CN111505964B - Full-real information source semi-physical simulation system and test method for aircraft engine - Google Patents
Full-real information source semi-physical simulation system and test method for aircraft engine Download PDFInfo
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- CN111505964B CN111505964B CN202010464629.7A CN202010464629A CN111505964B CN 111505964 B CN111505964 B CN 111505964B CN 202010464629 A CN202010464629 A CN 202010464629A CN 111505964 B CN111505964 B CN 111505964B
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- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B17/00—Systems involving the use of models or simulators of said systems
- G05B17/02—Systems involving the use of models or simulators of said systems electric
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- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0218—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
- G05B23/0256—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults injecting test signals and analyzing monitored process response, e.g. injecting the test signal while interrupting the normal operation of the monitored system; superimposing the test signal onto a control signal during normal operation of the monitored system
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Abstract
The utility model discloses an aeroengine control system full real information source semi-physical simulation system includes: the system comprises a comprehensive management subsystem, an engine simulation subsystem, a sensor simulation subsystem, an actuator and load simulation subsystem, a controller simulation subsystem and a fuel supply simulation subsystem. The method can be compatible with a hardware-in-loop system, and can realize physical simulation of a sensor and an execution load mechanism full-physical information source; in addition, the high-compatibility simulation of various aero-engines can be realized through the parameter configuration of the comprehensive management subsystem to each subsystem, and the method is suitable for various aero-engine control systems.
Description
Technical Field
The disclosure belongs to the technical field of test of an aero-engine control system, and particularly relates to a full-real information source semi-physical simulation system and a test method of the aero-engine control system.
Background
In the whole development process of the aircraft engine control system, a semi-physical simulation test is the most important ring before the test is carried out. Due to the characteristics of good controllability, safety, no limitation of climate environment, repeated use and the like of the semi-physical simulation technology, the defects of high cost, large risk, low pure numerical simulation precision, poor intuition and the like in a full physical test are well overcome, particularly in the fields of fault diagnosis and fault-tolerant control, a semi-physical simulation experiment platform can comprehensively verify a fault-tolerant system and more truly and safely traverse all fault types and fault modes, and the semi-physical simulation experiment platform becomes an important test means and technical tool in the process of pre-research, scheme demonstration or modification, design, manufacture, use, maintenance and the like of an aircraft engine digital control system at present. However, the current semi-physical verification method has the following disadvantages: 1. part of the source simulation is from circuit simulation and not from physical effect simulation devices (such as temperature, pressure and the like); 2. the signal source and load of part of the actuator are derived from circuit simulation and not physical effect simulation devices (such as guide vane angle, turbine guider and the like); 3. the test system platform is poor in design compatibility and cannot be applied to various types of aero-engine control systems.
Disclosure of Invention
Aiming at the problems of poor compatibility and incomplete physical effect simulation of the existing semi-physical simulation platform of the aero-engine, the disclosure aims to provide a full-real information source semi-physical simulation system and a test method of the aero-engine control system, which can flexibly configure physical effect simulation devices according to the control system configurations of different aero-engines, independently control and comprehensively manage the physical effect simulation devices, realize full-digital simulation of the aero-engine, hardware-in-loop simulation and semi-physical simulation, and provide a relatively real link for comprehensive verification, fault diagnosis, fault-tolerant control and the like of the aero-engine control system.
In order to achieve the above object, the present disclosure provides the following technical solutions:
a full real information source semi-physical simulation system of an aircraft engine control system comprises:
the engine simulation subsystem is used for simulating each section parameter of the aero-engine to obtain the running state of the aero-engine;
the sensor simulation subsystem is used for simulating corresponding sensors in the aircraft engine and outputting measurement signals of the corresponding sensors;
the actuator and load simulation subsystem is used for simulating an actuator and a load in the aircraft engine;
the controller simulation subsystem is used for simulating the engine full-authority electronic control system;
and the comprehensive management subsystem is used for sending configuration signals to the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem and the controller simulation subsystem and receiving feedback signals of the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem and the controller simulation subsystem.
Preferably, the integrated management subsystem comprises an integrated management platform, and is connected with the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem and the controller simulation subsystem through a distributed synchronous control bus.
Preferably, the engine simulation subsystem comprises an engine simulation computer, the engine simulation computer comprises an input interface and an output interface, the input interface is used for being connected with the actuator, the load simulation subsystem and the comprehensive management subsystem respectively, and the output interface is connected with the sensor simulation subsystem.
Preferably, the sensor simulation subsystem comprises a sensor simulation computer, a temperature sensor module, a pressure sensor module and a rotating speed sensor module; wherein the content of the first and second substances,
the temperature sensor module comprises a temperature simulator, a temperature characteristic controller and a temperature sensor and is used for measuring the total air inlet temperature of the engine, the front temperature of the high-pressure compressor and the rear exhaust temperature of the turbine;
the pressure sensor module comprises a pressure simulator, a pressure characteristic controller and a pressure sensor and is used for measuring the total intake pressure, the rear fan pressure and the rear turbine exhaust pressure of the engine;
the rotation speed sensor module comprises a rotation speed simulator, a rotation speed characteristic controller and a rotation speed sensor and is used for measuring the rotation speed of a high-pressure rotor and the rotation speed of a low-pressure rotor of the engine.
