation module is used for acquiring PI controller parameters corresponding to each flow control area according to the amplitude-frequency characteristic and the phase-frequency characteristic of the executing mechanism corresponding to each flow control area and outputting the PI controller parameters to the PI control parameter soft switching module;
And the PI control parameter soft switching module is used for acquiring the current actual fuel flow output by the flow PI controller module when the aviation fuel pump control system actually works, determining the current flow control area where the current actual fuel flow is positioned, and carrying out parameter soft switching on the flow PI controller module according to the PI controller parameters corresponding to the current flow control area and the flow control area at the last moment.
Optionally, the flow control area dividing module is configured to determine an initial flow instruction and an end flow instruction according to a full fuel flow domain of the aviation fuel pump control system, send the initial flow instruction and the end flow instruction to the flow PI controller module, and obtain a dividing result of the flow control area according to a change of a first derivative of an actual fuel flow output by the flow PI controller module in an automatic adjustment process of the initial flow instruction and the end flow instruction.
Optionally, the intelligent flow control device of the aviation fuel pump control system further comprises: a status indication module;
The state indication module is used for indicating that the aviation fuel pump control system is in a parameter identification state or an actual working state;
the flow control area dividing module is specifically configured to divide flow control areas for all fuel flow areas of the aviation fuel pump control system when the state indicating module indicates that the aviation fuel pump control system is in a parameter identification state.
Optionally, the actuator frequency response test module is specifically configured to,
Applying excitation corresponding to each flow control area to an executing mechanism in each flow control area, issuing flow instructions corresponding to each flow control area to a flow PI controller module, acquiring actual flow responses corresponding to each flow control area, and outputting the actual flow responses corresponding to each flow control area, steady-state output of the flow PI controller module and reference signals to an executing mechanism frequency response estimation module;
the flow instructions corresponding to the flow control areas are determined according to the upper boundary and the lower boundary of the flow control areas;
The corresponding excitation of each flow control area is u (t) =A.sin (wt), the reference signals are sin (wt) and cos (wt), A is the excitation signal amplitude, w is the bandwidth angular frequency of the aviation fuel pump control system, t is time, and A is determined according to the upper boundary and the lower boundary of the flow control area.
Optionally, the executing mechanism frequency response estimation module is specifically configured to obtain a frequency response corresponding to each flow control area according to an actual flow response corresponding to each flow control area, a steady-state output of the flow PI controller module, and a reference signal, and output an amplitude-frequency characteristic and a phase-frequency characteristic in the frequency response corresponding to each flow control area to the PI controller parameter automatic calculation module.
Optionally, the actuator frequency response estimation module is specifically configured to obtain, according to a steady-state output of the flow PI controller module corresponding to each flow control area and a reference signal, a first real part Re1 (T) and a first imaginary part Im1 (T) of a frequency response corresponding to each flow control area; obtaining a second real part Re2 (T) and a second imaginary part Im2 (T) of the frequency response corresponding to each flow control area according to the actual flow response and the reference signal corresponding to each flow control area; obtaining frequency response corresponding to each flow control region according to the first real part Re1 (T), the first imaginary part Im1 (T), the second real part Re2 (T) and the second imaginary part Im2 (T) by adopting the formula (Re 2 (T) +j. Im2 (T))/(Re 1 (T) +j. Im1 (T));
wherein t=2pi/w.
Optionally, the PI controller parameter automatic calculation module is specifically configured to,
Acquiring an actuator gain K (acu) according to amplitude-frequency characteristics and phase-frequency characteristics of the actuators corresponding to each flow control area, and determining that the amplitude of the frequency response of the flow PI controller is 1/K (acu) according to the actuator gain K (acu);
acquiring a phase lag angle of the actuating mechanism according to amplitude-frequency characteristics and phase-frequency characteristics of the actuating mechanism corresponding to each flow control area, and determining the phase lag angle of the frequency response of the PI controller according to the phase lag angle of the actuating mechanism and a preset phase margin of the control device;
And acquiring PI controller parameters corresponding to each flow control area according to the amplitude-frequency characteristic and the phase-frequency characteristic of the flow PI controller.
