CN114662247A - Design method of aero-engine servo control system - Google Patents
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Abstract
The application belongs to the field of aero-engine design, and relates to a design method of an aero-engine servo control system, which realizes the optimization design of the servo control system by establishing a strong coupling relation between each boundary condition and a design calculation result and establishing an optimization function according to the coupling relation, realizes the rapid convergence of the optimization function by establishing a limiting condition, and realizes the cross coupling design among accessories of the servo control system due to the use of all the commonly used boundary conditions; because the boundary condition meeting the design requirement is used as an initial value for carrying out optimization calculation, the designed servo control system necessarily meets the design requirement, the confidence coefficient of the calculation result is high, useless design burden and cost cannot be increased, and the size, the weight and the design difficulty of the servo control system are reduced on the premise of not influencing functions and performances.
Description
Technical Field
The application belongs to the field of aero-engine design, and particularly relates to a design method of an aero-engine servo control system.
Background
In the future, the sections of servo guide vanes of an aero-engine control system are numerous, the number of actuators is generally over 30, and if the requirements for the capacity of the servo guide vanes are still high according to the design idea of the traditional servo control system, the useless design burden and cost are increased, and the design of the external structure of the engine is also more complicated.
The existing engine servo control system has the following problems:
1) the boundary condition extraction is fuzzy, and the confidence coefficient of a theoretical design calculation result is poor;
2) the design method is simple, and mainly depends on increasing the size of the accessory or improving the accessory capacity, so that useless design burden and cost are increased by 'over-design';
3) the cross coupling design among accessories in the servo control system is deficient.
Therefore, how to reduce the size, weight and design difficulty of the servo control system is a problem to be solved on the premise of ensuring the function and performance stability of the servo control system.
Disclosure of Invention
The application aims to provide a design method of an aero-engine servo control system, and the problems that in the prior art, the servo control system is simple in design, heavy in weight, complex in design and poor in confidence coefficient are solved.
The technical scheme of the application is as follows: a design method of an aircraft engine servo control system comprises the following steps: setting theoretical calculation formulas of the driving force of the servo system, the flow of the servo system and the movement time of the actuator according to each boundary condition in the design process of the servo control system, and establishing the coupling relation between each boundary condition and the three-dimensional size of the actuator, the theoretical calculation driving force of the actuator, the theoretical calculation flow of the servo system and the theoretical calculation movement time of the actuator; establishing an optimization function by using the coupling relation, and establishing a limiting condition of the optimization function; determining an optimization target, giving initial values of each boundary condition, obtaining a difference value between an optimization result and the optimization target, establishing a residual function, judging whether the difference value meets the requirement of residual precision, and if not, correcting the initial values of the boundary conditions through the difference value to perform repeated optimization; if yes, executing the next step; and obtaining the final results of the actuator three-dimensional size, the actuator driving force theoretical calculation, the servo system flow theoretical calculation and the actuator movement time theoretical calculation to complete optimization.
Preferably, the optimization function is:
the method comprises the following steps that A1 is the diameter of a rodless cavity of an actuator, A2 is the diameter of a piston rod of the actuator, A3 is the stroke of the actuator, A4 is the installed quantity of the actuator, A5 is the time required by the full-stroke movement of the actuator, 6 is the pressure relationship behind a servo pump, A7 is the designed flow of a servo valve, A8 is the required load force of a geometric guide vane, B1 is the three-dimensional size of the actuator, B2 is the theoretical calculated driving force of the actuator, B3 is the theoretical calculated flow of a servo system, and B4 is the theoretical calculated movement time of the actuator.
Preferably, the limiting conditions of the priority function are: b1 is less than or equal to the limitation of the overall size; b2 is more than or equal to A8; b3 matches the a6 signature; b4 is less than or equal to A5.
Preferably, the servo system driving force theoretical calculation formula is as follows:
Ftake in max＝PAfter the pump×AWith rods-POil return×ARodless；
FExtension max＝PAfter the pump×ARodless-POil return×AWith rods
Wherein, FTake in maxThe theoretical maximum driving force is the retracting state of the single-support actuator; fExtension maxThe theoretical maximum driving force is the maximum driving force of the single-support actuator in the extending state; pAfter the pumpIs the servo pump back pressure; p isOil returnIs the return oil pressure; a. theWith rodsThe area of the rod cavity of the actuator; a. theRodlessThe area of the rodless cavity of the actuator.
