CN112834855B

CN112834855B - Method and system for testing electric actuation system

Info

Publication number: CN112834855B
Application number: CN202110063181.2A
Authority: CN
Inventors: 刘博�; 康元丽; 党利明
Original assignee: Commercial Aircraft Corp of China Ltd; Beijing Aeronautic Science and Technology Research Institute of COMAC
Current assignee: Commercial Aircraft Corp of China Ltd; Beijing Aeronautic Science and Technology Research Institute of COMAC
Priority date: 2021-01-18
Filing date: 2021-01-18
Publication date: 2023-10-27
Anticipated expiration: 2041-01-18
Also published as: CN112834855A

Abstract

The invention discloses a method and a system for testing an electric actuating system. Wherein the method comprises the following steps: acquiring sensor information and sensing data; generating data to be tested according to the sensor information and the sensing data; testing the data to be tested through an electric actuator to generate a test result; and displaying the test result. The invention solves the technical problems that the existing electric actuator test platform is mainly used for verifying the functions and performances of a single electric actuator, and cannot test and verify the functions and performances of an electric actuation system consisting of a plurality of electric actuators or a plurality of types of electric actuators.

Description

Method and system for testing electric actuation system

Technical Field

The invention relates to the field of aviation electricity, in particular to a method and a system for testing an electric actuating system.

Background

The conventional electric actuator test platform is mainly used for verifying the functions and performances of a single electric actuator, and cannot test and verify the functions and performances of an electric actuation system consisting of a plurality of electric actuators or a plurality of types of electric actuators. Meanwhile, the method and the system can be used for more intuitively comparing and analyzing the data of the simulation model of the electric actuation system and the real parts of the electric actuation system, thereby being beneficial to calibrating the simulation model and playing a reference and guiding role in testing the real parts of the electric actuation system.

The existing test platform for the electric actuator is similar to the scheme described in the document 'a dual-channel electromechanical actuating system test device', and most of the test platforms adopt a mode of abutting a tested piece and a loading actuator or passive spring loading. In the aspect of civil aircraft flight control system test, semi-physical simulation is mainly carried out by relying on an iron bird test bed, and the specific scheme is similar to that described in a patent document iron bird test bed, and the performance of a real aircraft flight control system is simulated by building a real-size airframe and wing rack of the model used by an aircraft and a real flight control electronic hardware or other hardware system. The current test verification platform and method for the electric actuating system have less researches and related patents and documents.

The conventional electric actuator test platform is mainly used for verifying the functions and performances of a single electric actuator, and cannot test and verify the functions and performances of an electric actuation system consisting of a plurality of electric actuators or a plurality of types of electric actuators. Meanwhile, the existing test platform mainly adopts a spring loading mode or an actuator opposite-top test mode, and cannot simulate dynamic corresponding characteristics of the electric actuator under the influence of factors such as moment of inertia, pneumatic load, connection rigidity, friction and the like of a control surface in the actual use process.

In view of the above problems, no effective solution has been proposed at present.

Disclosure of Invention

The embodiment of the invention provides a test method and a test system for an electric actuating system, which at least solve the technical problems that the conventional test platform for the electric actuators is mainly used for verifying the functions and performances of single electric actuators and cannot test and verify the functions and performances of the electric actuating system consisting of a plurality of electric actuators or a plurality of types of electric actuators.

According to an aspect of an embodiment of the present invention, there is provided an electric actuation system testing method including: acquiring sensor information and sensing data; generating data to be tested according to the sensor information and the sensing data; testing the data to be tested through an electric actuator to generate a test result; and displaying the test result.

Optionally, before the acquiring the sensor information and the sensing data, the method further includes: and acquiring power supply information of a power supply system.

Optionally, the testing mode for testing the data to be tested by the electric actuator includes one of the following: remote control mode, full digital simulation mode, semi-physical simulation mode.

Optionally, the remote control mode includes: step, frequency response, maximum loading force, maximum load speed and impact test on a power grid under the load condition are matched with the loading platform and the power supply system; the all-digital simulation mode comprises the following steps: simulating and testing limit working conditions; the semi-physical simulation mode comprises the following steps: and (3) performing simulation test under the influence of the inertia, friction and pneumatic load of the real control surface.

