CN111290289A - Engine hardware-in-loop simulation system - Google Patents
Engine hardware-in-loop simulation system Download PDFInfo
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- CN111290289A CN111290289A CN201811502759.4A CN201811502759A CN111290289A CN 111290289 A CN111290289 A CN 111290289A CN 201811502759 A CN201811502759 A CN 201811502759A CN 111290289 A CN111290289 A CN 111290289A
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- G05—CONTROLLING; REGULATING
- 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
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Abstract
The invention relates to a system for simulating engine hardware in a loop, which comprises: the flight remote sensing subsystem is connected with an electronic controller, the electronic controller is connected with a data acquisition card, the data acquisition card is connected with an engine simulation model machine, the engine simulation model machine is connected with a visual scene upper computer, and the visual scene upper computer is connected with the engine simulation model machine. In the loop simulation process, the decision plan and the given quantity are input through the flight rocker subsystem, so that the method is more intuitive, is convenient for online adjustment, and can assist researchers to obtain more experience; the flight rocker subsystem is used for one-key switching, so that simulation of all-condition models and fault models is facilitated, operability and demonstration are high, the system is simply and conveniently applied to semi-physical simulation experiments of various engines, repeated design of the system is avoided, and meanwhile test work of new function expansion of the system is greatly simplified.
Description
Technical Field
The invention relates to the field of hardware-in-loop simulation, in particular to an engine hardware-in-loop simulation system.
Background
And a real object is accessed in the simulation system to replace a mathematical model, so that the simulation system is closer to the actual situation and more accurate information is obtained. With the continuous improvement of the performance requirement of the engine, the control law is more and more complex. In the development process of the digital electronic control system of the engine, the semi-physical simulation technology can avoid high energy consumption and high risk existing in the test, the rationality of the control plan logic function and the control rule of the electronic controller of the engine is mainly verified by a hardware-in-loop simulation platform, and a basic verification platform is established for researching the advanced engine multivariable control system. However, the existing simulation platform has certain defects in operability and interactivity.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides an engine hardware-in-loop simulation system.
The technical scheme adopted by the invention for realizing the purpose is as follows:
an engine hardware-in-loop simulation system comprising:
the flight remote sensing subsystem is connected with the electronic controller and sends a task instruction to the electronic controller;
the electronic controller is connected with the flight rocker subsystem and the data acquisition card, receives a task instruction of the flight rocker subsystem, and outputs a digital control signal to the data acquisition card according to the task instruction; receiving the state variable returned by the engine simulation model machine sent by the data acquisition card;
the data acquisition card is connected with the electronic controller and the engine simulation model machine, receives the digital control signal sent by the electronic controller, converts the digital control signal into an analog control signal and sends the analog control signal to the engine simulation model machine; receiving the state variable returned by the engine simulation model machine, digitizing the state variable and sending the state variable to the electronic controller;
the engine simulation model machine is connected with the data acquisition card and the scene upper computer, receives the analog control signal, carries out model simulation and transmits the state variable back to the data acquisition card; all the state variables are sent to a visual upper computer;
and the view upper computer is connected with the engine simulation model machine and is used for monitoring, displaying and storing all state variables.
The electronic controller, the engine simulation model machine and the flight rocker subsystem are in communication connection through UART or UDP.
The electronic controller adopts a Cotex-M4 chip as a main control chip, adopts three sets of power supplies to access an external power supply, namely an adjustable voltage power supply circuit, an isolation power supply circuit and an LDO power supply circuit, the output ends of the isolation power supply circuit and the LDO power supply circuit are connected with a switching value circuit, the switching value circuit performs voltage conversion and drive enhancement on a switching signal, and the output end of the switching value circuit is connected with the main control chip; the output end of the adjustable voltage power supply circuit is connected with the main control chip; the output end of the main control chip is connected with the output port.
The adjustable voltage power supply circuit includes: the power supply end is connected with a transient diode, a patch Schottky diode and an isolation capacitor to form a gate-type circuit, the gate-type circuit is connected with an input port of an LM2596 chip through a fuse, an output end of the LM2596 chip outputs adjustable voltage after being grounded through a filter capacitor and an inductor, and other ports of the chip are grounded.
The isolated power supply circuit includes: the power supply end is connected with the filter capacitor and the inductor through the fuse, the filter capacitor and the inductor are connected with the input end of the CE9908 chip, the 0V output end of the CE9908 chip is grounded through the filter capacitor, the 0V output end of the CE9908 chip is connected with the input negative end through the filter capacitor, and the isolation voltage output end of the CE9908 chip is grounded through the light-emitting isolation diode and outputs voltage.
