CN115811373B - Communication verification system and method for front cabin of airplane and storage medium - Google Patents
Communication verification system and method for front cabin of airplane and storage medium Download PDFInfo
- Publication number
- CN115811373B CN115811373B CN202310121908.7A CN202310121908A CN115811373B CN 115811373 B CN115811373 B CN 115811373B CN 202310121908 A CN202310121908 A CN 202310121908A CN 115811373 B CN115811373 B CN 115811373B
- Authority
- CN
- China
- Prior art keywords
- flight
- data
- simulation
- flight data
- equipment
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The embodiment of the application discloses a communication verification system, a method and a storage medium for an aircraft front cabin, wherein the communication verification system for the aircraft front cabin comprises: the flight simulation system comprises a data source generation module, a signal generation module and an avionics equipment simulation module, wherein the data source generation module is used for generating and storing flight data by using a ground control simulation platform to drive simulated flight software and sending the flight data to the signal generation module; the signal generation module is used for generating a corresponding analog signal after receiving the flight data and outputting the analog signal to the avionic device simulation module; the avionics equipment of the avionics equipment simulation module comprises a flight data interface and management assembly, an air traffic service assembly, a control display unit and a wireless quick access recorder, and is used for real-time communication with a high-throughput satellite communication network.
Description
Technical Field
The application relates to the technical field of avionics, in particular to a communication verification system and method for an aircraft front cabin and a storage medium.
Background
With the launch of new in-flight entertainment/interconnect aircraft (IFE/IFC) passenger services and the future prediction of air traffic flow growth in Air Traffic Management (ATM) environments, the aviation industry has thus far shown great interest in satellite systems as a means of supplementing air-to-ground communications, where aircraft are interconnected to the ground via an antenna on the back of the aircraft with an aerial communications satellite, i.e., satellite communications (SATCOM) technology. The current airborne satellite communication wave bands mainly comprise an L wave band, a Ku wave band, a Ka wave band and the like. The frequency band of the L-band communication satellite is mainly between 1GHz and 2GHz, but the L-band communication satellite is only suitable for communication services with less bandwidth requirements, such as a voice link and the like, due to limited satellite resources, the frequency band of Ku-band satellite communication is mainly between 10GHz and 20GHz, the services begin in 2001, are firstly promoted by Boeing companies and are used for providing onboard Internet services for passengers, and the Ku-band satellite communication satellite has the advantages of abundant satellite resources, perfect ground facilities and mature airborne equipment and is an existing mainstream airborne satellite communication mode. However, because the Ku band satellite has limited bandwidth resources, cannot meet the requirement of large-scale use of a fleet, and has higher cost, and the Ka band communication satellite is used as a main high-throughput satellite, the frequency band of the Ka band communication satellite is between 26GHz and 40GHz, and the Ka band communication satellite has the characteristics of rich orbital position, small terminal size, high transmission rate and rich frequency resources, so that the data connection mode of the high-throughput communication satellite represented by the Ka band communication satellite is more stable in connection, higher in transmission rate, higher in economic value for an airline company, and the Ku band satellite is a main development direction of satellite communication in the future. The existing high-flux satellite communication mode is mainly used for providing on-board internet service for passengers, for a front cabin, the existing communication mode still mainly carries out voice and data communication of the front cabin through High Frequency (HF), very High Frequency (VHF), L-band satellites and the like, the bandwidth is narrow, the airplane can generate data with GB as a unit in the flying process, particularly a novel airplane, the data generated each time of landing and landing even exceeds 100GB, and the requirement of intelligent application of the front cabin of the digital airplane under the background of 4.0 times of industry can not be met by the existing on-board interconnection mode,
therefore, the intelligent aircraft uses the rear cabin broadband IFC service as a rear-complement front cabin communication mode through a high-flux communication satellite, shares flight data in real time through an airborne system, helps an airline company to monitor the operation condition of the aircraft in real time, and is a solution for the intelligent aircraft sought by the units such as the existing domestic satellite terminal, an operation company, a civil aviation bureau and the like.
To achieve this goal, a high-throughput satellite-based front cabin data communication verification platform is needed to implement feasibility verification, testing and possible failure analysis work for the high-throughput satellite-based front cabin data communication link.
Disclosure of Invention
An object of the embodiments of the present application is to provide a system, a method and a storage medium for verifying aircraft front cabin communication, so as to solve the problem that a high-throughput satellite-based front cabin data communication verification platform is needed in the prior art to implement feasibility verification and testing of a high-throughput satellite-based front cabin data communication link and possible failure analysis work.
In order to achieve the above object, an embodiment of the present application provides an aircraft front cabin communication verification system, including: a data source generating module, a signal generating module and an avionics equipment simulation module,
the data source generation module is used for generating and storing flight data by using a ground control simulation platform to drive simulated flight software, and sending the flight data to the signal generation module;
the signal generation module is used for generating a corresponding analog signal after receiving the flight data and outputting the analog signal to the avionic device simulation module;
the avionics device of the avionics device simulation module comprises a flight data interface and management assembly, an air traffic service assembly, a control display unit and a wireless fast access recorder, and is used for receiving the analog signals through the flight data interface and management assembly, converting a part of the analog signals into ARINC717 data through the flight data interface and management assembly, transmitting the ARINC717 data to the wireless fast access recorder, analyzing and converting the ARINC717 data into engineering values in real time through built-in software, performing related logic calculation triggering on the other part of the analog signals through an airplane state monitoring system of the flight data interface and management assembly or generating ACARS messages after the control display unit is operated, and enabling the wireless fast access recorder to be connected with an onboard satellite antenna unit through setting the air traffic service assembly to finally communicate with a high-flux satellite communication network in real time.
