CN102054380A - Configurable virtual avionic system - Google Patents
Configurable virtual avionic system Download PDFInfo
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- CN102054380A CN102054380A CN2010105907036A CN201010590703A CN102054380A CN 102054380 A CN102054380 A CN 102054380A CN 2010105907036 A CN2010105907036 A CN 2010105907036A CN 201010590703 A CN201010590703 A CN 201010590703A CN 102054380 A CN102054380 A CN 102054380A
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Abstract
The invention relates to the field of avionics, and discloses a configurable virtual avionic system which aims to solve the technical problems of low biofidelity, poor sense of reality, low accuracy, bad positioning effect, unrealizable independent operation and configuration of a single module and the like of a conventional virtual avionic system. A motivating center of the configurable virtual avionic system is respectively connected with a polyfunctional control display unit I and a polyfunctional control display unit II, three data output terminals of the motivating center are respectively connected with a pilot control panel I, a pilot control panel II and a central electronic aviation display, and two data input terminals of the motivating center are respectively connected with two output terminals of a top instrument panel; two data output terminals of an aviation control unit are respectively connected with the input terminal of the pilot control panel I and the input terminal of the pilot control panel II; the pilot control panel I is connected with the output terminal of a main pilot control panel and the output terminal of the polyfunctional control display unit I; and the pilot control panel II is connected with the output terminal of a copilot control panel and the output terminal of the polyfunctional control display unit II.
Description
Technical field
The present invention relates to the avionics field, particularly configurable virtual avionics system.
Background technology
On September 12nd, 2007 is disclosed, publication number is the Chinese patent of CN101034503A, disclose a kind of " light flight simulating device " technology, as the equipment of what comes into a driver's in the display module and out of my cabin, what comes into a driver's has comprised instrument and the guidance panel in the avionics system in its middle deck with the helmet; Realize that with data glove and tracker the concrete operations of hand are mapped to the pseudo operation that shows in the helmet.Though this patent can be simulated instrument and guidance panel in the avionics system with the helmet, fidelity is not high, and the sense of reality is not strong; Come artificial hand's the degree of accuracy of operation not high with data glove and tracker, polarization is bad and these hardware switchs can not be corresponding one by one with operating switch in the true avionics system.The interactivity that can not well simulate between driver and the avionics system though the light flight simulating device that this convenience is used in office has characteristics such as volume is little, in light weight is operated, and can not reach training driver person's purpose well.
On August 27th, 2008 is disclosed, and publication number is the Chinese patent of CN101051959A, discloses a kind of " based on the general-purpose aviation simulator of pseudo operation " technology, and instrument in the avionics system of this patent and guidance panel all are liquid crystal touch screens.Though the virtual switch of this use touch manner can switch to different types flexibly with virtual knob, but practical operation switch and knob can not obtain real force feedback, can not allow like this driver very fast confirm oneself operation from sense of touch, can not well train the driver; And each module independence in the avionics system of this flight simulator is not high, inconvenient trouble shooting and test, independent operating that more can not single module and realize configuration.
There is following shortcoming in the traditional virtual avionics system:
1. fidelity is not high, the sense of reality is not strong;
2. degree of accuracy is not high, polarization is bad;
3. hardware switch can not be corresponding one by one with operating switch in the true avionics system;
4. each module independence is not high, and inconvenient trouble shooting and test also can not realize the independent operating and the configuration of single module.
Summary of the invention
The present invention is intended to solve the traditional virtual avionics system and has that fidelity is not high, the sense of reality is strong, degree of accuracy is not high, polarization is bad, can not realize technical matterss such as the independent operating of single module and configuration, so that a kind of configurable virtual avionics system with characteristics such as modularization, configurable, convenient test, maintenance are simple and easy, system building is rapid, fidelity is high, simulate effect is good to be provided.
The objective of the invention is to be achieved through the following technical solutions.
Configurable virtual avionics system of the present invention, driving center THRUST connects multiple control display unit one MCDU1, multiple control display unit two MCDU2 respectively, three data output terminals of driving center THRUST connect the first input end of driving control panel one EFIS1, first input end and the center electron flight displays ECAM that drives control panel two EFICS2 respectively, and two data input pin connects two output terminals of top instrument panel Over-head Panel respectively; Two data output terminals of flight control unit F CU connect the input end of driving control panel one EFIS1, driving control panel two EFICS2 respectively; Second input end of driving control panel one EFIS1 connects the main output terminal of driving control panel CAPT EFIS Control Panel, and its 3rd input end connects the output terminal of multiple control display unit one MCDU1; The second input end auxiliary connection of driving control panel two EFICS2 is driven the output terminal of control panel F/O EFIS Control Panel, and its 3rd input end connects the output terminal of multiple control display unit two MCDU2.
