CN117031984A - Electronic instrument simulation system of full-motion aircraft simulator - Google Patents
Electronic instrument simulation system of full-motion aircraft simulator Download PDFInfo
- Publication number
- CN117031984A CN117031984A CN202311043909.0A CN202311043909A CN117031984A CN 117031984 A CN117031984 A CN 117031984A CN 202311043909 A CN202311043909 A CN 202311043909A CN 117031984 A CN117031984 A CN 117031984A
- Authority
- CN
- China
- Prior art keywords
- data
- simulation
- display
- module
- display unit
- 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.)
- Pending
Links
- 238000004088 simulation Methods 0.000 title claims abstract description 225
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 27
- 238000012545 processing Methods 0.000 claims description 48
- 239000011159 matrix material Substances 0.000 claims description 13
- 238000013461 design Methods 0.000 claims description 8
- 238000005538 encapsulation Methods 0.000 claims description 4
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 238000004806 packaging method and process Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000012549 training Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B17/00—Systems involving the use of models or simulators of said systems
- G05B17/02—Systems involving the use of models or simulators of said systems electric
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention discloses an electronic instrument simulation system of a full-motion aircraft simulator, and relates to the technical field of instrument simulation. The invention comprises the following steps: a main control computer and an electronic instrument simulation system; the main control computer is connected with the electronic instrument simulation system through a VDN network; the main control computer is used for generating electronic flight control simulation data, weather radar simulation data and air data inertial reference system simulation data; the electronic instrument simulation system is used for generating and displaying a plurality of instrument interfaces according to the electronic flight control simulation data, the weather radar simulation data and the air data inertial reference system simulation data. According to the invention, the main control computer and the electronic instrument simulation system are arranged, so that the rationality and the accuracy of the simulation of the electronic instrument of the full-motion aircraft simulator can be improved.
Description
Technical Field
The invention relates to the technical field of instrument simulation, in particular to an electronic instrument simulation system of a full-motion aircraft simulator.
Background
With the rapid development of modern aviation technology, the types of instruments and equipment on board the aviation field are increased. The use of more advanced airborne equipment provides a pilot with quicker and more comprehensive aircraft position, state information and battlefield situation information, and simultaneously provides higher requirements for the pilot to master the use operation and principle of various airborne equipment. Full-motion flight simulators are an effective means of training pilots in common use today in the international aviation world. The simulation avionic instrument system influences the reality of the flight simulation and the coverage rate of training tasks, is an important technical index for determining the simulation degree and the advanced degree of the flight simulator, and influences the advanced level of the whole simulator.
The current instrument simulation technology does not provide a good solution for unified processing logic running between different modules, and has great defects in terms of reusability of programs, development efficiency and reduced coupling among various parts of business logic. Meanwhile, the real-time acquisition and analysis of the data of each system of the aircraft are poor, the fidelity of an instrument system is reduced, and the identification level of the flight simulator is influenced.
Disclosure of Invention
The invention aims to provide an electronic instrument simulation system of a full-motion aircraft simulator, which can improve the rationality and the precision of the simulation of the electronic instrument of the full-motion aircraft simulator.
In order to achieve the above object, the present invention provides the following solutions:
an all-terrain aircraft simulator electronic instrument simulation system, comprising: a main control computer and an electronic instrument simulation system;
the main control computer is connected with the electronic instrument simulation system through a VDN network;
the main control computer is used for generating electronic flight control simulation data, weather radar simulation data and air data inertial reference system simulation data;
the electronic instrument simulation system is used for generating and displaying a plurality of instrument interfaces according to the electronic flight control simulation data, the weather radar simulation data and the air data inertial reference system simulation data.
Optionally, the weather radar simulation data is ARINC453 data;
the electronic flight control simulation data and the air data inertial reference system simulation data are ARINC429 data.