Optionally, the flight data interface and management component is configured to obtain, collect and process aircraft parameters, collect aircraft discrete and ARINC429 DITS data bus inputs, output the aircraft discrete and ARINC429 DITS data bus inputs to the digital flight data recorder, and output data of the digital flight data recorder to the wireless fast access recorder;
the air traffic service component is used for providing a data link host platform, a router and an air traffic control application program to carry out data link communication and can carry out management of a data link medium;
the control display unit is used for inserting system control parameters, a flight plan and information of displaying a flight progress and airplane performance;
the wireless fast access recorder is used for storing the flight data into a built-in solid-state flash memory PCMCIA PC card medium, connecting broadband satellite communication equipment and interconnecting the data of various avionic equipment connected to the avionic equipment simulation module of the wireless fast access recorder with an electronic flight bag through WAP.
Optionally, the data source generating module includes: a simulated cockpit, a flight simulation system, a steering system, a display system and/or a computer system,
the simulation cockpit is a flight simulator ground simulation operation platform and comprises a top plate, a front panel, a rear electronic panel, a main instrument panel, cockpit equipment, a central operation platform and/or a seat;
the flight simulation system has simulated flight environments such as visual scenes, weather, sound and the like when the airplane flies, and performs data interaction with other system computers through the Ethernet so as to provide flight data of flight states, flight instruments and flight operations;
the control system comprises a control lever, pedals, an accelerator control console, a front wheel turning control handle, a landing gear handle and/or a stopping brake handle, and is used for simulating flight driving control of a pilot in a cockpit and providing a rudder deflection angle, a slat deflection angle, a throttle lever angle and/or a multifunctional flow plate position for the flight simulation system;
the display system is used for providing the outer scene of the simulated cockpit in real time, reading related ground scene and model data according to a real scene database, rendering an image in real time, converting the image into a video signal and generating continuous images on a screen;
the computer system is used for simulating flight states of different weather and time through flight simulation software.
Optionally, the signal generation module is configured to generate a corresponding analog signal based on the flight data through an ARINC429 bus signal converter.
Optionally, the method further comprises:
and the airborne power supply module is used for controlling the working state of the avionics equipment and switching between high-frequency satellite links and high-speed satellite links.
Optionally, the method further comprises:
the device comprises a rack, wherein a special switch and a data loading interface of each avionic device are arranged on the rack, the special switch is used for switching on and off the avionic devices, and the data loading interface is used for updating software of the avionic devices.
In order to achieve the above object, the present application further provides an aircraft front cabin communication verification method, including the steps of: simulating flight software to generate flight data of airplanes of different types at different time and in different weather by a ground simulation control platform according to control drive of a driver, wherein the flight data are taken off and landed from different airports;
the flight data are converted into corresponding analog signals through the board card and transmitted to avionic equipment of an avionic equipment simulation module, and the avionic equipment simulation module comprises a flight data interface and management assembly, an air traffic service assembly, a control display unit and a wireless fast access recorder;
the flight data interface and the management component are used for receiving the analog signals, one part of the analog signals are converted into ARINC717 data through the flight data interface and the management component, the ARINC717 data are transmitted to the wireless fast access recorder and then are analyzed and converted into engineering values through built-in software in real time, the other part of the analog signals are triggered through relevant logic calculation of an aircraft state monitoring system of the flight data interface and the management component or generate ACARS messages after the control display unit is operated, the wireless fast access recorder is connected with an onboard satellite antenna unit through the arrangement of the air traffic service component, and finally the wireless fast access recorder is communicated with a high-flux satellite communication network in real time.
Optionally, the avionics device that converts the flight data into corresponding analog signals through the board card and transmits the analog signals to the avionics device simulation module includes:
firstly, a board card is connected to a computer through a USB interface, a function is called to enable an operating system of a host to obtain access to equipment hardware, the hardware configuration before the equipment is reset, and a required equipment channel is configured;
and initializing data, defining the data by referring to an interface control file, exchanging data between a computer and equipment, converting the flight data into the analog signal, and transmitting the analog signal to the avionic equipment of the avionic equipment simulation module.
Optionally, the ground simulation maneuvering platform is equipped with Prepar3D V software to simulate real flight environment and support generation of the flight data, instrument display on the test bed equipment and output of the flight data.
To achieve the above object, the present application also provides a computer storage medium having a computer program stored thereon, wherein the computer program, when executed by a machine, implements the steps of the method as described above.
The embodiment of the application has the following advantages:
the embodiment of the application provides an aircraft front deck communication verification system, includes: the flight simulation system comprises a data source generation module, a signal generation module and an avionic device simulation module, wherein the data source generation module is used for generating and storing flight data by using a ground control simulation platform to drive simulated flight software and sending the flight data to the signal generation module; the signal generation module is used for generating a corresponding analog signal after receiving the flight data and outputting the analog signal to the avionic device simulation module; the avionics equipment of the avionics equipment simulation module comprises a flight data interface and management assembly, an air traffic service assembly, a control display unit and a wireless fast access recorder, and is used for receiving the analog signals through the flight data interface and management assembly, converting a part of the analog signals into ARINC717 data through the flight data interface and management assembly, analyzing and converting the data into engineering values in real time through built-in software after transmitting the engineering values to the wireless fast access recorder, performing related logic calculation triggering on the other part of the analog signals through an airplane state monitoring system of the flight data interface and management assembly or generating ACARS messages after the control display unit is operated, and enabling the wireless fast access recorder to be connected with an airborne satellite antenna unit through setting the air traffic service assembly to finally communicate with a high-flux satellite communication network in real time.