Configurable virtual avionics system of the present invention is wherein driven control panel one EFIS1, driving control panel two EFICS2, center electron flight displays ECAM, multiple control display unit one MCDU1, multiple control display unit two MCDU2, flight control unit F CU, the main connected mode of control panel CAPT EFIS Control Panel, copilot control panel F/O EFIS Control Panel, top instrument panel Over-head Panel and the center of driving THRUST intermodule of driving all based on ICP/IP protocol.
Configurable virtual avionics system of the present invention is wherein driven control panel one EFIS1 and is made of the basic flight display module one and the navigation flight display module one that connect based on ICP/IP protocol; Driving control panel two EFICS2 is made of the basic flight display module two and the navigation flight display module two that connect based on ICP/IP protocol.
Configurable virtual avionics system of the present invention, wherein center electron flight displays ECAM is made of the UPPER center electron flight displays and the LOWER center electron flight displays that connect based on ICP/IP protocol.
Configurable virtual avionics system of the present invention wherein drives center THRUST and is made of the flight management vectoring computer, full powers mathematics electronic controller and the sound module that connect based on ICP/IP protocol.
The beneficial effect of the virtual avionics system that the present invention is configurable:
1. the human-computer interaction interface of the avionics system of one-piece construction of the present invention and Air Passenger series is identical, and the fidelity height can reach good effect to training driver person;
2. after to real avionics system modularization, simplify the structure, improved the independence of each module, reduced the degree of coupling of intermodule;
3. each module that has configurable property can easily be built the virtual avionics system of Air Passenger series of different demands apace, realizes the purpose of the multiple aircraft cockpit of a cover software high-speed simulation Air Passenger series;
4. realize network service by ICP/IP protocol between each module, reduced the complicacy of virtual avionics system, made things convenient for the fault detect of each module, reduced the maintenance difficulties of each module.
Description of drawings
Fig. 1 logic schematic diagram of the present invention
The number in the figure explanation:
EFIS1 drives control panel one, EFICS2 and drives control panel two, ECAM center electron flight displays, the multiple control display unit one of MCDU1, the multiple control display unit two of MCDU2, FCU flight control unit, CAPT EFIS Control Panel master and drive control panel, F/O EFIS Control Panel copilot control panel, Over-head Panel top instrument panel, THRUST and drive the center
Embodiment
Detailed structure of the present invention, application principle, effect and effect with reference to accompanying drawing 1, are illustrated by following embodiment.
Consult shown in Figure 1, configurable virtual avionics system of the present invention drives center THRUST and connects multiple control display unit one MCDU1, multiple control display unit two MCDU2 respectively, three data output terminals of driving center THRUST connect the first input end of driving control panel one EFIS1, first input end and the center electron flight displays ECAM that drives control panel two EFICS2 respectively, and two data input pin connects two output terminals of top instrument panel Over-head Panel respectively; Two data output terminals of flight control unit F CU connect the input end of driving control panel one EFIS1, driving control panel two EFICS2 respectively; Second input end of driving control panel one EFIS1 connects the main output terminal of driving control panel CAPT EFIS Control Panel, and its 3rd input end connects the output terminal of multiple control display unit one MCDU1; The second input end auxiliary connection of driving control panel two EFICS2 is driven the output terminal of control panel F/O EFIS Control Panel, and its 3rd input end connects the output terminal of multiple control display unit two MCDU2.
Drive control panel one EFIS1, driving control panel two EFICS2, center electron flight displays ECAM, multiple control display unit one MCDU1, multiple control display unit two MCDU2, flight control unit F CU, the main connected mode of control panel CAPT EFIS Control Panel, copilot control panel F/O EFIS Control Panel, top instrument panel Over-head Panel and the center of driving THRUST intermodule of driving all based on ICP/IP protocol.
