Semi-physical simulation system of aero-engine thrust reversing system

Abstract

The invention discloses a semi-physical simulation system of an aero-engine thrust reverser system. The semi-physical simulation system comprises a real-time simulation platform, a thrust reverser component integration platform, an engine controller and a thrust reverser controller. Wherein the real-time simulation platform simulates the running state of the aero-engine through an integrated real-time simulation model and a hardware input and output model. The thrust reverser component integration platform simulates the actuation state of the thrust reverser system in the semi-physical simulation environment through the integrated thrust reverser component simulation model. The engine controller is connected with the real-time simulation platform and the aero-engine, and the real-time simulation platform issues simulation operation information of the aero-engine to the aero-engine through the engine controller connected with the real-time simulation platform. The reverse thrust controller is respectively connected with the real-time simulation platform and the reverse thrust component integration platform, and the real-time simulation platform obtains simulation reverse thrust information from the reverse thrust component integration platform through the reverse thrust controller connected with the real-time simulation platform and transmits the simulation reverse thrust information to the engine controller to verify the function of the reverse thrust system.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aero-engine simulation, in particular to a semi-physical simulation system of an aero-engine reverse thrust system. BACKGROUND

[0002] The aero-engine reverse thrust system is an important device for aircraft landing deceleration. For a large-bypass-ratio turbofan engine, the reverse thrust system is arranged with a reverse thrust mechanism in the nacelle to change the direction of the outer bypass airflow, so that the direction of the airflow is opposite to the direction of the engine thrust, thereby decelerating the aircraft.

[0003] The reverse thrust device of the engine involves structural coupling between the interface with the aircraft engine and control logic coupling. The controller of the reverse thrust system jointly controls the deployment and stowage of the reverse thrust system with the engine controller and the aircraft controller. The control logic is complex, and therefore a complex full-loop simulation environment needs to be developed to verify the function and component matching of the reverse thrust control system.

[0004] The prior art only involves fluid simulation and power simulation of the reverse thrust device, or only involves mechanical design of the reverse thrust component, and does not involve control system simulation and semi-physical simulation of the reverse thrust system, which cannot meet the verification requirements of the function and component matching of the reverse thrust controller system, thereby affecting the research and development of the aero-engine. SUMMARY

[0005] The following presents a simplified summary of one or more aspects in order to provide a basic understanding of such aspects. This summary is not an extensive overview of all contemplated aspects, and is intended to neither identify key or critical elements of all aspects nor delineate the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed description that is presented later.

[0006] The present application aims to solve the above problems, and provides a semi-physical simulation system of an aero-engine reverse thrust system, which is used to simulate the aerodynamic load of the reverse thrust system under various states of the engine, thereby being applied to semi-physical simulation tests of the aero-engine reverse thrust system.

[0007] The technical scheme of the present application is as follows:

[0008] The present application provides a semi-physical simulation system of an aero-engine reverse thrust system, comprising: a real-time simulation platform, a reverse thrust component integration platform, an engine controller, and a reverse thrust controller; wherein,

[0009] The real-time simulation platform comprises a real-time simulation model of the aero-engine and a hardware input-output model, and the running state of the aero-engine is simulated by the integrated real-time simulation model and hardware input-output model;

[0010] The reverse thrust component integration platform integrates a reverse thrust component simulation model of a reverse thrust system, and the actuation state of the reverse thrust system in a semi-physical simulation environment is simulated through the integrated reverse thrust component simulation model;

[0011] The engine controller is connected with the real-time simulation platform and the aero-engine respectively, the real-time simulation platform sends the simulation running information of the aero-engine to the aero-engine through the engine controller connected therewith, so that the aero-engine runs based on the simulation running information;

[0012] The reverse thrust controller is connected with the real-time simulation platform and the reverse thrust component integration platform respectively, the real-time simulation platform obtains the simulated reverse thrust information from the reverse thrust component integration platform through the reverse thrust controller connected therewith, and transmits the simulated reverse thrust information to the engine controller to verify the function of the aero-engine reverse thrust system.