According to another aspect of an embodiment of the present invention, there is also provided an electric actuation system test system including: the acquisition module is used for acquiring sensor information and sensing data; the generation module is used for generating data to be tested according to the sensor information and the sensing data; the test module is used for testing the data to be tested through the electric actuator to generate a test result; and the display module is used for displaying the test result.

According to another aspect of the embodiment of the present invention, there is also provided a nonvolatile storage medium, where the nonvolatile storage medium includes a stored program, and when the program runs, the program controls a device in which the nonvolatile storage medium is located to execute an electric actuation system testing method.

According to another aspect of the embodiment of the present application, there is also provided an electronic device including a processor and a memory; the memory stores computer readable instructions, and the processor is configured to execute the computer readable instructions, where the computer readable instructions execute an electrical actuation system testing method when executed.

In the embodiment of the application, the sensor information and the sensing data are acquired; generating data to be tested according to the sensor information and the sensing data; testing the data to be tested through an electric actuator to generate a test result; the mode of displaying the test results solves the technical problems that the existing electric actuator test platform is mainly used for verifying the functions and performances of single electric actuators and cannot test and verify the functions and performances of an electric actuation system consisting of a plurality of electric actuators or a plurality of types of electric actuators.

Drawings

The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application and do not constitute a limitation on the application. In the drawings:

FIG. 1 is a schematic diagram of a test system solution architecture according to an embodiment of the present invention;

FIG. 2 is a schematic diagram of a simulation environment program architecture in accordance with an embodiment of the present invention;

FIG. 3 is a schematic diagram of an electric actuation system configuration, according to an embodiment of the present invention;

FIG. 4 is a schematic diagram of interface management computer software according to an embodiment of the invention;

FIG. 5 is a motion schematic according to an embodiment of the invention;

FIG. 6 is a schematic diagram of a simulation start-up procedure in accordance with an embodiment of the present invention;

FIG. 7 is a flow chart of a method of testing an electrical actuation system according to an embodiment of the present invention;

fig. 8 is a block diagram of an electric actuator system test system according to an embodiment of the present invention.

Detailed Description

In order that those skilled in the art will better understand the present invention, a technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in which it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present invention without making any inventive effort, shall fall within the scope of the present invention.

It should be noted that the terms "first," "second," and the like in the description and the claims of the present invention and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that the embodiments of the invention described herein may be implemented in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.

In accordance with an embodiment of the present invention, there is provided a method embodiment of an electric actuation system test method, it being noted that the steps illustrated in the flowchart of the figures may be performed in a computer system, such as a set of computer executable instructions, and that although a logical sequence is illustrated in the flowchart, in some cases the steps illustrated or described may be performed in a different order than what is illustrated herein.

Example 1

FIG. 7 is a flow chart of a method for testing an electrical actuation system according to an embodiment of the present invention, as shown in FIG. 7, the method comprising the steps of:

step S702, sensor information and sensing data are acquired.

Step S704, generating data to be tested according to the sensor information and the sensing data.

Step S706, the data to be tested is tested through the electric actuator, and a test result is generated.

And step S308, displaying the test result.

Specifically, the embodiment of the invention mainly comprises a digital simulation environment of a flight control system and an electric actuation loading platform. The digital simulation environment of the flight control system comprises a simulation main control computer, a flight simulation computer, an interface management computer, a vision computer, an electric actuation loading platform, a test bed, a typical electric actuator, a power supply system and the like, wherein the electric actuation loading platform comprises a typical electric actuator, a measurement and control computer, an aileron false part, a spoiler false part, a rudder false part and the like. The technical scheme architecture is shown in figure 1. The digital simulation environment of the flight control system is mainly used for simulating and providing typical working condition data of the flight simulation environment of the civil aircraft and the electric actuating system, realizing communication, control and data acquisition with the electric actuator, and realizing loading control of a loading platform and data acquisition of a power supply system. The digital simulation environment architecture of the flight control system is shown in fig. 2.

The simulation main control computer is a control center of the whole closed-loop simulation experiment system and has the functions of hardware management and software management of simulation resources and test resources. Namely: all hardware interfaces and configurations of the full system and the flight control system are completed. The simulation main control computer is responsible for the configuration of a semi-physical simulation test mode, can control the switching between a reference object and a mathematical model, and realizes a plurality of simulation modes; completing management and control of the semi-physical simulation platform, and taking charge of sending semi-physical simulation test instructions, including running, suspending, stopping simulation and the like; the working conditions of various simulation and real-part equipment of the system can be displayed in real time.