Driving control panel one EFIS1 is made of basic flight display module PFD (Primary Flight Display) that connects based on ICP/IP protocol and navigation flight display module ND (Navigation Display); Driving control panel two EFICS2 is made of basic flight display module PFD (Primary Flight Display) two that connects based on ICP/IP protocol and navigation flight display module ND (Navigation Display) two.Center electron flight displays ECAM is made of the UPPER center electron flight displays and the LOWER center electron flight displays that connect based on ICP/IP protocol.Driving center THRUST is made of the flight management vectoring computer, full powers mathematics electronic controller and the sound module that connect based on ICP/IP protocol.
After the related data (such as flight planning) that the multiple control display unit MCDU of integrated control and processing capacity obtains flying by its hardware panel identical with multiple control display unit MCDU in the true Air Passenger series aircraft just within it portion handle these data, last aspect feeds back to the hardware panel of oneself and does demonstration, on the other hand relevant data is sent to the PFD and the ND that drive among the control panel EFIS and does corresponding demonstration.The information that obtains from the hardware operation panel in the FCU module (as speed, height above sea level, course etc.) also is sent to the MCDU module and processes correspondence is done in the back in the EFIS module demonstration.The module of THRUST control that has been integrated equally also and processing capacity, handle not only that the input that self obtains from throttle lever is also handled from MCDU and OVER HEAD PANEL in the data that send, to handle data later at last and send the ECAM demonstration to and feed back to MCDU, promptly THRUST is playing the part of the role of core processing.
The MCDU module is made of input control panel and information processing computing machine.The human-computer interaction interface of MCDU in the input control panel of MCDU and the Air Passenger series aircraft driving cabin is identical.The information processing computing machine of MCDU has comprised the database of the global course line of a cover, destination, airport, runway etc., has also comprised the relevant information of Air Passenger series aircraft.When from the input control panel input information of MCDU, the information processing computing machine of MCDU can be done certain storage to these information, such as aloft decision speed V1, cruising altitude, cost index etc.; When from the input control panel input information of MCDU, the information processing computing machine of MCDU can be done certain processing to these information, will and check its correctness in the lane database inquiry of the information processing computing machine of MCDU during such as the ICAO on an airport of input, do invalid input if this airport code correctly also can obtain the data of aspects such as its longitude and latitude, height above sea level, runway and handle.In order to inquire about these data fast, the information processing computing machine of MCDU has also been set up a cover index tabulation.No matter these be store or handle after data all be need be sent to by the information processing computing machine of MCDU show among the EFIS and THRUST in processing again.
The THRUST module is to be made of throttle lever Input Control Element, sound feedback unit and information processing computing machine.Wherein the throttle lever in the throttle lever Input Control Element is all identical with throttle lever shape, size and gear etc. in the Air Passenger series aircraft driving cabin, the sound feedback unit is the then integrated number voice output unit of Air Passenger series aircraft, the data computation that the information processing computing machine then transmits in conjunction with input, MCDU and the OVER HEAD PANEL of throttle lever goes out the various data of aircraft, as near environment speed, height above sea level, course, oil mass and the aircraft etc., send ECAM and MCDU again to and export certain warning sound at last.
Communication between THRUST, MCDU, OVER HEAD PANEL and the ECAM all is based on ICP/IP protocol
The EFIS module is made of independently PFD and ND, and Presentation Function just is unidirectional during with communicating by letter between other modules.
PFD is made of display unit and information processing computing machine.Wherein display unit is identical with PFD display in the Air Passenger series aircraft driving cabin, and the information processing computing machine then is responsible for the acceptance and the processing of data and outputs to display unit doing demonstration.PFD in the virtual avionics system of Air Passenger series aircraft is the integrator of a plurality of instrument of Air Passenger series aircraft, displaying contents is identical with the PFD of true Air Passenger series aircraft with layout, has included contents such as speed, height above sea level, course, flight attitude, offline mode, the indication of instrument land and some warnings.Its medium velocity shows and has comprised that present speed, decision speed, stalling speed, hypervelocity speed, minimum can select speed, new line speed, receive wing flap speed etc.; The flight attitude demonstration has comprised the angle of pitch, yaw angle, roll angle etc.; Offline mode shows auto-throttle, robot pilot, flight director and the instrument land mode of having comprised.
ND also is made of display unit and information processing computing machine, and its display unit is the same with ND in the true Air Passenger series aircraft driving cabin, and the information processing computing machine then is responsible for the acceptance and the processing of data and outputs to display unit doing demonstration.ND has five patterns, mainly the mode with compass has shown the course, has shown the frequency distance of true air speed, ground velocity, wind speed, guidance station with the numerical value mode, has shown destination information with the mode of distinct symbols, mode with line has shown the air route, also has information such as landform weather.