[0013] According to the embodiment of the semi-physical simulation system of the aero-engine reverse thrust system, the real-time simulation model includes an engine model, an aircraft model and a communication model; wherein,

[0014] The engine model is used for simulating the running state of each component of the aero-engine, and transmits the running state simulation data to the engine controller through the communication model connected therewith;

[0015] The aircraft model is used for simulating the running operation of the aero-engine, and transmits the running operation simulation data to the engine controller through the communication model connected therewith;

[0016] The communication model includes a sensor interface, a communication interface and a switching value output interface, the running state simulation data of the engine model and the running operation simulation data of the aircraft model are read through the set sensor interface, the communication interface and the switching value output interface, and are transmitted to the engine controller to control the running of the aero-engine.

[0017] According to the embodiment of the semi-physical simulation system of the aero-engine reverse thrust system, the hardware input and output model includes a sensor signal board card model, a communication board card model and a switching value board card model; wherein,

[0018] The sensor board card model is connected with the real-time simulation model, and simulates the sensor signal of the engine according to the real-time state information of the engine transmitted by the real-time simulation model;

[0019] The communication board card model is connected with the reverse thrust controller and the engine controller respectively, and the reverse thrust signal data of the reverse thrust controller is transmitted to the engine controller through the built-in board card covering the communication protocol of the engine;

[0020] The digital output board model includes a digital input board and a digital output board. The built-in digital input board receives digital signals from the controller, and the digital output board simulates various digital signals output by the real-time simulation model.

[0021] According to an embodiment of the semi-physical simulation system of the aero-engine thrust reverser system of the present invention, the hardware input / output model further includes a signal simulation board model for receiving signals output by the engine model; wherein, the signal simulation board includes an electro-hydraulic servo valve simulation board, which collects the current signal emitted by the engine controller and converts the current signal into a digital quantity and transmits it to the engine model.

[0022] According to an embodiment of the semi-physical simulation system for an aero-engine thrust reverser system of the present invention, the thrust reverser component integration platform includes a hydraulic oil source, an isolation controller, a directional controller, and a thrust reverser actuator; wherein...

[0023] The hydraulic oil source is connected to the isolation controller, and oil is supplied to the direction controller through the isolation controller, thereby providing hydraulic power to the thrust reverser integration platform;

[0024] The isolation controller is connected to the hydraulic oil source and the directional controller respectively, and isolates the hydraulic oil source from the downstream thrust reverser through the isolation controller;

[0025] The directional controller is connected to both the thrust reverser controller and the thrust reverser actuator. After receiving the thrust reverser control signal from the thrust reverser controller, the directional controller pumps hydraulic oil into the thrust reverser actuator, thereby controlling the thrust reverser actuator to perform the thrust reverser operation.

[0026] According to an embodiment of the semi-physical simulation system of the aero-engine thrust reverser system of the present invention, the thrust reverser component integration platform further includes a thrust reverser defense component; wherein, the thrust reverser defense component includes a third defense lock solenoid valve and a third defense lock actuator, for locking the thrust reverser operation of the thrust reverser system, thereby preventing the thrust reverser system from being accidentally opened in a non-command state.

[0027] According to an embodiment of the semi-physical simulation system for an aero-engine thrust reverser system of the present invention, the engine controller includes an engine control module, an engine status acquisition module, and an engine communication module; wherein...

[0028] The engine control module is used to perform high-pressure speed control, fuel flow control, and engine status control of aero engines.

[0029] The engine status acquisition module is used to collect status information of various sections of the aero-engine.

[0030] The engine communication module is used to enable communication between the aero engine and the aircraft and thrust reverser controller.

