CN114840977A - Simulation method, device, equipment and medium for electric vertical take-off and landing aircraft - Google Patents

Abstract

The invention discloses a simulation method, a device, equipment and a medium for an electric vertical take-off and landing aircraft, wherein the method comprises the following steps: acquiring a function description file and an interface definition file which respectively correspond to at least one aircraft part; for each aircraft part, determining a part simulation model corresponding to the aircraft part based on the functional description file, the interface definition document and the general simulation component corresponding to the aircraft part; 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; and executing simulation operation on the current modeling simulation product to obtain a simulation result corresponding to the simulation request. The embodiment of the invention solves the problem that the existing different current modeling simulation products belong to different simulation platforms, realizes the sharing of upstream and downstream resource data in the simulation process of the eVTOL aircraft, and improves the simulation efficiency and the development efficiency of the eVTOL aircraft.

Description

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

Technical Field

The invention relates to the technical field of eVTOL aircrafts, in particular to a simulation method, a simulation device, simulation equipment and a simulation medium of an electric vertical take-off and landing aircraft.

Background

An eVTOL (electrical Vertical Take-Off and Landing) aircraft is a safe, sustainable, barrier-free form of aviation, which has the potential to completely change the urban traffic network and play an indispensable role in future smart cities. The whole life cycle of the eVTOL aircraft is a large and complicated system engineering, and involves the cooperative coordination of a plurality of business systems such as equipment manufacturers, operators, infrastructure providers, air navigation service providers and regulatory agencies.

At present, each business system respectively and independently designs a simulation platform and uses an independent data storage library according to aircraft components in an eVTOL aircraft used by the business system, and simulation resource sharing among different business systems can be realized only by means of communication under lines, so that the simulation efficiency and the development efficiency of the eVTOL aircraft are greatly reduced.

Disclosure of Invention

The invention provides a simulation method, a simulation device and a simulation medium for an electric vertical take-off and landing aircraft, which aim to solve the problem that the existing different current modeling simulation products belong to different simulation platforms, and improve the simulation efficiency and the development efficiency of an eVTOL aircraft.

According to an aspect of the present invention, there is provided a method of simulating an electric vertical take-off and landing aircraft, the method comprising:

acquiring a function description file and an interface definition file which respectively correspond to at least one aircraft part; wherein the function description file characterizes function parameter information of the aircraft component, and the interface definition document characterizes interface parameter information of the aircraft component;

for each aircraft part, determining a part simulation model corresponding to the aircraft part based on the functional description file, the interface definition document and the general simulation component corresponding to the aircraft part;

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;

and executing simulation operation on the current modeling simulation product to obtain a simulation result corresponding to the simulation request.

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

the interface definition document acquisition module is used for acquiring a function description file and an interface definition document which respectively correspond to at least one aircraft component; wherein the function description file characterizes function parameter information of the aircraft component, and the interface definition document characterizes interface parameter information of the aircraft component;

The component simulation model determination module is used for determining a component simulation model corresponding to each aircraft component based on a function description file, an interface definition document and a general simulation component corresponding to the aircraft component;

the current modeling simulation product determining module is used for responding to the detection of the simulation request, and determining a current modeling simulation product based on at least one target component simulation model corresponding to the simulation request;

and the simulation result determining module is used for executing simulation operation on the current modeling simulation product to obtain a simulation result corresponding to the simulation request.

According to another aspect of the present invention, there is provided an electronic apparatus including:

at least one processor; and

a memory communicatively coupled to the at least one processor; wherein the content of the first and second substances,

the memory stores a computer program executable by the at least one processor, the computer program being executable by the at least one processor to enable the at least one processor to perform a method of simulating an electrically powered vertical takeoff and landing aircraft as described in any of the embodiments of the present invention.

According to another aspect of the present invention, there is provided a computer-readable storage medium having stored thereon computer instructions for causing a processor to execute a method of simulating an electric vertical take-off and landing aircraft according to any one of the embodiments of the present invention.

According to the technical scheme, a component simulation model corresponding to the aircraft component is determined based on a general simulation component, the obtained functional description file and the interface definition document corresponding to the aircraft component for each aircraft component corresponding to the eVTOL aircraft, a simulation request is detected in response, a current modeling simulation product is determined based on at least one target component simulation model corresponding to the simulation request, and a simulation operation is performed on the current modeling simulation product to obtain a simulation result.

It should be understood that the statements in this section do not necessarily identify key or critical features of the embodiments of the present invention, nor do they necessarily limit the scope of the invention. Other features of the present invention will become apparent from the following description.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

Fig. 1 is a flowchart of a simulation method of an electric vertical takeoff and landing aircraft according to an embodiment of the present invention;

FIG. 2 is a flowchart of a method for generating a component simulation model according to an embodiment of the present invention;

FIG. 3 is a flow chart of a simulation control mode according to an embodiment of the present invention;

FIG. 4 is a flowchart of a simulation method for an electric vertical takeoff and landing aircraft according to a second embodiment of the present invention;

fig. 5 is a schematic diagram of a development mode of a life cycle of an eVTOL aircraft according to a second embodiment of the invention;

fig. 6 is a schematic structural diagram of a simulation apparatus of an electric vertical take-off and landing aircraft according to a third embodiment of the present invention;

fig. 7 is a schematic structural diagram of an electronic device according to a fourth embodiment of the present invention.

