CN113934153A - Multi-channel simulation method and system for aircraft engine control system - Google Patents
Multi-channel simulation method and system for aircraft engine control system Download PDFInfo
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Abstract
The invention provides a multi-channel simulation method of an aircraft engine control system, which comprises the following steps: providing a plurality of EEC main programs, wherein each EEC main program is used as a channel and comprises a communication information management component; providing a FADEC simulation program comprising a multi-channel signal management component configured to select a master channel among a plurality of channels; providing a simulation scheduling platform comprising a channel information management component; operating the simulation scheduling platform, loading a plurality of EEC main programs and FADEC simulation programs to a simulation path, and configuring a channel information configuration file to formulate communication protocol configuration among processes; and respectively starting the EEC main program and the FADEC simulation program of a plurality of channels by using the simulation scheduling platform, opening the ground detection monitoring software, and starting the simulation. The invention also provides a multi-channel simulation system of the aircraft engine control system, which is used for realizing the simulation method.
Description
Technical Field
The invention mainly relates to the field of design of an aircraft engine control system, in particular to a multi-channel simulation method and system of the aircraft engine control system.
Background
An Aircraft Engine (Aircraft Engine) is a highly complex and precise thermodynamic machine and is the heart of an Aircraft, and an Aircraft Engine Control System (Control System) is a key factor for ensuring the efficient and stable operation of the heart. The control technology of the aero-engine is an important branch of the aero-engine profession, and it has become a trend to accurately realize the development work of an engine control system, shorten the development period, reduce the research cost and establish a simulation platform with high fidelity and high reliability to improve the development efficiency of the engine control system. An Engine Electronic Controller (EEC) is used as a full-authority digital Engine Controller, the Controller is a dual-channel hot backup Controller, and two identical processors run to complete the same program so as to improve the safety of Engine control. In order to guarantee the safety of the control system of the aero-engine and improve the research and development efficiency of the control system, the establishment of a dual-channel platform of an electronic controller of the aero-engine for simulation analysis design has very important significance.
Full Digital Simulation (Full Digital Simulation) of an aero-engine control system is a key technical means for control system design, but an existing Full Digital Simulation platform of an aero-engine lacks a Double-Channel (Double Channel) Simulation function, and a control algorithm and logic design verification work related to Double-Channel logic need to be verified on an electronic controller in a target code form. In the current verification link, limited by the verification environment, the number of electronic controller devices capable of being used for verification is limited, when the workload is large and a plurality of persons need to work simultaneously, the task time needs to be allocated due to the constraint of device resources, and therefore, the target code verification work needs to be performed in a long time. The defects of the existing simulation means result in that an algorithm designer does not have an effective dual-channel algorithm simulation means in the design stage; the algorithm verification can be carried out only when software integration is completed and a hardware debugging stage is started, so that the research and development efficiency of a control system is influenced; meanwhile, the limited hardware resources can cause resource shortage, thereby causing insufficient verification.
Chinese patent application 201310440242.8 discloses a "rapid prototyping simulation method for an aircraft engine control system", which comprises the steps of firstly establishing a control algorithm model, performing prototyping design on the control system by using a virtual instrument technology and a real-time hardware platform, compiling and downloading the designed aircraft engine control algorithm model to the real-time hardware platform by using an automatic code generation technology, and rapidly establishing a control algorithm prototype; secondly, the rapid control prototype is responsible for collecting output signals of the engine simulator after passing through the signal interface unit, calculating related control quantity of the engine according to the control instruction and sending the related control quantity to the engine simulator, and realizing closed loop control of the engine; and finally, a control system designer observes the control effect in real time through a monitoring computer, continuously modifies the control algorithm model according to the performance requirement of the designer on the control system, and repeats the closed loop simulation process of the rapid control prototype until the requirement of the control system designer is met.
However, this method also has the following significant disadvantages: firstly, the rapid prototype simulation method of the aircraft engine control system cannot realize double-channel simulation, so that double-channel control and algorithm cannot be simulated; secondly, the method only allows a single user to operate each time, and cannot realize simultaneous work of multiple users; thirdly, the simulation method needs at least two hardware devices, and the resource occupation is more.
Disclosure of Invention
In order to solve the technical problems, the invention provides a multi-channel simulation method of an aircraft engine control system, which can realize high-fidelity multi-channel all-digital simulation of the aircraft engine control system, is not limited by verification on a real electronic controller, and obviously improves the research and development efficiency of the aircraft engine control system.
The multichannel simulation method of the aircraft engine control system comprises the following steps:
providing a plurality of EEC main programs, wherein each EEC main program is used as a channel and comprises a communication information management component, the communication information management component is configured to read a channel information configuration file to acquire channel information, and the channel information comprises a channel number of a current channel and communication protocol configuration;
providing a FADEC (Full Authority Digital Electronic Control) simulation program, wherein the FADEC simulation program comprises a multi-channel signal management component and is configured to select a main Control channel among a plurality of channels;
providing a simulation scheduling platform, wherein the simulation scheduling platform comprises a channel information management component, the channel information management component is configured to manage the simulation paths of a plurality of pipelines and a channel information configuration file under the FADEC simulation path so as to formulate the communication protocol configuration among the processes, and each EEC main program, FADEC simulation program and simulation scheduling platform are independent processes;
operating a simulation scheduling platform, loading a plurality of EEC main programs and FADEC simulation programs to a simulation path, and configuring a channel information configuration file to formulate communication protocol configuration among processes; and
and respectively starting the EEC main program and the FADEC simulation program of a plurality of channels by using a simulation scheduling platform, opening the ground detection monitoring software, and starting simulation.