[0031] According to an embodiment of the semi-physical simulation system for an aero-engine thrust reverser system of the present invention, the thrust reverser controller includes a thrust reverser control module, a thrust reverser acquisition module, and a thrust reverser communication module; wherein...

[0032] The thrust reverser control module is used to control the deployment and retraction of the thrust reverser system.

[0033] The backpropagation acquisition module is used to acquire proximity switch signals from various components of the backpropagation system.

[0034] The thrust reverser communication module is used to enable communication between the thrust reverser component integration platform and the aircraft and aero-engine.

[0035] The present invention also provides a computer-readable medium storing a semi-physical simulation system of an aero-engine thrust reverser system as described above, wherein the computer-readable medium, when executed, implements the system functions as described above.

[0036] The present invention also provides a semi-physical simulation device for an aero-engine thrust reverser system, comprising:

[0037] Memory, used to store instructions that can be executed by a processor; and

[0038] A processor is used to execute the instructions to implement the functions of the semi-physical simulation system of the aero-engine thrust reverser system as described above.

[0039] Compared with existing technologies, this invention offers the following advantages: For the simulation of aero-engine thrust reverser systems, this invention establishes a high-confidence aero-engine environment, including a time-based simulation platform, a thrust reverser component integration platform, an engine controller, and a thrust reverser controller, to simulate the thrust reverser's actuation state. Through this invention, a hydraulic control system can be used to simulate the actuation load of the aero-engine thrust reverser system, thereby simulating the aerodynamic loads under various engine conditions. This provides data support for researchers in verifying the functionality and component compatibility of the thrust reverser controller system, improving the efficiency of aero-engine development. Attached Figure Description

[0040] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0041] Figure 1 This is a system architecture diagram illustrating an embodiment of the semi-physical simulation system for the aero-engine thrust reverser system of the present invention.

[0042] Figure 2This is a data flow diagram illustrating an embodiment of a semi-physical simulation system for an aero-engine thrust reverser system according to the present invention. Detailed Implementation

[0043] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are merely some examples or embodiments of this application. For those skilled in the art, these drawings can be applied to other similar scenarios without creative effort. Unless obvious from the context or otherwise specified, the same reference numerals in the drawings represent the same structures or operations.

[0044] As indicated in this application and claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not specifically singular and may include plural forms. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0045] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of this application. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following drawings denote similar items; therefore, once an item is defined in one drawing, it need not be further discussed in subsequent drawings.

[0046] In detailing the embodiments of the present invention, for ease of explanation, the cross-sectional views illustrating the device structure will be partially enlarged and not to scale. Furthermore, the schematic diagrams are merely examples and should not limit the scope of protection of the present invention. In actual fabrication, the three-dimensional spatial dimensions of length, width, and depth should be included.

[0047] In the description of this application, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is usually based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this application and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this application; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0048] An embodiment of a semi-physical simulation system for an aero-engine thrust reverser system is disclosed herein. Figure 1 This is a flowchart illustrating an embodiment of a semi-physical simulation system for the aero-engine thrust reverser system of the present invention. Figure 2 This is a data flow diagram illustrating an embodiment of a semi-physical simulation system for an aero-engine thrust reverser system according to the present invention.

[0049] like Figure 1 As shown, in this embodiment, the semi-physical simulation system of the aero-engine thrust reverser system includes a real-time simulation platform, a thrust reverser component integration platform, an engine controller, and a thrust reverser controller. The real-time simulation platform includes a real-time simulation model and a hardware input / output model of the aero-engine, simulating the operating state of the aero-engine through the integrated real-time simulation model and hardware input / output model. The thrust reverser component integration platform integrates the thrust reverser component simulation model of the thrust reverser system, simulating the operating state of the thrust reverser system under the semi-physical simulation environment. The engine controller is connected to both the real-time simulation platform and the aero-engine. The real-time simulation platform sends simulated operating information of the aero-engine to the aero-engine through the connected engine controller, thereby controlling the aero-engine to operate based on the simulated operating information. The thrust reverser controller is connected to both the real-time simulation platform and the thrust reverser component integration platform. The real-time simulation platform obtains simulated thrust reverser information from the thrust reverser component integration platform through the connected thrust reverser controller and transmits it to the engine controller to verify the function of the aero-engine thrust reverser system.