Detailed Description

In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

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

Example one

Fig. 1 is a flowchart of a simulation method for an electric vertical take-off and landing aircraft according to an embodiment of the present invention, which is applicable to a case where simulation operations are performed on an eVTOL aircraft, and the method may be performed by a simulation apparatus for an electric vertical take-off and landing aircraft, which may be implemented in hardware and/or software, and the simulation apparatus for an electric vertical take-off and landing aircraft may be configured in a terminal device. As shown in fig. 1, the method includes:

And S110, acquiring a function description file and an interface definition document corresponding to at least one aircraft part respectively.

In an embodiment, optionally, a function description file and an interface definition document respectively corresponding to at least one aircraft component imported by the business system are obtained. The interface defines the document format of the document to be Excel. Specifically, the aircraft component in the present embodiment includes a functional component in an eVTOL aircraft, and of course, may also include a scene component in the use process of the eVTOL aircraft. For example, the functional components include, but are not limited to, pneumatic components, flight control components, flight management systems, obstacle avoidance systems, and the like, and the scene components include airspace management systems, airport and tarmac management systems, and the like. The functional components can meet the simulation requirements of equipment manufacturers and basic equipment suppliers, and the scene components can meet the simulation requirements of operators, air navigation service providers and regulatory agencies. The specific type of aircraft component is not limited herein and can be customized by the actual simulation requirements of the different business systems.

In another embodiment, optionally, obtaining the function description file and the interface definition document corresponding to each of the at least one aircraft component includes: responding to the received real simulation models respectively corresponding to at least one aircraft part imported by the service system, and performing analysis operation on the real simulation models to obtain a function description file and an interface definition document respectively corresponding to the at least one aircraft part; and/or, in response to receiving a function description file imported by the service system and an interface definition document in a non-excel format, performing analysis operation on the interface definition document to obtain the interface definition document in the excel format.

Specifically, the real simulation model is a component simulation model developed by the service system. The non-excel format may be, for example, a formula definition format or an interpolation data table format.

The method has the advantages that the requirement on the data type of the input data of the service system can be reduced, and the adaptability between the simulation platform and the service system is improved.

In the present embodiment, the function description file characterizes function parameter information of the aircraft component, and the interface definition file characterizes interface parameter information of the aircraft component.

And S120, determining a component simulation model corresponding to each aircraft component based on the function description file, the interface definition document and the general simulation component corresponding to the aircraft component.

In an embodiment, optionally, the determining the component simulation model corresponding to the aircraft component based on the function description file, the interface definition file, and the general simulation component corresponding to the aircraft component includes: performing standardization processing on the interface definition document to obtain an interface control document, and determining a component interface framework of the component simulation assembly based on the interface control document; and performing packaging operation on the general simulation assembly based on the function description file to obtain a component simulation assembly corresponding to the aircraft component.

In particular, the component simulation component comprises 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 the running environment of Windows and Linux dual operating systems. The loadable data file contains a function description file.

In an embodiment, optionally, performing a normalization process on the interface definition document to obtain an interface control document, includes: displaying interface data in the interface definition document to a user through a visualization tool, and acquiring a plurality of target interface data input by the user; the target interface data is interface data used for simulation; and respectively executing standardized processing on each target interface data based on the standard data structure to obtain an interface control document.

Specifically, the interface definition document includes various interface data of the aircraft component, and for example, the interface data includes real sensor interface data, power interface data, fault indication interface data, and the like. The simulation platform displays all interface data in the interface definition document to a user, the user accepts or rejects the interface data in the interface definition document, and the interface data supporting modeling and simulation, namely target interface data, is reserved. Illustratively, the target interface data includes interface data related to the data link, such as bus bar power supply interface data, stimulus logic interface data, and failure indication interface data, and, of course, includes input interface data and output interface data.

Because the data structures of the interface definition documents corresponding to different service systems have differences, the data structures of the interface definition documents are standardized. The standard data structure may be, for example, a name, a type, a unit, a description, a convention, a dimension, a refresh rate, a value range, an enumeration type, an initialization value, a signal name, an annotation, a communication type, and the like.

In one embodiment, the interface control document is optionally packaged as a tab and the tab is saved in a tab file. The tab describes connecting each component simulation assembly to establish simulation, and lists tab names respectively corresponding to each current modeling simulation product.

In an 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 accordingly, based on the function description file, the general simulation component is subjected to a packaging operation to obtain a component simulation component corresponding to the aircraft component, including: performing packaging operation on the general simulation component based on the performance data of the aircraft component to obtain a first simulation component; loading technical index data of the aircraft component into the first simulation assembly to obtain a second simulation assembly; and executing a verification operation on the second simulation component based on the real component data and the simulation component data corresponding to the second simulation component to obtain a successfully verified component simulation component.

