CN116679585A

CN116679585A - Ground comprehensive test equipment, method, device, equipment and medium for flight control system

Info

Publication number: CN116679585A
Application number: CN202310610865.9A
Authority: CN
Inventors: 叶彩红; 吕良博; 陈亮; 王晓坡; 张彪; 黄伟; 杨颖涛; 汪孝锋; 郭小龙; 涂青青; 王勇
Original assignee: Beijing Huali Zhifei Technology Co ltd
Current assignee: Beijing Huali Zhifei Technology Co ltd
Priority date: 2023-05-26
Filing date: 2023-05-26
Publication date: 2023-09-01

Abstract

The invention relates to the technical field of computer simulation, and discloses ground comprehensive test equipment, method, device and medium of a flight control system, wherein the comprehensive test equipment comprises: the test management system is used for providing different simulation test configurations for a preset test stage of the flight control system and controlling and managing data of the simulation model and the test configuration of the flight control system; the comprehensive wiring system is connected with the flight control system and is used for switching different simulation test environments according to different simulation test configurations; the flight state simulation system is respectively connected with the test management system and the comprehensive wiring system, and is used for receiving simulation test signals of the test management system, providing an operation platform for a simulation test configuration and providing a simulation test signal interface for the comprehensive wiring system. The invention solves the comprehensive test configuration requirement that the current ground test equipment cannot be fully covered without a flight control system in the early design stage and a real flight control system is connected into a test loop in the later development stage.

Description

Ground comprehensive test equipment, method, device, equipment and medium for flight control system

Technical Field

The invention relates to the technical field of computer simulation, in particular to ground comprehensive test equipment, method, device and medium of a flight control system.

Background

The flight control system (for short, flight control system) is one of the core airborne subsystems of aircrafts such as military or civil aircrafts, unmanned aircrafts, bullets and the like, is an important link and core work in the development stage for the development of aircrafts with high technical complexity, and is an important link in the development process of aircrafts by carrying out flight simulation test on the ground and comprehensively detecting and verifying the functions and performances of the flight control system.

The comprehensive test and verification platform of the flight control system is built on the ground, the functions of flight control strategy verification, flight control algorithm verification, flight performance research, flight efficiency evaluation and the like are realized, and the comprehensive test and verification platform has important effects on improving the overall performance of the aircraft, improving the flight quality and improving the safety and reliability, and provides guarantee for the flight safety of the aircraft, so that the ground semi-physical simulation test and verification equipment of the flight control system is very important.

The prior ground test equipment based on the flight control system can provide a professional flight simulation and flight control algorithm real-time operation platform, but can not provide hardware resources to access the real flight control system hardware equipment, or only concentrate on the specific stage of V-shaped development of the flight control system, so that the comprehensive test equipment penetrating through the full life cycle of V-shaped development of the flight control system is needed, and the comprehensive test equipment can meet the comprehensive test configuration requirement that the full coverage does not have the flight control system in the early design stage and the real flight control system is accessed to a test loop in the later development stage.

Disclosure of Invention

In view of the above, the embodiment of the invention provides a ground comprehensive test device, a method, a device, equipment and a medium for a flight control system, which are used for solving the problem that the current ground test device cannot be fully covered with the comprehensive test configuration requirement that the flight control system is not arranged in the early design stage and the real flight control system is connected into a test loop in the later development stage.

In a first aspect, an embodiment of the present invention provides a ground comprehensive test apparatus for a flight control system, including:

the test management system is used for providing different simulation test configurations for a preset test stage of the flight control system and controlling and data managing the simulation model and the simulation test configuration of the flight control system;

the comprehensive wiring system is connected with the flight control system and is used for switching different simulation test environments according to the different simulation test configurations;

the flight state simulation system is respectively connected with the test management system and the comprehensive wiring system, and is used for receiving simulation test signals of the test management system, providing an operation platform for simulation test configuration and providing a simulation test signal interface for the comprehensive wiring system.

According to the ground comprehensive test equipment of the flight control system, different simulation test configurations are provided in a preset flight control system test stage through the test management system, the different simulation test configurations run on the flight state simulation system, different simulation test environments are switched through the test configurations of the comprehensive wiring system, the comprehensive test function of the flight control system on the ground is completed according to the simulation and test task requirements of the flight control system in different test stages, the ground comprehensive test equipment of the flight control system penetrates through the full life cycle of V-shaped development of the flight control system, and the problem that the current ground test equipment cannot fully cover the comprehensive test configuration requirements of the flight control system in the early design stage and the real flight control system is connected into a test loop in the later development stage is solved.

With reference to the first aspect, in one embodiment, the flight control system includes a flight control computer and an external crosslinking device; the simulation model of the flight control system comprises a flight control simulation model and an external crosslinking equipment simulation model; the test management system comprises:

the model management unit is used for managing the flight control simulation model and the external cross-linking equipment simulation model;

the simulation control unit is used for sending simulation test signals to the flight state simulation system and the test configuration management unit;

the test configuration management unit is in communication connection with the flight state simulation system, and is used for receiving simulation test signals of the simulation control unit, providing simulation test configurations according to the simulation test signals and carrying out switching management on the simulation test configurations; the simulation test configuration comprises: the full-digital real-time simulation test configuration of the simulation test is carried out between the flight control simulation model and the external crosslinking equipment simulation model, the external crosslinking equipment is connected into the rapid control prototype simulation test configuration of the simulation test in the flight control simulation model, the flight control computer is connected into the hardware-in-loop semi-physical simulation test configuration of the simulation test in the external crosslinking equipment simulation model, and the flight control calculation and the external crosslinking equipment are connected into the semi-physical comprehensive simulation test configuration of the simulation test in the external crosslinking equipment simulation model.

According to the ground comprehensive test equipment of the flight control system, through the full-digital real-time simulation test configuration for simulation tests between the flight control simulation model and the external cross-linking equipment simulation model provided by the test management system, the external cross-linking equipment is connected into the rapid control prototype simulation test configuration for simulation tests in the flight control simulation model, the flight control computer is connected into the hardware-in-loop semi-physical simulation test configuration for simulation tests in the external cross-linking equipment simulation model, and the flight control calculation and the external cross-linking equipment is connected into the semi-physical comprehensive simulation test configuration for simulation tests in the external cross-linking equipment simulation model, the simulation and test task requirements of each development stage such as full-digital, rapid control prototype, hardware-in-loop semi-physical comprehensive simulation and the like are met, the full life cycle of development of the flight control system is covered, and the semi-physical simulation comprehensive test verification hardware equipment is provided.

In an alternative embodiment, a flight status simulation system includes:

the flight control engine is used for receiving the simulation test signals of the test configuration management unit and providing an operation platform for the simulation test configuration;

and the external interface is used for providing a simulation test signal interface for the comprehensive wiring system.

The ground comprehensive test equipment of the flight control system provided by the embodiment of the invention provides a real-time operation platform for simulation models such as flight simulation, flight control algorithm and the like through the flight state simulation system, and provides a simulation test signal interface for the comprehensive wiring system, thereby realizing the simulation and signal acquisition of signals of the flight control system and external crosslinking equipment.