Preferably, the actuator and load simulation subsystem comprises an actuator simulation computer, a fuel metering module, a gas compressor and fan guide vane module, a turbine guider module, a spray pipe throat module, a thrust vector nozzle module, a variable bleed air and bleed air module and a load simulation module; wherein the content of the first and second substances,
the fuel metering module comprises an electro-hydraulic servo valve, a fuel pump regulator, a turbine flowmeter and a first position sensor and is used for metering the flow of fuel supplied to an engine;
the compressor and fan guide vane module comprises a fan guide vane angle adjusting electrohydraulic servo valve, a force sensor, a second position sensor and an actuator and is used for simulating a variable compressor and a guide vane adjusting mechanism in the engine;
the turbine guider module comprises a guide vane angle electro-hydraulic servo valve, a force sensor, a third position sensor and an actuator and is used for adjusting the guide vane angle of the turbine guider;
the spray pipe throat module comprises a spray pipe throat area adjusting electrohydraulic servo valve, a spray pipe throat actuator, a force sensor and a fourth position sensor and is used for adjusting the spray pipe throat area;
the thrust vector nozzle module comprises a tail nozzle area adjusting electrohydraulic servo valve, a tail nozzle actuating cylinder, a force sensor and a fifth position sensor and is used for adjusting the tail nozzle area;
the variable bleed air and bleed air module comprises a compressor bleed air valve, a force sensor and a sixth position sensor and is used for simulating the bleed air and bleed air valve of the inner duct and the outer duct of the engine.
Preferably, the controller simulation subsystem comprises a controller simulation calculation module, a throttle lever and a seventh position sensor.
Preferably, the system further comprises a fuel supply simulation subsystem, wherein the fuel supply simulation subsystem comprises a main fuel pump, a motor driving device, a gear transmission device and a fuel tank and is used for simulating an oil supply system of the aircraft engine.
The invention also provides a fault-tolerant control semi-physical verification method of the aircraft engine simulation system, which comprises the following steps:
s100, starting a simulation system, and configuring an engine simulation subsystem, a sensor simulation subsystem, an actuator and load simulation subsystem, a controller simulation subsystem and a fuel supply subsystem through a comprehensive management subsystem;
s200, the integrated management subsystem randomly generates an electronic/electric or sensor drift fault signal, and transmits the fault signal to the engine simulation subsystem, the sensor simulation subsystem, the fuel supply simulation subsystem, the actuator and load simulation subsystem and the controller simulation subsystem through a bus to perform a fault simulation test;
s300, the comprehensive management subsystem observes the state parameters of all sections of the engine by collecting engine flight simulation verification data of the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem, the controller simulation subsystem and the fuel supply simulation subsystem, monitors the control quality and fault tolerance of the test in real time, and evaluates, warns and records the control quality and fault tolerance.
Preferably, in step S100, the configuring, by the integrated management subsystem, the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem, the controller simulation subsystem, and the fuel supply subsystem includes:
randomly configuring a target height, a target Mach number and state maintaining time of the target Mach number to the engine simulation subsystem to complete selection of a group of flight envelope lines;
configuring initial temperature, pressure and rotating speed parameters to the sensor subsystem;
inputting a fault-tolerant control algorithm to the controller simulation subsystem;
configuring environmental parameters of height, mach number and inlet air temperature to the engine subsystem;
configuring motor drive control parameters to the fuel delivery subsystem;
and configuring load parameters to the actuator and the load simulation subsystem.
The present disclosure also provides a semi-physical verification of a control algorithm for a simulation system, comprising the steps of:
s1000, creating a controller basic component in a controller simulation subsystem, realizing description, interface relation and function realization of the controller component and building an engine control function by the controller in an S-function programming mode based on an MATLAB development environment;
s2000, building Simulink according to a control algorithm to be verified, and embedding an algorithm module into a basic component module of the controller;
s3000, after the building of the control basic component is completed in the MATLAB/Simulink, compiling the MATLAB Simulink file into a C code and downloading the C code into a controller simulation subsystem for simulation;
s4000, starting each system of the semi-physical simulation platform, selecting a verification experiment, designing target height, target Mach number and state maintaining time in the comprehensive management subsystem, selecting a group of flight envelopes, transmitting flight targets and environment parameters to the controller simulation subsystem through a bus, and simulating the aircraft to fly to the target height and the target Mach number according to certain constraints;
and S5000, transmitting the state parameters of each section of the engine to a control comprehensive management subsystem through a bus, observing the control quality, surge margin and other parameters of the rotating speed, temperature and pressure parameters measured by an engine sensor, monitoring the control quality, fault tolerance performance and the like of a test in real time, and carrying out evaluation, warning, recording and other operations so as to verify a control algorithm.