[0050] Specifically, in this embodiment, the real-time simulation model runs in the real-time operating system of the real-time simulation platform, including an engine model, an aircraft model, and a communication model. The engine model is created by modeling the aerodynamic and thermodynamic characteristics of each engine component and generating an executable file that can run in the real-time operating system. This file includes the characteristics of each engine component and can calculate the temperature, pressure, and rotational speed of the high and low pressure shafts at various cross-sections of the engine in real time, thereby simulating the operating state of each component of the aero-engine. The simulation data is then transmitted to the engine controller via the connected communication model.

[0051] The aircraft model is used to simulate the pilot's operation of the engine throttle lever, fuel control switch, etc., and can be presented on the host computer of the simulation system in the form of a cockpit interface. Users can inject use cases into the aircraft model through the interface to simulate various pilot operations. When building the aircraft model, model code can be written according to the execution logic of the aircraft controller, and then a feasibility file that can run on the real-time operating system can be generated to simulate the operation of the aero-engine. The simulation data of the operation is transmitted to the engine controller through a connected communication model.

[0052] The communication model includes sensor interfaces, communication interfaces, and digital output interfaces. For example, it serves as the communication interface between the aircraft engine and the engine controller, transmitting information about the engine's external environment, such as altitude, Mach number, and ambient static pressure. Through the communication model, the engine can receive status information from the engine controller, such as high and low pressure speeds, total temperature and pressure at the engine cross-section, and sensor fault codes. Furthermore, after reading the simulation data of the engine model's operating status and the aircraft model's operational simulation data, the communication interface can transmit the data to the engine controller to control the aero-engine's operation.

[0053] Specifically, in this embodiment, after the test personnel operate the cockpit model of the aircraft, the communication model obtains the aircraft status information of the aircraft model through its built-in communication interface, such as the real-time status of the cockpit model, and then sends the aircraft status information to the engine controller. Furthermore, in this embodiment, after receiving the engine status information sent by the engine controller, the communication model can also display the engine status information on the cockpit model's interface to simulate the cockpit display panel on the aircraft, making it easier for the test personnel to monitor the engine status.

[0054] In this embodiment, the hardware input / output model includes a sensor signal board model, a communication board model, and a digital output board model. The sensor board model is connected to the real-time simulation model, simulating engine sensor signals (e.g., engine temperature, pressure, speed) based on the real-time engine status information received from the simulation model. The communication board model is connected to both the thrust reverser controller and the engine controller, transmitting thrust reverser signal data from the thrust reverser controller to the engine controller via a built-in board that covers the engine communication protocol. The digital output board model includes digital input boards and digital output boards. The built-in digital input board receives digital signals from the controller, and the digital output board simulates various digital signals output by the real-time simulation model.

[0055] Specifically, in this embodiment, the sensor board model includes RTD boards, thermocouple boards, piezoresistive boards, LVDT boards, etc., and the communication board model includes boards covering the engine communication protocol. The input to the sensor board model is the real-time speed, pressure, temperature, and corresponding sensor signal values ​​calculated by the engine model. The engine model converts the calculated physical quantity signals into analog signals, and then the sensor board model outputs the analog signals to the engine controller.

[0056] Furthermore, in this embodiment, a signal simulation board model can also be used to receive signals output by the engine model. This signal simulation board includes an electro-hydraulic servo valve simulation board, which collects the current signals emitted by the engine controller and converts them into digital signals, transmitting them to the engine model.