In an alternative embodiment, an integrated wiring system includes:

the first interface adaptation box is connected with the flight control engine through an external interface; the first interface adaptation box is used for receiving simulation test signals transmitted by the flight control engine, branching the simulation test signals according to different simulation test configurations, and transmitting the branched simulation test signals to the first signal switching box and/or the second signal switching box;

the first signal switching box is used for automatically switching the simulation test environment between the flight control simulation model and the flight control computer according to the simulation test signal;

the second signal switching box is connected with the first signal switching box and is used for automatically switching the simulation test environment between the external cross-linking equipment simulation model and the external cross-linking equipment according to the simulation test signal;

the second interface adaptation box is respectively connected with the first signal switching box and the second signal switching box; the second interface adaptation box is used for accessing the flight control computer and the external crosslinking equipment into corresponding simulation test environments according to the simulation test configuration.

According to the ground comprehensive test equipment of the flight control system, which is provided by the embodiment of the invention, the real-time simulation environment is physically connected with the equipment of the flight control system of the aircraft through the first interface adaptation box and the second interface adaptation box of the comprehensive wiring system, and different simulation test environments are switched by the first signal switching box and the second signal switching box aiming at different test stages of the flight control system, so that the simulation and test task requirements of all-digital, rapid control prototypes, hardware in various development stages such as a ring semi-physical object, a semi-physical object and the like can be completed.

In an alternative embodiment, the integrated test device further comprises a test cable system comprising a test cable and a network cable;

the test cable is used for connecting the flight control system simulation model with the flight control system and/or the external crosslinking equipment and connecting the external crosslinking equipment simulation model with the flight control system and/or the external crosslinking equipment;

the network cable is used for connecting the test management system with the flight state simulation system and connecting the flight state simulation system with the comprehensive wiring system.

According to the ground comprehensive test equipment for the flight control system, provided by the embodiment of the invention, the test cable of the test cable system is used for realizing the connection between the simulation model of the flight control system and the flight control system, the network cable is used for realizing the connection between the test management system and the flight state simulation system and the connection between the flight state simulation system and the comprehensive wiring system, and signal transmission support is provided for switching different simulation test environments in different test stages of the flight control system.

In a second aspect, an embodiment of the present invention provides a ground comprehensive test method for a flight control system, which is applied to the ground comprehensive test device for a flight control system according to the first aspect or any one of the corresponding embodiments of the first aspect, where the comprehensive test method includes:

acquiring a preset flight control system test stage;

and sending a simulation test signal according to the test stage of the flight control system, providing a simulation test configuration according to the simulation test signal, and automatically switching the simulation test environment according to the simulation test configuration.

According to the ground comprehensive test method for the flight control system, different simulation test configurations are provided by presetting different test stages of the flight control system, the different simulation test configurations run on the flight state simulation system, different simulation test environments are switched through the test configurations of the comprehensive wiring system, the comprehensive test function of the flight control system on the ground is completed according to the simulation and test task requirements of the flight control system in different test stages, the ground comprehensive test method for the flight control system penetrates through the full life cycle of V-shaped development of the flight control system, and the problem that the current ground test equipment cannot fully cover the comprehensive test configuration requirements of the flight control system in the early design stage and the real flight control system is connected into a test loop in the later development stage is solved.

In an alternative embodiment, the acquiring a predetermined flight control system test phase includes:

the method comprises the steps of acquiring a flight simulation development and flight control algorithm design test stage, a flight control algorithm verification test stage, a flight control cross-linking design and verification test stage and a semi-physical ground comprehensive simulation test stage which are sequentially carried out.

In an alternative embodiment, the method for automatically switching the simulation test environment according to the simulation test configuration includes the steps of:

transmitting a full-digital real-time simulation test signal in the flight simulation development and flight control algorithm design test stage, providing a full-digital real-time simulation test configuration according to the full-digital real-time simulation test signal, and accessing the flight control simulation model and an external cross-linking equipment simulation model into a simulation test environment to perform the full-digital real-time simulation test;

transmitting a rapid control prototype simulation test signal in a flight control algorithm verification test stage, providing a rapid control prototype simulation test configuration according to the rapid control prototype simulation test signal, and accessing external crosslinking equipment into a flight control simulation model to perform a rapid control prototype simulation test;

Transmitting a hardware-in-loop semi-physical simulation test signal in the flight control crosslinking design and verification test stage, providing a hardware-in-loop semi-physical simulation test configuration according to the hardware-in-loop semi-physical simulation test signal, and connecting a flight control computer into an external crosslinking equipment simulation model to perform a hardware-in-loop semi-physical simulation test;

and transmitting a semi-physical comprehensive simulation test signal in a semi-physical ground comprehensive simulation test stage, providing a semi-physical comprehensive simulation test configuration according to the semi-physical comprehensive simulation test signal, and connecting the flight control calculation and the external crosslinking equipment into an external crosslinking equipment simulation model to perform the semi-physical comprehensive simulation test.

The ground comprehensive test method of the flight control system provided by the embodiment of the invention is used for developing an early stage of flight simulation development and flight control algorithm design test stage, establishing a flight simulation and flight control model at the stage, providing a simulation platform for model operation, constructing a full-digital flight simulation environment, and simultaneously realizing the process of quickly verifying the flight control algorithm along with the verification of a quick control prototype (Rapid Control Prototype, RCP) in the quality assurance simulation test stage. In the middle development stage of the flight control system, namely the flight control cross-linking design and verification test stage, the hardware design and production of the flight control system core equipment, namely the flight control computer, are completed, the cross-linking simulation environment of the flight control computer is built, the development and verification of the flight control computer are realized, hardware resources are provided for accessing the real flight control computer, the semi-physical simulation test environment of the hardware in the loop is built, namely the test verification is carried out on the design and analysis results, so as to confirm whether the development requirement of the flight control system is met. In the later development stage of the flight control system, namely in the semi-physical ground comprehensive simulation test stage, the real equipment of the external crosslinking equipment is connected and matched with the simulation model of the external crosslinking equipment, so that a semi-physical ground comprehensive simulation test environment is constructed, the functions and the flight performance of the flight control system are comprehensively and comprehensively verified, the V-shaped development full life cycle of the flight control system is covered, and the flight simulation of the flight control system on the ground, the flight control strategy verification, the flight control performance verification function and the flight performance comprehensive test function of the flight control system are completed.

In a third aspect, an embodiment of the present invention provides a ground comprehensive test device for a flight control system, which is applied to the ground comprehensive test device for a flight control system according to the first aspect or any one of the corresponding embodiments, where the comprehensive test device includes:

the acquisition module is used for acquiring a preset flight control system test stage;

the control module is used for sending a simulation test signal according to the test stage of the flight control system, providing a simulation test configuration according to the simulation test signal, and automatically switching the simulation test environment according to the simulation test configuration.

In a fourth aspect, an embodiment of the present invention provides a computer apparatus, including: the system comprises a memory and a processor, wherein the memory and the processor are in communication connection, the memory stores computer instructions, and the processor executes the computer instructions so as to execute the ground comprehensive test method of the flight control system in the second aspect or any corresponding implementation mode.