The flight simulation computer is the core control unit of the aircraft. Acquiring the current flight state of the aircraft by acquiring signals of sensors (inertial navigation, GPS, altimeter and the like) of the aircraft body; and according to the preset flight path and the current flight state of the aircraft, a control instruction is calculated through a control law module, and the actuating system executes corresponding actions after receiving the control instruction, so that the flight attitude of the aircraft is adjusted, the purpose of changing the flight state of the aircraft is achieved, and the whole flight system forms a closed-loop control system.

Control logic tasks in flight simulation computers include flight control computer models (FCMs), actuator control electronics models (ACE), actuator models, and aircraft ontology models. The flight control computer model is used for stabilizing and controlling the flight attitude and track movement of the aircraft, and calculates control instructions by calculating the preset track and the current flight state of the aircraft and the control law module. The actuator control model is an associated system that connects the flight control computer model and the actuator model. The control instruction of the control lever is received and forwarded to the flight control computer model, then the control instruction output by the flight control computer is received, and the effective instruction is output to the actuator model. The aircraft ontology model comprises a most basic six-degree-of-freedom ontology model and an aircraft environment model. The aircraft environment model comprises models of wind fields, atmospheric density and the like, is used for calculating aerodynamic force, and is converted into hinge moment of each control surface through the aerodynamic force. The actuator model consists of a hydraulic actuator model and 3 types of electric actuator models, and the used models are built in a Matlab/Simulink environment. The interface management computer software is an important part of the test platform, and aims to realize communication among the simulation main control computer, the flight simulation computer and the electric actuation loading platform. In addition, the vision computer program is used for providing a near real flying vision in a flying simulation closed loop test.

In addition, other functions that can be realized by the embodiment of the invention are as follows:

(1) The function and performance of the single actuator can be verified; (2) The function and performance of an electric actuation system consisting of a plurality of actuators or types of actuators can be verified; (3) The data analysis function on the simulation main control computer can be used for comparing the real data of the electric actuator with the simulation model data of the electric actuator, checking the model and improving the simulation degree of the model and the platform. (4) The influence of the electric actuating system on the power supply system under different load working conditions and under different flight envelope task instructions can be verified.

In addition, according to the specific implementation manner of the embodiment of the invention, the platform mainly comprises a digital simulation environment of the flight control system and an electric actuation loading platform. As shown in fig. 1, the digital simulation environment of the flight control system comprises a simulation main control computer, a flight simulation computer, an interface management computer and a vision computer, and the electric actuation loading platform comprises a typical electric actuator, a measurement and control computer, an aileron false part, a spoiler false part, a rudder false part, a test bench, a typical electric actuator, a power supply system and the like. In this patent, a typical electric actuator EMA, EHA, EBHA is taken as an example, and the composition and principle of the test platform are described.

1. The digital simulation environment of the flight control system is mainly used for simulating and providing typical working condition data of the flight simulation environment of the civil aircraft and the electric actuating system, realizing communication, control and data acquisition with the electric actuator, and realizing loading control of a loading platform and data acquisition of a power supply system. The digital simulation environment architecture of the flight control system is shown in fig. 2.

(1) The simulation main control computer is a control center of the whole closed-loop simulation experiment system and has the functions of hardware management and software management of simulation resources and test resources. Namely: all hardware interfaces and configurations of the full system and the flight control system are completed. Meanwhile, the task scheduling and control of each subsystem are guaranteed, and the safety and the rapidness of the test are guaranteed. The simulation main control computer is responsible for the configuration of a semi-physical simulation test mode, can control the switching between a reference object and a mathematical model, realizes multiple simulation modes, completes the management and control of a semi-physical simulation platform, and is responsible for the sending of semi-physical simulation test instructions, including running, suspending, stopping simulation and the like; the data analysis and recording software in the simulation main control computer displays various parameters and information in various data expression forms in the simulation process; and the key flight test data can be recorded by storing the key flight test data into a data file, and the test process playback function driven by the test data is supported. The simulation main control program runs on a general PC, the CPU frequency is not less than 1GHz, four cores and the memory is not less than 2G (32-bit operating system)/4 GB (64-bit operating system); the operating system is a Windows operating system.