Through the system, a forecabin data communication verification platform based on a high-throughput satellite is constructed through avionics devices such as a flight simulator, a fast access recorder (WQAR), a Multifunctional Control Display Unit (MCDU), a flight data interface and management module (FDIMU), an air traffic service module (ATSU), and the like, and the flight simulator simulates the driving operation of a pilot in the flight process and stores the generated flight parameters in the WQAR according to a pilot operation program, and finally carries out real-time communication on flight data and the high-throughput satellite through an antenna through a wireless access point, so that the feasibility verification, test and possible fault analysis work of a forecabin data communication link based on the high-throughput satellite are realized.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
Fig. 1 is a block diagram of an aircraft cockpit communication verification system according to an embodiment of the present application;
fig. 2 is an overall technical architecture diagram of an aircraft front cabin communication verification system according to an embodiment of the present application;
fig. 3 is a flowchart of a method for verifying aircraft nose cabin communication according to an embodiment of the present application.
Detailed Description
The present disclosure is not intended to be limited to the particular embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In addition, the technical features mentioned in the different embodiments of the present application described below may be combined with each other as long as they do not conflict with each other.
An embodiment of the present application provides an aircraft cockpit communication verification system, and referring to fig. 1, fig. 1 is a block diagram of an aircraft cockpit communication verification system provided in an embodiment of the present application, and it should be understood that the system may further include additional blocks not shown and/or may omit blocks shown, and the scope of the present application is not limited in this respect.
The verification system platform provided by the application is mainly divided into three modules: the system comprises a data source generation module 101, a signal generation module 102 and an avionics device simulation module 103.
The data source generating module 101 is configured to generate and store flight data by using a ground control simulation platform to drive simulated flight software, and send the flight data to the signal generating module 102.
Specifically, in some embodiments, flight data is generated and stored by data source generation module 101 using the air passenger a320 ground simulation maneuvering platform driven simulated flight software.
In some embodiments, the data source generation module 101 comprises: a simulated cockpit, a flight simulation system, a steering system, a display system and/or a computer system,
the simulation cockpit is a flight simulator ground simulation operation platform and comprises a top plate, a front panel, a rear electronic panel, a main instrument panel, cockpit equipment, a central operation platform and/or a seat;
the flight simulation system has simulated flight environments such as visual scenes, weather, sound and the like when the airplane flies, and performs data interaction with other system computers through the Ethernet so as to provide flight data of flight states, flight instruments and flight operations;
the control system comprises a control lever, pedals, an accelerator control console, a front wheel turning control handle, a landing gear handle and/or a stopping brake handle, and is used for simulating the flight driving control of a pilot in a cockpit and providing a rudder deflection angle, a slat deflection angle, a throttle lever angle and/or a multifunctional flow plate position for the flight simulation system;
the display system is used for providing the outer scene of the simulated cockpit in real time, reading related ground scene and model data according to a real scene database, rendering an image in real time, converting the image into a video signal and generating continuous images on a screen;
the computer system is used for simulating flight states of different weather and time through flight simulation software.
Specifically, the simulated cockpit is an air passenger A320 flight simulator ground simulation manipulation platform, is restored according to 1:1 carried out by a real A320 airplane cockpit, and has the ground and air characteristics of an A320 airplane. Complete roof function, complete front panel, rear electronic panel function, main instrument panel, cabin equipment, center console, seats, etc.
The flight simulation system has the simulated flight environments of visual scenes, weather, sound and the like when the airplane flies, and performs data interaction with other system computers through the Ethernet to provide data of flight states, flight instruments and flight operations for other systems.
And the control system is used for simulating the flight driving control of a pilot in the cockpit through the control system of the airman A320 flight simulator and is also responsible for providing states such as a rudder deflection angle, a slat deflection angle, an accelerator rod angle, a multifunctional flow plate position and the like for the flight simulation system. The control system comprises a control lever, a pedal, a throttle control console, a front wheel turning control handle, a landing gear handle, a parking brake handle and the like which are visible in the cabin. Operations may be implemented including, but not limited to: the method comprises the following steps of ground sliding, taking off, climbing, cruising, descending, carrying out, landing, starting and stopping of an airplane, visual flight, instrument flight, flight in special weather, automatic driving flight, navigation flight and the like.
And the display system provides a simulated extravehicular scene in real time, reads related scene and model data according to the real scene database, renders an image in real time, converts the image into a video signal and sends the video signal to the display system, and generates a real and continuous image on a screen. The display system can select two modes of television display or projection display.
A computer system: flight states of different weather and time are simulated through flight simulation software.
The signal generating module 102 is configured to generate a corresponding analog signal after receiving the flight data, and output the analog signal to the avionics device simulation module 103.
In some embodiments, the signal generation module 102 is configured to generate a corresponding analog signal based on the flight data via an ARINC429 bus signal converter implementation.
Specifically, after receiving the simulated flight data, the signal generation module 102 generates a simulated signal by using the board card and an API on the board card to implement ARINC429 bus signals, and outputs the simulated signal. ARINC429 is a standard for inter-airborne electronic device data transmission specifications proposed and promulgated by the american aviation engineering committee. The protocol standards specify digital information transfer requirements between avionics equipment and related systems. The ARINC429 bus adopts a twisted pair shielded wire to unidirectionally transmit digital data information in a serial mode, the transmission speed is divided into low-speed transmission and high-speed transmission, wherein the low-speed transmission rate is 12-14.5kb/s, and the high-speed transmission rate is 100kb/s.