In a fifth aspect, an embodiment of the present invention provides a computer readable storage medium, where computer instructions are stored on the computer readable storage medium, where the computer instructions are configured to cause a computer to perform the ground integrated test method of the flight control system according to the second aspect or any implementation manner corresponding to the second aspect.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.

FIG. 1 is a block diagram of a ground integrated test apparatus for a flight control system according to some embodiments of the invention;

FIG. 2 is a block diagram of the hardware architecture of another flight control system ground integrated test device in accordance with some embodiments of the invention;

FIG. 3 is a block diagram of a connection relationship of an all-digital real-time simulation test configuration of a ground integrated test device of a flight control system according to some embodiments of the invention;

FIG. 4 is a block diagram of the functional modules of the ground integrated test equipment of the flight control system according to some embodiments of the invention;

FIG. 5 is a block diagram of the functional modules of the flight control system ground integrated test equipment according to some embodiments of the invention;

FIG. 6 is a block diagram of a different test phase of a V-type of another flight control system ground integrated test device in accordance with some embodiments of the invention;

FIG. 7 is a schematic diagram of an all-digital real-time simulation test of another flight control system ground integrated test apparatus in accordance with some embodiments of the invention;

FIG. 8 is a block diagram of a connection relationship of an all-digital real-time simulation test configuration of another flight control system ground comprehensive test device according to some embodiments of the invention;

FIG. 9 is a schematic diagram of a rapid control prototype simulation test of a ground integrated test apparatus of a flight control system in accordance with some embodiments of the present invention;

FIG. 10 is a block diagram of a connection relationship of a rapid control prototype simulation test configuration of a ground integrated test apparatus of a flight control system in accordance with some embodiments of the present invention;

FIG. 11 is a schematic diagram of a hardware-in-the-loop semi-physical simulation test of a ground integrated test device of a flight control system according to some embodiments of the invention;

FIG. 12 is a block diagram of a hardware-in-the-loop semi-physical simulation test configuration connection relationship of a ground integrated test device of a flight control system according to some embodiments of the invention;

FIG. 13 is a schematic diagram of a semi-physical comprehensive simulation test of a ground comprehensive test apparatus of a flight control system in accordance with some embodiments of the invention;

FIG. 14 is a structural block diagram of a connection relationship of a flight control system ground integrated test device semi-physical integrated simulation test configuration in accordance with some embodiments of the present invention;

FIG. 15 is a flow chart of a method of ground integrated testing of a flight control system according to some embodiments of the invention;

FIG. 16 is a flow chart of another flight control system ground integrated test method according to some embodiments of the invention;

FIG. 17 is a block diagram of a ground integrated test device for a flight control system in accordance with an embodiment of the present invention;

fig. 18 is a schematic diagram of a hardware structure of a computer device according to an embodiment of the present invention.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

In this embodiment, a ground comprehensive test device for a flight control system is provided, the flight control system is an aircraft for recording short of the flight control system, fig. 1 is a structural block diagram of the ground comprehensive test device for the flight control system, and as shown in fig. 1, the comprehensive test device includes:

The test management system 11 is used for providing different simulation test configurations for a preset test stage of the flight control system, and controlling and data managing the simulation model and the simulation test configuration of the flight control system; specifically, referring to fig. 6, the preset flight control system test stage is of a V-shaped design, and includes: the early development stage (i.e. the left side of the V-shape) is the design and development stage, and a model for flight simulation and flight control needs to be established for the experimental stage of flight simulation development and flight control algorithm design, a simulation platform for model operation is provided, an all-digital flight simulation environment is built, and meanwhile, the rapid verification process of the flight control algorithm is realized along with the verification of a quality assurance activity-rapid control prototype (Rapid Control Prototype, RCP). In the middle development stage (namely the right side of the V shape) of the flight control system, namely the flight control cross-linking design and verification test stage, the hardware design and production of the flight control system core equipment-the flight control computer are completed at the stage, the flight control algorithm verification test of the flight control computer is realized, a flight control computer cross-linking simulation environment is required to be built, hardware resources are provided to be connected to the real flight control computer, and the hardware in-loop semi-physical simulation test environment is built, namely the test and verification are carried out on the design and analysis results so as to confirm whether the development requirement of the flight control system is met. In the later development stage (V-shaped right side) of the flight control system, namely in the semi-physical ground comprehensive simulation test stage, the real equipment of the external crosslinking equipment is connected, and the connection with the external equipment such as an angular rate gyroscope, an air pressure sensor, an inertial navigation equipment, a navigation simulator, an atmospheric data simulator and the like in the external crosslinking equipment is integrated, so that a semi-physical ground test environment can be constructed, and the functions and the flight performance of the flight control system can be comprehensively verified. With reference to fig. 2 and 3, the test management system is implemented by adopting a conventional industrial personal computer PC-01, and a control and management functional module is designed on the conventional industrial personal computer PC-01, so that different simulation test configurations are provided for a preset test stage of the flight control system, and the simulation model and the simulation test configuration of the flight control system are controlled and data managed.

The comprehensive wiring system 12 is connected with the flight control system 14 and is used for switching different simulation test environments according to different simulation test configurations; specifically, with reference to fig. 2 and 3, the integrated wiring system 12 includes devices such as an interface adaptation box and a signal switcher, so that a real-time simulation environment can be physically connected with an airborne flight control system of an aircraft and an external crosslinking device, and the interface adaptation box and the signal switcher can switch different simulation test environments according to different simulation test configurations.

The flight state simulation system 13 is respectively connected with the test management system and the comprehensive wiring system, and is used for receiving simulation test signals of the test management system, providing an operation platform for a simulation test configuration and providing a simulation test signal interface for the comprehensive wiring system. Specifically, with reference to fig. 2 and fig. 3, the flight state simulation system 13 adopts a simulation integrated machine, and includes a high-performance flight control engine board, an analog quantity, a digital quantity, a serial port, various avionics buses, a hardware interface board and other hardware resource boards, and a real-time operating system and board driving are installed on the high-performance flight control engine board, so as to provide a real-time operation platform for simulation models such as flight simulation and flight control algorithm, and realize simulation and signal acquisition of signals of crosslinked peripheral devices of the flight control system.

In an alternative embodiment, flight control system 14 includes a flight control computer and an external crosslinking device; the simulation model of the flight control system comprises a flight control simulation model and an external crosslinking equipment simulation model; the external crosslinking apparatus includes: the flight control system and external test equipment needing crosslinking comprise hardware equipment of a sensor and an actuating mechanism, a satellite navigation simulator and equipment to be tested of a three-axis table.

The test management system 11 includes:

the model management unit is used for managing the flight control simulation model and the external cross-linking equipment simulation model; specifically, with reference to fig. 4, the master control management software of the ground comprehensive test equipment of the flight control system adopts simulation test comprehensive test verification Software (SIVB) to realize unified management and debugging, and is installed on the test management system 11, wherein the simulation models comprise a flight control simulation model and an external cross-linking equipment simulation model, and include management of system models such as an angular rate gyro sensor, an atmospheric sensor, a satellite navigation simulator and a three-axis turntable, so as to realize management of the flight control simulation model and the external cross-linking equipment simulation model, support functions such as loading and compiling of the simulation models, support various modeling environments such as visual business Matlab simulation, complex system modeling and simulation platform amosimilim, multidisciplinary domain system simulation similitude, multidisciplinary system simulation platform dymium, and formation micro resistivity scanning imaging FMI, support loading of different simulation models according to different test configurations, and manage the simulation models.

