A simulation method, device, equipment and medium for electric vertical take-off and landing aircraft

Abstract

The present invention discloses a simulation method, device, equipment and medium for an electric vertical take-off and landing aircraft, the method comprising: obtaining a function description file and an interface definition document respectively corresponding to at least one aircraft component; for each aircraft component, determining a component simulation model corresponding to the aircraft component based on the function description file, interface definition document and general simulation component corresponding to the aircraft component; in response to detecting a simulation request, determining a current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request; performing a simulation operation on the current modeling and simulation product to obtain a simulation result corresponding to the simulation request. The embodiment of the present invention solves the problem that different current modeling and simulation products belong to different simulation platforms, realizes the sharing of upstream and downstream resource data during the simulation process of the eVTOL aircraft, and improves the simulation efficiency and development efficiency of the eVTOL aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of eVTOL aircraft, and in particular to a simulation method, device, equipment and medium for an electric vertical take-off and landing aircraft. Background Art

[0002] eVTOL (Electric Vertical Take-Off and Landing) aircraft is a safe, sustainable and barrier-free form of aviation. eVTOL aircraft has the potential to revolutionize urban transportation networks and play an indispensable role in future smart cities. The entire life cycle of eVTOL aircraft is a large and complex system engineering, involving the coordination of multiple business systems such as equipment manufacturers, operators, infrastructure providers, air navigation service providers and regulators.

[0003] At present, each business system designs a simulation platform and uses a separate data repository based on the aircraft components in the eVTOL aircraft it uses. The sharing of simulation resources between different business systems can only be achieved through offline communication, which greatly reduces the simulation efficiency and development efficiency of the eVTOL aircraft. Summary of the invention

[0004] The present invention provides a simulation method, device, equipment and medium for an electric vertical take-off and landing aircraft, which improves the simulation efficiency and development efficiency of the eVTOL aircraft by solving the problem that different current modeling and simulation products belong to different simulation platforms.

[0005] According to one aspect of the present invention, a simulation method for an electric vertical take-off and landing aircraft is provided, the method comprising:

[0006] Acquire a function description file and an interface definition document respectively corresponding to at least one aircraft component; wherein the function description file represents function parameter information of the aircraft component, and the interface definition document represents interface parameter information of the aircraft component;

[0007] For each aircraft component, determining a component simulation model corresponding to the aircraft component based on a function description file, an interface definition document, and a general simulation component corresponding to the aircraft component;

[0008] In response to detecting a simulation request, determining a current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request;

[0009] Perform a simulation operation on the current modeling and simulation product to obtain a simulation result corresponding to the simulation request.

[0010] According to another aspect of the present invention, there is provided a simulation device for an electric vertical take-off and landing aircraft, the device comprising:

[0011] An interface definition document acquisition module, used to acquire a function description file and an interface definition document respectively corresponding to at least one aircraft component; wherein the function description file represents function parameter information of the aircraft component, and the interface definition document represents interface parameter information of the aircraft component;

[0012] A component simulation model determination module, configured to determine, for each aircraft component, a component simulation model corresponding to the aircraft component based on a function description file, an interface definition document, and a general simulation component corresponding to the aircraft component;

[0013] A current modeling and simulation product determination module is used to determine a current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request in response to detecting the simulation request;

[0014] The simulation result determination module is used to perform simulation operations on the current modeling and simulation product to obtain simulation results corresponding to the simulation request.

[0015] According to another aspect of the present invention, an electronic device is provided, the electronic device comprising:

[0016] at least one processor; and

[0017] a memory communicatively connected to the at least one processor; wherein,

[0018] The memory stores a computer program executable by the at least one processor, and the computer program is executed by the at least one processor so that the at least one processor can execute the simulation method of the electric vertical take-off and landing aircraft described in any embodiment of the present invention.

[0019] According to another aspect of the present invention, a computer-readable storage medium is provided, wherein the computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a processor to implement the simulation method of an electric vertical take-off and landing aircraft described in any embodiment of the present invention when executed.

[0020] The technical solution of the embodiment of the present invention determines, for each aircraft component corresponding to the eVTOL aircraft, a component simulation model corresponding to the aircraft component based on a general simulation component, a function description file corresponding to the acquired aircraft component, and an interface definition document; in response to detecting a simulation request, determines a current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request; performs a simulation operation on the current modeling and simulation product to obtain a simulation result; thereby solving the problem that different current modeling and simulation products belong to different simulation platforms, realizing the sharing of upstream and downstream resource data during the simulation process of the eVTOL aircraft, and improving the simulation efficiency and development efficiency of the eVTOL aircraft.