[0057] In this embodiment, the switch input board model includes a switch input board and a switch output board. The switch input board receives switch signals from the controller, while the switch output board simulates various switch signals output by the aircraft model. During simulation, the switch input board model receives the starter air valve switching signal from the controller. This starter air valve switching signal is generated by the controller. After receiving the starter air valve switching signal, the switch input board transmits the signal to the engine model. The engine model determines whether to start the engine based on the starter air valve's switching status.

[0058] The digital output board is used to simulate the digital signals output by the aircraft model. During simulation, the aircraft model outputs digital signals to the digital output board, which then transmits these signals (including signals from the fuel control switch, starter switch, etc.) to the engine controller. The engine controller then controls the engine based on the status of these digital signals.

[0059] Furthermore, in this embodiment, the communication interface can simulate not only the communication between the aircraft controller and the engine controller, but also the communication between the thrust reverser controller and the engine controller. The communication interface has a physical / simulation switching function. When a physical thrust reverser controller is connected, it switches to physical mode, in which case the physical thrust reverser controller connects to the engine controller via the communication interface. When no thrust reverser controller is connected, it switches to simulation mode, in which case a communication simulation board simulates the communication module of the thrust reverser controller, enabling communication between the thrust reverser controller and the engine controller.

[0060] In this embodiment, the thrust reverser integration platform includes a hydraulic oil source, an isolation controller, a directional controller, and a thrust reverser actuator. The hydraulic oil source is connected to the isolation controller, supplying oil to the directional controller via the isolation controller, thereby providing hydraulic power to the thrust reverser integration platform. The isolation controller is connected to both the hydraulic oil source and the directional controller, isolating the hydraulic oil source from the downstream thrust reverser actuator. The directional controller is connected to both the thrust reverser controller and the thrust reverser actuator. Upon receiving a thrust reverser control signal from the thrust reverser controller, the directional controller supplies hydraulic oil to the thrust reverser actuator, thereby controlling the thrust reverser actuator to perform thrust reverser operations.

[0061] Specifically, in this embodiment, the directional controller includes components such as an electro-hydraulic servo valve and a proximity sensor. During simulation, the directional controller first receives commands from the thrust reverser controller. If the thrust reverser command is to open, the directional controller will change the direction of hydraulic flow through the electro-hydraulic servo valve, causing the thrust reverser actuator to operate in the direction of thrust reverser opening. If the thrust reverser command is to retract, the directional controller will change the direction of hydraulic flow through the electro-hydraulic servo valve, causing the thrust reverser actuator to operate in the direction of thrust reverser retraction. Furthermore, in this embodiment, the hydraulic oil source for the directional controller comes from an isolation system; the directional controller can only control the flow direction of hydraulic oil when the isolation system opens the oil source.

[0062] In this embodiment, the thrust reverser actuator includes multiple actuator cylinders for executing commands from the directional control system. When the directional control system generates an oil circuit for thrust reverser opening, the thrust reverser actuation system executes the thrust reverser opening command. When the directional control system generates an oil circuit for thrust reverser retraction, the thrust reverser actuation system executes the thrust reverser retraction command.

[0063] In one embodiment, the thrust reverser actuator includes four actuator cylinders, distributed on both sides of the engine. A synchronizer shaft is mounted on the actuator cylinders on the same side, and the synchronizer shaft is fitted with a synchronizer shaft lock SL. Since the actuator cylinders can only operate after the synchronizer shaft lock is unlocked, the synchronizer shaft lock needs to be unlocked by the thrust reverser controller during simulation. Furthermore, in this embodiment, one of the two actuator cylinders on the same side is also equipped with a manual lock for manual unlocking and locking.