Compared with the prior art, the beneficial effect that this disclosure brought does:
1. the system is a semi-physical simulation system, is compatible with a hardware-in-loop system, and can realize physical simulation of a sensor and an execution load mechanism full-physical information source;
2. the high-compatibility simulation of various aero-engines can be realized by the parameter configuration of the comprehensive management subsystem to each subsystem, and the system is suitable for various aero-engine control systems.
Drawings
FIG. 1 is a schematic structural diagram of a full-real-information-source semi-physical simulation system of an aircraft engine control system according to an embodiment of the disclosure;
wherein, 1-the integrated management subsystem; 2-an engine simulation subsystem; 3-a sensor simulation subsystem; 4-a fuel supply simulation subsystem; 5-actuator and load simulation subsystem; 6-control the simulation subsystem.
Detailed Description
Specific embodiments of the present disclosure will be described in detail below with reference to fig. 1. While specific embodiments of the disclosure are shown in the drawings, it should be understood that the disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
It should be noted that certain terms are used throughout the description and claims to refer to particular components. As one skilled in the art will appreciate, various names may be used to refer to a component. This specification and claims do not intend to distinguish between components that differ in name but not function. In the following description and in the claims, the terms "include" and "comprise" are used in an open-ended fashion, and thus should be interpreted to mean "include, but not limited to. The description which follows is a preferred embodiment of the invention, but is made for the purpose of illustrating the general principles of the invention and not for the purpose of limiting the scope of the invention. The scope of the present disclosure is to be determined by the terms of the appended claims.
To facilitate an understanding of the embodiments of the present disclosure, the following detailed description is to be considered in conjunction with the accompanying drawings, and the drawings are not to be construed as limiting the embodiments of the present disclosure.
In one embodiment, as shown in fig. 1, the present disclosure provides a full-real source semi-physical simulation system for an aircraft engine control system, including:
the engine simulation subsystem is used for simulating each section parameter of the aero-engine to obtain the running state of the aero-engine;
the sensor simulation subsystem is used for simulating corresponding sensors in the aircraft engine and outputting measurement signals of the corresponding sensors;
the actuator and load simulation subsystem is used for simulating an actuator and a load in the aircraft engine;
the controller simulation subsystem is used for simulating the engine full-authority electronic control system;
and the comprehensive management subsystem is used for sending configuration signals to the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem and the controller simulation subsystem and receiving feedback signals of the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem and the controller simulation subsystem.
In this embodiment, the integrated management subsystem includes an integrated management platform, which is connected to the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem, the controller simulation subsystem, and the fuel supply simulation subsystem through a distributed synchronous control bus, and which transmits a system configuration signal to each managed subsystem, receives state feedback and signal data of each subsystem, and implements control, supervision, and management of the entire semi-physical simulation system. Parameters of all parts, environmental parameters and engine model parameters of the semi-physical simulation system can be changed only by operating the comprehensive management subsystem, fault injection is directly carried out on all the simulation systems, simulation under various engine models, environments and fault conditions is achieved, and universality of the engine models, complexity of the environments and authenticity of the fault conditions are really achieved. Meanwhile, the characteristic curve and the state change of the specified component can be directly observed on the comprehensive management platform, the simulation parameters are stored, and data support is provided for post-processing.
In another embodiment, the engine simulation subsystem comprises an engine simulation computer comprising an input and an output interface, wherein the input interface is connected to the actuator and load simulation subsystem and the integrated management subsystem, respectively, and the output interface is connected to the sensor simulation subsystem.
In the embodiment, the engine simulation computer is used as a platform for running the real-time dynamic model of the engine, and an input interface of the engine simulation computer is used for receiving position signals measured by each position sensor in the actuator and the load simulation subsystem and receiving height and Mach number signals configured by the comprehensive management computer; the output interface is used for outputting temperature, pressure and rotating speed target control signals to the sensor simulation subsystem and outputting real-time state data of the engine model to the comprehensive management computer.
In another embodiment, the sensor simulation subsystem includes a sensor simulation computer, a temperature sensor module, a pressure sensor module, and a speed sensor module; wherein the content of the first and second substances,
the temperature sensor module comprises a temperature simulator, a temperature characteristic controller and a temperature sensor, wherein the temperature simulator, the temperature characteristic controller and the temperature sensor form a control loop and are used for measuring the total air inlet temperature of the engine, the front temperature of the high-pressure air compressor and the rear exhaust temperature of the turbine;
the pressure sensor module comprises a pressure simulator, a pressure characteristic controller and a pressure sensor, wherein the pressure simulator, the pressure characteristic controller and the pressure sensor form a control loop and are used for measuring the total intake pressure, the rear fan pressure and the rear turbine exhaust pressure of the engine;
the rotation speed sensor module comprises a rotation speed simulator, a rotation speed characteristic controller and a rotation speed sensor, wherein the rotation speed simulator, the rotation speed characteristic controller and the rotation speed sensor form a control loop for measuring the rotation speed of a high-pressure rotor and the rotation speed of a low-pressure rotor of the engine.