[0021] It should be understood that the contents described in this section are not intended to identify the key or important features of the embodiments of the present invention, nor are they intended to limit the scope of the present invention. Other features of the present invention will become easily understood through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0023] Figure 1 is a flow chart of a simulation method for an electric vertical take-off and landing aircraft provided according to Embodiment 1 of the present invention;

[0024] Figure 2 is a flow chart of a method for generating a component simulation model according to Embodiment 1 of the present invention;

[0025] Figure 3 is a flow chart of a simulation control mode provided according to the first embodiment of the present invention;

[0026] Figure 4 is a flow chart of a simulation method for an electric vertical take-off and landing aircraft provided according to a second embodiment of the present invention;

[0027] Figure 5 is a schematic diagram of a development model of the life cycle of an eVTOL aircraft provided according to the second embodiment of the present invention;

[0028] Figure 6 is a structural schematic diagram of a simulation device for an electric vertical take-off and landing aircraft provided according to a third embodiment of the present invention;

[0029] Figure 7 It is a structural schematic diagram of an electronic device provided according to Embodiment 4 of the present invention. DETAILED DESCRIPTION

[0030] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0031] It should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0032] Embodiment 1

[0033] Figure 1 This is a flow chart of a simulation method for an electric vertical take-off and landing aircraft provided according to the first embodiment of the present invention. This embodiment is applicable to the case of performing simulation operations on an eVTOL aircraft. The method can be performed by a simulation device for an electric vertical take-off and landing aircraft. The simulation device for an electric vertical take-off and landing aircraft can be implemented in the form of hardware and / or software. The simulation device for an electric vertical take-off and landing aircraft can be configured in a terminal device. Figure 1 As shown, the method includes:

[0034] S110: Obtain a function description file and an interface definition document corresponding to at least one aircraft component.

[0035] In one embodiment, optionally, the function description files and interface definition documents corresponding to at least one aircraft component imported by the business system are obtained. The document format of the interface definition document is Excel. Specifically, the aircraft components in this embodiment include functional components in the eVTOL aircraft, and of course, may also include scene components during the use of the eVTOL aircraft. Exemplarily, the functional components include but are not limited to pneumatic components, flight control components, flight management systems, obstacle avoidance systems, etc., and the scene components include airspace management systems and airport and apron management systems, etc. Functional components can meet the simulation requirements of equipment manufacturers and basic equipment suppliers, and scene components can meet the simulation requirements of operators, air navigation service providers and regulatory agencies. The specific types of aircraft components are not limited here, and can be customized according to the actual simulation requirements of different business systems.

[0036] In another embodiment, optionally, a function description file and an interface definition document respectively corresponding to at least one aircraft component are obtained, including: in response to receiving a real simulation model respectively corresponding to at least one aircraft component imported into a business system, performing a parsing operation on the real simulation model to obtain a function description file and an interface definition document respectively corresponding to at least one aircraft component; and / or, in response to receiving a function description file and an interface definition document in a non-Excel format imported into the business system, performing a parsing operation on the interface definition document to obtain an interface definition document in an Excel format.

[0037] Specifically, the real simulation model is a component simulation model developed by the business system. Exemplarily, the non-Excel format may be a formula definition format or an interpolation data table format.

[0038] The advantage of this setting is that it can reduce the requirements on the data type of the business system input data and improve the adaptability between the simulation platform and the business system.

[0039] In this embodiment, the function description file represents the function parameter information of the aircraft component, and the interface definition document represents the interface parameter information of the aircraft component.

[0040] S120. For each aircraft component, determine a component simulation model corresponding to the aircraft component based on a function description file, an interface definition document, and a general simulation component corresponding to the aircraft component.

[0041] In one embodiment, optionally, the component simulation model includes a component simulation component and an interface control document. Accordingly, based on the functional description file, interface definition document and general simulation component corresponding to the aircraft component, the component simulation model corresponding to the aircraft component is determined, including: performing standardization processing on the interface definition document to obtain the interface control document, and determining the component interface framework of the component simulation component based on the interface control document; based on the functional description file, performing a packaging operation on the general simulation component to obtain the component simulation component corresponding to the aircraft component.

[0042] Specifically, the component simulation assembly includes a high-level interface software library and a loadable data file. The high-level interface software library is compiled based on a specific programming language standard and supports Windows and Linux dual operating system operating environments. The loadable data file includes a function description file.

[0043] In one embodiment, optionally, standardization processing is performed on the interface definition document to obtain an interface control document, including: displaying the interface data in the interface definition document to the user through a visualization tool, and obtaining multiple target interface data input by the user; wherein the target interface data is interface data for simulation; based on the standard data structure, standardization processing is performed on each target interface data to obtain an interface control document.

[0044] Specifically, the interface definition document contains various interface data of aircraft components. Exemplarily, the interface data includes real sensor interface data, power interface data, fault prompt interface data, etc. This simulation platform displays all interface data in the interface definition document to the user, and the user selects and discards the interface data in the interface definition document, and retains the interface data that supports modeling and simulation, that is, the target interface data. Exemplarily, the target interface data includes busbar power supply interface data, excitation logic interface data, fault prompt interface data and other interface data related to the data link, and of course, also includes input interface data and output interface data.

[0045] Since the data structures of interface definition documents corresponding to different business systems are different, the data structures of interface definition documents are standardized. For example, the standard data structure can be name, type, unit, description, convention, dimension, refresh rate, value range, enumeration type, initialization value, signal name, comment and communication type, etc.

[0046] In one embodiment, the interface control document is optionally encapsulated as a tab, and the tab is saved in a tab file. The tab describes connecting each component simulation component to establish a simulation, and lists the tab name corresponding to each current modeling and simulation product.

