CN-122018364-A - Hardware-in-the-loop test system of aviation hybrid electric propulsion system

CN122018364ACN 122018364 ACN122018364 ACN 122018364ACN-122018364-A

Abstract

The application provides an on-loop test system for hardware of an aviation hybrid electric propulsion system, which belongs to the technical field of aviation hybrid electric propulsion systems and particularly comprises a hardware platform, wherein the hardware platform comprises an operating rod, an instruction analysis computer, a computing board card and a demonstration computer, a hybrid electric propulsion system digital simulation model is deployed on the computing board card, an operating instruction generated by the operating rod is sent to the instruction analysis computer, the instruction analysis computer analyzes the operating instruction and sends the operating instruction to the computing board card, the hybrid electric propulsion system digital simulation model on the computing board card calculates the running state of the hybrid electric propulsion system digital simulation model in real time based on the operating instruction, and generates running parameters, and the computing board card demonstrates by sending the running parameters to the demonstration computer. By the processing scheme, key performances of the energy distribution strategy and the control system can be effectively verified.

Inventors

WU JINGYAO
WANG YE
XIAO BING
LI RUICHAO
QIN ZHENG
JI CHUNSHENG
RONG LI

Assignees

太行国家实验室

Dates

Publication Date: 20260512
Application Date: 20260415

Claims (9)

