Full-process information flow test method and system based on electric Glink bus architecture

Abstract

The invention discloses a full-process information flow test method based on an electric Glink bus architecture. The method comprises the steps that a comprehensive test system sends a take-off ground instruction to a simulation test system; after the simulation test system receives the take-off ground instruction, inertial measurement unit pulse data and integrated navigation data are calculated; the data are output to a flight control computer through a Glink bus; the flight control computer generates a servo instruction according to the data and outputs the servo instruction to the simulation test system; the simulation test system simulates servo characteristics to obtain a servo actual swing angle and further obtain data for next cycle calculation; and the simulation test system monitors and stores all simulation information, and obtains the working state of the whole-flow electric Glink bus. The invention further discloses a system for implementing the method. The method can capture, monitor, store and analyze the information flow in the whole process of the aircraft, verifies the stability of the working state of the electric Glink bus and the reliability of data in the whole process of an aircraft control system, and has a wide application prospect.

Description

Technical Field

[0001] This invention relates to a full-process information flow testing method and system based on the electric Glink bus architecture, belonging to the field of aircraft control system testing technology. Background Technology

[0002] The electric Glink bus is a communication bus that has emerged and been used in recent years. However, no method has yet been proposed to verify the stability of its working state, the reliability of its data, the correctness of the design of the control system algorithm, and the rationality of its parameters in the aircraft control system. Summary of the Invention

[0003] The purpose of this invention is to overcome the above-mentioned defects and provide a full-process information flow testing method and system based on the electric Glink bus architecture. This solves the technical problem that it is currently impossible to experimentally verify the application status of the electric Glink bus in aircraft control systems. This invention constructs a full-process information flow verification architecture for the electric Glink bus, which can simulate the full-process information flow control system data during the entire flight process of an aircraft. It can capture, monitor, store, and analyze the information flow in the entire process, verify the stability of the electric Glink bus working state, the reliability of the data, and the correctness of the control algorithm design scheme and the rationality of parameter selection in the entire process of the aircraft control system. It has broad application prospects.

[0004] To achieve the above-mentioned objectives, the present invention provides the following technical solution: A full-process information flow testing method based on the electrical Glink bus architecture includes: The integrated test system sends takeoff ground commands to the simulation test system; After receiving the takeoff ground command, the simulation test system simulates the inertial navigation system (INS) to obtain INS pulse data and integrated navigation data; the INS pulse data and integrated navigation data are then output to the flight control computer via the Glink bus. The flight control computer performs calculations based on inertial group pulse data and integrated navigation data, generates servo commands, and outputs the servo commands to the simulation test system via the Glink bus; The simulation test system simulates servo characteristics, calculates the actual servo swing angle based on servo commands, simulates the inertial navigation system based on the actual servo swing angle, and obtains inertial navigation pulse data and integrated navigation data for the next cycle calculation. The simulation test system monitors and stores all simulation information throughout the entire flight process of the aircraft. By parsing the stored data offline, it obtains the working status of the electric Glink bus in the entire process of the aircraft control system, and verifies the stability of the electric Glink bus operation status and the reliability of the bus data.

[0005] Furthermore, the simulation test system is used to simulate the inertial navigation system by calculating a six-degree-of-freedom dynamic model and a motion equation model.

[0006] Furthermore, the simulation test system includes a time clock, an electrical Glink NT node, and an electrical Glink MT node; The time synchronization clock is used to ensure time synchronization between the simulation test system and the flight control computer; The electrical Glink NT node is used for electrical Glink bus data exchange between the flight control computer and the integrated test system; The electric Glink MT node is used to capture, monitor, store, and analyze the entire process of the electric Glink bus.

[0007] Furthermore, the flight control computer is used to aggregate electrical Glink bus data; The flight control computer is responsible for running the control algorithm and communicating with the simulation test system via the Glink bus to verify the rationality of the control algorithm design and the correctness of the parameter selection.