The avionics device of the avionics device simulation module 103 comprises a flight data interface and management component, an air traffic service component, a control display unit and a wireless fast access recorder, and is used for receiving the analog signals through the flight data interface and management component, converting a part of the analog signals into ARINC717 data through the flight data interface and management component, analyzing and converting the data into engineering values in real time through built-in software after transmitting the engineering values to the wireless fast access recorder, performing related logic calculation triggering on the other part of the analog signals through an airplane state monitoring system of the flight data interface and management component or generating ACARS messages after the control display unit is operated, and enabling the wireless fast access recorder to be connected with an airborne satellite antenna unit through setting the air traffic service component to finally communicate with a high-flux satellite communication network in real time.
Specifically, the avionics device simulation module 103 mainly comprises the main stream avionics devices of the aircraft in service, and mainly comprises: flight data interface and management components (FDIMU), air traffic service components (ATSU), control display units (MCDU), wireless fast access recorders (WQAR).
In some embodiments, the flight data interface and management component is configured to acquire, collect, and process aircraft parameters, collect aircraft discrete and ARINC429 DITS data bus inputs, and output to a digital flight data recorder, and output data from the digital flight data recorder to the wireless fast access recorder;
the air traffic service component is used for providing a data link host platform, a router and an air traffic control application program to carry out data link communication and can carry out management of a data link medium;
the control display unit is used for inserting system control parameters, a flight plan and displaying information of flight progress and airplane performance;
the wireless fast access recorder is used for storing the flight data into a built-in solid-state flash memory PCMCIA PC card medium, connecting broadband satellite communication equipment and interconnecting the data of various avionics connected to the avionics simulation module 103 of the wireless fast access recorder with an electronic flight bag through WAP.
Specifically, FDIMU: the FDIMU is primarily responsible for acquiring, collecting and processing all required aircraft parameters to collect aircraft dispersion and ARINC429 DITS data bus inputs and output them to a Digital Flight Data Recorder (DFDR) and, in addition, may output DFDR data to WQAR.
ATSU: the ATSU is a core component of the ACARS system on the airbus, and is mainly used for providing a data link host platform, a router and an air traffic control application program for the airbus such as a318, a319, a320, a321, a330 and a340 to perform data link communication, and can manage a data link medium. By means of managing data link information exchange, the ATSU enables the pilot to report the airplane condition to a ground supervision center through data transmission connection (very high frequency voice communication system backup) between the airplane and an air traffic service center and between the airplane and an airline company.
MCDU: is the main input/display interface between the pilot and the Flight Management (FM) portion of the Flight Management and Guidance Computer (FMGC), and system control parameters, flight plans and displays information about flight schedule and aircraft performance can be inserted on the MCDU.
WQAR: WQAR is the same as ordinary QAR, is the compatible substitute plug-in of the existing digital ACMS (aircraft state monitoring system, link with sensor, detector on the aircraft, mainly carry on the airborne data acquisition and processing, can monitor aircraft state, performance and finish the special engineering investigation, its data form of transmission is through ACARS real-time message data, the transmission efficiency is low, the price is expensive, the general aviation department sends ACARS message data once half an hour, therefore generally all adopt QAR data that WQAR stores in order to analyze the data of the full flight of aircraft section), the recorder, it receives the digital data with Bipolar, biphase or Plesey format. Storing flight data in a built-in solid state flash memory PCMCIA PC card medium; after the wireless option airplane is configured to land and shut down, the WQAR first compresses and encrypts data, and then automatically sends the data to a wireless QAR ground base station (WGBS) of an airline company through a mobile phone network so as to obtain QAR data. In the verification platform, the WQAR has the functions of connecting broadband satellite communication equipment, realizing real-time communication based on a high-flux broadband satellite and providing a safety protection function. And secondly, the data of various avionics devices connected with the WQAR are interconnected with an Electronic Flight Bag (EFB) through the WAP.
The avionics equipment simulation module 103 is driven by a signal output by a board card through the signal generation module 102, the FDIMU generates ARINC717 data and transmits the ARINC717 data to the WQAR, the WQAR converts the data into an engineering value and transmits the engineering value to a related system and a terminal through a mobile phone 3G network or a high-flux broadband satellite, and in addition, the WQAR transmits an ACARS message generated by the MCDU in real time through communication of an ATSU high-frequency interface by means of a mobile phone network or a high-flux broadband satellite network, namely, the function of 'ACARS OVER IP'. The method comprises the steps that analog signals are transmitted to an FDIMU through a data transmission channel on a board card, one part of the analog signals are converted into ARINC717 data through the FDIMU, the ARINC717 data are transmitted to a WQAR and then are analyzed and converted into engineering values through built-in software in real time, the other part of the analog signals are triggered through related logic calculation of an FDIMU ACMS or generate ACARS messages after MCDU operation, the WQAR is connected with an airborne satellite antenna unit through setting ATSU, and finally the ATSU is communicated with a high-flux satellite communication network in real time.
In some embodiments, further comprising:
and the airborne power supply module is used for controlling the working state of the avionics equipment and switching between high-frequency satellite links and high-speed satellite links.
In some embodiments, further comprising:
the device comprises a rack, wherein a special switch and a data loading interface of each avionic device are arranged on the rack, the special switch is used for switching on and off the devices, and the data loading interface is used for updating software of the avionic devices.
The following embodiments specifically illustrate a platform of the aircraft forward cabin data communication verification system based on high-throughput satellite approaching to the real environment proposed by the present application by referring to fig. 2:
s1: the ground simulation operation platform (the simulation cabin of the data source generation module 101) of the front cabin communication verification platform is of an A320 model;
s2: the ground simulation operation platform is provided with Prepar3D V software to simulate a real flight environment and support generation of simulated flight data, display of a test bed equipment instrument and output of Prepar3D simulated flight data;
s3: the platform supports a Ballard board card to realize conversion between Prepar3D simulated flight data and avionics bus data, and finally ARINC429 and 717 bus data can be generated and accessed into a test bed.