Preferably, the theoretical calculation formula of the flow of the servo system is as follows:
Qgeneral assembly＝QActuation 1+QActuating 2+...
Wherein QActuated byThe flow rate of a single actuator; qGeneral assemblyIs the servo system flow; a. theRodlessThe area of a rodless cavity of the actuator; l is a radical of an alcoholActuated byIs the stroke of the actuator; t isActuated byTime is required for the full-stroke movement of the actuator.
Preferably, the theoretical calculation formula of the movement time of the actuator is as follows:
wherein ρ is the density of the working medium: η is the flow efficiency: t is tExtend outFor actuator extension time: t is tRetractionFor actuator retraction time: l isActuated byFor the stroke of the actuator: qServo valveCorresponding to the flow of the servo valve for a single actuator: pr is the return pressure of the control device: ps is the control device inlet pressure: c is the area ratio of two cavities of the actuator: fLoad(s)Demand load force for geometric vanes; a. theWith rodsThe actuator has a rod cavity area.
According to the design method of the servo control system of the aircraft engine, the servo control system is optimized and designed by establishing the strong coupling relation between each boundary condition and the design calculation result and establishing the optimization function according to the coupling relation, the optimization function is rapidly converged by establishing the limiting conditions, and the cross coupling design among accessories of the servo control system is realized due to the use of all the commonly used boundary conditions; because the boundary condition meeting the design requirement is used as an initial value for carrying out optimization calculation, the designed servo control system necessarily meets the design requirement, the confidence coefficient of the calculation result is high, useless design burden and cost cannot be increased, and the size, the weight and the design difficulty of the servo control system are reduced on the premise of not influencing functions and performances.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be understood that the drawings described below are merely exemplary of some embodiments of the application.
FIG. 1 is a schematic overall flow diagram of the present application;
FIG. 2 is a diagram illustrating a relationship between boundary conditions and design calculations according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
A design method of an aircraft engine servo control system is shown in figure 1 and comprises the following steps:
step S100, setting theoretical calculation formulas of driving force of a servo system, flow of the servo system and movement time of an actuator according to boundary conditions in the design process of the servo control system, and establishing coupling relations between the boundary conditions and three-dimensional sizes of the actuator, the theoretical calculation driving force of the actuator, the theoretical calculation flow of the servo system and the theoretical calculation movement time of the actuator;
the design process of the servo control system basically comprises eight boundary conditions, namely the diameter of a rodless cavity of an actuator, the diameter of a piston rod of the actuator, the stroke of the actuator, the installation number of the actuators, the motion required time of the full stroke of the actuator, the pressure relationship behind a servo pump, the design flow of a servo valve and the required load force of a geometric guide vane. The boundary conditions and the design calculation results have strong coupling relation. After the boundary conditions are confirmed, four design calculation results such as actuator three-dimensional size, actuator theoretical calculation driving force, servo system theoretical calculation flow, actuator theoretical calculation movement time and the like can be obtained. Wherein the three-dimensional size of the actuator does not need to be calculated by a formula.
Preferably, the servo system driving force theoretical calculation formula is as follows:
Ftake in max＝PAfter the pump×AWith rods-POil return×ARodless；
FExtension max＝PAfter the pump×ARodless-POil return×AWith rods
Wherein, FTake in maxThe theoretical maximum driving force is the retracting state of the single-support actuator; fExtension maxThe theoretical maximum driving force is the maximum driving force of the single-support actuator in the extending state; pAfter the pumpIs the servo pump back pressure; pOil returnIs the return oil pressure; a. theWith rodsThe area of the rod cavity of the actuator; a. theRodlessThe area of the rodless cavity of the actuator.
Preferably, the servo system flow theoretical calculation formula is as follows:
Qgeneral assembly＝QActuation 1+QActuating 2+...
Wherein Q isActuated byThe flow rate of a single actuator; qGeneral assemblyIs the servo system flow; a. theRodlessThe area of a rodless cavity of the actuator; l isActuated byIs the stroke of the actuator; t is a unit ofActuated byTime is required for the full-stroke movement of the actuator.