Optionally, the PI control parameter soft handoff module is specifically configured to,
When the aviation fuel pump control system actually works, determining whether a control parameter switching mark exists, if not, acquiring the current actual fuel flow output by the flow PI controller module, determining a current flow control area where the current actual fuel flow is located, judging whether the current flow control area is consistent with the flow control area at the last moment, and if not, generating the control parameter switching mark;
When the control parameter switching mark exists, the PI controller parameters corresponding to the flow control area at the previous moment are gradually adjusted to the PI controller parameters corresponding to the current flow control area according to the preset adjustment times, and the control parameter switching mark is canceled after the adjustment is completed.
The invention provides an intelligent flow control device of an aviation fuel pump control system, which realizes accurate control of the fuel flow of an aeroengine in a full flow area through parameter switching of a flow area division and a PI controller; by automatic flow area division, scientificity of flow control area division is improved, and debugging efficiency of the device is improved; the PI controller parameters are calculated based on the frequency response estimation of the actuating mechanism, so that the full-flow-domain constant-gain constant-phase margin control of the aero-engine can be realized, and the control margin of the aero-engine can be guaranteed more conveniently.
Detailed Description
The intelligent flow control device of the aviation fuel pump control system provided by the invention is specifically explained below.
The invention provides an intelligent flow control device of an aviation fuel pump control system, which comprises: the system comprises a flow control area dividing module, a state indicating module, an executing mechanism frequency response testing module, an executing mechanism frequency response estimating module, a PI controller parameter automatic calculating module, a PI control parameter soft switching module and a flow PI controller module;
Wherein, actuating mechanism can be electronic fuel pump.
The flow control area dividing module is used for dividing the area of the full fuel flow area of the aviation fuel pump control system and sending the divided area to the executing mechanism frequency response testing module;
The state indicating module is used for indicating that the aviation fuel pump control system is in a parameter identification state or an actual working state.
The actuating mechanism frequency response testing module is used for applying excitation corresponding to each flow control area to the actuating mechanism in each flow control area, acquiring actual flow response corresponding to each flow control area, and outputting the actual flow response corresponding to each flow control area to the actuating mechanism frequency response estimating module;
The executing mechanism frequency response estimation module is used for acquiring the executing mechanism frequency response corresponding to each flow control area according to the actual flow response corresponding to each flow control area, and outputting the amplitude frequency characteristic and the phase frequency characteristic in the executing mechanism frequency response corresponding to each flow control area to the PI controller parameter automatic calculation module;
The PI controller parameter automatic calculation module is used for acquiring PI controller parameters corresponding to each flow control area according to the amplitude-frequency characteristic and the phase-frequency characteristic of the executing mechanism corresponding to each flow control area and outputting the PI controller parameters to the PI control parameter soft switching module;
And the PI control parameter soft switching module is used for acquiring the current actual fuel flow output by the flow PI controller module when the aviation fuel pump control system actually works, determining the current flow control area where the current actual fuel flow is positioned, and carrying out parameter soft switching on the flow PI controller module according to the PI controller parameters corresponding to the current flow control area and the flow control area at the last moment.
And the flow PI controller module is used for controlling the aviation fuel pump control system to track the instruction flow and outputting the actual fuel flow.
Optionally, the closed loop gain of the control device is 1, the bandwidth angular frequency of the aviation fuel pump control system is preset to w, and the initial parameter of the flow PI controller is preset to KP 0,KI0. Where KP 0 is a proportional term coefficient and KI 0 is an integral term coefficient.
Optionally, the flow control region dividing module comprises a flow acceleration control sub-module, a flow first derivative calculating sub-module and a flow region dividing sub-module.
The flow acceleration control sub-module is used for issuing a flow area division starting flow instruction and a rated flow instruction to the flow PI controller module.
The flow acceleration control sub-module is further used for determining the start and the end of flow area division.