Exemplary performance data includes performance curves and/or parameter values for performance parameters, such as, for example, a flight control system, including, but not limited to, maximum pitch angle, minimum pitch angle, maximum grade angle, minimum lift angle, maximum lift angle, minimum rudder angle, maximum rudder angle, on/off airspeed hold, setting a reference altitude in meters, setting a vertical speed reference in meters/second, and the like.

Wherein the first emulation component is capable of supporting parameter debugging and functional testing.

The specification data includes specification values and/or boundary values, which are used to define simulation requirements of the part simulation model.

Illustratively, 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, and the like, and the actual component parameters include, but is not limited to, actual input parameter data, actual output parameter data, and internal parameters of the actual aircraft component, and the like.

Fig. 2 is a flowchart of a method for generating a component simulation model according to an embodiment of the present invention. In this embodiment, the component simulation model includes a component simulation component including loadable data files and a high-level interface software library, and an interface control document. Specifically, the business system imports an eVTOL aircraft function requirement file, an eVTOL aircraft rule specification file and an interface definition document through a human-computer interface provided by the simulation platform. Selecting internal parameters of the first simulation assembly from the eVTOL aircraft function requirement file, namely performance data in the eVTOL aircraft function requirement file, wherein the performance data form a loadable data file. And executing packaging operation on the general simulation component according to the selected performance data to obtain a first simulation component. Loading technical index data in the eVTOL aircraft rule specification file into the first simulation assembly, creating a second simulation assembly, performing conformance verification on the second simulation assembly based on the real assembly data and the simulation assembly data of the second simulation assembly, and taking the second simulation assembly which is successfully verified as a component simulation assembly.

The method comprises the steps of obtaining an interface definition document from an eVTOL aircraft interface definition document storage area, selecting target interface data which are used for modeling and simulation support in the interface definition document, and respectively executing standardization processing on each target interface data based on a standard data structure to obtain an interface control document. Based on the interface control document, a component interface framework for the component simulation assembly is determined. When the document format of the interface definition document is a non-excel format, performing analysis operation on the interface definition document to obtain the interface definition document in the excel format.

And S130, in response to the detection of the simulation request, determining a current modeling simulation product based on at least one target component simulation model corresponding to the simulation request.

Specifically, when a plurality of target component simulation models are available, the output interface of one target component simulation model is connected with the input interface of another corresponding target component simulation model, and a current modeling simulation product is constructed.

And S140, executing simulation operation on the current modeling simulation product to obtain a simulation result corresponding to the simulation request.

In one embodiment, the simulation of the component simulation model follows a simulation control pattern. Wherein the simulation control pattern provides an entry point through functions and state machines to arrange simulations, the simulation control pattern consumes and produces data defined in the component simulation model that interacts with other component simulation models by configuring specific names.

The simulation time step is the special control input of the part simulation model, and can still be modified in the simulation operation process under the same allocation of the simulation control mode.

Fig. 3 is a flowchart of a simulation control mode according to an embodiment of the present invention. Specifically, the simulation control mode includes a loading mode, an initialization mode, a reloading mode, a running mode, an unloading mode, and an intermitting mode. The loading mode is used for loading data, opening files, loading configuration parameters of the component simulation model and establishing connection of a path where the component simulation model is located; an initialization mode for executing initialization input, internal and output values predefined by each component simulation model; a reload mode for resetting the input, internal and output values of each component simulation model, recalculated from external conditions; the operation mode is used for executing the circular calculation of the simulation program according to the fixed simulation step length; an intermittent mode for a mode defined opposite to the cyclic calculation of the running mode, but without performing the calculation; and the unloading mode is used for unloading data, closing files, unloading configuration parameters of the component simulation model and closing the connection of the path of the component simulation model.

Specifically, the simulation control mode starts from a loading mode, and jumps to an initialization mode after the loading is finished, the initialization mode judges whether the execution of the simulation control mode is finished, if so, jumps to a overloading mode, and if not, the initialization mode is continued until all target component simulation models in the current modeling simulation product are initialized. And the heavy-load mode can also judge whether the execution of the heavy-load mode is finished, and in the running process of the heavy-load mode, if the external conditions require the current modeling simulation product to be reinitialized, the heavy-load mode jumps to the initialization mode. And the operation mode executes infinite loop calculation according to a fixed simulation step length, and correspondingly jumps to an initialization mode, a reloading mode, an intermittent mode or an unloading mode if external conditions require the current modeling simulation product to reinitialize, reload again, stop or finish operation. And the pause mode executes infinite loop according to the fixed simulation step length without calculation, and correspondingly jumps to the initialization mode, the reloading mode, the running mode or the unloading mode if external conditions require the current modeling simulation product to reinitialize, reload, rerun or finish running. The external conditions mainly come from the operation of a human-computer interface of the simulation platform.