S4: the platform is provided with an airborne power supply module which can output 28V direct current for the use of the avionic equipment;
s5: the platform is provided with a rack, a special switch and a data loading interface of each avionic device are arranged on the rack, the special switch is used for turning on and off the avionic devices and can be turned off when the avionic devices do not need to work so as to prolong the service life of the avionic devices, and the data loading interface is used for updating the software of the avionic devices.
S6: the verification platform supports integration with an existing airborne server and an existing airborne satellite antenna to support real-time communication of flight data and a high-throughput satellite link;
s7: firstly, forming an air passenger A320 ground simulation operation platform based on a simulation cockpit, a flight simulation system, an operation system and a display system, and performing simulation flight driving operation by a driver according to a flight operation manual;
s8: the ground simulation control platform drives Prepar3D V simulation flight software to generate flight data of different types of airplanes for taking off and landing from different airports in different time and weather according to the control of a driver;
s9: secondly, converting the data signals generated by the Prepar3D into electric signals (analog signals) according to ARINC429 coding rules through a Ballard card, namely an ARINC429 bus board card, and transmitting the electric signals to the avionics equipment of the avionics equipment simulation module 103 (comprising a flight data interface and management component (FDIMU), an air traffic service component (ATSU), a control display unit (MCDU) and a wireless fast access recorder (WQAR)); the specific process is that firstly, the board card is connected to the computer through the USB interface, the function is called to enable the operating system of the host to obtain access to the hardware of the equipment, the hardware configuration before the equipment is reset, and the required equipment channel is configured. Initializing data, defining the data by referring to an interface control file (ICD) file, exchanging data between a computer and equipment, finally converting a flight data signal generated by Prepar3D into an ARINC429/ARINC717 electric signal, and transmitting the electric signal to avionic equipment;
s10: the avionics equipment simulation module 103 is driven by signals output by the board card through the signal generation module 102 and is interconnected according to an A320 airplane WDM manual, and each piece of avionics equipment after interconnection is operated according to airborne specifications so as to ensure normal work of the avionics equipment;
s11: the MCDU is used as a unique human-computer interface interaction window for debugging and controlling the ATSU and the FDIMU;
s12: the FDIMU generates an Arinc717 data report by recording flight parameters including airspeed, altitude, unit operation and other flight data, and transmits the Arinc717 data report to the WQAR, and the WQAR can analyze and convert various parameters of the airplane into engineering values in real time through built-in software such as TMI and AMA; generating an ARINC619 message through ACMS software and a system and transmitting the ARINC619 message to the ATSU through an ACARS interface;
s13: after the data transmitted by the FDIMU is converted into engineering values by the WQAR, the data are communicated with a high-flux satellite in real time through an airborne antenna by utilizing the routing function of the data, or are communicated with an airborne EFB through wireless flight data analysis interface software (WFDAI);
s14: the ATSU can convert ARINC619 messages transmitted by the FDIMU into ARINC618 protocol messages through Honeywell AOC database software configuration, mainly comprises OOOI (OUT/OFF/ONN/INN) messages, position messages and the like, updates the database of the ATSU through ADL (aircraft Dataloader) and a DATA LOAD interface of a test bench, provides ACARS message link communication functions of the ATSU and WQAR, and realizes satellite link transmission test through configuration in ATSU AOC software.
To sum up, the application constructs an aircraft front cabin communication verification system platform based on a high-flux communication satellite, the system platform synthesizes an air passenger A320 flight simulator simulation operation platform, a Ballard card, and various avionics devices such as MCDU, ATSU, FDIMU, WQAR and the like to construct a comprehensive avionics verification system platform close to the real passing environment of the aircraft front cabin, so as to carry out experiments of leading-edge technologies such as feasibility verification, efficiency evaluation, fault analysis and the like of a communication data link of the front cabin high-flux satellite.
According to the system, a high-throughput satellite-based forecabin data communication verification platform is constructed by avionics devices (the avionics devices in the avionics device simulation module, namely WQAR, FDIMU, ATSU and MCDU) in an avionics device simulation module, namely flight data interface and management module (FDIMU), air traffic service module (ATSU), and the like, wherein the avionics devices are used by an air passenger A320 flight comprehensive data module.
In order to solve the feasibility verification problem of a front cabin data communication link based on a high-throughput satellite, a full-motion flight simulator close to the driving environment of a real pilot is used for simulating the ground and air characteristics of the airplane in the full flight section from takeoff to landing, and the flight parameters are interconnected with a ground base station in real time through the high-throughput satellite by means of a WQAR (wireless information quality assurance) internal integrated routing function. The whole scheme simulates a real link of the aircraft forecabin data communication and lays a platform foundation for verifying the feasibility of the high-flux data communication technology of the aircraft forecabin based on the high-flux satellite.
The verification platform constructs a communication and control environment similar to a real airplane data transmission link through an air passenger A320 flight simulator simulation operation platform and main stream avionics equipment of an in-service airplane, creatively provides a feasible verification platform for a high-flux satellite-based front cabin communication scheme, and an airborne satellite communication solution provider can also utilize the platform to perform efficiency evaluation, fault analysis, development of an airplane front cabin intelligent communication scheme and the like on the whole communication link.