In this embodiment, the sensor simulation computer serves as a signal acquisition platform of the sensor simulation subsystem, and the input end of the sensor simulation computer receives target control signals of temperature, pressure and rotation speed sent by the engine simulation subsystem, receives system configuration signals sent by the comprehensive management subsystem, and receives temperature, pressure and rotation speed signals fed back by the temperature sensor module, the pressure sensor module and the rotation speed sensor module; the output end of the system respectively sends a control signal and a system configuration signal to the temperature characteristic controller, the pressure characteristic controller and the rotating speed characteristic controller, and sends temperature, pressure and rotating speed signals fed back by the temperature sensor module, the pressure sensor module and the rotating speed sensor module to the comprehensive management subsystem.
It can be appreciated that the temperature sensor module is used to simulate the total intake air temperature of the engine
Partial pressure compressor front temperature
Turbine exhaust gas temperature
Real-time temperature parameter values. The temperature characteristic controller is connected with the temperature simulator and the sensor simulation computer through an internal bus and connected with the comprehensive management subsystem through the sensor simulation computer, and controls the temperature simulator by receiving a temperature control target value sent by the engine simulation subsystem and received by the sensor simulation computer and a temperature feedback value measured by the temperature sensor, so that the temperature simulator can maintain constant temperature and the temperature sensor module can be monitored and managed in real time. The temperature sensor is rigidly connected with the temperature simulator, measures to obtain a real-time temperature parameter value simulated by the temperature simulator, and transmits the real-time temperature parameter value into the controller simulation subsystem through the sensor simulation computer to perform real-time control. The temperature simulator comprises an alcohol nozzle, an air bottle and an air nozzle.
It can be appreciated that the pressure sensor module is used to simulate total intake pressure of the engine
Back pressure of fan
Turbine exhaust rear pressure
Real time pressure parameter value. The pressure characteristic controller is connected with the pressure sensor module and the sensor simulation computer through an internal bus and is connected with the comprehensive management subsystem through the sensor simulation computer, and the pressure characteristic controller controls the opening of the inflating valve and the deflating valve by receiving a pressure control target value sent by the engine simulation subsystem and received by the sensor simulation computer and a pressure feedback value measured by the pressure sensor, so that a gas cabin in the pressure simulator maintains constant pressure and the pressure sensor module is ensured to be monitored and managed in real time. The pressure sensor is rigidly connected with the pressure simulator, and the pressure sensor measures and obtains a real-time pressure parameter value simulated by the pressure simulator, and the real-time pressure parameter value is transmitted to the controller simulation subsystem through the sensor simulation computer to be controlled in real time. The pressure simulator comprises a gas cabin, an inflation valve and an air release valve.
It can be appreciated that the speed sensor module is used to simulate the engine high pressure rotor speed (N) 2 ) Low rotor speed (N) 1 ) The rotating speed characteristic controller controls current and voltage values by receiving a rotating speed control target value sent by the engine simulation subsystem and high and low voltage rotating speed feedback values measured by the rotating speed sensor from the sensor simulation computer, so that the small inertia motor maintains constant rotating speed, and the rotating speed simulation system can be monitored and managed in real time. The rotating speed sensor is rigidly connected with the rotating speed simulator, measures the real-time rotating speed parameter value simulated by the rotating speed simulator, and transmits the real-time rotating speed parameter value to the controller simulation subsystem through the sensor simulation computer for real-time control. The rotating speed simulation device comprises 2 small inertia motors, high-voltage and low-voltage rotating speed simulation environments of the engine are constructed by using the small inertia motors and the controller, and high-voltage rotating speed and low-voltage rotating speed in different environments can be simulated.
In another embodiment, the system further comprises a fuel supply simulation subsystem comprising a main fuel pump, a motor drive, a gear assembly and a fuel tank for simulating an aircraft engine fuel supply system.
In this embodiment, the motor driving device and the gear transmission device are rigidly connected to the main fuel pump through the transmission shaft, and the power switching device is installed between the motor driving device and the main fuel pump, and provides two different power sources for the main fuel pump, and can be switched at any time. The main fuel pump receives two power sources, one power source is from a power source simulating a real engine, namely from a high-pressure rotor rotating shaft, and power divided by the rotating speed simulating device is used for driving a gear to drive the main fuel pump to supply oil; the other type of the fuel pump is directly driven by a motor and used as a standby power source, a controller of the motor driving device receives a system configuration signal sent by the comprehensive management subsystem, controls the motor to output driving force to the main fuel pump, and uploads a real-time feedback signal to the comprehensive management subsystem. The oil tank receives the high-pressure oil used by the physical effect simulation device of each actuator so as to recycle the high-pressure oil.