The simulation control unit is used for sending simulation test signals to the flight state simulation system and the test configuration management unit, specifically sending simulation test signals to the flight state simulation system and the test configuration management unit according to the simulation test configuration, and realizing control management of the flight simulation test, and comprises the functions of simulation engineering management, simulation configuration management, simulation system management, simulation operation management, simulation parameter management and the like.

The test configuration management unit is in communication connection with the flight state simulation system, and is used for receiving simulation test signals of the simulation control unit, providing simulation test configurations according to the simulation test signals and carrying out switching management on the simulation test configurations; the simulation test configuration comprises: the full-digital real-time simulation test configuration of the simulation test is carried out between the flight control simulation model and the external crosslinking equipment simulation model, the external crosslinking equipment is connected into the rapid control prototype simulation test configuration of the simulation test in the flight control simulation model, the flight control computer is connected into the hardware-in-loop semi-physical simulation test configuration of the simulation test in the external crosslinking equipment simulation model, and the flight control calculation and the external crosslinking equipment are connected into the semi-physical comprehensive simulation test configuration of the simulation test in the external crosslinking equipment simulation model. Specifically, the test configuration management unit can provide switching management of 4 test configurations such as a full-digital real-time simulation test, a rapid control prototype, a hardware-in-loop semi-physical test, a semi-physical comprehensive test and the like, and realize a model configuration function of 4 different configurations, a parameter mapping function of different configurations and a test configuration management function.

The trial management system 11 further includes:

automated test unit: the automatic test unit is connected with the test configuration management unit and is used for automatically executing the simulation test in all development stages of the full-digital real-time simulation test, the rapid control prototype, the hardware-in-loop semi-physical test, the semi-physical comprehensive test and the like, so that the functions of importing test cases, editing, automatically executing, generating test reports and the like are realized.

A data management unit: the data management unit is connected with the automatic test unit and is used for monitoring and collecting simulation test data, modifying test parameters on line, storing and analyzing the test data and the like.

The communication between the test management system 11 and the flight state simulation system 12 is shown in fig. 5, the model management unit in the test management system 11 imports different simulation test models into the simulation control unit, and the simulation control unit sends simulation test signals to the test configuration management unit and the flight control engine of the flight state simulation system according to the test stage of the flight control system, and the test configuration management unit provides corresponding simulation test configurations. The automatic test unit realizes the automatic execution of the full-digital real-time simulation test, the rapid control prototype, the hardware simulation test in various development stages such as the ring semi-physical test, the semi-physical comprehensive test and the like, and realizes the functions of importing test cases, editing, automatically executing, generating test reports and the like. The data management unit is used for realizing the functions of monitoring, collecting, modifying test parameters on line, storing and analyzing the test data and the like of the simulation test data.

The test management system provided by the embodiment of the invention has the functions of controlling and managing the simulation test, managing the simulation model, switching the test configuration, automatically testing, managing the test data and the like, has a man-machine interaction main control interface for operating, configuring and managing the simulation test of the flight control system, can perform starting and stopping management of the simulation test process, can configure the flight control computer simulation model and the external cross-linking equipment simulation model according to different system architectures, can configure simulation computer signal resources, provides various monitoring controls, and can optionally monitor the connection of the controls and physical signals.

In an alternative embodiment, the flight status simulation system 12 includes: the flight control engine is used for receiving the simulation test signals of the test configuration management unit and providing an operation platform for the simulation test configuration;

the external interface is used for providing a simulation test signal interface for the comprehensive wiring system, and particularly, the external interface is realized by adopting a hardware interface board card, and the simulation test signal interface is provided for the comprehensive wiring system, so that the simulation and signal acquisition of signals of the flight control system and the external crosslinking equipment are realized.

In an alternative embodiment, the integrated wiring system 13 includes:

The first interface adaptation box LB-01 is connected with the flight control engine through an external interface; the first interface adaptation box is used for receiving simulation test signals transmitted by the flight control engine, branching the simulation test signals according to different simulation test configurations, and transmitting the branched simulation test signals to the first signal switching box and/or the second signal switching box; specifically, referring to fig. 2 and 3, the first interface adaptation box LB-01 receives a simulation test signal transmitted by the flight control engine, converts the simulation test signal into an interface in a form of SCSI (Small Computer System Interface ) and/or DB (D data interface), and branches signals related to an atmospheric sensor, an angular rate gyro, and the like in a simulation flight control computer and an external crosslinking device in the flight control system; the simulation test signal is converted into a standard aviation plug signal and a third party test monitoring signal which are connected with real-part equipment such as a flight control system or external crosslinking equipment, and the split simulation test signal is transmitted to the first signal switching box SW-01 and/or the second signal switching box SW-02.

The first signal switching box SW-01 is used for automatically switching the simulation test environment between the flight control simulation model and the flight control computer according to the simulation test signal; specifically, referring to fig. 2 and 3, the first signal switching box SW-01 includes a first terminal, a first common terminal and a second terminal; the first signal switching box SW-01 realizes the simulation test signal switcher through the first terminal, the first common terminal and the second terminal, comprises the switching of 2 states of the flight control simulation model and the flight control computer, and provides a switching control program to realize the automatic switching of the flight control computer hardware equipment and the flight control simulation model.

The second signal switching box SW-02 is connected with the first signal switching box and is used for automatically switching the simulation test environment between the external cross-linking equipment simulation model and the external cross-linking equipment according to the simulation test signal; specifically, referring to fig. 2 and 3, the second signal switching box SW-02 includes a third terminal, a second common terminal and a fourth terminal; the second signal switching box SW-02 realizes a simulation test signal switcher through a third terminal, a second common terminal and a fourth terminal, comprises an external crosslinking device simulation model and switching of 2 states of an external crosslinking device real part, realizes switching of the external crosslinking device simulation test signal and equipment such as an atmosphere sensor, an angular rate gyroscope and an executing mechanism in the external crosslinking device, provides a switching control program, and realizes automatic switching of the external crosslinking device hardware equipment real part and the simulation model.

The second interface adaptation box LB-02 is respectively connected with the first signal switching box and the second signal switching box; the second interface adaptation box is used for accessing the flight control computer and the external crosslinking equipment into corresponding simulation test environments according to the simulation test configuration. Specifically, with reference to fig. 2 and 3, the simulation test signals switched by the first signal switching box SW-01 and/or the second signal switching box SW-02 are converted into standard aviation plug signal forms connected with the finished product real piece equipment, namely, the flight control computer and the external crosslinking equipment are connected into corresponding simulation test environments according to simulation test configurations, so that the real airborne flight control computer, an atmospheric sensor in the external crosslinking equipment, an angular rate gyro and an executing mechanism are connected into the simulation test environments.

the test cable is used for connecting the flight control system simulation model with the flight control system and/or the external crosslinking equipment and connecting the external crosslinking equipment simulation model with the flight control system and/or the external crosslinking equipment; specifically, the test cable is also called a real part cable, and is used for connecting the flight control system simulation model and the flight control system, connecting the flight control system simulation model and the external crosslinking device, and also used for connecting the external crosslinking device simulation model and the flight control system, and connecting the external crosslinking device simulation model and the external crosslinking device, so as to realize cable connection among the flight control system simulation model, the external crosslinking device simulation model, the flight control system and the real part device of the external crosslinking device.