Optionally, the main control computer includes:
the system comprises an electronic flight control simulation unit, a weather radar simulation unit and an atmospheric data inertial reference system simulation unit;
the electronic flight control simulation unit, the weather radar simulation unit and the air data inertial reference system simulation unit are all connected with the VDN network;
the electronic flight control simulation unit is used for generating electronic flight control simulation data;
the weather radar simulation unit is used for generating weather radar simulation data;
the atmosphere data inertial reference system simulation unit is used for generating atmosphere data inertial reference system simulation data.
Optionally, the electronic instrument analog simulation system includes:
the display management simulation module group and the display simulation subsystem are connected in sequence;
the display management simulation module group is connected with a main control computer through the VDN network; the display management simulation module group is used for acquiring an SSM mark matrix value and an SSM state matrix value according to an ARINC protocol, checking the validity of the received ARINC429 and ARINC453 data based on the SSM mark matrix value and the SSM state matrix value, converting the ARINC429 data into ARINC629 data, transmitting the ARINC629 data to the data processing module, and transmitting the ARINC453 data to the data processing module;
the data processing module is used for analyzing and acquiring data according to ARINC453 and ARINC629 protocols, analyzing and acquiring data driving variables according to the data content in the received ARINC data packet, and transmitting the acquired data driving variables to the display unit data driving module;
the display simulation subsystem is used for analyzing and acquiring data according to ARINC453 and ARINC629 protocols, analyzing and acquiring data driving variables according to the data content in the received ARINC data packet, generating a plurality of instrument interfaces and displaying the instrument interfaces, binding the data driving variables with a plurality of elements of the instrument interfaces, and driving the conversion of the states of each element in the instrument interfaces according to the data driving variables.
Optionally, the managing the simulation module group includes:
the system comprises a first display management simulation module, a second display management simulation module and a third display management simulation module;
the first display management simulation module, the second display management simulation module and the third display management simulation module are all connected with a main control computer through the VDN network; the first display management simulation module, the second display management simulation module and the third display management simulation module are also connected with the display simulation subsystem;
the first display management simulation module is used for analyzing and acquiring ARINC data required by the driving position display unit according to ARINC453 and ARINC429 protocols, analyzing and converting ARINC429 signals into ARINC629 signals according to the received ARINC data content required by the driving position display unit, and sending the ARINC629 signals and the ARINC453 signals to the display simulation subsystem;
the second display management simulation module is used for analyzing and acquiring ARINC data required by the copilot display unit according to ARINC453 and ARINC429 protocols, analyzing and converting ARINC429 signals into ARINC629 signals according to the received ARINC data content required by the copilot display unit, and sending the ARINC629 signals and the ARINC453 signals to the display simulation subsystem;
the third display management simulation module is used for analyzing and obtaining ARINC data required by the standby display unit according to ARINC453 and ARINC429 protocols, analyzing and converting ARINC429 signals into ARINC629 signals according to the received ARINC data content required by the standby display unit, and sending the ARINC629 signals and the ARINC453 to the display simulation subsystem.
Optionally, the display simulation subsystem includes:
the display device comprises a data processing module, a display unit data driving module, a graphic processing module and a display unit group which are connected in sequence;
the data processing module is connected with the display unit data driving module;
the data processing module is used for analyzing and acquiring data according to ARINC453 and ARINC629 protocols, analyzing and acquiring data driving variables according to the data content in the received ARINC data packet, and sending the acquired data driving variables to the display unit data driving module;
the display unit data driving module is used for grouping and packaging driving variables updated in real time according to the data driving business logic; the display unit driving module is also used for sending the data driving variable to the graphic processing module and updating the data of elements in the graphic processing module in batches so as to realize dynamic real-time display of each display unit;
the graphic processing module is used for carrying out graphic interface design on each component in the display unit group and driving each display unit element to display according to the data drive after grouping and encapsulation;
the display unit group is used for displaying according to the graphical interface design and the data driving result.
Optionally, the display unit group includes:
a plurality of display units;
and the display units are connected with the graphic processing module.
