Integral pressure-difference control system and method for an aeroengine

Abstract

The application provides an aero-engine integral type constant differential pressure control system and method. In the system, a controlled object control system controls the controlled object based on an instruction oil pressure increment of a disturbance change, an incremental flow area of a metering valve, and a current incremental flow area of an actuating valve output by a stabilizing controller, and outputs an incremental pressure of the metering valve; the stabilizing controller obtains a new incremental flow area of the actuating valve based on a first adjustment difference between the incremental pressure of the metering valve output and an incremental spring cavity pressure of the actuating valve output by an integral controller; and the integral controller processes a second adjustment difference between the incremental pressure of the metering valve output by the controlled object control system and an instruction oil pressure increment input into the system by using a preset integral control algorithm, and obtains the incremental spring cavity pressure of the actuating valve. The system realizes robust servo tracking without static error.

Description

Technical Field

[0001] This application relates to the design of aircraft engine control systems, and more specifically, to an integral type differential pressure control system and method for aircraft engines. Background Technology

[0002] While variable differential pressure control structures are used in a very small number of fuel regulators in aero-engine fuel servo metering systems, such as the fuel regulator in Rolls-Royce's Spey MK202 turbofan engine, the vast majority of aero-engine companies worldwide use constant differential pressure control mechanisms for fuel flow metering. However, existing constant differential pressure control devices do not possess zero static error servo tracking capabilities; instead, they employ high proportional gain methods to improve their servo tracking performance. As automatic control theory shows, if a closed-loop system has only proportional components and no integral components, then the closed-loop system will always have static errors under all conditions. While using high proportional gain methods can reduce static errors, it reduces system stability and may even lead to instability during rapid engine acceleration and deceleration. Cases of engine failure due to fuel system instability are common. Modern high-performance aero-engines place high stability, high accuracy, and high robustness requirements on their control systems, making it imperative to improve the constant differential pressure servo performance and robustness of aero-engine fuel systems.

[0003] In recent years, with the development of simulation technology, the influence of parameters such as spring stiffness and orifice diameter on the performance of equal differential pressure regulating mechanisms has been explored, and simulation comparisons have been conducted for verification. Simultaneously, by establishing a dynamic model of the equal differential pressure regulating mechanism, the influence of some design parameters on system stability has been analyzed. Through simulation analysis, the influence of the return oil profile structure on system characteristics has been studied in depth. Based on CFD flow field simulation, the influence of hydrodynamic forces on valve core balance has been investigated. In addition, there are studies on the structural design and performance calculation analysis of differential pressure metering devices, as well as the influence of differential pressure valve hysteresis on speed fluctuations. Although these methods, based on classical control theory, generally employ high proportional gain methods to improve servo tracking performance and study high-gain equal differential pressure control devices, these methods cannot solve the design problem of robust servo tracking without steady-state error in equal differential pressure control devices. Summary of the Invention

[0004] The purpose of this application is to provide an integral type differential pressure control system and method for aero-engines, which solves the design problem of differential pressure valve design in the prior art that cannot solve the problem of non-static error robust servo tracking of differential pressure control devices.

[0005] In a first aspect, an integral-type differential pressure control system for an aero-engine is provided, characterized in that the system comprises: a controlled object control system, a stabilization controller, and an integral controller;

[0006] The controlled object control system is used to respond to changes in command oil pressure increment ΔP in response to disturbances. S and the increase in flow area ΔA of the metering valve J And the increment ΔA of the current operating valve flow area output by the stabilizing controller. Z The controlled object is controlled, and the pressure increment ΔP after the metering valve is output. C and nozzle inlet pressure increment ΔP O ;

[0007] The stabilization controller is used to measure the pressure increment ΔP after the metering valve output by the controlled object control system. C The pressure increment ΔP of the actuator valve spring chamber output by the integral controller Z The first adjustment difference is used to obtain the new execution valve flow area increment ΔA. Z So that the pressure increment ΔP after the metering valve output by the control system of the controlled object is... C This is the design value;

[0008] The integral controller is used to apply a preset integral control algorithm to the pressure increment ΔP after the metering valve output by the controlled object control system. C The increment of the command oil pressure ΔP input to the system S The second adjustment difference is processed to obtain the pressure increment ΔP of the actuator valve spring cavity. Z .