Optionally, in the multi-channel simulation method of the aircraft engine control system according to the present invention, each EEC main program further includes an underlying driver.
Optionally, in the multi-channel simulation method of the aircraft engine control system according to the present invention, the FADEC simulation program further includes an underlying driver simulation program, where the underlying driver and the underlying driver simulation program communicate with each other by way of inter-process communication.
Optionally, in the multi-channel simulation method of an aircraft engine control system according to the present invention, the configuration of the communication protocol of each EEC main program includes: a signal transmission simulation configuration, a simulation configuration of EMU (Engine Monitor Unit) communication, a simulation configuration of airplane communication, and ground inspection communication.
Optionally, in the multi-channel simulation method of the aircraft engine control system according to the present invention, the multi-channel signal management component is configured to select a main control channel among the plurality of channels according to an operation sequence of the plurality of EEC main programs, a manual channel switching instruction of the simulation scheduling platform, or an active channel switching instruction from the EEC main programs.
Optionally, in the multi-Channel simulation method of the aircraft engine control system according to the present invention, the multiple EEC main programs perform CCDL (Cross Channel Data Link) communication interaction through inter-process communication.
The invention also provides a multi-channel simulation system of the aircraft engine control system, which comprises the following components:
each EEC main program is used as a channel and comprises a communication information management component, the communication information management component is configured to read a channel information configuration file to acquire channel information, and the channel information comprises a channel number of a current channel and communication protocol configuration;
a FADEC simulation program comprising a multi-channel signal management component configured to select a master channel among a plurality of channels;
the simulation scheduling platform comprises a channel information management component, wherein the channel information management component is configured to manage simulation paths of a plurality of pipelines and channel information configuration files under FADEC simulation paths so as to formulate communication protocol configuration among processes;
ground detection monitoring software configured to receive ground detection communication content from a plurality of EEC main programs;
wherein each EEC main program, FADEC simulation program, simulation scheduling platform and ground inspection monitoring software are independent processes; when the simulation scheduling platform runs, loading a plurality of EEC main programs and FADEC simulation programs to a simulation path, configuring a channel information configuration file to establish communication protocol configuration among processes, respectively starting the EEC main programs and the FADEC simulation programs of a plurality of channels, opening the monitoring software, and starting simulation.
Optionally, in an embodiment of the multi-channel simulation system of an aircraft engine control system according to the present invention, each EEC main program further includes an underlying driver.
Optionally, in an embodiment of the multi-channel simulation system of the aircraft engine control system according to the present invention, the FADEC simulation program further includes an underlying driver simulation program, wherein the underlying driver and the underlying driver simulation program communicate with each other by way of inter-process communication.
Optionally, in an embodiment of the multi-channel simulation system of an aircraft engine control system according to the present invention, the communication protocol configuration of each EEC main program includes: a signal transmission simulation configuration, an EMU communication simulation configuration, an airplane communication simulation configuration, and an earth-detection communication simulation configuration.
Optionally, in an embodiment of the multi-channel simulation system of the aircraft engine control system according to the present invention, the multi-channel signal management component is configured to select a master channel among the plurality of channels according to a running sequence of the plurality of EEC main programs, a manual channel switching instruction of the simulation scheduling platform, or an active channel switching instruction from the EEC main program.
Optionally, in an embodiment of the multi-channel simulation system of the aircraft engine control system according to the present invention, the plurality of EEC main programs perform CCDL communication interaction through inter-process communication.
In order to solve the above technical problem, the present invention further provides a multi-channel simulation system of an aircraft engine control system, including:
a memory for storing instructions executable by the processor; and
and the processor is used for executing instructions to realize the multi-channel simulation method of the aircraft engine control system.
In order to solve the technical problem, the present invention further provides a computer readable medium storing computer program code, which when executed by a processor implements the above-mentioned multi-channel simulation method of an aircraft engine control system.
Compared with the prior art, the invention constructs a high-fidelity multi-channel all-digital simulation platform of the aero-engine control system in a way of inter-process communication and channel information configuration files, and has the following advantages:
the method skillfully utilizes the inter-process communication mode to simulate the signal flow of the aero-engine control system during actual operation, and can perform a multi-channel simulation test on the aero-engine control system with high fidelity;
by using the simulation method and the simulation system, the simulation verification work of aeroengine control logic, multi-channel control logic and multi-channel redundancy signal voting can be carried out in a full digital environment without being limited to verification on a real electronic controller;
because the simulation can be completed by a single machine, a plurality of persons can simultaneously carry out verification or test work, and the design and development efficiency of the control software of the control system of the aero-engine is obviously improved.