(2) The flight simulation computer is the core control unit of the aircraft. Acquiring the current flight state of the aircraft by acquiring signals of sensors (inertial navigation, GPS, altimeter and the like) of the aircraft body; and according to the preset flight path and the current flight state of the aircraft, a control instruction is calculated through a control law module, and the actuating system executes corresponding actions after receiving the control instruction, so that the flight attitude of the aircraft is adjusted, the purpose of changing the flight state of the aircraft is achieved, and the whole flight system forms a closed-loop control system. Control logic tasks in flight simulation computers include flight control computer models (FCMs), actuator control electronics models (ACE), actuator models, and aircraft ontology models. The flight control computer model is used for stabilizing and controlling the flight attitude and track movement of the aircraft, and calculates control instructions by calculating the preset track and the current flight state of the aircraft and the control law module. The actuator control model is an associated system that connects the flight control computer model and the actuator model. The control instruction of the control lever is received and forwarded to the flight control computer model, then the control instruction output by the flight control computer is received, and the effective instruction is output to the actuator model. The actuator control model comprises a mode switch instruction from a simulation main control computer, and the mode switch instruction is used for respectively controlling a full-digital simulation mode, a semi-physical simulation mode and a remote control mode. And in the semi-physical simulation mode, the control surface deflection corresponding to the true displacement of the electric actuator is accessed into a simulation system through an interface management computer to replace corresponding electric actuator model data. And under the remote control mode, the flight control computer model and the electric actuator model are shielded, only the test from the interface management computer to the electric actuator real part is performed, and the state data is fed back to the simulation main control computer in real time to perform state monitoring. The aircraft ontology model comprises a most basic six-degree-of-freedom ontology model and an aircraft environment model. The aircraft environment model comprises wind field, atmospheric density and other models, is used for calculating aerodynamic force, and is converted into hinge moment of each control surface through aerodynamic force, the calculated hinge moment is used for calculating the actuating displacement of the electric actuator model and the deflection of the control surface in a full digital simulation mode, and is output to a measurement and control computer in an electric actuator loading platform through an interface management computer in a semi-physical simulation mode, so as to provide the real load working condition of an electric actuator real part.

As shown in fig. 3, the actuator architecture adopted in the present patent mainly adopts a hydraulic actuator on the main control surface, adopts 2 EHA actuators on the inner side of the inside aileron, adopts 1 EBHA actuator on the upper side of the rudder, and adopts 2 EMA actuators on the No. 5 spoiler and the No. 10 spoiler. The actuator model consists of a hydraulic actuator model and a 3-type electric actuator model, wherein the used models are built in a Matlab/Simulink environment, and an object code generating module of a flight control simulation system is integrated, so that automatic generation of a C code of the Matlab/Simulink module is realized, a GNU compiler is integrated, and x86 and PowerPC series processors are supported.

The control logic in the flight simulation computer in the embodiment of the invention is to convert the steering column control instruction from a sensor to an analog signal, send the analog signal to an actuator control electronic model (ACE), and send the analog signal to a flight control computer model (FCM) through a data bus 485 after the analog signal is shaped and subjected to A/D conversion and the like. Meanwhile, the ACE also receives digital signals from an external sensor in an analog mode and sends the digital signals to the FCM through a 485 bus; the FCM performs CRC integrity check on the received signals, the result is used for control law calculation, the generated control instruction is sent to ACE, the ACE receives the control instruction sent by the FCM, after CRC check is performed, the control instruction is used for calculation of an electric actuator model and calculation of control surface deflection in a full-digital simulation mode, the control instruction is output to a real part controller of each electric actuator through an interface management computer in a semi-physical simulation mode, the electric actuator is controlled to execute the corresponding instruction and drive the control surface to move, and therefore control over the aircraft attitude is achieved, and meanwhile actual displacement data and state information of the electric actuator fed back by the interface management computer are received for flight control law calculation.

(3) The interface management computer, as shown in fig. 4, is an important part of the test platform, and aims to realize communication among the simulation master control computer, the flight simulation computer and the electric actuation loading platform. The interface management computer is communicated with the controller of the 3-class typical electric actuator EMA, EBHA, EHA through an RS485 bus, is communicated with the measurement and control computer in the electric actuation loading platform through a reflection memory module, is communicated with the flight simulation computer and the simulation main control computer through a UDP module, and receives current and voltage signals from an upper computer of the power supply system through UDP. The interface management computer runs on the general PC, the CPU frequency is not less than 2GHz, the four cores and the memory is not less than 4GB; the operating system is a Windows operating system and is provided with a serial port card and a reflective memory card, wherein the data throughput of the serial port card is not less than 2Mbps.