An embodiment of the present application provides a method for verifying communication of a front cabin of an aircraft, and referring to fig. 3, fig. 3 is a flowchart of a method for verifying communication of a front cabin of an aircraft provided in an embodiment of the present application, it should be understood that the method may further include additional blocks that are not shown and/or may omit blocks that are shown, and the scope of the present application is not limited in this respect.
In step 201, the ground simulation control platform drives the simulation flight software to generate flight data of airplanes of different types at different time and in different weather according to the control of the driver, and the airplanes take off and land from different airports.
In step 202, the flight data is converted into corresponding analog signals by the board card and transmitted to the avionics equipment of an avionics equipment simulation module, wherein the avionics equipment simulation module comprises a flight data interface and management component, an air traffic service component, a control display unit and a wireless fast access recorder.
At step 203, the flight data interface and management component receives the analog signal, a part of the analog signal is converted into ARINC717 data through the flight data interface and management component, the converted data is transmitted to the wireless fast access recorder and then is analyzed and converted into engineering values through built-in software in real time, another part of the analog signal is triggered by relevant logic calculation through an aircraft state monitoring system of the flight data interface and management component or ACARS messages are generated after the control display unit is operated, the wireless fast access recorder is connected with an onboard satellite antenna unit through the arrangement of the air traffic service component, and finally the high-flux satellite communication network is communicated in real time.
In some embodiments, the avionics device that converts the flight data into corresponding analog signals through the board card and transmits the analog signals to the avionics device simulation module includes:
firstly, a board card is connected to a computer through a USB interface, a function is called to enable an operating system of a host to obtain access to equipment hardware, the hardware configuration before the equipment is reset, and a required equipment channel is configured;
and initializing data, defining the data by referring to an interface control file, exchanging data between a computer and equipment, finally converting the flight data into the analog signal, and transmitting the analog signal to the avionic equipment of the avionic equipment simulation module.
In some embodiments, the ground simulation maneuvering platform is equipped with Prepar3D V software to simulate real flight environment and support the generation of the flight data, instrumentation display on the test rig, and output of the flight data.
For the specific implementation method, reference is made to the foregoing system embodiment, which is not described herein again.
The present application may be methods, apparatus, systems, and/or computer program products. The computer program product may include a computer-readable storage medium having computer-readable program instructions embodied thereon for carrying out various aspects of the present application.
The computer readable storage medium may be a tangible device that can hold and store the instructions for use by the instruction execution device. The computer readable storage medium may be, for example, but not limited to, an electronic memory device, a magnetic memory device, an optical memory device, an electromagnetic memory device, a semiconductor memory device, or any suitable combination of the foregoing. More specific examples (a non-exhaustive list) of the computer readable storage medium would include the following: a portable computer diskette, a hard disk, a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), a Static Random Access Memory (SRAM), a portable compact disc read-only memory (CD-ROM), a Digital Versatile Disc (DVD), a memory stick, a floppy disk, a mechanical coding device, such as punch cards or in-groove projection structures having instructions stored thereon, and any suitable combination of the foregoing. Computer-readable storage media as used herein is not to be construed as transitory signals per se, such as radio waves or other freely propagating electromagnetic waves, electromagnetic waves propagating through a waveguide or other transmission medium (e.g., optical pulses through a fiber optic cable), or electrical signals transmitted through electrical wires.
The computer-readable program instructions described herein may be downloaded from a computer-readable storage medium to a respective computing/processing device, or to an external computer or external storage device via a network, such as the internet, a local area network, a wide area network, and/or a wireless network. The network may include copper transmission cables, fiber optic transmission, wireless transmission, routers, firewalls, switches, gateway computers and/or edge servers. The network adapter card or network interface in each computing/processing device receives computer-readable program instructions from the network and forwards the computer-readable program instructions for storage in a computer-readable storage medium in the respective computing/processing device.
The computer program instructions for carrying out operations of the present application may be assembler instructions, instruction Set Architecture (ISA) instructions, machine-related instructions, microcode, firmware instructions, state setting data, or source code or object code written in any combination of one or more programming languages, including an object oriented programming language such as Smalltalk, C + + or the like and conventional procedural programming languages, such as the "C" programming language or similar programming languages. The computer-readable program instructions may execute entirely on the user's computer, partly on the user's computer, as a stand-alone software package, partly on the user's computer and partly on a remote computer or entirely on the remote computer or server. In the latter scenario, the remote computer may be connected to the user's computer through any type of network, including a Local Area Network (LAN) or a Wide Area Network (WAN), or the connection may be made to an external computer (for example, through the Internet using an Internet service provider). In some embodiments, the electronic circuitry can execute computer-readable program instructions to implement aspects of the present application by utilizing state information of the computer-readable program instructions to personalize the electronic circuitry, such as a programmable logic circuit, a Field Programmable Gate Array (FPGA), or a Programmable Logic Array (PLA).
Various aspects of the present application are described herein with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems) and computer program products according to embodiments of the application. It will be understood that each block of the flowchart illustrations and/or block diagrams, and combinations of blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer-readable program instructions.
These computer-readable program instructions may be provided to a processing unit of a general purpose computer, special purpose computer, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processing unit of the computer or other programmable data processing apparatus, create means for implementing the functions/acts specified in the flowchart and/or block diagram block or blocks. These computer-readable program instructions may also be stored in a computer-readable storage medium that can direct a computer, programmable data processing apparatus, and/or other devices to function in a particular manner, such that the computer-readable medium storing the instructions comprises an article of manufacture including instructions which implement the function/act specified in the flowchart and/or block diagram block or blocks.
The computer readable program instructions may also be loaded onto a computer, other programmable data processing apparatus, or other devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other devices to produce a computer implemented process such that the instructions which execute on the computer, other programmable apparatus or other devices implement the functions/acts specified in the flowchart and/or block diagram block or blocks.
The flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of instructions, which comprises one or more executable instructions for implementing the specified logical function(s). In some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
It is noted that, unless expressly stated otherwise, all features disclosed in this specification (including any accompanying claims, abstract and drawings) may be replaced by alternative features serving the same, equivalent or similar purpose. Thus, unless expressly stated otherwise, each feature disclosed is one example only of a generic series of equivalent or similar features. Where used, further, preferably, still further and more preferably is a brief introduction to the description of the other embodiment based on the foregoing embodiment, the combination of the contents of the further, preferably, still further or more preferably back strap with the foregoing embodiment being a complete construction of the other embodiment. Several further, preferred, still further or more preferred arrangements of the back tape of the same embodiment may be combined in any combination to form a further embodiment.
Although the present application has been described in detail with respect to the general description and the specific examples, it will be apparent to those skilled in the art that certain changes and modifications may be made based on the present application. Accordingly, such modifications and improvements are intended to be within the scope of this invention as claimed.
Claims (10)
1. An aircraft forward cabin communication verification system, comprising: a data source generating module, a signal generating module and an avionics equipment simulation module,
the data source generation module is used for generating and storing flight data by using a ground control simulation platform to drive simulated flight software and sending the flight data to the signal generation module;
the signal generation module is used for generating a corresponding analog signal after receiving the flight data and outputting the analog signal to the avionic device simulation module;
the avionics device of the avionics device simulation module comprises a flight data interface and management assembly, an air traffic service assembly, a control display unit and a wireless fast access recorder, and is used for receiving the analog signals through the flight data interface and management assembly, converting a part of the analog signals into ARINC717 data through the flight data interface and management assembly, transmitting the ARINC717 data to the wireless fast access recorder, analyzing and converting the ARINC717 data into engineering values in real time through built-in software, performing related logic calculation triggering on the other part of the analog signals through an airplane state monitoring system of the flight data interface and management assembly or generating ACARS messages after the control display unit is operated, and enabling the wireless fast access recorder to be connected with an onboard satellite antenna unit through setting the air traffic service assembly to finally communicate with a high-flux satellite communication network in real time.
2. The aircraft forward cabin communication verification system of claim 1,
the flight data interface and management component is used for acquiring, collecting and processing airplane parameters, collecting airplane discrete and ARINC429 DITS data bus input, outputting the airplane discrete and ARINC429 DITS data bus input to a digital flight data recorder, and outputting data of the digital flight data recorder to the wireless quick access recorder;
the air traffic service component is used for providing a data link host platform, a router and an air traffic control application program to carry out data link communication and manage a data link medium;
the control display unit is used for inserting system control parameters, a flight plan and displaying information of flight progress and airplane performance;
the wireless fast access recorder is used for storing the flight data into a built-in solid-state flash memory PCMCIA PC card medium, connecting broadband satellite communication equipment and interconnecting the data of various avionic equipment connected to the avionic equipment simulation module of the wireless fast access recorder with an electronic flight bag through WAP.
3. The aircraft cockpit communication verification system of claim 1, wherein said data source generation module comprises: a simulated cockpit, a flight simulation system, a steering system, a display system and/or a computer system,
the simulation cockpit is a flight simulator ground simulation operation platform and comprises a top plate, a front panel, a rear electronic panel, a main instrument panel, cockpit equipment, a central operation platform and/or a seat;
the flight simulation system has a visual scene, weather and sound simulation flight environment when the airplane flies, and performs data interaction with other system computers through Ethernet to provide flight data of flight states, flight instruments and flight operations;
the control system comprises a control lever, pedals, an accelerator control console, a front wheel turning control handle, a landing gear handle and/or a stopping brake handle, and is used for simulating the flight driving control of a pilot in a cockpit and providing a rudder deflection angle, a slat deflection angle, a throttle lever angle and/or a multifunctional flow plate position for the flight simulation system;
the display system is used for providing the outer scene of the simulated cockpit in real time, reading related ground scene and model data according to a real scene database, rendering an image in real time, converting the image into a video signal and generating continuous images on a screen;
the computer system is used for simulating flight states of different weather and time through flight simulation software.
4. The aircraft forward cabin communication verification system of claim 1,
the signal generation module is used for generating corresponding analog signals based on the flight data through an ARINC429 bus signal converter.
5. The aircraft forward cabin communication verification system of claim 1, further comprising:
and the airborne power supply module is used for controlling the working state of the avionics equipment and switching between high-frequency satellite links and high-speed satellite links.
6. The aircraft nose cabin communication verification system of claim 1, further comprising:
the device comprises a rack, wherein a special switch and a data loading interface of each avionic device are arranged on the rack, the special switch is used for switching on and off the devices, and the data loading interface is used for updating software of the avionic devices.
7. An aircraft nose cabin communication verification method is characterized by comprising the following steps:
driving simulated flight software to generate flight data of airplanes of different types at different time and in different weather according to the operation of a driver through a ground simulation operation platform, wherein the flight data are taken off and landed from different airports;
the flight data are converted into corresponding analog signals through the board card and transmitted to avionic equipment of an avionic equipment simulation module, and the avionic equipment simulation module comprises a flight data interface and management assembly, an air traffic service assembly, a control display unit and a wireless fast access recorder;
the flight data interface and the management component are used for receiving the analog signals, one part of the analog signals are converted into ARINC717 data through the flight data interface and the management component, the ARINC717 data are transmitted to the wireless quick access recorder and then analyzed and converted into engineering values through built-in software in real time, the other part of the analog signals are triggered through relevant logic calculation of an aircraft state monitoring system of the flight data interface and the management component or generate ACARS messages after the control display unit is operated, the wireless quick access recorder is connected with an airborne satellite antenna unit through the arrangement of the air traffic service component, and finally the wireless quick access recorder is communicated with a high-flux satellite communication network in real time.