The network cable is used for connecting the test management system with the flight state simulation system and connecting the flight state simulation system with the comprehensive wiring system. Specifically, the network cable is realized by adopting test network hardware equipment and consists of accessories such as a reflective memory card, an Ethernet switch, an optical fiber cable and the like, so that the communication connection between the test management system and the flight state simulation system and the communication connection between the flight state simulation system and the comprehensive wiring system are realized; the hardware support is provided for transmitting the simulation test signals between the test management system and the flight state simulation system and transmitting the simulation test signals between the flight state simulation system and the comprehensive wiring system.

As one or more specific application embodiments of the embodiment of the invention, the ground generalized test equipment of the flight control system provided by the embodiment of the invention can meet the requirement of comprehensive simulation tests of each simulation test stage in the V-shaped development flow of the flight control system, and as shown in FIG. 6, the simulation test stages comprise a flight simulation development and flight control algorithm design test stage, a flight control algorithm verification test stage, a flight control cross-linking design and verification test stage and 4 semi-physical ground comprehensive simulation test stages which are sequentially carried out. Specifically:

(1) And a flight simulation development and flight control algorithm design test stage: providing flight simulation and flight control simulation, and realizing a full-digital real-time simulation test environment by using a full-digital real-time simulation test configuration;

(2) And a flight control algorithm verification test stage: accessing real external crosslinking equipment, and realizing a rapid control prototype simulation test environment of the flight control system by using a rapid control prototype simulation test configuration;

(3) Flight control crosslinking design and verification test stage: accessing a real flight control computer, and realizing a flight control system hardware-in-loop semi-physical simulation test environment by using a hardware-in-loop semi-physical simulation test configuration;

(4) Semi-physical ground comprehensive simulation test stage: the method is connected with a real flight control computer and a part of real external cross-linking equipment, and the semi-physical ground comprehensive simulation test environment of the flight control system is realized by using a semi-physical ground comprehensive simulation test configuration.

In an alternative implementation mode, in the initial stage of development of the flight control system, namely the stage of flight simulation development and flight control algorithm design test, flight simulation development and flight control logic design are required, a full-digital real-time simulation test environment is provided, and the development of models supporting a flight simulation model, flight control system control logic, a flight control algorithm, an external cross-linking equipment simulation model, such as an atmospheric sensor, an angular rate gyro and the like, is operated. The full-digital real-time simulation working principle diagram is shown in fig. 7, at this stage, the simulation control unit sends full-digital real-time simulation test signals, the test configuration management unit provides full-digital real-time simulation test configurations, the automatic test and data management functions are provided to realize the full-digital real-time simulation test functions, the flight state simulation system provides a platform for model real-time operation, and the full-digital real-time simulation test environment of the flight control system is constructed. The hardware connection relation of the all-digital real-time simulation test is shown in fig. 8. At this time, a first terminal of a first signal switching box SW-01 of the integrated wiring system is connected to the flight control system simulation model, a first terminal is connected to a first common terminal, the first common terminal is connected to a second common terminal of a second signal switching box SW-02, the second common terminal is connected to a third terminal of the second signal switching box SW-02, and the third terminal is connected to the external crosslinking apparatus simulation model. In the test stage, the simulation management control unit sends a full-digital real-time simulation test signal, the test configuration management unit provides a full-digital real-time simulation test configuration according to the full-digital real-time simulation test signal, and the comprehensive wiring system and the test cable are configured to access the fly-control simulation model and simulation models such as an atmospheric sensor, an angular rate gyroscope and the like in the external crosslinking equipment into a simulation test environment according to the full-digital real-time simulation test configuration to perform the full-digital real-time simulation test.

In an alternative embodiment, after the full digital real-time simulation test stage is completed, the construction of the flight control algorithm and the development of the flight control simulation model are completed, and then the flight control algorithm needs to be verified by establishing a rapid control prototype simulation test configuration. The method comprises the steps of establishing a rapid control prototype simulation test configuration, simulating a flight control simulator through the flight control simulation model, supporting the operation of a flight control algorithm logic model, configuring a hardware interface to be connected with real external crosslinking equipment, and realizing the simulation and verification of the flight control algorithm logic and performance through a simulation test. The working principle diagram of the development of the rapid control prototype simulation test configuration is shown in fig. 9. In the stage of the rapid control prototype simulation test, the connection relationship of the rapid control prototype simulation test configuration is shown in fig. 10, and the flight control algorithm is to be rapidly verified, at this time, the first terminal of the first signal switching box SW-01 of the integrated wiring system is connected with the flight control system simulation model, the first terminal is connected with the first common terminal, the first common terminal is connected with the second common terminal of the second signal switching box SW-02, the second common terminal is connected with the fourth terminal of the second signal switching box SW-02, and the fourth terminal is connected with the external crosslinking device. In the test stage, the simulation control unit sends a rapid control prototype simulation test signal, the test configuration management unit provides a rapid control prototype simulation test configuration according to the rapid control prototype simulation test signal, provides automatic test and data management functions to realize the rapid control prototype simulation test function, and configures the comprehensive wiring system and the test cable to connect real parts such as an atmospheric sensor, an angular rate gyro and the like in the external crosslinking equipment into the flight control simulation model for simulation test according to the rapid control prototype simulation test configuration.

In an alternative implementation mode, after the flight control algorithm verification is completed, the development and production stage of the flight control computer is entered, and after the hardware entity of the flight control computer is developed, the interface design, function and performance of the flight control computer are required to be tested and verified, so that the hardware-in-the-loop semi-entity simulation test environment of the flight control computer is built. The method comprises the steps of establishing a hardware-in-loop semi-physical simulation environment, simulating flight simulation of an aircraft through a real-time simulation model and external cross-linking equipment simulation, providing a hardware resource interface by a flight state simulation system, switching between a flight control simulation model and a flight control system by a comprehensive wiring system, and accessing a real flight control computer. And the interface design, the function and the performance of the flight control computer are tested and verified through a simulation test. The working principle diagram of the hardware-in-the-loop semi-physical simulation test is shown in fig. 11. Under the hardware-in-loop semi-physical simulation test configuration, the connection relation of the flight control computer hardware in the loop semi-physical simulation test configuration is shown in fig. 12. The interface design, function and performance of the flight control computer are tested and verified. At this time, the second terminal of the first signal switching box SW-01 of the integrated wiring system is connected to the flight control system, the second terminal is connected to the first common terminal, the first common terminal is connected to the second common terminal of the second signal switching box SW-02, the second common terminal is connected to the third terminal of the second signal switching box SW-02, and the third terminal is connected to the external crosslinking apparatus simulation model. In the test stage, a simulation control unit sends a hardware-in-loop semi-physical simulation test signal, a test configuration management unit provides a hardware-in-loop semi-physical simulation test configuration according to the hardware-in-loop semi-physical simulation test signal, and provides functions of automatic test, test data monitoring and the like, a flight state simulation system provides a flight control system cross-linking environment simulation operation platform, comprises a flight simulation model, an inertial measurement unit, a navigation model, a sensor and other simulation models, provides a hardware interface, and configures a comprehensive wiring system and a test cable to access a real flight control computer according to the hardware-in-loop semi-physical simulation test configuration to construct a hardware-in-loop simulation test environment.