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The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the principle of the invention. In the drawings:
FIG. 1 is a schematic diagram of a multi-channel simulation method and system for an aircraft engine control system according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of the EEC main program of the multi-channel simulation method and system of the aircraft engine control system according to one embodiment of the present invention;
FIG. 3 is a schematic diagram of a FADEC simulation program for a multi-channel simulation method and system for an aircraft engine control system according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a simulation scheduling platform of the multi-channel simulation method and system of the aircraft engine control system according to an embodiment of the invention.
Detailed Description
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings used in the description of the embodiments will be briefly introduced below. It is obvious that the drawings in the following description are only examples or embodiments of the application, from which the application can also be applied to other similar scenarios without inventive effort for a person skilled in the art. Unless otherwise apparent from the context, or otherwise indicated, like reference numbers in the figures refer to the same structure or operation.
As used in this application and the appended claims, the terms "a," "an," "the," and/or "the" are not intended to be inclusive in the singular, but rather are intended to be inclusive in the plural unless the context clearly dictates otherwise. In general, the terms "comprises" and "comprising" merely indicate that steps and elements are included which are explicitly identified, that the steps and elements do not form an exclusive list, and that a method or apparatus may include other steps or elements.
The relative arrangement of the components and steps, the numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present application unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
The use of "first," "further," and "last" etc. in this application is used to describe operations performed according to the methods in embodiments of the present application. It should be understood that the operations described using this term are not necessarily performed exactly in order. Rather, various steps may be processed in reverse order or simultaneously. Meanwhile, other operations are added to or removed from these processes.
Example one
The embodiment of the invention provides a multi-channel simulation method of an aircraft engine control system. Fig. 1 is a schematic diagram of a multi-channel simulation method and system of an aircraft engine control system according to the present invention, that is, a schematic diagram of a multi-channel simulation method of an aircraft engine control system according to an embodiment of the present invention. As shown in fig. 1, the multi-channel simulation method of the aircraft engine control system according to the first embodiment provides two EEC main programs, and provides a FADEC simulation program, a simulation scheduling platform, and a ground inspection monitoring software, so that the full-digital two-channel simulation with high fidelity of the aircraft engine control system can be realized, the investment of manpower and hardware equipment is saved, and the research and development efficiency of the aircraft engine control system is significantly improved.
The principle of the multi-channel simulation method of the aircraft engine control system according to the first embodiment of the present invention is described in detail below with reference to fig. 1. It is understood that the following description is only exemplary, and those skilled in the art can make various changes, such as increasing the number of main programs of the EEC to realize more channel simulation, without departing from the spirit and scope of the present invention, and such various changes are all within the spirit and scope of the present invention.
In this embodiment, as shown in fig. 1, a multi-channel simulation method of an aircraft engine control system according to the present invention includes the following steps. It should be noted that the present invention does not limit the sequence of the following steps, and any modification or change made to the following steps for implementing the multi-channel simulation method of the present invention is within the spirit and scope of the present invention.
First, in the embodiment shown in fig. 1, the steps of the multi-channel simulation method of an aircraft engine control system according to the present invention include providing two EEC main program processes. As described in the background, the Engine Electronic Controller (EEC) is of the dual channel hot standby controller type, the two EEC main program processes in this embodiment are used to simulate the two channels of the dual channel hot standby controller of the aircraft Engine Electronic Controller (EEC), respectively, and are distinguished using two different channel numbers, referred to as the a channel and the B channel in this embodiment, and the two EEC main program processes run identical EEC main programs.
In one embodiment of the present invention, the EEC main program is configured to use an executable file that has already been compiled, such as the exe format.
More specifically, FIG. 2 is a schematic diagram of the EEC main program of the multi-channel simulation method and system for an aircraft engine control system according to an embodiment of the present invention. Referring to fig. 2, a detailed description is given to an EEC main program of a multi-channel simulation method of an aircraft engine control system according to an embodiment.
As shown in fig. 2, configuring each EEC main program includes configuring a communication management component configured to read the channel information configuration file in the same path as the EEC main program to obtain the channel information. The channel information includes the channel number of the current channel and the communication protocol configuration. As indicated by the reference in fig. 1, the channel number in the channel information is a or B, and the communication protocol configuration includes an EMU communication analog configuration, an airplane communication analog configuration, a signal transmission analog configuration, and a ground detection communication analog configuration. The method comprises the steps that two identical EEC main programs are started from different paths when the operation is started, and the initialization stage of the EEC main programs determines to operate in an A channel or B channel mode by identifying channel information with a channel number of A or B in a configuration file under the current path, and is used for simulating an operation mode that an Engine Electronic Controller (EEC) loads the same target file in a double-channel mode and obtains channel information from hardware in the initialization stage.
With continued reference to fig. 2, in an embodiment of the present invention, the configuring of the main program of the EEC in the multi-channel simulation method for an aircraft engine control system according to the present invention further includes configuring an EEC application program to implement all logic functions of the engine control system control software. The EEC application may use all source codes designed by engine control software, or may use a model generation code in a model verification stage, and includes functions such as input signal processing, fault diagnosis, fault processing, main loop control, servo loop control, and output signal management, and also has functions of analysis and package sending such as communication with an EMU, aircraft, and ground inspection.