The LDO power supply circuit includes: the power supply end is connected with an input port of the AMS1117 chip, an output port of the AMS1117 chip outputs isolated adjustable voltage through the voltage-regulating resistor and the filter capacitor parallel circuit, a blending end of the AMS1117 chip is connected to the voltage-regulating resistor, and an output end and an input end of the AMS1117 chip are connected through a protection diode.
The switching value circuit includes: the input end of the TXS0108 chip receives an external digital switching signal and transmits the external digital switching signal to the main control chip through the output end of the TXS0108 chip, and the enabling end of the TXS0108 chip is grounded through the isolation capacitor.
The engine simulation model machine is a computer loaded with an engine simulation model.
The invention has the following beneficial effects and advantages:
1. the electronic controller, the simulation model machine and the flight rocker subsystem can communicate through a serial port or UDP (user Datagram protocol), so that an online/offline simulation experiment can be realized;
2. in the loop simulation process, a decision plan and a given quantity are input through a flight rocker subsystem, so that the method is more intuitive, is convenient for online adjustment, and can assist researchers to obtain more experience;
3. the simulation model is switched by one key through the flight rocker subsystem, so that the simulation of the full-working-condition model and the fault model is facilitated.
Drawings
FIG. 1 is a block diagram of the system of the present invention;
FIG. 2 is a block diagram of the electronic controller of the present invention;
FIG. 3 is a circuit diagram of the adjustable voltage power supply of the present invention;
FIG. 4 is an isolated power supply circuit diagram of the present invention;
FIG. 5 is a circuit diagram of the LDO power supply of the present invention;
fig. 6 is a diagram of a switching value conversion enhancement circuit of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein, but rather should be construed as modified in the spirit and scope of the present invention as set forth in the appended claims.
It will be understood that when an element is referred to as being "disposed on" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention.
FIG. 1 is a block diagram of the system of the present invention;
the engine hardware is at return circuit simulation system, includes: simulation host computer, view host computer, flight rocker subsystem, data acquisition card, electronic controller and engine simulation model machine, wherein:
and the simulation upper computer is used for downloading the established engine model and control algorithm into the engine simulation model machine and the electronic controller through MATLAB-simulink.
The view upper computer is in communication connection with the engine simulation model machine, provides a monitoring means and a man-machine interaction function and is used for monitoring the running state and the health state of the engine, performing on-line management on the working tasks of the engine, switching the working modes of the engine and displaying the current condition of the engine in real time by combining a schematic diagram.
The engine simulation model machine is stored with a dynamic model of the engine, is connected with the electronic controller, and is used for resolving in real time according to the engine dynamic model and generating a series of virtual sensor equipment signals, so that the autonomous closed-loop control of the flying robot is realized, and the communication work with the visual upper computer is completed.
And the electronic controller is connected with the flight rocker subsystem and the data acquisition card and is used for receiving the virtual sensor equipment signal sent by the engine simulation model computer and sending an execution throttle control signal obtained after the control algorithm calculation to the engine simulation model machine.
The flight rocker subsystem uses a Rotwitch X52HOTAS flight rocker, and sends an instruction to the electronic controller through a UART (universal asynchronous receiver/transmitter), so that the switching of the functions of the engine is realized, the working state of the engine is changed, and different tasks are completed. The flight rocker is connected with the PC through the UART.
And the data acquisition card is used for converting the virtual sensor equipment signal generated by the engine simulation model computer into a digital signal and sending the digital signal to the electronic controller.
The emulation host computer includes: the system comprises a nonlinear model, a variable parameter model and a controller, and can be downloaded to an engine simulation model machine and an electronic controller through an MATLAB-simulink key;
establishing a nonlinear model based on a mechanism model, acquiring parameters of a core machine by a two-dimensional interpolation method, and calculating a common working point by combining an N-R method;
the variable parameter model is developed based on the balanced manifold, a full envelope variable parameter model is established, and a large deviation model can be established for large dynamic simulation;
the controller comprises multivariable protection logic and logic limit based on the pressure, temperature and the like of the gas compressor, the combustion chamber, the turbine and the tail nozzle, and abnormal working conditions are avoided.
The engine simulation model machine can output virtual sensor variables, and the virtual sensor variables comprise: temperature, pressure, flow and health parameters of the fan, the compressor, the combustion chamber, the turbine, the duct and the tail nozzle.
The view upper computer is connected with the engine simulation model machine through a UART/UDP protocol, and can perform start-stop operation and initial working condition setting and switching on the engine simulation model machine.
Fig. 2 is a block diagram of the electronic controller according to the present invention.