[0009] Secondly, an integral-type differential pressure control method for an aero-engine is provided, applied to the system described in the first aspect. This method may include:

[0010] Based on the command oil pressure increment ΔP in response to disturbance changes S and the increase in flow area ΔA of the metering valve J And the increment ΔA of the current operating valve flow area output by the stabilizing controller. Z The controlled object is controlled, and the pressure increment ΔP after the metering valve is output. C and nozzle inlet pressure increment ΔP O ;

[0011] Based on the pressure increment ΔP after the metering valve output by the control system of the controlled object C The pressure increment ΔP of the actuator valve spring chamber output by the integral controller Z The first adjustment difference is used to obtain the new execution valve flow area increment ΔA. Z So that the pressure increment ΔP after the metering valve output by the control system of the controlled object is... C This is the design value;

[0012] Using a preset integral control algorithm, the pressure increment ΔP after the metering valve output by the control system of the controlled object is... C The increment of the command oil pressure ΔP input to the system S The second adjustment difference is processed to obtain the pressure increment ΔP of the actuator valve spring cavity. Z .

[0013] Thirdly, a computer-readable storage medium is provided, wherein a computer program is stored therein, and when executed by a processor, the computer program implements the steps of any of the methods described in the second aspect above.

[0014] The integrated differential pressure control system for aero-engines provided in this application embodiment controls the controlled object based on the increment of command oil pressure and the increment of flow area of ​​the metering valve in response to disturbance changes, as well as the increment of flow area of ​​the current actuating valve output by the stabilizing controller. This controls the system and outputs the increment of pressure after the metering valve and the increment of pressure before the nozzle. The stabilizing controller obtains a new increment of flow area of ​​the actuating valve based on a first adjustment difference between the increment of pressure after the metering valve output by the controlled object control system and the increment of pressure in the actuating valve spring cavity output by the integral controller, ensuring that the increment of pressure after the metering valve output by the controlled object control system is the design value. The integral controller uses a preset integral control algorithm to process a second adjustment difference between the increment of pressure after the metering valve output by the controlled object control system and the increment of command oil pressure input to the system, thereby obtaining the increment of pressure in the actuating valve spring cavity. This system, based on the stabilizing controller and the integral controller, achieves robust, zero-steady-state-error servo tracking. Attached Figure Description

[0015] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments of this application will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 A block diagram of a differential pressure valve control circuit design provided in this application embodiment;

[0017] Figure 2 A schematic diagram of the control process of an integral type differential pressure control system for an aero-engine is provided in an embodiment of this application;

[0018] Figure 3 A schematic diagram of the control process within a controlled object control system, a stabilizer controller, and an integral controller, provided as an embodiment of this application;

[0019] Figure 4 This is a flowchart illustrating an integral differential pressure control method for an aero-engine provided in an embodiment of this application. Detailed Implementation

[0020] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0021] The integral differential pressure control system for aero-engines provided in this application addresses the design problem of differential pressure valves and consists of two parts:

[0022] (1) An integral differential pressure control device is proposed, and a controller with dual control functions of integral control and stabilization control is constructed. The stabilization controller solves the asymptotic stability and disturbance suppression problem of the object, and the integral controller realizes zero steady-state error tracking of the command, which solves the problem that the existing differential pressure control device does not have the ability to track integral zero steady-state error.

[0023] (2) Based on the robust LQR design method of the output feedback regulator, the structural parameters of the integral controller and the stabilizing controller were designed, and the design of differential pressure control device with robust servo tracking capability was realized, providing an engineering-feasible technical approach for high-precision control of fuel metering in aero-engines.