Optionally, the system further comprises: a button state acquisition module;
the button state acquisition module is connected with the display management simulation module group;
the button state acquisition module is used for sending discrete signals to the display management simulation module group when the button state is pressed.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the invention provides an electronic instrument simulation system of a full-motion aircraft simulator, which comprises: a main control computer and an electronic instrument simulation system; the main control computer is connected with the electronic instrument simulation system through a VDN network; the main control computer is used for generating electronic flight control simulation data, weather radar simulation data and air data inertial reference system simulation data; the electronic instrument simulation system is used for generating and displaying a plurality of instrument interfaces according to the electronic flight control simulation data, the weather radar simulation data and the air data inertial reference system simulation data. According to the invention, the main control computer and the electronic instrument simulation system are arranged, so that the rationality and the accuracy of the simulation of the electronic instrument of the full-motion aircraft simulator can be improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of an electronic instrument simulation system of a full-motion aircraft simulator in an embodiment of the invention;
FIG. 2 is a schematic diagram of the CHECKHDG element of the FBMSG module according to the embodiment of the present invention;
FIG. 3 is a schematic diagram of a software architecture of an electronic instrument simulation system of a full-motion aircraft simulator in an embodiment of the invention;
fig. 4 is a schematic diagram of a management simulation module according to an embodiment of the invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide an electronic instrument simulation system of a full-motion aircraft simulator, which can improve the rationality and the precision of the simulation of the electronic instrument of the full-motion aircraft simulator.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Example 1
As shown in fig. 1 and 3, the present embodiment provides an electronic instrument simulation system of a full-motion aircraft simulator, including: a main control computer and an electronic instrument simulation system; the main control computer is connected with the electronic instrument simulation system through a VDN network; the main control computer is used for generating electronic flight control simulation data, weather radar simulation data and air data inertial reference system simulation data; the electronic instrument simulation system is used for generating and displaying a plurality of instrument interfaces according to the electronic flight control simulation data, the weather radar simulation data and the air data inertial reference system simulation data. The meteorological radar simulation data are ARINC453 data; the electronic flight control simulation data and the air data inertial reference system simulation data are ARINC429 data.
The main control computer comprises: the system comprises an electronic flight control simulation unit, a weather radar simulation unit and an atmospheric data inertial reference system simulation unit; the electronic flight control simulation unit, the weather radar simulation unit and the air data inertial reference system simulation unit are all connected with the VDN network; the electronic flight control simulation unit is used for generating electronic flight control simulation data; the weather radar simulation unit is used for generating weather radar simulation data; the atmosphere data inertial reference system simulation unit is used for generating atmosphere data inertial reference system simulation data.
The electronic instrument simulation system comprises: the display management simulation module group and the display simulation subsystem are connected in sequence; the display management simulation module group is connected with the main control computer through a VDN network; the display management simulation module group is used for acquiring an SSM mark matrix value and an SSM state matrix value according to an ARINC protocol, carrying out validity check on the received ARINC429 and ARINC453 data based on the SSM mark matrix value and the SSM state matrix value, converting the ARINC429 data into ARINC629 data, sending the ARINC629 data to the data processing module, and sending the ARINC453 data to the data processing module; the data processing module is used for analyzing and acquiring data according to ARINC453 and ARINC629 protocols, analyzing and acquiring data driving variables according to the data content in the received ARINC data packet, and transmitting the acquired data driving variables to the display unit data driving module; the display simulation subsystem is used for analyzing and acquiring data according to ARINC453 and ARINC629 protocols, analyzing and acquiring data driving variables according to the data content in the received ARINC data packet, generating a plurality of instrument interfaces and displaying the instrument interfaces, binding the data driving variables with a plurality of elements of the instrument interfaces, and driving the conversion of the states of each element in the instrument interfaces according to the data driving variables.