[0064] Furthermore, in this embodiment, the thrust reverser integration platform also includes a thrust reverser defense component for locking the thrust reverser actuation of the thrust reverser system, thereby preventing the thrust reverser system from accidentally opening without authorization. The thrust reverser defense component includes a third-line lock solenoid valve, a third-line lock actuator, an electro-hydraulic servo valve, a hydraulic actuator, and a proximity switch. When the thrust reverser defense component receives a lock signal from the aircraft, the electro-hydraulic servo valve controls the hydraulic actuator to lock the thrust reverser device. The locking process restricts the opening of the thrust reverser nacelle through a limit mechanism. When an unlock signal is sent from the aircraft, the electro-hydraulic servo valve controls the hydraulic actuator to unlock the thrust reverser device.

[0065] Furthermore, in this embodiment, the thrust reverser component is driven by the hydraulic pressure of the isolation system. Power can only be output to the thrust reverser component after the isolation system unlocks the hydraulic oil source. The control signal for the hydraulic oil source from the isolation system originates from the aircraft; the isolation system only supplies oil to the downstream directional controller and thrust reverser component when the aircraft issues an unlocking command.

[0066] In this embodiment, the engine controller includes an engine control module, an engine status acquisition module, and an engine communication module. The engine control module performs high-pressure speed control, fuel flow control, and engine status control on the aero-engine. The engine status acquisition module collects status information from various sections of the aero-engine, including but not limited to temperature, pressure, high and low pressure speeds, actuator displacement of the fuel system, and fault status of onboard sensors. The engine communication module enables communication between the aero-engine, the aircraft, and the thrust reverser controller.

[0067] Specifically, such as Figure 2 As shown, in this embodiment, the engine controller establishes communication with the thrust reverser controller through the communication interface 429_2 of the real-time simulation platform and the interface 429_1 of the thrust reverser controller. Then, the engine controller acquires the displacement LVDT2 signal of the thrust reverser actuator through the sensor interface of the real-time simulation platform. The sensor interface of the real-time simulation platform is connected to the displacement LVDT1 of the thrust reverser actuator. Through the conversion of the sensor interface, the engine controller achieves the function of acquiring the displacement of the thrust reverser actuator.

[0068] In this embodiment, the thrust reverser controller includes a thrust reverser control module, a thrust reverser acquisition module, and a thrust reverser communication module. The thrust reverser control module controls the deployment and retraction of the thrust reverser system. The thrust reverser acquisition module collects proximity switch signals from various components of the thrust reverser system. Examples include the proximity switch SOV2 for the electro-hydraulic servo valve of the defensive line component, the proximity switch signal SOV3 for the directional control valve, and the proximity switch SOV1 for the synchronous shaft lock control valve. The thrust reverser communication module enables communication between the thrust reverser component integration platform and the aircraft and aero-engine.

[0069] Specifically, in this embodiment, the thrust reverser controller is powered by the 28V switching output POWER of the simulation platform. The simulation platform controls the isolation valve via SWO2 and the control valve of the defense system via SWO3. The thrust reverser controller controls the directional valve via SWO4. The thrust reverser system can be operated physically within the system or via a simulation model. When operating as a simulation model, the physical components consist only of the engine controller and the thrust reverser controller.

[0070] This specification also provides a computer-readable medium storing a physical simulation system of an aero-engine thrust reverser system. When executed by a processor, the computer-readable medium implements the functions of the physical simulation system of the aero-engine thrust reverser system as described above.

[0071] This specification also provides a semi-physical simulation device for an aero-engine thrust reverser system, comprising: a memory for storing instructions executable by a processor; and a processor for executing the instructions to realize the functions of the semi-physical simulation system for the aero-engine thrust reverser system as described above.

[0072] The prior description of this disclosure is provided to enable any person skilled in the art to make or use this disclosure. Various modifications to this disclosure will be apparent to those skilled in the art, and the general principles defined herein may be applied to other variations without departing from the spirit or scope of this disclosure. Therefore, this disclosure is not intended to be limited to the examples and designs described herein, but should be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0073] Those skilled in the art will further appreciate that the various illustrative logic blocks, modules, circuits, and algorithm steps described in conjunction with the embodiments disclosed herein can be implemented as electronic hardware, computer software, or a combination of both. To clearly illustrate this interchangeability between hardware and software, the various illustrative components, blocks, modules, circuits, and steps are described above in a generalized manner in terms of their functionality. Whether such functionality is implemented as hardware or software depends on the specific application and the design constraints imposed on the overall system. Those skilled in the art may implement the described functionality in different ways for each specific application, but such implementation decisions should not be construed as departing from the scope of the invention.