[0024] 1. Structure:

[0025] Figure 1 This is a schematic diagram of an equal pressure differential valve structure provided in an embodiment of this application, as shown below. Figure 1 As shown, P S P is the command oil pressure. C To measure the pressure after the valve, P Z To perform valve pressure regulation, P O P is the pressure before the nozzle. T For return oil pressure; A J To measure the flow area of ​​the valve-type orifice, A Z To determine the flow area of ​​the valve-type orifice, A1 is the throttling nozzle area of ​​the cavity behind the high-pressure oil metering valve, and A2 is the nozzle area. in A is the throttling flow area of ​​the oil inlet of the regulating chamber of the differential pressure control device. out A is the throttling flow area of ​​the oil outlet in the regulating chamber of the differential pressure control device. y A represents the pressure-bearing areas at both ends of the differential pressure control device. zx To measure the pressure-bearing area at both ends of the valve; x y0The initial position of the differential pressure valve is x. y For the displacement of the differential pressure valve, x z To perform the valve movement displacement, x z0 To execute the initial position of the valve, V Z To achieve the desired valve spring cavity volume, V O V is the volume of the cavity before the nozzle. C To measure the volume of the cavity behind the valve.

[0026] It should be noted that the increments of each physical quantity described below refer to the difference (or deviation) between the value of a physical quantity at a later time and the value of the corresponding physical quantity at the previous time.

[0027] The purpose of the integral type differential pressure control system for aero-engines provided in this application is to ensure the pressure P in the cavity after the metering valve. C Servo tracking command oil pressure P S And suppress the metering valve area opening A J Pressure P after the metering valve caused by the change C Changes ensure the pressure difference P across the metering valve. S -P C As this is the design value, the differential pressure control device is a typical servo tracking and disturbance suppression system.

[0028] 1.1 Control Principle

[0029] Based on servo tracking and disturbance suppression functions, the control process of the integral differential pressure control system for aero-engines is as follows: Figure 2 As shown. This system may include a controlled object control system, a stabilized controller, and an integral controller; wherein, the stabilized controller and the integral controller may be referred to as servo controllers.

[0030] Controlled object control system, used to respond to changes in command oil pressure increment ΔP in response to disturbances. S and the increase in flow area ΔA of the metering valve J And the current execution valve flow area increment ΔA output by the stabilizing controller. Z The controlled object is controlled, and the pressure increment ΔP after the metering valve is output. C and nozzle inlet pressure increment ΔP O ;

[0031] A stabilization controller is used to measure the pressure increment ΔP after the metering valve based on the output of the controlled object's control system. C The pressure increment ΔP of the actuator valve spring chamber output by the integral controller Z The first adjustment difference is used to obtain the new execution valve flow area increment ΔA. Z So that the pressure increment ΔP after the metering valve output by the controlled object's control system is... CThis is the design value;

[0032] An integral controller is used to control the pressure increment ΔP after the metering valve output by the controlled object system using a preset integral control algorithm. C The increment of the command oil pressure ΔP from the input system S The second adjustment difference is processed to obtain the pressure increment ΔP of the actuator valve spring cavity. Z .

[0033] The control process of the above system includes two adjustment processes:

[0034] 1)ΔP S and ΔA J The disturbance input is used as the controlled object. At this time, by controlling the output variable ΔP... C The negative feedback stabilizing controller is adjusted to suppress the effects of disturbance inputs;

[0035] 2)ΔP S As the system's reference input. At this point, by adjusting the output variable ΔP... C Adjusting the negative feedback integral controller to make the pressure increment ΔP after the metering valve... C Servo tracking command oil pressure increment ΔP S .

[0036] Furthermore, Figure 3 For the control processes within the controlled object control system, the stabilized controller, and the integral servo feedforward compensator, such as Figure 3 As shown, the integral controller may include an equal pressure differential valve, an integral control gain unit (or "Kc unit"), and an integral flow path; the stabilizing controller may include an actuating valve and a stabilizing control gain unit (or "Kz unit"). The controlled object control system may include a controlled flow path, which is used to execute the above-mentioned processes performed by the controlled object control system.

[0037] (1) Control system of the controlled object

[0038] The controlled flow path in the controlled object control system is also used to input the incremental speed of the actuator valve output. and the incremental speed of the differential pressure valve movement

[0039] Specifically, based on the command oil pressure increment ΔP in response to disturbance changes. S and the increase in flow area ΔA of the metering valve J And the current increase in the flow area of ​​the valve ΔA Z Incremental speed of equal pressure differential valve movement and the increase in the speed of the valve movement The controlled object is controlled, and the pressure increment ΔP after the metering valve is output.C and nozzle inlet pressure increment ΔP O .