The flow acceleration control sub-module determines the start of flow area division by the following steps: differentiating the deviation e start＝ystart- y of the actual flow y output by the flow PI controller module from the start command flow y start, recording the deviation of the sampling time as e start (k), recording the deviation of the sampling time as e start (k+1), and obtaining the differentiation result as e start′＝(estart(k+1)-estart (k))/Ts, wherein ts=0.001 is the sampling period, if |e start' | <0.03, the start condition is satisfied, setting the acceleration start flag F acc_start =1, clearing the acceleration end flag, and enabling F acc_stop =0. Where k is the sampling instant.
Similarly, the deviation e stop＝ystop- y between the end command flow y stop and the actual flow y output by the flow PI controller module is differentiated, the deviation of the sampling time is e stop (k), the deviation of the sampling time is e stop (k+1), the differentiation result is e stop′＝(estart(k+1)-estart (k))/Ts, wherein ts=0.001 is the sampling period, if |e stop' | <0.02, the end condition is satisfied, the acceleration end flag F acc_stop =1 is set, the acceleration start flag is cleared, and F acc_start =0.
And the flow first derivative calculation sub-module is used for calculating the flow derivative in real time through y '(k+1) = (y (k+1) -y (k))/Ts when F acc_start =1 and F acc_stop =0, wherein y (k+1) is the flow of the current sampling period, y (k) is the flow of the last sampling period, and y (k+1) and y' (k+1) are stored.
And the flow area dividing sub-module is used for determining an inflection point of y ' (k+1) according to the stored y (k+1) and y ' (k+1) through differential operation y ' (k+1) = (y ' (k+1) -y ' (k))/(Ts), and if y ' (k+1) | >2.3, y (k+1) corresponds to a flow dividing point, and the number n is increased by 1 when z n＝y(k+1)/ystop x 100% and y ' (k+1) | >2.3 conditions occur each time. When F acc_stop =1, let B count =n, correspond to the number of boundary flow points, let Zone count =n-1, correspond to the number of flow control areas. The corresponding flow area is [ z 1,z2,z3,…,zn ].
N is a positive integer greater than 1.
Optionally, the state indication module is used for indicating that the aviation fuel pump control system is in a parameter identification state or an actual working state (also referred to as a flow control state).
In the parameter identification state, the PI controller parameters of all the flow control areas are calculated through an execution mechanism frequency response testing module, an execution mechanism frequency response estimating module and a PI controller parameter automatic calculating module.
It can be understood that the calculation of the PI controller parameters of each flow control area is performed sequentially, and when all the calculation is completed, the parameter identification state is exited, and the actual working state can be entered.
Optionally, the executing mechanism frequency response testing module comprises a testing start generating sub-module, a testing excitation applying sub-module, a testing data recording sub-module and a testing end generating sub-module.
The test start generation sub-module is used for generating a test start mark and clearing a test end mark when the test start condition is met.
The test initiation generating sub-module is further configured to record a steady-state output u (t 0) and a steady-state flow value y (t 0) of the flow PI controller module at a time t 0 when the test initiation condition is satisfied.
In the test initiation generation submodule, the method for determining the satisfaction of the initiation conditions comprises the following steps: in a given flow control region, such as [ z 1,z2],z1 ] is the lower boundary and z 2 is the upper boundary. And (z 1+z2)/2 is taken as a flow instruction and is issued to a flow PI controller module, the deviation e rec(k+1)＝y(k+1)-(z1+z2)/2 between the flow y (k+1) and the flow y (z 1+z2)/2 is monitored, and if the I e rec (k+1) I <0.001, the starting condition is met.
The test excitation applying sub-module is used for superposing u (t 0) with u (t) =A×sin (wt) serving as excitation when the test start mark is effective and the test end mark is ineffective as input of the executing mechanism. Wherein A is the amplitude of the excitation signal, w is the bandwidth angular frequency of the aviation fuel pump control system, and t is time. A is determined to be 0.03 x (z 1+z2)/2.
And the test data recording sub-module is used for recording four groups of signals, i.e. u (T) -u (T 0),y(t)-y(t0), sin (wt) and cos (wt), in a period of T=2pi/w after the flow y (T) is stable when the test start mark is valid and the test end mark is invalid. The determination of y (t) stability is similar to the starting conditions.