[0047] In one embodiment, optionally, the function description file includes a function requirement file and a specification file, the function requirement file includes performance data of aircraft components, and the specification file includes technical indicator data of aircraft components. Accordingly, based on the function description file, a packaging operation is performed on the general simulation component to obtain a component simulation component corresponding to the aircraft component, including: based on the performance data of the aircraft component, a packaging operation is performed on the general simulation component to obtain a first simulation component; the technical indicator data of the aircraft component is loaded into the first simulation component to obtain a second simulation component; based on the real component data and the simulation component data corresponding to the second simulation component, a verification operation is performed on the second simulation component to obtain a component simulation component that has been successfully verified.

[0048] Among them, exemplarily, the performance data includes parameter values ​​of performance curves and / or performance parameters. Taking the flight control system as an example, the performance parameters include but are not limited to maximum pitch angle, minimum pitch angle, maximum bank angle, minimum lift angle, maximum lift angle, minimum rudder angle, maximum rudder angle, turning on / off airspeed hold, setting reference altitude in meters and setting vertical speed reference in meters / second, etc.

[0049] Among them, the first simulation component can support parameter debugging and functional testing.

[0050] Exemplarily, the technical indicator data include technical indicator values ​​and / or boundary values, which are used to limit simulation requirements of the component simulation model.

[0051] Among them, exemplarily, the simulation component data includes but is not limited to simulation input parameter data, simulation output parameter data, and internal parameters of the second simulation component, etc. Correspondingly, the real component parameters include but are not limited to real input parameter data, real output parameter data, and internal parameters of real aircraft components, etc.

[0052] Figure 2It is a flow chart of a method for generating a component simulation model provided according to the first embodiment of the present invention. In this embodiment, the component simulation model includes a component simulation component and an interface control document, wherein the component simulation component includes a loadable data file and a high-level interface software library. Specifically, the business system imports the eVTOL aircraft function requirement file, the eVTOL aircraft rule description file and the interface definition document through the human-machine interface provided by this simulation platform. The internal parameters of the first simulation component, that is, the performance data in the eVTOL aircraft function requirement file, are selected from the eVTOL aircraft function requirement file, wherein the performance data constitutes a loadable data file. For the selected performance data, a packaging operation is performed on the general simulation component to obtain a first simulation component. The technical indicator data in the eVTOL aircraft rule description file is loaded into the first simulation component, a second simulation component is created, and the second simulation component is checked for compliance based on the real component data and the simulation component data of the second simulation component, and the second simulation component that has successfully been checked is used as the component simulation component.

[0053] The interface definition document is obtained from the eVTOL aircraft interface definition document storage area, and the target interface data supported by modeling and simulation in the interface definition document are selected, and based on the standard data structure, each target interface data is subjected to standardization processing to obtain an interface control document. Based on the interface control document, the component interface framework of the component simulation component is determined. Among them, when the document format of the interface definition document is not in Excel format, the interface definition document is parsed to obtain an interface definition document in Excel format.

[0054] S130 . In response to detecting a simulation request, determining a current modeling simulation product based on at least one target component simulation model corresponding to the simulation request.

[0055] Specifically, when there are multiple simulation models of the target component, the output interface of the simulation model of the target component is connected to the input interface of another corresponding simulation model of the target component to construct the current modeling simulation product.

[0056] S140: Execute a simulation operation on the current modeling and simulation product to obtain a simulation result corresponding to the simulation request.

[0057] In one embodiment, the simulations of the component simulation models all follow the simulation control mode, wherein the simulation control mode provides an entry point to arrange the simulation through functions and state machines, and the simulation control mode consumes and produces data defined in the component simulation model, and interacts with other component simulation models by configuring specific names.

[0058] Among them, the component simulation model is a fixed-step model, and its simulation time step is a dedicated control input of the component simulation model. It is subject to the same adjustment of the simulation control mode and can still be modified during the simulation operation.

[0059] Figure 3 It is a flowchart of a simulation control mode provided according to the first embodiment of the present invention. Specifically, the simulation control mode includes a loading mode, an initialization mode, a reload mode, a running mode, an unloading mode and an intermittent mode. Among them, the loading mode is used for data loading, file opening, component simulation model configuration parameter loading and creating a connection to the path where the component simulation model is located; the initialization mode is used to execute the pre-defined initialization input, internal and output values ​​of each component simulation model; the reload mode is used to reset the input, internal and output values ​​of each component simulation model and recalculate them by external conditions; the running mode is used to execute the cyclic calculation of the simulation program according to a fixed simulation step size; the intermittent mode is used for a mode defined opposite to the cyclic calculation of the running mode, which circulates but does not perform calculations; the unloading mode is used for data unloading, file closing, component simulation model configuration parameter unloading and closing the connection to the path where the component simulation model is located.

[0060] Specifically, the simulation control mode starts from the loading mode, and jumps to the initialization mode after the loading is completed. The initialization mode determines whether it has been executed. If so, it jumps to the reload mode. If not, it continues the initialization mode until all simulation models of target components in the current modeling and simulation product are initialized. The reload mode will also determine whether it has been executed. During the operation of the reload mode, if the external conditions require the current modeling and simulation product to be reinitialized, it will jump to the initialization mode. The operation mode performs infinite loop calculations according to a fixed simulation step. If the external conditions require the current modeling and simulation product to be reinitialized, reloaded, paused or terminated, it will jump to the initialization mode, reload mode, pause mode or unload mode accordingly. The pause mode performs infinite loops according to the fixed simulation step but does not calculate. If the external conditions require the current modeling and simulation product to be reinitialized, reloaded, rerun or terminated, it will jump to the initialization mode, reload mode, operation mode or unload mode accordingly. Among them, the external conditions mainly come from the operation of the human-computer interface of this simulation platform.