The management simulation module group includes: the system comprises a first display management simulation module, a second display management simulation module and a third display management simulation module; the first display management simulation module, the second display management simulation module and the third display management simulation module are all connected with the main control computer through a VDN network; the first display management simulation module, the second display management simulation module and the third display management simulation module are also connected with the display simulation subsystem; the first display management simulation module is used for analyzing and acquiring ARINC data required by the driving position display unit according to ARINC453 and ARINC429 protocols, analyzing and converting ARINC429 signals into ARINC629 signals according to the received ARINC data content required by the driving position display unit, and sending the ARINC629 signals and the ARINC453 signals to the display simulation subsystem; the second display management simulation module is used for analyzing and acquiring ARINC data required by the copilot display unit according to ARINC453 and ARINC429 protocols, analyzing and converting ARINC429 signals into ARINC629 signals according to the received ARINC data content required by the copilot display unit, and sending the ARINC629 signals and the ARINC453 signals to the display simulation subsystem; the third display management simulation module is used for analyzing and obtaining ARINC data required by the standby display unit according to ARINC453 and ARINC429 protocols, analyzing and converting ARINC429 signals into ARINC629 signals according to the received ARINC data content required by the standby display unit, and sending the ARINC629 signals and the ARINC453 to the display simulation subsystem.
The display simulation subsystem (i.e., the display simulation system in fig. 1) includes: the display device comprises a data processing module, a display unit data driving module, a graphic processing module and a display unit group which are connected in sequence; the data processing module is connected with the display unit data driving module; the data processing module is used for analyzing and acquiring data according to ARINC453 and ARINC629 protocols, analyzing and acquiring data driving variables according to the data content in the received ARINC data packet, and transmitting the acquired data driving variables to the display unit data driving module; the display unit data driving module is used for grouping and packaging driving variables updated in real time according to the data driving business logic; the display unit driving module is also used for sending the data driving variable to the graphic processing module and updating the data of elements in the graphic processing module in batches so as to realize the dynamic real-time display of each display unit; the graphic processing module is used for carrying out graphic interface design on each component in the display unit group and driving each display unit element to display according to the data drive after the grouping encapsulation; the display unit group is used for displaying according to the graphical interface design and the data driving result.
The display unit group includes: a plurality of display units; the plurality of display units are all connected with the graphic processing module.
The invention provides an electronic instrument simulation system of a full-motion aircraft simulator, which comprises the following components: a button state acquisition module; the button state acquisition module is connected with the display management simulation module group; the button state acquisition module is used for sending discrete signals to the display management simulation module group when the button state is pressed.
Specifically, the invention comprises a main control computer, a network VDN and an electronic instrument simulation system; the main control computer comprises an electronic flight control simulation unit, a weather radar simulation unit and an atmosphere data inertial reference system simulation unit; the electronic instrument simulation system comprises a network VND, a display management simulation module, a button/switch, a data processing module and a display simulation system; the display simulation system comprises a display unit data driving module, a graphic processing module and a display unit.
Further, the electronic flight control simulation unit transmits ARINC453 data to the display management simulation module through the ARINC453 channel and the network VDN; the ARINC429 data are sent to the display management simulation module through an ARINC429 channel and a network VDN by the meteorological radar simulation unit and the atmospheric data inertial reference system simulation unit; the number of the display management simulation modules is 3. The display management simulation module 1 mainly drives a display unit (main flight display, navigation display, engine warning display, system module information display) of a driving cab. Display management simulation module 2: and a display unit (main flight display and navigation display) for driving the auxiliary driving position. Display management simulation module 3: and the standby simulation module can drive any one of all the display units. The buttons/switches are used to provide discrete signals to the display management emulation module.
The display management simulation module acquires ARINC429 and ARINC453VDN data through the network VDN, acquires SSM (flag/status matrix) values according to ARINC protocol, performs validity check on the received ARINC429 and ARINC453 data, decodes the ARINC data portion and converts the signal into ARINC629 data to be sent to the data processing module (for example, the display management simulation module 1 acquires information required by the driver's side display unit from the ARINC429 data portion and converts the information into ARINC 629) and sends ARINC453 data required by the display unit to the data processing module.
