阅读说明：本技术 组态化执行控制系统和方法 (System and method for controlling configurable execution ) 是由 吴树景 王波兰 卢娥 张帅 赵伟忠 侯如非 胡珊 葛志闪 杨振 于 2021-08-24 设计创作，主要内容包括：本发明提供了一种组态化执行控制系统和方法,包括：数据访问模块：定义及初始化与外界交互的通讯报文及全局变量,包括与人机控制界面交互数据结构、与飞行器交互数据结构；硬件驱动模块：与控制板上的硬件进行直接交互,并对硬件接口进行封装及转换,向用户层提供接口函数；通信交换模块：定义执行控制软件与人机界面软件、飞行器上计算机的通信方式,以及报文的收发逻辑；业务逻辑模块：定义对外部数据指令报文的解析及处理过程。本发明支持多种通信接口的灵活切换及相关参数配置,可供开发人员根据不同项目的多样化需求灵活调整和扩充,兼容多种报文收发逻辑,极大优化软件的调试效率,缩短开发迭代周期。(The invention provides a configuration execution control system and a method, comprising the following steps: a data access module: defining and initializing a communication message and global variables which interact with the outside, wherein the communication message and the global variables comprise a data structure interacting with a human-computer control interface and a data structure interacting with an aircraft; a hardware driving module: directly interacting with hardware on the control panel, packaging and converting a hardware interface, and providing an interface function for a user layer; a communication exchange module: defining the communication mode of the execution control software, the human-computer interface software and the computer on the aircraft and the receiving and sending logic of the message; a service logic module: and defining the analysis and processing process of the external data instruction message. The invention supports the flexible switching of various communication interfaces and the configuration of related parameters, can be flexibly adjusted and expanded by developers according to the diversified requirements of different projects, is compatible with various message transceiving logics, greatly optimizes the debugging efficiency of software and shortens the development iteration cycle.)

1. A system for controlling the execution of a configuration, comprising:

a data access module: defining and initializing a communication message and global variables which interact with the outside, wherein the communication message and the global variables comprise a data structure interacting with a human-computer control interface and a data structure interacting with an aircraft;

a hardware driving module: directly interacting with hardware on the control panel, packaging and converting a hardware interface, and providing an interface function for a user layer;

a communication exchange module: defining the communication mode of the execution control software, the human-computer interface software and the computer on the aircraft and the receiving and sending logic of the message;

a service logic module: and defining the analysis and processing process of the external data instruction message.

2. The configured execution control system of claim 1, wherein the hardware driver module comprises: the device comprises an IO read-write module, a storage detection module and a timer module;

the IO read-write module is used for performing power-on and power-off hardware IO operation, reading IO signals of each port, and detecting and monitoring power-on and power-off execution results and fault information;

the storage detection module is used for detecting the read-write safety and correctness of the file storage disk and guaranteeing the read-write reliability of the parameter file;

the timer module is used for releasing semaphore at a designated time interval so as to control the control system to periodically communicate with and control the aircraft.

3. The system of claim 1, wherein the communication switch module comprises: a 1553B communication module, an Ethernet communication module and a serial port communication module;

the 1553B communication module is used for receiving and transmitting data and controlling and processing messages with an aircraft with a 1553B communication interface;

the Ethernet communication module is used for receiving and transmitting data and controlling and processing messages with an aircraft with an Ethernet communication interface;

and the serial port communication module is used for receiving and transmitting data and controlling and processing messages with an aircraft with a serial communication interface.

4. The system of claim 3, wherein the 1553B communication module comprises:

initializing 1553B periodic transmission data chain: according to the configuration situation of the human-computer interface on the 1553B message serial number, traversing all the set message serial numbers, binding the sub-address, the message length and the transmission direction corresponding to each message, connecting the front and back relations in the 1553B cyclic link, and finally writing the messages into the bus in a BC _ CB format;

sending 1553B data: writing 1553B data, refreshing a message on a bus, converting the content and length of a data structure into a CDP format, calculating 1553B message checksum and filling the checksum into a tail part, writing the checksum into the 1553B bus in a CDP data state, and sending a corresponding message to a specified target address after writing;

reading 1553B data: firstly, acquiring a received message serial number to be read through a vector word, converting a message corresponding to the vector word message serial number into a CDP format, acquiring a subaddress of a hand lifter according to the vector word message, triggering corresponding interruption, and acquiring a message serial number corresponding to the hand lifter; and reading 1553B data, reading the received 1553B message into a CDP format, calculating and verifying a checksum, converting the checksum into a CHAR format, and outputting the read message.