According to the technical scheme, a component simulation model corresponding to the aircraft component is determined based on a general simulation component, an acquired functional description file and an acquired interface definition document corresponding to the aircraft component for each aircraft component corresponding to the eVTOL aircraft, a current modeling simulation product is determined based on at least one target component simulation model corresponding to the simulation request in response to the detection of the simulation request, and a simulation operation is performed on the current modeling simulation product to obtain a simulation result.

Example two

Fig. 4 is a flowchart of a simulation method of an electric vertical takeoff and landing aircraft according to a second embodiment of the present invention, which further details "current modeling simulation product" in the above-described embodiment. As shown in fig. 4, the method includes:

s210, acquiring a function description file and an interface definition document corresponding to at least one aircraft part respectively.

The simulation platform is connected with a data transmission interface of the service system through a setting interface, and data interaction with the service system is realized. Exemplary business systems include, but are not limited to, original equipment manufacturers, operators, infrastructure providers, air service providers, maintenance service providers, training centers and training solution providers, regulatory agencies, and the like. Among other things, original equipment manufacturers are used to design and manufacture eVTOL aircraft and receive regulatory approval. Operators are used to procure or rent eVTOL aircraft from asset management companies, providing periodic or chartered services. Infrastructure providers are used to design takeoff positions, landing positions, and terminal facilities for eVTOL aircraft. The air navigation service provider is responsible for coordinating the movement of the eVTOL aircraft through controlled airspaces and preventing collisions to ensure safe and effective air traffic flow. And the maintenance service provider provides maintenance service for the eVTOL aircraft and ensures the airworthiness of the eVTOL aircraft. Training centers and training solution providers use the eVTOL aircraft to train pilots. The monitoring facility provides certification for the design, manufacture and operation of the eVTOL aircraft.

And S220, determining a component simulation model corresponding to the aircraft component based on the function description file, the interface definition document and the general simulation component corresponding to the aircraft component for each aircraft component.

And S230, when the simulation request is detected, acquiring the simulation flow of the last modeling simulation product corresponding to the simulation request.

In this embodiment, the current modeling simulation product is a desktop simulation device, a flight program trainer, a system integration test platform, an iron bird and a training simulator in sequence according to a preset simulation sequence.

Fig. 5 is a schematic diagram of a development mode of a life cycle of an eVTOL aircraft according to a second embodiment of the present invention. The left side of the V-shaped development mode is the demand and validation phase of the eVTOL aircraft. Specifically, the scientific research simulation equipment is simulation equipment loaded with a complete set of general simulation components, a new function is implanted into a certain general simulation component according to the requirements of commercial demonstration or scientific research concepts, and preview effect demonstration is performed, for example, a function of implanting SVO (Simplified flight Operations) into the general simulation component corresponding to the flight control system, and in the simulation process of the scientific research simulation equipment, a user can intuitively experience the driving and operation experience of the SVO. The scientific research simulation equipment can be used for researching and developing or testing general simulation components, and illustratively, operations such as concept design, control rate and key system selection can be performed. Specifically, the desktop simulation device is a simulation device loaded with any one target component simulation model, and can be used for assisting a research and development team of the eVTOL aircraft to select design concepts and technologies and assisting system design, for example, in a simulation environment, design and improvement are performed on an algorithm architecture of a component simulation model corresponding to a flight control system. Specifically, the flight program trainer provides functions such as a touch screen and a spatial position of a cockpit for simulation equipment loaded with a plurality of target component simulation models, and can be used for verifying and testing airplane logic and operation programs and performing man-machine efficacy evaluation due to the fact that the flight program trainer provides perception of the spatial position of the cockpit.

Wherein, the right side of the V-shaped development mode is the confirmation stage of the eVTOL aircraft. Specifically, the engineering simulation data package is a set including all component simulation models corresponding to a certain model of the eVTOL aircraft, and the engineering simulation data package is continuously iterated and perfected along with the life cycle of the eVTOL aircraft and is consistent with the equipment model selection time of the eVTOL aircraft. Specifically, the system integration test platform loads a certain real aircraft component and a part of component simulation models, and because the engineering simulation data packet is a process from scratch, the early form of the system integration test platform is a desktop simulation device loaded with a small number of component simulation models, and the system integration test platform can be evolved into a simulation device consistent with the form of a real eVTOL aircraft cockpit along with continuous iteration and perfection. The ferry is a simulation device with a full-size data link consistent with the eVTOL aircraft, besides a full set of engineering simulation data packets are loaded, the airborne system uses more real devices, and the cross-linking relation among the devices is consistent with the real eVTOL aircraft. Specifically, the training simulator is equipment for training a pilot after the eVTOL aircraft is airworthwhile, and can simulate the state of the eVTOL aircraft under special conditions such as faults and severe weather while simulating the operation of the eVTOL aircraft under normal conditions, so as to train the pilot to operate correctly and guarantee aviation safety.

