Aircraft product simulation method supporting multi-mode calculation

Abstract

The invention relates to an aircraft product simulation method supporting multi-mode calculation, which comprehensively considers multiple factors such as function universality, compatibility and the like of an aircraft product model extension platform, and adopts echelon packaging and real-time scheduling technologies from the perspective of protecting an aircraft product control model. The first-stage package is a dynamic link library of two standard functions and five interaction components, and the second-stage package is an aircraft product integrated dynamic library containing a unique identification code. The access and replacement of different types of aircraft product component entities / models are supported, the aircraft product model extension calls the core function, calling of each component model can be realized, the requirements of real-time calculation of information such as anti-interference capability simulation motion trails, motion speeds and motion attitudes of different types of aircraft products are met, and the real-time calculation of the anti-interference capability simulation motion trails is realized. And analysis and distribution of open-loop data are supported, multi-mode aircraft product simulation is supported, and aircraft product model debugging time and cost can be effectively reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of semi-physical simulation systems, and mainly relates to an aircraft product simulation method supporting multi-mode solutions. Background Art

[0002] A semi-physical simulation system is generally composed of a virtual computer model and real hardware. It is an important means of system simulation technology. A semi-physical simulation system generally includes a simulation management extension, a simulator extension, a signal radiation extension, an attitude adjustment extension, an aircraft product model extension, etc. The basic premise of semi-physical simulation is that the computer model needs to meet strict real-time requirements, that is, the model running time must be consistent with natural time.

[0003] Aircraft products generally include measuring sensitive devices, command generation devices, control execution devices and other components. The semi-physical simulation of aircraft products mainly evaluates the working performance and overall control performance of aircraft products, among which the impact of the environment on aircraft products should be considered, mainly including the atmosphere, earth curvature, wind field, waves, as well as factors such as human interference and natural environment interference. Semi-physical simulation of aircraft products generally follows the principle of gradual progress, and carries out full digital closed-loop simulation (all aircraft products use mathematical models), partial closed-loop simulation (some components are physically introduced into the simulation loop, and some components use models instead of entities) and system closed-loop simulation (all equipment entities are introduced into the simulation loop).

[0004] As the natural environment and electromagnetic environment become more and more complex, the simulation of aircraft anti-interference ability is becoming more and more concerned. However, due to factors such as site, equipment layout, funding, and the complexity of the simulation system, the simulation of aircraft anti-interference ability generally introduces mathematical models of components such as power units, inertial measurement units, and satellite navigation, and conducts closed-loop simulation of angle measurement devices + command generation devices. Power units, inertial measurement units, satellite navigation, etc. are generally carried out separately. In this case, the aircraft product model extension occupies a very important position in the semi-physical simulation system, integrating models such as power units, inertial measurement units, and satellite navigation, outputting command information according to the command generation device model, and solving the motion trajectory, motion speed, motion posture, etc. of the flight actuator in real time to complete the simulation closed loop. The aircraft product model extension should realize three basic functions: first, it is connected to the aircraft product components or the corresponding physical effect mathematical models, and outputs the power unit command signal, angular velocity, angular acceleration and other information according to the simulation system beat; second, it can solve the flight actuator, target motion and aircraft-target relative motion; third, it outputs control instructions for the attitude adjustment extension, simulator extension, and signal radiation extension.

[0005] At present, in order to meet the simulation requirements of the anti-interference capability of specific aircraft products, the aircraft product model extension needs to be developed separately according to the composition and characteristics of the aircraft product, and cannot adapt to the closed-loop requirements of other types of aircraft products.

[0006] At present, in order to meet the simulation requirements of the anti-interference capability of specific aircraft products and solve the motion trajectory, motion speed, motion posture and other information of the flight actuator in real time, it is necessary to develop an aircraft product model extension that is adapted to this type of aircraft product separately, complete the component entity / model access, solution, data processing and other contents, generally design a specific aircraft product model extension, which is not universal and reconfigurable, and there are several problems: first, it cannot be adapted to other types of aircraft products; second, it is difficult to integrate with the simulation system for development and debugging, and faces the problems of inconsistent information interaction standards and inconsistent timing beats; third, the protection of the core product model, the aircraft product development unit will encapsulate the core control model, but the degree of encapsulation and how to call it are difficult to unify. In addition, in some open-loop test occasions, the motion trajectory data is directly provided, and how to unify it with the real-time solution mode is also a problem that needs to be solved. Summary of the invention

[0007] In order to overcome the above-mentioned deficiencies, the present invention provides an aircraft product simulation method supporting multi-mode solutions.