1. An in-loop test system for an aircraft hybrid electric propulsion system, comprising: The hardware platform comprises a control rod, an instruction analysis computer, a computer board card and a demonstration computer; The hybrid electric propulsion system digital simulation model comprises an energy management sub-model, a turboshaft engine sub-model, a generator sub-model, a battery energy storage sub-model, a direct current bus sub-model, a motor driving sub-model and a ducted fan propulsion sub-model, wherein the hybrid electric propulsion system digital simulation model operates on a computing board, a Simulink model corresponding to the hybrid electric propulsion system digital simulation model is constructed through a MATLAB/Simulink modeling platform, the Simulink model corresponding to the hybrid electric propulsion system digital simulation model is converted into a C language code, and the C language code is deployed on the computing board to realize the operation of the hybrid electric propulsion system digital simulation model on the computing board; The control command generated by the control rod is transmitted to a command analysis computer through a USB, the command analysis computer analyzes the control command and transmits the control command to a computing board card, a digital simulation model of the hybrid electric propulsion system on the computing board card calculates the running state of the digital simulation model of the hybrid electric propulsion system in real time based on the control command and generates running parameters, and the computing board card transmits the running parameters to a demonstration computer through UDP communication; The demonstration computer is used for displaying the operation parameters of the hybrid electric propulsion system digital simulation model, displaying the energy flow and dynamic distribution logic of the hybrid electric propulsion system digital simulation model in different working modes, simulating the complete flight mission profile of the aircraft and displaying real-time flight profile and flight parameter real-time monitoring data and real-time energy distribution data.
2. The system of claim 1, wherein the computing board card comprises two CPU processing nodes and one NPU processing node, the two CPU processing nodes and the one NPU processing node are communicatively connected to each other through a PCIe bus, and the two CPU processing nodes and the one NPU processing node are all configured to implement external data communication through a three-redundancy time triggered ethernet.
3. The on-loop test system of the aviation hybrid electric propulsion system according to claim 1, wherein the energy management sub-model is used for performing simulation calculation and dynamically distributing output power parameters of two generator simulation modules in the generator sub-model and a battery simulation module in the battery energy storage sub-model based on a simulation load demand of the motor driving sub-model, a simulation running state of the direct current bus sub-model and a simulation state of charge of the battery energy storage sub-model, and a parameter set configured by the energy management sub-model comprises a power distribution strategy parameter, upper and lower limit thresholds of the battery state of charge output by the battery energy storage sub-model, energy supply priority coefficients of the generator sub-model and the battery energy storage sub-model and fault redundancy distribution parameters; The turbine shaft engine sub-model is used for responding to a simulation control instruction of the generator sub-model, outputting corresponding rotating speed parameters through a built-in fuel oil regulation simulation module and a speed regulation simulation module, and providing simulation power driving parameters for the generator sub-model, wherein a parameter set configured by the turbine shaft engine sub-model comprises PID parameters of an engine speed regulator, a fuel oil flow-rotating speed mapping relation and an engine maximum rotating speed limiting parameter; The generator sub-model is used for converting the simulation mechanical energy parameters of the turboshaft engine sub-model into alternating current simulation parameters through simulation, and converting the alternating current simulation parameters into direct current simulation electrical parameters through a built-in rectifier simulation module, so as to provide stable simulation direct current power parameters for the direct current bus sub-model, and the parameter set configured by the generator sub-model comprises generator electromagnetic characteristic parameters, stator winding impedance parameters, power factor parameters, generator efficiency curve parameters, rectifier topology parameters, commutation reactance parameters, triggering angle control algorithm parameters, generator electromechanical conversion efficiency and rectifier ripple suppression parameters; The battery energy storage sub-model is used for simulating the storage characteristic of the simulated storage electric energy, a conversion simulation module is arranged in the battery energy storage sub-model, the conversion simulation module is used for realizing the two-way simulation power transmission between the battery energy storage sub-model and the direct current bus sub-model through a simulation DC/DC converter, the conversion simulation module is also used for responding to the charge and discharge instruction of the energy management sub-model and realizing the voltage stability control of the direct current bus sub-model in a simulation manner, and the parameter set configured by the conversion simulation module comprises DC/DC topological structure parameters, DC/DC conversion efficiency curve parameters, duty ratio control algorithm parameters, battery internal resistance characteristic parameters and battery charge and discharge rate limiting parameters; The DC bus sub-model is used for simulating and integrating the DC simulation electric parameters output by the rectifier simulation module and the simulation electric parameters output by the conversion simulation module, and providing unified DC simulation power supply parameters for the motor driving sub-model, and the parameter set configured by the DC bus sub-model comprises bus equivalent impedance parameters, line loss parameters and equalizing control parameters; The motor driving sub-model is used for receiving a simulation power supply signal of the direct current bus sub-model, responding to a control instruction and outputting a simulation mechanical power parameter, driving the ducted fan propulsion sub-model to complete simulation operation, and the parameter set configured by the motor driving sub-model comprises a motor electromagnetic parameter, a speed regulation control algorithm parameter, an efficiency curve parameter, a maximum torque or rotation speed limiting parameter and a stator impedance parameter; the ducted fan propulsion sub-model is used for converting the simulation mechanical power parameters output by the motor driving sub-model into pneumatic thrust simulation parameters to realize simulation reproduction of power output of an aircraft, and the parameter set configured by the ducted fan propulsion sub-model comprises a fan pneumatic characteristic parameter, a blade efficiency parameter, a rotating speed-thrust mapping relation parameter, a maximum thrust limiting parameter and a pneumatic loss function parameter; The energy management submodel, the turboshaft engine submodel, the generator submodel, the battery energy storage submodel, the direct current bus submodel, the motor driving submodel and the ducted fan propulsion submodel are connected through a virtual signal bus interaction link, so that real-time transmission of simulation parameters among the submodels is realized.