In one embodiment, optionally, branch management is used to control and regulate the life cycle of the modeling simulation product of the eVTOL aircraft in the simulation platform. The branch management aims to record the evolution process of the modeling simulation product and ensure that a developer can carry out accurate product configuration in each life stage of the eVTOL aircraft.

In one embodiment, optionally, the branch management includes an engineering branch, a training branch, and a development branch. The engineering branch is used for testing and verifying airborne equipment in the development process of the eVTOL (unmanned aerial vehicle), and can provide valuable guidance for testing flight parameters of related equipment on the ground and assist airworthiness verification. The system is suitable for an engineering simulation data packet, a system integration test bench and a bird in a V mode; the training branch is used for training an eVTOL aircraft crew member and can include a plurality of simulations such as faults and special conditions, and finally, the mature product of the training branch can provide core simulation software for an eVTOL aircraft flight simulator manufacturer. The training simulator is suitable for the V mode; the development branch is used for testing new concepts, new designs and overall system architectures of the eVTOL aircraft, and is different from the engineering branch, and the final direction is used for verifying the feasibility of concept design. The flight simulator is suitable for scientific research simulation equipment, desktop simulation equipment and flight program trainers in a V mode.

Specifically, the simulation request is used for representing the simulation requirement of the current modeling simulation product, and the last modeling simulation product corresponding to the current modeling simulation product is determined according to a preset simulation sequence. For example, assuming that the current modeling simulation product corresponding to the simulation request is a flight procedure trainer, the last modeling simulation product is a desktop simulation device.

And S240, judging whether the simulation process is finished or not, if so, executing S250, and if not, executing S270.

In this embodiment, the plurality of modeling simulation products are continuously iterated and perfected according to the simulation process, and when the last modeling simulation product is mature, the simulation process of the current modeling simulation product is started.

In an exemplary embodiment, if the simulation input parameter and the real input parameter of the previous modeling simulation product and the simulation output parameter and the real output parameter are the same, the simulation process of the previous modeling simulation product is considered to be finished. Exemplary, simulation parameters include, but are not limited to, geometric appearance parameters, aerodynamic characteristic parameters, flight maneuver, powertrain parameters, navigation and guidance strategy parameters, instrument indicating parameters, airspace management parameters, airport and tarmac parameters, and the like.

And S250, determining a current modeling simulation product based on at least one target component simulation model corresponding to the simulation request.

And S260, executing simulation operation on the current modeling simulation product to obtain a simulation result corresponding to the simulation request.

And S270, executing simulation operation on the last modeling simulation product to obtain a simulation result corresponding to the simulation request.

On the basis of the foregoing embodiment, optionally, the simulation result of the current modeling simulation product includes an updated function description file and/or an updated interface definition document corresponding to at least one target component simulation model, and correspondingly, after performing the simulation operation on the current modeling simulation product to obtain the simulation result corresponding to the simulation request, the method further includes: and aiming at each target component simulation model, based on the updated function description file and/or the updated interface definition document corresponding to the target component simulation model, performing optimization operation on the target component simulation model to obtain the optimized target component simulation model.

Specifically, the target component simulation model is optimized, so that iteration and perfection of a modeling simulation product corresponding to the target component simulation model are realized.

Specifically, if the simulation result includes the updated function description file, the encapsulation operation is re-executed on the component simulation component in the target component simulation model based on the updated function description file. If the simulation result contains the updated interface definition document, generating an updated interface control document based on the updated interface definition document, and determining a component interface framework of the part simulation component based on the updated interface control document.

According to the technical scheme of the embodiment, when the simulation request is detected, whether the simulation process of the last current modeling simulation product corresponding to the simulation request is finished or not is judged, if yes, the current modeling simulation product is determined based on at least one target component simulation model corresponding to the simulation request, and further, according to the preset simulation sequence, the modeling simulation products in the simulation platform are set to be desktop simulation equipment, a flight program trainer, a system integration test bench, a ferrugo and a training simulator in sequence, so that the problem that the development and test processes of the eVTOL aircraft are unclear is solved, the full life cycle of design, development, integration, check and verification of the eVTOL aircraft is supported from the time dimension, and the simulation efficiency and the development efficiency of the eVTOL aircraft are further improved.

EXAMPLE III

Fig. 6 is a schematic structural diagram of a simulation apparatus of an electric vertical take-off and landing aircraft according to a third embodiment of the present invention. As shown in fig. 6, the apparatus includes: interface definition document acquisition module 310, component simulation model determination module 320, current modeled simulation product determination module 330, and simulation result determination module 340.

The interface definition document acquiring module 310 is configured to acquire a function description file and an interface definition document corresponding to at least one aircraft component, respectively; the function description file represents the function parameter information of the aircraft component, and the interface definition file represents the interface parameter information of the aircraft component;

a component simulation model determination module 320, configured to determine, for each aircraft component, a component simulation model corresponding to the aircraft component based on the functional description file, the interface definition document, and the general simulation component corresponding to the aircraft component;

a current modeling simulation product determination module 330, configured to, in response to detecting the simulation request, determine a current modeling simulation product based on the at least one target component simulation model corresponding to the simulation request;

and the simulation result determining module 340 is configured to execute a simulation operation on the current modeling simulation product to obtain a simulation result corresponding to the simulation request.