[0074] The various illustrative logic blocks, modules, and circuits described in conjunction with the embodiments disclosed herein can be implemented or performed using a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components, or any combination thereof designed to perform the functions described herein. The general-purpose processor may be a microprocessor, but in alternatives, it may be any conventional processor, controller, microcontroller, or state machine. The processor may also be implemented as a combination of computing devices, such as a combination of a DSP and a microprocessor, multiple microprocessors, one or more microprocessors cooperating with a DSP core, or any other such configuration.

[0075] The steps of the methods or algorithms described in conjunction with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of both. The software module may reside in RAM memory, flash memory, ROM memory, EPROM memory, EEPROM memory, registers, hard disk, removable disk, CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor such that the processor can read and write information to / from the storage medium. In an alternative, the storage medium may be integrated into the processor. The processor and storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and storage medium may reside as discrete components in the user terminal.

[0076] In one or more exemplary embodiments, the described functionality may be implemented in hardware, software, firmware, or any combination thereof. If implemented in software as a computer program product, the functionality may be stored or transmitted as one or more instructions or code on or through a computer-readable medium. A computer-readable medium includes both computer storage media and communication media, encompassing any medium that facilitates the transfer of a computer program from one location to another. A storage medium may be any available medium accessible to a computer. By way of example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disc storage, disk storage or other magnetic storage devices, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and is accessible to a computer. Any connection is also legitimately referred to as a computer-readable medium. For example, if the software is transmitted from a website, server, or other remote source using coaxial cable, fiber optic cable, twisted pair, digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwave, then the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwave are included in the definition of a medium. As used in this article, disk and disc include compact discs (CDs), laser discs, optical discs, digital multi-purpose discs (DVDs), floppy disks, and Blu-ray discs. Disks typically reproduce data magnetically, while discs reproduce data optically using lasers. Combinations of these should also be included within the scope of computer-readable media.

Claims

1. A semi-physical simulation system for an aero-engine thrust reverser system, characterized in that, include: Real-time simulation platform, thrust reverser component integration platform, engine controller, and thrust reverser controller; among them, The real-time simulation platform includes a real-time simulation model of the aero-engine and a hardware input / output model. It simulates the operating state of the aero-engine through the integrated real-time simulation model and hardware input / output model. The thrust reverser component integration platform integrates the thrust reverser component simulation model of the thrust reverser system, and simulates the operating state of the thrust reverser system under a semi-physical simulation environment through the integrated thrust reverser component simulation model; The engine controller is connected to the real-time simulation platform and the aero-engine respectively. The real-time simulation platform sends simulation operation information of the aero-engine to the aero-engine through the connected engine controller, thereby controlling the aero-engine to operate based on the simulation operation information. The thrust reverser controller is connected to both the real-time simulation platform and the thrust reverser component integration platform. The real-time simulation platform obtains simulated thrust reverser information from the thrust reverser component integration platform through the connected thrust reverser controller and transmits it to the engine controller to verify the function of the aero-engine thrust reverser system.

2. The semi-physical simulation system for an aero-engine thrust reverser system according to claim 1, characterized in that, Real-time simulation models include engine models, aircraft models, and communication models; among them, The engine model is used to simulate the operating status of various components of an aero-engine and transmits the simulation data of the operating status to the engine controller through a communication model connected to it. The aircraft model is used to simulate the operation of the aircraft engine and transmits the simulation data of the operation to the engine controller through the communication model connected to it. The communication model includes sensor interfaces, communication interfaces, and switch output interfaces. Through the set sensor interfaces, communication interfaces, and switch output interfaces, the simulation data of the engine model's operating status and the simulation data of the aircraft model's operation are read and transmitted to the engine controller to control the operation of the aero-engine.