[0061] The technical solution of this embodiment determines, for each aircraft component corresponding to the eVTOL aircraft, a component simulation model corresponding to the aircraft component based on a general simulation component, a function description file corresponding to the acquired aircraft component, and an interface definition document; in response to detecting a simulation request, determines a current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request; performs a simulation operation on the current modeling and simulation product to obtain a simulation result; this solves the existing problem that different current modeling and simulation products belong to different simulation platforms, realizes the sharing of upstream and downstream resource data during the simulation process of the eVTOL aircraft, and improves the simulation efficiency and development efficiency of the eVTOL aircraft.

[0062] Embodiment 2

[0063] Figure 4 1 is a flow chart of a simulation method for an electric vertical take-off and landing aircraft according to the second embodiment of the present invention. This embodiment further refines the "current modeling simulation product" in the above embodiment. Figure 4 As shown, the method includes:

[0064] S210: Obtain a function description file and an interface definition document corresponding to at least one aircraft component.

[0065] Among them, this simulation platform is connected with the data transmission interface of the business system by setting an interface to realize data interaction with the business system. Among them, exemplary, the business system includes but is not limited to original equipment manufacturers, operators, infrastructure providers, air navigation service providers, maintenance service providers, training centers and training solution providers, and regulatory agencies, etc. Among them, the original equipment manufacturer is used to design and manufacture eVTOL aircraft and obtain regulatory approval. Operators use eVTOL aircraft purchased or leased from asset management companies to provide regular or charter services. Infrastructure providers are used to design the take-off position, landing position and terminal facilities of eVTOL aircraft. Air navigation service providers are responsible for coordinating the movement of eVTOL aircraft through controlled airspace and preventing collisions to ensure safe and efficient air traffic flow. Maintenance service providers provide maintenance services for eVTOL aircraft to ensure the airworthiness of eVTOL aircraft. Training centers and training solution providers use eVTOL aircraft to train pilots. Monitoring agencies provide certification for the design, manufacture and operation of eVTOL aircraft.

[0066] S220. For each aircraft component, determine a component simulation model corresponding to the aircraft component based on a function description file, an interface definition document, and a general simulation component corresponding to the aircraft component.

[0067] S230: When a simulation request is detected, a simulation process of a previous modeling and simulation product corresponding to the simulation request is obtained.

[0068] In this embodiment, the current modeling and simulation products are desktop simulation equipment, flight procedure trainer, system integration test bench, iron bird and training simulator according to a preset simulation order.

[0069] Figure 5 It is a schematic diagram of a development model of the life cycle of an eVTOL aircraft provided according to the second embodiment of the present invention. The left side of the V-shaped development model is the demand and verification stage of the eVTOL aircraft. Specifically, the scientific research simulation device is a simulation device loaded with a full set of general simulation components. According to the requirements of commercial demonstration or scientific research concept, a new function is implanted into a general simulation component to perform a preview effect demonstration. For example, the general simulation component corresponding to the flight control system is implanted with the SVO (Simplified Vehicle Operations) function. During the simulation process of the scientific research simulation device, the user can intuitively experience the driving and operation experience of SVO. The scientific research simulation device can be used to develop or test general simulation components. For example, conceptual design, control rate and key system selection can be performed. Specifically, the desktop simulation device is a simulation device loaded with a simulation model of any target component, which can be used to assist the research and development team of the eVTOL aircraft in selecting design concepts and technologies, and assist in system design. For example, in a simulation environment, the algorithm architecture of the component simulation model corresponding to the flight control system is designed and improved. Specifically, the flight procedure trainer is a simulation device loaded with multiple simulation models of target components, and provides functions such as touch screen and cockpit space position. Since it provides perception of cockpit space position, it can be used to verify and test aircraft logic, operating procedures and conduct human-machine effectiveness evaluation.

[0070] Among them, the right side of the V-shaped development model is the confirmation stage of the eVTOL aircraft. Specifically, the engineering simulation data package is a collection of simulation models of all components corresponding to a certain type of eVTOL aircraft. The engineering simulation data package is continuously iterated and improved along with the life cycle of the eVTOL aircraft, and is consistent with the equipment selection time of the eVTOL aircraft. Specifically, the system integration test bench is loaded with a real aircraft component and some component simulation models. Because the engineering simulation data package is a process from scratch, the early form of the system integration test bench is a desktop simulation device loaded with a small number of component simulation models. With continuous iteration and improvement, the system integration test bench will evolve into a simulation device consistent with the shape of the real eVTOL aircraft cockpit. The iron bird is a simulation device with a full-scale data link consistent with the eVTOL aircraft. In addition to loading a full set of engineering simulation data packages, the airborne system will use more real equipment, and the cross-linking relationship between equipment is also consistent with the real eVTOL aircraft. Specifically, the training simulator is a device used to train pilots after the eVTOL aircraft is airworthy. While simulating the operation of the eVTOL aircraft under normal conditions, it also simulates the status of the eVTOL aircraft under special conditions such as failures and bad weather, and is used to train pilots to operate correctly and ensure aviation safety.