According to the technical scheme, a component simulation model corresponding to the aircraft component is determined based on a general simulation component, an acquired functional description file and an acquired interface definition document corresponding to the aircraft component for each aircraft component corresponding to the eVTOL aircraft, a current modeling simulation product is determined based on at least one target component simulation model corresponding to the simulation request in response to the detection of the simulation request, and a simulation operation is performed on the current modeling simulation product to obtain a simulation result.

On the basis of the foregoing embodiment, optionally, the component simulation model includes a component simulation component and an interface control document, and the component simulation model determining module 320 includes:

the interface control document determining unit is used for executing standardized processing on the interface definition document to obtain an interface control document and determining a component interface framework of the component simulation assembly based on the interface control document;

a component simulation assembly determination unit used for executing packaging operation on the general simulation assembly based on the function description file to obtain a component simulation assembly corresponding to the aircraft component

On the basis of the foregoing embodiment, optionally, the interface control document determining unit is specifically configured to:

displaying interface data in the interface definition document to a user through a visualization tool, and acquiring a plurality of target interface data input by the user; the target interface data is interface data used for simulation;

and respectively executing standardized processing on each target interface data based on the standard data structure to obtain an interface control document.

On the basis of the foregoing 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 determining unit is specifically configured to:

performing packaging operation on the general simulation component based on the performance data of the aircraft component to obtain a first simulation component;

loading technical index data of the aircraft component into the first simulation assembly to obtain a second simulation assembly;

and executing a verification operation on the second simulation component based on the real component data and the simulation component data corresponding to the second simulation component to obtain a successfully verified component simulation component.

On the basis of the above embodiment, optionally, the current modeling simulation product sequentially includes, according to a preset simulation sequence, a desktop simulation device, a flight program trainer, a system integration test bench, an ironbird and a training simulator, and the apparatus further includes:

the simulation process determining module is used for judging whether the simulation process of the last current modeling simulation product corresponding to the simulation request is finished or not before determining the current modeling simulation product based on at least one target component simulation model corresponding to the simulation request;

if so, determining the current modeling simulation product based on at least one target component simulation model corresponding to the simulation request.

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

and the target component simulation model optimization module is used for executing optimization operation on the target component simulation model based on the updated function description file and/or the updated interface definition document corresponding to the target component simulation model to obtain the optimized target component simulation model after executing simulation operation on the current modeling simulation product to obtain a simulation result corresponding to the simulation request.

On the basis of the foregoing embodiment, optionally, the interface definition document acquiring module 310 is specifically configured to:

responding to a received real simulation model corresponding to at least one aircraft part in the aircraft imported by the service system, and performing analysis operation on the real simulation model to obtain a function description file and an interface definition document corresponding to the at least one aircraft part;

and/or the presence of a gas in the gas,

and responding to the received function description file imported by the service system and the interface definition document in the non-excel format, and performing analysis operation on the interface definition document to obtain the interface definition document in the excel format.

The simulation device of the electric vertical take-off and landing aircraft provided by the embodiment of the invention can execute the simulation method of the electric vertical take-off and landing aircraft provided by any embodiment of the invention, and has corresponding functional modules and beneficial effects of the execution method.

Example four

Fig. 7 is a schematic structural diagram of an electronic device according to a fourth embodiment of the present invention. The electronic device 10 is intended to represent various forms of digital computers, such as laptops, desktops, workstations, personal digital assistants, servers, blade servers, mainframes, and other appropriate computers. The electronic device may also represent various forms of mobile devices, such as personal digital assistants, cellular phones, smart phones, wearable devices (e.g., helmets, glasses, watches, etc.), and other similar computing devices. The components shown herein, their connections and relationships, and their functions, are meant to be exemplary only, and are not meant to limit implementations of the inventions described and/or claimed herein.

As shown in fig. 7, the electronic device 10 includes at least one processor 11, and a memory communicatively connected to the at least one processor 11, such as a Read Only Memory (ROM)12, a Random Access Memory (RAM)13, and the like, wherein the memory stores a computer program executable by the at least one processor, and the processor 11 can perform various suitable actions and processes according to the computer program stored in the Read Only Memory (ROM)12 or the computer program loaded from a storage unit 18 into the Random Access Memory (RAM) 13. In the RAM 13, various programs and data necessary for the operation of the electronic apparatus 10 can also be stored. The processor 11, the ROM 12, and the RAM 13 are connected to each other via a bus 14. An input/output (I/O) interface 15 is also connected to the bus 14.