In an alternative embodiment, after the interface, function and performance test verification of the flight control computer is completed, the flight control computer is required to be placed in a real airborne environment, and is connected with a real external cross-linking device to construct a semi-physical comprehensive simulation test environment, so that the comprehensive function and performance verification of the flight control computer is realized.

The method comprises the steps of establishing a hardware-in-loop semi-physical simulation environment, simulating flight simulation of an aircraft through a real-time simulation model, enabling a flight control system to crosslink external equipment, providing a hardware resource interface and a comprehensive wiring unit, and accessing a real flight control computer. And the interface design, the function and the performance of the flight control computer are tested and verified through a simulation test.

In the semi-physical comprehensive simulation test stage, a real airborne flight control computer is connected into a test loop, and meanwhile, a hardware interface and a comprehensive wiring system support part are provided for butt joint of real flight control crosslinking system equipment. In this stage, the external crosslinking devices such as a real flight control computer, a real atmospheric sensor, an angular rate gyro and the like are supported to be connected through the comprehensive wiring system and the test configuration management system. The working principle diagram of the semi-physical comprehensive simulation test is shown in fig. 13. Under the configuration, the environment of the flight control computer on the aircraft is simulated as truly as possible, the real flight control computer is accessed, and the real flight control computer can be accessed as much as possible, so that the comprehensive test and verification of the flight control computer are realized. The connection relation of the semi-physical comprehensive simulation test system is shown in fig. 14. At this time, the second terminal of the first signal switching box SW-01 of the integrated wiring system is connected to the flight control system, the first terminal and the second terminal are both connected to the first common terminal, the first common terminal is connected to the second common terminal of the second signal switching box SW-02, the second common terminal is connected to the third terminal and the fourth terminal of the second signal switching box SW-02, the third terminal is connected to the external crosslinking apparatus simulation model, and the fourth terminal is connected to the external crosslinking apparatus. In the test stage, the simulation control unit sends a semi-physical comprehensive simulation test signal, the test management system provides a semi-physical comprehensive simulation test configuration according to the semi-physical comprehensive simulation test signal, and provides functions of automatic test, data monitoring and the like, the flight state simulation system provides a real-time operation platform for part of flight simulation, and the comprehensive wiring system and the test cable are configured to access flight control calculation and external crosslinking equipment (a real inertial measurement unit, a receiver and an atmospheric system sensor) into an external crosslinking equipment simulation model according to the semi-physical comprehensive simulation test signal to perform a semi-physical comprehensive simulation test.

In the semi-physical comprehensive simulation test, the simulation systems such as a flight control system, a three-axis table of external crosslinking equipment, an atmospheric data sensor, a navigation simulator and the like can be integrated to complete the semi-physical comprehensive simulation test. And (3) accessing part of airborne equipment or part of real objects such as an inertial measurement unit, an atmospheric sensor and the like into a semi-physical comprehensive simulation test environment to complete a semi-physical comprehensive crosslinking test, and restoring the real environment of the flight control system on the aircraft as much as possible, thereby comprehensively verifying the functions and performances of the flight control system on the ground.

Fig. 15 is a flowchart of a ground comprehensive test method of a flight control system according to an embodiment of the present invention, as shown in fig. 15, the flowchart includes the steps of:

step S101, acquiring a preset flight control system test stage, specifically, acquiring a preset flight control system test stage includes acquiring a flight simulation development and flight control algorithm design test stage, a flight control algorithm verification test stage, a flight control cross-linking design and verification test stage, and 4 stages of a semi-physical ground comprehensive simulation test stage, where a V-shaped diagram of the flight control system test stage is shown in fig. 6.

Step S102, a simulation test signal is sent according to a test stage of the flight control system, a simulation test configuration is provided according to the simulation test signal, a simulation test environment is automatically switched according to the simulation test configuration, specifically, different simulation test signals are sent according to a preset simulation control management unit in a test management system of different test stages of the flight control system, different simulation test configurations are provided according to the simulation test signal test configuration management unit, different simulation test configurations run on a flight state simulation system, and different simulation test environments are switched through the test configuration of the comprehensive wiring system.

According to the ground comprehensive test method of the flight control system, provided by the embodiment of the invention, the comprehensive test function of the flight control system on the ground is completed according to the simulation and test task requirements of different test stages of the flight control system, the ground comprehensive test method of the flight control system penetrates through the full life cycle of V-shaped development of the flight control system, and the problem that the current ground test equipment cannot cover the comprehensive test configuration requirements of the flight control system in the early design stage and the real flight control system is connected into a test loop in the later development stage is solved.

In this embodiment, a ground comprehensive test method of a flight control system is provided, and fig. 16 is a flowchart of the ground comprehensive test method of the flight control system according to an embodiment of the present invention, as shown in fig. 16, the flowchart includes the following steps:

step S201, a preset flight control system test stage is obtained. Please refer to step S101 in the embodiment shown in fig. 15 in detail, which is not described herein.

Step S202, a simulation test signal is sent according to a test stage of the flight control system, a simulation test configuration is provided according to the simulation test signal, and a simulation test environment is automatically switched according to the simulation test configuration.

Specifically, the step S202 includes:

step S2021, transmitting a full-digital real-time simulation test signal in the flight simulation development and flight control algorithm design test stage, providing a full-digital real-time simulation test configuration according to the full-digital real-time simulation test signal, and accessing the flight control simulation model and the external cross-linking equipment simulation model into a simulation test environment to perform the full-digital real-time simulation test. Specifically, in the flight simulation development and flight control algorithm design test stage, a first terminal of a first signal switching box SW-01 of the integrated wiring system is connected with a flight control system simulation model, the first terminal is connected with a first common terminal, the first common terminal is connected with a second common terminal of a second signal switching box SW-02, the second common terminal is connected with a third terminal of the second signal switching box SW-02, and the third terminal is connected with an external crosslinking equipment simulation model. In this stage, the simulation management control unit sends a full-digital real-time simulation test signal, and according to the full-digital real-time simulation test signal, the test configuration management unit provides a full-digital real-time simulation test configuration according to the full-digital real-time simulation test signal, and the flight control simulation model and simulation models such as an atmospheric sensor, an angular rate gyro and the like in the external crosslinking device are connected into a simulation test environment to perform the full-digital real-time simulation test.