5. The configured execution control system of claim 1, wherein the business logic module comprises: a human-computer interface software message analysis processing module and an aircraft message analysis processing module;

the human-computer interface software message analysis processing module is used for analyzing a control command message from a human-computer interface of an operator so as to obtain an instruction to be issued to the aircraft;

the aircraft message analyzing and processing module is used for analyzing state information from the aircraft so as to obtain the current operating state of the aircraft, and the feedback to the human-computer interface of an operator is facilitated.

6. A method for controlling execution of a configuration, comprising:

a data access step: defining and initializing a communication message and global variables which interact with the outside, wherein the communication message and the global variables comprise a data structure interacting with a human-computer control interface and a data structure interacting with an aircraft;

a hardware driving step: directly interacting with hardware on the control panel, packaging and converting a hardware interface, and providing an interface function for a user layer;

communication exchange step: defining the communication mode of the execution control software, the human-computer interface software and the computer on the aircraft and the receiving and sending logic of the message;

and (3) service logic steps: and defining the analysis and processing process of the external data instruction message.

7. The method of claim 6, wherein the hardware driving step comprises:

an IO read-write step, which is to perform power-on and power-off hardware IO operation, read IO signals of each port and detect and monitor power-on and power-off execution results and fault information;

a storage detection step, namely performing read-write safety and correctness detection on the file storage disk and guaranteeing the read-write reliability of the parameter file;

and a timer step, releasing the semaphore at a designated time interval, and operating the control system to periodically communicate and control with the aircraft.

8. The method of claim 6, wherein the step of exchanging communications comprises:

1553B communication, namely performing data receiving and sending and message control processing with an aircraft with a 1553B communication interface;

an Ethernet communication step, which is to transmit and receive data and control and process messages with an aircraft with an Ethernet communication interface;

and a serial port communication step, namely performing data receiving and sending and message control processing on the aircraft with the serial communication interface.

9. The method of claim 8, wherein the 1553B communication step comprises:

initializing 1553B periodic transmission data chain: according to the configuration situation of the human-computer interface on the 1553B message serial number, traversing all the set message serial numbers, binding the sub-address, the message length and the transmission direction corresponding to each message, connecting the front and back relations in the 1553B cyclic link, and finally writing the messages into the bus in a BC _ CB format;

sending 1553B data: writing 1553B data, refreshing a message on a bus, converting the content and length of a data structure into a CDP format, calculating 1553B message checksum and filling the checksum into a tail part, writing the checksum into the 1553B bus in a CDP data state, and sending a corresponding message to a specified target address after writing;

reading 1553B data: firstly, acquiring a received message serial number to be read through a vector word, converting a message corresponding to the vector word message serial number into a CDP format, acquiring a subaddress of a hand lifter according to the vector word message, triggering corresponding interruption, and acquiring a message serial number corresponding to the hand lifter; and reading 1553B data, reading the received 1553B message into a CDP format, calculating and verifying a checksum, converting the checksum into a CHAR format, and outputting the read message.

10. The method of claim 6, wherein the business logic steps comprise:

a man-machine interface software message analyzing and processing step, which is used for analyzing a control command message from a man-machine interface of an operator so as to obtain an instruction to be issued to the aircraft;

and analyzing and processing the aircraft message, namely analyzing the state information from the aircraft so as to obtain the current operating state of the aircraft, so as to conveniently feed back to a human-computer interface of an operator.

Technical Field

The invention relates to the technical field of unmanned aerial vehicle control software, in particular to a configuration execution control system and method.

Background

The executive control group is the executive control center of the aircraft control system. The execution control software is loaded and operated in the execution combination equipment, mainly completes the communication with a human-computer interface, data recording equipment and an aircraft, completes the data processing and equipment control, completes the flow control of alignment, parameter binding, takeoff and the like, and detects and monitors the working state of the system, the equipment state and the aircraft state.