[0008] The technical solution adopted by the present invention to solve its technical problem is: A method for simulating an aircraft product supporting multi-mode solution comprises the following steps: Determine the usage pattern of the aircraft product model extension, If it is component entity / model access mode, execute step 1); If it is external open-loop data mode, execute step 2); Step 1) Encapsulate each module model that cannot be physically connected to the simulation system according to the general framework of two core functions and five core interaction components, so as to form several dynamic link libraries. Each dynamic link library exchanges information through two core functions and five core interaction components, and each module model can be run by calling the core function according to the requirements of the simulation system; the two core functions are: generation function and execution function; the five core interaction components are: initialization parameter component, simulation beat component, input parameter component, output parameter component, and state parameter component; on the basis of the first-level encapsulation dynamic link library, add a unique identification code to each module model, and schedule the model through the unique identification code; the scheduling function calls the generation function and execution function of the corresponding model on demand according to the unique identification code of the model, and configures the parameters of the core interaction components of the module model dynamic link library according to the parameter characteristics of each model dynamic library, and finally outputs a single model integrated dynamic library; receive the simulation beat-data parsing-data scheduling-data analysis process in a black box manner to complete the real-time solution and update of the actuator motion trajectory, motion speed, and motion posture information; Step 2) For open-loop test requirements, the component entity and model are no longer connected. The data analysis module analyzes the externally imported data frame by frame according to the standard protocol. The analyzed data contains the motion position, speed, attitude and angular velocity information of the aircraft and the target; the aircraft product and target information are output through the internal interface. The data distribution module receives the aircraft product and target information through the internal interface, and according to the timing interrupt, distributes the received information according to the aircraft product, target motion information and attitude information according to the frame period, and outputs it through the external interface.

[0009] The module models that cannot be physically connected to the simulation system include: an angle measurement device model, an instruction generation device model, a target motion model, an aircraft product-target motion model, an inertial measurement model, a satellite navigation model, a power device model and an aerodynamic model.

[0010] The generation function initializes the module model according to the simulation requirements, sets simulation parameters for the constructed module model, selects the model algorithm and configures the simulation environment to ensure that the model configuration matches the actual system components.

[0011] The execution function is used to receive the semi-physical simulation system time beat instructions according to the simulation beat component to solve the operation calls and parameter transmissions of each module model. The execution function adopts a standardized interface, the input parameters are obtained from the input parameter component, and the output parameters and state parameters are stored in the output parameter component and the state parameter component respectively.

[0012] Due to the adoption of the above-mentioned technical solution, the present invention has the following advantages: The present invention provides an aircraft product simulation method that supports multi-mode solution. The aircraft simulation model is encapsulated in stages, and supports the access and replacement of entities / models of different types of aircraft components. The aircraft product model extension calls the core function to realize the calling of each component model, thereby solving the need for real-time solution of information such as motion trajectory, motion speed, motion posture, etc. of the anti-interference capability simulation of different types of aircraft products, and supports the analysis and distribution of open-loop data, supports multi-mode aircraft simulation, and can effectively reduce the debugging time and cost of aircraft models. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is the overall framework diagram of the present invention; FIG2 is a schematic diagram of the first level packaging principle of the present invention; Figure 3 It is the second level packaging principle diagram of the present invention; Figure 4 This is a schematic diagram of the principle of the external open-loop data mode. DETAILED DESCRIPTION

[0014] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions 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 part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0015] A method for simulating an aircraft product supporting multi-mode solution is divided into a component entity / model access mode and an external open-loop data mode according to the usage mode of the aircraft product model extension, such as Figure 1 shown.

[0016] 1) Component entity / model access mode By comprehensively considering the functional versatility and compatibility of the aircraft product model extension platform and other factors, the hierarchical packaging and real-time scheduling technology are adopted. The first-level packaging focuses on the packaging of each module model of the aircraft product model extension, and the module models that cannot be physically connected to the simulation system are packaged according to the general framework of two core functions and five core interactive components, thereby forming several dynamic link libraries. Each dynamic link library exchanges information through two core functions and five core interactive components, and calls the core function according to the requirements of the simulation system to run each module model. The first-level packaging is as follows: Figure 2 As shown. The two core functions are: generation function and execution function; the five core interaction components are: initialization parameter component, simulation beat component, input parameter component, output parameter component, and state parameter component; (1) Generating function The generation function initializes the module according to the simulation requirements and configures the constructed model.

[0017] Model initialization includes the initialization of each module model in the aircraft product model extension, including the angle measurement device model, inertial measurement model, satellite navigation model, instruction generation device model, power device model, aerodynamic model, target motion model, and aircraft product-target motion model; Configure the model, including setting simulation parameters, selecting model algorithms, and configuring the simulation environment. Ensure that the model configuration matches the actual system components to obtain accurate simulation results.

[0018] (2) Execute function The execution function is used to receive the time beat instructions of the semi-physical simulation system according to the simulation beat component to solve the operation calls and parameter transmissions of each module. The execution function adopts a standardized interface. The input parameters are obtained from the input parameter component, and the output parameters and state parameters are stored in the output parameter component and the state parameter component respectively.