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, or the like; an output unit 17 such as various types of displays, speakers, and the like; a storage unit 18 such as a magnetic disk, an optical disk, or the like; and a communication unit 19 such as a network card, modem, wireless communication transceiver, etc. The communication unit 19 allows the electronic device 10 to exchange information/data with other devices via a computer network such as the internet and/or various telecommunication networks.

The processor 11 may be a variety of general and/or special purpose processing components having processing and computing capabilities. Some examples of processor 11 include, but are not limited to, a Central Processing Unit (CPU), a Graphics Processing Unit (GPU), various specialized Artificial Intelligence (AI) computing chips, various processors running machine learning model algorithms, a Digital Signal Processor (DSP), and any suitable processor, controller, microcontroller, or the like. The processor 11 performs the various methods and processes described above, such as a simulation method for an electric vertical take-off and landing aircraft.

In some embodiments, the method of simulating an electric vertical take-off and landing aircraft may be implemented as a computer program tangibly embodied in a computer-readable storage medium, such as the storage unit 18. In some embodiments, part or all of the computer program may be loaded and/or installed onto the electronic device 10 via the ROM 12 and/or the communication unit 19. When the computer program is loaded into RAM 13 and executed by processor 11, one or more steps of the method of simulating an electric vertical takeoff and landing aircraft described above may be performed. Alternatively, in other embodiments, the processor 11 may be configured by any other suitable means (e.g., by means of firmware) to perform the simulation method of the electric vertical takeoff and landing aircraft.

Various implementations of the systems and techniques described here above may be implemented in digital electronic circuitry, integrated circuitry, Field Programmable Gate Arrays (FPGAs), Application Specific Integrated Circuits (ASICs), Application Specific Standard Products (ASSPs), system on a chip (SOCs), load programmable logic devices (CPLDs), computer hardware, firmware, software, and/or combinations thereof. These various embodiments may include: implemented in one or more computer programs that are executable and/or interpretable on a programmable system including at least one programmable processor, which may be special or general purpose, receiving data and instructions from, and transmitting data and instructions to, a storage system, at least one input device, and at least one output device.

The computer program for implementing the simulation method of an electrically powered vertical takeoff and landing aircraft of the present invention may be written in any combination of one or more programming languages. These computer programs may be provided to a processor of a general purpose computer, special purpose computer, or other programmable data processing apparatus, such that the computer programs, when executed by the processor, cause the functions/acts specified in the flowchart and/or block diagram block or blocks to be performed. A computer program can execute entirely on a machine, partly on a machine, as a stand-alone software package partly on a machine and partly on a remote machine or entirely on a remote machine or server.

EXAMPLE five

An embodiment of the present invention further provides a computer-readable storage medium, where computer instructions are stored, and the computer instructions are used to cause a processor to execute a method for simulating an electric vertical take-off and landing aircraft, where the method includes:

acquiring a function description file and an interface definition file which respectively correspond to at least one aircraft part; the function description file represents the function parameter information of the aircraft component, and the interface definition file represents the interface parameter information of the aircraft component;

for each aircraft component, determining a component simulation model corresponding to the aircraft component based on the functional description file, the interface definition document and the general simulation component corresponding to the aircraft component;

in response to detecting the simulation request, determining a current modeling simulation product based on at least one target component simulation model corresponding to the simulation request;

and executing simulation operation on the current modeling simulation product to obtain a simulation result corresponding to the simulation request.

In the context of the present invention, a computer-readable storage medium may be a tangible medium that can contain, or store a computer program for use by or in connection with an instruction execution system, apparatus, or device. A computer readable storage medium may include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. Alternatively, the computer readable storage medium may be a machine readable signal medium. More specific examples of a machine-readable storage medium would include an electrical connection based on one or more wires, a portable computer diskette, 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 disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

To provide for interaction with a user, the systems and techniques described here can 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 a user; and a keyboard and a pointing device (e.g., a mouse or a trackball) by which a user can provide input to the electronic device. Other kinds of devices may also be used to provide for interaction with a user; for example, feedback provided to the user can 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, speech, or tactile input.

The systems and techniques described here can be implemented in a computing system that includes a back-end component (e.g., as a data server), or that includes a middleware component (e.g., an application server), or that includes a front-end component (e.g., a user computer having a graphical user interface or a web browser through which a user can interact with an implementation of the systems and techniques described here), or any combination of such back-end, middleware, or front-end components. The components of the system can be interconnected by any form or medium of digital data communication (e.g., a communication network). Examples of communication networks include: local Area Networks (LANs), Wide Area Networks (WANs), blockchain networks, and the internet.

The computing system may include clients and servers. A client and server are generally remote from each other and typically interact through a communication network. The relationship of client and server arises by virtue of computer programs running on the respective computers and having a client-server relationship to each other. The server can be a cloud server, also called a cloud computing server or a cloud host, and is a host product in a cloud computing service system, so that the defects of high management difficulty and weak service expansibility in the traditional physical host and VPS service are overcome.

It should be understood that various forms of the flows shown above may be used, with steps reordered, added, or deleted. For example, the steps described in the present invention may be executed in parallel, sequentially, or in different orders, and are not limited herein as long as the desired results of the technical solution of the present invention can be achieved.