[0008] Furthermore, the flight control computer is equipped with an electrical Glink bus listening port; The electrical Glink bus listening port is connected to the electrical Glink MT node of the simulation test system, transmitting all data from the electrical Glink bus to the electrical Glink MT node for listening and storage.

[0009] Furthermore, the integrated testing system is ground-based equipment.

[0010] Furthermore, the inertial navigation system pulse data includes gyroscope pulse data and table pulse data; Integrated navigation data includes aircraft position and velocity, satellite pseudorange and pseudorange rate.

[0011] Furthermore, the simulation test system accesses all simulation information through a single NT node; All simulation information includes inertial navigation pulse data, integrated navigation data, timing signals, and servo command information.

[0012] A full-process information flow test system based on an electric Glink bus architecture is used to implement the aforementioned full-process information flow test method based on an electric Glink bus architecture, including a simulation test system, an integrated test system, and a flight control computer; The integrated test system sends takeoff ground commands to the simulation test system; After receiving the takeoff ground command, the simulation test system simulates the inertial navigation system (INS) to obtain INS pulse data and integrated navigation data; the INS pulse data and integrated navigation data are then output to the flight control computer via the Glink bus. The flight control computer performs calculations based on inertial group pulse data and integrated navigation data, generates servo commands, and outputs the servo commands to the simulation test system via the Glink bus; The simulation test system simulates servo characteristics, calculates the actual servo swing angle based on servo commands, simulates the inertial navigation system based on the actual servo swing angle, and obtains inertial navigation pulse data and integrated navigation data for the next cycle calculation. The simulation test system monitors and stores the inertial pulse data and integrated navigation data throughout the entire flight process of the aircraft. By performing offline analysis on the stored data, the system obtains the working status of the electric Glink bus in the entire process of the aircraft control system, and verifies the stability of the electric Glink bus operation status and the reliability of the bus data.

[0013] This invention constructs a full-process information flow verification architecture for the electric Glink bus, which can simulate the full-process information flow control system data of an aircraft during flight. It can capture, monitor, store, and analyze the information flow throughout the entire process, verifying the stability of the electric Glink bus working state, the reliability of the data, the correctness of the control algorithm design scheme, and the rationality of the parameter selection in the entire process of the aircraft control system.

[0014] Compared with the prior art, the present invention has at least one of the following advantages: (1) The present invention constructs a full-process information flow verification architecture for the electric Glink bus, integrates the electric Glink bus between the simulation test system, the integrated test system and the flight control computer, simulates the information flow during the flight process on the ground, and verifies the information transmission of the electric Glink bus in flight state; (2) This invention adds an electrical Glink bus MT node to the simulation test system to realize the capture, monitoring, storage and analysis of all data of the Glink bus; (3) This invention performs dual-function verification of communication function and control algorithm at the same time, which verifies the stability of bus operation status and the reliability of bus data, and verifies the correctness of control algorithm design scheme and the rationality of parameter selection. Attached Figure Description

[0015] Figure 1 This is a diagram of the full-process information testing architecture of the Glink bus in this invention. Detailed Implementation

[0016] The features and advantages of the present invention will become clearer and more apparent from the following detailed description.

[0017] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments. Although various aspects of embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless specifically indicated otherwise.

[0018] This invention relies on the electric Glink bus to test the entire process information of the aircraft control system, and to evaluate the correctness of the control system's working state in the entire mission process. It mainly evaluates the stability and reliability of the electric Glink bus, the correctness of the control algorithm design scheme, and the rationality of parameter selection.

[0019] Figure 1 The diagram shows the full-process information testing architecture of the Glink bus. The test equipment is divided into three parts: simulation test system, integrated test system, and flight control computer.