[0040] (2) Stabilizer

[0041] The stabilization controller consists of an actuator gate and a stabilization control gain K. Z Composition, through the output ΔP C Feedback adjustments are made to ensure gradual system stability and suppress the effects of disturbances.

[0042] The actuator includes a metering valve for measuring the pressure increment ΔP after the output of the controlled object's control system. C The pressure increment ΔP of the actuator valve spring cavity output by the servo feedforward compensator Z The first adjustment difference yields the valve displacement increment Δx. z and the increase in valve speed Execute valve displacement change Δx z Equal to the change in valve-type orifice opening Δx uz ;

[0043] A stabilization control gain unit is used for stabilization control gain K. Z For the valve displacement increment Δx z The process is performed to obtain the increase in the flow area ΔA of the valve-type orifice. z stabilization control gain K Z Based on the increase in flow area ΔA of different actuator valve types z With different valve type openings x uz The ratio is determined.

[0044] Among them, the stabilization control law is determined by the flow area A of the actuator valve-type orifice. Z With opening x uz Design function A Z =f Z (x uz The decision is made, and its deviation is expressed as... Due to the change in valve displacement Δx z equal to Δx uz The stabilization control gain is obtained as

[0045] (3) Integral controller

[0046] The integral controller consists of an equal pressure differential valve and an integral control gain K. C Composed of an integrator and a flow path, the output ΔP is... C Feedback integral adjustment is performed to ensure progressive tracking performance.

[0047] The differential pressure valve is used to control the increment of the command oil pressure ΔP in the system. SThe pressure increment ΔP after the metering valve output by the controlled object's control system C The second adjustment difference e is processed to obtain the displacement increment Δx of the equal pressure differential valve. y and speed increment

[0048] Integral control gain unit, used for integral control gain K C The displacement increment Δx of the equal pressure differential valve y The process yields the throttling area increment ΔA of the differential pressure valve. C ;

[0049] The integral flow path is used for the proportional increment of the constant pressure differential valve displacement and the increment of the actuator valve speed output from the stabilizing controller. Obtain the pressure increment ΔP in the spring chamber of the actuator valve. Z The proportional increment of the displacement of the differential pressure valve is the integral control gain K. C Displacement increment Δx of the differential pressure valve y The product of.

[0050] Among them, the integral control law is determined by the throttling area A of the equal pressure difference valve. in With opening x uin Design function A in =f in (x uin ), Throttling area A out With opening x uout Design function A out =f out (x uout The decision is made, and the deviations are expressed as follows: and Due to the displacement increment Δx of the differential pressure valve y equal to Δx uin and -Δx uout The integral control gain that determines the integral control law is obtained as follows: Among them, K AY This represents the increase in import area ΔA in The determined control gain coefficient, K AT2 This represents the export area ΔA out The control gain coefficient is determined by the increment, VZ is the volume of the spring cavity of the actuator valve, and B is the bulk modulus of the oil.

[0051] The preset integral control algorithm is expressed as follows:

[0052] Where Δt is the control time, K C For integral control gain, ΔP Z V is the pressure increment of the spring chamber of the actuating valve.Z The volume of the valve spring cavity is determined by B, where B is the bulk modulus of the oil.

[0053] Furthermore, the above control process can be analyzed using the following algorithm:

[0054] 1.2 State-space model of the controlled object

[0055] The pressure-flow dynamic equation for the controlled flow path is:

[0056]

[0057] The formula for calculating the flow coefficient is as follows:

[0058] Among them, C qmax d is the maximum flow coefficient. h Let v be the hydraulic diameter and v be the viscosity, expressed as: Nu is the absolute viscosity, and lamc is the maximum critical flow number.

[0059] Choose A J A Z ,P S , P C ,P O Using these variables as variables, we perform linearization to obtain the linearized equations in increment representation:

[0060]

[0061] in,

[0062] The state-space model of the controlled object is as follows:

[0063]

[0064] y=Cx+Du+Hw (6)

[0065] Where, x=[ΔP C ΔP O ] T , w=[ΔA J ΔP S ],y=[ΔP C ],and

[0066]

[0067] C=[1 0], D=[0 0 0], H=[0 0] (7)

[0068] 1.3 Servo Controller Structure Design

[0069] The command signal ΔP that needs to be tracked S With the suppressed disturbance signal ΔA J All are constant signals, and their first-order differential equations are expressed as:

[0070] Define the tracking error signal as: e = ΔP C -ΔP S (9)

[0071] The system regulation output model is as follows:

[0072] Among them, C C =[1 0],D C =[0 0 0].