With continued reference to FIG. 2, in one embodiment of the present invention, the configuration of the main program of the EEC in the multi-channel simulation method for an aircraft engine control system further includes configuring a bottom layer driver to simulate the bottom layer driver of a real electronic controller. In an embodiment of the present invention, the method for configuring the bottom layer driver modifies the original bottom layer driver of the EEC application program, and mainly modifies the bottom layer function originally interacting with the hardware in the EEC application program into software simulation, that is, realizes signal transmission by inter-process communication. After configuration, as shown in fig. 2, the EEC application implements all the logic functions of the engine control system control software, and the EEC application configuration interacts with the bottom driver, which mainly implements the bottom driver that simulates a real electronic controller.
The method for configuring the bottom layer driver completely transplants codes of the EEC application program by modifying the bottom layer driver, so that the simulation of the EEC main program has high confidence level, and the simulation test of high fidelity is realized.
Further, in the embodiment shown in fig. 1, in accordance with the configuration method for the main program of the EEC in the first embodiment, the step of the multi-channel simulation method for the aircraft engine control system according to the present invention further includes providing a FADEC simulation program. In this embodiment, as shown in fig. 1, the method for configuring the FADEC simulation program includes configuring a multi-channel signal management component for implementing a main control channel selection between the a channel and the B channel according to an operation sequence of the EEC main program, a manual channel switching instruction of the simulation scheduling platform, or an active channel switching instruction from the EEC main program.
More specifically, fig. 3 is a schematic diagram of a multi-channel simulation method of an aircraft engine control system and a FADEC simulation program of the system according to an embodiment of the present invention, that is, a schematic diagram of a FADEC simulation program of a multi-channel simulation method of an aircraft engine control system according to an embodiment of the present invention. A configuration method of a FADEC simulation program of the multi-channel simulation method of the aircraft engine control system according to the first embodiment will be described in detail below with reference to fig. 3.
As shown in fig. 3, in the first embodiment, on the basis of configuring the multi-channel signal management component, the configuration of the multi-channel simulation method for the aircraft engine control system to the FADEC simulation program further includes configuring an underlying driver simulation program. The bottom layer driver simulator can communicate with the bottom layer driver in the EEC main program shown in fig. 2 in an inter-process communication manner, so as to realize signal input/output transmission, EMU communication interaction, airplane communication interaction and the like with the EEC main program.
Continuing with fig. 3, in a first embodiment, on the basis of the configuration of the multi-channel signal management component and the underlying driver simulation program, the configuration of the multi-channel simulation method of the aircraft engine control system to the FADEC simulation program further includes configuring an engine model, a sensor model, a signal injection module, an operating state information, a FADEC simulation bus, an EMU communication simulation module, and an aircraft communication module. Wherein:
the configuration of the engine model is a full-state and full-envelope discretization model of the aircraft engine constructed based on static characteristics and dynamic characteristics of various components (such as an air inlet channel, an outer duct, a fan supercharging stage, a high-pressure compressor, a high-pressure turbine, a low-pressure turbine, a fuel control component, a starter and the like) of the engine, and the engine model can be used for receiving control signals formed by selecting interprocess communication data from different channels by the multi-channel signal management component according to the state of a main control channel;
the configuration of the sensor model is that a discretization sensor model is established according to discretization equations of sensors such as an aircraft engine fuel system actuator cylinder, temperature and pressure and the like, so that conversion from physical quantity to sensor values such as a voltage value, a current value, a resistance value and the like is realized;
the signal injection module is configured to receive signal injections from the simulation scheduling platform as shown in fig. 1 and write to the FADEC simulation bus;
the running state information sending module is configured to send the running state of the FADEC simulation program, the running key data and the like to the simulation scheduling platform shown in fig. 1 in an inter-process communication manner;
the FADEC simulation bus is configured to realize data interaction of FADEC simulation programs;
the EMU communication simulation module is configured to receive communication data from the EEC main program, obtain a simulation data packet from the FADEC simulation bus, and send the communication data of the EEC through EMU communication;
the aircraft communication simulation module is configured to receive communication data from the main program of the EEC, obtain a simulation data package from the FADEC simulation bus, and send the communication data of the EEC through aircraft communication.
In one embodiment of the present invention, the configuration FADEC simulation program uses an executable file that has already been compiled, such as the. exe format.
In summary, in view of the above configuration of the FADEC simulation program and with reference to fig. 3, the FADEC simulation program in an embodiment of the present invention operates on the principle that the communication configuration information with the main program of the EEC is obtained from the channel information configuration file during the initialization process. The FADEC simulation program mainly simulates an engine model according to a control signal from an EEC main program, converts a simulation result into an EEC input signal through a sensor model, and sends the EEC input signal to the EEC main program by means of a bus and a bottom layer driving simulation program to realize closed loop. The EMU communication simulation module and the airplane communication simulation module mainly realize communication interaction with an EEC main program, ensure normal operation of the EEC main program, simultaneously receive signal injection from a simulation scheduling platform, and introduce injection signals into a multi-channel simulation system of the aero-engine control system in a bus data changing mode, wherein the signal injection comprises switch quantity input of a fuel control switch and the like, continuous quantity input of an accelerator lever angle and the like, continuous quantity of temperature and pressure and the like, fault data of disconnection and the like.