4. The hardware-in-the-loop test system of the aviation hybrid electric propulsion system according to claim 3, wherein the instruction analysis computer is provided with an instruction analysis sub-model, the instruction analysis sub-model is used for analyzing the operation instruction of the operating rod into a single control instruction and a total power instruction of a plurality of motor simulation modules in the motor driving sub-model, the input of the instruction analysis sub-model is the operation instruction of the operating rod, a direct current bus voltage value output by the direct current bus sub-model and a state-of-charge simulation feedback parameter output by the battery energy storage sub-model, and the output of the instruction analysis sub-model comprises a rotating speed reference value and a torque reference value of each motor simulation module.
5. The on-loop test system of the aviation hybrid electric propulsion system hardware in claim 1, wherein the method for converting the Simulink model corresponding to the hybrid electric propulsion system digital simulation model into a C-language code and deploying the C-language code on a computing board card to realize the operation of the hybrid electric propulsion system digital simulation model on the computing board card comprises the following steps: performing full-link compliance detection on the Simulink model, and checking algebraic rings, undefined signals and module connection logic error problems by an operation model advisor tool to finish correction; Replacing a module which only supports simulation in the Simulink model with a code generation compatible module compatible with the hardware of the computing board card; Optimizing all signal data types in the Simulink model into numerical types suitable for the computing board based on a hardware architecture of the computing board, configuring simulation step length and solver type of the Simulink model, and matching real-time operation requirements of the computing board; configuring an external interactive interface function and an internal logic interface function of a C language code of a digital simulation model of the hybrid electric propulsion system, defining an entry function of the C language code of the digital simulation model of the hybrid electric propulsion system, and completing mapping of input and output signals to obtain a standardized code frame; configuring C language code generation parameters according to hardware characteristics of a computing board card, starting an automatic code generation function of a MATLAB/Simulink modeling platform to compile a Simulink model, generating an intermediate representation file, and mapping the intermediate representation file into C language codes; performing static analysis on the C language code, detecting code defects in the code, and removing invalid codes to obtain an optimized C language code; The method comprises the steps of connecting a computing board card with a model development computer for developing a digital simulation model of the hybrid electric propulsion system in a communication mode, installing an operating system on the computing board card, configuring SSH service, installing a drive and dependency library on the computing board card, calling a cross compiler through a generated makefile on the model development computer, compiling optimized C language codes into executable files of the computing board card, and transmitting the executable files and the configuration files matched with the executable files to a designated directory of the computing board card through SCP or FTP so as to realize the direct running of programs of the digital simulation model of the hybrid electric propulsion system through commands at a terminal of the computing board card.
6. The on-loop test system of the aviation hybrid electric propulsion system hardware in claim 1, wherein the operation information of the hybrid electric propulsion system digital simulation model displayed by the demonstration computer is used for reflecting the stability of the hybrid electric propulsion system digital simulation model, and parameters and control strategies of the hybrid electric propulsion system digital simulation model are adjusted according to the stability of the hybrid electric propulsion system digital simulation model until the stability of the hybrid electric propulsion system digital simulation model reaches a preset requirement.
7. The on-loop test system of an aircraft hybrid electric propulsion system of claim 1, wherein the demonstration computer comprises an operating parameter management module for displaying operating parameters of the hybrid electric propulsion system digital simulation model, and wherein an interface of the operating parameter management module displays operating parameters of the turboshaft engine, the generator, the motor drive, and the battery energy storage.
8. The on-loop test system of the aviation hybrid electric propulsion system according to claim 1, wherein the demonstration computer comprises an energy distribution management module, the energy distribution management module is used for showing energy flow and dynamic distribution logic of the hybrid electric propulsion system digital simulation model in different working modes, and an interface of the energy distribution management module presents the energy flow and dynamic distribution logic of the hybrid electric propulsion system in four working modes of pure electricity, vortex electricity, hybrid charging and hybrid discharging through a real-time simulation curve, a digital instrument and a visualization structure of the hybrid electric propulsion system.
9. The on-loop test system of the aviation hybrid electric propulsion system according to claim 1, wherein the demonstration computer comprises a flight profile management module, the flight profile management module is used for simulating a complete flight mission profile of an aircraft and displaying real-time flight profile and flight parameter real-time monitoring data and real-time energy distribution data, an interface of the flight profile management module presents a flight height-time profile of each flight stage in a dynamic curve and records the energy parameters of each flight stage, the interface of the flight profile management module also presents aviation instruments for monitoring the flight speed, the flight height and the pitching angle in real time and reproducing the motion gesture, the spatial position and the speed state of each flight stage, and the interface of the flight profile management module also presents propulsion power, generating power and battery power in the form of a histogram and a digital frame and is used for dynamically reflecting the power cooperation of energy distribution in each flight stage.