[0073] Then you can define variables:

[0074] The servo mechanism design model is as follows:

[0075] in, and

[0076]

[0077] The feedback control law of the servo model is:

[0078] The control input can be expressed as: u=∫μ=-k1·∫e dt-k2·ΔP C +const (15)

[0079] Then we get:

[0080] The servo controller represented by the above formula is coupled with ΔP C Since it cannot achieve the integration function of equal pressure difference, the decoupling problem of the servo controller needs to be considered, which will be discussed in the following chapters.

[0081] 2. Decoupling and Separation Implementation of Servo Controller

[0082] 2.1 Integral Control Characteristics

[0083] (1) Dynamic characteristics of the differential pressure control device

[0084] Let the mass of the differential pressure control device be M. y The coefficient of viscous friction is K. f1 The elastic modulus of the spring is K1, and the initial compressive force of the spring is F. L The kinematic equations of the differential pressure control device are as follows:

[0085]

[0086] Let P S ,P C ,x y , As a variable, its linearized equation is expressed as:

[0087]

[0088] Its steady-state characteristics are:

[0089] Clearly, Δx y The steady-state time reflects the tracking error of the instruction.

[0090] (2) Dynamic characteristics of the regulating cavity of the valve

[0091] The pressure-flow dynamic equation for the regulating chamber of the valve is:

[0092]

[0093] Let A in A out ,P S ,P Z , As a variable, its pressure-flow linearized incremental equation is expressed as:

[0094]

[0095] in

[0096] Let the throttling area A of the differential pressure control device be... in With opening x uin The design function is A in =f in (x uin ), Throttling area A out With opening x uout The design function is A out =f out (x uout The linearized incremental equations are expressed as follows:

[0097]

[0098] Due to Δx uin =-Δx uout =Δx y ,but

[0099]

[0100] In steady state, if both the import and export circulation areas are 0, i.e., A in0 =A out0 =0, then K PY =0,K PT2 =0 (24)

[0101] Then equation (21) must have the following equation:

[0102]

[0103] Clearly, the above formula can achieve the desired result for Δx. y The integral effect.

[0104] Let the integral control gain K C Represented as:

[0105] but

[0106] Due to Δx y This indirectly reflects the tracking error of the pressure command, therefore this relationship inherently incorporates the integral effect of the pressure command tracking error.

[0107] In summary, the state-space model of the integral controller is obtained as follows:

[0108]

[0109]

[0110] in,

[0111] C S =[0 0 1],D S =[0 0] (29)

[0112] 2.2 Characteristics of the Stabilizer

[0113] Let the mass of the actuator gate be M. z The coefficient of viscous friction is K. f2 The elastic modulus of the spring is K2, and the initial compressive force of the spring is F. L2 The dynamic equations for the valve are as follows:

[0114]

[0115] Let PC ,P Z ,x z , As variables, we obtain its linearized incremental equation representation:

[0116]

[0117] Let the throttling area of ​​the actuator valve be A. Z With opening x uz The design function is A Z =f Z (x uz Its linearized incremental equation is expressed as:

[0118] Due to Δx uz =-Δx z ,but

[0119] In the above formula, ΔA Z Having state Δx z The state negative feedback effect, for Figure 2 The inner loop section of the system has a robust stabilizing effect to ensure the asymptotic stability of the system and a suppressing effect to system disturbances.

[0120] make The state-space model is obtained as follows:

[0121]

[0122] in, C I =[-K Z 0],D I =[0] (35)

[0123] Equation (34) constitutes the stabilization controller, and correspondingly, K Z This is called stabilization control gain.

[0124] 2.3 Integral Servo Controller Model

[0125] The integrated integral controller and the stabilizer controller are integral servo controllers, represented as follows:

[0126] u=C c ·x c +D c1 ·y+D c2 ·r (36)

[0127] in, y=[ΔP C ], r=[ΔP S ], u=[ΔAZ ].