Further, in light of the above configuration of the EEC main program and the FADEC simulation program in the first embodiment, in the embodiment shown in fig. 1, the step of the multi-channel simulation method of the aircraft engine control system according to the present invention further includes providing a ground fault monitoring software. The ground detection monitoring software is used for realizing the function of receiving ground detection communication from the EEC main program, analyzing the communication content according to the communication protocol among the processes and realizing the real-time human-computer interaction of the ground detection communication data. The ground detection monitoring software also has the function of recording communication data, can realize data playback, data analysis and the like, and is an important detection means related to EEC main program operation in the multi-channel simulation method of the aircraft engine control system.
Further, in light of the above configuration of the EEC main program, the FADEC simulation program, and the ground monitoring software in the first embodiment, in the embodiment shown in fig. 1, the multi-channel simulation method of the aircraft engine control system according to the present invention further includes providing a simulation scheduling platform.
More specifically, fig. 4 is a schematic diagram of a multi-channel simulation method of an aircraft engine control system and a simulation scheduling platform of the system according to the present invention, that is, a schematic diagram of a simulation scheduling platform of a multi-channel simulation method of an aircraft engine control system according to an embodiment of the present invention. Referring to fig. 4, a simulation scheduling platform of a multi-channel simulation method for an aircraft engine control system according to a first embodiment of the present invention is described in detail.
As shown in fig. 4, in a first embodiment, the configuration of the multi-channel simulation method for the aircraft engine control system for the simulation scheduling platform includes configuring a channel information management component, which is specifically configured to manage the simulation path of the a channel, the simulation path of the B channel, and the channel information configuration file under the FADEC simulation path, so as to formulate the inter-process communication protocol configuration. The EEC main program of the channel A, the EEC main program of the channel B, the FADEC simulation program and the simulation scheduling platform are independent processes. Through the simulation scheduling platform, information such as communication modes (such as virtual equipment, UDP, TCP and the like) and communication ports between the main program of the A channel and the main program of the B channel, the main program of the A channel and the FADEC simulation program, and the main program of the B channel and the FADEC simulation program are written into a simulation path of the A channel, a simulation path of the B channel and a channel information configuration file under the FADEC simulation path respectively. When the EEC main program of the channel A, the EEC main program of the channel B and the FADEC simulation program are started, the communication mode and the communication configuration can be determined by reading the channel information configuration files under respective paths so as to realize communication.
In one embodiment, in order to simulate the dual channel communication of an actual Engine Electronic Controller (EEC), the multiple EEC main programs also perform CCDL communication interaction through inter-process communication.
Continuing with fig. 4, in a first embodiment, on the basis of the configuration channel information management component, the configuration of the multi-channel simulation method for the aircraft engine control system to the simulation scheduling platform further includes configuring a program management module, a signal injection module and an operation state monitoring module. Wherein:
configuring the program management module to have a program loading function, loading the compiled EEC main program executable file and the compiled FADEC simulation program executable file to corresponding simulation paths, and respectively placing the EEC main program executable file under the simulation paths of the channel A and the channel B in a mode of not modifying the EEC main program executable file; meanwhile, the program management module is configured to have a program control function, the hardware-like power-on operation can be realized by starting the EEC main program under the simulation path of the channel A, the EEC main program under the simulation path of the channel B and the FADEC simulation program, the hardware-like power-off operation is simulated by closing the process, and the hardware-like reset operation is realized by closing the process and restarting the program;
the signal injection module is configured to inject signals through an interface of the simulation scheduling platform, one signal or a plurality of signals can be injected at a time, and continuous signal input can be carried out by reading a test case;
the running state monitoring module is configured to receive running state information from the FADEC simulation program and display the running state information on a human-computer interaction interface, wherein the running state information can comprise power-on states of an A channel and a B channel, an interprocess communication state, some key engine parameters and the like.
Finally, on the basis of the configuration of the EEC main program, the FADEC simulation program, and the simulation scheduling platform, as shown in fig. 1, the simulation scheduling platform is operated, the EEC main program of the channel a, the EEC main program of the channel B, and the FADEC simulation program are loaded to the corresponding simulation paths, and the corresponding channel information configuration files are configured to formulate the communication protocol configuration between the processes. And then, respectively starting the EEC main program of the channel A, the EEC main program of the channel B and the FADEC simulation program by using a simulation scheduling platform, and opening the ground detection monitoring software to start simulation. And (5) starting to record and detect the monitoring data after all the processes are confirmed to be normal.