The electronic controller includes:
the controller adopts a chip of Cotex-M4 as a main control chip. Three sets of power supplies are adopted for supplying power and respectively comprise an adjustable voltage power supply circuit, an isolation power supply circuit and an LDO power supply circuit. The adjustable voltage power supply circuit adopts 10V power supply output mainly comprising LM2596, the isolation power supply circuit is 5V power supply output with isolation, and the LDO power supply circuit is 3.3V power supply output consisting of LDO. Three sets of power supplies are used to power different devices on the controller. Electrostatic protection and reverse connection and overcurrent protection are designed at the input part of the controller. The sensor interface circuit sets the self-healing fuse according to the sensor characteristics. The acquisition interface part is provided with a corresponding voltage clamp to prevent possible damage to the main control chip. The switching value part designs the voltage conversion and driving enhancement based on TXS 0108.
The 10V power supply with the LM2596 as the main output is provided with an isolated 5V power supply output and a 3.3V power supply output consisting of LDOs. Three sets of power supplies are used to power different devices on the controller. Electrostatic protection and reverse connection and overcurrent protection are designed at the input part of the controller.
RS422 communication interface to exchange information with the host. The software control system of the electronic controller is written by SIMULINK, and the SIMULINK control program can be downloaded to the hardware of the electronic controller by one key by combining with the RTW code generation technology and the cross compiling technology.
The flight-stick subsystem includes one set of variable-range slide inputs, 0/1 command inputs 16.
The data acquisition card comprises 10 paths of 0-10V/12 bit AD/DA conversion, and carries out filtering and analysis pretreatment on the data.
The working process is as follows:
1) initializing a communication mode and a port number;
2) loading a model of the engine simulation model;
3) loading an algorithm controlled by an electronic controller;
4) starting simulation;
5) the engine simulation model machine receives the input signal, generates virtual sensor information and transmits the virtual sensor information to the electronic controller through the data acquisition card;
6) the engine simulation model machine receives the input signal, generates virtual sensor information and sends the virtual sensor information to the view upper computer through a UART (universal asynchronous receiver/transmitter);
7) the electronic controller receives variable information and flight rocker subsystem input, calculates the controlled variable and outputs multiple controlled variables;
8) and sending information such as control data and health parameters to a visual upper computer and storing the information to the local.
Fig. 3 is a circuit diagram of the adjustable voltage power supply of the present invention.
The adjustable voltage power circuit comprises an LM2596 chip, a transient diode, a patch Schottky diode, an isolation capacitor, a fuse, a filter capacitor and an inductor, wherein a power supply end is connected with the transient diode, the patch Schottky diode and the isolation capacitor to form a gate-shaped circuit, the gate-shaped circuit is connected with an input port of the LM2596 chip through the fuse, the output end of the chip outputs adjustable voltage after being grounded through the filter capacitor and the inductor, and other ports of the chip are grounded
The transient diode, the Schottky diode and the isolation capacitor form a gate-type circuit, when an external power supply end is powered on or powered off, the transient diode absorbs surge power, the voltage transformation module and a relatively small fuse are prevented from being too quickly lost, and in the process of stable work, the transient diode is blocked and the Schottky diode is conducted. The isolation capacitor, the filter capacitor and the filter inductor play a role in isolating, shielding and resisting interference. The output voltage can be adjusted by changing the proportion of the resistors R1 and R2. The fuse connected to the chip input terminal plays a role of protecting the chip.
Fig. 4 is an isolated power supply circuit diagram of the present invention.
The isolation power supply circuit comprises a CE9908 chip, a fuse, a filter capacitor, a filter inductor, an adaptive resistor and a light-emitting isolation diode, a power supply end is connected with the filter capacitor and the inductor through the fuse, the filter capacitor and the inductor are connected and connected with a chip input end, a 0V output end of the chip is grounded through the filter capacitor, a 0V output end of the chip is connected with an input negative end through the filter capacitor, and an isolation voltage output end of the chip is grounded and outputs voltage through the light-emitting isolation diode.
An isolation capacitor is arranged between the input end and the output end of the chip, so that the influence of voltage fluctuation of the power supply end on the main control chip is avoided, and logic dislocation is avoided. The output end light emitting diode and the adaptive resistor can monitor the working condition of the isolation circuit.
FIG. 5 is a circuit diagram of the LDO power supply of the present invention.
The LDO power supply circuit comprises an AMS1117 chip, a voltage regulating resistor, a filter capacitor and a protection diode, wherein an input port of the AMS1117 chip is provided, an output port of the AMS1117 chip is connected with the ground output of the filter capacitor parallel circuit through the voltage regulating resistor to isolate adjustable voltage, a regulating end of the AMS1117 chip is connected to the voltage regulating resistor, and an output end and an input end of the AMS1117 chip are connected through the protection diode.
Through changing the proportion of R1 and R2, regulate and control output voltage to the high-efficient low-voltage power supply demand of parts such as adaptation main control chip and external timer, the diode between chip input and output can avoid the short circuit when chip port direct ground connection and capacitance fault, and other parts of protection circuit avoid overcurrent breakdown, burn out.