ECAM is display module equally just, be divided into Upper ECAM and Lower ECAM, all be to be made of display unit and information processing computing machine, display unit also is the same with ECAM in the Air Passenger series aircraft driving cabin, and the data of THRUST module are then mainly accepted and handle to the information processing computing machine.
FCU, EFIS CONTROL PANEL and OVER HEAD PANEL then mainly are control actions, all are to be made of with the information processing computing machine and to import control panel all identical with the human-computer interaction interface of respective modules in the Air Passenger series aircraft driving cabin the input control panel.Input control panel such as FCU has knob of modification speed, course, height above sea level etc., EFIS CONTROL PANEL is divided into CAPT and F/O, promptly main the driving and copilot control, the display mode that switches ND, the knob of indication range etc. are arranged, and OVER HEAD PANEL has the switch of power lights in Control Engine, the cabin and button etc.
FCU, EFIS CONTROL PANEL, OVER HEAD PANEL, MCDU and THRUST have control function, promptly all be to constitute, and guidance panel and information processing computing machine are to finish exchanges data by the data line of USB interface by guidance panel and information processing computing machine.
Above-mentioned all modules realize the emulation true to nature of Air Passenger series aircraft driving cabin by can easily building the avionics system of virtual complete Air Passenger series fast based on the network interconnection of ICP/IP protocol.
The transmission of intermodular data is to finish by the information processing computing machine in each module.The information processing computing machine of THRUST is the core processing unit of all modules, be responsible for to handle the data from MCDU and OVER HEAD PANEL module, and output data is processed for MCDU, ECAM and EFIS and shows., through the information processing computing machine of MCDU is sent to information processing computing machine among the THRUST by the network based on ICP/IP protocol after, after the information processing computing machine of THRUST is according to corresponding these data of algorithm process, relevant information is sent to PFD among the EFIS again and shows warnings such as the information of V1 and safe operation of landing flaps and hypervelocity, stall as the V1 (decision speed) that imports in the guidance panel among the MCDU and aircraft weight; The original base of importing in the MCDU guidance panel, destination airport and air route information are sent to flight plan data after the information processing Computer Processing of MCDU in the information processing computing machine of EFIS and THRUST, do corresponding the demonstration and control again after the information processing Computer Processing of EFIS and THRUST respectively.The speed that the input control panel of FCU module obtains, course, height above sea level change information and handle by the information processing Computer Processing that the network based on ICP/IP protocol sends MCDU to after the information processing Computer Processing of FCU module again, transmit corresponding information by MCDU again and show that to EFIS same EFIS CONTROL PANEL also can change display mode and the indication range of ND among the EFIS by network interconnection.
Each module is again configurable, and the low module of these degrees of coupling can independent operating and do not relied on other modules.
The configurable property of these modules is very strong to the adaptability of different demands, when only needing the EFIS module can with other main frames to its provide demonstration related content that data allow PFD and ND to make things convenient for student's emphasis study and grasp flight knowledge in these two instrument, PFD and ND also can independently operate certainly; ECAM also can come out to move to satisfy the cognition of student to aircraft correlation circumstances such as aircraft engine rotating speed, oil mass, flap configuration, undercarriage control situations separately; MCDU equally also can allow the setting operation of student's fam flight plan and aircraft parameter under the situation that does not connect other devices; What other control module more can not be subjected to other limit module allows each button of the actual hands-on of student, switch and knob.Configurable performance like this allows the student well be trained on the program exercising machine of Air Passenger series very easily and the virtual avionics system overall startup of whole Air Passenger series need not have been reduced the specific aim that the complexity of training has more improved training.The independent operating characteristics of module are more suitable for driver's initial stage training like this.
Certainly, because very strong configurable property, these modules more can satisfy to the arbitrary network interconnection flight simulation training under the different situations, are fit to different trainings of driving the student of skill level.
The configurable property of module can also allow each module combinations in the driving cabin between the different type of machines of Air Passenger series in the virtual avionics system of the Air Passenger of this patent series, realized that the configurable software of a cover simulates different Air Passenger series aircraft driving cabin purposes fast, promptly made up Air Passenger series N and overlap different aircraft cockpits and do not need N to overlap that virtual avionics system only needs simply to change modules different in the different type of machines and a whole set of virtual avionics system of training need change of the different type of machines of general flight simulator or flight training device.The design of the configurable property of this patent has been shortened the construction cycle and has been reduced cost of development.