When the simulation is executed, the simulation scheduling platform can be started to run in a mode of manually injecting signals or injecting signals through test cases. The EEC main program obtains signal input, EMU communication input and airplane communication input from the FADEC simulation program through interprocess communication, converts the signal input, the EMU communication input and the airplane communication input into input of an EEC application program through a bottom layer driver program, transmits output signals, EMU communication sending content and airplane communication sending content to the FADEC simulation program through the bottom layer driver program and interprocess communication after EEC application program operation, and simultaneously transmits ground inspection observation data to ground inspection monitoring software through ground inspection communication.
After the simulation is finished, closing the EEC main program process of the channel A, the EEC main program process of the channel B and the FADEC simulation program process through the simulation scheduling platform, and finally closing the simulation scheduling platform, thereby finishing the simulation of the multiple channels. After the simulation is finished, the data analysis can be carried out on the recording file of the ground detection monitoring data to determine whether the simulation result is effective.
The method simulates two channels of a dual-channel hot backup controller of an aircraft Engine Electronic Controller (EEC) in a mode of two independent EEC main program processes, and ensures the independence between the two channel programs. In the first embodiment, in each step of the multi-channel simulation method for the aircraft engine control system according to the present invention, the configuration and management of the channel configuration file can effectively implement channel identification, so that the main program of the EEC can confirm, by means of the channel configuration file, which channel of the multiple channels the program runs through; in addition, the configuration of the channel configuration file also formulates the inter-process communication protocol configuration among all components, and skillfully utilizes the inter-process communication mode to simulate the signal flow of the aircraft engine control system during actual operation. Therefore, the multi-channel simulation method of the aero-engine control system can perform multi-channel simulation test on the aero-engine control system with high fidelity, is not limited by verification on a real electronic controller, saves manpower and equipment investment, and remarkably improves the design and development efficiency of control software of the aero-engine control system.
Example two
The second embodiment of the invention provides a multi-channel simulation system of an aircraft engine control system. Fig. 1 is a schematic diagram of a multi-channel simulation system of an aircraft engine control system according to an embodiment of the present invention, that is, a schematic diagram of a multi-channel simulation system of an aircraft engine control system according to a second embodiment of the present invention. As shown in fig. 1, the multi-channel simulation system of the aircraft engine control system according to the second embodiment has two EEC main programs, a FADEC simulation program, a simulation scheduling platform, and a ground inspection monitoring software, and can realize full-digital dual-channel simulation of high fidelity of the aircraft engine control system, thereby saving manpower and hardware equipment investment, and significantly improving the research and development efficiency of the aircraft engine control system.
The principle of the multi-channel simulation system of the aircraft engine control system according to the second embodiment of the present invention will be described in detail with reference to fig. 1. It is understood that the following description is only exemplary, and those skilled in the art can make various changes, such as increasing the number of main programs of the EEC to realize more channel simulation, without departing from the spirit and scope of the present invention, and such various changes are all within the spirit and scope of the present invention.
First, as shown in fig. 1, in the second embodiment, the multi-channel emulation system of the aircraft engine control system includes two EEC main program processes, as described in the background art, the type of the Engine Electronic Controller (EEC) is a dual-channel hot standby controller, the two EEC main program processes in this embodiment are respectively used for simulating two channels of the dual-channel hot standby controller of the aircraft Engine Electronic Controller (EEC), and are distinguished by using two different channel numbers, which are referred to as an a channel and a B channel in this embodiment, and the two EEC main program processes run identical EEC main programs.
As shown in fig. 2, each EEC main program includes a communication management component configured to read the channel information configuration file in the same path as the EEC main program to obtain the channel information. The channel information includes the channel number of the current channel and the communication protocol configuration. As indicated by the reference in fig. 1, the channel number in the channel information is a or B, and the communication protocol configuration includes an EMU communication analog configuration, an airplane communication analog configuration, a signal transmission analog configuration, and a ground detection communication analog configuration.
Referring to fig. 2, in an embodiment of the present invention, the EEC main program of the multi-channel simulation system of the aircraft engine control system further includes a bottom layer driver for simulating the bottom layer driver of the real electronic controller.
More specifically, with regard to the configuration of the main program of the EEC, reference may be made to the configuration of the main program of the EEC in the multi-channel simulation method of the aircraft engine control system according to the first embodiment of the present invention, which is not described herein again.
Further, as shown in fig. 3, the multi-channel simulation system of the aircraft engine control system according to the present invention further includes a FADEC simulation program. As shown in fig. 3, the FADEC simulation program includes a multi-channel signal management component, which is used to implement the selection of the main control channel between the a channel and the B channel according to the running sequence of the EEC main program, the manual channel switching instruction of the simulation scheduling platform, or the active channel switching instruction from the EEC main program.
Referring to fig. 3, in an embodiment of the present invention, the FADEC simulation program of the multi-channel simulation system of the aircraft engine control system further includes a bottom driver simulation program, and the bottom driver simulation program can implement communication with the bottom driver in a process communication manner.
More specifically, with regard to the configuration of the FADEC simulation program, reference may be made to the configuration of the FADEC simulation program in the first embodiment of the multi-channel simulation method of the aircraft engine control system according to the present invention, which is not described herein again.