[0128]

[0129] C c =[0 0 0 -K Z 0],D c1 =[0],D c2 =[0] (37)

[0130] The open-loop state-space model formed by the integral servo controller and the controlled object is as follows:

[0131]

[0132] y = C open ·x+D open ·u+H open ·w (38)

[0133] in, u=[ΔA Z ], w=[ΔA j ΔP S ] T ,and

[0134]

[0135]

[0136] C open =[0 0 0 1 0 0 0],D open =[0],H open =[0 0] (39)

[0137] Its output feedback control law is as follows:

[0138] 2.4 Integral Servo Controller Model

[0139] The integrated integral controller and the stabilizer controller are integral servo controllers, represented as follows:

[0140]

[0141] u=C c ·x c +D c1 ·y+D c2 ·r (36)

[0142] in, y=[ΔP C ], r=[ΔP S], u=[ΔA Z ].

[0143]

[0144] C c =[0 0 0 -K Z 0],D c1 =[0],D c2 =[0] (37)

[0145] The open-loop state-space model formed by the integral servo controller and the controlled object is as follows:

[0146]

[0147] y = C open ·x+D open ·u+H open ·w (38)

[0148] in, u=[ΔA Z ], w=[ΔA J ΔP S ] T ,and

[0149]

[0150]

[0151] C open =[0 0 0 1 0 0 0],D open =[0],H open =[0 0] (39)

[0152] Its output feedback control law is as follows:

[0153]

[0154] 2.5 Integral Servo Controller Design Algorithm

[0155] Within the range of inlet pressure disturbance and variable flow area disturbance, the system needs to meet the following steady-state performance requirements and dynamic performance requirements:

[0156] (1) Steady-state performance: Phase angle stability margin is greater than N°;

[0157] (2) Dynamic performance: Settling time less than t s The overshoot is less than σ.

[0158] 2.5.1 Steady-state flow continuity equation

[0159] In steady state, based on the continuity of the main flow, the pressure-flow steady-state equilibrium equation of the main flow cavity can be obtained as follows:

[0160] Let the pressure input at a certain design point be P. S,i The area of ​​the valve-type opening is A. J,i The design value of the pressure difference before and after the metering valve is known to be P. e In steady state, the pressure in the cavity after the metering valve, the pressure in the cavity before the nozzle, and the flow area of ​​the orifice of the actuator valve should satisfy: P C,i =P S,i -P e (49)

[0161]

[0162]

[0163] Furthermore, the parameter K can be calculated. AJ,i K PJ,i K AZ,i K PZ,i and K PT,i The value of .

[0164] 2.5.2 Dynamic Design of Steady-State Operating Point

[0165] (1) Design of the initial working point

[0166] Let x be the compression of the spring at the initial design point in steady state. szd,1 Then, according to the steady-state equilibrium equation of the execution gate: 0 = A zx P C -A zx P Z -K2x z -F L2 (52)

[0167] get:

[0168] Then, the parameter K is obtained. AY,1 and K AT2,1 The value of .

[0169] Secondly, determine the appropriate slope of the flow area change at the inlet and outlet throttling orifices. and By optimizing the weighting matrices Q and R, and calculating P1, the value of the control gain K can be obtained. Z,1 =R -1 B1 T P1(4).

[0170] (2) Design of other working points

[0171] Let i = 1, ..., n, where n is the number of steady-state operating points. When the valve enters steady-state operation, the relationship between the increment of the orifice opening and the change in area is as follows:

[0172] Then, the compression amount of the valve at the steady-state point is: x szd,i =x szd,i-1 +Δx uz,i (55)

[0173] According to the steady-state equilibrium equation of the execution gate, we get:

[0174] Then, the parameter K is obtained. AY,i and K AT2,i The value of .

[0175] Similarly, by optimizing the weighting matrices Q and R, P can be calculated. i The value of the control gain K is obtained. Z,i =R -1 B i T P i (4).