The detection and the investigation of virtual avionics system fault that the configurable property of these modules is more convenient, when finding to be reassembled into complete virtual avionics system very easily with identical module after which module breaks down, emphasis goes to keep in repair the module of being changed, save the malfunction elimination time, reduced the maintenance difficulties of module.
Therefore, adopt configurable virtual avionics system of the present invention, have modularization, configurable, convenient test, a plurality of advantages such as maintenance is simple and easy, system building is rapid, fidelity is high, simulate effect is good.
Claims (5)
1. configurable virtual avionics system, it is characterized in that: driving center (THRUST) connects multiple control display unit one (MCDU1), multiple control display unit two (MCDU2) respectively, three data output terminals at driving center (THRUST) connect the first input end of driving control panel one (EFIS1), first input end and the center electron flight displays (ECAM) of driving control panel two (EFICS2) respectively, and two data input pin connects two output terminals of top instrument panel (Over-head Panel) respectively; Two data output terminals of flight control unit (FCU) connect the input end of driving control panel one (EFIS1), driving control panel two (EFICS2) respectively; Second input end of driving control panel one (EFIS1) connects the main output terminal of driving control panel (CAPT EFIS Control Panel), and its 3rd input end connects the output terminal of multiple control display unit one (MCDU1); The second input end auxiliary connection of driving control panel two (EFICS2) is driven the output terminal of control panel (F/O EFIS Control Panel), and its 3rd input end connects the output terminal of multiple control display unit two (MCDU2).
2. configurable virtual avionics system as claimed in claim 1 is characterized in that: described driving control panel one (EFIS1), drive control panel two (EFICS2), center electron flight displays (ECAM), multiple control display unit one (MCDU1), multiple control display unit two (MCDU2), flight control unit (FCU), the main control panel (CAPT EFIS Control Panel) of driving, copilot control panel (F/O EFIS Control Panel), the connected mode of top instrument panel (Over-head Panel) and driving center (THRUST) intermodule is all based on ICP/IP protocol.
3. configurable virtual avionics system as claimed in claim 1 is characterized in that: described driving control panel one (EFIS1) is made of the basic flight display module one and the navigation flight display module one that connect based on ICP/IP protocol; Driving control panel two (EFICS2) is made of the basic flight display module two and the navigation flight display module two that connect based on ICP/IP protocol.
4. configurable virtual avionics system as claimed in claim 1 is characterized in that: described center electron flight displays (ECAM) is made of the UPPER center electron flight displays and the LOWER center electron flight displays that connect based on ICP/IP protocol.
5. configurable virtual avionics system as claimed in claim 1 is characterized in that: described driving center (THRUST) is made of the flight management vectoring computer, full powers mathematics electronic controller and the sound module that connect based on ICP/IP protocol.
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| CN2010105907036A CN102054380A (en) | 2010-12-16 | 2010-12-16 | Configurable virtual avionic system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103475522A (en) * | 2013-09-10 | 2013-12-25 | 中国民航大学 | Device and method for airplane centralized maintenance system simulation |
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| US6895582B1 (en) * | 2000-09-11 | 2005-05-17 | Rockwell Collins | Method and apparatus for high assurance computing using virtual machines on general purpose computing resources |
| CN101251959A (en) * | 2008-02-04 | 2008-08-27 | 于辉 | General-purpose aviation simulator based on virtual operation |
| CN101976278A (en) * | 2010-09-29 | 2011-02-16 | 南京信息工程大学 | Virtual reality technique-based airplane landing aid system and method thereof |
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| US5541863A (en) * | 1994-09-30 | 1996-07-30 | Rockwell International | Virtual integrated software testbed for avionics |
| US6895582B1 (en) * | 2000-09-11 | 2005-05-17 | Rockwell Collins | Method and apparatus for high assurance computing using virtual machines on general purpose computing resources |
| CN101251959A (en) * | 2008-02-04 | 2008-08-27 | 于辉 | General-purpose aviation simulator based on virtual operation |
| CN101976278A (en) * | 2010-09-29 | 2011-02-16 | 南京信息工程大学 | Virtual reality technique-based airplane landing aid system and method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103475522A (en) * | 2013-09-10 | 2013-12-25 | 中国民航大学 | Device and method for airplane centralized maintenance system simulation |
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Application publication date: 20110511 |