[0071] In one embodiment, branch management is optionally used to control and regulate the life cycle of the modeling and simulation product of the eVTOL aircraft in the simulation platform. The purpose of branch management is to record the evolution of the modeling and simulation product and ensure that developers can perform accurate product configuration at each life stage of the eVTOL aircraft.

[0072] In one embodiment, optionally, branch management includes an engineering branch, a training branch, and a research and development branch. Among them, the engineering branch is used to test and verify airborne equipment during the development of the eVTOL aircraft, and can provide valuable guidance for the flight parameters of related equipment in ground testing, and assist in airworthiness verification. Applicable to engineering simulation data packages, system integration test benches, and iron birds in V mode; the training branch is used to train eVTOL aircraft crew members, which will include many simulations such as failures and special situations. Ultimately, the mature products of this branch will be able to provide core simulation software for eVTOL aircraft flight simulator manufacturers. A training simulator suitable for V mode; an R&D branch is used to test new concepts, new designs, and overall system architectures of eVTOL aircraft. Unlike the engineering branch, its ultimate direction is to verify the feasibility of the conceptual design. Scientific research simulation equipment, desktop simulation equipment, and flight procedure trainers applicable to V mode.

[0073] Specifically, the simulation request is used to characterize the simulation requirements of the current modeling and simulation product, and the previous modeling and simulation product corresponding to the current modeling and simulation product is determined according to a preset simulation sequence. For example, assuming that the current modeling and simulation product corresponding to the simulation request is a flight procedure trainer, the previous modeling and simulation product is a desktop simulation device.

[0074] S240, determine whether the simulation process is completed, if yes, execute S250, if not, execute S270.

[0075] The multiple modeling and simulation products in this embodiment are a process of continuous iteration and improvement according to the simulation process. When the previous modeling and simulation product is mature, the simulation process of the current modeling and simulation product is entered.

[0076] Wherein, illustratively, if the simulation input parameters of the previous modeling and simulation product are the same as the real input parameters, and the simulation output parameters are the same as the real output parameters, then the simulation process of the previous modeling and simulation product is considered to be finished. Exemplarily, the simulation parameters include but are not limited to geometric appearance parameters, aerodynamic characteristic parameters, flight control mode, power system parameters, navigation and guidance strategy parameters, instrument indication parameters, airspace management parameters, airport and apron parameters, etc.

[0077] S250: Determine a current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request.

[0078] S260: Execute a simulation operation on the current modeling and simulation product to obtain a simulation result corresponding to the simulation request.

[0079] S270, performing a simulation operation on the previous modeling and simulation product to obtain a simulation result corresponding to the simulation request.

[0080] On the basis of the above embodiments, optionally, the simulation results of the current modeling and simulation product include updated function description files and / or updated interface definition documents corresponding to at least one target component simulation model. Accordingly, after performing a simulation operation on the current modeling and simulation product and obtaining a simulation result corresponding to the simulation request, the method further includes: for each target component simulation model, based on the updated function description file and / or updated interface definition document corresponding to the target component simulation model, performing an optimization operation on the target component simulation model to obtain an optimized target component simulation model.

[0081] Specifically, by performing optimization operations on the simulation model of the target component, the modeling and simulation product corresponding to the simulation model of the target component is iterated and improved.

[0082] Specifically, if the simulation result includes an updated function description file, then based on the updated function description file, the component simulation component in the target component simulation model is re-encapsulated. If the simulation result includes an updated interface definition document, then an updated interface control document is generated based on the updated interface definition document, and based on the updated interface control document, the component interface framework of the component simulation component is determined.

[0083] The technical solution of this embodiment is to determine, when a simulation request is detected, whether the simulation process of the previous current modeling and simulation product corresponding to the simulation request is completed. If so, the current modeling and simulation product is determined based on at least one target component simulation model corresponding to the simulation request. Furthermore, the embodiment of the present invention sets the modeling and simulation products in this simulation platform according to a preset simulation sequence, namely, a desktop simulation device, a flight procedure trainer, a system integration test bench, an iron bird, and a training simulator, thereby solving the problem of unclear development and testing processes of eVTOL aircraft, supporting the entire life cycle of design, development, integration, verification, and validation of eVTOL aircraft from a time dimension, and further improving the simulation efficiency and development efficiency of eVTOL aircraft.

[0084] Embodiment 3

[0085] Figure 6 1 is a schematic diagram of the structure of a simulation device for an electric vertical take-off and landing aircraft according to the third embodiment of the present invention. Figure 6 As shown, the device includes: an interface definition document acquisition module 310, a component simulation model determination module 320, a current modeling simulation product determination module 330 and a simulation result determination module 340.

[0086] The interface definition document acquisition module 310 is used to acquire a function description file and an interface definition document corresponding to at least one aircraft component; wherein the function description file represents function parameter information of the aircraft component, and the interface definition document represents interface parameter information of the aircraft component;

[0087] A component simulation model determination module 320 is used to determine, for each aircraft component, a component simulation model corresponding to the aircraft component based on a function description file, an interface definition document, and a general simulation component corresponding to the aircraft component;

[0088] A current modeling and simulation product determination module 330 is used to determine a current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request in response to detecting the simulation request;

[0089] The simulation result determination module 340 is used to perform simulation operations on the current modeling and simulation product to obtain simulation results corresponding to the simulation request.