Currently, with the continuous acceleration of the development cycle of project engineering, the running logic of software is increasingly complex, whether diversified software requirements can be met within a limited time or not can be quickly and reliably developed to execute control software and complete system joint test work, and the problems become difficult points and hot points in the development process of aircraft control software. In an aircraft control system, a plurality of control instruction tasks are completed by cooperation of a large number of digital devices (including human-computer interface devices, execution combination devices, navigation devices, aircraft embedded computers and the like), the communication modes among the devices are mostly serial communication, Ethernet communication, 1553B communication and the like, and in addition, message protocols are different, the flow direction and the rule of data transmission are complicated, so that the rapid and stable interaction among the devices is hindered; the method is a decision factor for executing whether control software can be developed and formed quickly or not by orienting to the operation requirements (such as power-on, alignment, takeoff and the like) of the differentiated control flow, whether common characteristics can be extracted or not, opening special customized operation and enabling the software to dynamically adapt to the continuously iterative software design requirements in a parameter configuration mode. Therefore, a configuration type, modularization and cutting diversified software system architecture becomes an urgent need for improving development and docking efficiency.

In conclusion, the configuration software architecture is a development trend of executing control software in the future, and becomes a necessary route for executing the development of the control software.

Patent document CN106569801B (application number: CN201610906709.7) discloses a configuration display and control system based on complex parameters, which includes a data configuration module, a control design module, an interface configuration module, and a display terminal module. The data configuration module realizes the configuration of test coverage parameters, data frame protocols, parameter processing formulas and user login authorities. The control design module realizes the design of the configuration control and supports the user to define the control. The interface configuration module is used for rapidly configuring a terminal interface meeting the test task. And the display terminal module loads a test task terminal interface accessible by the current user, interacts with the data center, receives test parameter data and attributes sent by each configuration control and displays the test parameter data and attributes. However, this patent cannot meet the control requirements when facing the operation requirements of various communication modes, different message protocols, data transmission with different flow directions and rules, and differentiated control flows between devices.

Disclosure of Invention

In view of the deficiencies in the prior art, it is an object of the present invention to provide a system and method for configuration execution control.

The invention provides a configuration execution control system, which comprises:

a data access module: defining and initializing a communication message and global variables which interact with the outside, wherein the communication message and the global variables comprise a data structure interacting with a human-computer control interface and a data structure interacting with an aircraft;

a hardware driving module: directly interacting with hardware on the control panel, packaging and converting a hardware interface, and providing an interface function for a user layer;

a communication exchange module: defining the communication mode of the execution control software, the human-computer interface software and the computer on the aircraft and the receiving and sending logic of the message;

a service logic module: and defining the analysis and processing process of the external data instruction message.

Preferably, the hardware driving module includes: the device comprises an IO read-write module, a storage detection module and a timer module;

the IO read-write module is used for performing power-on and power-off hardware IO operation, reading IO signals of each port, and detecting and monitoring power-on and power-off execution results and fault information;

the storage detection module is used for detecting the read-write safety and correctness of the file storage disk and guaranteeing the read-write reliability of the parameter file;

the timer module is used for releasing semaphore at a designated time interval so as to control the control system to periodically communicate with and control the aircraft.

Preferably, the communication switching module includes: a 1553B communication module, an Ethernet communication module and a serial port communication module;

the 1553B communication module is used for receiving and transmitting data and controlling and processing messages with an aircraft with a 1553B communication interface;

the Ethernet communication module is used for receiving and transmitting data and controlling and processing messages with an aircraft with an Ethernet communication interface;

and the serial port communication module is used for receiving and transmitting data and controlling and processing messages with an aircraft with a serial communication interface.

Preferably, the 1553B communication module includes:

initializing 1553B periodic transmission data chain: according to the configuration situation of the human-computer interface on the 1553B message serial number, traversing all the set message serial numbers, binding the sub-address, the message length and the transmission direction corresponding to each message, connecting the front and back relations in the 1553B cyclic link, and finally writing the messages into the bus in a BC _ CB format;

sending 1553B data: writing 1553B data, refreshing a message on a bus, converting the content and length of a data structure into a CDP format, calculating 1553B message checksum and filling the checksum into a tail part, writing the checksum into the 1553B bus in a CDP data state, and sending a corresponding message to a specified target address after writing;

reading 1553B data: firstly, acquiring a received message serial number to be read through a vector word, converting a message corresponding to the vector word message serial number into a CDP format, acquiring a subaddress of a hand lifter according to the vector word message, triggering corresponding interruption, and acquiring a message serial number corresponding to the hand lifter; and reading 1553B data, reading the received 1553B message into a CDP format, calculating and verifying a checksum, converting the checksum into a CHAR format, and outputting the read message.

Preferably, the service logic module includes: a human-computer interface software message analysis processing module and an aircraft message analysis processing module;

the human-computer interface software message analysis processing module is used for analyzing a control command message from a human-computer interface of an operator so as to obtain an instruction to be issued to the aircraft;

the aircraft message analyzing and processing module is used for analyzing state information from the aircraft so as to obtain the current operating state of the aircraft, and the feedback to the human-computer interface of an operator is facilitated.