Description

Hardware-in-the-loop test system of aviation hybrid electric propulsion system Technical Field The application relates to the field of aviation hybrid electric propulsion systems, in particular to an aviation hybrid electric propulsion system hardware-in-the-loop test system. Background The hybrid electric propulsion system is an important development direction of future aviation power systems by virtue of the flexibility of energy management and power output, integrates a plurality of highly coupled subsystems such as turbine power generation, battery energy storage, power transmission and distribution, propulsion systems and the like, relates to a complex control strategy and an energy management algorithm, and needs to fully verify the overall performance, the cooperative characteristics of components and the effectiveness of control logic in the research and development process. The interactive relation between the hardware characteristics and the system architecture is difficult to truly reflect only through digital simulation, and the bench test has the limitations of high cost, long period, high safety risk and the like. Disclosure of Invention In view of the above, the application provides an aviation hybrid electric propulsion system hardware-in-the-loop test system, which solves the problems in the prior art and can efficiently verify the key performances of an energy distribution strategy and a control system. The hardware-in-the-loop test system of the aviation hybrid electric propulsion system provided by the application adopts the following technical scheme: An aircraft hybrid electric propulsion system hardware-in-the-loop test system comprising: The hardware platform comprises a control rod, an instruction analysis computer, a computer board card and a demonstration computer; The hybrid electric propulsion system digital simulation model comprises an energy management sub-model, a turboshaft engine sub-model, a generator sub-model, a battery energy storage sub-model, a direct current bus sub-model, a motor driving sub-model and a ducted fan propulsion sub-model, wherein the hybrid electric propulsion system digital simulation model operates on a computing board, a Simulink model corresponding to the hybrid electric propulsion system digital simulation model is constructed through a MATLAB/Simulink modeling platform, the Simulink model corresponding to the hybrid electric propulsion system digital simulation model is converted into a C language code, and the C language code is deployed on the computing board to realize the operation of the hybrid electric propulsion system digital simulation model on the computing board; The control command generated by the control rod is transmitted to a command analysis computer through a USB, the command analysis computer analyzes the control command and transmits the control command to a computing board card, a digital simulation model of the hybrid electric propulsion system on the computing board card calculates the running state of the digital simulation model of the hybrid electric propulsion system in real time based on the control command and generates running parameters, and the computing board card transmits the running parameters to a demonstration computer through UDP communication; The demonstration computer is used for displaying the operation parameters of the hybrid electric propulsion system digital simulation model, displaying the energy flow and dynamic distribution logic of the hybrid electric propulsion system digital simulation model in different working modes, simulating the complete flight mission profile of the aircraft and displaying real-time flight profile and flight parameter real-time monitoring data and real-time energy distribution data. Optionally, the computing board card includes two CPU processing nodes and one NPU processing node, where the two CPU processing nodes and the one NPU processing node are connected to each other by a PCIe bus, and the two CPU processing nodes and the one NPU processing node are all configured to implement external data communication by triggering an ethernet through three redundancy times. Optionally, the energy management sub-model is used for performing simulation calculation and dynamically distributing output power parameters of two generator simulation modules in the generator sub-model and a battery simulation module in the battery energy storage sub-model based on the simulation load demand of the motor driving sub-model, the simulation running state of the direct current bus sub-model and the simulation state of charge of the battery energy storage sub-model, and the parameter set configured by the energy management sub-model comprises a power distribution strategy parameter, upper and lower limit thresholds of the battery state of charge output by the battery energy storage sub-model, energy supply priority coefficients of the generator sub-model and the battery energy storage sub-mo