In the test initiation generation sub-module, when an excitation signal is generated, two groups of signals sin (wt) and cos (wt) are also generated, recorded and output as reference signals of a follow-up actuator frequency response estimation module.
And the test end generation sub-module is used for generating a test end mark and clearing a test start mark after the test data record is ended.
Optionally, the actuator frequency response estimation module includes: the system comprises a first real part computing sub-module, a first imaginary part computing sub-module, a second real part computing sub-module, a second imaginary part computing sub-module and an executing mechanism frequency response real part and imaginary part computing sub-module.
The first real part calculation sub-module is configured to determine a first real part Re1 (T) according to data u (T) -u (T 0), sin (wt) recorded by the actuator frequency response test module, by integrating and averaging [ u (T) -u (T 0) ] sin (wt) signals in a T period.
The first imaginary part calculation sub-module is configured to determine a first imaginary part Im1 (T) by integrating and averaging [ u (T) -u (T 0) ] -cos (wt) signals in a T period according to the data u (T) -u (T 0) and cos (wt) recorded by the actuator frequency response test module.
The second real part calculation sub-module is configured to determine a second real part Re2 (T) by integrating and averaging [ y (T) -y (T 0) ]sin (wt) signals in a T period according to the data y (T) -y (T 0), sin (wt) recorded by the actuator frequency response test module.
The second imaginary part calculation sub-module is configured to determine a second imaginary part Im2 (T) by integrating and averaging [ y (T) -y (T 0) ] -cos (wt) signals in a T period according to the data y (T) -y (T 0) and cos (wt) recorded by the actuator frequency response test module.
The real part and imaginary part calculation sub-module of the actuator frequency response is used for calculating the real part Re (acu) of the actuator frequency response according to complex division (Re 2 (T) +j.Im2 (T))/(Re 1 (T) +j.Im1 (T)), and the imaginary part is the imaginary part j.Im (acu) of the actuator frequency response. Where j is a complex imaginary sign and acu represents an actuator.
Optionally, the PI controller parameter automatic calculation module includes: a PI controller frequency response amplitude computation sub-module, a PI controller frequency response phase computation sub-module, a PI controller parameter computation sub-module; wherein,
The amplitude-frequency characteristic calculation sub-module of the PI controller is used for determining that the amplitude of the frequency response of the PI controller is 1/K (acu) according to the closed loop gain of the control device is 1 and the actuator gain K (acu) calculated by the real part and the imaginary part of the frequency response of the actuator;
The PI controller frequency response phase sub-module is used for calculating phase lag < 2 > calculated according to a preset phase margin < 1 > of the control device and a real part and an imaginary part of the frequency response of the actuating mechanism, and determining phase lag < 3 > of the PI controller frequency response through < 3=180- < 1- < 2 >;
And the PI controller parameter calculation sub-module is used for determining parameters KP and KI of the PI controller. The specific method comprises the following steps:
Firstly, according to the model C(s) =kp+ki/(s) of the PI controller, substituting s=j×w into the expression of C(s), obtaining the real part and the imaginary part of C (j×w);
the KP and KI parameters are solved according to the two equations combination of K (acu) =sqrt (KP 2+(KI/(j*w))2), and tan (< 3) = (KI/w)/KP. And storing the parameters into a parameter cache, wherein the parameters correspond to the designated flow control area, the KP parameter corresponding to the designated area is marked as KP-Z spec, and the KI parameter is marked as KI-Z spec.
Optionally, the PI control parameter soft handover module includes a handover flag generation sub-module, a handover parameter acquisition sub-module, a soft handover control sub-module, and a handover flag cancellation sub-module;
The switching mark generation sub-module is used for generating a control parameter switching mark when the current flow and the last flow are positioned in different flow control areas (namely, the flow is in a cross-area mode);
The switching mark generation sub-module is further used for recording PI controller parameters KP old,KIold before the flow crosses the flow area;
The switching parameter acquisition sub-module is used for inquiring the PI controller parameter KP current,KIcurrent corresponding to the current area according to the flow area where the current flow is located;
And the soft handover control sub-module is used for realizing the soft handover of the PI controller parameters from KP old,KIold to KP current,KIcurrent. The method comprises the following steps:
First, KP current-KPold and KI current-KIold are calculated;
then, Δkp= (KP current-KPold)/100,ΔKI＝(KIcurrent-KIold)/100 is calculated;
Finally, at each control period kp+=Δkp, ki+=Δki.