The configuration execution control method provided by the invention comprises the following steps:

a data access step: defining and initializing a communication message and global variables which interact with the outside, wherein the communication message and the global variables comprise a data structure interacting with a human-computer control interface and a data structure interacting with an aircraft;

a hardware driving step: directly interacting with hardware on the control panel, packaging and converting a hardware interface, and providing an interface function for a user layer;

communication exchange step: defining the communication mode of the execution control software, the human-computer interface software and the computer on the aircraft and the receiving and sending logic of the message;

and (3) service logic steps: and defining the analysis and processing process of the external data instruction message.

Preferably, the hardware driving step includes:

an IO read-write step, which is to perform power-on and power-off hardware IO operation, read IO signals of each port and detect and monitor power-on and power-off execution results and fault information;

a storage detection step, namely performing read-write safety and correctness detection on the file storage disk and guaranteeing the read-write reliability of the parameter file;

and a timer step, releasing the semaphore at a designated time interval, and operating the control system to periodically communicate and control with the aircraft.

Preferably, the communication exchange step includes:

1553B communication, namely performing data receiving and sending and message control processing with an aircraft with a 1553B communication interface;

an Ethernet communication step, which is to transmit and receive data and control and process messages with an aircraft with an Ethernet communication interface;

and a serial port communication step, namely performing data receiving and sending and message control processing on the aircraft with the serial communication interface.

Preferably, the 1553B communication step includes:

initializing 1553B periodic transmission data chain: according to the configuration situation of the human-computer interface on the 1553B message serial number, traversing all the set message serial numbers, binding the sub-address, the message length and the transmission direction corresponding to each message, connecting the front and back relations in the 1553B cyclic link, and finally writing the messages into the bus in a BC _ CB format;

sending 1553B data: writing 1553B data, refreshing a message on a bus, converting the content and length of a data structure into a CDP format, calculating 1553B message checksum and filling the checksum into a tail part, writing the checksum into the 1553B bus in a CDP data state, and sending a corresponding message to a specified target address after writing;

reading 1553B data: firstly, acquiring a received message serial number to be read through a vector word, converting a message corresponding to the vector word message serial number into a CDP format, acquiring a subaddress of a hand lifter according to the vector word message, triggering corresponding interruption, and acquiring a message serial number corresponding to the hand lifter; and reading 1553B data, reading the received 1553B message into a CDP format, calculating and verifying a checksum, converting the checksum into a CHAR format, and outputting the read message.

Preferably, the business logic step includes:

a man-machine interface software message analyzing and processing step, which is used for analyzing a control command message from a man-machine interface of an operator so as to obtain an instruction to be issued to the aircraft;

and analyzing and processing the aircraft message, namely analyzing the state information from the aircraft so as to obtain the current operating state of the aircraft, so as to conveniently feed back to a human-computer interface of an operator.

Compared with the prior art, the invention has the following beneficial effects:

(1) the invention uses the software framework of the general framework, and can dynamically adapt to tasks of state management, ejection flow control, information processing, information exchange and the like of various aircrafts by configuring parameters to be bound of aircrafts of different models, and the flow details of the software can be redefined without modifying and compiling programs;

(2) the invention integrates the reusable module for the common demand among products and opens the expandable interface for the individual demand, thereby obtaining a good balance between reusability and flexibility and greatly improving the convenience, generalization and transparence of the execution control software;

(3) the configuration, expandable and universal execution control software provided by the invention can meet the differentiation requirements of various aircrafts in the aspects of communication, interaction, control and the like, and realizes quick, reliable, convenient and fast iterative development.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a diagram of a configuration execution control software architecture;

FIG. 2 is a diagram of a customized data buffer container;

FIG. 3 is a schematic diagram of a 1553B communication module;

fig. 4 is a schematic diagram of an extended message parsing module.