[0176] 2.5.3 Calculation of initial parameters for the valve

[0177] (1) Execute the gate

[0178] If the initial opening of the valve-type hole is x uz,0 The design point has an opening degree of x. uz,1 Let the initial compression of the valve spring be x. szd,0 Since Δx uz =Δx szd We get: x szd,0 =x szd,1 -(x uz,1 -x uz,0 (57)

[0179] (2) Differential pressure valve

[0180] The steady-state equilibrium equation of the differential pressure control device is: 0 = A y P S -A y P C -Kx y -F L (58)

[0181] Let the initial compression of the spring in the differential pressure control device be x. scd,0 Then F L =K·x scd,0 In steady state, the compression of the spring at the design point is:

[0182] If the initial opening of the orifice of the differential pressure control device is x uin,0 and x uout,0 The opening degree at the design point is x uin,1 and x uin,2 Since Δx y =Δx scd We get: x scd,0 =x scd,1 -(x uin,1 -x uin,0 (60)

[0183] Currently, the design and implementation method of the integral differential pressure control device proposed in this application has been applied to the modeling, simulation, and verification of a certain aero-engine fuel system, laying an important foundation for the design of aero-engine fuel systems and supporting the transformation and upgrading of the control system of a certain aero-engine. Therefore, this application has significant engineering application value and substantial economic benefits in the modeling and simulation of differential pressure control devices and other hydraulic systems using this system.

[0184] Corresponding to the above method, this application also provides a fuel servo differential pressure control method for aero-engines, such as... Figure 4 As shown, the method includes:

[0185] Step S410: Based on the command oil pressure increment and metering valve flow area increment in response to the disturbance change, and the current execution valve flow area increment output by the stabilizing controller, control the controlled object and output the pressure increment after the metering valve and the pressure increment before the nozzle.

[0186] Step S420: Based on the first adjustment difference between the pressure increment after the metering valve output by the controlled object control system and the pressure increment of the spring cavity of the actuator valve output by the integral controller, obtain a new flow area increment of the actuator valve so that the pressure increment after the metering valve output by the controlled object control system is the design value.

[0187] Step S430: Using a preset integral control algorithm, process the second adjustment difference between the pressure increment after the metering valve output by the controlled object control system and the command oil pressure increment input to the system to obtain the pressure increment of the spring chamber of the actuator valve.

[0188] In another embodiment provided in this application, a computer-readable storage medium is also provided, which stores instructions that, when executed on a computer, cause the computer to perform any of the aero-engine integral differential pressure control methods described in the above embodiments.

[0189] In another embodiment provided in this application, a computer program product containing instructions is also provided, which, when run on a computer, causes the computer to execute any of the aero-engine integral differential pressure control methods described in the above embodiments.

[0190] Those skilled in the art will understand that the embodiments in this application can be provided as methods, systems, or computer program products. Therefore, the embodiments in this application can take the form of entirely hardware embodiments, entirely software embodiments, or embodiments combining software and hardware aspects. Furthermore, the embodiments in this application can take the form of computer program products implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0191] This application describes embodiments of methods, apparatus (systems), and computer program products according to embodiments of this application with reference to flowchart illustrations and / or block diagrams. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0192] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0193] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0194] Although preferred embodiments have been described in this application, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of the embodiments of this application.

[0195] Obviously, those skilled in the art can make various modifications and variations to the embodiments of this application without departing from the spirit and scope of the embodiments of this application. Therefore, if these modifications and variations to the embodiments of this application fall within the scope of the claims in this application and their equivalents, then this application also intends to include these modifications and variations.

Claims

1. An integral-type differential pressure control system for an aero-engine, characterized in that, The system includes: a controlled object control system, a stabilizing controller, and an integral controller; The controlled object control system is used to control the oil pressure increment based on the change in disturbance. and metering valve flow area increment and the increment of the current operating valve flow area output by the stabilization controller. It controls the controlled object and outputs the pressure increment after the metering valve. and nozzle inlet pressure increment ; The stabilization controller is used to measure the pressure increment after the metering valve based on the output of the controlled object's control system. The pressure increment of the actuator valve spring chamber output by the integral controller The first adjustment difference is used to obtain the new increase in the flow area of ​​the actuator. So that the pressure increment after the metering valve output by the control system of the controlled object is... This is the design value; The integral controller is used to apply a preset integral control algorithm to the pressure increment after the metering valve output by the controlled object control system. The command oil pressure increment input to the system The second adjustment difference is processed to obtain the pressure increment of the actuator valve spring cavity. .