In another embodiment, the actuator and load simulation subsystem comprises an actuator simulation computer, a fuel metering module, a compressor and fan guide vane module, a turbine guider module, a nozzle throat module, a thrust vector nozzle module, a variable bleed and bleed module and a load simulation module; wherein the content of the first and second substances,
the fuel metering module comprises an electro-hydraulic servo valve, a fuel pump regulator, a turbine flowmeter and a first position sensor LVDT1 and is used for metering the flow of fuel supplied to an engine;
the compressor and fan guide vane module comprises a fan guide vane angle adjusting electrohydraulic servo valve, a force sensor, a second position sensor LVDT2 and an actuator, and is used for simulating a variable compressor and a guide vane adjusting mechanism in the engine;
the turbine guider module comprises a guide vane angle electro-hydraulic servo valve, a force sensor, a third position sensor LVDT3 and an actuator, and is used for adjusting the guide vane angle guided by the turbine;
the spray pipe throat module comprises a spray pipe throat area adjusting electrohydraulic servo valve, a spray pipe throat actuator, a force sensor and a fourth position sensor LVDT4 and is used for adjusting the spray pipe throat area;
the thrust vector nozzle module comprises a tail nozzle area adjusting electrohydraulic servo valve, a tail nozzle actuating cylinder, a force sensor and a fifth position sensor LVDT5 and is used for adjusting the tail nozzle area;
the variable bleed air and bleed air module comprises a compressor bleed air valve, a force sensor and a sixth position sensor LVDT6, and is used for simulating the bleed air and bleed air valve of the inner duct and the outer duct of the engine;
the load simulation module comprises a load controller, an actuator and a hydraulic servo valve and is used for simulating the load of the aero-engine.
In this embodiment, the actuator simulation computer is used as a signal acquisition and simulation platform for the actuator and the load simulation subsystem, and the input ends of the actuator simulation computer respectively receive a control signal sent by the controller simulation subsystem, a system configuration signal sent by the comprehensive management subsystem, and a position signal measured by the position sensor; the output end of the controller sends control signals sent by the controller simulation subsystem to each actuator respectively, and sends position signals measured by each sensor on each actuator to the engine simulation subsystem and the controller simulation subsystem.
It can be appreciated that the fuel metering module is the primary actuator for fuel flow control, and can accurately meter the fuel flow supplied to the engine combustion chamber, limiting the maximum and minimum fuel flow while ensuring the minimum pressure at which the fuel is supplied. One part of high-pressure oil output by the main fuel pump enters the constant-pressure valve to keep constant pressure so as to be used as an oil source of the electro-hydraulic servo valve, the other part of high-pressure oil is metered by the metering valve and then is conveyed to the combustion chamber, and redundant fuel oil returns to the inlet of the main pump through the oil return valve. The oil pressure at the nozzle is controlled by an equal pressure difference valve, and the equal pressure difference valve is used for keeping the front-back pressure difference of the metering valve unchanged by changing the oil return amount of the oil return valve, so that the fuel flow passing through the metering valve is in direct proportion to the metering window. The electro-hydraulic servo valve is connected with an actuating cylinder of the fuel pump regulator through an oil pipeline, and the electro-hydraulic servo valve changes the opening of a metering valve rigidly connected with a piston of the actuating cylinder by changing the position of the piston of the actuating cylinder according to a fuel flow control signal output by the controller simulation subsystem, and also determines the size of the main fuel flow. The LVDT1 signal of the first position sensor obtained by measurement is transmitted to the engine simulation subsystem through the actuator and the load simulation subsystem for model simulation, and the other path is transmitted to the controller simulation subsystem for closed-loop control. The turbine flowmeter is arranged on an oil outlet pipeline of the fuel pump regulator and can be used as an auxiliary device for measuring the flow of fuel oil.
The controller simulation subsystem is connected with the fan guide vane angle adjusting hydraulic servo valve in the compressor and the fan guide vane module, and is used for receiving high-pressure oil output by the main fuel pump and receiving a fuel flow control signal output by the controller simulation subsystem; and outputting fuel to adjust the piston of the actuator so as to adjust the angles of the gas compressor and the guide vane of the fan. The second position sensor LVDT2 is rigidly connected with the piston of the actuating cylinder, the piston position of the actuator is measured, namely the size of the angle of the guide vane of the air compressor and the fan is reflected, the signal of the second position sensor LVDT2 obtained by the measurement is transmitted to the engine simulation subsystem through the actuator and the load simulation subsystem computer, one path of the signal is used for updating the state of the engine in real time, and the other path of the signal is transmitted to the controller simulation subsystem for closed-loop control.
It can be understood that the guide vane angle adjusting electrohydraulic servo valve in the turbine guider module receives high-pressure oil output by the main fuel pump and receives a fuel flow control signal output by the controller simulation subsystem; and outputting fuel to adjust the piston of the actuator so as to adjust the guide vane angle of the turbine guider. The third position sensor LVDT3 is rigidly connected with the piston of the actuating cylinder, the piston position of the actuator is measured, namely the size of the guide vane angle of the turbine guider is reflected, the signal of the third position sensor LVDT3 is transmitted to the engine simulation subsystem through the actuator and the load simulation subsystem through one path to update the engine state in real time, and the other path is transmitted to the controller simulation subsystem for closed-loop control.