(4) The vision computer, the vision computer program developed in the embodiment of the invention divides the vision display program and the alarm information display program. The visual display program is based on a flight simulator of FlightGear and is used for providing a near-real flight scene in a flight simulation closed-loop test. The alarm information display program is developed by LabWindows, so that the alarm information and flight parameters in the system are displayed, and faults in the system are displayed more intuitively.

2. The electric actuation loading platform comprises a typical electric actuator, a measurement and control computer, an aileron false part, a spoiler false part, a rudder false part, a test bed, a typical electric actuator, a power supply system and the like. In this patent, a typical electric actuator EMA, EHA, EBHA is taken as an example, and the composition and principle of the test platform are described. 2 EHA actuators are adopted at the inner side of the inner aileron, and one of the left aileron and the right aileron is adopted; 1 EBHA actuator is adopted on the upper side of the rudder; on spoiler number 5 and spoiler number 10, 2 EMA actuators were employed.

(1) The measurement and control computer is used for realizing force closed-loop loading control and displacement closed-loop loading control of the control surface; providing load spectrum analysis and calculation software; parameter setting (including load spectrum and PID controller design), instruction real-time calculation, instruction distribution, test monitoring, data processing and display and the like can be performed. The control surface loading force instruction output by the interface management computer is received through communication between the reflective memory module and the interface management computer, meanwhile, the actual deviation measurement data and the loading force actual data of the control surface are input into the interface management computer through the reflective memory bus, and the interface management computer forwards the actual deviation measurement data and the loading force actual data to the flight simulation computer and the simulation main control computer through the network bus.

(2) The control surface false part mainly comprises an aircraft typical control surface aileron, a spoiler and a rudder.

(3) The test bed is used for providing support for the control surface and providing loading force by utilizing the hydraulic actuator to simulate the hinge moment born by the control surface. The dynamic load loading of the aileron under the instruction input of the flight control computer is satisfied, and the closed-loop control of the electric actuating system under the simulated flight state is completed; the motion diagram is shown in fig. 5. The electric actuator is fixed at the position of the driving actuator in the figure, is a linear actuator, pushes the control surface to deflect, and the arm of force is a driving rocker arm. And the hydraulic actuator provides a load force at the location where the hydraulic actuator is mounted to the load actuator.

(4) In the exemplary electric actuator, the exemplary electric actuator EMA, EHA, EBHA is taken as an example in the embodiment of the present invention, where EMA is used for a spoiler, EHA is used for an aileron, and EBHA is used for a rudder. Besides the common configuration, the alternate use of the 3 types of electric actuators can be realized by replacing the base, namely, the EHA is used for a rudder, the EBHA is used for a spoiler and other new configurations, and the EHA is used for verifying the performance of different electric actuators under the condition of being installed on different control surfaces.

(5) The power supply system is used for providing control electricity and power electricity required by the electric actuator, detecting the quality of a power supply, transmitting key information such as current, voltage and the like to the interface management computer in a network mode, and finally transmitting the key information to the simulation main control computer for real-time display and analysis. The power supply system in this example provides 28V dc control power and 270V dc power. The power cable, the control cable and the communication cable of the electric actuator in the example all adopt aviation plugs, so that connection is ensured to be reliable. The platform comprises 3 modes, a remote control mode, a full digital simulation mode and a semi-physical simulation mode. The start-up flow chart is shown in figure 2.

The remote control mode is used for realizing functional performance test of single type electric actuator material object, and the test functions which can be realized include step, frequency response, maximum loading force, maximum load speed, impact test to the power grid under the load condition and the like which are carried out by matching with the loading platform and the power supply system.

The operation flow is to configure the system into a remote control mode through the simulation main control computer, and the control instruction of the electric actuator is sent by the interface management computer. In the mode, the simulation main control computer and the electric actuator, the measurement and control computer and the power supply system which are only transmitted by the interface computer respectively transmit back the state parameters of the actuator, the actual deflection angle of the control surface, the actual loading force data and the current and voltage data, and do not transmit an actuator control instruction to the interface management computer

The full-digital simulation mode is used for simulating the working characteristics of the electric actuating system under a typical flight envelope, and can simulate certain limit working conditions so as to ensure the safety of the real-part test of the electric actuator.