And step S2022, transmitting a hardware-in-loop semi-physical simulation test signal in the flight control crosslinking design and verification test stage, providing a hardware-in-loop semi-physical simulation test configuration according to the hardware-in-loop semi-physical simulation test signal, and connecting the flight control computer into an external crosslinking equipment simulation model for simulation test. Specifically, in the flight control algorithm verification test stage, a first terminal of a first signal switching box SW-01 of the integrated wiring system is connected with a flight control system simulation model, the first terminal is connected with a first common terminal, the first common terminal is connected with a second common terminal of a second signal switching box SW-02, the second common terminal is connected with a fourth terminal of the second signal switching box SW-02, and the fourth terminal is connected with external crosslinking equipment. In the test stage, the simulation control unit sends a rapid control prototype simulation test signal, the test configuration management unit provides a rapid control prototype simulation test configuration according to the rapid control prototype simulation test signal, provides automatic test and data management functions, and enables real parts such as an atmospheric sensor, an angular rate gyroscope and the like in external crosslinking equipment to be connected into the flight control simulation model for simulation test.

And step S2023, providing a hardware-in-loop semi-physical simulation test configuration in the flight control crosslinking design and verification test stage, transmitting a hardware-in-loop semi-physical simulation test signal, and accessing the flight control computer into an external crosslinking equipment simulation model for simulation test according to the hardware-in-loop semi-physical simulation test signal. Specifically, in the stage of the flight control cross-linking design and verification test, a second terminal of a first signal switching box SW-01 of the integrated wiring system is connected with the flight control system, a second terminal is connected with a first common terminal, the first common terminal is connected with a second common terminal of a second signal switching box SW-02, the second common terminal is connected with a third terminal of the second signal switching box SW-02, and the third terminal is connected with an external cross-linking equipment simulation model. In the test stage, a simulation control unit sends a hardware-in-loop semi-physical simulation test signal, a test configuration management unit provides a hardware-in-loop semi-physical simulation test configuration according to the hardware-in-loop semi-physical simulation test signal, and provides functions of automatic test, test data monitoring and the like, a flight state simulation system provides a flight control system cross-linking environment simulation operation platform, comprises a flight simulation model, an inertial measurement unit, a navigation model, a sensor and other simulation models, provides a hardware interface, and configures a comprehensive wiring system and a test cable to access a real flight control computer according to the hardware-in-loop semi-physical simulation test configuration to construct a hardware-in-loop simulation test environment.

And step S2024, transmitting a semi-physical comprehensive simulation test signal in a semi-physical ground comprehensive simulation test stage, providing a semi-physical comprehensive simulation test configuration according to the semi-physical comprehensive simulation test signal, and connecting the flight control calculation and the external crosslinking equipment into an external crosslinking equipment simulation model for simulation test. Specifically, in the stage of the semi-physical ground comprehensive simulation test, a second terminal of a first signal switching box SW-01 of the comprehensive wiring system is connected with the flight control system, the first terminal and the second terminal are both connected with a first common terminal, the first common terminal is connected with a second common terminal of a second signal switching box SW-02, the second common terminal is connected with a third terminal and a fourth terminal of the second signal switching box SW-02, the third terminal is connected with an external crosslinking device simulation model, and the fourth terminal is connected with an external crosslinking device. In the test stage, the simulation control unit sends a semi-physical comprehensive simulation test signal, the test management system provides a semi-physical comprehensive simulation test configuration according to the semi-physical comprehensive simulation test signal, and provides functions of automatic test, data monitoring and the like, the flight state simulation system provides a real-time operation platform for part of flight simulation, and the comprehensive wiring system and the test cable are configured to access flight control calculation and external crosslinking equipment (a real inertial measurement unit, a receiver and an atmospheric system sensor) into an external crosslinking equipment simulation model according to the semi-physical comprehensive simulation test signal to perform a semi-physical comprehensive simulation test.

According to the ground comprehensive test method for the flight control system, provided by the embodiment of the invention, a stage of early flight simulation development and flight control algorithm design test is developed, a flight simulation and flight control model is built at the stage, a simulation platform for model operation is provided, an all-digital flight simulation environment is built, and meanwhile, the rapid verification of the flight control algorithm is realized along with the quality assurance simulation test stage-rapid control prototype verification. In the middle development stage of the flight control system, namely the flight control cross-linking design and verification test stage, the hardware design and production of the flight control system core equipment-the flight control computer are completed, the flight control computer cross-linking simulation environment is built, the development and verification of the flight control computer are realized, hardware resources are provided for accessing the real flight control computer, the hardware-in-loop semi-physical simulation test environment is built, namely the test verification is carried out on the design and analysis results, so as to confirm whether the development requirement of the flight control system is met. In the later development stage of the flight control system, namely in the semi-physical ground comprehensive simulation test stage, the real equipment of the external crosslinking equipment is connected and matched with the simulation model of the external crosslinking equipment, so that a semi-physical ground comprehensive simulation test environment is constructed, the functions and the flight performance of the flight control system are comprehensively and comprehensively verified, the V-shaped development full life cycle of the flight control system is covered, and the flight simulation of the flight control system on the ground, the flight control strategy verification, the flight control performance verification function and the flight performance comprehensive test function of the flight control system are completed.

The embodiment also provides a ground comprehensive test device for the flight control system, which is used for realizing the embodiment and the preferred implementation mode, and is not described again. As used below, the term "module" may be a combination of software and/or hardware that implements a predetermined function. While the means described in the following embodiments are preferably implemented in software, implementation in hardware, or a combination of software and hardware, is also possible and contemplated.

The embodiment provides a ground comprehensive test device of a flight control system, as shown in fig. 17, including:

the acquisition module 501 is configured to acquire a preset flight control system test stage;

the control module 502 is configured to send a simulation test signal according to a test stage of the flight control system, provide a simulation test configuration according to the simulation test signal, and automatically switch a simulation test environment according to the simulation test configuration.

In some alternative embodiments, the control module 502 includes:

the first control unit is used for sending all-digital real-time simulation test signals in the flight simulation development and flight control algorithm design test stage, providing all-digital real-time simulation test configuration according to the all-digital real-time simulation test signals, and connecting the flight control simulation model and the external cross-linking equipment simulation model into a simulation test environment to perform all-digital real-time simulation test.

And the second control unit is used for transmitting a rapid control prototype simulation test signal in the flight control algorithm verification test stage, providing a rapid control prototype simulation test configuration according to the rapid control prototype simulation test signal, and connecting external crosslinking equipment into the flight control simulation model to perform a rapid control prototype simulation test.

And the third control unit is used for sending a hardware-in-loop semi-physical simulation test signal in the flight control crosslinking design and verification test stage, providing a hardware-in-loop semi-physical simulation test configuration according to the hardware-in-loop semi-physical simulation test signal, and connecting the flight control computer into an external crosslinking equipment simulation model to perform a hardware-in-loop semi-physical simulation test.

And the fourth control unit is used for transmitting a semi-physical comprehensive simulation test signal in a semi-physical ground comprehensive simulation test stage, providing a semi-physical comprehensive simulation test configuration according to the semi-physical comprehensive simulation test signal, and connecting the flight control calculation and the external crosslinking equipment into an external crosslinking equipment simulation model to perform the semi-physical ground comprehensive simulation test.

The flight control system ground integrated test device in this embodiment is presented in the form of a functional unit, where the unit refers to an ASIC circuit, a processor and a memory that execute one or more software or firmware programs, and/or other devices that may provide the above-described functionality.