The jet pipe throat area adjusting hydraulic servo valve in the jet pipe throat module receives high-pressure oil output by the main fuel pump and receives a fuel flow control signal output by the controller simulation subsystem; and outputting fuel to adjust the piston of the actuator so as to adjust the throat area of the spray pipe. The fourth position sensor LVDT4 is rigidly connected with the piston of the actuating cylinder, the piston position of the actuator is measured, namely the size of the throat area of the spray pipe is reflected, the signal of the fourth position sensor LVDT4 is transmitted to the engine simulation subsystem through the actuator and the load simulation subsystem for updating the state of the engine in real time, and the signal of the fourth position sensor LVDT is transmitted to the controller simulation subsystem for closed-loop control.
The fuel flow control system comprises a thrust vector nozzle module, a controller simulation subsystem, a tail nozzle area adjusting electrohydraulic servo valve, a main fuel pump, a controller simulation subsystem and a controller simulation subsystem, wherein the tail nozzle area adjusting electrohydraulic servo valve in the thrust vector nozzle module receives high-pressure oil output by the main fuel pump and receives a fuel flow control signal output by the controller simulation subsystem; and outputting fuel to adjust the piston of the actuator so as to adjust the area of the tail nozzle. The fifth position sensor LVDT5 is rigidly connected with the piston of the actuating cylinder, the piston position of the actuator is measured, namely the size of the area of the tail nozzle is reflected, the signal of the fifth position sensor LVDT5 is transmitted to the engine simulation subsystem through the actuator and the load simulation subsystem for updating the state of the engine in real time, and the signal of the fifth position sensor LVDT is transmitted to the controller simulation subsystem for closed-loop control.
It can be understood that actuators of the bleed air and bleed air valves in the variable bleed air and bleed air module receive high-pressure oil output by the main fuel pump and receive fuel flow control signals output by the controller simulation subsystem; the size of the valve is adjusted by outputting fuel oil, so that the air entraining amount and the air bleeding amount are adjusted. The sixth position sensor LVDT6 is rigidly connected with the piston of the actuating cylinder, the piston position of the actuator is measured, namely bleed air and air release are reflected, the signal of the sixth position sensor LVDT6 is transmitted to the engine simulation subsystem through the actuator and the load simulation subsystem through one path to update the state of the engine in real time, and the other path is transmitted to the controller simulation subsystem for closed-loop control.
It can be understood that the hydraulic servo valve in the load simulation module receives high-pressure oil output by the main fuel pump and receives a fuel flow control signal output by the load controller; the output fuel adjusts the actuator piston, thereby adjusting the load. The load controller receives load configuration information sent by the comprehensive management subsystem and can simulate the load conditions of the actuating mechanisms of different engines in various states; and sending a fuel flow control signal to a hydraulic servo valve of a load, and sending a feedback signal to the comprehensive management subsystem to carry out unified health management and real-time monitoring.
In another embodiment, the controller simulation subsystem includes a controller simulation calculation module, a throttle lever simulation module, and a seventh position sensor LVDT7.
In this embodiment, the controller simulation calculation module adopts a Speedgoat basic version real-time target machine, and the control simulation subsystem is built on a Speedgoat platform by using Simulink simulation software and is connected with other subsystems of the system through rich type channels and I/O ports on the target machine. The input end of the controller simulation calculation module receives temperature, pressure and rotating speed signals measured by each corresponding sensor in the sensor simulation subsystem, position signals measured by each position sensor in the actuator and load simulation subsystem, system configuration signals sent by the comprehensive management subsystem and throttle lever position signals measured by a seventh position sensor LVDT 7; and sending a control feedback signal to the comprehensive management subsystem for health management and real-time monitoring, and sending a real-time control signal to the actuator and the load simulation subsystem. The throttle lever simulation module can truly simulate an airplane throttle lever, the angle of the throttle lever is measured by a seventh position sensor LVDT7 which is rigidly connected with the throttle lever, and important control input parameters such as a throttle lever angle (PLA) and the like are provided for an aero-engine.
In another embodiment, the present disclosure further provides a fault-tolerant control semi-physical verification method for an aircraft engine simulation system, including the following steps:
s100, starting a simulation system, and configuring an engine simulation subsystem, a sensor simulation subsystem, an actuator and load simulation subsystem, a controller simulation subsystem and a fuel supply subsystem through a comprehensive management subsystem;
in the step, a comprehensive management subsystem randomly configures target height, target Mach number and state maintaining time for the engine simulation subsystem to complete the selection of a group of flight envelopes;
configuring initial temperature, pressure and rotating speed parameters to the sensor subsystem;
inputting a fault-tolerant control algorithm to the controller simulation subsystem;
configuring environmental parameters of height, mach number and inlet air temperature to the engine subsystem;
configuring motor drive control parameters to the fuel delivery subsystem;
and configuring load parameters to the actuator and the load simulation subsystem.