The operation flow is to start the simulation main control computer, the flight simulation computer and the vision computer, the system is configured into an all-digital simulation mode through the simulation main control computer, and a simulation start instruction is sent to the simulation main control computer so as to start the all-digital simulation.

The semi-physical simulation mode is used for testing the working characteristics of the electric actuating system under a typical flight envelope, and can realize the performance simulation of the electric actuating system consisting of EHA, EMA and EBHA adopted in the example under the influence of real control surface inertia, friction and pneumatic load. In the semi-physical simulation mode, the configuration of the electric actuation system adopted by the configuration of the simulation main control computer can be replaced by EMA, EHA, EBHA actuators completely or partially.

As shown in fig. 6, the operation flow of the embodiment of the present invention is to start the simulation host computer, the flight simulation computer, the view computer, the interface management computer, and the electric actuation loading platform. The system is configured into a semi-physical simulation mode through the simulation main control computer, and a simulation starting instruction is sent to the simulation main control computer so as to start the semi-physical simulation mode.

According to the embodiment, as only part of control surface false parts adopting the electric actuators are involved, other control surfaces and actuators are replaced by simulation models, and no additional mechanical structure is adopted, so that the size, cost and development difficulty of the platform are controlled. Compared with the common all-digital simulation, the test method provided by the invention can simulate in a mode of replacing an electric actuator true part, and the recorded data can calibrate an electric actuation system model related in the all-digital simulation, so that the simulation accuracy is improved. The invention mainly expands and discusses according to the architecture, and the designed platform base can be replaced according to the type of the electric actuator, so the test platform is not limited to the configuration.

According to the embodiment of the invention, the test method is established, so that the test from the test of the single electric actuator to the test of the electric actuating system can be performed, and the electric actuating system test platform provided by the invention can complete the switching between full-digital simulation and semi-physical simulation. The invention is different from the iron bird test bed, which is required to be built, only relates to a part of control surface false parts adopting the electric actuator, other control surfaces and actuators are replaced by simulation models, and no additional mechanical structure is adopted, so that the size, cost and development difficulty of the platform are controlled. Compared with the common all-digital simulation, the test method provided by the invention can simulate in a mode of replacing an electric actuator true part, and the recorded data can calibrate an electric actuation system model related in the all-digital simulation, so that the simulation accuracy is improved.

Through the embodiment, the technical problem that the conventional electric actuator test platform is mainly used for verifying the functions and performances of a single electric actuator and cannot test and verify the functions and performances of an electric actuation system consisting of a plurality of electric actuators or a plurality of types of electric actuators is solved.

Example two

FIG. 8 is a block diagram of an electrical actuation system testing system, as shown in FIG. 8, in accordance with an embodiment of the present invention, the method includes the steps of:

An acquisition module 80 for acquiring sensor information and sensing data.

Optionally, the system further comprises: and the power supply module is used for acquiring power supply information of the power supply system.

And the generating module 82 is used for generating data to be tested according to the sensor information and the sensing data.

And the test module 84 is used for testing the data to be tested through the electric actuator to generate a test result.

And the display module 86 is configured to display the test result.

According to another aspect of the embodiment of the present invention, there is also provided an electronic device including a processor and a memory; the memory stores computer readable instructions, and the processor is configured to execute the computer readable instructions, where the computer readable instructions execute an electrical actuation system testing method when executed.

The foregoing embodiment numbers of the present application are merely for the purpose of description, and do not represent the advantages or disadvantages of the embodiments.

In the foregoing embodiments of the present application, the descriptions of the embodiments are emphasized, and for a portion of this disclosure that is not described in detail in this embodiment, reference is made to the related descriptions of other embodiments.

In the several embodiments provided in the present application, it should be understood that the disclosed technology may be implemented in other manners. The above-described embodiments of the apparatus are merely exemplary, and the division of the units, for example, may be a logic function division, and may be implemented in another manner, for example, a plurality of units or components may be combined or may be integrated into another system, or some features may be omitted, or not performed. Alternatively, the coupling or direct coupling or communication connection shown or discussed with each other may be through some interfaces, units or modules, or may be in electrical or other forms.

The units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

In addition, each functional unit in the embodiments of the present invention may be integrated in one processing unit, or each unit may exist alone physically, or two or more units may be integrated in one unit. The integrated units may be implemented in hardware or in software functional units.