Fig. 6 is a diagram of a switching value conversion enhancement circuit of the present invention.
The switching value conversion enhancing circuit comprises a TXS0108 chip and an isolation capacitor, wherein the input end of the chip receives an external digital switching signal and sends the external digital switching signal into the main control chip through the output end of the chip, and the enabling end of the chip is grounded through the isolation capacitor.
The digital value and the switching value are separated and converted through TXS0108 and are subjected to signal enhancement, the safety of the main control chip is guaranteed while signal isolation is achieved, and when an external circuit breaks down, the main controller is protected from short circuit.
Claims (8)
1. An engine hardware-in-loop simulation system, comprising:
the flight remote sensing subsystem is connected with the electronic controller and sends a task instruction to the electronic controller;
the electronic controller is connected with the flight rocker subsystem and the data acquisition card, receives a task instruction of the flight rocker subsystem, and outputs a digital control signal to the data acquisition card according to the task instruction; receiving the state variable returned by the engine simulation model machine sent by the data acquisition card;
the data acquisition card is connected with the electronic controller and the engine simulation model machine, receives the digital control signal sent by the electronic controller, converts the digital control signal into an analog control signal and sends the analog control signal to the engine simulation model machine; receiving the state variable returned by the engine simulation model machine, digitizing the state variable and sending the state variable to the electronic controller;
the engine simulation model machine is connected with the data acquisition card and the scene upper computer, receives the analog control signal, carries out model simulation and transmits the state variable back to the data acquisition card; all the state variables are sent to a visual upper computer;
and the view upper computer is connected with the engine simulation model machine and is used for monitoring, displaying and storing all state variables.
2. The engine hardware-in-loop simulation system of claim 1, wherein: the electronic controller, the engine simulation model machine and the flight rocker subsystem are in communication connection through UART or UDP.
3. The engine hardware-in-loop simulation system according to claim 1 or 2, wherein: the electronic controller adopts a Cotex-M4 chip as a main control chip, adopts three sets of power supplies to access an external power supply, namely an adjustable voltage power supply circuit, an isolation power supply circuit and an LDO power supply circuit, the output ends of the isolation power supply circuit and the LDO power supply circuit are connected with a switching value circuit, the switching value circuit performs voltage conversion and drive enhancement on a switching signal, and the output end of the switching value circuit is connected with the main control chip; the output end of the adjustable voltage power supply circuit is connected with the main control chip; the output end of the main control chip is connected with the output port.
4. The engine hardware-in-loop simulation system of claim 3, wherein: the adjustable voltage power supply circuit includes: the power supply end is connected with a transient diode, a patch Schottky diode and an isolation capacitor to form a gate-type circuit, the gate-type circuit is connected with an input port of an LM2596 chip through a fuse, an output end of the LM2596 chip outputs adjustable voltage after being grounded through a filter capacitor and an inductor, and other ports of the chip are grounded.
5. The engine hardware-in-loop simulation system of claim 3, wherein: the isolated power supply circuit includes: the power supply end is connected with the filter capacitor and the inductor through the fuse, the filter capacitor and the inductor are connected with the input end of the CE9908 chip, the 0V output end of the CE9908 chip is grounded through the filter capacitor, the 0V output end of the CE9908 chip is connected with the input negative end through the filter capacitor, and the isolation voltage output end of the CE9908 chip is grounded through the light-emitting isolation diode and outputs voltage.
6. The engine hardware-in-loop simulation system of claim 3, wherein: the LDO power supply circuit includes: the power supply end is connected with an input port of the AMS1117 chip, an output port of the AMS1117 chip outputs isolated adjustable voltage through the voltage-regulating resistor and the filter capacitor parallel circuit, a blending end of the AMS1117 chip is connected to the voltage-regulating resistor, and an output end and an input end of the AMS1117 chip are connected through a protection diode.
7. The engine hardware-in-loop simulation system of claim 3, wherein: the switching value circuit includes: the input end of the TXS0108 chip receives an external digital switching signal and transmits the external digital switching signal to the main control chip through the output end of the TXS0108 chip, and the enabling end of the TXS0108 chip is grounded through the isolation capacitor.
8. The engine hardware-in-loop simulation system of claim 1, wherein: the engine simulation model machine is a computer loaded with an engine simulation model.
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| CN201811502759.4A CN111290289A (en) | 2018-12-10 | 2018-12-10 | Engine hardware-in-loop simulation system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114326442A (en) * | 2022-01-06 | 2022-04-12 | 中国航发贵阳发动机设计研究所 | Universal engine control rule test verification platform framework |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114326442A (en) * | 2022-01-06 | 2022-04-12 | 中国航发贵阳发动机设计研究所 | Universal engine control rule test verification platform framework |
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