S200, the comprehensive management subsystem randomly generates electronic/electric or sensor drifting fault signals according to a fault mode library, and transmits the fault signals to the engine simulation subsystem, the sensor simulation subsystem, the fuel supply simulation subsystem, the actuator and load simulation subsystem and the controller simulation subsystem through a bus to perform a fault simulation test;
s300, the comprehensive management subsystem observes the state parameters of all sections of the engine by collecting engine flight simulation verification data of the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem, the controller simulation subsystem and the fuel supply simulation subsystem, monitors the control quality and fault tolerance of the test in real time, and evaluates, warns and records the control quality and fault tolerance.
In another embodiment, the present disclosure further provides a semi-physical verification of a control algorithm for a simulation system, comprising the steps of:
s1000, creating a controller basic component in a controller simulation subsystem, realizing description, interface relation and function realization of the controller component and building an engine control function by the controller in an S-function programming mode based on an MATLAB development environment;
s2000, building Simulink according to a control algorithm to be verified, and embedding an algorithm module into a controller basic component module;
s3000, after the building of the control basic component is completed in the MATLAB/Simulink, compiling the MATLAB Simulink file into a C code and downloading the C code into a controller simulation subsystem for simulation;
s4000, starting systems of a semi-physical simulation platform, selecting a verification experiment, designing target height, target Mach number and state maintaining time of the target Mach number in a comprehensive management subsystem, selecting a group of flight envelopes, transmitting flight targets and environmental parameters to a controller simulation subsystem through a bus, and simulating an airplane to fly to the target height and the target Mach number according to certain constraints;
and S5000, transmitting the state parameters of each section of the engine to a control comprehensive management subsystem through a bus, observing the control quality, surge margin and other parameters of the rotating speed, temperature and pressure parameters measured by an engine sensor, monitoring the control quality, fault tolerance performance and the like of a test in real time, and carrying out evaluation, warning, recording and other operations so as to verify a control algorithm.
The foregoing describes the general principles of the present application in conjunction with specific embodiments, however, it is noted that the advantages, effects, etc. mentioned in the present application are merely examples and are not limiting, and they should not be considered essential to the various embodiments of the present application. Furthermore, the foregoing disclosure of specific details is provided for purposes of illustration and understanding only, and is not intended to limit the application to the details which are set forth in order to provide a thorough understanding of the present application.
Claims (8)
1. An aircraft engine full-real information source semi-physical simulation system comprises:
the engine simulation subsystem is used for simulating each section parameter of the aero-engine to obtain the running state of the aero-engine;
the sensor simulation subsystem is used for simulating corresponding sensors in the aircraft engine and outputting measurement signals of the corresponding sensors, and comprises a sensor simulation computer, a temperature sensor module, a pressure sensor module and a rotating speed sensor module; wherein, the first and the second end of the pipe are connected with each other,
the temperature sensor module comprises a temperature simulator, a temperature characteristic controller and a temperature sensor, the temperature sensor module is used for simulating the real-time temperature parameter values of the total air inlet temperature, the front temperature of the high-pressure air compressor and the rear exhaust temperature of the turbine of the engine and measuring the total air inlet temperature, the front temperature of the high-pressure air compressor and the rear exhaust temperature of the turbine of the engine, and the temperature simulator comprises an alcohol nozzle, an air bottle and an air nozzle;
the pressure sensor module comprises a pressure simulator, a pressure characteristic controller and a pressure sensor, the pressure sensor module is used for simulating real-time pressure parameter values of total intake pressure, fan rear pressure and turbine rear exhaust pressure of the engine and measuring the total intake pressure, fan rear pressure and turbine rear exhaust pressure of the engine, and the pressure simulator comprises an air bin, an inflation valve and an deflation valve;
the rotating speed sensor module comprises a rotating speed simulator, a rotating speed characteristic controller and a rotating speed sensor, the rotating speed sensor module is used for simulating real-time rotating speed parameter values of the rotating speed of a high-pressure rotor and the rotating speed of a low-pressure rotor of the engine and measuring the rotating speed of the high-pressure rotor and the rotating speed of the low-pressure rotor of the engine, and the rotating speed simulator comprises 2 small-inertia motors;
the actuator and load simulation subsystem is used for simulating an actuator and a load in the aircraft engine and comprises an actuator simulation computer, a fuel metering module, a gas compressor and fan guide vane module, a turbine guider module, a spray pipe throat module, a thrust vector nozzle module, a variable bleed and bleed module and a load simulation module; wherein, the first and the second end of the pipe are connected with each other,
the fuel metering module comprises an electro-hydraulic servo valve, a fuel pump regulator, a turbine flowmeter and a first position sensor and is used for metering the flow of fuel supplied to an engine;
the air compressor and fan guide vane module comprises a fan guide vane angle adjusting electro-hydraulic servo valve, a force sensor, a second position sensor and an actuator and is used for simulating a variable air compressor and a guide vane adjusting mechanism in the engine;
the turbine guider module comprises a guide vane angle electro-hydraulic servo valve, a force sensor, a third position sensor and an actuator and is used for adjusting the guide vane angle of the turbine guider;
the spray pipe throat module comprises a spray pipe throat area adjusting electrohydraulic servo valve, a spray pipe throat actuator, a force sensor and a fourth position sensor and is used for adjusting the spray pipe throat area;
the thrust vector nozzle module comprises a tail nozzle area adjusting electrohydraulic servo valve, a tail nozzle actuating cylinder, a force sensor and a fifth position sensor and is used for adjusting the tail nozzle area;
the variable bleed air and bleed air module comprises a compressor bleed air valve, a force sensor and a sixth position sensor and is used for simulating the bleed air and bleed air valve of the inner duct and the outer duct of the engine;
the load simulation module comprises a load controller, an actuator and a hydraulic servo valve and is used for simulating the load of the aero-engine;
the controller simulation subsystem is used for simulating the engine full-authority electronic control system;
and the comprehensive management subsystem is used for sending configuration signals to the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem and the controller simulation subsystem and receiving feedback signals of the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem and the controller simulation subsystem.