The above-described embodiments should not be construed as limiting the scope of the invention. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions may be made in accordance with design requirements and other factors. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (10)

1. A simulation method of an electric vertical take-off and landing aircraft is characterized by comprising the following steps:

acquiring a function description file and an interface definition file which respectively correspond to at least one aircraft part; wherein the function description file characterizes function parameter information of the aircraft component, and the interface definition document characterizes interface parameter information of the aircraft component;

for each aircraft part, determining a part simulation model corresponding to the aircraft part based on the functional description file, the interface definition document and the general simulation component corresponding to the aircraft part;

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;

and executing simulation operation on the current modeling simulation product to obtain a simulation result corresponding to the simulation request.

2. The method of claim 1, wherein the component simulation model includes a component simulation component and an interface control document, and wherein determining the component simulation model corresponding to the aircraft component based on the functional description file, the interface definition document, and the generic simulation component corresponding to the aircraft component comprises:

Performing standardization processing on the interface definition document to obtain an interface control document, and determining a component interface framework of the component simulation assembly based on the interface control document;

and executing packaging operation on the general simulation assembly based on the function description file to obtain a component simulation assembly corresponding to the aircraft component.

3. The method of claim 2, wherein the performing the normalization process on the interface definition document to obtain an interface control document comprises:

displaying the interface data in the interface definition document to a user through a visualization tool, and acquiring a plurality of target interface data input by the user; wherein the target interface data is interface data for simulation;

and respectively executing standardization processing on the target interface data based on a standard data structure to obtain an interface control document.

4. The method according to claim 2, wherein 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 accordingly, the performing a packaging operation on the general simulation component based on the function description file to obtain a component simulation component corresponding to the aircraft component includes:

Performing packaging operation on the general simulation component based on the performance data of the aircraft component to obtain a first simulation component;

loading technical index data of the aircraft component into the first simulation assembly to obtain a second simulation assembly;

and executing a verification operation on the second simulation component based on the real component data and the simulation component data corresponding to the second simulation component to obtain a successfully verified component simulation component.

5. The method of claim 1, wherein the current modeled simulation product is sequentially a desktop simulation device, a flight procedure trainer, a system integration test bench, a bird, and a training simulator according to a predetermined simulation order, and wherein the method further comprises, prior to determining the current modeled simulation product based on the at least one target component simulation model corresponding to the simulation request:

judging whether the simulation process of the last current modeling simulation product corresponding to the simulation request is finished or not;

and if so, determining the current modeling simulation product based on at least one target component simulation model corresponding to the simulation request.

6. The method according to claim 1, wherein the simulation result of the current modeling simulation product includes an updated function description file and/or an updated interface definition document corresponding to at least one target component simulation model, respectively, and accordingly, after performing the simulation operation on the current modeling simulation product to obtain the simulation result corresponding to the simulation request, the method further includes:

And aiming at each target component simulation model, based on the updated function description file and/or the updated interface definition document corresponding to the target component simulation model, executing optimization operation on the target component simulation model to obtain the optimized target component simulation model.

7. The method according to any one of claims 1 to 6, wherein the obtaining of the function description file and the interface definition document corresponding to each of the at least one aircraft component comprises:

responding to a received real simulation model corresponding to at least one aircraft part imported by a service system, and performing analysis operation on the real simulation model to obtain a function description file and an interface definition document corresponding to the at least one aircraft part;

and/or the presence of a gas in the gas,

and responding to the received function description file imported by the service system and the interface definition document in the non-excel format, and performing analysis operation on the interface definition document to obtain the interface definition document in the excel format.

8. An apparatus for simulating an electric vertical take-off and landing aircraft, comprising:

the interface definition document acquisition module is used for acquiring a function description file and an interface definition document which respectively correspond to at least one aircraft component; wherein the function description file characterizes function parameter information of the aircraft component, and the interface definition document characterizes interface parameter information of the aircraft component;

The component simulation model determination module is used for determining a component simulation model corresponding to each aircraft component based on a function description file, an interface definition document and a general simulation component corresponding to the aircraft component;

the current modeling simulation product determining module is used for responding to the detection of the simulation request, and determining a current modeling simulation product based on at least one target component simulation model corresponding to the simulation request;

and the simulation result determining module is used for executing simulation operation on the current modeling simulation product to obtain a simulation result corresponding to the simulation request.

9. An electronic device, characterized in that the electronic device comprises:

at least one processor; and

a memory communicatively coupled to the at least one processor; wherein the content of the first and second substances,

the memory stores a computer program executable by the at least one processor to enable the at least one processor to perform the method of simulating an electric vertical take-off and landing aircraft of any one of claims 1-7.

10. A computer-readable storage medium, wherein the computer-readable storage medium stores computer instructions for causing a processor to implement the method of simulating an electric vertical take-off and landing aircraft of any one of claims 1-7 when executed.

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