[0020] The simulation test system includes a synchronization clock, an electric Glink NT node, and an electric Glink MT node. This system is responsible for calculating the six-degree-of-freedom dynamics and equations of motion models. The synchronization clock supplies the flight control computer, ensuring time synchronization between the two devices at a period of 5ms, thus guaranteeing the accuracy of the six-degree-of-freedom dynamics and equations of motion calculations. The electric Glink NT node is responsible for the electric Glink bus data exchange with the flight control computer and the integrated test system, including inertial navigation pulse data, integrated navigation data, timing signals, servo commands, and ground commands. The electric Glink MT node can capture, monitor, store, and analyze the entire electric Glink bus process.

[0021] The flight control computer is a data aggregation device for the electric Glink bus. It is mainly responsible for running control algorithms, communicating with the model in the simulation test system via the electric Glink bus, and verifying the rationality of the control algorithm design and the correctness of the parameter selection. The electric Glink bus listening port is connected to the electric Glink MT node of the simulation test system, and transmits all data of the electric Glink bus to the electric Glink MT node for listening and storage.

[0022] The integrated test system, a ground-based device, is primarily responsible for testing the flight control computer and sending ground commands such as takeoff. After the integrated test system sends the takeoff ground command, the simulation test system begins model calculations, and simultaneously, the flight control computer's control algorithm starts running. These three devices work collaboratively to simulate the entire flight process of the aircraft, capturing, listening to, storing, and analyzing the full flow of information from the electrical Glink bus during flight.

[0023] After the integrated test system sends the takeoff ground command, the simulation test system performs six-degree-of-freedom dynamics and motion equation model calculations for the aircraft, simulating the inertial navigation system (INS) model. It calculates the angle increment, apparent velocity increment, aircraft body angular rate and Mach number, angle of attack, sideslip angle, and altitude. Then, it sends the INS pulse data and integrated navigation data to the flight control system via the Glink bus. The flight control computer's control algorithm completes navigation, guidance, and attitude control calculations, generates servo commands, and sends them back to the simulation test system via the Glink bus. The simulation test system simulates servo characteristics, calculates the actual servo swing angle, and inputs it into the six-degree-of-freedom dynamics and motion equation model for the next cycle calculation. Data throughout the flight process is monitored and stored through the electrical Glink MT node of the simulation test system. Offline analysis of the data stored in the MT node is performed to obtain the electrical Glink bus operating status throughout the entire control system process, verifying the stability of the bus operation and the reliability of the bus data. Simultaneously, it verifies the correctness of the control algorithm design and the rationality of the parameter selection.

[0024] This invention constructs a full-process information flow verification architecture for the electric Glink bus. Based on the comprehensive electrical testing of the control system, it connects to a simulation test system. By injecting simulation information, it can realize the information flow during the simulated flight process on the ground, and verify the information transmission of the electric Glink bus in flight mode.

[0025] The simulation test system accesses all simulation information through an NT node, including inertial navigation pulse data, integrated navigation data, timing signals, servo command information, etc. It realizes the injection of flight status information with minimal changes to the system connection, and simulates the entire process of information flow control system data during the entire flight process. Adding an electric Glink bus MT node to the simulation test system enables the capture, monitoring, storage, and analysis of all Glink bus data.

[0026] By performing offline parsing and analysis on the data stored in the MT node, the working status of the electric Glink bus in the entire process of the control system is obtained, the stability of the bus operation status and the reliability of the bus data are verified, and the correctness of the control algorithm design scheme and the rationality of the parameter selection are also verified.

[0027] The present invention has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present invention. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and embodiments of the present invention without departing from the spirit and scope of the invention, and all such modifications and improvements fall within the scope of the present invention. The scope of protection of the present invention is defined by the appended claims.