[0090] The technical solution of this embodiment determines, for each aircraft component corresponding to the eVTOL aircraft, a component simulation model corresponding to the aircraft component based on a general simulation component, a function description file corresponding to the acquired aircraft component, and an interface definition document; in response to detecting a simulation request, determines a current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request; performs a simulation operation on the current modeling and simulation product to obtain a simulation result; this solves the existing problem that different current modeling and simulation products belong to different simulation platforms, realizes the sharing of upstream and downstream resource data during the simulation process of the eVTOL aircraft, and improves the simulation efficiency and development efficiency of the eVTOL aircraft.

[0091] Based on the above embodiment, optionally, the component simulation model includes a component simulation component and an interface control document, and the component simulation model determination module 320 includes:

[0092] An interface control document determination unit, used to perform standardization processing on the interface definition document to obtain an interface control document, and determine a component interface framework of the component simulation component based on the interface control document;

[0093] The component simulation component determination unit is used to perform packaging operations on the general simulation components based on the function description file to obtain the component simulation components corresponding to the aircraft components.

[0094] Based on the above embodiment, optionally, the interface control document determination unit is specifically used to:

[0095] The interface data in the interface definition document is displayed to the user through a visualization tool, and a plurality of target interface data input by the user is obtained; wherein the target interface data is the interface data used for simulation;

[0096] Based on the standard data structure, standardization processing is performed on each target interface data to obtain an interface control document.

[0097] Based on the above embodiment, optionally, the function description file includes a function requirement file and a specification file, the function requirement file includes performance data of the aircraft component, the specification file includes technical index data of the aircraft component, and the component simulation component determination unit is specifically used to:

[0098] Based on the performance data of the aircraft component, performing a packaging operation on the general simulation component to obtain a first simulation component;

[0099] Loading technical indicator data of the aircraft component into the first simulation component to obtain a second simulation component;

[0100] Based on the real component data and the simulated component data corresponding to the second simulated component, a verification operation is performed on the second simulated component to obtain a successfully verified component simulation component.

[0101] On the basis of the above embodiment, optionally, the current modeling and simulation products are desktop simulation equipment, flight procedure trainer, system integration test bench, iron bird and training simulator according to a preset simulation order, and the device also includes:

[0102] A simulation process determination module, used to determine whether the simulation process of the previous current modeling and simulation product corresponding to the simulation request is completed before determining the current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request;

[0103] If yes, then the current modeling and simulation product is determined based on at least one target component simulation model corresponding to the simulation request.

[0104] On the basis of the above embodiment, optionally, the simulation result of the current modeling and simulation product includes an updated function description file and / or an updated interface definition document respectively corresponding to at least one target component simulation model, and the device further includes:

[0105] The target component simulation model optimization module is used to perform optimization operations on the target component simulation model based on the updated function description file and / or updated interface definition document corresponding to the target component simulation model after performing simulation operations on the current modeling and simulation product and obtaining the simulation results corresponding to the simulation request, so as to obtain the optimized target component simulation model.

[0106] Based on the above embodiment, optionally, the interface definition document acquisition module 310 is specifically used to:

[0107] In response to receiving the real simulation model corresponding to at least one aircraft component in the aircraft imported by the business system, performing a parsing operation on the real simulation model to obtain a function description file and an interface definition document corresponding to the at least one aircraft component;

[0108] and / or,

[0109] In response to receiving the function description file imported by the business system and the interface definition document in a non-Excel format, a parsing operation is performed on the interface definition document to obtain the interface definition document in an Excel format.

[0110] The simulation device for an electric vertical take-off and landing aircraft provided in an embodiment of the present invention can execute the simulation method for an electric vertical take-off and landing aircraft provided in any embodiment of the present invention, and has functional modules and beneficial effects corresponding to the execution method.

[0111] Embodiment 4

[0112] Figure 7 1 is a schematic diagram of the structure of an electronic device provided according to Embodiment 4 of the present invention. The electronic device 10 is intended to represent various forms of digital computers, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device may also represent various forms of mobile devices, such as personal digital processing, cellular phones, smart phones, wearable devices (such as helmets, glasses, watches, etc.) and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely examples and are not intended to limit the implementation of the present invention described and / or required herein.

[0113] like Figure 7 As shown, the electronic device 10 includes at least one processor 11, and a memory connected to the at least one processor 11, such as a read-only memory (ROM) 12, a random access memory (RAM) 13, etc., wherein the memory stores a computer program that can be executed by at least one processor, and the processor 11 can perform various appropriate actions and processes according to the computer program stored in the read-only memory (ROM) 12 or the computer program loaded from the storage unit 18 to the random access memory (RAM) 13. In the RAM 13, various programs and data required for the operation of the electronic device 10 can also be stored. The processor 11, the ROM 12, and the RAM 13 are connected to each other through a bus 14. An input / output (I / O) interface 15 is also connected to the bus 14.