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

Example (b):

the invention provides a configuration execution control system, which comprises:

referring to fig. 1, a top-down, one-way dependent configuration execution control software architecture is designed, and each software execution mechanism exists in the form of a tailorable component for the free combination of secondary developers. Wherein a single block represents a software module and dashed blocks identify all extensible modules. The overall organizational architecture is divided into 4 layers:

1) a data access layer: the method is used for defining and initializing the communication message and the global variable interacted with the outside. Comprises the following steps: interacting a data structure with a human-computer control interface and interacting a data structure with an aircraft;

2) a hardware driving layer: the interface function is used for directly interacting with a hardware module on the control panel, and providing a simple and easy-to-use interface function with clear parameters for a user layer after packaging and converting a complex interface operated by the hardware. Comprises the following steps: the device comprises an IO read-write module, a storage detection module and a timer module;

3) a communication exchange layer: the method is used for defining various main flow communication modes for executing control software and peripheral equipment such as human-computer interface software, computers on aircrafts and the like, and receiving and sending logics of messages and the like. Comprises the following steps: a 1553B communication module, an Ethernet communication module and a serial port communication module;

4) and a service logic layer: the method is used for defining the analysis and processing process of the external data instruction message. Comprises the following steps: a human-computer interface software message analysis processing module and an aircraft message analysis processing module.

Referring to fig. 2, in 3 communication modes integrated by the software, 1553B communication has more complex configuration information and richer interaction modes compared with other 2 communication modes, so a 1553B communication operation module is separately constructed, and 3 main operation interfaces are opened:

1) initializing 1553B periodic transmission data chains. According to the configuration situation of the human-computer interface on the 1553B message serial number, traversing all the set message serial numbers, binding information such as a sub-address, a message length, a transmission direction and the like corresponding to each message, connecting the front and back relations in the 1553B cyclic link, and finally writing the information into a bus in a BC _ CB format;

2) and sending 1553B data. Firstly, writing 1553B data, refreshing a message on a bus, converting the content and length of a data structure into a CDP format, calculating 1553B message checksum and filling the checksum into a tail part, and writing the checksum into the 1553B bus in a CDP data state. After writing, sending the corresponding message to a specified target address;

3) the 1553B data is read. Firstly, acquiring a received message serial number to be read through a vector word, converting a message corresponding to the vector word message serial number into a CDP format, acquiring a subaddress of a hand lifter according to the vector word message, triggering corresponding interruption, and acquiring a message serial number corresponding to the hand lifter; and then, reading 1553B data, reading the received 1553B message into a CDP format, calculating and verifying a checksum, converting the checksum into a CHAR format, and outputting the read message.

Referring to fig. 3, a custom data buffer container using a queue as a template is designed for storing original data directly from a communication receiving channel waiting for frame grouping and frame unpacking. The operation interface provided by the data buffer container comprises:

1) a read-only interface: DataStart (start position of stored data), DataEnd (start position of data to be stored), get [ n ] (taking byte data of nth position), HasSize (length of data stored in container), RemainSize (length of data still stored in container);

2) a writable interface: pop (head data out-queue), Push (tail data in-queue), Clear (Clear in-queue data).

Referring to fig. 4, a message parsing framework for extension of the steps of the generalized flow template is designed. The generalized flow template is shown as a left dashed box, and the related steps include:

1) checking whether the data container head has data;

2) if the check of the previous step is passed, clearing the invalid message at the head of the message;

3) checking whether the current data container has a readable minimum length;

4) if the previous step passes the inspection, whether the 1 st complete message of the head is successfully acquired is inspected;

5) if the message passes the previous step, carrying out detailed analysis processing on the message;

6) returning to the step 1), and continuously analyzing the next message.

An example of an extension of the generalized flow object is shown on the right of fig. 4.