Further, as shown in fig. 1, the multi-channel simulation system of the aircraft engine control system according to the present invention further includes a ground fault monitoring software. The ground detection monitoring software is used for realizing the function of receiving ground detection communication from the EEC main program, analyzing the communication content according to the communication protocol among the processes and realizing the real-time human-computer interaction of the ground detection communication data. The ground detection monitoring software also has the function of recording communication data, can realize data playback, data analysis and the like, and is an important detection means related to EEC main program operation in the multi-channel simulation method of the aircraft engine control system.
Further, as shown in fig. 4, the multi-channel simulation system of the aircraft engine control system according to the present invention further includes a simulation scheduling platform. As shown in fig. 4, the simulation scheduling platform includes a channel information management component, which is specifically configured to manage the simulation path of the a channel, the simulation path of the B channel, and the channel information configuration file under the FADEC simulation path, so as to formulate the inter-process communication protocol configuration.
More specifically, with regard to the configuration of the simulation scheduling platform, reference may be made to the configuration of the simulation scheduling platform in the first embodiment of the multi-channel simulation method of the aircraft engine control system according to the present invention, which is not described herein again.
More specifically, for operations such as starting simulation, executing simulation, and ending simulation, reference may be made to the related description in the first embodiment of the multi-channel simulation method of an aircraft engine control system of the present invention, and details are not repeated herein.
In an embodiment of the invention, two EEC main programs, a FADCE simulation program, a simulation scheduling platform and ground inspection monitoring software can be run in one computer to form a multi-channel simulation system of an aircraft engine control system. The computer includes a memory and a processor. The memory is used for storing instructions executable by the processor, such as the two EEC main programs, the FADCE simulation program, the simulation scheduling platform and the ground monitoring software. The processor is used for executing instructions to realize the multi-channel simulation method of the aircraft engine control system. In the embodiment of the invention, the computer can be a single computer, so that a plurality of persons can simultaneously carry out verification or test work, and the design and development efficiency of the control software of the control system of the aero-engine is obviously improved.
In an embodiment of the present invention, the multi-channel simulation system of an aircraft engine control system of the present invention further includes a computer readable medium storing computer program code, which when executed by a processor implements the multi-channel simulation method of an aircraft engine control system as described above.
The above is a multi-channel simulation system of an aircraft engine control system according to the second embodiment of the present invention, and the system is provided with two independent EEC main program processes to simulate two channels of a dual-channel hot backup controller of an aircraft Engine Electronic Controller (EEC), so as to ensure independence between the two channel programs. In the second embodiment, in the multi-channel simulation system of an aircraft engine control system according to the present invention, the configuration and management of the channel configuration file can effectively implement channel identification, so that the main program of the EEC can determine, through the channel configuration file, which channel of the multiple channels the program runs through; in addition, the configuration of the channel configuration file also formulates the inter-process communication protocol configuration among all components, and skillfully utilizes the inter-process communication mode to simulate the signal flow of the aircraft engine control system during actual operation. Therefore, the multi-channel simulation system of the aircraft engine control system can perform multi-channel simulation test on the aircraft engine control system with high fidelity, is not limited by verification on a real electronic controller, and saves manpower and equipment investment.
Having thus described the basic concept, it will be apparent to those skilled in the art that the foregoing disclosure is by way of example only, and is not intended to limit the present application. Various modifications, improvements and adaptations to the present application may occur to those skilled in the art, although not explicitly described herein. Such modifications, improvements and adaptations are proposed in the present application and thus fall within the spirit and scope of the exemplary embodiments of the present application.
Also, this application uses specific language to describe embodiments of the application. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
Aspects of the present application may be embodied entirely in hardware, entirely in software (including firmware, resident software, micro-code, etc.) or in a combination of hardware and software. The above hardware or software may be referred to as "data block," module, "" engine, "" unit, "" component, "or" system. The processor may be one or more Application Specific Integrated Circuits (ASICs), Digital Signal Processors (DSPs), digital signal processing devices (DAPDs), Programmable Logic Devices (PLDs), Field Programmable Gate Arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or a combination thereof. Furthermore, aspects of the present application may be represented as a computer product, including computer readable program code, embodied in one or more computer readable media. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disk, floppy disk, magnetic strips … …), optical disks (e.g., Compact Disk (CD), Digital Versatile Disk (DVD) … …), smart cards, and flash memory devices (e.g., card, stick, key drive … …).
The computer readable medium may comprise a propagated data signal with the computer program code embodied therein, for example, on a baseband or as part of a carrier wave. The propagated signal may take any of a variety of forms, including electromagnetic, optical, and the like, or any suitable combination. A computer-readable medium may be any computer-readable medium that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code on a computer readable medium may be propagated over any suitable medium, including radio, electrical cable, fiber optic cable, radio frequency signals, or the like, or any combination of the preceding.
Similarly, it should be noted that in the preceding description of embodiments of the application, various features are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure aiding in the understanding of one or more of the embodiments. This method of disclosure, however, is not intended to require more features than are expressly recited in the claims. Indeed, the embodiments may be characterized as having less than all of the features of a single embodiment disclosed above.