[0114] A number of components in the electronic device 10 are connected to the I / O interface 15, including: an input unit 16, such as a keyboard, a mouse, etc.; an output unit 17, such as various types of displays, speakers, etc.; a storage unit 18, such as a disk, an optical disk, etc.; and a communication unit 19, such as a network card, a modem, a wireless communication transceiver, etc. The communication unit 19 allows the electronic device 10 to exchange information / data with other devices through a computer network such as the Internet and / or various telecommunication networks.

[0115] The processor 11 may be a variety of general and / or dedicated processing components with processing and computing capabilities. Some examples of the processor 11 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various dedicated artificial intelligence (AI) computing chips, various processors running machine learning model algorithms, a digital signal processor (DSP), and any appropriate processor, controller, microcontroller, etc. The processor 11 executes the various methods and processes described above, such as a simulation method for an electric vertical take-off and landing aircraft.

[0116] In some embodiments, the simulation method of the electric vertical take-off and landing aircraft can be implemented as a computer program, which is tangibly contained in a computer-readable storage medium, such as a storage unit 18. In some embodiments, part or all of the computer program can be loaded and / or installed on the electronic device 10 via the ROM 12 and / or the communication unit 19. When the computer program is loaded into the RAM 13 and executed by the processor 11, one or more steps of the simulation method of the electric vertical take-off and landing aircraft described above can be performed. Alternatively, in other embodiments, the processor 11 can be configured to execute the simulation method of the electric vertical take-off and landing aircraft in any other appropriate manner (for example, by means of firmware).

[0117] Various implementations of the systems and techniques described above herein can be implemented in digital electronic circuit systems, integrated circuit systems, field programmable gate arrays (FPGAs), application specific integrated circuits (ASICs), application specific standard products (ASSPs), systems on chips (SOCs), load programmable logic devices (CPLDs), computer hardware, firmware, software, and / or combinations thereof. These various implementations can include: being implemented in one or more computer programs that can be executed and / or interpreted on a programmable system including at least one programmable processor, which can be a special purpose or general purpose programmable processor that can receive data and instructions from a storage system, at least one input device, and at least one output device, and transmit data and instructions to the storage system, the at least one input device, and the at least one output device.

[0118] The computer program for implementing the simulation method of the electric vertical take-off and landing aircraft of the present invention can be written in any combination of one or more programming languages. These computer programs can be provided to a processor of a general-purpose computer, a special-purpose computer or other programmable data processing device, so that when the computer program is executed by the processor, the functions / operations specified in the flow chart and / or block diagram are implemented. The computer program can be executed entirely on the machine, partially on the machine, partially on the machine as an independent software package and partially on a remote machine, or completely on a remote machine or server.

[0119] Embodiment 5

[0120] Embodiment 5 of the present invention further provides a computer-readable storage medium, wherein the computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a processor to execute a simulation method for an electric vertical take-off and landing aircraft, the method comprising:

[0121] Acquire a function description file and an interface definition document respectively corresponding to at least one aircraft component; wherein the function description file represents function parameter information of the aircraft component, and the interface definition document represents interface parameter information of the aircraft component;

[0122] For each aircraft component, determine the component simulation model corresponding to the aircraft component based on the function description file, interface definition document and general simulation component corresponding to the aircraft component;

[0123] In response to detecting the simulation request, determining a current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request;

[0124] Perform simulation operations on the current modeling and simulation product to obtain simulation results corresponding to the simulation request.

[0125] In the context of the present invention, a computer-readable storage medium may be a tangible medium that may contain or store a computer program for use by or in combination with an instruction execution system, device or equipment. A computer-readable storage medium may include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices or equipment, or any suitable combination of the foregoing. Alternatively, a computer-readable storage medium may be a machine-readable signal medium. A more specific example of a machine-readable storage medium may include an electrical connection based on one or more lines, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0126] To provide interaction with a user, the systems and techniques described herein may be implemented on an electronic device having: a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to the user; and a keyboard and a pointing device (e.g., a mouse or trackball) through which the user can provide input to the electronic device. Other types of devices may also be used to provide interaction with the user; for example, the feedback provided to the user may be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user may be received in any form (including acoustic input, voice input, or tactile input).

[0127] The systems and techniques described herein may be implemented in a computing system that includes backend components (e.g., as a data server), or a computing system that includes middleware components (e.g., an application server), or a computing system that includes frontend components (e.g., a user computer with a graphical user interface or a web browser through which a user can interact with implementations of the systems and techniques described herein), or a computing system that includes any combination of such backend components, middleware components, or frontend components. The components of the system may be interconnected by any form or medium of digital data communication (e.g., a communication network). Examples of communication networks include: a local area network (LAN), a wide area network (WAN), a blockchain network, and the Internet.

[0128] A computing system may include a client and a server. The client and the server are generally remote from each other and usually interact through a communication network. The client and server relationship is generated by computer programs running on the corresponding computers and having a client-server relationship with each other. The server may be a cloud server, also known as a cloud computing server or cloud host, which is a host product in the cloud computing service system to solve the defects of difficult management and weak business scalability in traditional physical hosts and VPS services.

[0129] It should be understood that the various forms of processes shown above can be used to reorder, add or delete steps. For example, the steps described in the present invention can be executed in parallel, sequentially or in different orders, as long as the desired results of the technical solution of the present invention can be achieved, and this document does not limit this.