The invention is oriented to the requirements of executing the rapid development and cutting of control software. And designing a dynamic execution control software architecture, and designing a reusable module as a dynamic component for flexible recombination during secondary development, thereby greatly improving the development efficiency. The invention is oriented to executing the difference of the communication modes between the control software and other equipment. Integrating 3 common communication software modules: a serial port communication module, an Ethernet communication module and a 1553B communication module. Each module adopts a multi-state technology to package the driving layer, provide an interface for the logic layer and provide a unified bidirectional transceiving interface and a message analysis logic framework. The invention is oriented to the macro commonality and the micro difference on the control flow of the execution control software. In one aspect, extracting a portion of commonality between aircraft models comprises: the system comprises a message buffer container, an IO read-write module, a timer, a storage device and other generalized modules; on the other hand, abstracting the differentiated part into a scalable module waiting for padding, including: message frame-assembling/frame-disassembling/checking process, interaction with aircraft control command, data structure definition and the like. The invention supports various communication modes, extracts and integrates the commonalities and individual requirements of all items by using an abstract interface, and provides a tailorable and extensible development framework. The configuration framework is constructed based on the object-oriented technology and the modularization idea, developers can flexibly adjust according to diversified requirements of different tasks, the development period is effectively shortened, and the debugging efficiency is improved. The invention can flexibly switch between three communication modes of serial port communication, Ethernet communication and 1553B communication and missile communication by means of parameter setting of the display control message according to the communication mode differentiation requirements of each aircraft control task. And all communication modes are packaged into classes by object-oriented technology, and the differentiated settings are extracted as parameters for designers to carry out rapid parameterization configuration and replication. And a uniform transceiving interactive interface is provided, so that cross-interface communication is facilitated. The invention can carry out customized extension on operations such as frame grouping, frame unpacking, checking and the like during message receiving and sending according to the requirement of the differentiation of message protocols of various types of weapons. The message is buffered by the buffer of the customizable data container, and the instructive polymorphic inheritance design can be carried out according to the established message analysis framework. The invention can carry out configuration and programming in a cutting mode on control steps, sequences, priorities and the like of power-on, alignment, ignition and the like according to the differentiation requirements of control processes of various types of weapons. The method comprises the steps of packaging components such as IO operation, timer inspection and the like into software modules, and connecting hardware drive and service logic in an interface mode to achieve flexible decoupling of software and hardware.

The configuration execution control method provided by the invention comprises the following steps: a data access step: defining and initializing a communication message and global variables which interact with the outside, wherein the communication message and the global variables comprise a data structure interacting with a human-computer control interface and a data structure interacting with an aircraft; a hardware driving step: directly interacting with hardware on the control panel, packaging and converting a hardware interface, and providing an interface function for a user layer; communication exchange step: defining the communication mode of the execution control software, the human-computer interface software and the computer on the aircraft and the receiving and sending logic of the message; and (3) service logic steps: and defining the analysis and processing process of the external data instruction message.

The hardware driving step includes: an IO read-write step, which is to perform power-on and power-off hardware IO operation, read IO signals of each port and detect and monitor power-on and power-off execution results and fault information; a storage detection step, namely performing read-write safety and correctness detection on the file storage disk and guaranteeing the read-write reliability of the parameter file; and a timer step, releasing the semaphore at a designated time interval, and operating the control system to periodically communicate and control with the aircraft.

The communication exchange step includes: 1553B communication, namely performing data receiving and sending and message control processing with an aircraft with a 1553B communication interface; an Ethernet communication step, which is to transmit and receive data and control and process messages with an aircraft with an Ethernet communication interface; and a serial port communication step, namely performing data receiving and sending and message control processing on the aircraft with the serial communication interface.

The 1553B communication step comprises the following steps: initializing 1553B periodic transmission data chain: according to the configuration situation of the human-computer interface on the 1553B message serial number, traversing all the set message serial numbers, binding the sub-address, the message length and the transmission direction corresponding to each message, connecting the front and back relations in the 1553B cyclic link, and finally writing the messages into the bus in a BC _ CB format; sending 1553B data: writing 1553B data, refreshing a message on a bus, converting the content and length of a data structure into a CDP format, calculating 1553B message checksum and filling the checksum into a tail part, writing the checksum into the 1553B bus in a CDP data state, and sending a corresponding message to a specified target address after writing; reading 1553B data: firstly, acquiring a received message serial number to be read through a vector word, converting a message corresponding to the vector word message serial number into a CDP format, acquiring a subaddress of a hand lifter according to the vector word message, triggering corresponding interruption, and acquiring a message serial number corresponding to the hand lifter; and reading 1553B data, reading the received 1553B message into a CDP format, calculating and verifying a checksum, converting the checksum into a CHAR format, and outputting the read message.

The business logic step includes: a man-machine interface software message analyzing and processing step, which is used for analyzing a control command message from a man-machine interface of an operator so as to obtain an instruction to be issued to the aircraft; and analyzing and processing the aircraft message, namely analyzing the state information from the aircraft so as to obtain the current operating state of the aircraft, so as to conveniently feed back to a human-computer interface of an operator.

Those skilled in the art will appreciate that, in addition to implementing the systems, apparatus, and various modules thereof provided by the present invention in purely computer readable program code, the same procedures can be implemented entirely by logically programming method steps such that the systems, apparatus, and various modules thereof are provided in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system, the device and the modules thereof provided by the present invention can be considered as a hardware component, and the modules included in the system, the device and the modules thereof for implementing various programs can also be considered as structures in the hardware component; modules for performing various functions may also be considered to be both software programs for performing the methods and structures within hardware components.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.