Numerals describing the number of components, attributes, etc. are used in some embodiments, it being understood that such numerals used in the description of the embodiments are modified in some instances by the use of the modifier "about", "approximately" or "substantially". Unless otherwise indicated, "about", "approximately" or "substantially" indicates that the number allows a variation of ± 20%. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximations that may vary depending upon the desired properties of the individual embodiments. In some embodiments, the numerical parameter should take into account the specified significant digits and employ a general digit preserving approach. Notwithstanding that the numerical ranges and parameters setting forth the broad scope of the range are approximations, in the specific examples, such numerical values are set forth as precisely as possible within the scope of the application.
Although the present application has been described with reference to the present specific embodiments, it will be recognized by those skilled in the art that the foregoing embodiments are merely illustrative of the present application and that various changes and substitutions of equivalents may be made without departing from the spirit of the application, and therefore, it is intended that all changes and modifications to the above-described embodiments that come within the spirit of the application fall within the scope of the claims of the application.
Claims (14)
1. A multi-channel simulation method of an aircraft engine control system comprises the following steps:
providing a plurality of EEC main programs, wherein each EEC main program is used as a channel and comprises a communication information management component, the communication information management component is configured to read a channel information configuration file to acquire channel information, and the channel information comprises a channel number of a current channel and communication protocol configuration;
providing a FADEC simulation program comprising a multi-channel signal management component configured to select a master channel among a plurality of channels;
providing a simulation scheduling platform, wherein the simulation scheduling platform comprises a channel information management component, the channel information management component is configured to manage simulation paths of a plurality of channels and channel information configuration files under FADEC simulation paths so as to formulate communication protocol configuration among processes, and each EEC main program, each FADEC simulation program and each simulation scheduling platform are independent processes;
operating the simulation scheduling platform, loading the EEC main programs and the FADEC simulation programs to a simulation path, and configuring the channel information configuration file to formulate communication protocol configuration among processes; and
and respectively starting the EEC main program and the FADEC simulation program of a plurality of channels by using the simulation scheduling platform, opening the ground detection monitoring software, and starting simulation.
2. The method of claim 1 wherein each EEC main program further comprises an underlying driver.
3. The method of claim 2, wherein the FADEC emulator further comprises an underlying driver simulator, wherein the underlying driver and the underlying driver simulator communicate by way of interprocess communication.
4. The method of claim 1, wherein the communication protocol configuration of each EEC main program comprises: a signal transmission simulation configuration, an EMU communication simulation configuration, an airplane communication simulation configuration, and an earth-detection communication simulation configuration.
5. The method of claim 1, wherein the multi-channel signal management component is configured to select a master channel among the plurality of channels according to an order of execution of the plurality of EEC main programs, a manual channel switch instruction of an emulation scheduling platform, or an active channel switch instruction from an EEC main program.
6. The method of claim 1, wherein said plurality of EEC main programs interact for CCDL communications via inter-process communications.
7. A multi-channel simulation system for an aircraft engine control system, comprising:
each EEC main program is used as a channel and comprises a communication information management component, the communication information management component is configured to read a channel information configuration file to acquire channel information, and the channel information comprises a channel number of a current channel and communication protocol configuration;
a FADEC simulation program comprising a multi-channel signal management component configured to select a master channel among a plurality of channels;
the simulation scheduling platform comprises a channel information management component, wherein the channel information management component is configured to manage simulation paths of a plurality of pipelines and channel information configuration files under FADEC simulation paths so as to formulate communication protocol configuration among processes;
ground detection monitoring software configured to receive ground detection communication content from the plurality of EEC main programs;
wherein each EEC main program, the FADEC simulation program, the simulation scheduling platform and the ground inspection monitoring software are independent processes; when the simulation scheduling platform runs, loading the EEC main programs and the FADEC simulation programs to a simulation path, configuring the channel information configuration file to establish communication protocol configuration among processes, respectively starting the EEC main programs and the FADEC simulation programs of the channels, opening the ground inspection monitoring software, and starting simulation.
8. The system of claim 7, wherein each EEC main program further comprises an underlying driver.
9. The system of claim 8, wherein the FADEC emulator further comprises an underlying driver simulator, wherein the underlying driver and the underlying driver simulator communicate by way of interprocess communication.
10. The system of claim 7, wherein the communication protocol configuration of each EEC main program comprises: a signal transmission simulation configuration, an EMU communication simulation configuration, an airplane communication simulation configuration, and an earth-detection communication simulation configuration.
11. The system of claim 7, wherein the multi-channel signal management component is configured to select a master channel among the plurality of channels according to a running order of the plurality of EEC main programs, a manual channel switch instruction of an emulation scheduling platform, or an active channel switch instruction from an EEC main program.
12. The system of claim 11, wherein the plurality of EEC main programs interact with CCDL communications via inter-process communications.
13. A multi-channel simulation system for an aircraft engine control system, comprising:
a memory for storing instructions executable by the processor; and
a processor for executing the instructions to implement the method of any one of claims 1-6.
14. A computer-readable medium having stored thereon computer program code which, when executed by a processor, implements the method of any of claims 1-6.
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