And the switching mark cancellation sub-module is used for canceling the switching mark after the soft switching is completed, and switching is not restarted during the effective period of the switching mark, so that the actual flow is prevented from fluctuating at the boundary to be switched back and forth.
The judging method for the completion of the soft handoff comprises the following steps: the KP parameter and the KI parameter in the PI controller are equal to the PI parameter corresponding to the target flow control area.
The intelligent control system is mainly used for intelligent control of the fuel pump control system of the aeroengine. The intelligent aircraft engine fuel pump control system based on the four-core architecture has the main functions of improving steady state and dynamic control performance of the aircraft engine fuel pump control system under all working conditions, reducing differences among individual products, improving product robustness and consistency and improving debugging production efficiency. The policies and methods presented herein may be implemented by an embedded control system implementation.
Claims (8)
1. An intelligent flow control device of an aviation fuel pump control system, which is characterized by comprising: the system comprises a flow control area dividing module, an executing mechanism frequency response testing module, an executing mechanism frequency response estimating module, a PI controller parameter automatic calculating module, a PI control parameter soft switching module and a flow PI controller module;
the flow control area dividing module is used for dividing the flow control area of the full fuel flow area of the aviation fuel pump control system and sending the flow control area to the executing mechanism frequency response testing module;
The actuating mechanism frequency response testing module is used for applying excitation corresponding to each flow control area to the actuating mechanism in each flow control area, acquiring actual flow response corresponding to each flow control area, and outputting the actual flow response corresponding to each flow control area to the actuating mechanism frequency response estimating module;
The executing mechanism frequency response estimation module is used for acquiring the executing mechanism frequency response corresponding to each flow control area according to the actual flow response corresponding to each flow control area, and outputting the amplitude frequency characteristic and the phase frequency characteristic in the executing mechanism frequency response corresponding to each flow control area to the PI controller parameter automatic calculation module;
the PI controller parameter automatic calculation module is used for acquiring PI controller parameters corresponding to each flow control area according to the amplitude-frequency characteristic and the phase-frequency characteristic of the executing mechanism corresponding to each flow control area and outputting the PI controller parameters to the PI control parameter soft switching module;
And the PI control parameter soft switching module is used for acquiring the current actual fuel flow output by the flow PI controller module when the aviation fuel pump control system actually works, determining the current flow control area where the current actual fuel flow is positioned, and carrying out parameter soft switching on the flow PI controller module according to the PI controller parameters corresponding to the current flow control area and the flow control area at the last moment.
2. The control device according to claim 1, wherein the flow control area dividing module is configured to determine a start flow instruction and an end flow instruction according to a full fuel flow domain of the aviation fuel pump control system, send the start flow instruction and the end flow instruction to the flow PI controller module, and obtain a dividing result of the flow control area according to a change of a first derivative of an actual fuel flow output by the flow PI controller module in an automatic adjustment process of the start flow instruction and the end flow instruction.
3. The control device according to claim 1, characterized by further comprising: a status indication module;
The state indication module is used for indicating that the aviation fuel pump control system is in a parameter identification state or an actual working state;
the flow control area dividing module is specifically configured to divide flow control areas for all fuel flow areas of the aviation fuel pump control system when the state indicating module indicates that the aviation fuel pump control system is in a parameter identification state.