Further functional descriptions of the above respective modules are the same as those of the above corresponding embodiments, and are not repeated here.

The embodiment of the invention also provides computer equipment, which is provided with the ground comprehensive test device of the flight control system shown in the figure 17.

Referring to fig. 18, fig. 18 is a schematic structural diagram of a computer device according to an alternative embodiment of the present invention, as shown in fig. 18, the computer device includes: one or more processors 10, memory 20, and interfaces for connecting the various components, including high-speed interfaces and low-speed interfaces. The various components are communicatively coupled to each other using different buses and may be mounted on a common motherboard or in other manners as desired. The processor may process instructions executing within the computer device, including instructions stored in or on memory to display graphical information of the GUI on an external input/output device, such as a display device coupled to the interface. In some alternative embodiments, multiple processors and/or multiple buses may be used, if desired, along with multiple memories and multiple memories. Also, multiple computer devices may be connected, each providing a portion of the necessary operations (e.g., as a server array, a set of blade servers, or a multiprocessor system). One processor 10 is illustrated in fig. 18.

The processor 10 may be a central processor, a network processor, or a combination thereof. The processor 10 may further include a hardware chip, among others. The hardware chip may be an application specific integrated circuit, a programmable logic device, or a combination thereof. The programmable logic device may be a complex programmable logic device, a field programmable gate array, a general-purpose array logic, or any combination thereof.

Wherein the memory 20 stores instructions executable by the at least one processor 10 to cause the at least one processor 10 to perform the methods shown in implementing the above embodiments.

The memory 20 may include a storage program area that may store an operating system, at least one application program required for functions, and a storage data area; the storage data area may store data created from the use of the computer device of the presentation of a sort of applet landing page, and the like. In addition, the memory 20 may include high-speed random access memory, and may also include non-transitory memory, such as at least one magnetic disk storage device, flash memory device, or other non-transitory solid-state storage device. In some alternative embodiments, memory 20 may optionally include memory located remotely from processor 10, which may be connected to the computer device via a network. Examples of such networks include, but are not limited to, the internet, intranets, local area networks, mobile communication networks, and combinations thereof.

Memory 20 may include volatile memory, such as random access memory; the memory may also include non-volatile memory, such as flash memory, hard disk, or solid state disk; memory 604 may also include a combination of the types of memory described above.

The computer device also includes a communication interface 30 for the computer device to communicate with other devices or communication networks.

The embodiments of the present invention also provide a computer readable storage medium, and the method according to the embodiments of the present invention described above may be implemented in hardware, firmware, or as a computer code which may be recorded on a storage medium, or as original stored in a remote storage medium or a non-transitory machine readable storage medium downloaded through a network and to be stored in a local storage medium, so that the method described herein may be stored on such software process on a storage medium using a general purpose computer, a special purpose processor, or programmable or special purpose hardware. The storage medium can be a magnetic disk, an optical disk, a read-only memory, a random access memory, a flash memory, a hard disk, a solid state disk or the like; further, the storage medium may also comprise a combination of memories of the kind described above. It will be appreciated that a computer, processor, microprocessor controller or programmable hardware includes a storage element that can store or receive software or computer code that, when accessed and executed by the computer, processor or hardware, implements the methods illustrated by the above embodiments.

Although embodiments of the present invention have been described in connection with the accompanying drawings, various modifications and variations may be made by those skilled in the art without departing from the spirit and scope of the invention, and such modifications and variations fall within the scope of the invention as defined by the appended claims.

Claims

1. The ground comprehensive test equipment of the flight control system is characterized by comprising the following components:

the test management system is used for providing different simulation test configurations for a preset test stage of the flight control system and controlling and data managing the simulation model of the flight control system and the simulation test configurations;

the flight state simulation system is respectively connected with the test management system and the comprehensive wiring system, and is used for receiving simulation test signals of the test management system, providing an operation platform for a simulation test configuration and providing a simulation test signal interface for the comprehensive wiring system.

2. The apparatus of claim 1, wherein the flight control system comprises a flight control computer and an external crosslinking apparatus; the simulation model of the flight control system comprises a flight control simulation model and an external crosslinking equipment simulation model; the test management system includes:

3. The apparatus of claim 2, wherein the flight status simulation system comprises:

The flight control engine is used for receiving the simulation test signals of the simulation control management unit and providing an operation platform for the simulation test configuration;

4. The apparatus of claim 3, wherein the integrated wiring system comprises:

the first interface adaptation box is connected with the flight control engine through the external interface; the first interface adaptation box is used for receiving the simulation test signals transmitted by the flight control engine, branching the simulation test signals according to different simulation test configurations, and transmitting the branched simulation test signals to the first signal switching box and/or the second signal switching box;

the second interface adaptation box is respectively connected with the first signal switching box and the second signal switching box; the second interface adaptation box is used for accessing the flight control computer and the external crosslinking equipment into corresponding simulation test environments according to simulation test configurations.

5. The apparatus of claim 2, further comprising a test cable system, the test cable system comprising a test cable and a network cable;

the test cable is used for connecting the flight control system simulation model with the flight control system and/or external crosslinking equipment and connecting the external crosslinking equipment simulation model with the flight control system and/or external crosslinking equipment;

6. A ground integrated test method for a flight control system, which is applied to the ground integrated test device for a flight control system according to any one of claims 1 to 5, and comprises the following steps:

acquiring a preset flight control system test stage;

7. The method of claim 6, wherein the acquiring a predetermined flight control system test phase comprises:

8. The method of claim 7, wherein providing a simulation test configuration according to the flight control system test phase, transmitting a simulation test signal, and automatically switching a simulation test environment according to the simulation test signal comprises:

transmitting a rapid control prototype simulation test signal in the flight control algorithm verification test stage, providing a rapid control prototype simulation test configuration according to the rapid control prototype simulation test signal, and accessing external crosslinking equipment into a flight control simulation model to perform a rapid control prototype simulation test;

transmitting a hardware-in-loop semi-physical simulation test signal in the flight control crosslinking design and verification test stage, providing a hardware-in-loop semi-physical simulation test configuration according to the hardware-in-loop semi-physical simulation test signal, and accessing a flight control computer into an external crosslinking equipment simulation model to perform a hardware-in-loop semi-physical simulation test;

And transmitting a semi-physical comprehensive simulation test signal in the semi-physical ground comprehensive simulation test stage, providing a semi-physical comprehensive simulation test configuration according to the semi-physical comprehensive simulation test signal, and accessing the flight control calculation and external crosslinking equipment into an external crosslinking equipment simulation model to perform the semi-physical comprehensive simulation test.

9. A ground integrated test device for a flight control system according to any one of claims 1 to 5, said device comprising:

10. A computer device, comprising:

the system comprises a memory and a processor, wherein the memory and the processor are in communication connection, the memory stores computer instructions, and the processor executes the computer instructions, so that the ground comprehensive test method of the flight control system is executed.

11. A computer-readable storage medium having stored thereon computer instructions for causing a computer to perform the ground integrated test method of the flight control system of any one of claims 6 to 8.