After the data processing module receives ARINC453 and ARINC629 data, the data processing module analyzes and acquires the data according to ARINC453 and ARINC629 protocols. And analyzing the data content in the received ARINC data packet to obtain data driving variables (PV, PF, PC, PN, PR and other variables), and sending the obtained data driving variables to a display unit data driving module. And meanwhile, the parsed data-driven variables are packaged into ARINC629 data and sent to a display management simulation module for other modules to use (the process of using the ARINC629 data by other modules is not involved). ARINC packet data table contents and corresponding drive variables (labels 001 and 203 are examples) are shown in Table 1.
Table 1 ARINC packet data table contents and corresponding drive variable table
Taking chekhdg (check heading) display element as an example, the data processing module logic is as follows:
as shown in Table 1, the 12 th bit of CHECKHDG in the tag 001 packet has a bit number of 1, i.e., the 12 th bit represents CHECKHDG. The last two columns in the table are marked 0 for invalid display and 1 for valid display. The data processing module obtains the value PV_CHECKHDG of the CHECKHDG driving variable according to the table (the variable name is generally consistent with the variable name of the display unit data driving module in the display simulation system).
The specific meaning of the data-driven variables is as follows:
PV: a boolean variable for controlling the validity of the display element;
PF (: shaping variables for controlling the display state of the display elements;
PC: a shaping variable for controlling the color of the display element;
PN: the double-precision floating point variable is used for providing display data, displacement and the like for the display element;
PR: double-precision floating-point variables, typically used to control the rotation of display elements;
the display unit data driving module updates driving variables of all components in real time, and the image processing module uses a model module in the WPF to realize data driving and service logic encapsulation in the view module.
The graphic processing module uses a view module in WPF (display interface) to carry out graphic interface design on each component in 6 display units (a main flight display unit, a navigation display unit, an engine warning display unit, a system module information display unit and the like) of the instrument. Typically, the individual components of each display unit are implemented using a view module. The navigation display unit comprises all components listed in table 2, and each component is used for carrying out position restoration, drawing and variable binding on each element in the component by the view module. And calling each component in the display unit view module so as to realize the display of each display unit.
Table 2 navigation display unit component list
The data driving of each component comes from a display unit data driving module, and the display unit data driving module updates the driving variable of each component in real time. The values of different variables are bound to each display unit component element in the image processing module, so that real-time display of each display unit component element (including whether the element is displayed, the state of the element display, the color of the element display, the numerical value of the element display and the like) is realized. The display module data drives and displays the CHECKHDG (check heading) element in the FWC (flight warning control message) component in the principle navigation display, and each element of the FBMSG component is shown in figure 2. The chekhdg element binding variables and display requirements are shown in table 3.
TABLE 3CHECKHDG element binding variable and display requirement table
The checkhidg element binds the pv_checkhidg variable to control the display of the display element. The display unit data driving module receives the PV_CHECKHDG input by the data processing module, updates the value of the variable PV_CHECKHDG bound to the CHECKHDG element according to the PV_CHECKHDG value input by the data processing module, and the value of the PV_CHECKHDG bound to the element can control whether the CHECKHDG display element in the graphic processing module is displayed or not.
The display unit is used for displaying and presenting the whole flight and aircraft system information required by the crew. The display unit is adjusted by the display name displayed during normal operation, and is divided into main flight display, navigation display, engine warning display and system module information display according to different display functions.
The invention is based on the deep research of the full-motion flight simulator, analyzes and compares the design concept and control logic of the foreign airborne avionics system, and provides the full-motion flight simulator electronic instrument simulation method according to the use operation and principle of the electronic instrument, so that the acquisition, management, analysis and driving of the avionics instrument interface display of the output data of each simulation system of the aircraft are realized. And the real-time data monitoring is used for acquiring and analyzing and simulating various states of each electronic instrument, so that the data of each system is responded quickly and synchronously, and the fidelity of the electronic instrument and the full coverage of training tasks are improved.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other. For the system disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant points refer to the description of the method section.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to assist in understanding the methods of the present invention and the core ideas thereof; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (8)
1. An electronic instrument simulation system of a full-motion aircraft simulator, comprising: a main control computer and an electronic instrument simulation system;
the main control computer is connected with the electronic instrument simulation system through a VDN network;
the main control computer is used for generating electronic flight control simulation data, weather radar simulation data and air data inertial reference system simulation data;
the electronic instrument simulation system is used for generating and displaying a plurality of instrument interfaces according to the electronic flight control simulation data, the weather radar simulation data and the air data inertial reference system simulation data.