[0130] The above specific implementations do not constitute a limitation on the protection scope of the present invention. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A simulation method for an electric vertical take-off and landing aircraft, characterized in that: include: Acquire a function description file and an interface definition document respectively corresponding to at least one aircraft component; wherein the function description file represents function parameter information of the aircraft component, and the interface definition document represents interface parameter information of the aircraft component; For each aircraft component, determining a component simulation model corresponding to the aircraft component based on a function description file, an interface definition document, and a general simulation component corresponding to the aircraft component; In response to detecting a simulation request, determining a current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request; Performing a simulation operation on the current modeling and simulation product to obtain a simulation result corresponding to the simulation request; The component simulation model includes a component simulation component and an interface control document. Accordingly, the component simulation model corresponding to the aircraft component is determined based on the function description file, the interface definition document and the general simulation component corresponding to the aircraft component, including: Performing standardization processing on the interface definition document to obtain an interface control document, and determining a component interface framework of the component simulation component based on the interface control document; Based on the functional description file, a packaging operation is performed on the general simulation component to obtain a component simulation component corresponding to the aircraft component.

2. The method according to claim 1, characterized in that The step of performing standardization processing on the interface definition document to obtain an interface control document includes: By means of a visualization tool, the interface data in the interface definition document is displayed to the user, and a plurality of target interface data input by the user is obtained; wherein the target interface data is interface data used for simulation; Based on the standard data structure, standardization processing is performed on each of the target interface data to obtain an interface control document.

3. The method according to claim 1, characterized in that The function description file includes a function requirement file and a specification file, the function requirement file includes performance data of the aircraft component, and the specification file includes technical indicator data of the aircraft component. Accordingly, based on the function description file, the general simulation component is packaged to obtain a component simulation component corresponding to the aircraft component, including: Based on the performance data of the aircraft component, performing a packaging operation on the general simulation component to obtain a first simulation component; Loading the technical indicator data of the aircraft component into the first simulation component to obtain a second simulation component; Based on the real component data and the simulated component data corresponding to the second simulated component, a verification operation is performed on the second simulated component to obtain a successfully verified component simulation component.

4. The method according to claim 1, characterized in that: The current modeling and simulation products are, according to a preset simulation order, a desktop simulation device, a flight procedure trainer, a system integration test bench, an iron bird, and a training simulator. Accordingly, before determining the current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request, the method further includes: Determine whether the simulation process of the previous current modeling and simulation product corresponding to the simulation request is completed; If yes, then the current modeling and simulation product is determined based on at least one target component simulation model corresponding to the simulation request.

5. The method according to claim 1, characterized in that The simulation result of the current modeling and simulation product includes an updated function description file and / or an updated interface definition document respectively corresponding to at least one target component simulation model. Accordingly, after performing a simulation operation on the current modeling and simulation product and obtaining a simulation result corresponding to the simulation request, the method further includes: For each target component simulation model, an optimization operation is performed on the target component simulation model based on an updated function description file and / or an updated interface definition document corresponding to the target component simulation model to obtain an optimized target component simulation model.

6. The method according to any one of claims 1 to 5, characterized in that: The obtaining of the function description file and the interface definition document respectively corresponding to at least one aircraft component comprises: In response to receiving the real simulation model corresponding to at least one aircraft component respectively imported by the business system, performing a parsing operation on the real simulation model to obtain a function description file and an interface definition document corresponding to at least one aircraft component respectively; and / or, In response to receiving the function description file imported by the business system and the interface definition document in a non-Excel format, a parsing operation is performed on the interface definition document to obtain the interface definition document in an Excel format.

7. A simulation device for an electric vertical take-off and landing aircraft, characterized in that: include: An interface definition document acquisition module, used to acquire a function description file and an interface definition document respectively corresponding to at least one aircraft component; wherein the function description file represents function parameter information of the aircraft component, and the interface definition document represents interface parameter information of the aircraft component; A component simulation model determination module, configured to determine, for each aircraft component, a component simulation model corresponding to the aircraft component based on a function description file, an interface definition document, and a general simulation component corresponding to the aircraft component; A current modeling and simulation product determination module is used to determine a current modeling and simulation product based on at least one target component simulation model corresponding to the simulation request in response to detecting the simulation request; A simulation result determination module, used to perform a simulation operation on the current modeling and simulation product to obtain a simulation result corresponding to the simulation request; The component simulation model includes a component simulation component and an interface control document. The component simulation model determines a module, including: An interface control document determination unit, used to perform standardization processing on the interface definition document to obtain an interface control document, and determine a component interface framework of the component simulation component based on the interface control document; The component simulation component determination unit is used to perform a packaging operation on the general simulation component based on the function description file to obtain the component simulation component corresponding to the aircraft component.

8. An electronic device, characterized in that: The electronic device comprises: at least one processor; and a memory communicatively connected to the at least one processor; wherein, The memory stores a computer program executable by the at least one processor, and the computer program is executed by the at least one processor so that the at least one processor can execute the simulation method of the electric vertical take-off and landing aircraft according to any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a processor to implement the simulation method of an electric vertical take-off and landing aircraft according to any one of claims 1 to 6 when executed.

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