[0028] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A method for testing the entire information flow based on the electrical Glink bus architecture, characterized in that, include: The integrated test system sends takeoff ground commands to the simulation test system; After receiving the takeoff ground command, the simulation test system simulates the inertial navigation system (INS) to obtain INS pulse data and integrated navigation data; the INS pulse data and integrated navigation data are then output to the flight control computer via the Glink bus. The flight control computer performs calculations based on inertial group pulse data and integrated navigation data, generates servo commands, and outputs the servo commands to the simulation test system via the Glink bus; The simulation test system simulates servo characteristics, calculates the actual servo swing angle based on servo commands, simulates the inertial navigation system based on the actual servo swing angle, and obtains inertial navigation pulse data and integrated navigation data for the next cycle calculation. The simulation test system monitors and stores all simulation information throughout the entire flight process of the aircraft. By parsing the stored data offline, it obtains the working status of the electric Glink bus in the entire process of the aircraft control system, and verifies the stability of the electric Glink bus operation status and the reliability of the bus data.

2. The full-process information flow testing method based on the electrical Glink bus architecture according to claim 1, characterized in that, The simulation test system is used to simulate inertial navigation systems by calculating a six-degree-of-freedom dynamic model and a motion equation model.

3. The full-process information flow testing method based on the electrical Glink bus architecture according to claim 1, characterized in that, The simulation test system includes a time synchronization clock, an electrical Glink NT node, and an electrical Glink MT node; The time synchronization clock is used to ensure time synchronization between the simulation test system and the flight control computer; The electrical Glink NT node is used for electrical Glink bus data exchange between the flight control computer and the integrated test system; The electric Glink MT node is used to capture, monitor, store, and analyze the entire process of the electric Glink bus.

4. The full-process information flow testing method based on the electrical Glink bus architecture according to claim 1, characterized in that, The flight control computer is used to collect data from the electrical Glink bus; The flight control computer is responsible for running the control algorithm and communicating with the simulation test system via the Glink bus to verify the rationality of the control algorithm design and the correctness of the parameter selection.

5. The full-process information flow testing method based on the electrical Glink bus architecture according to claim 1, characterized in that, The flight control computer is configured with an electrical Glink bus listening port; The electrical Glink bus listening port is connected to the electrical Glink MT node of the simulation test system, transmitting all data from the electrical Glink bus to the electrical Glink MT node for listening and storage.

6. The full-process information flow testing method based on the electrical Glink bus architecture according to claim 1, characterized in that, The integrated testing system is ground-based equipment.

7. The full-process information flow testing method based on the electrical Glink bus architecture according to claim 1, characterized in that, Inertial navigation system pulse data includes gyro pulse data and table pulse data; Integrated navigation data includes aircraft position and velocity, satellite pseudorange and pseudorange rate.

8. The full-process information flow testing method based on the electrical Glink bus architecture according to claim 1, characterized in that, The simulation test system accesses all simulation information through a single NT node; All simulation information includes inertial navigation pulse data, integrated navigation data, timing signals, and servo command information.

9. A full-process information flow testing system based on the electrical Glink bus architecture, characterized in that, The method for implementing the full-process information flow test method based on the electrical Glink bus architecture as described in any one of claims 1-8 includes a simulation test system, an integrated test system, and a flight control computer; The integrated test system sends takeoff ground commands to the simulation test system; After receiving the takeoff ground command, the simulation test system simulates the inertial navigation system (INS) to obtain INS pulse data and integrated navigation data; the INS pulse data and integrated navigation data are then output to the flight control computer via the Glink bus. The flight control computer performs calculations based on inertial group pulse data and integrated navigation data, generates servo commands, and outputs the servo commands to the simulation test system via the Glink bus; The simulation test system simulates servo characteristics, calculates the actual servo swing angle based on servo commands, simulates the inertial navigation system based on the actual servo swing angle, and obtains inertial navigation pulse data and integrated navigation data for the next cycle calculation. The simulation test system monitors and stores the inertial pulse data and integrated navigation data throughout the entire flight process of the aircraft. By performing offline analysis on the stored data, the system obtains the working status of the electric Glink bus in the entire process of the aircraft control system, and verifies the stability of the electric Glink bus operation status and the reliability of the bus data.

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