2. The electronic instrument simulation system of the full-motion aircraft simulator according to claim 1, wherein the weather radar simulation data is ARINC453 data;
the electronic flight control simulation data and the air data inertial reference system simulation data are ARINC429 data.
3. The electronic instrument simulation system of a full-motion aircraft simulator of claim 1, wherein the master control computer comprises:
the system comprises an electronic flight control simulation unit, a weather radar simulation unit and an atmospheric data inertial reference system simulation unit;
the electronic flight control simulation unit, the weather radar simulation unit and the air data inertial reference system simulation unit are all connected with the VDN network;
the electronic flight control simulation unit is used for generating electronic flight control simulation data;
the weather radar simulation unit is used for generating weather radar simulation data;
the atmosphere data inertial reference system simulation unit is used for generating atmosphere data inertial reference system simulation data.
4. The electronic instrument simulation system of claim 1, wherein the electronic instrument simulation system comprises:
the display management simulation module group and the display simulation subsystem are connected in sequence;
the display management simulation module group is connected with a main control computer through the VDN network; the display management simulation module group is used for acquiring an SSM mark matrix value and an SSM state matrix value according to an ARINC protocol, checking the validity of the received ARINC429 and ARINC453 data based on the SSM mark matrix value and the SSM state matrix value, converting the ARINC429 data into ARINC629 data, transmitting the ARINC629 data to the data processing module, and transmitting the ARINC453 data to the data processing module;
the data processing module is used for analyzing and acquiring data according to ARINC453 and ARINC629 protocols, analyzing and acquiring data driving variables according to the data content in the received ARINC data packet, and transmitting the acquired data driving variables to the display unit data driving module;
the display simulation subsystem is used for analyzing and acquiring data according to ARINC453 and ARINC629 protocols, analyzing and acquiring data driving variables according to the data content in the received ARINC data packet, generating a plurality of instrument interfaces and displaying the instrument interfaces, binding the data driving variables with a plurality of elements of the instrument interfaces, and driving the conversion of the states of each element in the instrument interfaces according to the data driving variables.
5. The system of claim 4, wherein the set of management simulation modules comprises:
the system comprises a first display management simulation module, a second display management simulation module and a third display management simulation module;
the first display management simulation module, the second display management simulation module and the third display management simulation module are all connected with a main control computer through the VDN network; the first display management simulation module, the second display management simulation module and the third display management simulation module are also connected with the display simulation subsystem;
the first display management simulation module is used for analyzing and acquiring ARINC data required by the driving position display unit according to ARINC453 and ARINC429 protocols, analyzing and converting ARINC429 signals into ARINC629 signals according to the received ARINC data content required by the driving position display unit, and sending the ARINC629 signals and the ARINC453 signals to the display simulation subsystem;
the second display management simulation module is used for analyzing and acquiring ARINC data required by the copilot display unit according to ARINC453 and ARINC429 protocols, analyzing and converting ARINC429 signals into ARINC629 signals according to the received ARINC data content required by the copilot display unit, and sending the ARINC629 signals and the ARINC453 signals to the display simulation subsystem;
the third display management simulation module is used for analyzing and obtaining ARINC data required by the standby display unit according to ARINC453 and ARINC429 protocols, analyzing and converting ARINC429 signals into ARINC629 signals according to the received ARINC data content required by the standby display unit, and sending the ARINC629 signals and the ARINC453 to the display simulation subsystem.