Preferably, the theoretical calculation formula of the motion time of the actuator is as follows:
wherein ρ is the density of the working medium: η is the flow efficiency: t is tExtend outFor actuator extension time: t is tRetracting and advancingFor actuator retraction time: l is a radical of an alcoholActuated byFor the actuator stroke: qServo valveCorresponding servo valve flow for a single actuator: pr is the return pressure of the control device: ps is a control deviceMouth pressure: c is the area ratio of two cavities of the actuator: fLoad(s)Demand load force for geometric vanes; a. theWith rodsThe actuator has a rod cavity area.
Through a servo system flow theoretical calculation formula, a servo system flow theoretical calculation formula and an actuator movement time theoretical calculation formula, a strong coupling relation between each boundary condition and the three-dimensional size of the actuator, the actuator theoretical calculation driving force, the servo system theoretical calculation flow and the actuator theoretical calculation movement time is established, and a foundation is provided for optimizing each parameter subsequently.
As shown in fig. 2, step S200, establishing an optimization function by using the coupling relationship, and establishing a limiting condition of the optimization function; the optimization function is:
the method comprises the following steps that A1 is the diameter of a rodless cavity of an actuator, A2 is the diameter of a piston rod of the actuator, A3 is the stroke of the actuator, A4 is the installed quantity of the actuator, A5 is the time required by the full-stroke movement of the actuator, 6 is the pressure relationship behind a servo pump, A7 is the designed flow of a servo valve, A8 is the required load force of a geometric guide vane, B1 is the three-dimensional size of the actuator, B2 is the theoretical calculated driving force of the actuator, B3 is the theoretical calculated flow of a servo system, and B4 is the theoretical calculated movement time of the actuator.
Preferably, the constraints of the priority function are: b1 is less than or equal to the limit of the overall size; b2 is more than or equal to A8; b3 matches the a6 signature; b4 is less than or equal to A5.
By setting the optimization function and establishing the limiting conditions, the optimization function can be rapidly converged during optimization.
Step S300, determining an optimization target, giving initial values of each boundary condition, acquiring a difference value between an optimization result and the optimization target, establishing a residual function, judging whether the difference value meets the requirement of residual accuracy, and if not, correcting the initial values of the boundary conditions through the difference value to perform repeated optimization; if yes, executing the next step;
the optimization targets can be set according to requirements, for example, the minimum overall dimension can be set as a target value, the minimum actuator weight and the optimal actuator performance can also be set, different optimization targets are established according to requirements, the different optimization targets respectively correspond to different residual error functions, different optimization results can be obtained, and the residual error precision requirement is set manually.
And S400, acquiring the final results of the actuator three-dimensional size, the actuator driving force theoretical calculation, the servo system flow theoretical calculation and the actuator movement time theoretical calculation, and finishing optimization.
When the aero-engine servo control system is designed, the servo control system is optimized and designed by establishing a strong coupling relation between each boundary condition and a design calculation result and establishing an optimization function according to the coupling relation, the optimization function is quickly converged by establishing a limiting condition, and cross coupling design among accessories of the servo control system is realized due to the use of all commonly used boundary conditions; because the boundary condition meeting the design requirement is used as an initial value for carrying out optimization calculation, the designed servo control system necessarily meets the design requirement, the confidence coefficient of the calculation result is high, useless design burden and cost cannot be increased, and the size, the weight and the design difficulty of the servo control system are reduced on the premise of not influencing functions and performances.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A design method of an aircraft engine servo control system is characterized by comprising the following steps:
setting theoretical calculation formulas of the driving force of the servo system, the flow of the servo system and the movement time of the actuator according to each boundary condition in the design process of the servo control system, and establishing the coupling relation between each boundary condition and the three-dimensional size of the actuator, the theoretical calculation driving force of the actuator, the theoretical calculation flow of the servo system and the theoretical calculation movement time of the actuator;
establishing an optimization function by using the coupling relation, and establishing a limiting condition of the optimization function;
determining an optimization target, giving initial values of each boundary condition, obtaining a difference value between an optimization result and the optimization target, establishing a residual function, judging whether the difference value meets the requirement of residual precision, and if not, correcting the initial values of the boundary conditions through the difference value to perform repeated optimization; if yes, executing the next step;
and obtaining the final results of the actuator three-dimensional size, the actuator driving force theoretical calculation, the servo system flow theoretical calculation and the actuator movement time theoretical calculation to complete optimization.
2. The aircraft engine servo control system design method of claim 1, wherein said optimization function is:
the method comprises the following steps that A1 is the diameter of a rodless cavity of an actuator, A2 is the diameter of a piston rod of the actuator, A3 is the stroke of the actuator, A4 is the installed quantity of the actuator, A5 is the time required by the full-stroke movement of the actuator, 6 is the pressure relationship behind a servo pump, A7 is the designed flow of a servo valve, A8 is the required load force of a geometric guide vane, B1 is the three-dimensional size of the actuator, B2 is the theoretical calculated driving force of the actuator, B3 is the theoretical calculated flow of a servo system, and B4 is the theoretical calculated movement time of the actuator.
3. A method of designing an aircraft engine servo control system according to claim 2, wherein the constraints of the priority function are: b1 is less than or equal to the limitation of the overall size; b2 is more than or equal to A8; b3 matches the a6 characteristics; b4 is less than or equal to A5.
4. The method of designing an aircraft engine servo control system according to claim 1, wherein the servo system driving force theoretical calculation formula is:
Ftake in max＝PAfter the pump×AWith rods-POil return×ARodless；
FExtension max＝PAfter the pump×ARodless-POil return×AWith rods
Wherein, FTake in maxThe theoretical maximum driving force is the retracting state of the single-support actuator; fExtension maxThe theoretical maximum driving force is the maximum driving force of the single-support actuator in the extending state; pAfter the pumpIs the servo pump back pressure; pOil returnIs the return oil pressure; a. theWith rodsThe area of the rod cavity of the actuator; a. theRodlessThe area of the rodless cavity of the actuator.
5. The method of designing an aircraft engine servo control system of claim 1, wherein the servo system flow theoretical calculation formula is:
Qgeneral assembly＝QActuation 1+QActuating 2+...
Wherein QActuated byThe flow rate of a single actuator; qGeneral assemblyIs the servo system flow; a. theRodlessThe area of a rodless cavity of the actuator; l is a radical of an alcoholActuated byIs the stroke of the actuator; t isActuated byTime is required for the full-stroke movement of the actuator.
6. The method of designing an aircraft engine servo control system according to claim 1, wherein the theoretical equation for the calculation of actuator movement time is:
wherein ρ is the working medium density: η is the flow efficiency: t is tExtend outFor actuator extension time: t is tRetracting and advancingFor the actuator retraction time: l isActuated byFor the stroke of the actuator: qServo valveCorresponding to the flow of the servo valve for a single actuator: pr is the return pressure of the control device: ps is the control device inlet pressure: c is the area ratio of the two cavities of the actuator: fLoad(s)Demand load force for geometric vanes; a. theWith rodsThe actuator has a rod cavity area.
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| CN108916144A (en) * | 2018-07-04 | 2018-11-30 | 北京航天发射技术研究所 | A kind of dynamic hydraulic combined oil supply system |
| US20200362770A1 (en) * | 2018-11-07 | 2020-11-19 | Dalian University Of Technology | Design method for optimization of transient control law of aero-engine |
| CN114265368A (en) * | 2021-12-07 | 2022-04-01 | 中国航发控制系统研究所 | Adaptive estimation method for combination state of servo control system of aircraft engine |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108916144A (en) * | 2018-07-04 | 2018-11-30 | 北京航天发射技术研究所 | A kind of dynamic hydraulic combined oil supply system |
| US20200362770A1 (en) * | 2018-11-07 | 2020-11-19 | Dalian University Of Technology | Design method for optimization of transient control law of aero-engine |
| CN114265368A (en) * | 2021-12-07 | 2022-04-01 | 中国航发控制系统研究所 | Adaptive estimation method for combination state of servo control system of aircraft engine |
Non-Patent Citations (2)
| Title |
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| 严杰;: "一种变量泵斜盘电液伺服控制系统研究", 中国制造业信息化, no. 13, 1 July 2011 (2011-07-01) * |
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