[0019] The second level of encapsulation focuses on solving the scheduling problem of each model. On the basis of the first level of encapsulation of the dynamic link library, a unique identification code is added to each module model, and the model is scheduled through the unique identification code. The scheduling function calls the generation function and execution function of the corresponding model on demand according to the unique identification code of the model, and configures the parameters of the core interactive components of the model dynamic library according to the parameter characteristics of each model dynamic library, and finally outputs a single aircraft model integrated dynamic library, such as Figure 3 As shown. The simulation beat-data analysis-data scheduling-data analysis process is received in a black box mode to complete the real-time calculation and update of the actuator motion trajectory, motion speed, motion posture and other information. For external open-loop data, data analysis is directly performed and data scheduling is completed.

[0020] 2) External open-loop data mode For open-loop test requirements, component entities and models are no longer connected. The data analysis module obtains external data files through the external interface, performs data analysis, and outputs aircraft and target information through the internal interface. The data distribution module receives aircraft and target information through the internal interface, distributes the received information according to aircraft and target motion information and attitude information according to the frame period according to the timing interrupt, and outputs it through the external interface, such as Figure 4 shown.

[0021] (1) External data analysis Parse the externally imported data frame by frame according to the standard protocol, which generally includes the motion position, speed, attitude, and angular velocity information of the aircraft product and the target; (2) Data allocation In response to the timing beat of the simulation management extension, the motion position, speed, and attitude information of the aircraft product and the target will be sent to the relative motion model according to the frame period for it to solve the line of sight angle, relative motion relationship and other information. The aircraft product attitude information will be sent to the control instruction model to solve the attitude adjustment extension control instruction information.

[0022] By comprehensively considering the functional versatility and compatibility of the aircraft product model extension platform and other factors, from the perspective of protecting the aircraft control model, the hierarchical packaging and real-time scheduling technology is adopted. The first-level packaging is a dynamic link library of two standard functions + five interactive components ("5+2" dynamic link library), and the second-level packaging is an aircraft module integrated dynamic library with a unique identification code. The aircraft product model extension schedules the aircraft component model in real time according to the identification code, and completes the real-time calculation and data distribution of the actuator motion trajectory, motion speed, motion posture and other information in the form of a black box, and supports the analysis and distribution of open-loop data.

[0023] The parts not described in detail in the above content are prior art, so they are not described in detail.

Claims

1. An aircraft product simulation method supporting multi-mode solution, characterized in that: The steps include: Determine the usage pattern of the aircraft product model extension, If it is component entity / model access mode, execute step 1); If it is external open-loop data mode, execute step 2); Step 1) Encapsulate each module model that cannot be physically connected to the simulation system according to the general framework of two core functions and five core interaction components, so as to form several dynamic link libraries. Each dynamic link library exchanges information through two core functions and five core interaction components, and each module model can be run by calling the core function according to the requirements of the simulation system; the two core functions are: generation function and execution function; the five core interaction components are: initialization parameter component, simulation beat component, input parameter component, output parameter component, and state parameter component; on the basis of the first-level encapsulation dynamic link library, add a unique identification code to each module model, and schedule the model through the unique identification code; the scheduling function calls the generation function and execution function of the corresponding model on demand according to the unique identification code of the model, and configures the parameters of the core interaction components of the module model dynamic link library according to the parameter characteristics of each model dynamic library, and finally outputs a single aircraft product model integrated dynamic library; receive the simulation beat-data analysis-data scheduling-data analysis process in a black box manner to complete the real-time solution and update of the actuator motion trajectory, motion speed, and motion posture information; Step 2) For open-loop test requirements, the component entity and model are no longer connected. The data analysis module analyzes the externally imported data frame by frame according to the standard protocol. The analyzed data contains the motion position, speed, attitude and angular velocity information of the aircraft product and the target; the aircraft product and target information is output through the internal interface. The data distribution module receives the aircraft product and target information through the internal interface, and according to the timing interrupt, the received information is distributed according to the aircraft product, target motion information and attitude information according to the frame period, and outputs it through the external interface.

2. The aircraft product simulation method supporting multi-mode solution according to claim 1, characterized in that: The module models that cannot be physically connected to the simulation system include: an angle measurement device model, an instruction generation device model, a target motion model, an aircraft product-target motion model, an inertial measurement model, a satellite navigation model, a power device model and an aerodynamic model.

3. The aircraft product simulation method supporting multi-mode solution according to claim 2, characterized in that: The generation function initializes the module model according to the simulation requirements, sets simulation parameters for the constructed module model, selects the model algorithm and configures the simulation environment to ensure that the model configuration matches the actual system components.

4. The aircraft product simulation method supporting multi-mode solution according to claim 2, characterized in that: The execution function is used to receive the semi-physical simulation system time beat instructions according to the simulation beat component to solve the operation calls and parameter transmissions of each module model. The execution function adopts a standardized interface, the input parameters are obtained from the input parameter component, and the output parameters and state parameters are stored in the output parameter component and the state parameter component respectively.

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