6. The electronic instrument simulation system of claim 4, wherein the display simulation subsystem comprises:
the display device comprises a data processing module, a display unit data driving module, a graphic processing module and a display unit group which are connected in sequence;
the data processing module is connected with the display unit data driving module;
the data processing module is used for analyzing and acquiring data according to ARINC453 and ARINC629 protocols, analyzing and acquiring data driving variables according to the data content in the received ARINC data packet, and sending the acquired data driving variables to the display unit data driving module;
the display unit data driving module is used for grouping and packaging driving variables updated in real time according to the data driving business logic; the display unit driving module is also used for sending the data driving variable to the graphic processing module and updating the data of elements in the graphic processing module in batches so as to realize dynamic real-time display of each display unit;
the graphic processing module is used for carrying out graphic interface design on each component in the display unit group and driving each display unit element to display according to the data drive after grouping and encapsulation;
the display unit group is used for displaying according to the graphical interface design and the data driving result.
7. The electronic instrument simulation system of claim 6, wherein the display unit group comprises:
a plurality of display units;
and the display units are connected with the graphic processing module.
8. The full motion aircraft simulator electronic instrument simulation system of claim 4, wherein the system further comprises: a button state acquisition module;
the button state acquisition module is connected with the display management simulation module group;
the button state acquisition module is used for sending discrete signals to the display management simulation module group when the button state is pressed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311043909.0A CN117031984A (en) | 2023-08-18 | 2023-08-18 | Electronic instrument simulation system of full-motion aircraft simulator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311043909.0A CN117031984A (en) | 2023-08-18 | 2023-08-18 | Electronic instrument simulation system of full-motion aircraft simulator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117031984A true CN117031984A (en) | 2023-11-10 |
Family
ID=88633365
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311043909.0A Pending CN117031984A (en) | 2023-08-18 | 2023-08-18 | Electronic instrument simulation system of full-motion aircraft simulator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117031984A (en) |
-
2023
- 2023-08-18 CN CN202311043909.0A patent/CN117031984A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109855651B (en) | Ground test system and test method for modern aircraft radio communication navigation system | |
| CN110531978B (en) | Cabin display system | |
| CN104050332A (en) | Distributed-type real-time comprehensive simulation method of avionics system | |
| JPH10109697A (en) | Aircraft avionic system making use of instruments satisfied by arinc specifications and method enabling communication between instruments per arinc specification 429 and 629 | |
| US20030023740A1 (en) | System and method for operating software in a flight simulator environment | |
| CN104064071A (en) | Small fixed flight training device system | |
| CN112162495A (en) | Inertial navigation simulation system and method based on ARINC429 bus | |
| CN102254465A (en) | Aircraft safety warning system based on virtual technology | |
| CN106991001A (en) | Radionavigation recognizes simulation system | |
| CN110765670B (en) | Helicopter simulator comprehensive display image dynamic generation method | |
| CN105116791A (en) | Comprehensive display control system software framework of small helicopter | |
| CN117031984A (en) | Electronic instrument simulation system of full-motion aircraft simulator | |
| CN212484651U (en) | Flight simulation training system of training plane | |
| Wu et al. | Design and realization of Display Control software in Integrated Avionic system for General Aviation based on the VxWorks | |
| CN109388121A (en) | A kind of flight control computer test device | |
| CN110844114A (en) | Portable aerostat test system | |
| CN110027718B (en) | Touch display control system for large civil aircraft cockpit | |
| CN217008440U (en) | Simulation training platform for function test of integrated avionics system | |
| CN113359124B (en) | Airborne hover indicator | |
| Zheng et al. | Flight simulator architecture development and implementation | |
| CN117993109A (en) | Aircraft simulation system based on aircraft working system design | |
| Balmus | Aircraft Data Acquisition | |
| CN213815087U (en) | Multi-functional simulation training terminal of fixed wing aircraft | |
| CN114927023B (en) | Main navigation system verification system based on airport airspace flight simulation platform | |
| Prevot et al. | Rapid prototyping and exploration of advanced air traffic concepts |
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 |