2. The system as described in claim 1, characterized in that, The integral controller includes an equal pressure differential valve, an integral control gain unit, and an integral flow path; The differential pressure valve is used to control the increment of the command oil pressure of the system. Pressure increment after metering valve output by the controlled object control system Second adjustment difference Process the data to obtain the displacement increment of the differential pressure valve. and corresponding velocity increment ; The integral control gain unit is used for integrating the integral control gain. The displacement increment of the equal pressure differential valve The process is performed to obtain the increment of the throttling area of ​​the differential pressure valve. ; The integral flow path is used to calculate the proportional increment of the differential pressure valve displacement and the increment of the actuator valve speed output by the stabilizing controller. Obtain the pressure increment of the spring chamber of the actuator valve. The proportional increment of the displacement of the differential pressure valve is the integral control gain. The displacement increment of the equal pressure differential valve The product of.

3. The system as described in claim 2, characterized in that, The sedation controller includes an actuation gate and a sedation control gain unit; The actuator valve is used to control the pressure increment after the metering valve output by the control system of the controlled object. The pressure increment of the actuator valve spring cavity output by the integral flow path The first adjustment difference is used to obtain the valve displacement increment. and the increase in the speed of the valve movement The change in valve displacement is executed. Equivalent to the change in the opening of the valve-type orifice ; The stabilization control gain unit is used for stabilization control gain. The incremental displacement of the actuator valve The process is performed to obtain the increase in the flow area of ​​the valve-type orifice. The stabilization control gain Based on the flow area of ​​different actuator valve types With different valve opening sizes The ratio is determined.

4. The system as described in claim 3, characterized in that, The controlled object control system is also used to input the incremental movement speed of the actuator valve output by the actuator valve. and the incremental speed of the differential pressure valve movement ; Specifically, based on the command oil pressure increment in response to disturbance changes. and metering valve flow area increment and the increase in the current execution valve flow area The incremental movement speed of the differential pressure valve and the increase in the speed of the valve movement It controls the controlled object and outputs the pressure increment after the metering valve. and nozzle inlet pressure increment .

5. The system as described in claim 2, characterized in that, The control law of the integral controller is determined by the throttling area of ​​the equal pressure differential valve. With opening Design function throttling area With opening Design function The decision, and its deviation are expressed as follows: and Among them, the displacement increment of the equal pressure differential valve equal and Therefore, the integral control gain of the control law is: ； in, Indicates the increase in import area The determined control gain coefficient, Indicated by export area The control gain coefficient is determined by the increment. The volume of the valve spring cavity is determined by B, where B is the bulk modulus of the oil.

6. The system as described in claim 5, characterized in that, The preset integral control algorithm is expressed as follows: In steady state, ; Where △t is the control time. For integral control gain, This is the pressure increment of the spring chamber of the actuator valve. The volume of the valve spring cavity is determined by B, where B is the bulk modulus of the oil.

7. The system as described in claim 3, characterized in that, The control law of the stabilizing controller is determined by the flow area of ​​the actuator valve orifice. With the opening of the valve-type hole Design function The decision, its deviation is expressed as Among them, the valve displacement change is executed. Equivalent to the change in the opening of the valve-type orifice The stabilization control gain is .

8. A method for integral differential pressure control of an aero-engine, characterized in that, Applied to the system described in claims 1-7, the method comprises: Command oil pressure increment based on disturbance changes and metering valve flow area increment and the increment of the current operating valve flow area output by the stabilization controller. It controls the controlled object and outputs the pressure increment after the metering valve. and nozzle inlet pressure increment ; Based on the pressure increment after the metering valve output by the control system of the controlled object The pressure increment of the actuator valve spring chamber output by the integral controller The first adjustment difference is used to obtain the new increase in the flow area of ​​the actuator. So that the pressure increment after the metering valve output by the control system of the controlled object is... This is the design value; A preset integral control algorithm is used to control the pressure increment after the metering valve output by the control system of the controlled object. The command oil pressure increment input to the system The second adjustment difference is processed to obtain the pressure increment of the actuator valve spring cavity. .

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that, when executed by a processor, implements the steps of the method described in claim 8.

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