2. The aircraft engine full-real information source semi-physical simulation system of claim 1, wherein the integrated management subsystem comprises an integrated management platform connected with the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem and the controller simulation subsystem through a distributed synchronous control bus.
3. The aircraft engine full reality source semi-physical simulation system of claim 1, wherein the engine simulation subsystem comprises an engine simulation computer comprising input and output interfaces, wherein the input interfaces are connected to the actuator and load simulation subsystem and the integrated management subsystem, respectively, and the output interface is connected to the sensor simulation subsystem.
4. The aircraft engine full real source semi-physical simulation system of claim 1, wherein the controller simulation subsystem comprises a controller simulation calculation module, a throttle lever and a seventh position sensor.
5. The aircraft engine full real source semi-physical simulation system according to claim 1, further comprising a fuel supply simulation subsystem, the fuel supply simulation subsystem comprising a main fuel pump, a motor drive, a gear transmission and a fuel tank for simulating an oil supply system of the aircraft engine.
6. A fault-tolerant control semi-physical verification method for the aircraft engine full-real information source semi-physical simulation system of claim 5, comprising the following steps:
s100, starting a simulation system, and configuring an engine simulation subsystem, a sensor simulation subsystem, an actuator and load simulation subsystem, a controller simulation subsystem and a fuel supply subsystem through a comprehensive management subsystem;
s200, the integrated management subsystem randomly generates an electronic/electric or sensor drift fault signal, and transmits the fault signal to the engine simulation subsystem, the sensor simulation subsystem, the fuel supply simulation subsystem, the actuator and load simulation subsystem and the controller simulation subsystem through a bus to perform a fault simulation test;
s300, the comprehensive management subsystem observes the state parameters of all sections of the engine by collecting engine flight simulation verification data of the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem, the controller simulation subsystem and the fuel supply simulation subsystem, monitors the control quality and fault tolerance of the test in real time, and evaluates, warns and records the control quality and fault tolerance.
7. A fault-tolerant control semi-physical verification method according to claim 6, wherein the configuring of the engine simulation subsystem, the sensor simulation subsystem, the actuator and load simulation subsystem, the controller simulation subsystem and the fuel supply subsystem by the integrated management subsystem in step S100 comprises:
randomly configuring a target height, a target Mach number and state maintaining time of the target Mach number to the engine simulation subsystem to complete selection of a group of flight envelope lines;
configuring initial temperature, pressure and rotating speed parameters to the sensor simulation subsystem;
inputting a fault-tolerant control algorithm to the controller simulation subsystem;
configuring environmental parameters of height, mach number and inlet air temperature to the engine simulation subsystem;
configuring motor drive control parameters to the fuel delivery subsystem;
and configuring load parameters to the actuator and the load simulation subsystem.
8. A semi-physical verification method for a control algorithm of the aircraft engine full-real source semi-physical simulation system of any one of claims 1 to 5, comprising the following steps:
s1000, creating a controller basic component in a controller simulation subsystem, realizing description, interface relation and function realization of the controller component based on an MATLAB development environment in an S-function programming mode, and realizing construction of an engine control function by the controller;
s2000, building Simulink according to a control algorithm to be verified, and embedding an algorithm module into a basic component module of the controller;
s3000, after the building of the control basic component is completed in the MATLAB/Simulink, compiling the MATLAB Simulink file into a C code and downloading the C code into a controller simulation subsystem for simulation;
s4000, starting each system of the semi-physical simulation platform, selecting a verification experiment, designing target height, target Mach number and state maintaining time in the comprehensive management subsystem, selecting a group of flight envelopes, transmitting flight targets and environment parameters to the controller simulation subsystem through a bus, and simulating the aircraft to fly to the target height and the target Mach number according to certain constraints;
and S5000, transmitting the state parameters of each section of the engine to a control comprehensive management subsystem through a bus, observing the control quality and surge margin parameters of the rotating speed, temperature and pressure parameters measured by an engine sensor, monitoring the control quality and fault tolerance performance of the test in real time, and carrying out evaluation, warning and recording operation to verify the control algorithm.
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