3. The semi-physical simulation system for an aero-engine thrust reverser system according to claim 1, characterized in that, The hardware input / output model includes sensor signal board model, communication board model, and digital input / output board model; among them, The sensor board model is connected to the real-time simulation model, and the sensor signals of the engine are simulated based on the real-time status information of the engine input from the real-time simulation model. The communication board model is connected to the thrust reverser controller and the engine controller respectively. The built-in board covering the engine communication protocol transmits the thrust reverser signal data from the thrust reverser controller to the engine controller. The digital output board model includes a digital input board and a digital output board. The built-in digital input board receives digital signals from the controller, and the digital output board simulates various digital signals output by the real-time simulation model.

4. The semi-physical simulation system for an aero-engine thrust reverser system according to claim 3, characterized in that, The hardware input / output model also includes a signal simulation board model, which is used to receive signals output by the engine model. The signal simulation board includes an electro-hydraulic servo valve simulation board, which collects the current signal sent by the engine controller and converts the current signal into a digital quantity to be transmitted to the engine model.

5. The semi-physical simulation system for an aero-engine thrust reverser system according to claim 1, characterized in that, The thrust reverser component integration platform includes a hydraulic power source, an isolation controller, a directional controller, and a thrust reverser actuator; among which, The hydraulic oil source is connected to the isolation controller, and oil is supplied to the direction controller through the isolation controller, thereby providing hydraulic power to the thrust reverser integration platform; The isolation controller is connected to the hydraulic oil source and the directional controller respectively, and isolates the hydraulic oil source from the downstream thrust reverser through the isolation controller; The directional controller is connected to both the thrust reverser controller and the thrust reverser actuator. After receiving the thrust reverser control signal from the thrust reverser controller, the directional controller pumps hydraulic oil into the thrust reverser actuator, thereby controlling the thrust reverser actuator to perform the thrust reverser operation.

6. The semi-physical simulation system for an aero-engine thrust reverser system according to claim 1, characterized in that, The thrust reverser component integration platform also includes a thrust reverser defense line component; among which, the thrust reverser defense line component includes a third defense line lock solenoid valve and a third defense line lock actuator, which are used to lock the thrust reverser operation of the thrust reverser system, thereby preventing the thrust reverser system from being accidentally opened in a non-command state.

7. The semi-physical simulation system for an aero-engine thrust reverser system according to claim 1, characterized in that, The engine controller includes an engine control module, an engine status acquisition module, and an engine communication module; among which, The engine control module is used to perform high-pressure speed control, fuel flow control, and engine status control of aero engines. The engine status acquisition module is used to collect status information of various sections of the aero-engine. The engine communication module is used to enable communication between the aero engine and the aircraft and thrust reverser controller.

8. The semi-physical simulation system for an aero-engine thrust reverser system according to claim 1, characterized in that, The thrust reverser controller includes a thrust reverser control module, a thrust reverser acquisition module, and a thrust reverser communication module; among which, The thrust reverser control module is used to control the deployment and retraction of the thrust reverser system. The backpropagation acquisition module is used to acquire proximity switch signals from various components of the backpropagation system. The thrust reverser communication module is used to enable communication between the thrust reverser component integration platform and the aircraft and aero-engine.

9. A computer-readable medium storing a semi-physical simulation system of an aero-engine thrust reverser system, characterized in that, The computer-readable medium, when executed by a processor, implements the system functions as described in any one of claims 1-8.

10. A semi-physical simulation device for an aero-engine thrust reverser system, characterized in that, include: Memory is used to store instructions that can be executed by the processor; as well as A processor for executing the instructions to implement the system functions as described in any one of claims 1-8.

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