The integrated units, if implemented in the form of software functional units and sold or used as stand-alone products, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present invention may be embodied essentially or in part or all of the technical solution or in part in the form of a software product stored in a storage medium, including instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), a removable hard disk, a magnetic disk, or an optical disk, or other various media capable of storing program codes.

The foregoing is merely a preferred embodiment of the present invention and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present invention, which are intended to be comprehended within the scope of the present invention.

Claims

1. A method of testing an electrical actuation system, comprising:

acquiring power supply information of a power supply system;

acquiring sensor information and sensing data;

generating data to be tested according to the sensor information and the sensing data;

testing the data to be tested through an electric actuator to generate a test result;

the test system comprises a digital simulation environment of a flight control system and an electric actuation loading platform;

the digital simulation environment of the flight control system comprises a simulation main control computer, a flight simulation computer, an interface management computer and a vision computer; the system has the main functions of simulating and providing the flight simulation environment of the civil aircraft and typical working condition data of an electric actuating system, realizing communication, control and data acquisition with the electric actuator, and realizing loading control of a loading platform and data acquisition of a power supply system;

the electric actuation loading platform comprises 3 types of typical electric actuators, a measurement and control computer, aileron false parts, spoiler false parts, rudder false parts, a test bench and a power supply system; class 3 typical electrical actuators include EMA, EHA, EBHA;

The test mode comprises one of the following steps: a remote control mode, a full digital simulation mode and a semi-physical simulation mode;

the remote control mode is used for realizing the functional performance test of the true parts of the single type of electric actuator, and comprises the following steps: step, frequency response, maximum loading force, maximum load speed and impact test on a power grid under the load condition are matched with the loading platform and the power supply system; shielding the flight control computer model and the electric actuator model in a remote control mode, and only testing from an interface management computer to an electric actuator real part and feeding back state data to a simulation main control computer in real time for state monitoring;

the all-digital simulation mode is used for simulating the working characteristics of the electric actuating system under a typical flight envelope, and comprises the following steps: simulating and testing limit working conditions; calculating aerodynamic force in a full digital simulation mode, converting the aerodynamic force into hinge moment of each control surface, wherein the calculated hinge moment is used for calculating actuating displacement of an electric actuator model and calculating deflection of the control surface;

the semi-physical simulation mode is used for testing the working characteristics of the electric actuating system under a typical flight envelope, and comprises the following steps: performance simulation test under the influence of real control surface inertia, friction and pneumatic load; under the semi-physical simulation mode, the control surface deflection corresponding to the true displacement of the electric actuator is accessed into the digital simulation environment of the flight control system through an interface management computer to replace corresponding electric actuator model data; calculating aerodynamic force in a semi-physical simulation mode, converting the aerodynamic force into hinge moment of each control surface, wherein the calculated hinge moment is used for being output to a measurement and control computer in an electric actuation loading platform through an interface management computer and used for providing real load working conditions of real parts of an electric actuator;

The adopted actuator architecture is that a hydraulic actuator is mainly adopted on a main control surface, 2 EHA actuators are adopted on the inner side of an inner aileron, 1 EBHA actuator is adopted on the upper side of a rudder, and 2 EMA actuators are adopted on a No. 5 spoiler and a No. 10 spoiler; the alternating use of 3 types of typical electric actuators is realized by replacing the base, and the alternating use is used for verifying the performance of different electric actuators under the condition of being installed on different control surfaces;

the actuator model consists of a hydraulic actuator model and 3 types of typical electric actuator models, and the used models are built in a Matlab/Simulink environment;

and displaying the test result.

2. An electrical actuation system testing system, comprising:

the power supply module is used for acquiring power supply information of the power supply system;

the acquisition module is used for acquiring sensor information and sensing data;

the generation module is used for generating data to be tested according to the sensor information and the sensing data;

the test module is used for testing the data to be tested through the electric actuator to generate a test result; the system specifically comprises a digital simulation environment of a flight control system and an electric actuation loading platform;

And the display module is used for displaying the test result.

3. A non-volatile storage medium comprising a stored program, wherein the program when run controls a device in which the non-volatile storage medium resides to perform the method of claim 1.

4. An electronic device comprising a processor and a memory; the memory has stored therein computer readable instructions for execution by the processor, wherein the computer readable instructions when executed perform the method of claim 1.