4. The control device of claim 1, wherein the actuator frequency response test module is configured to,
Applying excitation corresponding to each flow control area to an executing mechanism in each flow control area, issuing flow instructions corresponding to each flow control area to a flow PI controller module, acquiring actual flow responses corresponding to each flow control area, and outputting the actual flow responses corresponding to each flow control area, steady-state output of the flow PI controller module and reference signals to an executing mechanism frequency response estimation module;
the flow instructions corresponding to the flow control areas are determined according to the upper boundary and the lower boundary of the flow control areas;
The corresponding excitation of each flow control area is u (t) =A.sin (wt), the reference signals are sin (wt) and cos (wt), A is the excitation signal amplitude, w is the bandwidth angular frequency of the aviation fuel pump control system, t is time, and A is determined according to the upper boundary and the lower boundary of the flow control area.
5. The control device according to claim 4, wherein the actuator frequency response estimation module is specifically configured to obtain a frequency response corresponding to each flow control area according to an actual flow response corresponding to each flow control area, a steady-state output of the flow PI controller module, and a reference signal, and output an amplitude-frequency characteristic and a phase-frequency characteristic in the frequency response corresponding to each flow control area to the PI controller parameter automatic calculation module.
6. The control device according to claim 5, wherein the actuator frequency response estimation module is specifically configured to obtain a first real part Re1 (T) and a first imaginary part Im1 (T) of the frequency response corresponding to each flow control region according to the steady-state output of the flow PI controller module corresponding to each flow control region and the reference signal; obtaining a second real part Re2 (T) and a second imaginary part Im2 (T) of the frequency response corresponding to each flow control area according to the actual flow response and the reference signal corresponding to each flow control area; obtaining frequency response corresponding to each flow control region according to the first real part Re1 (T), the first imaginary part Im1 (T), the second real part Re2 (T) and the second imaginary part Im2 (T) by adopting the formula (Re 2 (T) +j. Im2 (T))/(Re 1 (T) +j. Im1 (T));
wherein t=2pi/w.
7. The control device according to claim 1, wherein the PI controller parameter auto-calculation module is configured to,
Acquiring an actuator gain K (acu) according to amplitude-frequency characteristics and phase-frequency characteristics of the actuators corresponding to each flow control area, and determining that the amplitude of the frequency response of the flow PI controller is 1/K (acu) according to the actuator gain K (acu);
acquiring a phase lag angle of the actuating mechanism according to amplitude-frequency characteristics and phase-frequency characteristics of the actuating mechanism corresponding to each flow control area, and determining the phase lag angle of the frequency response of the PI controller according to the phase lag angle of the actuating mechanism and a preset phase margin of the control device;
And acquiring PI controller parameters corresponding to each flow control area according to the amplitude-frequency characteristic and the phase-frequency characteristic of the flow PI controller.
8. The control device according to claim 1, wherein the PI control parameter soft handover module is configured to,
When the aviation fuel pump control system actually works, determining whether a control parameter switching mark exists, if not, acquiring the current actual fuel flow output by the flow PI controller module, determining a current flow control area where the current actual fuel flow is located, judging whether the current flow control area is consistent with the flow control area at the last moment, and if not, generating the control parameter switching mark;
When the control parameter switching mark exists, the PI controller parameters corresponding to the flow control area at the previous moment are gradually adjusted to the PI controller parameters corresponding to the current flow control area according to the preset adjustment times, and the control parameter switching mark is canceled after the adjustment is completed.
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| CN202759406U (en) * | 2012-06-28 | 2013-02-27 | 控制技术有限公司 | Optimal switching system for frequency converter-driven multi-motor control system |
| US20180187608A1 (en) * | 2017-01-04 | 2018-07-05 | General Electric Company | Method for loop gain sizing of gas turbines |
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| US10934944B2 (en) * | 2018-11-07 | 2021-03-02 | Dalian University Of Technology | Method for optimization of transient control law of aero-engine |
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| CN105715384A (en) * | 2014-12-05 | 2016-06-29 | 中国航空工业集团公司航空动力控制***研究所 | Parameter adjusting method of incremental PI controller used for improving accelerating performance of aircraft engine |
| CN105446373A (en) * | 2015-12-24 | 2016-03-30 | 武汉理工大学 | Intelligent control method for optimizing oil unloading of marine cargo oil pump based on fuzzy immune PID |
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