8. The method for verifying communication of the aircraft nose cabin according to claim 7, wherein the step of converting the flight data into corresponding analog signals through the board card and transmitting the analog signals to the avionics device of the avionics device simulation module comprises:
firstly, a board card is connected to a computer through a USB interface, a function is called to enable an operating system of a host to obtain access to equipment hardware, the hardware configuration before the equipment is reset, and a required equipment channel is configured;
and initializing data, defining the data by referring to an interface control file, exchanging data between a computer and equipment, finally converting the flight data into the analog signal, and transmitting the analog signal to the avionic equipment of the avionic equipment simulation module.
9. The aircraft nose cabin communication verification method of claim 7,
the ground simulation manipulation platform is provided with Prepar3D V software to simulate a real flight environment and support generation of the flight data, instrument display on a test bed device and output of the flight data.
10. A computer storage medium having a computer program stored thereon, wherein the computer program, when executed by a machine, implements the steps of the method of any of claims 7 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310121908.7A CN115811373B (en) | 2023-02-16 | 2023-02-16 | Communication verification system and method for front cabin of airplane and storage medium |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310121908.7A CN115811373B (en) | 2023-02-16 | 2023-02-16 | Communication verification system and method for front cabin of airplane and storage medium |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115811373A CN115811373A (en) | 2023-03-17 |
| CN115811373B true CN115811373B (en) | 2023-04-11 |
Family
ID=85487877
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310121908.7A Active CN115811373B (en) | 2023-02-16 | 2023-02-16 | Communication verification system and method for front cabin of airplane and storage medium |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115811373B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116488709B (en) * | 2023-05-24 | 2024-07-02 | 飞天联合（北京）系统技术有限公司 | Method and device for generating, converting and transmitting aircraft ACARS (aircraft access control information system) message |
| CN117092932B (en) * | 2023-10-19 | 2024-01-23 | 西安羚控电子科技有限公司 | Simulation test signal monitoring method and system |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6234799B1 (en) * | 1998-04-06 | 2001-05-22 | American Gnc Corporation | Real-time IMU simulator |
| CN206115770U (en) * | 2016-05-31 | 2017-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft flight analogue test device |
| CN114884601A (en) * | 2022-02-26 | 2022-08-09 | 国营芜湖机械厂 | Avionics integrated test time synchronization system based on satellite simulator and synchronization method thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020173888A1 (en) * | 2001-05-21 | 2002-11-21 | Shelton Robert Leo | Aircraft location and tracking system |
-
2023
- 2023-02-16 CN CN202310121908.7A patent/CN115811373B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6234799B1 (en) * | 1998-04-06 | 2001-05-22 | American Gnc Corporation | Real-time IMU simulator |
| CN206115770U (en) * | 2016-05-31 | 2017-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft flight analogue test device |
| CN114884601A (en) * | 2022-02-26 | 2022-08-09 | 国营芜湖机械厂 | Avionics integrated test time synchronization system based on satellite simulator and synchronization method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 许宗飞 等.基于GPS射频模拟信号源的无人机导航系统研究.计算机测量与控制.2010,(第03期),第655-657页. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115811373A (en) | 2023-03-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115811373B (en) | Communication verification system and method for front cabin of airplane and storage medium | |
| US7271740B2 (en) | System and process for providing improved aircraft operational safety | |
| US10511515B1 (en) | Protocol buffer avionics system | |
| CN110278023A (en) | A kind of application system and method based on vacant lot broadband connections | |
| Bailey et al. | Experimental validation: Subscale aircraft ground facilities and integrated test capability | |
| CN112650279B (en) | Cloud flight management system and cloud flight management method for airplane | |
| EP3761287A1 (en) | Systems and methods for remotely monitoring an aircraft | |
| CN116469294A (en) | Flight simulation and air traffic control simulation interaction device, combined training system and method | |
| Sullivan et al. | The NASA 747-400 flight simulator-A national resource for aviation safety research | |
| CN113256843B (en) | Integrated flight recording device and method | |
| CN109871565A (en) | A kind of integrated electronic system simulator of general-purpose aircraft | |
| Zhu et al. | UAV-based flight inspection system | |
| Lenz et al. | Simulation platform for reduced crew operations—A case study | |
| Yin et al. | Flight Autonomy Impact To The Future Avionics Architecture | |
| Yun-sheng et al. | A flexible airborne datalink system architecture for civil helicopters | |
| Zeitler et al. | Datalink System Maturation and Flight Testing of the Sagitta UAS Demonstrator | |
| Mulkerin | Free flight is in the future: Large-scale controller pilot data link communications emulation testbed | |
| Garbarino et al. | In flight validation of a satellite based weather awareness and hazard avoidance system for general aviation | |
| Griebel et al. | DART–providing distress assistance with real-time aircraft telemetry | |
| Sullivan et al. | Implementing FANS in the NASA 747-400 flight simulator for airspace operational research | |
| CN217008440U (en) | Simulation training platform for function test of integrated avionics system | |
| Cummings | Software radios for airborne platforms | |
| Stough III et al. | Reducing aviation weather-related accidents through high-fidelity weather information distribution and presentation | |
| Formisano | Clean Sky 2 LPA DISruptive COckpit Large Aircraft demonstrator (aka DisCo demonstrator) | |
| Howell et al. | The NASA Langley Research Center's Unmanned Aerial System Surrogate research aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |